document title / titre du document TRP W ORK PLAN ... - emits - ESA
document title / titre du document TRP W ORK PLAN ... - emits - ESA document title / titre du document TRP W ORK PLAN ... - emits - ESA
document title / titre du document TRP WORK P LAN 2005 – 2007 C OMPLETE L IST OF A CTIVITIES prepared by/préparé par TRP Management Office reference/réference TEC-SB/7935/dc issue/édition 1 revision/révision 0 date of issue/date d’édition 12/02/2009 status/état 31/12/2008 Document type/type de document Information Note Distribution/distribution a TEC-SB_7935_TRP2008-2010
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<strong>document</strong> <strong>title</strong> / <strong>titre</strong> <strong>du</strong> <strong>document</strong><br />
<strong>TRP</strong> W<strong>ORK</strong> P LAN 2005 – 2007<br />
C OMPLETE L IST OF A CTIVITIES<br />
prepared by/préparé par<br />
<strong>TRP</strong> Management Office<br />
reference/réference<br />
TEC-SB/7935/dc<br />
issue/édition 1<br />
revision/révision 0<br />
date of issue/date d’édition 12/02/2009<br />
status/état 31/12/2008<br />
Document type/type de <strong>document</strong> Information Note<br />
Distribution/distribution<br />
a<br />
TEC-SB_7935_<strong>TRP</strong>2008-2010
s<br />
<strong>TRP</strong> W<strong>ORK</strong><strong>PLAN</strong> 2008-2010<br />
Complete Llist of Activities<br />
issue 1 revision 0 -<br />
3page ii of iii<br />
APPROVAL<br />
Title<br />
Titre<br />
<strong>TRP</strong> Work Plan 2005-2007 – Complete List of Activities<br />
issue<br />
issue<br />
revision<br />
revision<br />
author<br />
auteur<br />
<strong>TRP</strong> Management Office<br />
date<br />
date<br />
10/02/2009<br />
approved by<br />
approuvé par<br />
date<br />
date<br />
CHANGE LOG<br />
reason for change /raison <strong>du</strong> changement issue/issue revision/revision date/date<br />
CHANGE RECORD<br />
Issue: Revision:<br />
reason for change/raison <strong>du</strong> changement page(s)/page(s) paragraph(s)/paragraph(s)
s<br />
<strong>TRP</strong> W<strong>ORK</strong><strong>PLAN</strong> 2008-2010<br />
Complete Llist of Activities<br />
issue 1 revision 0 -<br />
3page iii of iii<br />
T A B L E O F C O N T E N T S<br />
1 INTRODUCTION<br />
2 COMPLETE LIST OF ACTIVITIES<br />
3 DESCRIPTION OF ACTIVITIES
s<br />
<strong>TRP</strong> W<strong>ORK</strong><strong>PLAN</strong> 2005-2007<br />
Complete List of Activities<br />
issue 1 revision 0<br />
page 1 of 5<br />
1 INTRODUCTION<br />
This information note presents the complete list of activities that constitute the <strong>TRP</strong> 2005-2007<br />
work plan cycle, their status and descriptions.<br />
The <strong>document</strong> is structured as follows:<br />
Chapter 1, Intro<strong>du</strong>ction<br />
Chapter 2 includes tables listing all activities divided by following Service Domains:<br />
1. Technologies related to Earth Observation<br />
2. Technologies related to Science<br />
3. Technologies related to Human Spaceflight Manned Exploration<br />
4. Technologies related to Space Transportation & Re-entry Technologies<br />
5. Technologies related to Telecommunication / Navigation<br />
6. Generic Technologies and Techniques<br />
and provides following information:<br />
IPC Approval:<br />
Status:<br />
Budget:<br />
.<br />
Status of approval of the corresponding procurement proposal.<br />
(YXXXX= Year of approval for workplan activities previously<br />
endorsed & corresponding procurement proposals approved, if<br />
applicable.<br />
Proposed: Not yet approved/submitted to AC/IPC<br />
Intended: Approved by IPC but not committed yet<br />
Contracted: Contract signed<br />
Closed: Contract closed, all deliverables received<br />
Deleted: Removed from work plan<br />
Deferred: Previously approved but postponed<br />
Budget planned for this activity. Total Contract Authorisation (CA)<br />
values, given in KEURO, at yearly economic conditions.
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Procurement Policy:<br />
C<br />
= Open Competitive Tender; (Ref. Article 5.1 <strong>ESA</strong> Contract<br />
Regulations).<br />
C(1)* = Activities in open competition limited to the non-Large-System<br />
Integrators.<br />
Note: In these activities, LSIs are not allowed to submit prime<br />
proposals to <strong>ESA</strong>. LSIs can participate as subcontractors. In this<br />
case, the proposal must demonstrate that:<br />
- the tasks assigned to the LSI do not constitute the core<br />
activities of the proposed development;<br />
- The technical expertise provided by the LSI is essential to the<br />
activity;<br />
- the non-LSI in the team retains the key capabilities to develop<br />
and exploit the results of the technology activity;<br />
- the presence of the LSI in the proposal does not<br />
undetermined or limit the leading role of the non-LSI in the<br />
team.<br />
(Otherwise, the bid will not be considered for further evaluation).<br />
C(2)* = Activities in open competition, where a significant participation<br />
of non-Large-System Integrators is requested.<br />
Note: These activities are open to all potential bidders, LSIs and<br />
non-LSIs. However, LSIs that submit bids are requested to<br />
include in those bids a relevant participation of non-LSIs, in<br />
quality and quantity, in accordance with the ITT guidelines - in<br />
the form of a percentage range of expected participation of non-<br />
LSIs – on which the C(2) measure is applied. (Otherwise, the bid<br />
will not be considered for further evaluation).<br />
C(3)* = Activity restricted to SMEs & R&D organisations, preferably in<br />
cooperation.<br />
The measure is proposed when the technology activity relates to<br />
early phases of the technology development (TRL
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<strong>TRP</strong> W<strong>ORK</strong><strong>PLAN</strong> 2005-2007<br />
Complete List of Activities<br />
issue 1 revision 0<br />
page 3 of 5<br />
(judged in terms of quantity indicated as guidelines of the ITT on<br />
which the C(4) measure is applied). Offers shall provide an<br />
analysis of the potential advantages of the proposed<br />
participation (e.g. long-term rospects for future work). If no such<br />
participation is offered, the bid shall contain evidence of the<br />
effort made to meet these requirements and the reasons for the<br />
lack of success. (Otherwise, the bid will not be considered for<br />
further evaluation).<br />
C(R) = Competition is restricted to a few companies, indicated in the<br />
"Remarks'' column; (Ref. Article 5.2 <strong>ESA</strong> Contract Regulations).<br />
DN/S = Direct Negotiation/Specialisation; the contract will be awarded<br />
by direct negotiation in implementation of a defined in<strong>du</strong>strial<br />
policy or resulting from a sole supplier situation (Ref. Articles<br />
6.1.A,D,F <strong>ESA</strong> Contract Regulations).<br />
DN/C = Direct Negotiation/Continuation; the contract will be awarded in<br />
direct negotiation being the immediate continuation of a previous<br />
activity with the same contractor (Ref. Article 6.1.C <strong>ESA</strong><br />
Contract Regulations)<br />
Country:<br />
Remarks:<br />
Prime contractor country<br />
Provides information on Prime contractor and sub-contractors in case the<br />
activity is contracted or gives other additional info.<br />
Chapter 3 provides the descriptions of the activities. The Technology Activity Template provide<br />
following information:<br />
Description:<br />
Deliverables:<br />
Current TRL:<br />
Target TRL:<br />
Describes the activity, providing the context information, the purpose of<br />
the activity and the main tasks.<br />
Provides short description of the tangible outcome e.g. breadboard,<br />
demonstrator, S/W, test data. A final report is standard for every<br />
activity.<br />
Describes the current NASA TRL level of the pro<strong>du</strong>ct that is going to be<br />
developed in this activity.<br />
The NASA TRL level expected for the pro<strong>du</strong>ct at the end of the activity.<br />
For equipments <strong>TRP</strong> usually concludes with TRL 3, GSTP at level 5/6.<br />
However in the case of components target TRL level in <strong>TRP</strong> could be<br />
higher. It is also understood that TRL levels do not apply to S/W and tools.
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For these cases description of SW quality, i.e: architecture, beta version,<br />
prototype, or full operational, achieved at the end of the activity.<br />
Application Need/Date:<br />
Describes the required TRL level and date for the technology development<br />
of which the respective activity is part of on the base of the maturity<br />
required by the application. The general rule is that a requirement specifies<br />
the need date for a pro<strong>du</strong>ct. For equipments/payloads this is in general<br />
TRL 5/6, - the level generally required for Phase B of a project. The<br />
exceptions are components, where TRL 8 (flight readiness) should be<br />
achieved. For S/W and tools separate readiness levels are defined below<br />
Application/Mission: Describes the first possible mission/application/follow-on and the flight<br />
date.<br />
Technology Readiness Level, as stated by NASA, to be achieved at end of the activity for<br />
TRL1 - Basic principles observed and reported<br />
TRL2 - Technology concept and/or application formulated<br />
TRL3 - Analytical and experimental critical function and/or characteristic proof-of-concept<br />
TRL4 - Component and/or breadboard validation in laboratory environment<br />
TRL5 - Component and/or breadboard validation in relevant environment<br />
TRL6 - System/subsystem model or prototype demonstration in a relevant environment (ground<br />
or space)<br />
TRL7 - System prototype demonstration in a space environment<br />
TRL8 - Actual system completed and "flight qualified" through test and demonstration (ground<br />
or space)<br />
TRL9 - Actual system "flight proven" through successful mission operations<br />
Readiness Levels for S/W and tools<br />
Algorithm Single algorithms are implemented and tested to allow their characterisation<br />
and feasibility demonstration.<br />
Prototype A subset of the overall functionality is implemented to allow e.g. the<br />
demonstration of performance.<br />
Beta Version Implementation of all the software (software tool) functionality is complete.<br />
Verification & Validation process is partially completed (or completed for<br />
only a subset of the functionality).<br />
S/W Release Verification and Validation process is complete for the intended scope. The<br />
software (software tool) can be used in an operational context.
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Complete List of Activities<br />
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TECHNOLOGY R&D<br />
Research & feasibility<br />
demonstration<br />
CAT. A<br />
predevelopment<br />
prequalification<br />
Innovative/Prospective<br />
Technology<br />
T.R.L. 1-2<br />
<strong>TRP</strong><br />
Support to Programmes &<br />
Generic Technologies<br />
T.R.L. 3 T.R.L. 4 and/or T.R.L. 5<br />
CAT. B<br />
Support to In<strong>du</strong>stry’s<br />
Competitiveness<br />
(Short Term)<br />
T.R.L. 4 and/or T.R.L. 5<br />
CAT. C<br />
<strong>ESA</strong> Technology Landscape (NASA TRL's)<br />
Contract Duration:<br />
Dossier 0 Reference:<br />
SW clause applicability:<br />
Duration of the activity (e.g. 24 month)<br />
Identifies the related Dossier 0 (ESTER) Requirement<br />
Special approval is required for activities labelled:<br />
either “Operational Software” or “Open Source Code”,<br />
for which the Clauses/sub-clauses 42.8 and 42.9 (“Operational<br />
Software”) and 42.10 and 42.11 (“Open Source Code”) of the<br />
General Clauses and Conditions for <strong>ESA</strong> Contracts (<strong>ESA</strong>/C/290,<br />
rev.6), respectively, are applicable.<br />
Consistency with Harmonisation Roadmap and Conclusions:<br />
Consistency with any related Harmonisation Roadmap or Dossier or<br />
Conclusion report, if applicable.
f<br />
Chapter 2<br />
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.1 - Data exploitation<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T101-07GD Image Information Mining 1200<br />
C(1) /<br />
C(4)<br />
I<br />
ACS, U. Trento + SARMAP (CH) +<br />
CNES (F) + DLR (D)<br />
- Contracted 20433<br />
Y2004 T101-08GD Mission Planning for Constellations and Multi-use 400 C F EADS-Astrium - Contracted 19480<br />
Y2004 T101-09GD EO data archives: Improved access and presentation 400 C(4) - Intended<br />
Total 1.1 - Data exploitation 400 1,200 400<br />
Page 1 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.2 - Microwave Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T102-01EE Multi-frequency feeds for Earth Observation applications 300 C F EADS-Astrium, IEEA - Contracted 20158<br />
Y2006<br />
T102-03EE<br />
Rigorous numeric techniques applied to microwave interaction with natural targets:<br />
volume scattering<br />
150 C F Cert/Onera, Noveltis<br />
Open Source<br />
Code<br />
Contracted 20449<br />
Y2004 T102-04EE KU Band SAR Snow Measurements for Snow Applications 150 C(1) A<br />
ENVEO + VEXCEL (GB) + U.<br />
Helsinki (Fin) + Noveltis (F)<br />
- Contracted 18668<br />
Y2004 T102-04EE KU Band SAR Snow Measurements for Snow Applications 135 C(1) N NORUT - Contracted 18595<br />
Y2006 T102-05ET Microwave Photonics Millimetre-wave Generation 250 C F<br />
TRT + Un. Duisburg (D) + Thales<br />
Sys (F)<br />
- Contracted 21615<br />
Y2004 T102-07ET P-Band Ice Sounding Radar Demonstrator Development 300 C(2) TU Denmark - Contracted 19307<br />
Y2006 T102-10ET GaN Highly Efficient HPA for X- and Ku-band SAR and Altimeter Applications 450 C I<br />
Thales Alenia Space +<br />
UMS(D)+Thales Alenia<br />
Space(F)+Thales<br />
Detexis(F)+Un.Bologna(I)<br />
- Contracted 21796<br />
Y2006<br />
/<br />
Y2007<br />
T102-11ET GaN Self Protected LNA for X- and ku-band Radar Applications 350 C UK Budget increased // Qinetiq - Contracted 21794<br />
Page 2 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.2 - Microwave Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T102-12EE Innovative Low-loss FSS structures 450 17 C(1) UK RAL, Astrium, U. Belfast - Contracted 19854<br />
Y2006 T102-14ET LNAs for mm-waves 350 C Fin<br />
DA Design + FHG (D) + Millilab<br />
(Fin)<br />
- Contracted 21710<br />
Y2006 T102-16ET HBV multipliers for high power and high frequency 350 C S<br />
Wasa Millimeteer, Un.<br />
Chalmers+Astrium (D)<br />
- Contracted 21172<br />
Y2006 T102-17ET Integrated Schottky structures 400 C D ACST+RPG(D) - Contracted 21628<br />
Y2006 T102-18ET New Investigations of RF breakdown in microwave transmission lines 250 C(1) E<br />
Aurora Safety & Testing, Un. Polit.<br />
Cartagena, RYMSA + EPFL (CH)<br />
Open Source<br />
Code<br />
Contracted 20007<br />
Y2006 T102-22ET Active calibration for radiometers 200 C F Astrium, LAAS - Contracted 21313<br />
Y2006 T102-23EE P-band SAR wave interaction and information retrieval 200 C(3) F<br />
Un. P. Sabatier, Cert/Onera + DLR<br />
(D) + Un. Wageningen (NL) + Un.<br />
Chalmers (S)<br />
- Contracted 20290<br />
Y2005 T102-28ET Development Schottky MMICs for high frequencies 475 C(1) IRL<br />
Farran Technology, Tydal + UMS<br />
(F)<br />
- Contracted 20206<br />
Page 3 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.2 - Microwave Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2005 T102-28ET Development Schottky MMICs for high frequencies 430 8 C(1) UK<br />
RAL, Un. Bath + Observatoire de<br />
Paris, EADS-Astrium (F)<br />
- Contracted 20223<br />
Y2004 T102-29ET Active Receive-Only Digital Front-End for Radar and SAR - Phase 1 & 2 700 60 DN/S D EADS-ASTRIUM + Subco - Contracted 19468<br />
Y2004 T102-30EE Next Generation L/S band SSPA Demonstrator for Radar 350 C(2) F<br />
Alcatel + Un. Limonge, Amcad<br />
Engineering, UMS<br />
- Contracted 19127<br />
Y2006 T102-32EE Understanding directionality in surface scattering by imaging radar 150 C(1) CH<br />
Gamma Rem Sensing + CNR (I) +<br />
Un. Munchen (D)<br />
- Contracted 21659<br />
Y2006 T102-41ET Altimetric Measurements of 2D Ocean Surface Currents 150 C E<br />
Starlab<br />
Barcelona+Ifremer(F)+Astrium(UK)<br />
- Contracted 21300<br />
Y2006 T102-43ET Integrated Receiver and ADC for Active Array SAR 400 C Fin<br />
VTT + DA-Design (Fin) + TU<br />
Helsinki (Fin)<br />
- Contracted 21673<br />
Y2006 T102-44ET Research into GPS Sea-Ice and Dry Snow Reflectometry 300 C(3) E<br />
IEEC + GFZ (D) + IFAC (I) + AD<br />
Telecom (E)<br />
- Contracted 21793<br />
Y2006 T102-45ET Advanced SAR-Instrument based on Digital Beamforming 150 C D Astrium, DLR+TU Denmark (DK) - Contracted 21079<br />
Page 4 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.2 - Microwave Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T104-17EE<br />
Bio- & geo-physical retrieval algorithm definition for active remote sensing of land<br />
surfaces at P- and L-band<br />
200 C(3) D<br />
DLR+Onera (F)+SARVision<br />
(NL)+AEL Consultants<br />
(UK)+Un.Wales<br />
- Contracted 21131<br />
Total 1.2 - Microwave Instruments 285 1,350 2,255 858 2,927<br />
Page 5 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.2.1 - Microwave Equipment & Antennas (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2001 ETM-157 HBV devices 200 DN/S F U. Lille - Contracted 18164<br />
Y2002 ETP-111 Novel Simulation Interferometric radar altimeter 150 C(1)<br />
CLS, Alcatel, Boots Technologies<br />
+ Starlab Barcelona (E)<br />
- Contracted 18764<br />
Y2000 ETP-137 PARIS: additional work 50 C UK<br />
Astrium - C under prime for<br />
ETP-137A<br />
- Contracted 16110<br />
Y2000 ETP-137.A PARIS Technology Concept Definition/Integration - Phase 2 242 400 DN/C UK Astrium - Contracted 16110<br />
Y2000 ETP-137.B PARIS multi-beam array 300 C UK<br />
Astrium - C under prime for<br />
ETP-137A<br />
- Contracted 16110<br />
Y2000 ETP-137.C Beam Forming Networks for PARIS Concept 500 C UK<br />
Astrium - C under prime for<br />
ETP-137A<br />
- Contracted 16110<br />
Y2000 ETP-137.D PARIS Receiver and Signal Processor 500 C UK<br />
Astrium - C under prime for<br />
ETP-137A<br />
- Contracted 16110<br />
Y2002 ETP-153 New Radiometer concepts: Active Cold Load for Radiometer Calibration 300 C(2) Fin Ylinen +TUD (DK) - Contracted 18907<br />
Page 6 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.2.1 - Microwave Equipment & Antennas (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003 ETP-163.C L-Band Radiometry / Advanced Filter and Correlator integration and validation 590 120 DN/C E CASA, UPCA + U. Hel. (Fin) - Contracted 15138<br />
Y2002 ETP-190 Mo<strong>du</strong>lar Signal Generation and Detection for Future SAR Instruments 300 C(2) UK<br />
Com Dev Europe + SEA (UK).<br />
Only 100kE committed, owing to<br />
contract closure.<br />
- Contracted 18492<br />
Total 1.2.1 - Microwave Equipment & Antennas (Source: <strong>TRP</strong><br />
2000-2003)<br />
1,482 2,000 170<br />
Page 7 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.3 - Optical Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T103-01FP High efficient Laser Pump Source for LIDAR Applications 600 C(1) I CESI, GA, Scimex - Contracted 18949<br />
Y2004 T103-02FP Pulsed laser source in NIR for LIDAR applications 300 C(1) F Onera, LMD + NEO (N) + CSIC (E) - Contracted 19813<br />
Y2004<br />
T103-03M<br />
M<br />
NIR Detector for LIDAR Applications 400 C(1) UK<br />
SSTL, U. Heriott-Watt, U.<br />
Sheffield, Hovemere<br />
- Contracted 19816<br />
Y2006<br />
/<br />
Y2007<br />
T103-10GD Back-illuminated thinned CMOS imager focal plane 500 C(2)<br />
Increased budget, 500kE <strong>TRP</strong> +<br />
300kE EO<br />
- Intended<br />
Y2006<br />
T103-11EE<br />
Enhanced Quantum Well Infrared Photodetector (QWIP) Array Detector: Definition<br />
and optimisation<br />
750 C(1) F<br />
Alcatel Thales III<br />
Vlab+IMEC(B)+Astrium(F)<br />
- Contracted 21248<br />
Y2004<br />
T103-13M<br />
M<br />
L3CCD/EMCCD Technology for LIDAR Applications 300 DN/S UK<br />
EEV, 500kE to be funded by<br />
EOEP; see <strong>ESA</strong>/IPC(2004)1,<br />
add.23<br />
- Contracted 19152<br />
Y2004 T103-16FP Ultra-compact medium-resolution spectrometer for land application 570 DN/C I<br />
GA, ENEA + E2V (UK) + Ecole<br />
Nat. Sup. Phys. (F)<br />
- Contracted 20401<br />
Y2006<br />
T103-24M<br />
M<br />
Next Generation panchromatic detectors 800 C(2) - Intended<br />
Page 8 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.3 - Optical Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T103-25M<br />
M<br />
Reliable space-compatible pump laser diodes 800 C F Nuvonyx + Osram - Contracted 20529<br />
Y2006<br />
T103-25M<br />
M<br />
Reliable space-compatible pump laser diodes 770 C UK Intense - Contracted 20642<br />
Y2006<br />
T103-26M<br />
M<br />
Laser interferometry high-precision tracking for LEO 400 C I<br />
Alenia Spazio + Ist. Metr.<br />
Colonnetti<br />
- Contracted 20512<br />
Y2006<br />
T103-27M<br />
M<br />
Large format APS detectors with on-chip intelligence for lightning imaging 600 C(2) F<br />
Astrium + Inst Sup Aeronautique et<br />
Espace (F)+SSTL(UK)<br />
- Contracted 21856<br />
Y2006<br />
T103-28M<br />
M<br />
High Energy Fiber-based Laser and Receiver development in the 2 micron region for<br />
atmospheric CO2 and other greenhouse gases measurements<br />
600 C(1) UK<br />
Qinetic+Crystal Fibre<br />
(DK)+NPL(UK)<br />
- Contracted 21921<br />
Y2006<br />
T104-13M<br />
M<br />
Instrument technology for fluorescence 300 C UK<br />
ABSL Space Pro<strong>du</strong>cts +<br />
Astrium(F)+Lidar<br />
Technologies(UK)<br />
- Contracted 22124<br />
Y2006 T104-15EE Vegetation Fluorescense Retrieval Algorithm 200 C D<br />
FLEX Mission. GFZ Postdam +<br />
Un.Polit.Vanlencia (E) + NLR (NL)<br />
- Contracted 20882<br />
Y2006<br />
T104-16M<br />
M<br />
Non-linear Laser Crystal Development for Frequency Conversion 400 C(1) D DLR + IHB (D) - Contracted 21747<br />
Page 9 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.3 - Optical Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T104-18EE<br />
Aerosol modeling and synergetic aerosol correction algorithms for passive optical/IR<br />
sensors<br />
200 C(3) NL<br />
Argoss+Un.Bremen (D)+Finnish<br />
Meteorological Institute (FIN)<br />
- Contracted 21107<br />
Y2006 T104-20QC SWIR Laser Diodes 200 C E Tecnologica - Contracted 21957<br />
Total 1.3 - Optical Instruments 900 2,470 1,170 4,150<br />
Page 10 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.4 - Platforms/ Other Instruments<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T104-02EE Very large space antenna aperture - architecture trade off 300 C F Alcatel + Kayser Threde (D) - Contracted 20392<br />
Y2004 T104-02EE Very large space antenna aperture - architecture trade off 300 C UK<br />
Astrium, Vexcel, U. Cambridge,<br />
BAE<br />
- Contracted 20393<br />
T104-07MC Array Antenna Based on Inflatable Technology<br />
C<br />
350kE. Postponed after<br />
T104-02EE.<br />
- Deferred<br />
Y2005<br />
T104-11FP<br />
Autonomous High Data Rate Secured Downlink System - Breadboard (Old <strong>title</strong>: High<br />
Data Rate Downlink Data Processor Chain – Breadboard)<br />
400 C - Intended<br />
Total 1.4 - Platforms/ Other Instruments 600 400<br />
Page 11 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.4.1 - Lidar (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 EEO-003 Solid State Phase Conjungation 600 C F<br />
Thales. Combined with<br />
T-M-QCA-08-04<br />
- Closed 18284<br />
Y2001<br />
T-M-QCA-0<br />
8-04<br />
Radiation testing and evaluation for Core Laser Technologies (CHOCOLATE) 200 C(1) F<br />
Thales Research & Technology +<br />
CEN(B), Univ. Liege (B).<br />
Combined with EEO-003<br />
- Contracted 18284<br />
Total 1.4.1 - Lidar (Source: <strong>TRP</strong> 2000-2003) 800<br />
Page 12 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.4.2 - Instruments and Sensor Breakthrough (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 EEA-044 Geo Atmospheric Sounder Ph.1 500 C(2) D EADS + Tikra(DK) + RAL(UK) - Closed 17924<br />
Y2002 EEA-044 Geo Atmospheric Sounder Ph.1 500 C(2) S Omnisys, Saab - Closed 17923<br />
Y2002 EEA-044 Geo Atmospheric Sounder Ph.2A 1400 DN/C S Omisys, Saab - Contracted 19449<br />
Y2002 EEA-044 Geo Atmospheric Sounder Ph.2B 1100 DN/C S Omisys, Saab - Contracted 19449<br />
Total 1.4.2 - Instruments and Sensor Breakthrough (Source: <strong>TRP</strong><br />
2000-2003)<br />
1,000 1,400 1,100<br />
Page 13 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.4.3 - Earth Observation P/L (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 MME-003<br />
Laser-cooled Atom Sensor for Ultra-High-Accuracy Gravitational Acceleration and<br />
Rotation Measurements<br />
147 C(1) D U. Hannover - Contracted 18330<br />
Y2002 MMO-624 Advanced LIDAR concepts 200 C I C. Gavazzi, INFR, INOA - Contracted 18944<br />
Total 1.4.3 - Earth Observation P/L (Source: <strong>TRP</strong> 2000-2003) 347<br />
Page 14 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.4.4 - Payload Data Exploitation (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
PDE-KEO-<br />
001<br />
Knowledge Centred Earth Observation - Phase 1 700 C I<br />
ACT + DLR (D) +CNES (F) + GDT<br />
(E)<br />
- Contracted 18345<br />
Y2003<br />
PDE-KEO-<br />
001<br />
Knowledge Centred Earth Observation - Phase 2 600 DN/C I<br />
ACT + DLR (D) +CNES (F) + GDT<br />
(E)<br />
- Contracted 18345<br />
Y2002<br />
PDE-User-<br />
05.B<br />
Multiple Image Registration - MIR 150 DN/S N Norwegian Comp. (follow-on) - Contracted 18341<br />
Total 1.4.4 - Payload Data Exploitation (Source: <strong>TRP</strong> 2000-2003) 850 600<br />
Page 15 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.1 - Missions in Development Phase: BEPI-COLOMBO<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T201-02M<br />
M<br />
Development of microlasers for laser altimetry on future planetary orbiters 650 C(1) D Zeiss Optronik - Contracted 19351<br />
Y2004<br />
/<br />
Y2007<br />
T201-03SC Breadboard & Demonstrator of a Micro-pore Optics 550 74<br />
C(1) +<br />
DN/C<br />
F<br />
Photonis + Un. Leicester (UK) +<br />
Cosine Research (NL)<br />
- Contracted 19371<br />
Y2004 T201-04SC Scintillator sensor development 600 DN/S NL<br />
Consortium led by Cosine<br />
Research (NL) + 500K€ CTP<br />
- Contracted 19161<br />
Y2004 T201-06SC Active Pixel Sensor Focal Plane Assembly for NIR 547 C(1) F Sofradir - Contracted 19606<br />
Y2004<br />
/<br />
Y2007<br />
T201-06SC Active Pixel Sensor Focal Plane Assembly for NIR - Additional work 150 DN/C F<br />
Sofradir. Equally cofunded <strong>TRP</strong> +<br />
CTP (SCI).<br />
- Contracted 19606<br />
Total 2.1 - Missions in Development Phase: BEPI-COLOMBO 2,347 74 150<br />
Page 16 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.2 - Missions in Pre-Assessment Phase: Darwin<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 MMO-630 High Precision Optical Metrology 700 DN/C F<br />
Astrium (F) +Astrium (D) + TNO<br />
(NL)<br />
- Contracted<br />
T203-02ES Formation Flying Control and Avionics<br />
Postponed, awaiting System Study<br />
results. 500 K€<br />
- Deferred<br />
Y2005<br />
T203-06M<br />
M<br />
Passive optical components for interferometry 1,500 C(2) - Intended<br />
Y2004<br />
T203-08MC Solid cryogen cryostat<br />
Postponed, awaiting System Study<br />
results. 500 K€<br />
- Deferred<br />
Y2006 T203-09SC Wavefront tilt sensor 500 C(2) - Intended<br />
Y2005<br />
T203-11M<br />
M<br />
Integrated optics 1000 C F<br />
Thales Alenia Space + INIST (F) +<br />
LVC (F) + In. Charles Gerhard (F)<br />
+ Inst. Nationale Polytechnique<br />
Grenoble (F)<br />
- Contracted 20742<br />
Y2004 T203-13SC Pressure Regulator for Cold Gas Micropropulsion C<br />
Postponed, awaiting System Study<br />
results. 750 K€<br />
- Deferred<br />
T203-16M<br />
M<br />
Development of compact absolute distance metrology system C(2) 500kE. Postponed - Deferred<br />
Page 17 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.2 - Missions in Pre-Assessment Phase: Darwin<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
T203-17M<br />
M<br />
Fibre coupled acousto-optical mo<strong>du</strong>lator C(1) 500kE. Postponed - Deferred<br />
T203-18MP Formation Flying electric propulsion system 1,400 C Postponed awaiting system study. - Deferred<br />
Y2006<br />
T203-19M<br />
M<br />
FIR linear Detector Array 2,000 C(1) Phased Activity - Intended<br />
Y2006<br />
T203-20M<br />
M<br />
Single mode waveguide 1000 C D+NL<br />
Change in PP. Astrium + Fibre<br />
Photonics (UK)<br />
- Contracted 20915<br />
Y2006<br />
T203-20M<br />
M<br />
Single mode waveguide 1000 C NL<br />
Change in PP. TNO+LVC(F)+Un.<br />
Southampton(UK)<br />
- Contracted 20914<br />
Total 2.2 - Missions in Pre-Assessment Phase: Darwin 3,700 5,400<br />
Page 18 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.2.1 - Darwin (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003 EEO-048 BiB detector 350 35 C B IMEC + Alcatel (F) - Contracted 18599<br />
Y2001 MMO-632 Fiber optical wavefront filtering 500 36 C(2) N<br />
Kongsberg + Alcatel, Onera (F) +<br />
Sintef (N)<br />
- Contracted 18772<br />
Y2001 MMO-632 Fiber optical wavefront filtering ph.1 100 C(2) CH<br />
Contrvaves + Astrium, U. Stuttgard<br />
(D) + U. Wien (A) + TNO (NL)<br />
- Contracted 18773<br />
Y2001 MMO-632 Fiber optical wavefront filtering Ph.2 400 C(2) CH<br />
Contrvaves + Astrium, U. Stuttgard<br />
(D) + U. Wien (A) + TNO (NL)<br />
- Contracted 18773<br />
Y2003/<br />
Y2006<br />
MMO-634 High Stability Optical Benches for Darwin 1,000 C Increased budget - Intended<br />
MMS-987 Darwin Solar Array/Solar Shade C<br />
Deferred, awaiting System Study<br />
results. 800 K€<br />
- Deferred<br />
Total 2.2.1 - Darwin (Source: <strong>TRP</strong> 2000-2003) 950 400 36 35 1,000<br />
Page 19 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.3 - Missions in Pre-Assessment Phase: XEUS<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T204-03M<br />
M<br />
High performance X-ray optics 1199 C(2) NL<br />
Cosine Research + SRON (NL) +<br />
Max Planck Institut (D) + Danish<br />
National Space Center (DK) +<br />
Kayser-Threde (D) + Micronit (NL)<br />
- Contracted 20885<br />
Y2006<br />
T204-04M<br />
M<br />
Micropore baffle 400 C(2) - Intended<br />
Y2006 T204-06SC Low bandgap supercon<strong>du</strong>cting sensor 600 C(1) - Intended<br />
Y2006<br />
T204-07M<br />
M<br />
TES Spectrometer 700 C(1) - Intended<br />
Y2006 T204-08MC 50mK Continuous Cooling System 400 40 C F CEA - Contracted 21227<br />
Y2006 T204-08MC 50mK Continuous Cooling System 440 C UK Astrium - Contracted<br />
Total 2.3 - Missions in Pre-Assessment Phase: XEUS 1,599 2,180<br />
Page 20 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.3.1 - XEUS (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
Y2002/<br />
Y2006<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Readdressing and splitting of the<br />
original activity. SRON+Physikalish<br />
SCI-X10.a Supercon<strong>du</strong>cting Read Out for Microcalorimeters 300 C(1) NL Tech<br />
- Contracted 21278<br />
Bundesan(D)+VTT(FIN)+INAF(I),T<br />
hales<br />
Y2002/<br />
Y2006<br />
SCI-X10.b Supercon<strong>du</strong>cting Read Out for Supercon<strong>du</strong>cting tunnel junctions 500 C(1)<br />
Readdressing and splitting of the<br />
original activity<br />
- Intended<br />
Y2007 SCI-X11 Large Format Detector Read-Out - Additional work 400 DN/C I Thales Alenia Space - Contracted 17189<br />
Y2001 SCI-X4 Optical rejection filter 300 C(1) FIN Metorex - Contracted 18122<br />
Y2002 SCI-X8 Multilayer coatings for high energy 251 C(1) I MediaLario - Contracted 18023<br />
Total 2.3.1 - XEUS (Source: <strong>TRP</strong> 2000-2003) 551 700 500<br />
Page 21 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.4 - Long Term Mission / Technology Reference Missions: Gamma Ray Imager<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2005 T206-01SC Gamma Ray Optics Development 400 C I<br />
Thales Alenia Space + Un. Paul<br />
Sabatier (F) + IKZ (D) + Inst. Laue<br />
Langvin (F)<br />
- Contracted 20357<br />
Total 2.4 - Long Term Mission / Technology Reference Missions:<br />
Gamma Ray Imager<br />
400<br />
2.- Science / Robotic Exploration Preparation<br />
2.5 - Long Term Mission / Technology Reference Missions: Venus Entry Probe<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T210-01M<br />
M<br />
A thin balloon envelope for harsh environments C(1) Deferred (not in Cosmic Vision) - Deferred<br />
Total 2.5 - Long Term Mission / Technology Reference Missions:<br />
Venus Entry Probe<br />
Page 22 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.6 - Other Technologies / Missions<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T214-05SC High Resolution, Low Mass, Pore Optics 850 C(1) D<br />
Kayser-Threde + Cosine Research<br />
(NL)<br />
- Contracted 18981<br />
Y2004 T214-05SC High Resolution, Low Mass, Pore Optics: additional work 173 DN/C D<br />
Kayser-Threde + Cosine Research<br />
(NL)<br />
- Contracted 18981<br />
Y2006 T214-05SC High Resolution, Low Mass, Pore Optics: additional work 197 DN/C D<br />
Kayser-Threde + Cosine Research<br />
(NL)<br />
- Contracted 18981<br />
Total 2.6 - Other Technologies / Missions 850 173 197<br />
Page 23 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.7 - GAIA (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 SCI-G16 Optimum Compression Algorithm 200 C E<br />
GTD Sistemas de Informacion,<br />
IEEC<br />
Open Source<br />
Code<br />
Contracted 20615<br />
Total 2.7 - GAIA (Source: <strong>TRP</strong> 2000-2003) 200<br />
Page 24 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.8 - Cosmic Vision 2025 (Solar Orbiter, WFI, ..)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T202-01M<br />
M<br />
Solar Blind sensor 600 C SOLO/SPO missions - Intended<br />
T215-01M<br />
M<br />
NIR large format sensor array 1500 C<br />
WFI mission. Deferred. Moved to<br />
<strong>TRP</strong> 2008-2010.<br />
- Deferred<br />
Y2006 T215-02MC Solar sails Materials 400 C(1) L SPO/IHP missions - Contracted<br />
Y2006<br />
T215-03M<br />
M<br />
Low bandgap EUV sensor 500 C(1) - Intended<br />
Y2006<br />
T215-04M<br />
M<br />
Planetary surface Dating Instrument (Luminescence dating) 600 C(2) DK<br />
NEO mission // TU Denmark +<br />
Cosine (NL) + TU Denmark (DK)<br />
- Contracted 21506<br />
Y2006 T215-05EE Jupiter Radiation Environment and Effect Tools 400 C UK<br />
Jupiter mission // Qinetiq + Onera<br />
(F) + DH Consultancy (B)<br />
Operational<br />
SW<br />
Contracted 21290<br />
Y2006 T215-06EP High radiation tolerant Low Intensity Low Temperature GaAs solar cells 500 50 C D<br />
Jupiter mission. Azurspace,<br />
FHG+CESI (I)<br />
- Contracted 21292<br />
Y2006<br />
T215-07M<br />
M<br />
Demonstration of the deployment of a highly integrated low power ice penetrating<br />
radar antenna<br />
600 C(2) Jupiter mission - Intended<br />
Page 25 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.- Science / Robotic Exploration Preparation<br />
2.8 - Cosmic Vision 2025 (Solar Orbiter, WFI, ..)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T215-08EE Wideband Spectrometer 250 C D MPAE - Contracted 21142<br />
Y2006 T215-08EE Wideband Spectrometer 250 C UK<br />
Astrium+Astrium(F)+RAL(UK),Un.<br />
Dundee<br />
- Contracted 21181<br />
Y2000<br />
/<br />
Y2006<br />
T215-09MC H2 Sorption Cooler 600 DN/C NL Un. Twente - Contracted 21348<br />
Total 2.8 - Cosmic Vision 2025 (Solar Orbiter, WFI, ..) 2,900 3,350<br />
Page 26 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.1 - Advanced habitats<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T301-03MC Design Verification & manufacturing aspects relevant for inflatable Mo<strong>du</strong>les 800 C(2) I<br />
ALS + Aero Sekur + LTA<br />
Technologie (D) + Samtech (B) +<br />
Sener (E) + Austrian Aerospace<br />
(A)<br />
- Contracted 19345<br />
Y2004 T301-10MC Polymerisation of Composite Structures in Free Space 300 C(2) F<br />
EADS-ST + Un. Reims,<br />
EADS-Astrium + ARCS (A) + M.<br />
Bernasconi Cons. (CH)<br />
- Contracted 19226<br />
Total 3.1 - Advanced habitats 1,100<br />
Page 27 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.2 - Automation and advanced robotic technologies<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T302-02M<br />
M<br />
Compact Automatic Tool Exchange Device 400 C(1) I GA, Tecnomare - Contracted 18774<br />
Y2004<br />
T302-08M<br />
M<br />
Vision Based Manipulation of non-co-operative objects 300 45 C(1) B<br />
Trasys, U. Leuven + GA (I) + IRIA<br />
(F)<br />
- Contracted 19145<br />
Total 3.2 - Automation and advanced robotic technologies 400 300 45<br />
Page 28 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.2.1 - Automation & Robotics (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 MMA-622 Dextrous Robot System - Phase 1&2 700 C(2) CH<br />
Contraves, HTS, CSEM + Dutch<br />
Space (NL)<br />
- Contracted 18183<br />
Y2002 MMA-622 Dextrous Robot System - Phase 1&2 700 C(2) I GA, Tecnomare + Sener (E) - Contracted 18184<br />
Y2002 MMA-622 Dextrous Robot System - Phase 3 1300 500 C(R) GA, Tecnomare + Sener (E) - Contracted 18184<br />
Total 3.2.1 - Automation & Robotics (Source: <strong>TRP</strong> 2000-2003) 1,400 1,300 500<br />
Page 29 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.3 - Closed loop life support technologies<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T303-02MC Bioregenerative Life Support Basic Development 250 250 250 DN/C F UPB, Melissa Partners - Contracted 38608<br />
Y2004 T303-11MC Air Sampling System for Microbial Contaminants Identification 250 C F<br />
Biomerieux + Statice Etudes et<br />
Developpement<br />
- Contracted 20605<br />
Total 3.3 - Closed loop life support technologies 250 250 500<br />
Page 30 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.3.1 - Optical/Electro-Optical Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y1998 97/XAO08 Quantum Well Photodector 150 DN/S S ACREO - Contracted 18264<br />
Y2002 MMO-635 Assessment of Phasing Capabilities of Fibre Optic Devices 250 35 DN/S A TU Wien - Contracted 37028<br />
Total 1.3.1 - Optical/Electro-Optical Technologies (Source: <strong>TRP</strong><br />
2000-2003)<br />
400 35<br />
Page 31 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.4 - Crew Health and Performance<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T304-01M<br />
M<br />
Integrated Countermeasures for microgravity effects 340 C(2) D<br />
Novotec + Un. Hospital Freiburg<br />
(D) + Astrium (D)<br />
- Contracted 20767<br />
Y2004<br />
T304-01M<br />
M<br />
Integrated Countermeasures for microgravity effects 340 C(2) F<br />
Medes IMPS + Verhaert (B) + DLR<br />
(D) + Medessat (F) + Un. Antwerp<br />
(B)<br />
- Contracted 20766<br />
Total 3.4 - Crew Health and Performance 680<br />
3.- Human Spaceflight Manned Exploration<br />
3.5 - Free-Flyers (Rendezvous and Docking, In-Orbit Assembly and Servicing)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T306-03M<br />
M<br />
Selfcalibrating 3-D optical metrology 200 DN/C UK EM Technology - Contracted 18584<br />
Total 3.5 - Free-Flyers (Rendezvous and Docking, In-Orbit Assembly<br />
and Servicing)<br />
200<br />
Page 32 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.6 - Instrumentation for Life Science<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T307-05M<br />
M<br />
Immuno-Biochemical Analyser 500 DN/C D<br />
EADS-Astrium + Diacdem<br />
Chip-Technologies + NTE (E)<br />
- Contracted 19391<br />
Y2004<br />
T307-09M<br />
M<br />
Virtual reality stimulator 300 C(1) NL<br />
Space Application Services + Un.<br />
Paris Descartes (F) + Un. Brussels<br />
(B)<br />
- Contracted 20650<br />
Y2004<br />
T307-15M<br />
M<br />
Life Support Technology for MISS 600 C(2) I Alenia Spazio - Contracted 19133<br />
Total 3.6 - Instrumentation for Life Science 1,100 300<br />
Page 33 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.7 - Instrumentation for Physical Science<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T308-03M<br />
M<br />
Oxygen sensing/control 500 DN/C D EADS-ST and Sub ITT - Contracted 19963<br />
Y2004<br />
T308-06M<br />
M<br />
Enhanced Mini Lda 360 DN/C D<br />
ZARM-Technik, PTB<br />
Braunschweig, Laser Zentrum<br />
Hannover, BT<br />
- Contracted 16554<br />
Total 3.7 - Instrumentation for Physical Science 360 500<br />
3.- Human Spaceflight Manned Exploration<br />
3.8 - Payload Data Handling<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T310-02ES COTS based space borne computer 1 300 C F<br />
Thales Alenia Space + Thales<br />
Alenia Space (I) + Austrian<br />
Aerospace (A)<br />
- Contracted<br />
Total 3.8 - Payload Data Handling 300<br />
Page 34 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.9 - Intelligent Space Systems Operation (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 EME-018 SDE and Space Palmtop Applications 200 C D Astrium + Skytek (Irl) - Contracted 18694<br />
Y2002 EME-018 SDE and Space Palmtop Applications 200 C DK Terma + Siemens (A) - Contracted 18695<br />
Y2006 EME-019 On-Board Model Checking 200 C I<br />
Thales Alenia Space + Fond.<br />
Bruno Kessler (I) + Thales Alenia<br />
Space (F)<br />
Operational<br />
SW<br />
Intended 20580<br />
Y2002 ESD-023 Mission Execution Crew Assistant 500 C(1) NL TNO Human Factor<br />
Open Source<br />
Code<br />
Contracted 19149<br />
Y2002 ETD-037 High Performance Resilient Computer For Autonomous Robotics 750 C(2) I<br />
ALS, GA + Syderal (CH) + FHG<br />
(D)<br />
- Contracted 18750<br />
Y2002 MMA-624 Satellite Servicing Building Blocks 750 75 C(2) F EADS-Astrium - Contracted 19505<br />
Total 3.9 - Intelligent Space Systems Operation (Source: <strong>TRP</strong><br />
2000-2003)<br />
1,150 1,250 75 200<br />
Page 35 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.10 - Aurora<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2005 03/E15 Experimental and theoretical study of Mars <strong>du</strong>st effects 250 C D HPS - Contracted 19632<br />
Y2005 03/W15 Solar cell development for Mars exploration missions 400 C D<br />
RWE, FHG + Galileo Avionica,<br />
CESI (I)<br />
- Contracted 20509<br />
Y2005 03/W25 Solar cell electrical characterization facility for Mars exploration missions 200 DN/S INTA - Intended<br />
Y2005/<br />
Y2006<br />
03/W35 Martian <strong>du</strong>st simulation facility for solar cells 400 C DK Change in PP. Un.Aarhus - Contracted 21285<br />
Y2005 04/G15 Precision landing GNC test facility 1000 C I<br />
CGS, Un. Padova, Un. D'Annunzio<br />
+ EADS-Astrium (F) +<br />
OHB-Systems (D) + Scisys (UK) +<br />
GMV (E)<br />
Operational<br />
SW<br />
Contracted 19541<br />
Y2005<br />
04/G25 +<br />
T306-01ES<br />
Autonomous Rendez-vous GNC test facility + Integrated Multi-Range Rendezvous<br />
Control System<br />
1000 C E<br />
GMV, Sener + Skysoft (P) +<br />
Alcatel (F) + Alenia (I)<br />
Operational<br />
SW<br />
Contracted 19846<br />
Y2005<br />
04/G25 +<br />
T306-01ES<br />
Autonomous Rendez-vous GNC test facility + Integrated Multi-Range Rendezvous<br />
Control System<br />
580 C F EADS-Astrium<br />
Operational<br />
SW<br />
Contracted 19983<br />
Y2005 04/K15 Mars climate database and physical models 350 DN/C F<br />
LMD/CNRS + U. Oxford (UK) +IAA<br />
(E)<br />
- Contracted 11369<br />
Page 36 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.10 - Aurora<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 04/K15 Mars climate database and physical models 18 DN/C F LMD/CNRS<br />
Operational<br />
SW<br />
Contracted 11369<br />
Y2005 04/K25 Martian radiation environment models 400 C UK - Contracted 19770<br />
Y2005 04/K35 Cleaning / sterilisation technologies 213 C DK Lytzen - Contracted 21367<br />
Y2005 04/T45 Passive variable thermal con<strong>du</strong>ctance device for Mars rover applications 300 C F<br />
EADS-Astrium + EADS-Astrium<br />
(UK) + Euro Heat Pipes (B)<br />
- Contracted 19994<br />
Y2005 T213-01SC Water sensor for Mars Exploration 600 C UK<br />
Open University +NEO, Novsys (N)<br />
+ Stella Polaris (P)<br />
- Contracted 19751<br />
Y2004<br />
T213-03M<br />
M<br />
Sampling drill tools for rocky and granular soils 150 C - Intended<br />
Y2005<br />
T213-04M<br />
M<br />
Ultrasonic Tools for Planetary Surface Exploration 300 49 C(1) UK Magna Parva - Contracted 20314<br />
Y2004<br />
T213-06M<br />
M<br />
Imaging Lidar technology 900 C(4) D Jena-Optronik - Contracted 19635<br />
Page 37 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
3.- Human Spaceflight Manned Exploration<br />
3.10 - Aurora<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T213-06M<br />
M<br />
Imaging Lidar technology 900 C(4) UK ABSL, Hovemere + Sensl (IRL) - Contracted 19603<br />
Y2004<br />
T213-07M<br />
M<br />
Down hole hammering Mechanism 250 C(1) I GA + TU Helsinki (N) - Contracted 19294<br />
Y2005<br />
T213-08M<br />
M<br />
Biochemical analyser 150 C(1) D ESE, Diacdem Chip-Technologies - Contracted 20389<br />
Total 3.10 - Aurora 1,750 5,648 400 612<br />
Page 38 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.1 - Materials and Structures / Advanced Hot Structures and Thermal Protection Systems<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T401-02MC Damage Tolerance of Cryogenic Pressure Vessels 200 C D<br />
MT Aerospace, DLR, Un.Stuttgart<br />
+ Inegi (P)<br />
- Contracted 21020<br />
Total 4.1 - Materials and Structures / Advanced Hot Structures and<br />
Thermal Protection Systems<br />
200<br />
4.- Space Transportation / Re-entry Technologies<br />
4.1.1 - Structures & Thermal Protection (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/MCS-00<br />
1<br />
Full Scale structure Qualification Methodologies 1500 104 DN/S I ALS, CIRA + MAN (D) - Contracted 16751<br />
Y2002 MCT-998 Smart Thermal Protection System 400 C E INASMET +ALTA(I) + EADS(F) - Contracted 17799<br />
Total 4.1.1 - Structures & Thermal Protection (Source: <strong>TRP</strong><br />
2000-2003)<br />
400 1,500 104<br />
Page 39 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.2 - Materials and Structures / Advanced Materials<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T403-02Q<br />
M<br />
High temperature complex parts based on intermetallic components 200 C E<br />
Inasmet (E) + Qinetiq (UK) +<br />
Snecma (F)<br />
- Contracted 18955<br />
Y2004 T403-03MC Multiphysic Modeling of Near-surface Phenomena 200 40 C I Un. Roma - Contracted 19168<br />
Y2004<br />
T403-03MC<br />
.B<br />
Multidisciplinary Modeling of Fluid Structure Interaction 205 40 DN/S IRL ESIL, Special Measure IRL. - Contracted 19631<br />
Y2004 T403-09MC Increase of Bolted Joint performance for CFRP 500 C D<br />
DLR, HPS, Kayser-Threde +<br />
Contraves (CH), INEGI (P) +<br />
CASA (E)<br />
- Contracted 19793<br />
Y2005 T403-14MC Cryogenic Composite Tanks and Lines 400 DN/C A<br />
Magna Steyr, Special Measure<br />
Austria. (+150kE GSTP)<br />
- Contracted 21225<br />
Total 4.2 - Materials and Structures / Advanced Materials 605 500 400 80<br />
Page 40 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.3 - Materials and Structures / Advanced Structures<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T405-01MC Non-destructive inspection methods for re-usable CFRP structures 250 C - Intended<br />
Total 4.3 - Materials and Structures / Advanced Structures 250<br />
Page 41 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.4 - Propulsion / Advanced Liquid Propulsion<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 MPC-846 Acquisition and Evaluation of Cryo-Solid Propulsion: Additional Testing 140 DN/C D<br />
Aerospace Institute - LO, ADIRIM<br />
& PARTNERS<br />
- Contracted 16830<br />
Y2004 T402-05MP Scaling of Thermal Cavitation Effects on Cavitation-In<strong>du</strong>ced Instabilities 350 40 C(1) I<br />
Alta + Inst. Nat. Pol. Grenoble (F)<br />
+ Un. Pisa (I)<br />
- Contracted 20081<br />
Y2004<br />
T402-10MP<br />
Unsteady subscale force measurements within a launch vehicle base buffeting<br />
environment<br />
450 C(1) D<br />
DLR,<br />
Astrium+Astrium(F)+Onera(F)+NL<br />
R(NL)<br />
- Contracted 21163<br />
Total 4.4 - Propulsion / Advanced Liquid Propulsion 940 40<br />
Page 42 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.5 - Propulsion / Advanced Propulsion Concepts for In-Space Operations<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T404-02MP Technical Assessment for High Power Magneto Plasma Dynamics (MPD) Systems 300 C I<br />
Alta + Un.Stuttgart (D) + Snecma<br />
(F)<br />
- Contracted 21797<br />
Y2004 T404-03MP Advanced Electric Propulsion for a Service Mo<strong>du</strong>le for VEGA 350 C I Elv + others - Contracted 20072<br />
Total 4.5 - Propulsion / Advanced Propulsion Concepts for In-Space<br />
Operations<br />
350 300<br />
4.- Space Transportation / Re-entry Technologies<br />
4.6 - Propulsion / Air-breathing Propulsion<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T407-01MP Design of Flight Test Configuration for High-speed Airbreathing Propulsion 650 C D<br />
DLR, EADS-ST + Imperial College,<br />
Fluid Gravity, CGC Technology,<br />
Gas Dynamics (GB) + SSC (S)<br />
- Contracted 18828<br />
Total 4.6 - Propulsion / Air-breathing Propulsion 650<br />
Page 43 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.7 - Propulsion / Solid Propulsion<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T402-08MP Cryogenic RCS thruster technology C<br />
385kE, postponed to mid 2007,<br />
awaiting system study.<br />
- Deferred<br />
Y2006 T411-01MP Hybrid propulsion evaluation for liquid booster application 250 C F SNPE + Avio(I) - Contracted 20676<br />
Y2004 T413-01MP Experimental demonstration of opto-pyro systems for launcher applications 400 45 C(1) CH Contraves - Contracted 20363<br />
Y2004 T413-01MP Experimental demonstration of opto-pyro systems for launcher applications 400 278 C(1) N KDA + EADS-ST (F) - Contracted 19800<br />
Total 4.7 - Propulsion / Solid Propulsion 800 250 323<br />
Page 44 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.7.1 - Propulsion Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2000 MMM-956 Journal bearings for turbopumps 400 C F<br />
Snecma + Un. Liege (B) + Aea<br />
Technology (UK) + Energie<br />
Technologie, MAN (D) + Avio (I)<br />
- Contracted 18768<br />
Total 4.7.1 - Propulsion Technologies (Source: <strong>TRP</strong> 2000-2003) 400<br />
Page 45 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.8 - Aerothermodynamics (ATD)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T406-04MP CFD validation in CO2 environment 350 C D<br />
DLR + Onera (F) +VKI (B) + FG<br />
(UK)<br />
- Contracted 19548<br />
Y2004 T406-04MP CFD validation in CO2 environment 350 C UK<br />
Fluid Gravity + U. Stuttgart (D)<br />
+EADS, U. Provence (F)<br />
- Contracted 19677<br />
Y2004<br />
T406-09MP<br />
Development and qualification of in Flight Test Measurement (FTM) techniques:<br />
Electron Beam Fluorescence fo Aerothermodynamic Applications<br />
200 C F Onera - Contracted 20454<br />
Y2004<br />
T406-09MP<br />
Development and qualification of in Flight Test Measurement (FTM) techniques:<br />
Nose & Payloads<br />
1025 C D<br />
DLR, U. Stuttgart + CIRA +<br />
Hyperschall Technologie<br />
Goettinger<br />
- Contracted 20062<br />
Y2004<br />
T406-09MP<br />
Development and qualification of in Flight Test Measurement (FTM) techniques:<br />
Nose & Payloads<br />
930 C I<br />
CIRA, Alta + DLR, Hyperschall<br />
Technologie Goettinger (D), Onera<br />
(F), VKI (B)<br />
- Contracted 20061<br />
Y2004 T406-12MP Preparation of an electrodynamic-heatshield flight experiment 200 50 C D EADS-ST, DLR - Contracted 19337<br />
Y2007 T406-13MP Advanced Methods for Hypersonic plasma - flow control 350 C - Intended<br />
Total 4.8 - Aerothermodynamics (ATD) 550 2,505 400<br />
Page 46 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.8.1 - Aerothermodynamics (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/MPA-00<br />
1<br />
In-Flight Aerothermodynamic Measurements 480 DN/S I<br />
CIRA + DLR(D) + ONERA(F) +<br />
subs<br />
- Closed 18125<br />
Y2003<br />
/<br />
Y2007<br />
94/8.2.1.4,<br />
03/MPA-00<br />
2<br />
Plasma Radiation Database 105 105 DN/S UK Fuid Gravity - Contracted 11148<br />
Total 4.8.1 - Aerothermodynamics (Source: <strong>TRP</strong> 2000-2003) 480 105 105<br />
Page 47 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.9 - Avionics and GNC<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T408-01MX<br />
Modern Guidance Schemes for the Terminal Area Energy Management (TAEM)<br />
Flight Phase of Reusable Space Transportation Systems<br />
100 C p Spinworks + Astos Solutions(D)<br />
Open Source<br />
Code<br />
Contracted 22007<br />
Y2004 T408-06ES Robust Multi-mission Navigator 650 C(2) F<br />
Astrium, Astrium (D) + AAS (A) +<br />
Deimos (E/P) +SciSys (UK)<br />
Open Source<br />
Code<br />
Contracted 19105<br />
Total 4.9 - Avionics and GNC 650 100<br />
4.- Space Transportation / Re-entry Technologies<br />
4.10 - Health Management System (HMS)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T410-01MC Health Monitoring system for TPS and Hot Structures 200 C D<br />
ASTRIUM + Univ. Stuttgart (D) +<br />
Dutch Space (NL)<br />
- Contracted 21688<br />
Total 4.10 - Health Management System (HMS) 200<br />
Page 48 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
4.- Space Transportation / Re-entry Technologies<br />
4.11 - Intelligent Space Systems Operation (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 MXO-001 Health Management System for Re-usable Space Transportation 700 C(2) D<br />
Total 4.11 - Intelligent Space Systems Operation (Source: <strong>TRP</strong><br />
2000-2003)<br />
700<br />
EADS-ST, DFKI + Alenia, U.<br />
Roma, Cira (I) + Deimos (E/P) +<br />
Sctd (NL) + Snecma (F) +U.<br />
Aalborg (DK)<br />
- Contracted 19197<br />
5.- Telecommunication / Navigation<br />
5.1 - Conventional Fixed Telecommunication Service<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
ETM-101<br />
Surface Treatment and Coatings for the Re<strong>du</strong>ction of Multipactor and Passive<br />
Intermo<strong>du</strong>lation Phase 2<br />
200 DN/S D Tesat + UAM (E) - Contracted 17025<br />
Y2004 T503-03ET RF breakdown in Multicarrier systems 400 C(2) E<br />
Aurora Safety & Testing, Un. Polit.<br />
Valencia, Un. Valencia + EPFL<br />
(CH) + T<strong>ESA</strong>T Spacecom (D)<br />
Operational<br />
SW<br />
Contracted 19918<br />
Total 5.1 - Conventional Fixed Telecommunication Service 600<br />
Page 49 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.2 - Engineering and Verification Tools & Techniques<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T506-01EE European Antenna Modelling Component Library - Telecommunications 450 50 330 250 DN/S DK Ticra + Satimo (I) - Contracted 18802<br />
Y2004 T506-02MC Modelling of Porous Shells 400 C(4) D<br />
HPS, Invent, TU Munich + Saab,<br />
Royal Inst. Technology (S) + Inegi<br />
(P)<br />
- Contracted 20168<br />
Total 5.2 - Engineering and Verification Tools & Techniques 450 450 330 250<br />
Page 50 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.3 - High capacity multi-beam systems<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T501-02EE Active multi-beam antenna concept using advanced very high order multilayer BFN 250 C(2) I<br />
Activity re<strong>du</strong>ced in scope - Space<br />
Engineering, MECSA<br />
- Contracted 20614<br />
Y2006<br />
T501-04EE<br />
Development of high order propagation models for multimedia Satellite<br />
Communication Systems<br />
300 C Revised description.<br />
Operational<br />
SW<br />
Intended<br />
Y2004 T501-06ET High Frequency SIGE MMICS for Converter 500 C D<br />
Kayser-Threde, IMST, IHP + Saab<br />
Ericsson (S)<br />
- Contracted 18927<br />
Y2004 T501-07ET High Reliability MEMS Re<strong>du</strong>ndancy Switch 750 C(2) F<br />
CEA + Thales Alenia Space (F) +<br />
CNRS (F) + Un Athens (GR)<br />
- Contracted 20832<br />
Y2004 T501-07ET High Reliability MEMS Re<strong>du</strong>ndancy Switch 750 C(2) I<br />
Fond. Bruno Kessler + Un. Munich<br />
(D) + CMR IMM (I), Space<br />
engineering, Thales, Un. Bologna,<br />
Un. Padova, Un. Perugia<br />
- Contracted 20847<br />
Y2006<br />
T501-08EE<br />
Innovative architectures for re<strong>du</strong>cing the number of controls of multiple beam<br />
telecommunication antennas<br />
350 C I<br />
Space Engineering + Aristotle Univ<br />
(GR) + CNIT (I)<br />
- Contracted 21689<br />
Y2004 T501-10ET High throughput highly re-configurable bent-pipe processor for access networks 1500 C(2) F<br />
Alcatel + Alenia Spazio, Space<br />
Engineering (I)<br />
- Contracted 19941<br />
Y2004 T501-10ET High throughput highly re-configurable bent-pipe processor for access networks 500 C(2) UK EADS-Astrium - Contracted 19942<br />
Page 51 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.3 - High capacity multi-beam systems<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T501-11EE New concepts for <strong>du</strong>al-gridded reflectors (study) 400 30 C D<br />
HPS, Invent, TU Munchen + ASD<br />
(I) + ASC (DK)<br />
- Contracted 19658<br />
Y2004 T501-11EE New concepts for <strong>du</strong>al-gridded reflectors (study) 400 C S Saab Ericson - Contracted 19678<br />
Y2004<br />
T501-12ET<br />
Study of Enhanced digital transmission techniques for Broadband Satellite Digital<br />
Transmissions<br />
400 C(2) B Newtec CY - Contracted 19370<br />
Y2006 T501-14ET Broadband low-power ADC design & prototyping 990 C F<br />
See <strong>ESA</strong>/IPC(2006)88. E2V<br />
Technol., Thales+Astrium (UK<br />
- Contracted 21411<br />
Y2006 T501-15ET Broadband low-power DAC design & prototyping 900 177 C D<br />
Total 5.3 - High capacity multi-beam systems 900 2,800 2,650 1,847<br />
See <strong>ESA</strong>/IPC(2006)88. Kayser<br />
Threde, Advico Microelectronics,<br />
IHP+ Maser<br />
Engineering(NL)+SAAB Ericsson<br />
Space(S)<br />
- Contracted 21274<br />
Page 52 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.4 - Mobile Communications<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T502-06EE Simulation of the satellite to indoor propagation channel at L and S bands 200 C E - Contracted 19778<br />
Total 5.4 - Mobile Communications 200<br />
Page 53 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.5 - Navigation & Positioning<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T504-02EM Energetic Electron Environment Models for MEO 250 C(1) F Onera + QinetiQ (UK) + SSTL (UK) Operational<br />
SW<br />
Contracted 21403<br />
Y2004<br />
T504-05GN<br />
Satellite and station clock modelling for GNSS, link between physical models and<br />
estimation / prediction processes<br />
250 C(1) - Intended<br />
Y2006 T504-08ET Next Generation Compact Atomic Clocks 400 C(1) - Intended<br />
Y2006 T504-10ET Development of Innovative Atomic Clock for Satellite 500 C(1) - Intended<br />
Y2006 T504-11ET Signal Processing Techniques and Demonstrator for Indoor GNSS Positioning 600 C(2) D<br />
IFEN + Sepa (I) + Un Munich (D) +<br />
Audens Act Consulting (D) +<br />
Telespazio (I)<br />
- Contracted 20834<br />
Y2006 T504-11ET Signal Processing Techniques and Demonstrator for Indoor GNSS Positioning 600 C(2) E<br />
GMV + Skysoft (P) + Un Barcelona<br />
(E) + Nemerix (CH) + Un Leeds<br />
(UK) + Thales Alenia Space (F)<br />
- Contracted 20835<br />
Y2006 T504-14ET Evolutionary Navigation Systems 300 C D<br />
Astrium+Joann.Research<br />
Centre(A)+JAST(CH)<br />
- Contracted 21273<br />
Y2006<br />
T504-16M<br />
M<br />
Development of key Optical Clock technologies 400 C(1) - Intended<br />
Total 5.5 - Navigation & Positioning 1,200 2,100<br />
Page 54 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.5 - Navigation & Positioning<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
5.- Telecommunication / Navigation<br />
5.6 - Satellite / Platform Technologies<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T505-04ES Low Cost Coarse Earth Sensor Development 300 C(1) I Galileo Avionica - Contracted 19555<br />
Y2006 T505-14EP Fuel cells for Telecom systems 150 C D Astrium+Astrium(F)+QinetiQ(UK) - Contracted 21370<br />
Y2006 T505-14EP Fuel cells for Telecom systems 150 C F Thales+Prototech(N) - Contracted 21349<br />
Total 5.6 - Satellite / Platform Technologies 300 300<br />
Page 55 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.6.1 - Antenna Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 EEA-013 Q/V Band Antenna S/S 250 C I Space Eng. - Contracted 18094<br />
Y2002 EEA-013 Q/V Band Antenna S/S: additional work 49 C I Space Eng. - Contracted 18094<br />
Y2002 MMM-946 Hybrid mechanical-electronic pointing system 450 C E Sener - Contracted 18186<br />
Total 5.6.1 - Antenna Technologies (Source: <strong>TRP</strong> 2000-2003) 700 49<br />
Page 56 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.6.2 - On-Board Equipment Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/ETM-00<br />
1<br />
SAW Filter Development (original activity: SAW resonator technology for L and<br />
S-band space applications)<br />
300 DN/S N AME - Contracted 13635<br />
Y2003<br />
03/ETM-00<br />
1<br />
SAW Filter Development (original activity: SAW resonator technology for L and<br />
S-band space applications)<br />
200 350 DN/S N<br />
AME (Special measures for<br />
Norway) >> continued in <strong>TRP</strong><br />
2008-2010<br />
- Contracted 20002<br />
Y1998<br />
/ 2003<br />
97/XRF02 Tool for high speed end to end system simulation 330 C(2) F<br />
Astrium + DGRO (D) + Critical S/W<br />
(P)<br />
- Contracted 18660<br />
Y2000 EEP-009 Characterization and modeling of Propagagation effect Q/V Band 250 C UK RAL + U. Louvain (B) - Contracted 17841<br />
Y2001 ETM-080 Cold Cathode TWT 500 C(1) F Thales - Contracted 19388<br />
Total 5.6.2 - On-Board Equipment Technologies (Source: <strong>TRP</strong><br />
2000-2003)<br />
880 500 200 350<br />
Page 57 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.- Telecommunication / Navigation<br />
5.7.2 - Telecommunication P/L (Source: <strong>TRP</strong> 2000-2003)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 EEO-010 Technology for optical payloads 350 C(1) E Sener - Contracted 18610<br />
Total 5.7.2 - Telecommunication P/L (Source: <strong>TRP</strong> 2000-2003) 350<br />
Page 58 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.1 - On-board Data Systems<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/EDP-00<br />
1<br />
SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A) 450 40 DN/S D Astrium + ATMEL - Contracted 18329<br />
Y2006<br />
03/EDP-00<br />
1<br />
SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A): enhancement 80 DN/C D Astrium + ATMEL - Contracted 18329<br />
Y2002<br />
03/ESD-00<br />
1<br />
Rf Wireless Intra-Spacecraft Communications - Phase 1 550 C UK<br />
SEA+Astrium(F)+Aerospace<br />
Wireless(NL)+SSC(S)+4Links(UK)<br />
- Contracted 21405<br />
Y2002<br />
03/ESD-00<br />
1<br />
Rf Wireless Intra-Spacecraft Communications - Phase 2 950 C UK<br />
SEA+Astrium(F)+Aerospace<br />
Wireless(NL)+SSC(S)+4Links(UK)<br />
- Contracted 21405<br />
Y2002<br />
03/ESD-00<br />
2<br />
Optical Wireless-Intra-Spacecraft Communications - Phase 1 500 C E Inta - Contracted 19545<br />
Y2002<br />
03/ESD-00<br />
2<br />
Optical Wireless-Intra-Spacecraft Communications - Phase 2 1000 C E Inta - Contracted 19545<br />
Y1998 97/WSP01 Fast Transform DSP Coproc Ph. 2 & 3 600 DN/C D Astrium - Closed 15314<br />
Y2003 ESD-006 Design & verification of validation techniques for On-Board Microprocessors 500 DN/S S Gaisler Research - Contracted 18533<br />
Page 59 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.1 - On-board Data Systems<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003 ESD-016 Safeguard Data Recorder 500 C D<br />
EADS ST + Un. Braunschweig +<br />
EADS-Astrium (F)<br />
- Contracted 17442<br />
Y2001 ESD-034 Optical Wireless Data Transmission 500<br />
C(1) /<br />
C(4)<br />
CH<br />
Contraves, CSEM +UPM, ERZIA<br />
(CH)<br />
- Contracted 18493<br />
Y2000<br />
/<br />
Y2006<br />
ESM-006 High Speed Link Interconnect Network – Additional work 200 DN/C D<br />
Astrium + Austrian Aerospace (A)<br />
+ Un. Dundee (UK)<br />
- Contracted 15803<br />
Y2001 ETD-025 Compact Data Processing Unit 200 C(2) CH Syderal, EPFL - Contracted 18792<br />
Y2001<br />
/<br />
Y2006<br />
/<br />
Y2007<br />
ETD-028 Integrated Payload Data Processing System System 250 40 60 C(2) I Aurelia Microelettronica - Contracted 18780<br />
Y2002 ETD-036 Next Generation Mass Memory Architecture 200 C - Intended<br />
Y2002 ETD-038 Space wire Controller Remote User 500 77 23 17 10 C(2) S Saab - Contracted 18585<br />
Y2002 ETD-039 TOPNET: Pilot Operation Implementation - Topnet Deployment 166 C(2) F<br />
Astrium + Astrium (D) + Astrium<br />
(UK) + Sodern (F) + Galileo<br />
Avionica (I)<br />
- Contracted 20677<br />
Page 60 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.1 - On-board Data Systems<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 ETD-039 TOPNET: Pilot Operation Implementation - Topnet Deployment 166 C(2) F<br />
Thales Alenia Space + Thales<br />
Alenia Space (I)<br />
- Contracted 20665<br />
Y2002 ETD-039 TOPNET: Pilot Operation Implementation - Topnet Deployment 166 C(2) UK<br />
4Links Limited + SAAB Space (S)<br />
+ Science and Technology (UK)<br />
- Contracted 20670<br />
Y2006 T603-05ET FPGA Based Generic Mo<strong>du</strong>le and Dynamic Reconfigurator 500 C - Intended<br />
Y2004/<br />
Y2006<br />
T603-08ES Next Generation Multi-purpose Microprocessors 800 C - Intended<br />
Y2005 T603-09ES Validation and further development Spacecraft-Controller-on-a-Chip (SCOC) 250 30 DN/C F Astrium Velizy - Contracted 20167<br />
Y2006 T603-20ET Development of a Mass Memory Mo<strong>du</strong>le with Embedded File System Support 600 C(2) Awaiting for ETD-036 results - Intended<br />
Y2006 T603-22ES Synthesizable VHDL IP cores 250 C CH Syderal - Contracted 22043<br />
Y2006<br />
T603-27ED<br />
Evaluation of Radiation Effects on Deep Sub-micron CMOS Technologies (Original<br />
<strong>title</strong>:SEE Identification, Modelling & Severity assessment)<br />
300 C - Intended<br />
Page 61 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.1 - On-board Data Systems<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T608-26ES<br />
Radiation Hardened by Design ASIC library qualification, procurement and<br />
maintenance<br />
400 DN/S B IMEC - Contracted<br />
Y2004 T609-08ET Massively Parallel Processor Breadboarding 400 C(2) NL Recore Systems+Un.Twente(NL) - Contracted 21986<br />
Y2006 T609-25ED SpaceWire Network Bandwidth Performance Simulation Tool 200 C<br />
Operational<br />
SW<br />
Intended<br />
Y2006 T609-26ED OCP-IP building blocks for Space-SoC 150 C F<br />
Astrium + Gaisler Research (S) +<br />
Magillem (F)<br />
- Contracted 21393<br />
Y2006 T609-27ED Standardisation of spacecraft onboard communication services 200 C UK Scisys + Astrium (F)<br />
Operational<br />
SW<br />
Contracted 21288<br />
Total 6.1 - On-board Data Systems 2,900 617 1,993 1,405 4,910<br />
Page 62 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.2 - Space System Software<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 EME-012 Component Oriented Development Techniques 250 C F<br />
Alcatel + U. Padova (I) + P&P<br />
Software (CH) + GMV (E)<br />
Operational<br />
SW<br />
Contracted 20463<br />
Y2006 EME-012 Component Oriented Development Techniques 250 C F Astrium + Intecs (I)<br />
Operational<br />
SW<br />
Contracted 20464<br />
Y2001 EME-014 Compact Computer Core S/W 500 C(2) F Astrium + Scisys (UK) - Contracted 18787<br />
Y2006 EME-017 Tools For The Pro<strong>du</strong>ction Of O/B Sw Running On New Generation Computers 200 C P<br />
Edisoft + Syderal (CH) + Aonix<br />
(UK) + EADS-Astrium (F)<br />
Open Source<br />
Code<br />
Contracted 20385<br />
Y2001<br />
EME-100<br />
(EME-011,<br />
T-M-QQS-1<br />
Effective Use of autocoded Comp. 650 C(2) F<br />
4-4)<br />
EADS LV + SciSys(UK) +<br />
Synspace (CH)+ Gerlich (D)<br />
- Contracted 18056<br />
Y2006<br />
T603-28QQ<br />
Validation of Safety and Dependability Critical Software Componenets with Model<br />
Based Requirements<br />
200 C p Skysoft+GMV(E) - Contracted 21404<br />
Y2006<br />
T603-29S<br />
W<br />
System and Software Functional Requirements Techniques 250 C I<br />
INTECS + Thales (F) + Sapienza<br />
Un.Rome (I) + Thales (I)<br />
- Contracted 21188<br />
Y2004 T607-01EM Automation of the life cycle: automatic test generation 272 C(1) P<br />
Operational<br />
SW<br />
Contracted 19812<br />
Page 63 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.2 - Space System Software<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T607-05EM Verification and Validation: Testing Object Orientation 250 C(3) P Critical Software<br />
Open Source<br />
Code<br />
Contracted 20043<br />
Y2006 T607-08EM Standardisation and Building Blocks: Standardisation watch and verification 300 C<br />
Operational<br />
SW<br />
Intended<br />
Total 6.2 - Space System Software 1,150 1,022 200 750<br />
Page 64 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.3 - S/C Power<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003 EPB-001.C Development of Regenerative H2/O2 fuelcell 150 DN/S N Prototech - Contracted 18312<br />
Y2003 EPG-025 Solar Cells Testing Spasolab 244 270 220 220 DN/S E Multi-year contract. - Contracted 18444<br />
Y2003 ESB-008.A Adaptation of terrestrial fuel cells for space applications 50 DN/S D Ballard - Contracted 18534<br />
Y2002 ESG-007 Thin Film Solar Cells Ph. 3 600 DN/C NL Dutch Space + HMI (D) - Contracted 17644<br />
Y2001 ESG-009 Reverse Bias Protection of GaAs Solar Cells 150 C D Astrium, RWE - Contracted 18199<br />
Y2001 ESG-010 Development Of Interconnection Techniques For Thin Film Solar Cells 200 C NL Dutch Space + HMI (D) - Contracted 20391<br />
Y2001 ESG-017 Flexible Blanket Technology 100 C F Alcatel - Contracted 18037<br />
Y2001 ESP-003 Solar Array Sizing tool for Phase A/B studies 100 C B IAL - Closed 17947<br />
Page 65 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.3 - S/C Power<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
T505-05EP Thin Film cell and mo<strong>du</strong>le development 600 C - Deferred<br />
Y2006 T505-11EP Advanced research and pre-development of new materials for space solar cells 200 C(1) - Intended<br />
Y2005 T604-02EP Advanced Lithium Batteries Evaluation 300 C(1) F CEA - Contracted 20044<br />
Y2006 T604-03EP Development of Next Generation GaAs Based Multi-Junction Solar Cells - 2 1100 DN/C D<br />
RWE, FHG + CESI (I) + UMICORE<br />
(B) + Frauenhoffer (D)<br />
- Contracted<br />
Y2004 T604-05EP Development of Next Generation GaAs Based Multi-Junction Solar Cells - 1 2,000 DN/C D<br />
RWE, FHG + CESI (I) + UMICORE<br />
(B)<br />
- Contracted 18767<br />
Y2006 T604-06EP Nanotechnology for Space Solar Cells 200 C - Intended<br />
Y2006<br />
T604-07EP<br />
Efficient Low Cost Power Conversion for Standard and Advanced Fast Digital<br />
Electronics<br />
600 C S Saab Space - Contracted 20680<br />
Y2006 T604-08EP Integrated Current Limiter 350 C(R)<br />
C(R) restricted to DK, N, FIN, A,<br />
IRL.<br />
- Intended<br />
Page 66 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.3 - S/C Power<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T604-10EP Study of new Power Systems architectures for LEO missions 400 C - Intended<br />
Total 6.3 - S/C Power 3,394 270 520 2,720 1,150<br />
Page 67 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.4 - S/C Environment & Effects<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/EMA-00<br />
1<br />
Muon Telescope 200 DN/S D U. Greifswald, HTS - Contracted 18835<br />
Y2002 EMA-022 Spacecraft Charging & Plasma Interaction Guidelines 100 C UK Qinetic - Contracted 18061<br />
Y2004 T602-01EM Solar Energetic Particle Environment modelling 400 C(1) B<br />
Belgian Inst Space Aeronomy, Un.<br />
Leeuwen+Un.Polit.Cataluna(E)+Un - Contracted 20162<br />
. Southampton(EK), Qinetiq<br />
Y2004 T602-02EM Radiation Effects on Advanced Technologies: Models and Software Ph.1 250 C(1) UK<br />
Qinetiq + Rhea System, Belgian<br />
Institute Space Aeronomy (B) +<br />
Un. Bern (CH)<br />
- Contracted 19103<br />
Y2004 T602-02EM Radiation Effects on Advanced Technologies: Models and Software Ph.2 350 DN/C UK<br />
Qinetiq + Etamax (D) + TRAD (F) +<br />
Un. Genova (I), SPaceIT (CH)<br />
- Contracted 19103<br />
Y2006 T602-03EM Development of a predictive discharge numerical model on solar panels 200 C F Onera+Artenum(F)+Astrium(F)<br />
Operational<br />
SW<br />
Contracted 22048<br />
Y2007 T602-04EM Rapid prototyping toolkit for space environment engineering tools 250 C D<br />
Resubmitted after positive<br />
Harmonisation check // Etamax<br />
Space<br />
Open Source<br />
Code<br />
Contracted 21739<br />
Y2004<br />
T602-05MC<br />
Harmonisation of Thermal and Space Environment Analysis Software and Interfaces<br />
- Exchange of Thermal Models via STEP-TAS<br />
300 C<br />
prime + subs Alstom (UK) /<br />
Astrium-SAS (F) / Alcatel (F) +<br />
RAL (UK) / Astrium (D)<br />
Open Source<br />
Code<br />
Contracted 20382<br />
Page 68 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.4 - S/C Environment & Effects<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T602-06EM Space Weather Warning for Space Systems 300 C<br />
Open Source<br />
Code<br />
Intended<br />
T602-08EE Time-dependent Engineering Models of GEO and LEO Radiation Belts 340 DN/S F<br />
Onera + BIRA (B) + QinetiQ (UK).<br />
// Deferred<br />
Operational<br />
SW<br />
Deferred<br />
Y2006 T602-09EE Investigation and analysis of very high energy accelerators for radiation simulation 300 C D<br />
FHG+SpaceIT(CH)+Gesellschaft<br />
fur<br />
Schwerionforschung(D)+Maprad(I)<br />
- Contracted 21985<br />
Y2006 T607-11EE Rapid Reverse Monte Carlo and Ion Physics for Dose and SEE 200 C UK<br />
Phase1// Qinetiq + TRAD (F) +<br />
Spaceit (CH)<br />
Open Source<br />
Code<br />
Contracted 21435<br />
Y2004 T609-14QC General Spacecraft Environment Monitor 350 DN/S CH Contraves - Contracted 18619<br />
Total 6.4 - S/C Environment & Effects 650 250 650 740 1,250<br />
Page 69 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.5 - Space System Control<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
Y2002<br />
/<br />
Y2005<br />
/<br />
Y2007<br />
2004 2005 2006 2007 2008 31/12/2008<br />
MME-002 Integrated-Optics Laser gyro Technology (IOLG) Ph.2B 147 65 DN/C I Macchine Intelligenti - Contracted 16782<br />
Y2006<br />
T603-01M<br />
M<br />
Novel Optical Gyro Concept 500 C F<br />
Atmel + CNRS (F) + Un<br />
Montpellier (F) + Thales Avionics<br />
(F)<br />
- Contracted 20856<br />
Y2004/<br />
Y2005 T603-03ES Robust LPV Gain Sche<strong>du</strong>ling Techniques for Space Applications 300 C E Deimos + Un. Leicester (UK) + TU<br />
Delft (NL)<br />
Open Source<br />
Code<br />
Contracted 20565<br />
Y2004/<br />
Y2005 T603-03ES Robust LPV Gain Sche<strong>du</strong>ling Techniques for Space Applications 300 C F EADS-Astrium, CNRS, Onera Open Source<br />
Code<br />
Contracted 20489<br />
Y2006 T603-04ES Robust Model Predictive Control (MPC) for Space Constrained Systems 400 C<br />
Operational<br />
SW<br />
Intended<br />
Y2004 T603-10ES MEMS Rate Sensor 930 1000 C(1) UK SEA, BAe Systems, Selex - Contracted 18800<br />
Y2006 T603-11ES Attitude Determination Tailored to Multiple Heads Star Tracker 150 C F<br />
Alcatel (F) + Alcatel Alenia Space<br />
(I)<br />
Operational<br />
SW<br />
Contracted 20299<br />
Y2004 T603-12ES Autonomous On-Board Momentum Management C Deferred (low priority, 300kE) - Deferred<br />
Page 70 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.5 - Space System Control<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T603-13ES Modern Control Techniques Applied to Satellite FDIR 350 C F Astrium<br />
Open Source<br />
Code<br />
Contracted 21106<br />
T603-30EC Sensor on a Chip Feasibility study and Avionics Evolution 650 180 C I<br />
Galileo Avionica + BAE (UK) +<br />
Cypress Semicond. Corp (B) +<br />
Alcatel Alenia Space (F)<br />
- Contracted 20252<br />
Y2006 T603-36EC Future technology studies for APS Star Trackers 500 89 C D<br />
Jena Optotronic + Cypress<br />
Semicon<strong>du</strong>ctor Corporation (D) +<br />
Gaisler Research(D) + Zaimler<br />
Technik(D) + Frauenhofer(D)<br />
- Contracted 20781<br />
Y2006 T603-36EC Future technology studies for APS Star Trackers 500 C DK Terma + TNO(NL) - Contracted 20966<br />
Y2006 T603-38EC Enhanced CCD Star Tracker 400 DN/S DK Terma. Special Measure DK. - Contracted 20209<br />
Y2006 T603-41EC System study to define European accelerometer development 200 C F<br />
Thales,Memscap,Thales<br />
Avionics+Thales(I)+SEA(UK)<br />
- Contracted 21221<br />
Total 6.5 - Space System Control 1,077 2,800 1,765 1,019<br />
Page 71 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.6 - RF Payload System<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 ETP-029 O/B SAR Calibration 200 C F Alcatel - Contracted 18439<br />
Y2002 ETT-059 Neural networks for radionavigation 400 C(3) F M3S, T<strong>ESA</strong> + GMV, UPCA (E) - Contracted 18824<br />
Y2004 T603-14ET Frequency Flexible Synthesizer Breadboard suitable for O/B TTC 200 C I Alenia - Closed 18769<br />
Y2004 T603-14ET Frequency Flexible Synthesizer Breadboard suitable for O/B TTC: additional work 39 C I Alenia - Contracted 18769<br />
Y2004 T603-29ET Telecommand & Telemetry System Security 300 C F EADS-Astrium - Contracted 19130<br />
Y2006 T603-31QC Linearity Assessement of GaN Technology 500 C(1) D<br />
Tesat, FBI + Qinetiq (UK) + TU<br />
Denmark (DK)<br />
- Contracted 20456<br />
Y2006<br />
T603-32ET<br />
Power/Efficiency flexibility of spaceborne SSPA using Doherty scheme associated to<br />
a linearizer<br />
550 C F<br />
Thales Alenia Space + Un. Basque<br />
Country (E) + Un. Limoges (F) +<br />
Amcad Engineering (F) + United<br />
Monolithic Semicon<strong>du</strong>ctors (F)<br />
- Contracted 20703<br />
Y2006 T603-33ET Solid State Isolators based on GaN technology 400 C NL TNO + FBH(D) - Contracted 21854<br />
Page 72 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.6 - RF Payload System<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T603-33ET Solid State Isolators based on GaN technology 400 C UK Qinetiq+ComDev Europe (UK) - Contracted 21904<br />
Y2006 T603-37ET Future Multipurpose TT&C Systems & Techniques 300 C I Space Engineering - Contracted 21174<br />
Y2006 T603-39ET Design and Synthesis of a New Class of Receiver Filters 150 C E<br />
Un.Polit.Catalunya + Mier<br />
Comunicaciones (E)<br />
- Contracted 21398<br />
Y2006<br />
/<br />
Y2008<br />
T603-40ET<br />
Evaluation and validation of electromagnetic software, test facilities and test<br />
standards in Europe to predict and test RF breakdown and passive intermo<strong>du</strong>lation<br />
(PIM)<br />
530 DN/S Budget increased / PP change - Intended<br />
Total 6.6 - RF Payload System 400 739 500 850 1,480<br />
Page 73 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.7 - Electromagnetics Technology<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/EEA-00<br />
1<br />
Quasi Optical Modelling 250 DN/S DK Ticra - Contracted 18123<br />
Y2003<br />
03/EEE-00<br />
1<br />
Development of low frequency probes 150 DN/S DK TU Denmark - Contracted 18222<br />
Y2003<br />
03/EEE-00<br />
2<br />
Instrumentation for injecting current shaped waveforms 398 DN/S CH Montena - Contracted 18788<br />
Y2001 EEE-006 Novel Techniques For General Antenna Characterisation In The Time Domain 300 C - Intended<br />
Y2001 EEE-008 Spacecraft EMI control in the presence of composite materials 300 C(1) D<br />
HPS, Kayser Threde (D) + Mira,<br />
NPL (UK)<br />
- Contracted 18985<br />
Y2003<br />
ETM-192 /<br />
T-M-QCT-0<br />
6-FZ3<br />
Design of photonic crystals front-end (Photonic crystals: Material selection and<br />
fabrication)<br />
250 DN/C E U.P. Navarra + Sub in Competition - Contracted 15632<br />
Y2004 T603-27EE Secured link for TT&C antennas design phase 297 C(2) UK BAE Systems - Contracted 19674<br />
Y2004 T603-28EE RCS Quiet Zone Characterization at Millimetre Wavelengths 100 DN/S NL March Microwave Systems - Contracted 19230<br />
Page 74 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.7 - Electromagnetics Technology<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006 T605-01EE Advanced System Level Con<strong>du</strong>cted Emission Analysis and Simulation for EMC 250 C I<br />
Carlo Gavazzi<br />
Space+Terma(DK)+Polit. Milano(I)<br />
Operational<br />
SW<br />
Contracted 21051<br />
Y2006 T605-13EE Advanced System Level Radiated Noise Analysis and Simulation for EMC 250 C I<br />
Carlo Gavazzi Space+EM<br />
Software(D)+Polit.Milano(I)<br />
Operational<br />
SW<br />
Contracted 21215<br />
Y2006 T607-10EE European Antenna Modelling Component Library - Step 2 250 DN/C DK<br />
Ticra + IDS (I), SATIMO (F), and<br />
others<br />
Operational<br />
SW<br />
Contracted 18802<br />
Total 6.7 - Electromagnetics Technology 798 650 297 500 550<br />
Page 75 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.8 - System Design & Verification<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 EMM-004 Virtual spacecraft design (Ph.1&2) 2000 C(R) D<br />
EADS-Astrium, EADS-ST + ALS (I)<br />
+ EADS-Astrium (F)<br />
- Contracted 18699<br />
Y2006<br />
T504-15SR<br />
Technology reference and proof of concept for a space based Automated<br />
Identification System for maritime security<br />
500 100 DN/S N<br />
Norvegian Defence Research<br />
Establishment + subs<br />
- Contracted 20492<br />
Y2004 T605-05AC Grid-based distributed concurrent design (GDCD) 500 C(2) I<br />
Datamat + DNV, EPG (N) + Alcatel<br />
(F) + Alenia (I)<br />
- Contracted 19602<br />
Y2004 T605-06MT Virtual AIV Techniques for Virtual Integration of a Satellite in the Test Facilities 250 C(2) DK Terma - Contracted 18775<br />
Y2004 T605-15EM Space System Reference Model 200 C D Astrium (D,F) + Prostep (D) - Contracted 20396<br />
Y2006 T607-06EM System-Software Co-Engineering: Performance and Verification 500 C D<br />
Rhein-Westfal<br />
Tech.Hochschule+Thales(F)+Fond<br />
. Bruno Kessler (I)<br />
- Contracted 21171<br />
Y2006 T607-09SR Concepts for future spacecraft architecture and development approaches 800 C F Thales+Thales(I)+SSTL(UK) - Contracted 21214<br />
Y2006<br />
T607-12S<br />
W<br />
System of Systems analysis and design environment 500 C UK Vega+Thales(I) - Contracted 21254<br />
Page 76 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.8 - System Design & Verification<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T607-13S<br />
W<br />
Monitoring and Control Data Modelling 300 C I<br />
Space Software Italia + PNA<br />
Group(NL)<br />
Operational<br />
SW<br />
Contracted 22080<br />
Y2006<br />
T607-14S<br />
W<br />
Building Block Approach for EGSE 250 DN/C DK<br />
Rovsing + Dutch Space (NL) +<br />
Critical SW (P) + SciSys (UK)<br />
Operational<br />
SW<br />
Contracted 21321<br />
Total 6.8 - System Design & Verification 250 2,500 500 2,000 650<br />
Page 77 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.9 - Mission Control & Operations (GS Data Sys)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 GI-001 XML Framework 600 C(1) DK Terma + Siemens (A) - Contracted 18074<br />
Y2003 GSS-041 InP X-Band Cryo LNAs 200 DN/S E Fundae. Gen. - Contracted 17955<br />
Y2006 T603-34GI TC Authentication 300 C A Siemens<br />
Operational<br />
SW<br />
Contracted 20957<br />
Y2006 T603-34GI TC Authentication 300 C F Thales IS, Telin<strong>du</strong>s<br />
Operational<br />
SW<br />
Contracted 20956<br />
Y2006 T603-35GI Security communications for SLE services 250 C F Cap Gemini<br />
Operational<br />
SW<br />
Contracted 21281<br />
Y2004<br />
T605-07GI<br />
Feasibility of Automated Regression Testing for Space Systems Operational<br />
Software<br />
400 C A<br />
Siemens + Critical Software (PT) +<br />
Terma (DK)<br />
- Contracted 18898<br />
Y2004 T605-09GI N-Tier architectures applied to Ground Operations Systems 200 C D Terma - Contracted 20807<br />
Y2004<br />
T605-17GI<br />
European Technology Harmonisation on Ground Systems Software - First Set of<br />
Standard Interfaces<br />
500 C PT<br />
Critical Software + Dutch Space<br />
(NL) + Vega (D) + SciSys (UK) +<br />
GMV (E)<br />
- Contracted 19095<br />
Total 6.9 - Mission Control & Operations (GS Data Sys) 800 900 1,050<br />
Page 78 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.9 - Mission Control & Operations (GS Data Sys)<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
6.- Generic Technologies and Techniques<br />
6.10 - Flight Dynamics & Navigation<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T606-08GF<br />
Analysis of a Standardised Approach to the Emulation of the Highly Autonomous<br />
Avionics Systems of Interplanetary S/ C<br />
120 C D EDS - Contracted 19614<br />
Total 6.10 - Flight Dynamics & Navigation 120<br />
Page 79 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.11 - Mission Analysis & Space Debris<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T605-08GA Astro-toolbox: a toolbox for preliminary mission analysis 100 C E GMV + Un. Glasgow (UK) - Contracted 19617<br />
Total 6.11 - Mission Analysis & Space Debris 100<br />
Page 80 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.12 - Ground Station System & Networking<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T606-01GS Two-layer servo concept with movable BWG mirrors 250 C(1) I ADS International - Contracted 19515<br />
Y2004 T606-02GS Multipurpose Highly Stable System for Ground Station Characterisation 500 C E Indra Espacio - Contracted 19516<br />
Y2006 T606-06GS Experimental InP Ka band cryocooled LNAs 250 DN/C E<br />
Fundacion General de la<br />
Universidad + ETHZ (CH)<br />
- Contracted 20746<br />
Y2006 T606-06GS Experimental InP Ka band cryocooled LNAs 250 DN/C S Un. Chalmers - Contracted 20744<br />
Y2006<br />
T606-12GS<br />
Study and Breadboarding of a Sapphire Oscillator for Ultra-High Short-Term Station<br />
stability<br />
500 C F<br />
CNRS + Timetech (D) + National<br />
Physical Laboratory (UK)<br />
- Contracted 20135<br />
Total 6.12 - Ground Station System & Networking 750 500 500<br />
Page 81 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.15 - Mechanisms & Tribology<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/MMM-0<br />
01<br />
Self Contained Deployment Mechanism 850 DN/S N Kongsberg - Contracted 18770<br />
Y2007<br />
03/MMM-0<br />
01<br />
Self Contained Deployment Mechanism 200 DN/C N Kongsberg - Contracted 18770<br />
Y2003<br />
03/MMM-0<br />
02<br />
Integrated SADM+HDRM 650 DN/S N Kongsberg - Closed 18622<br />
Y2003<br />
03/MNT-00<br />
1<br />
Mirco Nano Satellite Technologies 500 DN/S S U. Uppsala - Contracted 18600<br />
Y2004<br />
T601-21M<br />
M<br />
APSEE: Arc Phenomena in Space Environment & Equipment 400 DN/S CH Meccanex + ONERA (F) - Contracted 18700<br />
Y2006<br />
T601-36M<br />
M<br />
Unlimited resetable, no-shock Hold-Down and Release Mechanism (HDRM) 350 C(1) A Austrian Aerospace - Contracted 21291<br />
Y2005<br />
T601-47MX<br />
AEA Technology (ESR<br />
/ MMM-960 Tribology Application Programme 200 200 200 200 DN/S UK Technology). Multi-year frame<br />
contract: 2007<br />
Operational<br />
SW<br />
Closed<br />
Y2006<br />
T608-31M<br />
M<br />
Fully Variable Bearing Active Preload System 450 DN/C UK ESR Technology - Contracted 20511<br />
Page 82 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.15 - Mechanisms & Tribology<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T608-32M<br />
M<br />
Angular position sensor based on MEMS technology 300 C(1) CH Ruag - Contracted 20404<br />
Total 6.15 - Mechanisms & Tribology 2,600 200 950 750<br />
Page 83 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.16 - Optics & Opto-Electronics<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002/<br />
Y2005<br />
MMO-670<br />
Materials for Ultra-Stable Lightweight Optical Benches and Mirrors (old <strong>title</strong>: Ultra<br />
lightweight Telescopes)<br />
600 88 C F<br />
Alcatel Alenia Space, Seso + ECM<br />
(D)<br />
- Contracted 20383<br />
Y2006<br />
T507-06M<br />
M<br />
Entangled photon source for Quantum Communications 250 C - Intended<br />
Y2004<br />
T609-05M<br />
M<br />
Instrument concepts using dynamic diffraction gratings (ICDDG) 200 C F Alcatel, LAS - Contracted 20519<br />
Y2004<br />
T609-05M<br />
M<br />
Instrument concepts using dynamic diffraction gratings (ICDDG) 200 C FIN VTT - Contracted 20532<br />
Y2006<br />
T609-16M<br />
M<br />
Advanced Side-pumping Technique for Double Clad Fiber Lasers 400 C(1) - Intended<br />
Y2006<br />
T609-17M<br />
M<br />
Programmable optoelectronic adaptive lens 250 C NL Cosine + Un. Durham (UK) - Contracted 21473<br />
Y2006<br />
T609-23M<br />
M<br />
Programmable micro-diffraction gratings 400 C(2) CH CSEM,INMI,LAS+Thales(F) - Contracted 21212<br />
T609-24M<br />
M<br />
Micro-optical beam delivery device for optical terminals for formation-flying cluster<br />
constellations<br />
C 250kE. Postponed. - Deferred<br />
Total 6.16 - Optics & Opto-Electronics 800 600 988<br />
Page 84 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.16 - Optics & Opto-Electronics<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
6.- Generic Technologies and Techniques<br />
6.17 - Aerothermodynamics<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004<br />
T601-25MP<br />
Development of advanced models and acceleration of Monte Carlo methods for<br />
simulation of rarefied gas dynamics<br />
200 C I Alta + HPCC (D) - Contracted 20169<br />
Y2007 T601-28MP Feasibility Demonstration of a European Space Propulsion Simulation Tool 398 DN/C E<br />
Empresarios Agrupados +<br />
EADS-ST (D), EADS-ST (F),<br />
Cenaero (B)<br />
Operational<br />
SW<br />
Intended 21490<br />
Y2006 T601-48MP Validation of aerothermo chemistry models for reentry applications 650 650 C<br />
UK +<br />
B<br />
(D) +Astrium(F),CEA DAM CESTA,<br />
CNRS, ISA, Lab<br />
EM2C+CNR-IMM(I)+IST(P) ///<br />
(21234) Von Karman Inst. + EPFL<br />
(CH) + DLR (D) + HPS (D) + Lab<br />
Operational<br />
SW<br />
Contracted<br />
Y2006<br />
T601-49MP<br />
Hypersonic facility instrumentation enhancements for improved flight extrapolation<br />
and scaling<br />
500 C F<br />
Onera Dsac + DLR (F) + Von<br />
Karman Institute (B)<br />
- Contracted 20719<br />
Total 6.17 - Aerothermodynamics 200 1,150 1,048<br />
Page 85 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.18 - Propulsion<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y1998 98/YPE01 SMART- 1 EPS Flight Equipment 126 DN/C F Snecma - Contracted 13516<br />
Y2002 GAD 3.10 Investigation Into MEMS - MEOMS Packaging 100 C - Intended<br />
Y2000 MPC-842 Green Propellants Phase 2 238 DN/C D EADS - Contracted 17929<br />
Y2000 MPC-842 Green Propellants Phase 2 238 DN/C F SNECMA - Contracted 17789<br />
Y2002 MPC-850 Hydrogen Storage Technologies 250 C N Prototech - Contracted 17925<br />
Y2001 MPE-878 New Grid System for Ion Engines (additional activities) 150 DN/C UK Qinetic, CCN - Contracted 16614<br />
Y2004 T505-02MP Development of a High Thrust Density cusped Plasma Thruster 600 DN/S D<br />
Thales. See<br />
<strong>ESA</strong>/IPC(2005)3,add.3<br />
- Contracted 20019<br />
Y2004 T505-09MP Hall-effect Thruster with Multi-Sectional Con<strong>du</strong>ctive Walls 360 DN/S F SNECMA + Alta - Contracted 20332<br />
Page 86 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.18 - Propulsion<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T601-02MP Development of advanced EP Thruster characterisation diagnostics 250 50 C I<br />
Aerospazio + Astrium, U. Giessen,<br />
U. Leipzig (D)<br />
- Contracted 20461<br />
Y2004 T601-02MP Development of advanced EP Thruster characterisation diagnostics 250 C I Alta - Contracted 20486<br />
Y2004 T601-17MP Development of a Circular Slit Field Emission Thruster 400 C I Alta +Alcatel, Snecma (F) - Contracted 20445<br />
Y2005 T601-31MP Advanced Technologies Demonstrator for Very High-Power Hall-Effect Thrusters 600 DN/S F SNECMA + Alta - Contracted 20332<br />
Y2006<br />
/<br />
Y2007<br />
T601-42MP Development of a fuel/oxidiser compatible diaphragm 500 DN/S UK MT Aerospace + subs - Intended<br />
Y2004 T608-25QC Reliability of MEMS based pressure sensors 250 DN/C N Presens - Contracted 18804<br />
Y2004 T608-27QC Methodology for complex Micro-Propulsion Systems Space Validation 120 C S Nanospace - Contracted 20720<br />
Y2004 T609-22MP Innovative Gas Storage in Satellites 300 DN/S N<br />
Prototech + IFE (Special measures<br />
for Norway)<br />
- Contracted 19399<br />
Total 6.18 - Propulsion 776 300 2,935 120 650<br />
Page 87 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.18 - Propulsion<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Page 88 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.19 - Structures & Pyrotechnics<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2002 MCS-001 Ultra light Structures - Phase 1 500 C(2) F<br />
EADS-LV + Zodiac, Ecole N.S.<br />
Lille, Ideamech, EADS-Astrium +<br />
MC Bernasconi (CH) + KDA (N) +<br />
IABG (D)<br />
- Contracted 18738<br />
Y2002 MCS-001 Ultra light Structures - Phase 2&3 1497 190 DN/C F EADS-LV (Team from Ph.1) - Contracted 18738<br />
Y2002 MCS-002 Electro Active Polymer Actuator 1,410 C I<br />
Kayser Italia,U. Roma,U. Pisa +<br />
DLR,HPS(D) +Risoe(DK)<br />
- Contracted 18548<br />
Y2006 T505-06MC Active Structures for Large Solar Array Panels 250 C D<br />
Astrium (D)+IABG(D)+TU<br />
Munich(D)<br />
- Contracted 22120<br />
Y2004<br />
T601-05MC<br />
Derivation of satellite equipment design and test specifications from random<br />
vibration environments<br />
200 C D<br />
Astrium (D,F,UK) + Alcatel (F) +<br />
Alenia (I)<br />
- Contracted 20502<br />
Y2004 T601-09MC Establishment of satellite mechanical shock design and verification guidelines 150 C F Alcatel, Astrium + Alenia (I) - Contracted 20503<br />
Y2004 T601-11MC Assessment and Improvement of Dynamic Test Data 250 C F<br />
Astrium, Intespace + Un. Kassel<br />
(D)<br />
- Contracted 20307<br />
Y2004 T601-14MC Random Vibration Environment derivation by Vibro-acoustic simulation 200 C D HPS + IABG(D) + ESI Group(D) - Contracted 20731<br />
Page 89 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.19 - Structures & Pyrotechnics<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2004 T601-14MC Random Vibration Environment derivation by Vibro-acoustic simulation 200 C E<br />
EADS Casa Espacio + Un. Pol.<br />
Madrid (E)<br />
- Contracted 20779<br />
Y2006 T601-46MC Vibro-Acoustic Analysis & Test methods for Large Deployable Structures 450 C NL<br />
Dutch Space + Un. Polit.<br />
Madrid(E)+01DB<br />
Metravib(F)+Thales Alenia<br />
Space(I)<br />
- Contracted 21805<br />
Y2006<br />
T601-50MC<br />
Advancement in Thermo-Elastic Distortion Verification Methods for spacecraft<br />
structures<br />
300 C<br />
Phase 1. (Ph2. in 2009, see <strong>TRP</strong><br />
2008-2010)<br />
- Intended<br />
Y2004 T605-11MC Non-Contact Measurements of Membranes 200 C(3) B Un. Liegi + TU Munich (D) - Contracted 20042<br />
Y2004<br />
T605-12MC<br />
Improvement of force limited vibration testing methods for equipment/instrument unit<br />
mechanical verification<br />
250 C(2) I<br />
Thales Alenia Space + Un.<br />
Leicester (UK) + Mecano (F) +<br />
IABG (D)<br />
- Contracted 20689<br />
Y2006<br />
T605-20MC<br />
Advancement of Mechanical Verification Methods for non-linear spacecraft<br />
structures<br />
300 C F<br />
Astrium+LMS(B)+Interspace(F)+As<br />
trium(UK)<br />
- Contracted 21359<br />
Total 6.19 - Structures & Pyrotechnics 1,910 1,497 990 650 1,300<br />
Page 90 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.20 - Thermal<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003 MCT-694 MST Compressor for JT cooler 400 DN/S UK RAL - Contracted 18248<br />
Y2002/<br />
Y2006<br />
MCT-698 Mini And Micro Heat Pipes 200 C B<br />
Revised description. Euro Heat<br />
Pipes + Astrium (D)<br />
- Contracted 21432<br />
Y2003 MCT-700 Regenerator Technology for 10-100K Stirling and Pulse Tube Coolers 600 DN/S UK RAL + CEA Grenoble (F) - Contracted 18771<br />
Y2003 MCT-701 Maxi compressor for low temperature cooler 500 DN/S UK Astrium,RAL - Contracted 19218<br />
Y2001 MCV-882 Thermal Concept Design Tool 200 C(1) I Blue Eng<br />
Open Source<br />
Code<br />
Contracted 18115<br />
Y2004 T601-04MC Thermal model correlation using genetic algorithms C Deferred, low priority. - Deferred<br />
Y2004 T601-24MC Novel, Composite Wicks (for two-phase loops) 350 C - Intended<br />
Y2006 T601-39MC Cryogenic Harness for Detector Arrays 350 C - Intended<br />
Total 6.20 - Thermal 1,200 500 900<br />
Page 91 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.20 - Thermal<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Page 92 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.22 - Components<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
03/QCT-00<br />
1<br />
Evaluation Thermistors 125 DN/S IRL Beatherm - Contracted 17827<br />
Y2001 GAD 1.01<br />
Process Development And Concept Validation Of Metamorphic High Electron<br />
Mobility Transistor Ph.2<br />
Deferred (low priority, 200kE) - Deferred<br />
Y2001<br />
GAD 2.06<br />
A<br />
Design And Evaluation Initiative For Rad Tolerant Components 600 DN/S F STM - Intended<br />
Y2001<br />
GAD 2.06<br />
C<br />
Reliability Assessment Of European Power Mosfets Phase 1 And 2 C(1) Deferred (low priority, 500kE) - Deferred<br />
Y2001<br />
GAD<br />
2.06.D<br />
Study Of RF Compression & Overdrive on Components 200 C - Intended<br />
Y2003 GAD 3.04 Testing of Chip Scale Package (CSP) 100 DN/S F Astrium - Contracted 14936<br />
Y2003 GAD 4.02 HDI demonstration Mo<strong>du</strong>le with CSP / ECR32 MCM Validation 150 DN/S F Astrium - Contracted 14936<br />
Y2003 QCA-004 Utilisation of the Proton Irradiation Facility (PIF) for Components Studies 550 DN/C CH PSI - Contracted 18465<br />
Page 93 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.22 - Components<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003 QCA-005 Utilisation of the Radiation Effects Facility (RADEXF) for Components Studies 330 110 110 DN/S Fin U. Jyvaskyla // Multi-year contaract - Contracted 18197<br />
Y2002 QCT-006 Component for high power conditioning applications (SiC, GaN, ) 500 C(1) E CRISA - Contracted 18755<br />
Y2004 T608-01QC Radiation Test methodology for Optocouplers Devices for Space Applications 150 DN/S F EADS-Astrium - Contracted 19623<br />
Y2004<br />
T608-05Q<br />
M<br />
Carbon Nanotube based composite Material 300 C(1) D<br />
HPS, Futurecarbon, NMW, EADS<br />
(D)<br />
- Contracted 19128<br />
Y2007<br />
T608-05Q<br />
M<br />
Carbon Nanotube based composite Material: additional testing 100 80 DN/C D<br />
HPS, Futurecarbon, NMW, EADS<br />
(D)<br />
- Contracted 19128<br />
Y2004<br />
/<br />
Y2007<br />
T608-24QC WALES: Wafer Level Encapsulation for micro-Systems 550 DN/S CH<br />
Y2004 T608-28QC MEMSRAD: MEMS sensitivity to space RADiation 300 C F<br />
Change of PP; budget increased.<br />
CSEM + LETI (F) + FGH (D) +<br />
IMEC (B)<br />
Astrium (F, D, UK), EADS-Astrium,<br />
Info<strong>du</strong>c + Lusospace (P) +<br />
Angstrom Aerospace Corp. (S) +<br />
Alcatel Alenia Space (F) + EADS<br />
(D)<br />
- Intended<br />
- Contracted 20293<br />
Y2006 T608-29QC Radiation testing of candidate microelectronic components for space applications 600 C - Intended<br />
Page 94 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.22 - Components<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2006<br />
T608-34Q<br />
M<br />
Performance benchmarking of European GaN epitaxial wafer suppliers 250 C D FBH, Tesat, UMS - Contracted 20328<br />
Y2006 T608-36QC SRAM based FPGA for space applications 300 C - Intended<br />
Y2006<br />
T608-37QC<br />
Study of long term parametric drifts of EEE components for inclusion in component<br />
detail specifications and worst case analysis<br />
250 C - Intended<br />
Y2006 T608-38QC Survey of available micro and nanotechnology 200 C UK<br />
NPL + Inst. Nanotechnology (UK)<br />
+ Esys (UK)<br />
- Contracted 21669<br />
Y2006 T608-39MC Nanotube re-inforced structural materials for spacecraft applications 250 C - Intended<br />
Y2006 T608-42ET Deep-Sub-Micron ASIC technology assessment and High-Speed-Serial-Links design 1200 C(R) F<br />
C(R) with Atmel (F) and STM (I/F).<br />
See <strong>ESA</strong>/IPC(2006)88. ST<br />
Microelectronics,<br />
Thales+ISD(GR)+Astrium(UK)<br />
- Contracted<br />
Y2006 T608-43QC GaN Reliability Enhancement and Technology Transfer Initiative (GREAT2) 1,800 C D<br />
See <strong>ESA</strong>/IPC(2006)89. T<strong>ESA</strong>T<br />
Spacecom + IMEC (B) + Ferdinand<br />
Braun Inst. (D) + FHG (D) + UMS<br />
- Contracted 21499<br />
(D)<br />
Y2001<br />
T-M-QCT-0<br />
2-MT<br />
MTSL Lab 150 150 DN/C IRL NMRC - Contracted 10582<br />
Page 95 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.22 - Components<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
T-S-QCA-0<br />
2-08<br />
Utilisation of the Heavy-ion Irradiation Facility (HIF) for Components Studies 373 150 DN/S B Un. Louvain // Multi-year contract - Contracted 12471<br />
Y2003<br />
T-S-QCT-0<br />
2-FZ4<br />
Micro-Optical Electromechanical Systems (MOEMS) Delta Space Qualification<br />
Methodology (Critical evaluation techniques for micromachined devices)<br />
300 C(2) F Alcatel - Contracted 18669<br />
Total 6.22 - Components 2,428 710 800 1,540 4,750<br />
Page 96 of 97
<strong>TRP</strong> Work Plan 2005-2007<br />
Complete List of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.- Generic Technologies and Techniques<br />
6.23 - Materials & Processes<br />
IPC<br />
Appr.<br />
<strong>TRP</strong> Ref. Title Budget (K€) PP C'try Remarks<br />
SW Clause<br />
applicability<br />
Status as of Contract<br />
2004 2005 2006 2007 2008 31/12/2008<br />
Y2003<br />
(03/)EEA-0<br />
02<br />
Metamaterials for Space 250 DN/S CH EPFL - Contracted 18545<br />
Y2006<br />
T608-04Q<br />
M<br />
Assessment of the reliability of High Density Integrated Boards (HDIs) for future<br />
space use<br />
250 C - Intended<br />
Y2006<br />
T608-12Q<br />
M<br />
Study of the impact of the power meshed plane on electromagnetic behaviour of<br />
electronic boards (PCBs).<br />
160 C - Intended<br />
Y2006<br />
T608-15Q<br />
M<br />
Test and validation of contamination models through ground experiments modeling 200 DN/S F Onera - Intended<br />
Y2006<br />
T608-30Q<br />
M<br />
Joining technology to bond Carbon to Carbon in stable sandwich structures 250 DN/S F Alcatel + Snecma - Contracted 20479<br />
Y2006<br />
T608-33Q<br />
M<br />
Radiation stable optical adhesives 300 C D ZARM Technik + FHG (D) - Contracted 20784<br />
Total 6.23 - Materials & Processes 250 250 300 610<br />
Page 97 of 97
f<br />
Chapter 3<br />
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.- Earth Observation<br />
1.1 - Data exploitation<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T101-07GD<br />
Image Information Mining<br />
This activity shall identify and implement demonstrators of Image Information Mining methods, in particular for change<br />
detection, applicable to medium resolution SAR or optical sensors, addressing all aspects from preparation of data in the<br />
archives up to semantic classification of images and of extracted information or accompanying text. Tasks include:<br />
Requirements, trade-offs of potential new concepts, feasibility assessment, demonstrators and evaluation, system<br />
architecture.<br />
Deliverables:<br />
Software demonstrator and <strong>document</strong>ation.<br />
Current TRL: Target TRL: Prototype Application Need/Date: SW operational by 2009<br />
Application/Mission: EO image archieves Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-572, T-7699<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T101-08GD<br />
Title:<br />
Mission Planning for Constellations and Multi-use<br />
Implementation of demonstrators to identify the critical issues and demonstrate the feasibility of possible solutions for quasi<br />
conflict-free planning of payload acquisitions for missions based on satellite constellations and serving different user<br />
communities (e.g.: civil, military, institutional, research, etc.). The demonstrators, solutions, and scenarios will take into<br />
consideration the experience made by <strong>ESA</strong> in parallel planning ERS-1, ERS-2, and Envisat for different user communities with<br />
various priorities, and in implementing and testing a multi-mission conflict re<strong>du</strong>ction planning tool. The project shall also take<br />
into account the need of the forthcoming constellations of EO satellites.<br />
Deliverables:<br />
Software and test scenarios.<br />
Current TRL: Target TRL: Prototype Application Need/Date: SW operational by 2008<br />
Application/Mission: GMES Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-536<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 1 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T101-09GD<br />
EO data archives: Improved access and presentation<br />
The objective of this activity is to identify, implement and test new methods for easing user access to archived data via<br />
advanced technologies permitting multi-mission, integrated search, browsing and direct access to data or information (also<br />
extracted in real time), best supporting (also as indicated by system suggestions) user applications, maintaining an high level<br />
of system security. The system should make simple for the user to obtain only the necessary information at the highest<br />
possible level, with the minimum of additional effort, and in formats compatible (and as transparent as possible) with his<br />
application or process.<br />
Deliverables:<br />
Study analysis report, System Design Documents, Demonstration system.<br />
Current TRL: Target TRL: Prototype Application Need/Date: SW operational by 2009<br />
Application/Mission: EO data archieves Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-539<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 2 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.2 - Microwave Instruments<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-01EE<br />
Multi-frequency feeds for Earth Observation applications<br />
This activity should study feed concepts that can operate in several frequency bands, with wide-band, <strong>du</strong>al polarisation<br />
capability, and compact volumes, for usage in remote sensing instruments such as radiometers, radars and altimeters. It<br />
should be mentioned that depending on frequencies separation and bandwidth involved very different feed concepts have to<br />
be considered. This justify the need to consider several design.<br />
Deliverables:<br />
Feed concepts for multi-frequency operation capability.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Post EPS radiometer Contract Duration: 14 months<br />
SW Clause : - Dossier0 Ref.: T-7612<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T102-03EE<br />
Rigorous numeric techniques applied to microwave interaction with natural targets:<br />
Title:<br />
volume scattering<br />
The main objective of this activity is to review the validity of microwave interaction models with natural targets that in<strong>du</strong>ce<br />
volume interaction. This aims at assessing their limitations in terms of range of input parameters, quantifying their accuracy<br />
and - whenever possible - providing insight on possible improvements. Based on theoretical considerations, the first objective<br />
shall be the assessment of the validity range of the simplified approaches. The second objective is to implement a numerical<br />
test facility, which would give the possibility of validating asymptotic approaches. The third objective is - at least for the<br />
application cases described above, and based on the test facility - to derive the validity range and the limitations of the current<br />
approximate models. The fourth objective is to propose possible improvements to the asymptotic solutions or to propose<br />
alternative solutions to obtain results closer to reality.<br />
Deliverables:<br />
Data package including the demonstration software of the asymptotic approaches used in the study as well as a downsized<br />
version of the numeric "test facility".<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: SW operational by 2009<br />
EO and Planetology microwave<br />
Application/Mission: Contract Duration: 24 months<br />
Instruments<br />
SW Clause : Open Source Code Dossier0 Ref.: T-7769<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 3 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-04EE<br />
KU Band SAR Snow Measurements for Snow Applications<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T102-05ET<br />
Title:<br />
Microwave Photonics Millimetre-wave Generation<br />
The trend in terrestrial communications has been to faster and faster data rates, now well into the tens of Gigabits per second<br />
range. This has led to the development of very high speed components primarily dedicated to digital communications.<br />
However, those components could also be used in the analogue domain (i.e. GHz instead of Gb/s).The aim of this activity is to<br />
evaluate the feasibility of broadly tunable high frequency generation (tens of GHz) based on microwave photonics<br />
implementation. This is of interest for millimetre and sub-millimetre-wave LO generation and distribution.<br />
Deliverables:<br />
Microwave photonics high frequency generation demonstrator<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: mm/sub-mm missions (e.g. PREMIER) Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Passive Millimetre and Submillimetre wave Instruments (no RM)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-07ET<br />
P-Band Ice Sounding Radar Demonstrator Development<br />
The objective of the activity is to perform a feasibility study on ice-sounding radars in order to:- Trade-off system parameters-<br />
Select the most suitable transmit pulse characteristics and waveform.- Examine nadir and off-nadir surface ambiguity<br />
suppression techniques.- Make a performance analysis over simulated representative target (best knowledge of Antarctic<br />
ice-sheet and bedrock).The study will conclude with the development of a hardware demonstrator in the form of a P-band<br />
ice-sounding instrument developed using COTS equipment which eventually might be suitable for mounting on-board an<br />
aircraft for a possible future campaign to verify the findings of the study and to pave the way for a space borne ice-sounding<br />
mission.<br />
Deliverables:<br />
A P-band ice-sounding instrument developed using COTS equipment suitable for mounting on-board an aircraft.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL6 by 2009<br />
Application/Mission: P-band Ice Sounding Radar Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7625<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 4 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-10ET<br />
GaN Highly Efficient HPA for X- and Ku-band SAR and Altimeter Applications<br />
Semicon<strong>du</strong>ctor components based on GaN material have already demonstrated unparalleled performances on laboratory<br />
level compared to classical GaAs based materials. The prospects are impressively good. The material properties are ideal for<br />
radar applications. Power levels can be achieved, which were in former times the domain of vacuum devices like travelling<br />
wave tubes.<br />
Within the framework of this activity an HPA device shall be designed, manufactured and tested for demonstration of high<br />
power handling capability at X and Ku-band.<br />
Deliverables:<br />
Technology demonstrator with the usual <strong>document</strong>ation<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: future SAR and altimeter missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-737<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Critical RF Payload Technologies<br />
<strong>TRP</strong> Reference: T102-11ET<br />
Title:<br />
GaN Self Protected LNA for X- and ku-band Radar Applications<br />
Semicon<strong>du</strong>ctor Components based on GaN material have already demonstrated unparalleled performances on laboratory<br />
level compared to classical GaAs based materials. The prospects are impressively good. The material properties are ideal for<br />
radar applications. GaN is very often only proposed for high power applications, although the material has excellent noise<br />
properties very close to GaAs based materials. The high breakdown voltage is of great importance because this allows save<br />
operation in the vicinity of high power levels, typical for all Radar applications. Limiter always needed in conjunction with GaAs<br />
devices will become unnecessary or only very simple device. Noise figure is going to improve. Furthermore if considered for<br />
integration in T/R Mo<strong>du</strong>les The power device and the LNA can be integrated on the same chip. Two chip or even single chip<br />
T/R mo<strong>du</strong>les become feasible with corresponding cost advantages.<br />
Deliverables:<br />
Tested demonstrator LNAs with and without on chip limiter in X and Ku band. Design and Test Documentation.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: future SAR and altimeter missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7737<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Critical RF Payload Technologies<br />
<strong>TRP</strong> Reference: T102-12EE<br />
Title:<br />
Innovative Low-loss FSS structures<br />
The objective of this activity is to develop an accurate computer model to design multi-layer mesh filters. The simulation tool<br />
will account for the effects of non-perfect element shapes, metal con<strong>du</strong>ctivity and slot thickness. Investigate potentially<br />
suitable novel materials and micromachining techniques and create controllable and repeatable fabrication routes with suitable<br />
structural properties. Investigate potentially suitable techniques to make all-metal FSS structures and create controllable and<br />
repeatable fabrication routes with suitable structural properties. This should be followed by preliminary fabrication trials and<br />
process optimization. Measurements will be performed to quantify the efficiency improvement and increased out of band<br />
rejection. If applicable, existing prediction tools will be updated to explain discrepancies with theory and experiment.<br />
Deliverables:<br />
FSS hardware, prediction tools, full performance report.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL4 by 2010<br />
Application/Mission: mmWave sounders, imagers Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-326<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 5 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-14ET<br />
LNAs for mm-waves<br />
Objective of this activity is the development of low-noise amplifiers (LNAs) with improved noise performance for 183/220 GHz<br />
for application in future atmospheric sounders. Recent developments in Indium Phosphide (InP) and metamorphic (MHEMT)<br />
technologies have made LNAs possible for the frequencies above 100 GHz. First demonstrations, however, did not have<br />
sufficiently good noise performance. In addition to re<strong>du</strong>cing the gate length close to 50 nm, optimisation of the fabrication<br />
process and device structure and geometry are needed for improvement. This activity aims to take benefit of the on-going<br />
developments of low-noise MMIC processes towards higher frequencies, and develop an LNA with improved noise<br />
performance.<br />
Deliverables:<br />
LNA Breadboard<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Post-EPS, MTG Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-326<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T102-16ET<br />
Title:<br />
HBV multipliers for high power and high frequency<br />
HBV multipliers are developed aiming at achieving high power capability at mm/sub-mm waves with high efficiency. One<br />
important advantage of Heterostructure Barrier Varactors (HBVs) over Schottky varactors is the possibility of tailoring the<br />
device to a desired power level by epitaxially cascading an appropriate number of barriers. This capability has never been<br />
explored in detail. An on-going <strong>TRP</strong> activity aims at achieving the understanding of the power limiting mechanisms, and to<br />
perform the initial development of HBV devices for very high power level. In the proposed activity, the objective is to reach an<br />
output power capability around 1 W at 100 GHz by further development of the multi-barrier devices, and establishing a<br />
suitable mounting technique. A demonstrator employing one or more of these devices will be designed, manufactured and<br />
tested.<br />
Deliverables:<br />
HBV Multipliers demonstration model<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012<br />
all heterodyne instruments at<br />
Application/Mission:<br />
mm/sub-mm, Post-EPS, MTG<br />
Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-326, T-7712, T, 424<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Passive Millimetre and Submillimetre Wave Instruments<br />
Page 6 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-17ET<br />
Integrated Schottky structures<br />
Schottky diodes are generic components that are used in practically all millimetre and sub-millimetre wave receivers. They are<br />
especially critical to future Earth observation instruments. At the highest frequencies Schottky circuits (mixers, frequency<br />
multipliers) have to be realised as integrated structures and tailored to the specific application, in routes that allow the<br />
integration of sub-micron Schottky diodes with matching and coupling circuitry on a suitable substrate (e.g. membrane or<br />
transferred substrate). The most promising technology approach will be used to realise waveguide demonstrators for<br />
frequencies above 300GHz.<br />
Deliverables:<br />
Mixer and multiplier demonstrators in waveguide package<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2012<br />
Post-EPS, MTG, Sentinels 45, CIWSIR,<br />
Application/Mission: Contract Duration: 24 months<br />
Premier, GOMAS<br />
SW Clause : - Dossier0 Ref.: T-7711<br />
Consistency with Harmonisation<br />
Passive Millimetre and Submillimetre Wave Instruments<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-18ET<br />
New Investigations of RF breakdown in microwave transmission lines<br />
Micro-strip and bar-line are two types of transmission lines, which are nowadays used in many space components because of<br />
their low loss and re<strong>du</strong>ced weight. However, these transmission lines, located between the RF output amplifier and the<br />
transmitting antenna are prone to suffer from RF breakdown <strong>du</strong>e to the high RF power levels generated by the transistors in<br />
the Solid State Amplifier (SSPA). Breakdown in these components implies, in most of the cases, the lost of the RF chain and,<br />
in some cases, even the lost of the mission. Many of the existing and future space programs (Envisat, Terrasar, Galileo,<br />
Metop, ATV, etc.) include high power SSPA in their payloads. The output section of these amplifiers and several of the<br />
components, which drive the RF signal towards the antenna are made of micro-strip and bar-line technology. The RF<br />
performance of these payloads is limited by the power handling of the components using this technology. A mo<strong>du</strong>lar software<br />
tool compatible with existing general electromagnetic software shall be pro<strong>du</strong>ced to simulate and prevent the multipactor and<br />
corona breakdown in these two transmission lines would imply a significant step not only in the investigations of these two<br />
unwanted phenomenon, but also would have a a great impact in the design and testing process of all high power components<br />
based on this technology.<br />
Deliverables:<br />
Software simulation tool for micro-strip and bar-lines; a number of representative samples on both technologies; final report on<br />
all theoretical and testing investigations<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Telecom, EO Contract Duration: 18 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-7829<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 7 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-22ET<br />
Active calibration for radiometers<br />
The principle of the use of the active cold load (ACL) for radiometer calibration has already been preliminarily demonstrated at<br />
X-band (10.7 GHz ) by a bredboard (Contract 18907). This proposed activity is aimed to further enhance and demonstrate the<br />
ACL concept towards higher frequencis and potential applications especially in Earth Observation. Important possibilties are<br />
foreseen in passive EO systems at frequencies between 18 to 37 GHz where significant mass, power, and cost re<strong>du</strong>ction<br />
could be achieved by substituting the currently used mechanically switched quasi-optical calibration systems by the use of<br />
electrically switched solid-state calibration ACLs.<br />
On the other hand, the use of an ACL could be advantagious when integrated into a quasi-optical cold calibration target which<br />
would give more freedom in the mechanical design and calibration routines by avoiding the need for frequent sky calibration.<br />
The activity first aims at investigating suitable technologies that are adequate to ACLs at frequencies from 18 to 37 GHz<br />
(MMIC vs. disctere, M/InP-HEMT, HBT...). Secondly, the ACLs are designed and breadboarded to demonstrate the capability<br />
of the ACLs to be used as replacements of mechanical calibration systems in the future. Both coaxial and quasi-optical ACLs<br />
will be implemented to demonstrate the benefits of the concept for different types of radiometer front-ends.<br />
Deliverables:<br />
Cold load demonstrator<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2015<br />
Application/Mission: GEOsounder, Post-EPS Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-423<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T102-23EE<br />
Title:<br />
P-band SAR wave interaction and information retrieval<br />
P-band SAR has been considered a potential tool for measuring forest biomass since the 1980s. Its proponents claim to offer<br />
a larger dynamic range than possible with shorter wavelengths. Qualitatively that seems correct, but limited quantitative<br />
assessments and immature physical understanding do not help us quantify its scientific value. The study develops<br />
physically-based wave interaction and retrieval models appropriate to P-band and to high biomass forests. The observational<br />
and theoretical basis for P-band will be reviewed. A scattering model is to be developed in order to evaluate the sensitivity of<br />
polarimetric P-band signals to forest, soil and environment variables. A sensitivity analysis will be con<strong>du</strong>cted, using the<br />
forward model to identify key drivers for backscatter. The potential accuracy of a universal retrieval algorithm is to be<br />
assessed through the review and the modelling.<br />
Deliverables:<br />
Identification of scientific observational drivers and tresholds. Physical model appropriate to P-band. Identification of key<br />
scattering components and their relationship to biomass. Assessment of retrieval algorithms and their use in potential mission.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Future P-band SAR missions. One of<br />
Application/Mission: the Earth Explorer candidate missions is Contract Duration: 12 months<br />
covering this type of measurements<br />
SW Clause : - Dossier0 Ref.: T-7625<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 8 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-28ET<br />
Development Schottky MMICs for high frequencies<br />
Schottky diodes are generic components that are used in practically all millimetre and sub-millimetre wave receivers. They are<br />
especially critical to future Earth observation instruments. Since the availability of Schottky technology for frequencies above<br />
100 GHz is very limited (single U.S. supplier), it is important to develop a European source.<br />
United Monolithic Semicon<strong>du</strong>ctors (UMS) is a European GaAs foundry that has a dedicated Schottky MMIC process<br />
commercially available for applications below 100 GHz. Preliminary studies have indicated that it is possible to intro<strong>du</strong>ce<br />
modifications that will improve the performance at higher frequencies, without changing the core fabrication process.<br />
The aim of this activity is to investigate theoretically and experimentally such modifications, develop the device design and the<br />
necessary processing steps, and demonstrate the improved performance at 200/300 GHz.<br />
The activity will include a theoretical study for diode optimisation using device and EM simulators, design of the discrete<br />
devices and MMIC Demonstrators, fabrication run(s) using the BES process of UMS, process experiments for different<br />
modifications in the fabrication, and the design, construction and characterisation of the Demonstrators. The Demonstrators<br />
will consist of discrete devices and fully functioning MMICs (mixer/multiplier) for 200/300 GHz. At least one MMIC will be<br />
mounted and characterised in a waveguide housing.<br />
Deliverables:<br />
Characterised Demonstrators (discrete devices and MMICs). Definition of processing modifications.<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: EO, Sience Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7711<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T102-29ET<br />
Title: Active Receive-Only Digital Front-End for Radar and SAR - Phase 1 & 2<br />
Traditional SAR design has a well-known limitation between resolution and swath width, which have to be traded-off. A way<br />
out of this limitation is in the intro<strong>du</strong>ction of a bi-static approach with separated transmit and receive antenna, mounted on the<br />
same platform. This leads to the novel high-resolution wide swath approach for SAR, which makes use of innovative digital<br />
beam forming <strong>du</strong>ring receive and solves in this way the well known restriction.<br />
- Within phase 1 of the proposed activity a SAR system design based on this new concept shall be carried out. The key<br />
system performance parameters have to be determined by simulation and evaluated in comparison to traditional approaches.<br />
Critical components and subunits needed for a front-end demonstrator have to be identified and specified.<br />
- In phase 2 of the activity the critical components and subunits have to be breadboarded and feasibility shall be<br />
demonstrated. The scan while receive function, the key feature, has to be demonstrated.<br />
Deliverables:<br />
Fully tested Digital Rx-only Tile Demonstrator. Documentation.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL6 by 2010<br />
Application/Mission: SAR Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7752<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 9 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-30EE<br />
Next Generation L/S band SSPA Demonstrator for Radar<br />
The objective of the activity is the design, manufacturing and test of SSPAs (Solid State Power Amplifier) at L and S-band<br />
using advanced European microwave power technology. Newly available GaAs HBT and wide bandgap technologies under<br />
development now ( SiC, GaN) are good candidates for the development of very high power(i.e. over 50 watt) and thermally<br />
robust SSPAs that will represent a breakthrough on power capabilities at L and S band.Special attention shall be given to the<br />
packaging problems associated with the high power levels involved.These SSPAs shall demonstrate high power capabilities<br />
and good thermal properties. Possible applications are on next generation SAR antennas, active array antennas operating at<br />
L and S band.<br />
Deliverables:<br />
Fully tested elegant breadboard of very high power (over 50 watt) L and S band SSPA.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2009<br />
Application/Mission: L- band Radar Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7825<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T102-32EE<br />
Title:<br />
Understanding directionality in surface scattering by imaging radar<br />
The work will provide a more comprehensive extension of current approaches to electromagnetic modelling of radar-soil<br />
interactions, making use of explicit directional descriptions of soil roughness power spectra. The use of such power spectra,<br />
or reasonable parameterisations of them, within scattering models is intended to replace the trivial omni-directional<br />
descriptions now widely used, and allow for clarity in identifying the key interaction physics. This clarity of physical interaction<br />
is at the heart of this work and a key output will be the identification of the most important (directional) spectral ranges of soil<br />
roughness that determine backscatter and the role of other scales up to and beyond the resolution scale of the radar<br />
instrument. Benefit will be taken from currently running GSP activity on numerical validation of surface scattering models.<br />
Experimental demonstration, either from historical ERS-1/-2 or Envisat datasets plus relevant observations of soil roughness<br />
will be required to support the theoretical aspects of this work. Such datasets exist within a number of European groups.<br />
Deliverables:<br />
Demonstration software incorporating explicit directional effects for microwave soil scattering. Recommendations for<br />
strategies to avoid or mitigate retrieval errors associated with unforeseen directional artefacts in future satellite SAR data.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2008<br />
Imaging radar missions (e.g. Sentinel-1,<br />
Application/Mission: Contract Duration: 18 months<br />
Envisat/ASAR)<br />
SW Clause : - Dossier0 Ref.: T-51<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
Page 10 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-41ET<br />
Altimetric Measurements of 2D Ocean Surface Currents<br />
Understanding of ocean circulation and currents is of special importance to oceanographers and climatologists. Conventional<br />
altimeters provide highly accurate measurements at the sub-satellite point, but this coverage is insufficient for faster changing<br />
currents, eddies and, in particular, coastal areas, which also suffer from land contamination in the signal. Along track SAR<br />
interferometry (ATI) is one way in which surface currents can be derived and dedicated systems to do this have been<br />
proposed in the past. ATI though only provides one ocean surface current vector - orthogonal to the direction of flight. This<br />
approach is extended in <strong>ESA</strong> patent 511, which describes a technique for deriving 2D ocean surface currents using two<br />
antennas pro<strong>du</strong>cing four squinted beams each. While the basics for the technique are outlined in the patent, a further system<br />
study should be performed in order to optimise all the system parameters, perform modelling and determine performance<br />
parameters for frequencies from X- to Ka-band as well as the potential of formation flying two satellites in order to realise the<br />
desired along and accross track baselines.<br />
Deliverables:<br />
Basic system design (or designs) of the instrument for measurement of 2D Ocean Surface Currents.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2015<br />
Application/Mission: Future ocean missions Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-8153<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T102-43ET<br />
Title:<br />
Integrated Receiver and ADC for Active Array SAR<br />
Next generation spaceborne SAR will utilise digital beam forming techniques to improve performance and flexibility. For this<br />
application early down conversion and medium number of bit digitalisation on subarray level would be needed. Power<br />
consumption is crucial while high bandwidth is needed. New semicon<strong>du</strong>ctor technologies based on SiGe have the potential to<br />
integrate digital and analogue functions on the same chip with low power consumption.<br />
Within the activity an integrated receiver and medium number of bits A/D converter shall be designed manufactured and<br />
tested in order to prove the concept for next generation of SAR instruments.<br />
Deliverables:<br />
Technology demonstrator and <strong>document</strong>ation<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Future SAR missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7752, T-7602<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
Page 11 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-44ET<br />
Research into GPS Sea-Ice and Dry Snow Reflectometry<br />
Sea-Ice applications:<br />
Reflected GPS signals obtained over sea-ice <strong>du</strong>ring airborne campaigns and via the UK-DMC satellite suggest that phase<br />
coherency can be maintained for some time allowing accurate altimetry to be performed. UK-DMC data however, suffers from<br />
poor datation and relatively low SNR whereas airborne data is limited, expensive to acquire and provides only a snapshot of<br />
ice conditions. In order to investigate fully the potential for GNSS Reflectometry to derive sea-ice parameters including<br />
freeboard a longer term alternative needs to be found. This could be in the form of mounting up and down looking GPS<br />
antennas at a suitable location overlooking sea-ice e.g. Zeppelin Mountain on Svalbard, and then collecting and analysing<br />
data over a protracted period, say 6 months. The resultant dataset would be invaluable in determining the ability of GNSS-R<br />
techniques to retrieve sea-ice parameters.<br />
Dry-snow applications:<br />
Dome Concordia in Antarctica is currently being investigated for its suitability as a calibration site for SMOS. The extremely<br />
dry snow with minimal precipitation each year, make it very attractive for this purpose. To test this a radiometer has been<br />
mounted on a tower at Dome C. Research into GPS Reflectometry over land has shown that provided the moisture content<br />
does not change then the forward scattering of GPS signals correlates extremely well over the same ground-track on different<br />
days. Since L-band penetrates many metres into dry snow, by mounting a down-looking GPS on the same tower at Dome C,<br />
a dataset could be built up over time showing L-band forward scattering as a function of incidence angle at this location. This<br />
would be of great interest to scientists and add insight into the radiometer retrieved signal. In addition, if both L1 and L2<br />
reflections could be captured then high accuracy TEC maps could be generated for the area.<br />
Deliverables:<br />
Long-term GPS-R dataset collected from a fixed position over sea-ice. Data analysis for altimetric purposes and ice<br />
properties.<br />
Dataset of L-band forward scattering as a function of incidence angle over the SMOS calibration site Dome C, Antarctica. High<br />
resolution TEC maps for the sky above Dome C.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Future altimeter/ice mission, SMOS /<br />
Application/Mission: Contract Duration: 18 months<br />
SMOS ops<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
N/A<br />
Roadmap and Conclusions:<br />
Page 12 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T102-45ET<br />
Advanced SAR-Instrument based on Digital Beamforming<br />
Next generation high performance SAR systems will benefit from digital beamforming techniques to overcome limitations<br />
related with tolerance and temperature stability problems inherent with classical analogue implementations. Digital<br />
implementation of beamforming opens the door to new modes of operation such as scanning on receive, adaptive pattern<br />
nulling and multibeam capability. Major parts of this kind of radar electronics can be reused in other radar bands because it is<br />
inherently frequency independent.<br />
First <strong>ESA</strong> internal investigations have shown feasibility of such SAR front-ends in terms of processing speed and power<br />
consumption.<br />
New advanced analogue and digital semicon<strong>du</strong>ctor technologies (GaN, SiGe, deep sub-micron) meanwhile available or under<br />
development for ground based commercial telecom and military systems are beneficial for implementing such kind of system.<br />
The compatibility of these technologies with the environmental conditions in LEO applications has to be investigated.<br />
Digital implementation of beamforming would open the door to further optimisation of instrument architecture, making it<br />
possible to simplify the remaining analogue part of the system in terms of development and integration.<br />
The main objective of the study will be to elaborate the performance improvements and/or cost re<strong>du</strong>ctions expected from<br />
utilisation of digital beamforming and advanced technologies for next generation instruments, staggered in mid- and long-term<br />
time scale.<br />
The following work has to be performed in order to meet the objective:<br />
- Definition of key performance figures and functional requirements for next generation SAR systems for different applications.<br />
- Survey on advanced technologies available and under development suitable for SAR systems based on digital beamforming.<br />
- Instrument architecture trade-off and optimisation for taking maximum benefit from the identified digital implementation<br />
possibilities.<br />
- Establishment of a conceptual design together with estimate of power, mass and thermal figures, and assessment of<br />
performance.<br />
- Definition of technology roadmaps identifying development needs of critical parts for implementation of advanced<br />
instruments.<br />
- Outline of a Breadboard for the proof of critical elements as potential next step.<br />
Deliverables:<br />
- Technical note on technologies for advanced SAR<br />
- Technical note on advanced architectures<br />
- Technical note on implementation roadmaps<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5/6 by 2013<br />
Application/Mission: Advanced SAR Systems Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7736<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
N/A<br />
Page 13 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T104-17EE<br />
Bio- & geo-physical retrieval algorithm definition for active remote sensing of land<br />
Title:<br />
surfaces at P- and L-band<br />
This project aims to define, demonstrate and assess algorithms for the retrieval of a set of bio- and geo-physical parameters<br />
from observations that include a strong contribution from L-band SAR.<br />
A set of bio- and geo-physical parameters will be selected, based on perceived scientific or operational need and on expected<br />
feasibility. These are expected to include (but not be limited to) forest and other vegetation biomass, soil moisture, snow<br />
water equivalent. Targets for operational effectiveness of retrieval algorithms shall be identified at the outset.<br />
The work will take advantage of previous research on the refinement of wave interaction models and descriptions of the<br />
natural surfaces and vegetation appropriate to these wavelengths. New and independent developments of interaction models<br />
are not expected. Here, state-of-the-art descriptions and interaction models are to be used to construct, refine and predict the<br />
robustness of quantitative retrieval algorithms.<br />
The project will require validation experiments to be analysed. These are expected to be based on P- and L-band airborne<br />
and, where possible, satellite datasets plus complementary remote sensing and other data or knowledge. In particular, data<br />
from recent <strong>ESA</strong> led airborne campaigns and from Japan’s ALOS satellite (PALSAR instrument) should be a significant input<br />
to the study.<br />
Although not the focus of work at this stage of maturity, initial consideration of assimilation into land surface process models<br />
would be encouraged as a theme setting the scene for future study activities.<br />
Deliverables:<br />
Prototype algorithm<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: SW operational by 2009<br />
Application/Mission: Biomass mission / Habitat Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
Page 14 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.2.1 - Microwave Equipment & Antennas (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETM-157<br />
HBV devices<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7711<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETP-111<br />
Novel Simulation Interferometric radar altimeter<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-383<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ETP-137<br />
Title:<br />
PARIS: additional work<br />
This activity aims at the development of the receivers and the signal processor (complex correlator unit) which would provide<br />
the power versus delay waveforms that carry the information on the geophysical parameters (ocean height, ocean wind,<br />
significant wave height and TEC). This activity will comprise the breadboarding and testing of the breadboard, according to the<br />
requirements defined <strong>du</strong>ring the concept definition study.<br />
Deliverables:<br />
Breadboard (+testing).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL6 by 2009<br />
Application/Mission: GNSS-R Contract Duration: 14 months<br />
SW Clause : - Dossier0 Ref.: T-7734<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 15 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
ETP-137.A<br />
Title: PARIS Technology Concept Definition/Integration - Phase 2<br />
The study was divided into two phases. In Phase I the scientific requirements for mesoscale ocean altimetry have been<br />
reviewed and the concept of the PARIS altimeter instrument has been defined, including the requirements for the related<br />
building blocks. During the current Phase II these building blocks will be integrated into the PARIS airborne sensor<br />
demonstrator, including testing of the demonstrator.<br />
Deliverables:<br />
Technical note. Sensor demonstrator (+testing).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL6 by 2009<br />
Application/Mission: GNSS-R Contract Duration: 14 months<br />
SW Clause : - Dossier0 Ref.: T-7734<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ETP-137.B<br />
Title:<br />
PARIS multi-beam array<br />
Navigation signals are weak and therefore a multi-beam antenna followed by a beam-former is needed. Navigation signals are<br />
narrow in bandwidth which means averaging and/or phase processing is needed to get altimetry accuracy below 10 cm. The<br />
main objectives of this activity are the design, breadboarding and testing of a multiple-beam array according to the<br />
requirements defined <strong>du</strong>ring the concept definition study. The most promising solution shall be identified , following an initial<br />
trade-off among different antenna solutions based on PARIS operational scenarios, the selection and preliminary design of a<br />
couple of promising candidate.<br />
Deliverables:<br />
Technical Note. Breadboard.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL6 by 2009<br />
Application/Mission: GNSS-R Contract Duration: 14 months<br />
SW Clause : - Dossier0 Ref.: T-7734<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ETP-137.C<br />
Title:<br />
Beam Forming Networks for PARIS Concept<br />
Navigation signals are weak and therefore a multi-beam antenna followed by a beam-former is needed. Navigation signals are<br />
narrow in bandwidth which means averaging and/or phase processing is needed to get altimetry accuracy below 10 cm. This<br />
activity addresses the need for the development of a PARIS Beamforming Network for a receive only phased array. In order to<br />
obtain a compact, lightweight Beamforming Network, advanced technologies like multilayer Radiofrequency (RF) substrates<br />
and Monolithic Microwave Integrated Circuits (MMICs) shall be used. This activity will comprise the breadboarding and testing<br />
of the breadboard, according to the requirements defined <strong>du</strong>ring the concept definition study.<br />
Deliverables:<br />
Breadboard (+testing).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL6 by 2009<br />
Application/Mission: GNSS-R Contract Duration: 14 months<br />
SW Clause : - Dossier0 Ref.: T-7734<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 16 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETP-137.D<br />
PARIS Receiver and Signal Processor<br />
This activity aims at the development of the receivers and the signal processor (complex correlator unit) which would provide<br />
the power versus delay waveforms that carry the information on the geophysical parameters (ocean height, ocean wind,<br />
significant wave height and TEC). This activity will comprise the breadboarding and testing of the breadboard, according to the<br />
requirements defined <strong>du</strong>ring the concept definition study.<br />
Deliverables:<br />
Breadboard (+testing).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL6 by 2009<br />
Application/Mission: GNSS-R Contract Duration: 14 months<br />
SW Clause : - Dossier0 Ref.: T-7734<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETP-153<br />
New Radiometer concepts: Active Cold Load for Radiometer Calibration<br />
During the course of this study the concept for an instrument and a demonstrator will be defined and critical<br />
technologies/building blocks identified.<br />
Deliverables:<br />
Breadboard.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2015<br />
Application/Mission: Post EPS/METOP Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-423<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SMOS<br />
ETP-163.C<br />
L-Band Radiometry / Advanced Filter and Correlator integration and validation<br />
Deliverables:<br />
Breadboard (+testing).<br />
Current TRL: TRL3 Target TRL: TRL3/4 Application Need/Date: TRL6 by 2006<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: D47<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 17 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETP-190<br />
Mo<strong>du</strong>lar Signal Generation and Detection for Future SAR Instruments<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: D48<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 18 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
1.3 - Optical Instruments<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T103-01FP<br />
High efficient Laser Pump Source for LIDAR Applications<br />
Improving the efficiency of the laser pump source could benefit a space lidar system by either decreasing the power demand<br />
at spacecraft level or extending the performance and measuring capabilities of the space lidar. First generation of laser pump<br />
sources developed for ATLID or wind space lidars are deemed to be improved by new crystals and new pumping geometries<br />
which have been developed in European laboratories in the past years. This activity is focused on pulsed laser systems and is<br />
targeting a performance of 10% electro-optical efficiency.<br />
Deliverables:<br />
Breadboard of the laser<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2009<br />
Application/Mission: future Earth Explorer Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T103-02FP<br />
Title:<br />
Pulsed laser source in NIR for LIDAR applications<br />
The activity proposed is supporting potential new lidar missions aiming at sounding atmospheric constituents as CO2, O3,<br />
CH4, H2O.Pulsed laser source in NIR have been studied in the past for space lidars in the wavelength ranges of 2micron and<br />
10micron, other spectral domain in the NIR could be of interest, 1.4micron to 4micron (to be defined in link with GSP<br />
study).This activity aim at supporting the definition of these new lidar missions by providing a first assessment of available<br />
technologies and the suitability for high energy pulsed laser sources and space lidars.<br />
Deliverables:<br />
Technology review report. Design and performance assessment report. Test report. Laboratory demo.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: future Earth Explorer Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T103-03MM<br />
Title:<br />
NIR Detector for LIDAR Applications<br />
The activity proposed is supporting potential new lidar missions aiming at sounding atmospheric constituents such as CO2,<br />
O3, CH4, H2O.<br />
The optical detector is an important sub-system in the lidar instrument concept. In general It has to provide features such as<br />
high quantum efficiency, photon counting capability and high dynamic range.<br />
Current studies of detectors for lidar are rather focussed from UV to visible spectral range and assessment/background on<br />
high performance detector in the 1.4-4micron spectral range for lidar applications is missing. This study should aim at<br />
supporting the definition of these new lidar missions by providing a first assessment of available technologies.<br />
Deliverables:<br />
Technology review report. Design and performance assessment report. Test report<br />
Current TRL: - Target TRL: TRL1 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Lidar for Earth Exploration Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T103-10GD<br />
Back-illuminated thinned CMOS imager focal plane<br />
The suitability of Active Pixel Sensors (APS) with the on-chip capabilities of the CMOS technology for numerous detector /<br />
sensor application is presently uncontested. Furthermore, since charge is not being clocked, their susceptibility to<br />
proton-in<strong>du</strong>ced lattice damage is negligible (ionizing damage must be - and can be - mastered). The main drawback of<br />
monolithic APS is their electro-optic / radiometric performance disadvantage wrt modern, back-illuminated CCD's (a.o.<br />
uniformity, noise, QE): In particular, hyper-spectral imagers for Earth Observations (EO), which would otherwise strongly<br />
benefit from the system-on-a-chip capability of APS's, need the performance levels of the latter. The present activity aims at<br />
developing the back-illuminated (BI), thinned solution, offering a cost advantage over the hybrid-Silicon approach (as well as<br />
monoliticity) together with the same electro-optical performances as BI CCDs it is intended to eventually replace. Main<br />
challenges are the back-surface accumulation (as in the BI CCDs; mastered well here) and the optical inter-pixel isolation.<br />
Deliverables:<br />
Fully characterized performance demonstrator model of modest dimensions<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2009-2010<br />
Application/Mission: MTG Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-368, T-7767<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Optical Remote Passive Instruments - Detectors<br />
<strong>TRP</strong> Reference:<br />
T103-11EE<br />
Enhanced Quantum Well Infrared Photodetector (QWIP) Array Detector: Definition and<br />
Title:<br />
optimisation<br />
Future thermal-infrared Earth-observation instruments are expected to need spectral channels near 15 microns for accurate<br />
temperature measurements. At this wavelength, long HgCdTe arrays often used for pushbroom instruments show<br />
technological limitations, leading to performance non-uniformities and the need to segment the array in butted mo<strong>du</strong>les.<br />
Quantum Well Infrared Photocon<strong>du</strong>ctor (QWIP) detectors offer a promising alternative to the more established infrared<br />
detector technologies such as HgCdTe or InSb at the expense of a slightly lower operating temperature, AlGaAs/GaAs<br />
superlattices can be used to pro<strong>du</strong>ce large detector arrays with high uniformity, at a wavelength which can be expected to<br />
extend further into the thermal-infrared range, and at a lower cost <strong>du</strong>e to the growing maturity of QWIP technology. In the<br />
context of the EO programmes, it is necessary to pursue the development of a detector in the long IR wavelength range,<br />
typically around 15 microns, to meet the requirements of planned instruments, such as the IR Sounder for post-MSG. It is<br />
clear that these requirements have much in common with the development possibilities of the Quantum Well Infrared<br />
Photocon<strong>du</strong>ctor trial detector activity. Following the initial feasibility demonstration anticipated under that present contract, it is<br />
proposed to progress to a mission-representative array, in terms of pixel size, element number, uniformity, operating<br />
temperature and other parameters, to provide the basis for an EO instrument. Particular emphasis will be placed on<br />
characterising and optimising the relationship between dark current, operating temperature and cut-off wavelength.<br />
Deliverables:<br />
QWIP detector arrays demonstration model, operating in the 15 (TBC) micron band, with approximately with operating<br />
temperatures higher than 55K, with corresponding readout electronics and mission-relevant performance parameters<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2008-2009<br />
Application/Mission: Future IR missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-367<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T103-13MM<br />
L3CCD/EMCCD Technology for LIDAR Applications<br />
The L3CCD (Low Light Level)/Electron Multiplying technology is a rather new technology developed by E2V (UK) combining<br />
the CCD capability with the photon counting capability. The detector has been primarily developed for night vision applications<br />
but could have very interesting applications in space lidar remote sensing where very low backscatter signals have to be<br />
detected and photon counting capability is required for the acquisition chain. Such a detector would provide very high quantum<br />
efficiency, as other silicon CCDs associated with quasi-null detection noise. This would improve the Signal to Noise Ratio and<br />
the lidar capabilities, when compared to Accumulation CCDs as proposed for AEOLUS mission. It would furthermore provide<br />
shot-to-shot capability.If the suitability of such a detector, and in particular the amplification process, for lidar application is not<br />
demonstrated, it is then proposed to assess such a devices for generic lidar applications.The concept of such detectors is<br />
suitable for any UV-Visible and NIR lidar. The proposed tasks are : derive detector design requirements for lidar applications;<br />
breadboard and manufacture of CCDs based on EMCCD/L3CCD technology; define, develop and breadboard a set-up for<br />
operating the detector including proximity electronics Integration and Tests; performance consolidation and suitability of the<br />
detector for lidar applications.<br />
Deliverables:<br />
Detector design report Detector breadboard Electronics and set-up to operate the detector Reports on results of assessment<br />
and suitability to lidar applications.<br />
Current TRL: TRL2 Target TRL: TRL5 Application Need/Date: TRL5 by 2009<br />
Application/Mission: Future LIDAR missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T103-16FP<br />
Title:<br />
Ultra-compact medium-resolution spectrometer for land application<br />
The objective of this activity is to develop a linear variable filter elegant spectrometer breadboard. This activity will make use<br />
of the linear variable filter technology developed in a previous <strong>TRP</strong> contract. The novelty of the concept is to glue a linearly<br />
variable filter glass directly onto the detector array, thus achieving a very compact spectrometer instrument for hyperspectral<br />
medium resolution applications. The linear variable filter coated on a cover glass will be packaged and aligned to a detector<br />
array, which has been already space qualified. The overall assembly of filter and detector will be optically and environmentally<br />
tested.<br />
Deliverables:<br />
Elegant breadboard of a linear variable filter spectrometer in which the filter is directly applied to the detector. The breadboard<br />
will be optically, electronically and environmentally tested.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: GMES, Post-EPS Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7861<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 21 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T103-24MM<br />
Next Generation panchromatic detectors<br />
Hyper-spectral imagers for EO covers both the visible and the infra-red (with varying long-wavelength cut-off)spectral region.<br />
MCT is the "workhorse" in the IR with adjustable cut-off wavelength, Silicon detectors (CCDs) cover the visible band. While<br />
these established detector technologies used for each wavelength region have very good performance, it requires the costly<br />
development /qualification of two (or more!) detectors and associated front-end electronics as well as a complex<br />
accommodation in the instrument's focal plane.<br />
MCT as a material has a very good response in the VIS, it is the substrate in these hybridized, "back-illuminated" detectors<br />
which is opaque at short wavelengths. The substrate removal (backside thinning) of this rather unforgiving material (in<br />
contrast to Silicon) is recently considered very prosing by the relevant in<strong>du</strong>stry. The development of such a "panchromatic"<br />
detector will allow the use of a single detector covering the entire spectral range of interest with the corresponding tremendous<br />
advantages (substantial simplification and savings in power, mass and size) including elimination of cross-calibration and<br />
co-registration problems for (Hyper-) spectral imagers as the primary instruments in EO.<br />
The activity shall consist in the development of a technology / performance demonstrator of modest dimensions, focussing on<br />
the optimization/mastery of the metallurgy and post-processing of the detector material and it's electro-optical performance.<br />
Deliverables:<br />
Detector array Demonstration Model<br />
Current TRL: TRL2-3 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: FLEX / Sentinel 5 Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-325<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Optical Remote Passive Instruments - Detectors<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T103-25MM<br />
Reliable space-compatible pump laser diodes<br />
This activity will focus on the development of improved wafer technology for high-power laser diode (array and/or stacks) as<br />
pump for solid-state lasers. Aspects of space environmental compatibility, lifetime and reliability are the key technology to be<br />
addressed.<br />
Deliverables:<br />
Improved high-power laser diode wafers samples, testing and characterization.<br />
Current TRL: TRL2-3 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008-2009<br />
Application/Mission: Forthcoming Lidar missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 22 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T103-26MM<br />
Laser interferometry high-precision tracking for LEO<br />
The GSP study “Laser Doppler Interferometry Mission for Earth Gravity”, has identified a number of technological criticalities<br />
for LEO laser interferometry high precision tracking. The laser beam steering mechanism needs to be further investigated. In<br />
particular, repeatability of the beam pointing calls for a testing activity to ensure reliable results. Another issue is the final<br />
implementation of the laser interferometer: a heterodyne interferometer with amplitude mo<strong>du</strong>lation scheme has been proposed<br />
to mitigate photo-detector noise issues and proof-of-concept tests have been performed that confirm feasibility. Additional<br />
tests with state-of-the-art components and, possibly longer baselines, are needed to demonstrate the required performances.<br />
Deliverables:<br />
Test-bed demonstrator of critical technologies.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Future EO solid Earth Missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7747<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T103-27MM<br />
Large format APS detectors with on-chip intelligence for lightning imaging<br />
The Lightning Imaging Mission is intended for continuous mapping of lightning discharges <strong>du</strong>ring both day and night, into a<br />
geostationary orbit. Detection on a geostationary earth disk basis, real time observation of the total lightning flash activity<br />
represents valuable improvements for all operational applications. From geostationary orbit, the sensor will be capable of<br />
detecting all forms of lightning with a high spatial resolution and detection efficiency. Since this data will be distributed in real<br />
time, it will be an invaluable tool to aid weather forecasters in detecting severe storms in time to give advance warning to the<br />
public. The lightning imagery mission will also support applications in atmospheric chemistry, as lightning plays a significant<br />
role in generating nitrous oxides. The natural nitrous oxide budget is a matter of great uncertainty at this time, and long-term<br />
observations of one of its sources will prove valuable as the subject develops.<br />
The selected observation technique is based on the detection of the strongest lightning emission feature within the cloud top<br />
optical spectra pro<strong>du</strong>ced by the neutral oxygen line at 777.4 nm.<br />
Deliverables:<br />
Sensor demonstration model<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: MTG Enhancement Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-325bis<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Optical Remote Passive Instruments - Detectors<br />
Page 23 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T103-28MM<br />
High Energy Fiber-based Laser and Receiver development in the 2 micron region for<br />
Title:<br />
atmospheric CO2 and other greenhouse gases measurements<br />
In the context of the third cycle of Earth Explorer Core Missions the Agency is currently investigating the technical feasibility of<br />
an active optical sensing mission to measure the concentration of atmospheric carbon dioxide (CO2). A spaceborne<br />
Differential Absorption Lidar operating at the near-infrared absorption band of CO2 around 2.05 micron constitutes one of the<br />
candidate measurement concepts. Regarding the required system performance it appears that the use of pulsed laser<br />
sources with an average power on the several Watts level offers advantages over mo<strong>du</strong>lated continuous-wave (CW) laser<br />
based concepts. In the parameter regime of modest laser pulse energy (mJ level) and kHz pulse repetition rates an all-fibre<br />
laser concept is a promising candidate. Given its intrinsically high optical efficiency, system compactness and alignment<br />
insensitivity a fibre laser offers significant assets for spaceborne implementation. On the other hand the targeted fibre laser<br />
system will have to tackle major technological challenges that come with the combination of cutting-edge pulse energies out of<br />
a fibre and highly demanding spectral requirements in particular on centre wavelength stability and spectral purity. This activity<br />
will address the development of a laser diode pumped all-fibre laser source at 2.05 micron for spaceborne CO2<br />
measurements.<br />
Deliverables:<br />
Technology demonstrators of Tx/Rx key elements.<br />
Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: TRL5 by 2010<br />
Application/Mission: A-Scope Mission Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Lidar Critical Solid-state Components<br />
<strong>TRP</strong> Reference: T104-13MM<br />
Title:<br />
Instrument technology for fluorescence<br />
This activity will address the development of critical technologies for the measurement of fluorescence from low Earth orbit<br />
satellites (fluorosensors). The FLEX mission aims to pro<strong>du</strong>ce global scale maps of vegetation photosynthetic activity<br />
contributing to biosphere and global carbon cycle studies. The mission is based on a three-instrument system for measuring<br />
plant fluorescence, multi-angle hyperspectral reflectance and canopy temperature. Early instrument pre-development shall be<br />
dedicated to the demonstration of the feasibility to measure the weak fluorescence signals over heterogeneous natural<br />
vegetation and to achieve high spectral resolution and spectral stability across a large field-of-view.<br />
Deliverables:<br />
Breadboard of critical instrument core unit demonstrating the achievable sensitivity of the fluorosensor.<br />
Current TRL: TRL0-1 Target TRL: TRL3 Application Need/Date: TRL5 by 2011<br />
Application/Mission:<br />
FLEX (Fluorescence Explorer) mission<br />
(selected for assessment studies for third<br />
cycle Earth Explorer Core Mission)<br />
Contract Duration:<br />
18 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
Page 24 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T104-15EE<br />
Vegetation Fluorescense Retrieval Algorithm<br />
Vegetation fluorescence can be used as an early indicator for the vegetation health, status and vitality. Observation of<br />
vegetation fluorescence from space would advance knowledge of the biosphere dynamics, one of the major issues in Earth<br />
Science.<br />
The vegetation fluorescence signal is composed by the far-red and red chlorophyll fluorescence and the blue-green<br />
fluorescence which are associated to different processes. The measurement of the photosynthetic activity of vegetation<br />
requires very accurate atmospheric corrections in order to isolate the fluorescence signal.<br />
The aim of this study is to define an atmospheric correction algorithm accurate enough in order to be used for the<br />
determination of the vegetation fluorescence signal from passive optical data. The study shall include a review of the main<br />
strategies used by the scientific community to perform atmospheric corrections.<br />
Deliverables:<br />
Tested algorithm<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: SW operational by 2009<br />
Application/Mission: FLEX Mission Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T104-16MM<br />
Title:<br />
Non-linear Laser Crystal Development for Frequency Conversion<br />
The activity aims at developing solid-state nonlinear materials optimized for space applications as far as optical quality,<br />
conversion efficiency, laser in<strong>du</strong>ced damage threshold, radiation tolerance and vacuum operation are concerned. In particular:<br />
1) development and characterization of nonlinear materials from various European manufacturers with respect to their space<br />
suitability (e.g. radiation hardness, thermo-mechanical properties, laser-in<strong>du</strong>ced damage threshold in vacuum); 2) modeling<br />
and experimental investigation of degradation and failure mechanisms of solid-state nonlinear materials (including vacuum<br />
operation, contamination effects, colour-center formation, solarization, UV degradation).<br />
Deliverables:<br />
Technical note. Crystals samples, fully tested and characterised in a rappresentative environment.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010<br />
All Lidar missions, e.g. Earth Care,<br />
Application/Mission: Contract Duration: 24 months<br />
A-Scope<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Lidar Critical Solid-state Components<br />
Roadmap and Conclusions:<br />
Page 25 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T104-18EE<br />
Aerosol modeling and synergetic aerosol correction algorithms for passive optical/IR<br />
Title:<br />
sensors<br />
The aim of this study is to enhance the wave interaction modeling of aerosols for passive optical remote sensing instruments.<br />
A brief review of existing aerosol models and aerosol atmospheric corrections shall be performed. Assessment of the<br />
empirical content and of the domain of validity of these models and algorithms shall be carried out. This study shall focus on a<br />
sound theoretical description of the aerosol effects on the top of atmosphere observed surface reflectances. Separated and<br />
concomitant multi-spectral / multi-angular / polarized approaches shall be studied to retrieve aerosol optical properties and to<br />
correct surface reflectances for their effects. Synergetic approaches are strongly encouraged to solve the uncertainties<br />
inherent to single instrument measurements and to test the general applicability of the aerosol correction algorithms output by<br />
the study.<br />
This activity would be beneficial for all passive optical imaging sensors (e.g. the candidate Earth Explorer missions A-SCOPE<br />
and FLEX, or the GMES Sentinel-2 mission) and should also include occultation measurement techniques.<br />
Deliverables:<br />
Tested prototype algorithm<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: SW operational by 2009<br />
Application/Mission: A-Scope, FLEX, GMES Sentinel-2 Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T104-20QC<br />
Title:<br />
SWIR Laser Diodes<br />
Since a number of years Distributed-FeedBack (DFB) semicon<strong>du</strong>ctor laser diodes capable to be tuned to any frequency in the<br />
Short Wave InfraRed (SWIR) domain, with wavelenghts up to ~2.8 micron, are available. They have been used on-ground in<br />
telecommunications and can be regarded as the optical equivalent of the voltage control oscillators (VCO) in electronics: the<br />
emitted wavelength depends only on well-controlled parameters in a robust and repro<strong>du</strong>cible way. Fast tuning is possible by<br />
e.g. current control and large mode-hop-free tuning ranges are achievable. Applications of these laser diodes in space<br />
include remote sensing by active limb sounding. Very good frequency and intensity stability performance is required for this<br />
and other applications, at output powers in the order of tens of mW in continuous wave (CW) operation. There is no<br />
experience with such diodes in space and the capability to maintain the ground-proven performance in the space environment<br />
is being questioned. This activity will select and fully analyse the most promising SWIR laser diodes with respect to the<br />
relevant optical, electrical, mechanical, reliability parameters, deriving specific conclusions for the envisaged applications.<br />
Deliverables:<br />
Technical note<br />
Current TRL: TRL2-3 Target TRL: TRL4 Application Need/Date: TRL5 by 2009<br />
Active (optical) limb sounding missions,<br />
Application/Mission: e.g. ACCURATE; optical communication Contract Duration:<br />
missions<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
12 months<br />
Page 26 of 227
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TEC-SB/7935/dc<br />
12/Feb/09<br />
1.4 - Platforms/ Other Instruments<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T104-02EE<br />
Very large space antenna aperture - architecture trade off<br />
Earth observation and telecommunication antennas operating at low frequencies require large aperture in order to provide the<br />
required directivity. This activity will investigate innovative ways to generate very large aperture in space. Beside Reflect<br />
Arrays (RA) and Direct Radiating Arrays (DRA), innovative concept such as smart skins and lenses including only very<br />
compact switches and phase shifters (amplifiers being located on the spacecraft) can allow for drastic cost re<strong>du</strong>ction in<br />
generating large aperture. Such innovative concepts are one order of magnitude less sensitive to surface errors thanks to<br />
phase compensation at elementary radiator level. An investigation of not continuous aperture like sparse array possibly<br />
coupled with Digital Beam Forming techniques and surface generated by formation flying satellite shall also be studied in the<br />
frame of this activity.<br />
Deliverables:<br />
Architecture trade-off report. Design report. No breadboarding (done in next activity).<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: P-band Radar Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7625, T-373<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 27 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T104-11FP<br />
Autonomous High Data Rate Secured Downlink System - Breadboard (Old <strong>title</strong>: High<br />
Title:<br />
Data Rate Downlink Data Processor Chain – Breadboard)<br />
Security for Earth Observation (EO) systems including the space borne assets is one of the urgently to be addressed topics.<br />
In addition guarantee the safety of the space assets the integrity and originality of the data from observation by space borne<br />
platforms up to delivery to users on ground needs to be implemented. This classically includes security in uplinks and<br />
downlinks and after reception on ground.<br />
A study on link protection for EO systems (recently con<strong>du</strong>cted by <strong>ESA</strong>, Contract No. 17176/03/NL/GS) showed, that currently<br />
no agreed security concept for the space/ground links exist. The existing <strong>ESA</strong> Packet Telecommand Decoder standard<br />
foresees only a very weak authentication scheme. Secure communication shall incorporate as minimum means for<br />
self-authentication, key agreement, message authentication and en-/decryption of telemetry data. Typically the high rate<br />
downlink is secured by encryption and message authentication. The encryption and authentication keys for the downlink are<br />
classically generated on ground and sent to the space platform via a command uplink, which needs then be highly secured.<br />
This is a feasible approach but requires the design of both a secured high rate downlink and a highly secured low rate up- and<br />
downlink. Also it requires a bi-directional communication link for the key exchange and authentication. Some ground stations<br />
are not providing real-time full <strong>du</strong>plex communication.<br />
A secured downlink system should be as far as feasible decoupled from the requirements of the command/control links, taking<br />
into account, that evaluation, standardization, development and implementation of a secured command and control link will<br />
take some years time from the current view.<br />
There are algorithms existing that provide secure key exchange and authentication by using a unidirectional link, only. Elliptic<br />
Curve (EC) based cryptography today is regarded as high secure implementation of the standard techniques. An EC based<br />
unidirectional scheme could provide the necessary level of security for a unidirectional link.<br />
The keys for encryption and authentication could in principle be generated on-board. This requires a cryptographically reliable<br />
key generator to be implemented space compliant.<br />
By combining both EC based unidirectional key exchange/authentication and on-board key generation an autonomous<br />
secured downlink system can be designed, which is decoupled from the security requirements of the command uplink. This<br />
could allow a straightforward “Sensor to User” end-to-end security concept.<br />
The currently used downlink systems provide some 100 Mbit/s data rate. The applied algorithms and protocols shall therefore<br />
be suitable for high rate implementation.<br />
The study objective is to identify alternative and optimised solutions for future applications in EO downlink systems and shall<br />
comprise following elements:<br />
• Analysis of Security requirements for downlink systems including the on ground part;<br />
• Design of a high rate secured downlink system with selection of appropriate algorithms and protocols;<br />
• Breadboard (BB) implementation of core technology to demonstrate feasibility of high rate application as well as space<br />
compliance.<br />
Deliverables:<br />
System Requirements Document, Breadboard of core elements + test report and test results evaluation.<br />
Current TRL: TRL1 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008-2009<br />
Application/Mission: EO, other programmes Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7794<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 28 of 227
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TEC-SB/7935/dc<br />
12/Feb/09<br />
1.4.1 - Lidar (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EEO-003<br />
Solid State Phase Conjungation<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T-M-QCA-08-04<br />
Radiation testing and evaluation for Core Laser Technologies (CHOCOLATE)<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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1.4.2 - Instruments and Sensor Breakthrough (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EEA-044<br />
Geo Atmospheric Sounder Ph.1<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-397<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Geo Atmospheric Sounder Ph.2A<br />
The primary advantage of remote sensing from GEO orbit, as opposed to Low-Earth (LEO) orbit, is that continuous<br />
monitoring is possible over a large area of the Earth’s surface and atmosphere, which allows the observation of real-time<br />
events.<br />
A preliminary review of potential (GEO) missions, based on preferred geophysical parameters, gave consideration to three<br />
main application areas for GEO sounding: numerical weather prediction, climatology and nowcasting.<br />
In contrast to LEO microwave sounders in operation today, the proposed “straw man” GEO instrument uses many more<br />
channels ranging potentially in frequency from 89 GHz through to 874 GHz.<br />
From GEO orbit, the best sounding technique would appear to be the use of spectroscopy / interferometry in the Thermal<br />
Infra-Red (TIR) spectral region as it implies an aperture of reasonable size even for high horizontal resolution. However, the<br />
quality of TIR observations sharply degrades in cloudy areas, preventing useful retrieval of atmospheric parameters for<br />
weather models.<br />
Observations in the microwave region, going up to submillimeter-wave frequencies, are less affected by the presence of<br />
clouds, and can be used to fill the gaps of TIR observations as described above. Due to the large aperture size required to<br />
achieve a reasonable horizontal resolution, its use so far has been restricted to the case of LEO satellites.<br />
The main challenges are the realisation of the antenna with a size compatible with the required spatial resolution (40 fold<br />
increase in the distance to the Earth as compared to the LEO) and the implementation of two-dimensional scanning necessary<br />
in the absence of a relative spacecraft-Earth movement.<br />
Furthermore, the wide frequency range is challenging from the point of view of focal plane assembly and receiver<br />
technologies.<br />
The objective of the activity is the design, manufacturing, and demonstration by test of these innovative enabling technologies<br />
for accurate observation at significant spatial resolution with microwave and (sub)millimetre-wave sensors from GEO.<br />
The activity has been con<strong>du</strong>cted in 2 phases, with the first phase comprising of definition of a concept, trade-offs and<br />
preliminary design. In order to promote innovation, 2 parallel contracts for phase 1 have been placed, to be followed by a<br />
selection by the Agency of the most promising instrument concept for demonstration in phase 2. Phase 2 will include detailed<br />
design, critical breadboarding, and manufacturing integration and test.<br />
Deliverables:<br />
Technical Note. Breadboard.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5/6 by 2012<br />
Application/Mission: Earth Observation from GEO Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.: T-397<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Geo Atmospheric Sounder Ph.2B<br />
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The primary advantage of remote sensing from GEO orbit, as opposed to Low-Earth (LEO) orbit, is that continuous<br />
monitoring is possible over a large area of the Earth’s surface and atmosphere, which allows the observation of real-time<br />
events.<br />
A preliminary review of potential (GEO) missions, based on preferred geophysical parameters, gave consideration to three<br />
main application areas for GEO sounding: numerical weather prediction, climatology and nowcasting.<br />
In contrast to LEO microwave sounders in operation today, the proposed “straw man” GEO instrument uses many more<br />
channels ranging potentially in frequency from 89 GHz through to 874 GHz.<br />
From GEO orbit, the best sounding technique would appear to be the use of spectroscopy / interferometry in the Thermal<br />
Infra-Red (TIR) spectral region as it implies an aperture of reasonable size even for high horizontal resolution. However, the<br />
quality of TIR observations sharply degrades in cloudy areas, preventing useful retrieval of atmospheric parameters for<br />
weather models.<br />
Observations in the microwave region, going up to submillimeter-wave frequencies, are less affected by the presence of<br />
clouds, and can be used to fill the gaps of TIR observations as described above. Due to the large aperture size required to<br />
achieve a reasonable horizontal resolution, its use so far has been restricted to the case of LEO satellites.<br />
The main challenges are the realisation of the antenna with a size compatible with the required spatial resolution (40 fold<br />
increase in the distance to the Earth as compared to the LEO) and the implementation of two-dimensional scanning necessary<br />
in the absence of a relative spacecraft-Earth movement.<br />
Furthermore, the wide frequency range is challenging from the point of view of focal plane assembly and receiver<br />
technologies.<br />
The objective of the activity is the design, manufacturing, and demonstration by test of these innovative enabling technologies<br />
for accurate observation at significant spatial resolution with microwave and (sub)millimetre-wave sensors from GEO.<br />
The activity has been con<strong>du</strong>cted in 2 phases, with the first phase comprising of definition of a concept, trade-offs and<br />
preliminary design. In order to promote innovation, 2 parallel contracts for phase 1 have been placed, to be followed by a<br />
selection by the Agency of the most promising instrument concept for demonstration in phase 2. Phase 2 will include detailed<br />
design, critical breadboarding, and manufacturing integration and test.<br />
Deliverables:<br />
Technical Note. Breadboard.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5/6 by 2012<br />
Application/Mission: Earth Observation from GEO Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.: T-397<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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1.4.3 - Earth Observation P/L (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
MME-003<br />
Laser-cooled Atom Sensor for Ultra-High-Accuracy Gravitational Acceleration and<br />
Title:<br />
Rotation Measurements<br />
Laser-cooling of atoms and atom-trapping is leading the way to new applications in Science. Very recently this concept has<br />
been proposed/investigated for the development of ultra-high accuracy gravitational acceleration and rotation sensor. This<br />
concept relies on coherent light pulses to stimulate transitions between (two) different states of atoms being laser-cooled and<br />
trapped in an optical cavity. It can be shown that <strong>du</strong>e to quantum mechanical effects, the superposition of two or more<br />
spatially separated atomic states can lead to the measurement of gravitational accelerations or rotation of the reference frame<br />
with the utmost accuracy.<br />
This study will assess this emerging concept for the development of Gravitational Acceleration or Rotation Sensors for Space<br />
and Planetary (Earth) Science.<br />
Deliverables:<br />
Definition of a technology roadmap, supported by key experimental verification and breadboarding.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2015<br />
Application/Mission: HYPER Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: -<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: MMO-624<br />
Title:<br />
Advanced LIDAR concepts<br />
This study activity will review advanced Light Detection & Range Finding (LIDAR) concepts like synthetic aperture LIDAR’s,<br />
Differential Absorption LIDAR (DIAL), distributed transmitter/receiver flight formations, and telescope array LIDAR’s, etc. It will<br />
also assess the performance advantage over conventional concepts, review the current technology status and identify<br />
possible technology solutions needed in order to take advantage of the new LIDAR concepts.<br />
Deliverables:<br />
Technical note.<br />
Current TRL: - Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Future LIDAR Missions e.g. DIAL Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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1.4.4 - Payload Data Exploitation (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference: PDE-KEO-001<br />
Title: Knowledge Centred Earth Observation - Phase 1<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-572<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title: Knowledge Centred Earth Observation - Phase 2<br />
Today, a big discrepancy exists between the current EO data offers (data sets or images) and the real user need<br />
(information). The manual process mainly performed by experts to mine information from images is currently too complex and<br />
expensive to be applied systematically or even on just an adequate number of acquired scenes. This hinders the access to<br />
the petabytes of available or new data, penalises large projects of human relevancy like those related to environment<br />
monitoring, and might even leave totally undetected important events.<br />
The situation might become worse in future, since, in order to cope with requirements for monitoring events as well as global<br />
and local changes, more missions and also constellations are being deployed, with broader sensor variety (e.g.: gas detection,<br />
hyper-spectral), increasing data rates (higher resolution, number of channels) and increasing complexity (e.g. data formats).<br />
Therefore, the user desire for value-added information (focused, concise, reliable, timely, understandable, compliant with user<br />
processes) will likely remain unsatisfied, despite the availability of potential answers in the EO data, unless a breakthrough is<br />
intro<strong>du</strong>ced. Emerging technologies, which could support / ease experts’ tasks also by applying their knowledge to large data<br />
sets, could provide this breakthrough. These technologies should perform automatic information mining and classification,<br />
through the support of “intelligent” learning systems capable to discover, store and use the knowledge necessary to retrieve<br />
and fuse data and information from EO and non-EO fields, to model user semantic and domain of interest, and to mask the<br />
inherent complexity of the entire mechanism.<br />
The aim of the KEO research activities is to foster the enlargement of EO data utilisation, and in particular of the large<br />
archives of multi-mission and multi-temporal images. This should be obtained through a better support to research,<br />
value-adding in<strong>du</strong>stry, service providers and EO user communities (like those involved in scientific investigations, in risk and<br />
disaster management, or in the Global Monitoring for Environment and Security programme), by permitting in sequential<br />
steps:<br />
• Identification of the relevant data by its content (and not simply on the basis of spatio-temporal queries)<br />
• Direct access to the information contained in the data (as opposite to access to the images).<br />
This aim can be pursued identifying technological opportunities for the following main objectives:<br />
• Information mining and classification based on algorithms or knowledge for bulk EO data processing at large archive centres<br />
or at small companies (which manage limited but specialised data sets); in particular data relevant to classification attributes<br />
(also for enhanced catalogue searches) and / or information (avoiding the need to access the images), through:<br />
- Interactive Information mining based on acquired knowledge<br />
- Bulk classification based on acquired knowledge<br />
- Bulk classification based on feature extraction algorithms<br />
• Intelligent human interfaces, characterised by:<br />
- Learning capability for knowledge transfer (from experts) or its dynamic acquisition <strong>du</strong>ring user sessions<br />
- Capability to understand / talk user semantic<br />
- Capability to support complex multidiscipline queries<br />
- Advanced features (including graphical / multi-modal / multi-media interactions, self-adaptation to user interest,<br />
recommending, etc.)<br />
• Knowledge Discovery / Management<br />
• Advanced Support Techniques (e.g.: for data / information fusion, information management, time series handling, etc.).<br />
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Deliverables:<br />
Demonstrated methods and evaluated S/W architecture<br />
Current TRL: Target TRL: Prototype Application Need/Date: SW operational by 2008<br />
Application/Mission: Image Information Mining Contract Duration: Ph. 2 12 months<br />
SW Clause : - Dossier0 Ref.: T-572<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
PDE-User-05.B<br />
Multiple Image Registration - MIR<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7699<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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1.3.1 - Optical/Electro-Optical Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
97/XAO08<br />
Quantum Well Photodector<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: MMO-635<br />
Title:<br />
Assessment of Phasing Capabilities of Fibre Optic Devices<br />
Optical phased arrays are today a well accepted technology for future space exploration interferometric missions, present<br />
attractive performance, mass and complexity advantages for laser communication systems, LIDAR systems and can play a<br />
major role for advanced applications like power relays. The aim here is to review the main requirements of telescope array<br />
systems (interferometry, LIDAR, power relay) and identify the main critical components and parameters for each application<br />
and assess possible solutions. There shall be a selection of an application for the evaluation of the capability of a fiber-based<br />
telescope array, e.g. for stellar interferometry. There is also the need for an evaluation of the performance of the system for<br />
the selected application and issue recommendations for solutions allowing to achieve the required performance.<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Assessment of Phasing Capabilities of Fibre Optic Devices<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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2.- Science / Robotic Exploration Preparation<br />
2.1 - Missions in Development Phase: BEPI-COLOMBO<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T201-02MM<br />
Development of microlasers for laser altimetry on future planetary orbiters<br />
The realisation of a diode pumped microlaser for planetary altimetry requires the development of a monolithic solid-state<br />
device providing efficient coherent pulsed emission with high repetition rates and modest pulse energies. The active material<br />
that provides these characteristics can be achieved by Nyodymium (Nd) or Yterbium (Yb) doped host materials, which<br />
provide very good conversion efficiencies to fundamental wavelengths in the 1 micron region. The Yb doped systems have<br />
better energy storage capability and thus may be a better option for the pulsed microlaser. The high repetition rates can be<br />
provided by a q-switch, which, in the monolithic case, would be a passive and not an active device. The passive unit is a<br />
saturable absorber and avoids the need for a high voltage source, as would be required for an electro-optic q-switch in a<br />
discrete resonator. This has many obvious advantages for space operations. The laser dimension can be a small as 1mm3 or<br />
less for Continuous Wave operations. For pulsed operation the need to be below surface and bulk damage thresholds will<br />
dictate the eventual size of the laser <strong>du</strong>e to laser fluence levels being dependent on beam diameter. Such a system does not<br />
presently exist in Europe and is deemed to be a requirement for Europe to provide a viable alternative to the conventional low<br />
repetition rate high energy systems which are currently available.<br />
Deliverables:<br />
Demonstrator of a micro-laser transmitter.<br />
Current TRL: TRL2 Target TRL: TRL5 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Bepi-Colombo, JEP/NEO Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-657<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T201-03SC<br />
Breadboard & Demonstrator of a Micro-pore Optics<br />
The activity shall focus on building a large size breadboard of a x-ray optic. Considerations shall be given about the coating of<br />
the walls for optimum reflection. Techniques for quality control of the alignment of the pores and of the coating shall be<br />
defined.<br />
More in detail, it shall be developed a demonstration of an x-ray optic, formed from pairs of micro channel plates mounted into<br />
Wolter I tandem pairs, integrated into a structure that maintains them in their correct positions.<br />
A previous <strong>ESA</strong> contract (C15668) developed the manufacturing capability to draw square fibres and stack them into a radial<br />
configuration, suitable for making MCP plates that were then slumped and used as constituents of a Wolter I optic. This<br />
contract follows on that work to demonstrate a mounted arrangement for the tandems into a complete optic, for which x-ray<br />
measurements shall demonstrate the current capability.<br />
Following a thorough revision of the technology development activities needed to the mission preparation, some weakness<br />
points have been highlighted and appropriate measures have been undertaken to re<strong>du</strong>ce the development risks.<br />
So at present, the activity encompasses the following main steps:<br />
- Phase 1: review of requirements and design of the optic and the structure. To cope with programmatic and technical needs,<br />
as well as to minimise risks, a first CCN has been implemented for a parallel concept structure design.<br />
- Phase 2: Manufacture of MCP plates and breadboard structure. Through the above mentioned CCN, the original Phase 2<br />
has been modified to include a CDR (critical design review) to select the most appropriate solution from the parallel detailed<br />
structure designs available at the end of Phase 2a. Following CDR it was decided to pursue no further technical development<br />
of the MCP plates or structure. The remaining funds will be used to procure MCP tandem plates from the prime, Photonis, at<br />
the current state of the art, using the material that has already been purchased under this activity. These will be used by the<br />
BepiColombo MIXS instrument team in the development of their micro-pore optic breadboard.<br />
Deliverables:<br />
Micro pore optic tandem plates.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Bepi-Colombo Contract Duration: 26 months<br />
SW Clause : - Dossier0 Ref.: T-757<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T201-04SC<br />
Title:<br />
Scintillator sensor development<br />
The activity addresses the development of new high-density high-light output scintillators for gamma-ray spectroscopy.<br />
Specific materials include the lanthium halides (LaBr:Ce and LaCl:Ce) and Lutenium based compounds (e.g., LuAP, LuYAP,<br />
LuYSO). These compounds are at present in a very early stage of development and pro<strong>du</strong>ction needs to be scaled to<br />
in<strong>du</strong>strial volumes. An important part of the activity is a representative set of tests, aimed to establishing the viability and<br />
suitability for the planetary environment.<br />
Deliverables:<br />
Several representative crystals and one breadboard detection system.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Bepi-Colombo Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: -<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T201-06SC<br />
Active Pixel Sensor Focal Plane Assembly for NIR<br />
The main objective of this activity is to develop, fabricate and validate an APS sensor to cover the wavelength range<br />
0.4-2.2um, possibly extending the wavelength range to 2.5um to be used as sensor onboard the BepiColombo mission.<br />
Previous development activity was mainly driven by European military needs and more recently, earth observation<br />
programmes. In the framework of the earth observation programme, a 256x1000pixel focal plane array has been developed<br />
and flown (SWIR hyperspectral application); however the sensor is targetted to the SWIR range. A cut-off at 0.8um is <strong>du</strong>e to<br />
the CdTe substrate on which the HgCdTe (MCT) detector is grown. In order to fullfill the science requirements of<br />
BepiColombo and indeed potential future scientific satellites, there is the need to further develop the technology in the<br />
following areas:<br />
1) re<strong>du</strong>ction of the thermal current; 2) extension of the wavelength range down to 400nm; 3) radiation hardening/verification.<br />
A compact focal plane assembly shall be attempted for mapping spectroscopy in the visible and NIR (Near InfraRed)<br />
wavelengths. Possible technologies to be explored are back-thinned MercuryCadmiumTelluride (MCT) or<br />
IndiumGalliumArsenide (InGaAs). The detector should be part of a breadboard for the imager/spectograph VIHI onboard<br />
BepiColombo. This activity will benefit from a experience gained in a similar activity, concluded with D/EOP, where a 250-1000<br />
MCT detector was developed. A further development and optimization is needed in order to accomodate the wavelength<br />
range from 0.4 to 2.2 microns.<br />
Deliverables:<br />
Compact focal plane breadboard.<br />
Current TRL: TRL2-3 Target TRL: TRL4 Application Need/Date: TRL6 by 2009<br />
Application/Mission: Bepi Colombo Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: -<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Active Pixel Sensor Focal Plane Assembly for NIR - Additional work<br />
The main objective of the original activity has been to develop, fabricate and validate an APS sensor to cover the wavelength<br />
range 0.4-2.2um, possibly extending the wavelength range to 2.5um to be used as sensor onboard the BepiColombo mission.<br />
Previous development activity was mainly driven by European military needs and more recently, earth observation<br />
programmes. In the framework of the earth observation programme, a 256x1000pixel focal plane array was developed and<br />
flown (SWIR hyperspectral application); however the sensor is targetted to the SWIR range. A cut-off at 0.8um is <strong>du</strong>e to the<br />
CdTe substrate on which the HgCdTe (MCT) detector is grown. In order to fullfill the science requirements of BepiColombo<br />
and indeed potential future scientific satellites, there has been the need to further develop the technology in the following<br />
areas: 1) re<strong>du</strong>ction of the thermal current; 2) extension of the wavelength range down to 400nm; 3) radiation<br />
hardening/verification.<br />
A compact focal plane assembly has been attempted for mapping spectroscopy in the visible and NIR (Near InfraRed)<br />
wavelengths. Possible technologies being explored are back-thinned MercuryCadmiumTelluride (MCT) or<br />
IndiumGalliumArsenide (InGaAs). The development is in a first instance intended for the imager/spectograph VIHI onboard<br />
BepiColombo, but could serve future missions requiring hyperspectral capability from visible to NIR wavelength range. This<br />
activity benefits from the experience gained in a similar activity, concluded with D/EOP, where a 250-1000 MCT detector was<br />
developed. Further development and optimization has been needed in order to accomodate the wavelength range from 0.4 to<br />
2.2 microns.<br />
In order to cover the additional development required when carefully reviewing the Bepi Colombo missions needs, a CCN will<br />
be placed.<br />
It will allow to cope with with a number of technology issues. In fact, the manufacturing and testing of a hyperspectral detector<br />
(0.4 to 2.2 um) for the Bepi Colombo/VIHI instrument appears to be extremely challenging at many levels. Due to the limited<br />
budget, the detector concept proposed by SOFRADIR is heavily relying on heritage of a previous D/EOP contract. This<br />
heritage is particularly obvious for the CMOS readout circuitry, which will be entirely used as such.<br />
This major design parameter has led to the need of total ionizing dose tests to prove the capability of the readout to withstand<br />
the harsh environment of Bepi Colombo. Within the original contract, it was possible to accommodate only one TID test, using<br />
an existing device of the EOP. However it is clear that this unique test will only respond very partially to the radiation<br />
tolerance, a second test would definitely give more credit to the campaign. The outcome of the test will determine whether the<br />
BepiColombo/VIHI team will use this detector or if they need to rely on a US backup (Rockwell or Raytheon). It is worth noting<br />
that the results of this radiation campaign may also be of particular interest for EOP and its future developments. Last but not<br />
least, a better knowledge of the TID behavior of the device will considerably improve our understanding of the proton tests,<br />
aiming at studying the potential displacements damage effects occurring in the thinned Mercury Cadmium Telluride substrate.<br />
The tests which will be carried out by SOFRADIR will cover the main electro-optical characteristics of the final device. Due to<br />
timescale and technical limitations of SOFRADIR’s test bench, some specific tests will not be achievable within this contract<br />
(e.g. spot scanning for visible MTF…). Therefore, it is of prime interest to have the possibility to carry out additional tests on<br />
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12/Feb/09<br />
the deliverable at ESTEC (where more adequate equipments exist). The present CCN will cover the needed upgrading of the<br />
deliverable by adding some peripheral units, including cooler and control electronics, to enable the above mentioned post<br />
delivery tests.<br />
Deliverables:<br />
Compact focal plane breadboard.<br />
Current TRL: TRL2-3 Target TRL: TRL4 Application Need/Date: TRL6 by 2009<br />
Application/Mission: Bepi Colombo Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7887<br />
Consistency with Harmonisation<br />
Optical Remote Passive Instruments - Detectors<br />
Roadmap and Conclusions:<br />
Page 39 of 227
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TEC-SB/7935/dc<br />
12/Feb/09<br />
2.2 - Missions in Pre-Assessment Phase: Darwin<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MMO-630<br />
High Precision Optical Metrology<br />
The objective of this activity is to improve the reliability of the optical metrology sensors as developed to breadboard level for<br />
precise formation flying of the DARWIN satellites. The aim is to reach the maturity status of "elegant breadboard"<br />
representative in form, fit and function for some presently critical parts (e.g. interferometric head, heterodyne mo<strong>du</strong>lation<br />
sub-system and fibre coupling system). An emphasis shall be put on the measurement stability in vacuum and under<br />
reasonable thermal variations as well as vibrational constraints and over representative distances. The activity's detailed<br />
definition shall be made with an aim of using and testing this type of metrology on PROBA-3 and other space missions. The<br />
output of this activity will also help to better define follow on activities currently foreseen in the <strong>TRP</strong>, addressing miniaturisation<br />
of the current concepts and new measurement techniques.<br />
Deliverables:<br />
Elegant Breadboard<br />
Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5 by 2008-2009<br />
Application/Mission: Darwin, Proba III Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7971, T-7747<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Roadmap: N/A<br />
<strong>TRP</strong> Reference: T203-06MM<br />
Title:<br />
Passive optical components for interferometry<br />
The first objective of this activity is to design, manufacture and test passive optical components for interferometry. This<br />
includes the development of achromatic beam splitters, dichroic filters, compensation and polarization plates, wide band<br />
antireflection coatings, etc. The second objective is to establish manufacturing techniques and technologies to achieve a<br />
constantly high optical quality of the above-mentioned components, such that differences between the interferometer arms are<br />
minimized. The functionality and performance of the components shall be demonstrated by means of a breadboard that shall<br />
be subjected to a verification test campaign in an environment compatible with DARWIN mission (e.g. Cryogenic<br />
Interferometry Facility).The broadband infrared beam (6-18 micron) has to be split in a specific ratio and accurately over the<br />
full wavelength range. Current technology for beam-splitters does not allow such accurate beam splitting over wide spectral<br />
ranges. Furthermore a number of dichroic plates, polarization beam splitters, compensator plates, antireflection coatings (e.g.<br />
multilayer dielectric stacks or sub-nm gratings, etc. on bulk and optical waveguides), reflective mirrors (with special metallic<br />
and associated protected coatings) are also used in the interferometer. The selected contractor will investigate and define<br />
techniques to guarantee and control minute differential effects between the arms of the interferometer <strong>du</strong>ring the<br />
manufacturing process, and will propose techniques capable of measuring such very small differences (e.g. differential<br />
spectral response, differential polarization effects, differential chromatic dispersion, etc).<br />
Deliverables:<br />
Breadboards of the passive components for interferometry, and modelization software.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Darwin Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7987<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 40 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T203-09SC<br />
Wavefront tilt sensor<br />
In this activity the wavefront tilt sensor shall be designed, breadboarded and tested. The testing shall be performed in a<br />
representative environment. Optimum wavelengths and operating points shall be specified.<br />
In the DARWIN mission a telescope pointing error will cause a tilt of the interferometer’s input beam, which translates into an<br />
amplitude error after wavefront filtering. The interferometer’s nulling performance is proportional to the square of the wavefront<br />
tilt angle, and already small tilt values will cause unacceptable amplitude differences. The baseline system design foresees<br />
high accuracy star trackers mounted in the focal plane of each telescope spacecraft with a large CCD detector. An alternative<br />
design is to sense the wavefront tilt as received in the central beam combiner spacecraft. The wavefront sensor is to be<br />
mounted in the cryogenic payload mo<strong>du</strong>le of the telescopes or the beam-combiner spacecraft. This shall be done coherently<br />
and complementary with the Fringe Sensor developments.<br />
Deliverables:<br />
Detailed resource specification of the sensor; breadboard; preliminary characterization of the performance; recommendations<br />
about integration and beam routing.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Darwin Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7973<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T203-11MM<br />
Title:<br />
Integrated optics<br />
This activity deals with the design and manufacturing of optical components and functional devices in integrated-optics<br />
technology. In comparison to a realisation of the same functionality by bulk optics, an integrated optics device provides large<br />
benefits by its low mass and its low sensitivity to temperature and other environmental factors. Whereas integrated-optics for<br />
telecommunications (operating at 1.5 micron) is a well-mastered technology, the spectral range of DARWIN is not yet<br />
explored or mastered. The challenge is to find materials which are transparent in this spectral range, but allow also defining<br />
two-dimensional waveguiding effects using reliable manufacturing processes. Therefore a number of different materials and<br />
technologies (e.g. integrated optics by photo inscription, Index guided photonic crystals) will have to be investigated<br />
experimentally, and the most promising combination will be selected for the manufacturing of sample devices.<br />
Deliverables:<br />
Integrated-optics components to be used in an interferometer breadboard.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Darwin Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7988<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 41 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T203-19MM<br />
FIR linear Detector Array<br />
The purpose of this activity is to develop a novel detector technology to realize the linear focal plane array (FPA) for the<br />
DARWIN mission spectrometer. The linear array must cover the wavelength band going at least from 6 to 18 µm with<br />
state-of-the-art sensitivity and take into account the mission thermal budget. The wavelength band and sensitivity<br />
requirements are essentially constrained by extra-solar planet contrast considerations. In addition, system design issues<br />
favour higher operating temperatures than those offered by existing detector technologies. Phased contract.<br />
Deliverables:<br />
Technology demonstrator<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Darwin Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7990<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T203-20MM<br />
Title:<br />
Single mode waveguide<br />
The wavefront quality of the interfering beams has to be improved in order to achieve the required nulling performance. This<br />
improvement can best be performed by filtering by means of propagating the wave in a single mode waveguide.<br />
Pre-developments of IR single mode fibres have been successfully completed, resulting in the identification of promising<br />
technologies such as SilverHalide, Calcogenide and Tellurium based waveguides. In this activity the manufacturing process<br />
shall be refined and the detailed properties of the waveguides determined.<br />
Deliverables:<br />
Process assessment, technology demonstrator.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Darwin Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7991<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
The proposed activity is not directly related to a harmonised subject.<br />
Page 42 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.2.1 - Darwin (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EEO-048<br />
BiB detector<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-709<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 43 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MMO-632<br />
Fiber optical wavefront filtering<br />
The DARWIN system requires wavefront errors of less than lambda/1000 at 5 micron between pairs of telescopes in order to<br />
achieve the required nulling quality. Such high wavefront quality is difficult to achieve without wavefront filtering measures.<br />
The aim here is to establish a wavefront filtering system (WFS) of the DARWIN telescope system. The sub-activities<br />
envisaged are: Establishment of wavefront filtering concepts for the DARWIN system based on single-mode fibres,<br />
Investigation of additional functionality, which can be fulfilled by a fibre-optic system, Design and breadboarding of a<br />
broadband single-mode IR fibres system, Performance Validation of the fibre-optic filtering (and nulling) system.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Darwin<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-658<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Fiber optical wavefront filtering ph.1<br />
The DARWIN system requires wavefront errors of less than lambda/1000 at 5 micron between pairs of telescopes in order to<br />
achieve the required nulling quality. Such high wavefront quality is difficult to achieve without wavefront filtering measures.<br />
The aim here is to establish a wavefront filtering system (WFS) of the DARWIN telescope system. The sub-activities<br />
envisaged are: Establishment of wavefront filtering concepts for the DARWIN system based on single-mode fibres,<br />
Investigation of additional functionality, which can be fulfilled by a fibre-optic system, Design and breadboarding of a<br />
broadband single-mode IR fibres system, Performance Validation of the fibre-optic filtering (and nulling) system.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Darwin<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-658<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Fiber optical wavefront filtering Ph.2<br />
The DARWIN system requires wavefront errors of less than lambda/1000 at 5 micron between pairs of telescopes in order to<br />
achieve the required nulling quality. Such high wavefront quality is difficult to achieve without wavefront filtering measures.<br />
The aim here is to establish a wavefront filtering system (WFS) of the DARWIN telescope system. The sub-activities<br />
envisaged are: Establishment of wavefront filtering concepts for the DARWIN system based on single-mode fibres,<br />
Investigation of additional functionality, which can be fulfilled by a fibre-optic system, Design and breadboarding of a<br />
broadband single-mode IR fibres system, Performance Validation of the fibre-optic filtering (and nulling) system.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Darwin Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-658<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 44 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MMO-634<br />
High Stability Optical Benches for Darwin<br />
The functionality and the performance of future science interferometric missions like DARWIN are based on the availability of<br />
ultra-high stability optical benches capable of maintaining dimensional stability of picometers over periods of hours without<br />
active control. This activity aims to assess the optical system technologies and materials suitable for achieving these stability<br />
and design, develop and test a representative scaled optical bench under cryogenic conditions demonstrating picometer<br />
stability over periods of up to 3 hours.<br />
Deliverables:<br />
Demonstrator<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 by 2015<br />
Application/Mission: Darwin Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.: T-668<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
Page 45 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.3 - Missions in Pre-Assessment Phase: XEUS<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T204-03MM<br />
High performance X-ray optics<br />
HPO optics will require further development with a view to improving the spatial resolution and overall mass. In addition a<br />
range of reflective coatings need to be developed ranging from Au to Ir together with layered synthetic microstructures for<br />
hard X-ray reflectivity. Building on the ongoing HPO Activity, the angular resolution shall be improved while optimising the<br />
required mass resources. In addition the high performance of the optics shall be extended to the edges of the optics mo<strong>du</strong>les.<br />
Deliverables:<br />
Assessment of the coating process and samples testing.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2011<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7959<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to Harmonised Technology.<br />
<strong>TRP</strong> Reference: T204-04MM<br />
Title:<br />
Micropore baffle<br />
On either side of the XEUS mirror elements a baffle system is required to provide X-ray and visible stray light baffling, and<br />
provide thermal and contamination control. A hierarchical micropore baffling system is required. Standard sheet metal<br />
baffles, for example in aluminium, could be significantly improved upon with use of pore optic technology, for instance in glass<br />
or silicon. Test samples need to be manufactured with relevant shape and dimensions to demonstrate the higher efficiency<br />
established with such systems. This activity complements T204-03MM.<br />
Deliverables:<br />
Breadboard.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5>2011<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7961<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to Harmonised Technology.<br />
<strong>TRP</strong> Reference: T204-06SC<br />
Title:<br />
Low bandgap supercon<strong>du</strong>cting sensor<br />
Small arrays of DROID devices have been demonstrated, but to meet XEUS energy resolution requirements, fabrication on<br />
narrower band gap material should be demonstrated. Methods to massively increase the array size to match field of view<br />
requirements are required.<br />
Deliverables:<br />
Process assessment and samples manufacturing.<br />
Current TRL: TRL2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7966<br />
Consistency with Harmonisation<br />
Not directly linked to Harmonised Technology.<br />
Roadmap and Conclusions:<br />
Page 46 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T204-07MM<br />
TES Spectrometer<br />
Small arrays of Transition Edge Sensor devices have been demonstrated to work at high X-ray energies, but do not meet<br />
XEUS energy resolution requirements. These detectors form a baseline for the next generation X-ray observatories<br />
instrumentation. For the XEUS energy range, fabrication of devices with lower heat capacity is necessary to meet the<br />
required performance. At the same time massively increasing the array size to match field of view requirements is required,<br />
which needs development of lead-out technology and multiplexing. The low energy performance needs to be developed &<br />
optimised for resolution and efficiency.<br />
Deliverables:<br />
Technical notes. Breadboarding.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7967<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T204-08MC<br />
Title:<br />
50mK Continuous Cooling System<br />
Future Scientific Mission as e.g. Xeus require temperatures for the detection chain between 50mK-100mK. For such<br />
applications, the need to develop in advance a vibration-free cooling system with a long lifetime which covers the cooling in<br />
the temperature range 4.5K down to 50mK was identified.<br />
The objective of this activity is to design a 50 mK cooling system, compatible with current mechanical coolers providing a<br />
pre-cooling temperature of 4.5K (4.5K- JT cooler qualified for Planck Mission).<br />
Different technologies can be used for building a system that reach 50mK, as e.g. Adiabatic Demagnetisation Refrigerators,<br />
dilution cooler or hybrid systems using He-sorption cooler for pre-cooling at 300mK. Current European technologies such as<br />
ADR or He-sorption are single shot devices and therefore only allow a limited observation time or are open-loop systems<br />
(dilution) with a limited lifetime. To comply with the need for the required observation times, large bulky systems would be<br />
required with a long recycling time in combination with a JT pre-cooler. A continuous system therefore allows building smaller<br />
systems and sizing the pre-cooling chain to the average power dissipation, rather than to the peak power dissipation required<br />
by a single-shot system.<br />
The concept of a cooling system will be selected <strong>du</strong>ring the proposal evaluation and within the initial phase of the activity a<br />
conceptual design will be established based on resource budget (mass, volume, electrical power etc). In the second phase the<br />
most promising concept(s) shall be designed, manufactured and tested on breadboard level. To re<strong>du</strong>ce as much as possible<br />
the interface problems between different types of coolers and refrigerator systems, efforts shall be put in designing a self<br />
standing, compact cryogenic system.<br />
The requirements of the cooler will be derived from the XEUS payload architecture study.<br />
Deliverables:<br />
Breadboard Cooler and associated technical <strong>document</strong>ation<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 by 2012<br />
XEUS mission (launch >2015), FIRI<br />
Application/Mission: Contract Duration:<br />
mission (launch >2025)<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Cryogenics<br />
Roadmap and Conclusions:<br />
30 months<br />
Page 47 of 227
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TEC-SB/7935/dc<br />
12/Feb/09<br />
2.3.1 - XEUS (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SCI-X10.a<br />
Supercon<strong>du</strong>cting Read Out for Microcalorimeters<br />
In the frame of the development of cryogenic instruments with large array sizes, as required to meet the science requirements,<br />
it is proposed to develop a low noise readout electronics, specifically tailored to x-ray microcalorimeter arrays. In this<br />
development program a low noise readout electronics based on a high bandwidth Super-Con<strong>du</strong>cting Quantum Interference<br />
Device (SQUID) will be studied, in conjunction with a suitable multiplexing scheme. The main issues to be addressed include<br />
the design of the amplifier system, power requirements, noise performance and the thermal requirements of the amplifier<br />
readout. These issues will be studied theoretically and then validated against breadboard designs and models.<br />
Deliverables:<br />
Technical Note (design of the amplifier system with multiplexing scheme, power requirements, noise performance and the<br />
thermal requirements of the amplifier readout). Breadboard (+testing).<br />
Current TRL: TRL2 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-682<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: SCI-X10.b<br />
Title:<br />
Supercon<strong>du</strong>cting Read Out for Supercon<strong>du</strong>cting tunnel junctions<br />
In the frame of the development of cryogenic instruments with large array sizes, as required to meet the science requirements,<br />
it is proposed to develop a low noise readout electronics for supercon<strong>du</strong>cting tunnel juncions. The electronics shall be based<br />
on high bandwidth Super-Con<strong>du</strong>cting Quantum Interference Devices (SQUID) in conjunction with a suitable multiplexing<br />
scheme. The main issues to be addressed include the design of the amplifier system, power requirements, noise<br />
performance, re<strong>du</strong>ction of channels through multiplexing and the thermal requirements of the amplifier readout. These issues<br />
will be studied theoretically and then validated against breadboard designs and models.<br />
Deliverables:<br />
Technical Note (design of the amplifier system including multiplexing topology, power requirements, noise performance and<br />
the thermal requirements of the amplifier readout). Breadboard (+testing).<br />
Current TRL: TRL2 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-682<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
Page 48 of 227
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SCI-X11<br />
Large Format Detector Read-Out - Additional work<br />
Within the original contract a basic development for a read-out for future high resolution imaging spectrometers is undertaken.<br />
The study will focus on the electronics required to readout future high resolution imaging spectrometers. It will result in a<br />
complete instrument capable of delivering packaged data containing spectral and imaging outputs from detector arrays of up<br />
to 10,000 pixels. The key issues to be addressed are the design of the full readout chain, power requirements, noise<br />
performance, thermal requirements, and the rate and speed limitations.<br />
More in detail, a read-out electronics for large array detectors shall be designed, fabricated and tested. The design shall be<br />
scalable, radiation tolerant and highly integrated. In order to re<strong>du</strong>ce the required interface circuitry to an absolute minimum,<br />
the ASIC shall include:<br />
1) ultra-low noise preamplifiers for each indivi<strong>du</strong>al detector pixel, to achieve detector statistical noise limits<br />
2) programmable filter stages for each pixel<br />
3) event detection circuitry, with internally programmable threshold settings<br />
4) analog-to-digital converters<br />
5) event prioritization circuitry<br />
6) digital glue logic.<br />
In addition to the basic development summarised above, it is now proposed to place a CCN to cover additional testing and<br />
validation issues. During the development of the ASIC, it was realized that the circuit could not be sufficiently tested without<br />
any detector connected to it. Therefore, in order to validate the full functionality, it is required to bump-bond a 2-D detector<br />
array to the ASIC and test this assembly under X-ray radiation. In addition, and for the specific need for BepiColombo, the<br />
ASIC needs to be validated under gamma and proton irradiation. These radiation tests will also help to understand the basic<br />
limitations of the particular foundry and CMOS process, which is used not only for this development but also by several other<br />
institutes / companies intending to design ASIC for BepiColombo and Solar Orbiter.<br />
Deliverables:<br />
Set of ASIC wafers and ASIC + Detector assemblies as well as the full design databases.<br />
Current TRL: TRL2-3 Target TRL: TRL4 Application Need/Date: TRL5 by 2009<br />
Application/Mission: XEUS / Bepi Colombo Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-757<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
N/A<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SCI-X4<br />
Optical rejection filter<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-712<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 49 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SCI-X8<br />
Multilayer coatings for high energy<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-701<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 50 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
2.4 - Long Term Mission / Technology Reference Missions: Gamma Ray Imager<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T206-01SC<br />
Gamma Ray Optics Development<br />
This activity aims at developing a combination of technologies that achieves true gamma ray focusing. This will allow improved<br />
localization and signal: noise for gamma ray observatories, and would be usable as a concentrator for gamma ray<br />
spectrometers. The aim is to develop imaging optics for the Gamma-ray energy range in the region of 100keV to ~2MeV.<br />
Using a Laue crystal diffraction lens, it is possible to focus gamma rays with quite high efficiency over rather narrow energy<br />
bands. The field of view, energy band and efficiency are all parameters that must be traded off in a practical design. The use<br />
of mosaic crystals, with slight misalignment between the microblocks within a large crystal, allows some tuning of these<br />
important parameters. The activity will develop improved crystal growing techniques to allow control of these parameters.<br />
Materials such as Ge, Cu and pyrolitic graphite, among others, will be investigated, and growth techniques will be correlated<br />
with measurements of the diffraction efficiency. For an optimized crystal choice, a system study will be performed to determine<br />
the parameters for a tunable system that allows (for a fixed focal length) to establish the angular control requirements to adapt<br />
the crystals to focusing indivi<strong>du</strong>al emission line energies of astrophysical interest (e.g. annhilation energy, or nucleo-synthesis<br />
pro<strong>du</strong>cts within supernovae remnants).<br />
Deliverables:<br />
Mirror samples with graded density multi-layers, and Laue crystal arrays demonstrator.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Gamma Ray Imager (>2015) Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-672<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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2.6 - Other Technologies / Missions<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T214-05SC<br />
High Resolution, Low Mass, Pore Optics<br />
Intro<strong>du</strong>ction of novel lightweight materials will be used in the design of high resolution deployable low mass optics. The activity<br />
is to develop a preliminary breadboard phase for future astrophysics missions. The aim of the technology development is to<br />
maintain the high throughput and resolution via. a high reflectivity over a wide range of wavelengths, with a flexible design<br />
geometry dependent on wavelength.<br />
Deliverables:<br />
Low mass optics breadboard.<br />
Current TRL: TRL2-3 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-815<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
High Resolution, Low Mass, Pore Optics: additional work<br />
Intro<strong>du</strong>ction of novel lightweight materials will be used in the design of high resolution deployable low mass optics. The activity<br />
is to develop a preliminary breadboard phase for future astrophysics missions. The aim of the technology development is to<br />
maintain the high throughput and resolution via. a high reflectivity over a wide range of wavelengths, with a flexible design<br />
geometry dependent on wavelength.<br />
Deliverables:<br />
Low mass optics breadboard.<br />
Current TRL: TRL2-3 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-815<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
High Resolution, Low Mass, Pore Optics: additional work<br />
Intro<strong>du</strong>ction of novel lightweight materials will be used in the design of high resolution deployable low mass optics. The activity<br />
is to develop a preliminary breadboard phase for future astrophysics missions. The aim of the technology development is to<br />
maintain the high throughput and resolution via a high reflectivity over a wide range of wavelengths, with a flexible design<br />
geometry dependent on wavelength.<br />
The present extension to the original contract (rider to contr. number 18981) is <strong>du</strong>e to the purchase of a additional silicon<br />
wafer to create an X-Ray Optical Unit (XOU), using a pair of CeSiC brackets that have already been manufactured under the<br />
original contract. The additional activity includes the assembly, alignment and X-ray test of XOU in petal structure, also<br />
manufactured under the original contract.<br />
Deliverables:<br />
Low mass optics breadboard.<br />
Current TRL: TRL2-3 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: XEUS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-815<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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2.7 - GAIA (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SCI-G16<br />
Optimum Compression Algorithm<br />
The objective of the activity is to identify and validate lossless or quasi lossless compression algorithms to be applied<br />
on-board and in real time to re<strong>du</strong>ce as much as possible payload data rate for scientific missions to be transmitted to ground.<br />
An efficient on-board data compression, taking advantage of the advanced processing technologies, could allow not only the<br />
transmission of higher data rate, but will also make more viable the spacecraft design, alleviating critical design constraints<br />
on-board as well on the ground, with re<strong>du</strong>ction of the overall cost. This activity should first identify, study and develop the most<br />
suitable algorithm taking into account current and future missions (e.g. GAIA, Wide Field Imager), then implement this<br />
algorithm in software as a library element for applications based on <strong>ESA</strong>'s space microprocessors.<br />
Deliverables:<br />
Optimised algorithm.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 by 2007<br />
Application/Mission: GAIA Contract Duration: 12 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-680<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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2.8 - Cosmic Vision 2025 (Solar Orbiter, WFI, ..)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T202-01MM<br />
Solar Blind sensor<br />
Detectors based on a Wide-Bandgap Semicon<strong>du</strong>ctor (WBG) as most likely candidate for the development of Solar Blind<br />
imaging sensors. These materials provide the following advantages over narrower-gap semicon<strong>du</strong>ctors: visible blindness,<br />
radiation hardness, VUV and EUV improved response etc. Alternative back-up solutions include MCP converters with APS<br />
readout.<br />
Deliverables:<br />
Breadboard. Technical data package.<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Mission: SolO/SPO Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-8019<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T215-02MC<br />
Title:<br />
Solar sails Materials<br />
This activity will concentrate on the development of the appropriate Sail material. Approaches to the fabrication of such sail<br />
material with Al/Cr coating, 2 µm thick film, loading 8 g m-2 need to be studied. Sail degradation resulting from the material<br />
thermal & radiation effects need to be considered via sample tests. In addition the material needs to be compliant with the<br />
sail deployment system & final jettison of a large ~150 x 150 m2 sail.<br />
Deliverables:<br />
Samples. Technical data package.<br />
Current TRL: - Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: SPO/IHP Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7994<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T215-03MM<br />
Title:<br />
Low bandgap EUV sensor<br />
UV/EUV and soft X-ray sensors based on low bandgap compound semicon<strong>du</strong>ctors are an ideal development to improve<br />
performance (efficiency and resolution) beyond sensors based on silicon. This development will concentrate on the material<br />
science of high quality films couple to the fabrication of the basic diode and small arrays.<br />
Deliverables:<br />
Breadboard. Technical data package.<br />
Current TRL: TRL0-1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: SPO Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-8019<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T215-04MM<br />
Planetary surface Dating Instrument (Luminescence dating)<br />
The age of a planetary surface is a very important information in order to understand surface mo<strong>du</strong>lations and overall<br />
geodynamic processes of a planetary body. So far no approach has been made to adapt a specific technique for this<br />
purpose. Optically Stimulated Luminescence Dating is used on Earth commonly to measure sediments up to an age of one<br />
million years. This technique makes use of the interaction between ionizing radiation and solid matter. Free charges are stored<br />
in lattice defects and accumulated over time. Under defined conditions the electrons fall back on lower energetic levels and<br />
release light, the luminescence signal. The intensity of the signal is relative to the age of a buried grain. This method can be<br />
adapted to investigations on Mars, as such data from the Martian surface are elementary for understanding of the evolution of<br />
the planet. The same can be applied to other and Near Earth Objects (NEO).<br />
Deliverables:<br />
Breadboard. Technical data package.<br />
Current TRL: TRL0-1 Target TRL: TRL2 Application Need/Date: TRL5 by 2012<br />
Application/Mission: NEO missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-8020<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T215-05EE<br />
Title:<br />
Jupiter Radiation Environment and Effect Tools<br />
The severe Jupiter radiation environment will be modelled. As a starting point the JPL and Salammbo code results will be<br />
used. The complete Jupiter spatial and energy range will be treated, and dynamic as well as long-term averages will be<br />
modelled. The results will be useable for engineering. The development will include the appropriate improvements to tools for<br />
shielding, internal charging (DICTAT), electronic radiation effects and solar array degradation as appropriate for the Jovian<br />
environment. Effects models for spacecraft nuclear elements will be included.<br />
Deliverables:<br />
Requirements analysis, models of environment and effects implemented in an engineering toolkit.<br />
Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL4 by 2007-2010<br />
Application/Mission: Jupiter missions Contract Duration: 24 months (Ph1&2)<br />
SW Clause : Operational SW Dossier0 Ref.: T-9<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Space Radiation Environment Models and In-Orbit Monitors (UPDATE)<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T215-06EP<br />
High radiation tolerant Low Intensity Low Temperature GaAs solar cells<br />
For Jupiter missions high efficiency / high radiation tolerant Low Intensity Low Temperature (LILT) solar cells, capable to<br />
survive the extreme Jovian radiation environment, are required. As the current technology status is not proven to be adequate<br />
to withstand the environment it is proposed, in a first step, to upgrade the existing and relevant photovoltaic/assembly facilities<br />
to allow for an appropriate characterization and verification of solar cells/assemblies w.r.t. the essential Jovian environment<br />
parameters. The definition of the facility performances and accuracies required shall be based on a study with a strong focus<br />
on the minimization of the solar array design margins to be applied when designing and verifying the technologies for missions<br />
to Jupiter's vicinity.<br />
In parallel to the facility related tasks of this activity a high radiation tolerant multi junction LILT solar cell structure shall be<br />
designed, the expected solar cell pro<strong>du</strong>ction performance predicted and compared with the performance and cost (recurring<br />
and non-recurring) of the existing 3G cell from RWE.<br />
It is planned to use the results from this activity to decide if a Jupiter mission specific solar cell or other solar array related<br />
developments are required to enable potential European Jovian missions.<br />
Deliverables:<br />
Technology assessment (of existing and potential of Jupiter specific solar cell performance).<br />
Upgraded facilities to allow for tests in Jovian representative environment.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2015<br />
Application/Mission: Jupiter missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: N/A<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T215-07MM<br />
Demonstration of the deployment of a highly integrated low power ice penetrating radar<br />
Title:<br />
antenna<br />
The main objective of this activity is to design and demonstrate by test the deployment and stability of the Yagi antenna for a<br />
low power ice penetrating radar suitable for the investigation of the icy shell of Europa, one of Jupiter's moons. This moon has<br />
been recognised as one of the key interests for planetary exploration by the international scientific community and is the goal<br />
of the Jovian Minisat Explorer Technology Reference Study performed by the Agency. The contractor shall perform the<br />
antenna Radio Frequency (RF), mechanical and thermal design/analyses and manufacture/test a Demonstration Model<br />
representative of the intended flight design in terms of materials and the following functions: Hold down, release, deployment,<br />
latching and pointing. The activity shall fully demonstrate the feasibility and the mechanical functionalities of the developed<br />
model. The antenna design is expected to be based on a highly integrated bars and hinge mechanisms (possibly elastic<br />
collapsible hinges) assembly <strong>du</strong>e to the very stringent mass and stowed volume requirements. Main critical issues lie in the<br />
antenna layout, the deployment kinematics, dynamics and simulations, the testability of the mechanical functions and, the<br />
selection of the most suitable materials with respect to ageing and sensitivity to radiations to be encountered in the Jovian<br />
environment in order to guarantee both the deployment and the RF performances of the antenna.<br />
Deliverables:<br />
Deployable antenna demonstration model<br />
Current TRL: TRL1 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2013<br />
Application/Mission: Jupiter missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
T-196, T-732, T-373, T-409,<br />
T-753<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T215-08EE<br />
Wideband Spectrometer<br />
This activity is devoted to the design and practical implementation of wide-band spectrometer system. The activity will start<br />
with a trade-off between several state-of the art technology options. After a preliminary design the activity will be followed by<br />
breadboarding at critical component level after which a re-design will be performed with a full-scale breadboard. Special<br />
emphasis will be given to low mass and low power consumption.<br />
An initial CDF study in very close co-operation with the science directorate has clearly demonstrated the need for this activity<br />
where the mass of the instrument was driving the entire design. With direct relevance to Dossier 0 Science requirements, this<br />
proposal was elaborated and justified within the Harmonisation dossier on Millimetre and Submillimetre waves together with<br />
experts from user directorates who have approved and supported it as relevant and important for their future programmes.<br />
Deliverables:<br />
Spectrometer demonstrator<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2009<br />
EO and Science missions (e.g. Jupiter,<br />
Application/Mission: Contract Duration: 14 months<br />
Venus,..)<br />
SW Clause : - Dossier0 Ref.: T-419<br />
Consistency with Harmonisation<br />
Passive Millimetre and Submillimetre wave Instruments<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T215-09MC<br />
H2 Sorption Cooler<br />
In the frame of a previous <strong>TRP</strong> activity a He4 Sorption cooler was successfully developed. The temperature range covered by<br />
the cooler is 14.5K down to 4.5K. Pre-cooling at 14.5K–15K is required by the He4 Sorption cooler in order to work properly.<br />
Using same technology as developed until now, changing the running gas to hydrogen, the new breadboard might be able to<br />
cool down from 50K to 14.5K. It is the objective of this activity to demonstrate that this is feasible.<br />
Tasks include:<br />
- re-design<br />
- breadboarding<br />
- extensive testing.<br />
Deliverables:<br />
Technical note, breadboard, test report.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2012<br />
Science missions such as DARWIN,<br />
Application/Mission: Contract Duration: 36 months<br />
XEUS (not before 2018).<br />
SW Clause : - Dossier0 Ref.: T-678<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.- Human Spaceflight Manned Exploration<br />
3.1 - Advanced habitats<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T301-03MC<br />
Design Verification & manufacturing aspects relevant for inflatable Mo<strong>du</strong>les<br />
The present activity is proposed in the frame of the development of larger pressurised volumes for habitation (less mature<br />
than Al mo<strong>du</strong>les), required by future manned space missions, longer and more demanding on the crew that LEO missions.<br />
This activity should investigate design, verification and manufacturing aspects relevant for inflatable mo<strong>du</strong>les, e.g. analysis<br />
and test technologies, specific design aspects such as the interface between hard and soft parts of the structure w.r.t. air<br />
tightness, strength, etc. (e.g. docking system or window to inflatable shell) and deployment systems. Preliminary tasks are:-<br />
Identification of possible materials to be used for inflatable mo<strong>du</strong>les- Identification of possible material configurations -<br />
Investigate design, verification and manufacturing aspects- Investigate analysis and test technologies for flexible materials-<br />
Specifically look at juncture between hard and soft materials- Evaluation of the findings.<br />
Deliverables:<br />
Technical datapackage, subscale breadboard of inflatable mo<strong>du</strong>le.<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010<br />
Manned missions, exploration (next step<br />
Application/Mission: should be an in-flight inflatable Contract Duration: 18 months<br />
demonstrator)<br />
SW Clause : - Dossier0 Ref.: T-7896, T-309<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T301-10MC<br />
Title:<br />
Polymerisation of Composite Structures in Free Space<br />
The capability of polymerisation in free-space conditions makes possible the in-orbit deployment of large structures with a long<br />
lifetime. Objective of the proposed activity is the development of the curing process of composite structures in free-space<br />
conditions. In particular: a reference curing process concept shall be developed (thermal, UV, etc); some environmental<br />
testing shall be performed; curing models shall be studied and breadboarded.<br />
Deliverables:<br />
Process description report. Curing process breadboard.<br />
Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: all inflatable (rigidizable) strucutres Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7896<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.2 - Automation and advanced robotic technologies<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T302-02MM<br />
Compact Automatic Tool Exchange Device<br />
Deliverables:<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010-2012<br />
Application/Mission: exploration missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T302-08MM<br />
Title:<br />
Vision Based Manipulation of non-co-operative objects<br />
Non-cooperative objects, in conventional robotics terms, are those which do not provide help to robotics means to ease their<br />
manipulation. In the case of robotics vision, this definition applies to objects not equipped with optical markers. This activity<br />
shall develop a concept of the software/hardware to allow a robot system equipped with a stereo camera sensor to<br />
operate-on/manipulate human-made non cooperative objects. This shall allow real time visual serving control of robot motion<br />
directly into the sensor frame. The activity shall also develop concepts for robust techniques to overcome the problems<br />
created by the extreme lighting conditions typical of orbital applications.<br />
Deliverables:<br />
Breadboard including Vision based manipulation software and hardware, Calibration and test equipment for the software.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010-2012<br />
Application/Mission: exploration missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-6<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.2.1 - Automation & Robotics (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
MMA-622<br />
Title: Dextrous Robot System - Phase 1&2<br />
This activity shall develop a scalable medium-size lightweight dextrous robot arm for external space manipulation applications<br />
to the level of a demonstrator with completely flight qualifiable design. This shall be suitable for being complemented with<br />
more dedicated sub-system developments under GSTP or a similar programme, and for customisation and full qualification<br />
testing by user programmes.<br />
Innovative approaches and technologies shall be exploited to drastically minimise mass and power consumption while<br />
providing adequate force capability and repeatability. A target is to achieve a flight model design of an arm with full joints<br />
instrumentation and harness, with a 1 g payload capacity of 10 kg, within a total mass of 20 kg.<br />
Interface compatibility with existing other building blocks of space robot arm systems (e.g. on-board controller and avionics)<br />
shall be observed.<br />
The activity shall include the following phases:<br />
1. Phase 1 (200 kEuros): System-level requirements analysis and definition, kinematics / structural / thermal / dynamic /<br />
control analyses, system architectural design and specification of requirements for sub-systems (joints, limbs structure, end<br />
effector, latching, ground support equipment).<br />
2. Phase 2 (500 kEuros): Evaluation and trade-off of radically different design concepts for low-power compact space robot<br />
joints according to the requirements established before. Detailed design, development, manufacturing and test of one joint<br />
demonstrator.<br />
3. Phase 3 (1300 kEuros): Upon possible design iterations based on the unit test results from Phase 2, development and<br />
manufacturing of a total of 7 similar joints. Integration in a dextrous robot arm system testbed, demonstration by system-level<br />
testing.<br />
Deliverables:<br />
Technical Note. System design and Requirements definition. Joint demonstrator (design, manufacturing and testing). 7 joints<br />
development, manufacturing, integration and testing in a dedicated test-bed.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010-2012<br />
Application/Mission: exploration missions Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-1<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title: Dextrous Robot System - Phase 3<br />
This activity shall develop a scalable medium-size lightweight dextrous robot arm for external space manipulation applications<br />
to the level of a demonstrator with completely flight qualifiable design. This shall be suitable for being complemented with<br />
more dedicated sub-system developments under GSTP or a similar programme, and for customisation and full qualification<br />
testing by user programmes.<br />
Innovative approaches and technologies shall be exploited to drastically minimise mass and power consumption while<br />
providing adequate force capability and repeatability. A target is to achieve a flight model design of an arm with full joints<br />
instrumentation and harness, with a 1 g payload capacity of 10 kg, within a total mass of 20 kg.<br />
Interface compatibility with existing other building blocks of space robot arm systems (e.g. on-board controller and avionics)<br />
shall be observed.<br />
The activity shall include the following phases:<br />
1. Phase 1 (200 kEuros): System-level requirements analysis and definition, kinematics / structural / thermal / dynamic /<br />
control analyses, system architectural design and specification of requirements for sub-systems (joints, limbs structure, end<br />
effector, latching, ground support equipment).<br />
2. Phase 2 (500 kEuros): Evaluation and trade-off of radically different design concepts for low-power compact space robot<br />
joints according to the requirements established before. Detailed design, development, manufacturing and test of one joint<br />
demonstrator.<br />
3. Phase 3 (1300 kEuros): Upon possible design iterations based on the unit test results from Phase 2, development and<br />
manufacturing of a total of 7 similar joints. Integration in a dextrous robot arm system testbed, demonstration by system-level<br />
testing.<br />
Deliverables:<br />
Technical Note. System design and Requirements definition. Joint demonstrator (design, manufacturing and testing). 7 joints<br />
development, manufacturing, integration and testing in a dedicated test-bed.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010-2012<br />
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Application/Mission: exploration missions Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-1<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.3 - Closed loop life support technologies<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T303-02MC<br />
Bioregenerative Life Support Basic Development<br />
MELISSA has as ultimate objective the development and on-ground demonstration of the basic technology needed to<br />
establish, maintain and control, with absolute minimum need for resupply, closed manned environments (e.g. Lunar Base,<br />
Mars Outpost, Mars transit vehicles).The work is focused on the ground feasibility demonstration of a closed loop of<br />
compartments, each specialised for a specific processing task. Thus waste pro<strong>du</strong>cts from the "crew" compartment are<br />
progressively processed as they move around the loop, finally arriving back at the beginning in the form of regenerated food,<br />
water and oxygen. Although the ultimate goal is space, there is considerable scope for terrestrial spin-off en route, which has<br />
already been realised in the form of 2 patents. Generally speaking, indivi<strong>du</strong>al partners specialise in particular areas, e.g. one<br />
particular compartment, system control algorithms, etc. The results of the past research have demonstrated the theoretical<br />
validity of the concept, as well as the feasibility of each independent compartment. The main objectives of this new phase will<br />
be a pilot scale demonstration, and performance assesment, with 3 coupled compartments.<br />
Deliverables:<br />
Technical notes. Breadboarding.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: manned mission, exploration Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.: T-7787<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T303-11MC<br />
Air Sampling System for Microbial Contaminants Identification<br />
Development of an air sampling system concept for microbial contaminants identification. The proposed activity will exploit the<br />
experience of terrestrial and space in<strong>du</strong>stry, respectively in terms of concentration of microbes from large air volume, DNA<br />
extraction and amplification, and of re<strong>du</strong>ced gravity constraints on liquid handling, hardware miniaturisation, to develop an<br />
instrument for continuous sampling of air on board manned spacecraft. Within this study it is proposed to review and trade-off<br />
the potential concepts of air sampling system compatible with future amplification of the genetic information of the microbial<br />
contaminants, to select the most promising concept, to built a breadboard unit, to test and evaluate this development. This<br />
work will be harmonised with the requirements and developments of MIDASS Project (Microorganisms Detection in the Air<br />
Space Systems).<br />
Deliverables:<br />
Deliverables will include design reports, drawings, test data and developed hardware (breadboard).<br />
Current TRL: TRL1 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: manned mission, exploration Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7778<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.4 - Crew Health and Performance<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T304-01MM<br />
Integrated Countermeasures for microgravity effects<br />
Prolonged microgravity leads to impairment of many Physiology Systems (PS), amongst them bones, muscles and the<br />
neuro-sensory system. Countermeasures to counteract the lack of gravity stimulation are delivered mainly via physical<br />
exercise (treadmill, ergometer) or use of special suits such as the Penguin (in MIR), but results are just moderate. To prepare<br />
for interplanetary missions - and for long-<strong>du</strong>ration ISS stays, additional musculo-skeletal and neuro-sensory countermeasures<br />
need be developed. The aim of this activity is to develop and test technology concepts for integrated countermeasure systems<br />
for each above-mentioned PS, study the compatibilities of the countermeasure technologies (bone, muscle, neurosensory),<br />
define complementarities, assess the design drivers and define a good ergonomics of the system. A biofeedback technology<br />
will also be studied where the vibration frequency, amplitude and direction will be tuned to optimise the musculo-tendinous<br />
responses (EMG, reflexes). The technologies will be characterized and, when possible, evaluated on humans.<br />
Deliverables:<br />
Technology application, evaluation report, specifications for adaptation to ISS.<br />
Current TRL: TRL2 Target TRL: TRL2-3 Application Need/Date: TRL5 > 2012<br />
Application/Mission: Manned Exploration Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7780<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.5 - Free-Flyers (Rendezvous and Docking, In-Orbit Assembly and Servicing)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T306-03MM<br />
Selfcalibrating 3-D optical metrology<br />
3-D imaging system has been developed that uses an interferometric technique to obtain range and profile information. The<br />
system is self-calibrating, once knowledge of the camera and projector are known, and can handle discontinuities. An<br />
improvement to the current system is proposed that would allow it to operate without a piezo stepper, allowing a significant<br />
mass saving. The objective of this work is to breadboard and test the new design. This follows from a concept studied under<br />
fast-track SME <strong>TRP</strong> initiative. Deliverables: Design, build and test of a self-calibrating, 3-D vision system breadboard. Analysis<br />
of system limitations as regards spatial and temporal resolution, field of view etc.<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.6 - Instrumentation for Life Science<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T307-05MM<br />
Immuno-Biochemical Analyser<br />
In-situ ISS Bio-chemical analysis has been recognized a high priority since many years. Results would then become available<br />
in real time, drawbacks of cryo-preservation would be avoided (download weight, biochemical degradation). Previous attempts<br />
to adapt ground clinical analyzers for space use didn't turn out positive results. Hence in the previous <strong>TRP</strong>, it was decided to<br />
explore a technology concept for a ISS-compatible biochemical analyser. Out of this activity, two major technologies have<br />
been confirmed or adapted:- a new microtiter plate (37.5 mm x 20mm 96 reaction wells) with capillary distribution<br />
(microgravity compatible) to be used for bio-chemical measurements,- a Two-Photon excitation (TPX) reader, combined with<br />
optical pressure pumping, has been validated on above microtiter plate, making it suitable for immuno-chemistry<br />
measurements. The aim of this activity is to develop the set of enabling technologies for a ISS-compatible biochemical<br />
analyser in a mid-term future to measure the classes of biochemicals required by ISS physiology research or astronaut<br />
medical follow-up.<br />
Deliverables:<br />
Full technology concept of a ISS-compatible biochemical analyzer, test adaptation proce<strong>du</strong>res, evaluation results.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 > 2010<br />
Application/Mission: ISS/Aurora Medical Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-1306<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T307-09MM<br />
Title:<br />
Virtual reality stimulator<br />
Cognitive neurophysiology is identified as one of the research themes of interest for the ISS. Besides electroencephalography<br />
and electromyography, it requires neurosensory stimulators, amongst them the visual/aural ones. Up to know, because<br />
computer power was limited, virtual reality generators for neurophysiology were custom-designed, closed systems, used only<br />
for one experiment. Moreover, it was not possible to make easy and simple modification of the protocols as scientists usually<br />
need it, this instead required major software and hardware redesigns. Making use of the enhanced capabilities of computers<br />
and virtual reality devices, the proposed activity aims at studying the enabling technologies for the realization of a<br />
multi-purpose, flexible Virtual-Reality generator for cognitive-neurophysiology, that could be used over several ISS increments<br />
by a the wide community of users.<br />
Deliverables:<br />
Documentation, enabling technologies and software for multipurpose virtual reality generator, and evaluation report.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5>2010<br />
Application/Mission: ISS/manned exploration Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T307-15MM<br />
Life Support Technology for MISS<br />
The aim of the activity is to develop a life support system for small animals with good scientific performance and low logistic<br />
load. Typical technologies to be considered include compensation systems for O2 consumption and removal of pro<strong>du</strong>ced CO2<br />
including recycling methods. Furthermore odour control and interaction with the water supply and the waste collection have to<br />
be taken into account. An initial concept phase will be followed by the breadboarding and functional/biological testing of the<br />
complete selected concept.<br />
Deliverables:<br />
Fully functional and verified breadboard of a life support system for small animals.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Photon Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-1314<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.7 - Instrumentation for Physical Science<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T308-03MM<br />
Oxygen sensing/control<br />
Any device operating at elevated temperatures has a strong demand for measuring partial Oxygen pressures as the content of<br />
this radical deteriorates every material in long term, and oxygen outgassing from compounds needs to be immediately<br />
detected to prevent facility damage. Within this activity a development of a sensor technique to measure oxygen partial<br />
pressure in the Electro-Magnetic Levitator processing atmosphere via electrolytic cells with high vacuum compatibility is<br />
proposed. Based on this sensor a control can be set-up that will be completed within this activity in terms of feasibility, too. In<br />
addition the activity will also focus on methods to re<strong>du</strong>ce resi<strong>du</strong>al oxygen concentrations.<br />
Deliverables:<br />
Tested sensor breadboard, oxygen re<strong>du</strong>ction and control loop breadboard<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008<br />
Application/Mission: ISS MSL/EML Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-822<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T308-06MM<br />
Title:<br />
Enhanced Mini Lda<br />
This activity aims at enhancing the features of a 1D-Mini-LDA System currently under development under ESTEC Contract<br />
No. 16554/02/NL/CP.The optical components of the 1D-Optical Measurement Head are already prepared for an upgrade to a<br />
2D-Optical Measurement Head. In addition to the upgrade of the measurement head the expected FSL/EC breadboard is<br />
planned to be used together with the head after having been extended on h/w and s/w level to allow for real simultaneous<br />
measurements of two velocity components and their directions. After design, manufacture, integration and calibration, the<br />
2D-Mini-LDA System shall be applied to representative experiments to verify its scientific measurement performance.<br />
Deliverables:<br />
One 2D Optical Measurement Head, representative for the FSL micro-gravity experiments, integrated into an<br />
updated/calibrated BB system for scientific measurement performance verification. Final Reoprt (+ measurements<br />
experimental verification).<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 by 2008<br />
Application/Mission: ISS FluidLab Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-822<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.8 - Payload Data Handling<br />
<strong>TRP</strong> Reference:<br />
T310-02ES<br />
Title: COTS based space borne computer 1<br />
The use of COTS components for the design of on-board computers is not new but has always been considered in a<br />
case-by-case basis when appropriate. Convergence between several in<strong>du</strong>strial domains: aircraft, automotive and space have<br />
demonstrated that COTS-based solutions used in these domains can be applied also to space. Evolution of the system design<br />
techniques is also rendering possible the use of robustness by design techniques better than intrinsic robustness by radiation<br />
hardening. It is then proposed to study COTS based solution for on-board computers in the domain of high reliability oriented<br />
systems and safety & availability oriented systems. The objective of this activity is to propose solutions towards space borne<br />
COTS based computers and to assess their efficiency and usability for real space missions. At the software level there are<br />
considerations about the reintegration of a failed unit. It is difficult point since modern powerful processors contain on-chip<br />
caches. Reloading of these caches is not possible, and thus the software in the triple units has to be aware that a<br />
resynchronisation is taking place and thus needs to flush the data and instruction caches of the non-failed units. Continuation<br />
of this activity is foreseen in GSTP.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Robotics, Exploration Missions Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7800<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.9 - Intelligent Space Systems Operation (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EME-018<br />
SDE and Space Palmtop Applications<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: EME-019<br />
Title:<br />
On-Board Model Checking<br />
Autonomous systems are able to sense their environment in order to take decision according to the current situation. In<br />
principle, the decision results into a set of actions that should not harm the satellite. However, when the decision is taken by a<br />
fault recovery mechanism, or even more generally, it is safer to verify that the set of actions will not put the satellite into a<br />
hazardous situation.<br />
In order to do so, it is possible to build a model of the states of the satellite, and to verify that when the actions are put on the<br />
model, the resulting state is still safe. This is called model checking. There are several model checking techniques on ground.<br />
However, very few have been embedded on board.<br />
The purpose of the activity is to exercise on a small but representative case study, model checking techniques to be<br />
embedded, and to verify that their performance in terms of memory size, response time and predictability are compliant with<br />
space on-board software requirements.<br />
Deliverables:<br />
Architectural concept + building blocks. (Operational SW usable by the community)<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational >=2007<br />
Application/Mission: planetary exploration Contract Duration: 9 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7667<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
ESD-023<br />
Mission Execution Crew Assistant<br />
For long <strong>du</strong>ration mission (> 1 year), the concept of crew autonomy versus ground control is likely to undergo drastic changes:<br />
• Crew for its own motivation and satisfaction needs to be closely involved into the decision making process<br />
• For cost reasons, staffing for flight control maybe re<strong>du</strong>ced as opposed to conventional shuttle/ISS missions (large number of<br />
real-time flight controllers).<br />
Object of this activity is to design and develop a crew assistance tool for mission planning and execution (Mission Execution<br />
Crew Assistant), to allow the crew to sche<strong>du</strong>le and make conscious decisions for short and mid term activities. The devised<br />
crew assistant is regarded as a complementary tool for mission support in order to optimize the ground/crew task sharing in a<br />
long <strong>du</strong>ration mission scenario.<br />
Deliverables:<br />
Crew assistance tool demonstrator.<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: SW operational (preparation<br />
-<br />
Prototype<br />
of manned missions) >=2015<br />
Application/Mission: manned planetary exploration Contract Duration: 18 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-8063<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETD-037<br />
High Performance Resilient Computer For Autonomous Robotics<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7739<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
MMA-624<br />
Satellite Servicing Building Blocks<br />
Proposals to construct satellites that could be re-fuelled or re-furbished in space have been put forward by several space<br />
actors in the past. However these proposals were quickly dismissed on the fear that the provisions needed on a serviceable<br />
satellite made it more complex, heavier and expensive, than a disposable one.<br />
Besides, in the past, servicing could not bring sensible advantages as life of satellites was mainly limited by the lifetime of<br />
components (e.g. gyros, high-power electronics) than by consumables (fuel).<br />
Advances in technology, trends in size and weight of commercial satellites as well as the increased bus standardisation (<strong>du</strong>e<br />
to the re<strong>du</strong>ction of satellite manufacturers) have changed past considerations.<br />
A satellite-servicing infrastructure together with its satellite engineering standards, and the increased flexibility of satellites built<br />
accordingly, would improve the competitiveness of European in<strong>du</strong>stry. For example satellites built for refuelling could be made<br />
sensibly lighter thus decreasing launch costs. Furthermore lighter satellites would allow higher utilization of launchers<br />
increasing the number of payloads per launch.<br />
To be noted: the DARPA is currently investigating a satellite refuelling system (Orbital Express/ASTRO) for which it has<br />
already awarded study contracts for $6M.<br />
The goal of this activity is to pro<strong>du</strong>ce technology to support co-operative servicing of satellites in GEO.<br />
The Agency has already investigated the needed technologies of Rendez-vous, docking and berthing through previous<br />
<strong>TRP</strong>/GSTP activities, this activity shall therefore focus only on the robotics aspects. Within this frame, objectives of this study<br />
will be first to analyse the objectives/tasks for servicing (re-fuelling, re-furbishing), then to pro<strong>du</strong>ce architecture and identify<br />
interfaces, and finally to design, manufacture and test a demonstrator of servicing hardware.<br />
Deliverables:<br />
Technical note (analysis of objectives/tasks for servicing, architecture, interfaces). Servicing hardware demonstrator (design,<br />
manufacture and test).<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: SW operational by 2010<br />
Application/Mission: all spacecraft Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-1<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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3.10 - Aurora<br />
<strong>TRP</strong> Reference: 03/E15<br />
Title:<br />
Experimental and theoretical study of Mars <strong>du</strong>st effects<br />
In the frame of planetary exploration, a number of issues are related to presence of particles in the flow surrounding a probe<br />
<strong>du</strong>ring its atmospheric entry. Three major situations can be addressed:<br />
(1) For Mars and Earth entries in particular, the presence of <strong>du</strong>st or ice high altitude in the atmosphere.<br />
(2) The particles (carbon etc ) pro<strong>du</strong>ced by the ablation of the heat shield and/or by potential re-condensation of gases in<br />
expansion regions.<br />
(3) The potential presence of organic material (spores, cells ) transported by the flow and contaminating unprotected payloads<br />
of the probe.<br />
This last point is particularly important in the case of sample return exobiology missions.<br />
The problems associated with the presence of the particles can be listed follows:<br />
(1) Mechanical/thermal abrasion of the heat shield<br />
(2) Increased convective fluxes linked to earlier flow transition turbulence<br />
(3) Inclusion of additional chemical species in the flow<br />
(4) Two phase flow<br />
(5) Emission of radiation by the <strong>du</strong>st particles<br />
(6) Electrostatic effects<br />
(7) Potential chemical contamination of payload<br />
(8) Potential biological contamination of payload<br />
It is proposed to perform an experimental and numerical study to assess the problems abovementioned for exobiology and<br />
Mars sample return missions of Aurora programme. The focus of the study will be on points 1, 2, 7 and 8: Assessment of the<br />
influence of <strong>du</strong>st and particles on the transition, the mechanical and thermal loads of the heat shield as a first task,<br />
assessment of contamination, and in particular of survival of biological samples in the hypersonic flow around a probe.<br />
For each of the two tasks, a review of the literature and in particular of the work performed in the frame of ISTC 1549 shall be<br />
performed, numerical approaches shall be selected, and facilities shall be identified for validation tests. A limited number of<br />
test cases shall be set-up and the numerical and experimental methodology selected shall be applied to the test cases. An<br />
effort shall be made to summarize the results and prepare engineering tools or correlations appropriate for design of future<br />
Aurora missions.<br />
Deliverables:<br />
Technical note (experimental/numerical study, assessment of problems for exobiology/Mars sample return missions).<br />
Current TRL: - Target TRL: TRL1 Application Need/Date: TRL5 by 2010<br />
Application/Mission: exploration missions Contract Duration: 15 months<br />
SW Clause : - Dossier0 Ref.: T-16<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference: 03/W15<br />
Title:<br />
Solar cell development for Mars exploration missions<br />
The program is devoted to the characterisation and pre-development of the solar cells to be used for operating in "Low<br />
Intensity Low Temperature" (LILT) conditions. The possible range of environments which could be experienced at Mars is very<br />
wide and dependent upon, in particular, the planetary coordinates, season, surface location and <strong>du</strong>st conditions, which<br />
together dictate the solar spectrum, intensity and diffuse/direct content. This study will characterise solar cell performance<br />
over a range of environmental conditions. However, in order to allow appropriate preparation for Exomars, particular emphasis<br />
will be given to solar cell characterisation over the specific range of conditions, which are expected to be relevant to this<br />
mission. In addition, investigation of the development of solar cells for Mars initiated in the framework of the Aurora General<br />
Study Programme (which focussed upon two possible mission scenarios) will be continued in order to further define the<br />
trade-off's associated with the requirements of different possible Mars missions. This is expected to include manufacture and<br />
testing of one or more new solar cell designs in order to further improve our understanding of the possible performance benefit<br />
under an appropriate range of Mars conditions..<br />
Deliverables:<br />
The following functional devices will be delivered:<br />
* 200 solar cell assemblies<br />
* Technology Data Package<br />
Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL8 by 2010<br />
Application/Mission: Exomars Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7720<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference: 03/W25<br />
Title:<br />
Solar cell electrical characterization facility for Mars exploration missions<br />
The differences between the Mars environment and the orbital environment in which the solar cells are most commonly used<br />
require dedicated facilities to test both the solar cell and the photovoltaic assembly Coupons.<br />
The critical differences between the two environments having strong impacts in the solar cell and photovoltaic assembly<br />
testing are:<br />
- Solar intensity and spectrum modified by <strong>du</strong>st<br />
- Low temperature operation<br />
- Dust deposition on the solar array surface<br />
The Mars surface is characterized by low temperature, low solar intensity and by a solar spectrum which is strongly affected<br />
by the atmosphere. The sunlight reaching Mars is strongly scattered by the <strong>du</strong>st particles hanging in the air; for this reason the<br />
diffused component is larger than the direct light. The direct part of the spectrum, incident on the Mars surface is more intense<br />
in the blue region whereas the diffuse part is more red <strong>du</strong>e to the blue light absorption. Being the opacity of the atmosphere<br />
defined as the optical depth, the total spectrum is redder when the optical depth increases. It can be roughly assumed that the<br />
solar cells will work on Mars at an average temperature between -80oC and +20oC with a solar constant between 0.2 and 0.4.<br />
These conditions are however changing over the course of one day and depend on the seasons and atmospheric<br />
phenomena.<br />
The atmospheric <strong>du</strong>st does not remain suspended in the atmosphere, but deposits out of the atmosphere onto any horizontal<br />
surfaces with a <strong>du</strong>st coverage rate of 0.3 % power loss per day. This is potentially the major lifetime limiting factor for a solar<br />
power system on any Mars mission longer than 100 days.<br />
For these reasons it is very important to upgrade and to modify the existing test facilities dedicated to the characterization and<br />
the qualification of the photovoltaic components, in order to be prepared for the future Aurora missions on the surface of Mars.<br />
To achieve the above described objectives, a first activity is proposed. The consideration / simulation of Martian <strong>du</strong>st<br />
deposition effects on the solar array surface will be addressed in another new Aurora technology activity en<strong>title</strong>d Martian Dust<br />
Simulation Facility for Solar Cells . The main technical objective is the realisation of a solar cell electrical characterization<br />
facility adequate to the specific Mars environment requirements by modifying and upgrading the already existing INTA facilities<br />
at SPASOLAB.<br />
These facilities will be adapted to the electrical characterization of both Silicon and Gallium Arsenide based solar cells.<br />
The following development steps are proposed as follows:<br />
- Modification/Upgrading of the optical system of Spasolab multi-zone solar simulator, dedicated to the multi-junction GaAs<br />
solar cells, by means of the realisation of a dedicated filter able to meet the requirements of the Mars surface illumination<br />
spectrum<br />
- Modification/Upgrading of the optical system of Spasolab single source solar simulator, dedicated to the Silicon solar cells,<br />
by means of the realisation of a dedicated filter able to meet the requirements of the Mars surface illumination spectrum<br />
- Modification/Upgrading of the Cryostat dedicated to the electrical characterization of the solar cells at low temperatures, in<br />
order to be suitable for the existing larger solar cells.<br />
Deliverables:<br />
Assessment/realisation of a solar cell electrical characterization facility (by modifying/upgrading the optical system of Spasolab<br />
).<br />
Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL4 in 2008<br />
Application/Mission: Mars Exploration Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7720<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 74 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference: 03/W35<br />
Title:<br />
Martian <strong>du</strong>st simulation facility for solar cells<br />
The differences between the Mars environment and the orbital environment in which the solar cells are most commonly used<br />
require dedicated facilities to test both the solar cell and the photovoltaic assembly Coupons.<br />
The critical differences between the two environments having strong impacts in the solar cell and photovoltaic assembly<br />
testing are:<br />
- Solar intensity and spectrum modified by <strong>du</strong>st<br />
- Low temperature operation<br />
- Dust deposition on the solar array surface<br />
The Martian <strong>du</strong>st does not remain suspended in the atmosphere, but deposits out of the atmosphere onto any horizontal<br />
surfaces with a <strong>du</strong>st coverage rate of 0.3 % power loss per day. This is potentially the major lifetime limiting factor for a solar<br />
power system on any Mars mission longer than 100 sols.<br />
For this particular reason it is very important to upgrade and to modify existing test facilities that could allow the<br />
characterization and the qualification of the photovoltaic components under representative Martian <strong>du</strong>st conditions so as to<br />
timely match the needs of future Aurora missions on the surface of Mars.<br />
To achieve the above mentioned technical objective, the following activity is proposed:<br />
- Development of a Martian <strong>du</strong>st simulating facility for solar cells and coupons by modifying an already existing Wind Tunnel<br />
facility.<br />
This activity will be mainly devoted to the realization of an environmental test chamber aimed at blowing representative Mars<br />
<strong>du</strong>st over the samples in order to perform specified <strong>du</strong>st adhesion experiments.<br />
The activity will be based on a Mars Dust and Environment Specification to be provided by <strong>ESA</strong>. Special emphasis will be<br />
more particularly placed on the definition of the detailed composition of representative Martian <strong>du</strong>st particulates and of the<br />
environmental conditions to be repro<strong>du</strong>ced under testing. This test specification will be elaborated in the currently running<br />
Aurora technology activity, <strong>title</strong>d Solar Array design and technology development for Mars exploration missions.<br />
Deliverables:<br />
Development of Martian <strong>du</strong>st simulating facility for solar cells/coupons by modifying an already existing Wind Tunnel facility<br />
(Mars <strong>du</strong>st particulate/environment study and consequent realization of an environmental test chamber).<br />
Current TRL: TRL1 Target TRL: TRL4-5 Application Need/Date: TRL5 in 2009<br />
Application/Mission: Mars Exploration Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7720<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Solar Generators & Solar Cells<br />
<strong>TRP</strong> Reference: 04/G15<br />
Title:<br />
Precision landing GNC test facility<br />
To mitigate technical, sche<strong>du</strong>le and cost associated with enabling GNC technologies of future planetary missions requiring<br />
safe precision landing, they have to be tested as much as possible on ground in a precision landing GNC test facility. The<br />
main objective of the activity is to develop a precision landing GNC test facility that will emulate real lander dynamics and test<br />
safe precision landing navigation, guidance and control technologies to the performance level required by future planetary<br />
landing vehicles. Starting from the outputs of the on-going activity on "Verification Strategy for Smart Lander", the activity will<br />
involve: (1) analysis and trade-offs of precision landing GNC test facility configurations, inc. test facility requirements definition;<br />
(2) mechanical and electrical detailed design of the selected baseline test facility configuration; (3) manufacturing, assembly,<br />
acceptance tests and test campaign definition, and (4) integration of smart lander technologies from on-going <strong>TRP</strong> activities<br />
and test campaign results analysis.<br />
Deliverables:<br />
Precision Landing GNC Test Facility; Documentations (technical data package, summary report and abstract), including<br />
precision landing test facility configuration trade-offs/analysis, detailed design, test results, GNC SW demonstrator, test<br />
plan/results.<br />
Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: TR5 in 2008<br />
Application/Mission: ExoMars, MSR Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-8071<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 75 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
04/G25 + T306-01ES<br />
Autonomous Rendez-vous GNC test facility + Integrated Multi-Range Rendezvous<br />
Title:<br />
Control System<br />
Building upon the heritage from ATV, the European reference rendezvous with manned targets in LEO, and ongoing<br />
technological developments applicable to rendezvous systems, the main objective of the study is to design and develop the<br />
2nd generation of space autonomous rendezvous GNC systems applicable to a wide set of potential missions (rendezvous<br />
with cooperative, non cooperative and natural objects). Special emphasis is given on a vision-based solution for the<br />
rendezvous navigation system from target acquistion to terminal approach. Two image processing algorithms, namely<br />
Features Extraction and Object Recognition & Matching, will be developed, prototyped and tested. These algorithms will be<br />
implemented on the NPAL camera breaborad that has been developed vision-based soft landing applications. In order to<br />
support image processing validation in the overall navigation chain, PANGU will be extended in order to generate<br />
representative space scene. Guidance Expert and robust control techniques, that take into account the specificity of<br />
performing rendezvous in elliptical orbit, will be developed and tested via Monte Carlo simulations. Finally, the preliminary<br />
design of the Autonomous Mission Management (AMM) will rely on a multi-layer architecture based on a decision level<br />
(planner) in charge of the onboard operation management, an execution level in charge of the time line detailed definition and<br />
execution, and an independant safety protection level in charge of the collision avoidance. The planner will make use of the<br />
guidance expert system in charge of re-computing adequate trajectories that fulfil the current system constraints. The AMM<br />
design will be validated via computer simulations using an upgraded functional engineering simulator.<br />
Deliverables:<br />
SW/HW, test facility + <strong>document</strong>ation. Documentation (technical data package, summary report, abstract), including<br />
autonomous rendezvous & capture GNC test facility configuration trade-offs/analysis, detailed design, GNC SW demonstrator,<br />
test plan/results.<br />
Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date:<br />
Application/Mission: exploration missions e.g. MSR Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-8070<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Autonomous Rendez-vous GNC test facility + Integrated Multi-Range Rendezvous<br />
Title:<br />
Control System<br />
The activity combines two sub-activities:<br />
1. Autonomous Rendez-vous GNC test facility (04/G25): redez-vous/docking and capture operations are of primary<br />
importance for sample return missions as well as in-orbit servicing and inspection. On the other hand, to mitigate technical,<br />
sche<strong>du</strong>le and cost associated with enabling GNC technologies of future planetary missions requiring rendezvous and sample<br />
capture, they have to be tested as much as possible on ground. The overall study objective is to take a major step towards a<br />
European capability for autonomous orbital rendezvous and docking. Starting from recent study results on lidar/vision-based<br />
GNC systems and heritage from ATV GNC development, the activity concerns (i) the adaptation or enhancement of existing<br />
mission and simulation tools, real-time avionics and dynamics test benches for the validation of a high integrity autonomous<br />
multi-range rendezvous & docking control system (HARVD); (ii) the rapid prototyping of the autonomous mission and vehicle<br />
management (AMM) software and fault detection, diagnosis and recovery (FDIR) software and the integration of the on-board<br />
HARVD S/W demonstrator; (iii) the testing of its real-time performance and autonomous operations and transition capabilities<br />
(terminal rendezvous phase) with hardware-in-the-loop (HIL) in a laboratory environment.<br />
2. Integrated Multi-Range Rendezvous Control System (T306-01ES): The main objective of the study is to define, develop and<br />
breaboard a generic multi-mission rendezvous GNC system applicable to a whole set of potential missions (rendezvous with<br />
cooperative, non cooperative and natural objects). The generic GNC architecture (sensors, actuators, algorithms, avionics)<br />
will be defined for two mission scenarios: in-orbit servicing (Earth environment) and sample return (Mars environment). The<br />
autonomous navigation system will make use of recent technology breakthroughs in vision and imagin lidar. Absolute and<br />
relative attitude and position measurements, from RF sensor and optical camera or lidar sensor, will seamlessly be integrated<br />
using an iterated, extended Kalman filter. Robust guidance and control algorithms will be developed for rendezvous in circular<br />
and elliptical orbits . For maneuver planning, it is foreseen to use a Lambert planner at long range with genetic algorithm<br />
optimization of start and transfer times. A Simplex planner with path constraints will be used at close range. Finally, a<br />
breadboard of the on-board software of the integrated multi-range rendezvous control system, inc. mission management and<br />
FDIR functions, will be developed and real-time performance tests with electrically stimulated relative navigation sensors and<br />
simulated actuator units on the <strong>ESA</strong> generic avionics testbed.<br />
Deliverables:<br />
SW/HW, test facility + <strong>document</strong>ation. Documentation (technical data package, summary report, abstract), including<br />
autonomous rendezvous & capture GNC test facility configuration trade-offs/analysis, detailed design, GNC SW demonstrator,<br />
test plan/results.<br />
Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date:<br />
Page 76 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
Application/Mission: exploration missions e.g. MSR Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-8070<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: 04/K15<br />
Title:<br />
Mars climate database and physical models<br />
In order to compute accurately the incoming solar flux on inclined solar panels, a Monte-Carlo radiative transfer code for the<br />
martian atmosphere has been developed by LMD. Additional work is now needed to complete the Mars Climate Database and<br />
Physical Model development. In particular, the following main tasks are foreseen: validation of the Monte-Carlo radiative<br />
transfer tool for Mars, with a reference radiative transfer tool; implementation of a graphical interface for the Monte-Carlo<br />
code; extension of the capability of the Monte-Carlo code with a feature to compute the incident solar flux for a generically<br />
oriented flat panel on the Mars surface.<br />
Deliverables:<br />
Technical note (incl. the illumination spectrum in four particular conditions); validation report; updated Monte-Carlo Mars Sun<br />
Radiation environment tool, incl. Source Files / User's Manual / test files.<br />
Current TRL:<br />
Target TRL: Operational Application Need/Date:<br />
N/A<br />
tool /<br />
SW operational by 2008<br />
method<br />
Application/Mission: Aurora, Exomars, HMM Contract Duration: 2 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-16<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Mars climate database and physical models<br />
Update the European resources for Mars mission development related to environmental and <strong>du</strong>st characterisation. Re<strong>du</strong>ce<br />
the uncertainties in the parameterization of physical processes.<br />
In order to prepare the future of Mars Exploration in Europe, and in particular improve our knowledge of the Martian<br />
environment at a level suitable for the Aurora program, the unique European Martian Circulation Model and Climate Database<br />
(developed by <strong>ESA</strong> with later support from CNES) must be improved by:<br />
- Inclusion of data from Mars Global Surveyor, Mars Express, and Mars Odyssey<br />
in the European Mars Climate Database (EMCD)<br />
- Dedicated study of the Mars atmosphere <strong>du</strong>st storms<br />
- High latitude processes on Mars (CO2 and H2O ice microphysics)<br />
- Inclusion of heating rate by phototelectrons in simulation of the<br />
thermosphere (120 - 300 km)<br />
- High resolution simulations of the lower atmosphere<br />
- Upgrades of the EMCD access software.<br />
Deliverables:<br />
Improved general circulation model of the Martian atmosphere, allowing mesoscale simulations; Assessment of Martian<br />
environment <strong>du</strong>ring <strong>du</strong>st storms; Improved Martian climate database based on assimilated data of current Mars missions.<br />
Current TRL:<br />
Target TRL: Operational Application Need/Date:<br />
N/A<br />
tool /<br />
SW operational by 2008<br />
method<br />
Application/Mission: Aurora, Exomars, HMM Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-16<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 77 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference: 04/K25<br />
Title:<br />
Martian radiation environment models<br />
The aim of this activity is to pro<strong>du</strong>ce dynamic models of the radiation environment on and around Mars.<br />
Due to the rarity of its atmosphere, the surface of Mars is exposed to large fraction of the incoming cosmic ray heavy ions,<br />
solar X-rays and ultraviolet radiation and, <strong>du</strong>ring solar active periods, to large fluxes of energetic solar charged particles.<br />
Adding to these, there is a contribution from secondary particles generated by nuclear reactions either in the atmosphere or<br />
on the Martian surface, neutrons being of particular concern.<br />
The following features will be addressed:<br />
- In-orbit radiation environment around Mars;<br />
- Atmospheric attenuation of incoming radiation<br />
(utilising the existing dynamic models of the Martian atmosphere);<br />
- Surface contours and altitude variations;<br />
- Effects of <strong>du</strong>st storms to radiation propagation;<br />
- Particle absorption and backscattering from the surface, taking into account the<br />
latest results on the water content and the elemental composition of the local soil;<br />
- Local pockets of magnetic fields in the southern hemisphere of the planet,<br />
and their potential radiation shielding effect.<br />
The study shall utilize the new data from Rosetta SREM instrument. The models shall enable input of galactic cosmic ray and<br />
solar event particle spectra as chosen by the user. The particle transport software shall utilise the open-source Geant4 toolkit<br />
and be implemented in an easy-to-use WWW-based engineering environment. Interface to the existing Mars environment<br />
data base<br />
(http://www-mars.lmd.jussieu.fr/mars/live_access.html)<br />
could be considered.<br />
Deliverables:<br />
New WWW-based, easy-to-use engineering models and software for Martian radiation environment prediction.<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: SW operational (updated<br />
TRL1<br />
TRL3<br />
model) >2007<br />
Application/Mission: Aurora missions phase B from 2007. Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-16<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 78 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference: 04/K35<br />
Title:<br />
Cleaning / sterilisation technologies<br />
Future Mars exploration missions will call for the implementation of planetary protection policy and regulations. The ExoMars<br />
of the Aurora programme will seek evidence of life through in situ investigations on the surface of Mars. A mission designed to<br />
return the first Martian samples is also being studied.<br />
One of the great challenges is to develop or find the adequate technologies that will make compliance with planetary<br />
protection policy routine and affordable. Planetary protection is directed to:<br />
- the control of microbial contamination associated with robotic space vehicles intended to land;<br />
- the control of contamination of the Earth by extraterrestrial solar system material collected and returned by such missions.<br />
A state-of-the-art survey will be first performed so as take stock of past relevant Russian and European experience gained in<br />
the Mars 96 mission and Beagle 2 project regarding the compliance with planetary protection requirements. The aim of the<br />
study is then to focus on technologies / techniques requiring additional development effort for possible implementation into the<br />
future Mars exploration missions of Aurora programme. Special attention will be more particularly paid to cleaning / cleaning<br />
validation of surfaces of S/C-payload elements to be sent to Mars or to be used in laboratories for specific testing.<br />
The goal is to remove all types of contaminants like microorganisms, cells, and organic molecules to levels beyond the<br />
sensitivity of the scientific instrument used for the detection of traces of life.<br />
The activity will address cleaning proce<strong>du</strong>res, equipment necessary to achieve the required cleanliness, instrumentation to<br />
verify the cleanliness level achieved and handling and packaging proce<strong>du</strong>res to maintain the required cleanliness level.<br />
The purity of the surfaces may be achieved by using flashes of UV light at 7eV, ozone, detergent followed by a second<br />
cleaning and inspection. The hardware should be designed to allow cleaning of all critical items to be in contact with soil and<br />
detection tools and allow integration of this material in a protective envelope before flight. Sterilization techniques will also be<br />
investigated for suits, laboratory cabinets, tools and containers.<br />
Deliverables:<br />
Preocess assessment note (cleaning proce<strong>du</strong>res, necessary equipment necessary, verification instrumentation,<br />
handling/packaging proce<strong>du</strong>res to maintain the required cleanliness level).<br />
Current TRL: TRL1 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Exomars Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7718<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: 04/T45<br />
Title:<br />
Passive variable thermal con<strong>du</strong>ctance device for Mars rover applications<br />
The primary task of the Thermal Control Subsystem is to guarantee that all satellite components can operate in a benign<br />
thermal environment. In general, in order to maintain the units within allowable temperature limits regardless of varying<br />
external conditions and unit operating mode, the radiator is sized for hot case operation and sufficient heater power has to be<br />
allocated in the other cases. However, power is a limited resource for a spacecraft and needs to be properly allocated among<br />
the subsystems. In the USA R&D in the field of thermal control has focused on developing novel techniques to effectively keep<br />
the temperature of electronics within the required limits while re<strong>du</strong>cing spacecraft power requirements. A paraffin-actuated<br />
heat switch as part of the thermal-control system for the battery on board a Mars rover has been developed and qualified. A<br />
heat switch is a variable thermal con<strong>du</strong>ctance device, which is mounted between a dissipating component and a cold sink.<br />
The temperature of electronics is passively controlled by the variation in con<strong>du</strong>ctance of the switch: the higher the power<br />
dissipation, the higher the thermal con<strong>du</strong>ctance. This allows the removal of excess heat from dissipating units when<br />
necessary, while the re<strong>du</strong>ction in con<strong>du</strong>ctance prevents the electronics to get too cold.<br />
The goal of this activity is to develop a lightweight heat switch device for passively controlling the temperature of dissipating<br />
units.<br />
Deliverables:<br />
High performance thermal switch at breadboard level (design, manufacturing and testing).<br />
Current TRL: TRL2 Target TRL: TRL5 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Exomars rover Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7716<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 79 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T213-01SC<br />
Water sensor for Mars Exploration<br />
This study is intended to develop a method, which can easily analyse water films on grains. Such a technique must be<br />
incorporated into an instrument requiring low resources (mass, power, volume) and placed on the surface of Mars. Since<br />
many sites on the Martian surface need to be visited, the instrument must be incorporated into a mobile surface rover having a<br />
soil penetration capability. A possible technique, which may satisfy the requirements, is infrared spectroscopy in combination<br />
with attenuated total reflection (ATR). In combination with a spectrometer the ATR method delivers an absorption spectrum of<br />
the substance close to the boundary between the grain and the thin film. In the case of water films on Martian soil grains a<br />
Fourier infrared spectrometer would appear appropriate. It would be sensitive not only to the water film but also detect other<br />
adsorbates on the grains surface. There are other techniques and physical principles which could serve to reach the scientific<br />
goals. Eventually the ideal technique or combination of techniques has to be identified. Measurement principles and<br />
instrument design issues of ATR-IR spectroscopy are addressed under a current <strong>ESA</strong> contract.Resources are crucial for this<br />
instrument and must be minimised and in particular the weight and corresponding small outer dimensions are the key drivers<br />
for the assessment of an advanced design of an ATR. Initially the instrument must be able to be incorporated into a transport<br />
vehicle. The baseline is the <strong>ESA</strong> Nanokhod rover having a sub-surface penetration capability, i.e. a drill with a sample return<br />
to the surface for ATR analysis from the Rover payload cab. In a second scenario the sensor should also be integrated into a<br />
surface penetrating device (the <strong>ESA</strong> mole now under development). The design should serve a wide range of exploration<br />
strategies for the Martian surface.<br />
Deliverables:<br />
Breadboard model.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008<br />
Application/Mission: ExoMars Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-670<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T213-03MM<br />
Title:<br />
Sampling drill tools for rocky and granular soils<br />
This activity will develop and demonstrate three alternative tool designs (ca. 20 mm in diameter) to be mounted on a drill, to<br />
collect soil samples (sand or rock) at a desired drilling depth, the Mars surface being considered as reference. Operation of<br />
the soil sampling tools is based on opening and closing the sample chamber in the tool at the desired depth. Operation of a<br />
rock sampling tool is based on a wedge-type core cutter ring or a conical core catcher. A combined rock and granular soil<br />
sampling tool will be able to sample both sandy and rocky soil with negligible losses. Tool actuation force will be traded-off: it<br />
may be generated either by electric actuators (motor, solenoid, shape memory alloy), or it may passively take advantage of<br />
drill rotation or reversal of the drill rotation.<br />
Deliverables:<br />
Drill Tool<br />
Current TRL: TRL2 Target TRL: TRL5 Application Need/Date: TRL5 in 2008<br />
Application/Mission: ExoMars, MSR Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-824<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 80 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T213-04MM<br />
Ultrasonic Tools for Planetary Surface Exploration<br />
The suitability of ultrasonic tools, e.g. for coring and drilling to limited depth (or generally sample acquisition and<br />
transportation) shall be studied and demonstrated with adequate hardware. A small initial feasibility study has been carried out<br />
by Leicester University in the frame of the AURORA programme, and has encouraged the use of ultrasonic tools for miniature<br />
sampling devices. Compared with classical mechanical corers and drills, ultrasonic equipment is very robust and simple as it<br />
does not require a high number of moving parts or a sophisticated drive mechanism. Several actuator types and mechanical<br />
amplifiers shall be studied. A major constraint is expected with the typical electric power limitations of planetary landing<br />
missions. Furthermore, the interaction of ultrasound with rock and softer materials is largely unknown.<br />
Deliverables:<br />
Demonstrator Model(s), including the ultrasonic trans<strong>du</strong>cer and drive electronics.<br />
Current TRL: TRL2 Target TRL: TRL3/4 Application Need/Date: TRL5 in 2008<br />
Application/Mission: ExoMars, MSR Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-824<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T213-06MM<br />
Title:<br />
Imaging Lidar technology<br />
Nowadays Imaging Lidars can perform measurements up to few kilometres at typical distance resolutions of a few centimetres<br />
at a rate of a few kHz. Imaging Lidars can support a number of space applications on orbiter mo<strong>du</strong>les, landers and planetary<br />
rovers like surface mapping, hazard avoidance and safe landing, navigation, multiple spacecraft operations (rendez-vous and<br />
docking), target properties recognition. However, since most of these systems rely on complex scanning mechanisms, they<br />
are bulky and often too heavy for future solar system exploration missions. The recent emergence of novel and advanced<br />
technologies like new 2-dimensional detector arrays (APD or CMOS arrays) and optical micro components (like MEMS and<br />
MOEMS) will bring a new trend in the development of compact, high resolution and multi-task sensor Imaging Lidars. This<br />
activity shall study the use of these novel technologies, assess the impact on the Lidar performances and develop an Imaging<br />
Lidar proof-of-concept breadboard that validates these technologies, making the Imaging Lidar a feasible instrument for space<br />
applications in the frame of AURORA.<br />
Deliverables:<br />
Imaging Lidar breadboard.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 in 2009<br />
Application/Mission: Aurora (ExoMars) Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7715<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T213-07MM<br />
Title:<br />
Down hole hammering Mechanism<br />
The objective is to develop a high-energy (0.5-2 J/impact) hammering system, that can be placed inside the drill string (20-40<br />
mm in diameter). Power generation can utilize an electric motor, but shape memory alloys and piezo-elements (operating in<br />
an inch-worm manner) can be considered as an option. An optional passive mechanism to take impact power directly from the<br />
drill rotation (without any additional power sources and power feed-through) can also be considered. Impact frequency will be<br />
limited by the power of the actuator; however, impact energy must be kept at a level high enough to provide the desired effect.<br />
Deliverables:<br />
Breadboard of a drill- hammering device.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 in 2008<br />
Application/Mission: ExoMars, MSR Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-824<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T213-08MM<br />
Biochemical analyser<br />
Bio-chemical analysis is taking an increasing importance not only for the Space Station but also for interplanetary missions,<br />
first for search for life and later for supporting manned missions. If a system can be made available for the ISS in a relatively<br />
short term, it will use commercial, wet reagents with stability span of a couple years maximum, hence not compatible with<br />
long-<strong>du</strong>ration interplanetary missions without re-supply capabilities. To be interplanetary-mission compatible, both technology<br />
and consumables (i.e. the reagents) must be adapted to re<strong>du</strong>ced volumes and be compatible with preservation constraints<br />
and re<strong>du</strong>ced operational capabilities (the first systems will be fully automated). No system is known that may be compatible<br />
with interplanetary mission requirements.<br />
Deliverables:<br />
Feasibility assessment.<br />
Current TRL: - Target TRL: TRL2 Application Need/Date: TRL5 > 2012<br />
Application/Mission: MSR Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-1272<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.- Space Transportation / Re-entry Technologies<br />
4.1 - Materials and Structures / Advanced Hot Structures and Thermal Protection Sy<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T401-02MC<br />
Damage Tolerance of Cryogenic Pressure Vessels<br />
Cryogenic pressure vessels are one of the key applications for reusable space launcher design. The use of friction stir welded<br />
aluminium lithium for such structures is expected to improve their efficiency in terms of saved mass and design solutions. The<br />
objective of the proposed activity is to study and characterise the friction stir welded Aluminium Lithium from damage<br />
tolerance point of view in cryogenic pressure vessel applications.<br />
Deliverables:<br />
Al-Li friction stir welding characterisation report; Al-Li friction stir welding defects NDI detection method report; Al-Li friction stir<br />
welding damage tolerance assessment. Test specimens.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 >2008-2010<br />
Application/Mission: launchers Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7653<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.1.1 - Structures & Thermal Protection (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/MCS-001<br />
Full Scale structure Qualification Methodologies<br />
The proposed activity focuses on the development of qualification techniques for hot structures and thermal protection<br />
systems by use of plasma facilities.<br />
The project aims at advancing the European Technology readiness level in such critical hot structural components, maturing<br />
the European know-how in aerodynamic control surfaces design, manufacturing and testing methodologies, for any future<br />
space transportation system application. This will be achieved by performing the design, development, manufacturing and<br />
qualification in the Scirocco facility of metallic and CMC (Ceramic Matrix Composite) components.<br />
Two significant test cases have been identified in order to provide actual results:<br />
• aerodynamic control surfaces, to test simple CMC structures<br />
• a hybrid structure winglet, to test the ceramic/metallic coupling.<br />
More in detail, the following main tasks will be carried out:<br />
1. Design manufacturing and testing of aerodynamic control surfaces of re-entry vehicles, consisting of design, fabrication and<br />
testing within Scirocco of ceramic flaps. For practical reasons an existing flight component has been selected as reference<br />
design for the flaps, the EXPERT flight test bed flaps. Indeed, the proposed activity would benefit of such an exceptional near<br />
term opportunity to validate the entire design-to-fly methodologies, and to perform a full verification loop with in-flight<br />
qualification.<br />
2. Demonstration of a ceramic/metallic hybrid structure, consisting of fabrication and testing of a winglet as suitable for a lifting<br />
re-entry demonstrator.<br />
The main technological issues will be relevant to the coupling of different hot structural materials and components, with<br />
different thermo-mechanical properties, subject to severe thermo-mechanical environments, such as those for winglets of<br />
reusable space transportation concepts.<br />
As reference component the scaled X-38 winglet upper fin has been selected, to mature the technology for any future lifting<br />
re-entry demonstrator development.<br />
Deliverables:<br />
Qualification breadboard of aerodynamic control surfaces of re-entry vehicles, i.e. ceramic flaps (design, manufacturing and<br />
testing within Scirocco). Breadboard of a winglet as suitable for a lifting re-entry demonstrator.<br />
Current TRL:<br />
TRL1-2 Target TRL: Application Need/Date: TRL8 (in-flight demo on<br />
TRL3-4<br />
EXPERT) by 2007<br />
Application/Mission: EXPERT, future re-entry vehicles Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-8133<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MCT-998<br />
Smart Thermal Protection System<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7897<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.2 - Materials and Structures / Advanced Materials<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T403-02QM<br />
High temperature complex parts based on intermetallic components<br />
The proposal intends to develop injection of parts made of gamma TiAl for propulsion thrusters parts with complex geometry.<br />
It comprises the following:- Critical review of requirements for propulsion parts suitable for TiAl materials will be performed.-<br />
Design of an of elegant breadboard (EBB).- Improvement of manufacturing process of intermetallic powder by a<br />
Self-propagating High-temperature Synthesis (SHS).<br />
Deliverables:<br />
Technical notes. Design of breadboard-Test samples and reports-Breadboard.<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010-2012<br />
highly loaded, high temperature parts in<br />
Application/Mission: propulsion systems. <strong>ESA</strong> next generation Contract Duration: 18 months<br />
concepts.<br />
SW Clause : - Dossier0 Ref.: T-8133<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T403-03MC<br />
Title:<br />
Multiphysic Modeling of Near-surface Phenomena<br />
In the last decade many advancements have been achieved in the theoretical modeling of hypersonic flows, but still<br />
phenomena exist that need to have deeper understanding for the improvement of TPS design with re<strong>du</strong>ced safety margins. In<br />
the design of Thermal Protection Systems (TPS) a crucial issue is the correct evaluation of the heat fluxes. To this end, it is<br />
proposed to describe by accurate modeling the complex flow/structure interactions, and namely phenomena of catalysis,<br />
oxidation and ablation. In particular: near surface phenomena will be identified and modelled, including fluid/structure<br />
interactions (catalysis, oxidation, ablation); a test case will be selected and simulated and a recommendation will be<br />
formulated on the basis of the results analysis.<br />
Deliverables:<br />
Technical note (+ near surface phenomena identification/model description). Model (fluid/structure interactions: catalysis,<br />
oxidation, ablation). Test case selection/simulation. Results analysis + conclusion/recommendation.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 >2010<br />
Exploration missions, FLPP, Planetary<br />
Application/Mission: Contract Duration: 18 months<br />
entry missions<br />
SW Clause : - Dossier0 Ref.: T-8091<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T403-03MC.B<br />
Multidisciplinary Modeling of Fluid Structure Interaction<br />
In the last decade Europe has invested significant effort in the development and qualification of various hot structures and<br />
thermal protection systems (TPS) as well as on the theoretical modeling of hypersonic flows; although major critical issues<br />
have been addressed and several investigations have been successfully carried out, further attention is required to improve<br />
the understanding of the physical phenomena occurring at the interfaces between the aerodynamic flow field and the TPS<br />
outer surface, to enhance the prediction of the thermo-mechanical environment, and, thereafter, to re<strong>du</strong>ce the design margins.<br />
To this end it is proposed to characterize the thermo-chemical fluid-surface interactions occurring in the proximity of the outer<br />
surface (and on the surface itself) by physical and numerical modeling and to study and apply a suitable fluid/structure<br />
coupled approach, so that the analysis capability of the flight thermo-mechanical environment is enhanced.<br />
A set of test cases will be selected and simulated and a recommendation will be formulated on the basis of the results<br />
analysis.<br />
Deliverables:<br />
Technical note (+ survey on critical fluid-surface interaction phenomena and fluid-Structure thermal coupling, Modeling report).<br />
Models. Computational mo<strong>du</strong>les. Test cases selection/simulation. Results analysis + conclusion/recommendation.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: SW operational >2010<br />
Design SW for TPS for Space<br />
Application/Mission: Transportation applications, entry Contract Duration: 18 months<br />
missions<br />
SW Clause : - Dossier0 Ref.: T-8091<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T403-09MC<br />
Title:<br />
Increase of Bolted Joint performance for CFRP<br />
Joining of structural CFRP-parts with bolts and rivets is a common approach for manufacturing and repairing in the space and<br />
aeronautical in<strong>du</strong>stry. However this joining method does not reflect an appropriate joining technology in terms of fiber<br />
reinforced plastics (FRP). The main principle in joining with bolts and rivets is the fact that forces are transferred not by<br />
tension and pressure force but by shear and bearing stress. Fiber reinforced plastics with common matrix systems usually<br />
reach good values for tension and pressure but not for bearing stresses and are therefore not suitable for a bolted joining.<br />
Current studies on metal-composite laminates for aircraft composite joints show that these offer better mechanical and fatigue<br />
performance over conventional composite bolted joints. An alternative way to increase the bearing stress would be by<br />
intro<strong>du</strong>cing local softened carbon fiber laminates. Therefore the development and evaluation of composite laminate bolted<br />
joint concepts for highly loaded launcher and RLV space applications is urgently needed. The proposed activity aims at<br />
studying and evaluating possible concepts of composite laminate bolted joint, for highly loaded space applications, including<br />
removable and replaceable joints.<br />
Deliverables:<br />
Design and verification guidelines for highly loaded composite structural joints. Reference design catalogue. Reference tests<br />
data collection. Test specimens.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 > 2008<br />
Application/Mission: spacecraft and launcher structures Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-534<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T403-14MC<br />
Cryogenic Composite Tanks and Lines<br />
During FESTIP 1 and 2, a feasibility study was carried out to assess the possibility of replacing all-metal cryogenic fluid<br />
transfer lines for launchers, with composite lines with low mass and good thermal insulation properties. This feasibility study<br />
took as reference the Ariane 5 feed line dimension: inside diameter of 185mm, with the length limited to 1m. Different<br />
techniques to design and manufacture such items using composite materials concluded that there are two different ways, both<br />
using filament winding technique for composite components: Single wall piping -composite piping with a metallic barrier/liner to<br />
re<strong>du</strong>ce the gas diffusion at cryogenic temperature; Double walled, vacuum insulated cryogenic composite line, which further<br />
re<strong>du</strong>ces the heat leaks through the system. The goal of this activity is to further develop the technology for designing and<br />
manufacturing light-weight cryogenic tanks and lines based on composite technology. Substantial mass re<strong>du</strong>ction for<br />
cryo-tanks and lines is expected while at the same time the parasitic heat leaks will be re<strong>du</strong>ced thereby increasing the lifetime<br />
of cryogenic storage (stand-time).The following tasks are envisaged:- adapt/develop processes, proce<strong>du</strong>res (e.g. machining<br />
steps, welding) to pro<strong>du</strong>ce small diameter lines including fittings and connections as well as cryo-tanks- design and<br />
manufacture a cryo-tank with some appropriate cryo-lines- perform a complete thermal and mechanical test programme with<br />
the built H/W to derive e.g. stand-time, parasitic heat leak, leakage.<br />
Deliverables:<br />
Processes and proce<strong>du</strong>res to pro<strong>du</strong>ce light-weight cryo-tanks, lines and systems based on composite technology. H/W: fully<br />
tested (thermal and mechanical) cryo-tank and lines.<br />
Current TRL: TRL1-2 Target TRL: TRL4-5 Application Need/Date: TRL5 by 2010<br />
Space Missions (Science, Aurora, etc.)<br />
requiring cryogenic liquid storage<br />
(>=2009); Launcher, for launcher mass<br />
Application/Mission:<br />
re<strong>du</strong>ction by re<strong>du</strong>cing the mass of the<br />
Contract Duration: 30 months<br />
propellant tank and of the fluid feed lines<br />
(>=2010)<br />
SW Clause : - Dossier0 Ref.: T-8138, T-605, T-703<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.3 - Materials and Structures / Advanced Structures<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T405-01MC<br />
Non-destructive inspection methods for re-usable CFRP structures<br />
Secure NDI methods for CFRP structures are mandatory to guarantee re-use of reusable launcher structures like CFRP<br />
LH2-tanks or to identify maintenance or repair needs. Baseline technology and widely used is ultrasonic inspection (US), but it<br />
has some limitations (exact damage detection and location, damage detection in complex and large structures, mobility of<br />
inspection system, accuracy of information). Other inspection technologies meanwhile reached respective maturity and are<br />
interesting alternatives. It is proposed to perfom non-destructive inspection of structures for RLV, in particular: identification<br />
typical re-usable launcher structures for inspection, Technology Review of Existing Methods, NDI Methods Evaluation<br />
Program (Damage Sample Test Program), Damage Classification for Re-Usable CFRP Structures, CFRP structure test<br />
program (e.g. tank structure), Recommendations and Synthesis.<br />
Deliverables:<br />
Technical notes: survey of typical re-usable launcher structures for inspection and existing methods, NDI Methods Evaluation<br />
Program, Re-Usable CFRP structures damages classification and test program, test specimens.<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010<br />
RLV and ELV structures, composite<br />
Application/Mission: tanks / spacecraft tanks; FLPP Contract Duration: 18 months<br />
demonstration vehicle<br />
SW Clause : - Dossier0 Ref.: T-8134<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.4 - Propulsion / Advanced Liquid Propulsion<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MPC-846<br />
Acquisition and Evaluation of Cryo-Solid Propulsion: Additional Testing<br />
Conventional solid rocket propellants have specific impulses that are low compared to cryogenic liquids. Cryogenic Solid<br />
Propellants (CSP), defined as frozen propellants that normally are liquids or gases, compare very favourably with conventional<br />
ones. The objective of this activity is to establish a firm evaluation of CSP in terms of applicability, performance, operability<br />
and cost. It is also necessary to establish the theoretical and experimental foundations of CSP-grain design, pro<strong>du</strong>ction,<br />
integration, handling, ignition, combustion etc and rapidly provide the knowledge base of a prototype demonstrator version of<br />
a CSP-motor. Experimental work carried out as part of this activity shall include investigations of strand burner and tests with<br />
sub-scale motors. This CCN will continue the experimental work.<br />
Deliverables:<br />
Test data<br />
Current TRL: TRL2 Target TRL: TRL2/3 Application Need/Date: TRL5 by 2020<br />
Application/Mission: Future launchers Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7741<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T402-05MP<br />
Scaling of Thermal Cavitation Effects on Cavitation-In<strong>du</strong>ced Instabilities<br />
Thermal cavitation effects, <strong>du</strong>e to evaporation or condensation phenomena at the cavity interface, have long been known to<br />
deeply affect the steady performance of cavitating turbopumps. The main objective of the activity consists in investigating<br />
whether and to what extent established scaling laws developed for steady thermal cavitation effects are also applicable for<br />
correlating dynamic cavitation phenomena, cavitation-in<strong>du</strong>ced instabilities, unsteady fluid forces and moments acting on<br />
turbopump in<strong>du</strong>cers. Thermal cavitation effects must be investigated by adjusting the liquid temperature as necessary for<br />
adequately scaling the pump prototype operating at design conditions (flow coefficient and cavitation number) with the given<br />
propellant. Instabilities must be characterized by both high-speed video movies and flow instrumentation (pressure and flow<br />
trans<strong>du</strong>cers), so to measure the instantaneous unsteady fluid forces acting on the rotors. Finally, some of the unsteady<br />
cavitation phenomena observed <strong>du</strong>ring the test campaign should be simulated and analysed with a 3D unsteady cavitation<br />
code, taking into account the thermal effects.<br />
Deliverables:<br />
Database and test data for validation of SW tools.<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: TRL5 by 2007<br />
Application/Mission: ArianeV and evolutions. Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-604<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
T402-10MP<br />
Unsteady subscale force measurements within a launch vehicle base buffeting<br />
Title:<br />
environment<br />
Prediction of the unsteady forces on a full-scale, main stage, nozzle is normally obtained via wind tunnel testing. In such wind<br />
tunnel testing however, problems arise when the forces on the nozzle need to be evaluated. In the past this has been<br />
achieved using heavy instrumentation of the nozzle, to allow integration of unsteady pressure measurements and, thus, the<br />
derivation of the forces. This technique has, to date, been proven to be unreliable and the results are sometimes questionable,<br />
<strong>du</strong>e to the drastic modification of the model of the nozzle required to accommodate the instrumentation. Based of the above,<br />
the proposed <strong>TRP</strong> activity is defined as follows: 1. In a first step, available literature should be examined and an evaluation of<br />
the potential for the separate techniques should be given.2. Secondly, a technical specification for a system, allowing the<br />
direct measurement of the unsteady forces on a scale nozzle in a representative environment, should be defined. 3. Finally,<br />
the performance of the new system should be: evaluated in testing; compared against the pressure integration techniques<br />
already developed; scaled for comparison against available flight data.<br />
Deliverables:<br />
Tech. Spec of Measurement methodology of unsteady forces on subsc. nozzle (representative of launch vehicle base flow<br />
environment). Final report (subsc. test results, comparison with avail. flight data, applicat. w.r.t. assoc. flow structure<br />
interations).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2011<br />
Application/Mission: all launchers, future launchers Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-436<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.5 - Propulsion / Advanced Propulsion Concepts for In-Space Operations<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T404-02MP<br />
Technical Assessment for High Power Magneto Plasma Dynamics (MPD) Systems<br />
The proposed activity has the following main objectives: 1. Mission analysis, to investigate MPD mission possibilities and<br />
subsequent MPD system requirements. 2. Preliminary consideration of a MPD in the 110-300kW range, and critical areas<br />
identification (self applied and externally applied magnetic field solutions shall be studied and a trade-off shall be performed);<br />
lifetime issues and possible improvement/solution shall be considered. The physical phenomena shall be analysed and<br />
possible design analytical and mathematical models shall be used to evaluate impacts on the MPD system. A comparison<br />
between self applied and applied magnetic field should be done.3. MPD roadmap: research and development activities plan to<br />
achieve the maturity of the technology shall be done, together with the required time sche<strong>du</strong>le evaluation. The Aurora<br />
programme shall be taken into consideration as main driver.<br />
Deliverables:<br />
1. Mission analysis report. 2. 110-300kW MPD preliminary design report.3. MPD roadmap report.4. Final report<br />
Current TRL: TRL2 Target TRL: TRL2-3 Application Need/Date: TRL5 >2015<br />
Future high power platforms (exploration,<br />
Application/Mission: Contract Duration:<br />
etc.)<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Electric Propulsion<br />
Roadmap and Conclusions:<br />
18 months<br />
<strong>TRP</strong> Reference: T404-03MP<br />
Title:<br />
Advanced Electric Propulsion for a Service Mo<strong>du</strong>le for VEGA<br />
This activity includes the detailed assessment and preliminary design of a service mo<strong>du</strong>le using electric propulsion (EP) to be<br />
applied for LEO-MEO/LEO-GEO transfer orbits in order to increase payload capability of the Vega launcher. The service<br />
mo<strong>du</strong>le shall be equipped with independent AOCS, telecommunications system, autonomous navigation system (to re<strong>du</strong>ce<br />
cost of the ground segment). A set of orbital maneuvers (station keeping, GEO transfers and corrections on LEO) shall be<br />
guaranteed. EP technologies to be assessed for the mo<strong>du</strong>le are related to both classical EP (i.e. gridded ion engines,<br />
Hall-effect thrusters and other types of EP. After a trade-off on performance, configuration and mission capability, the mo<strong>du</strong>le<br />
shall be designed and a development plan shall be prepared. The detailed activities include: feasibility study of EP (applied to<br />
Vega), I/F’s requirements w.r.t the launcher, mo<strong>du</strong>le configuration study, key technologies evaluation, mission analysis,<br />
development & cost plans for B, C, D phases.<br />
Deliverables:<br />
Technical reports. Design file.<br />
Current TRL: - Target TRL: TRL1 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Vega evolution. Contract Duration: 14 months<br />
SW Clause : - Dossier0 Ref.: T-7758<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.6 - Propulsion / Air-breathing Propulsion<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T407-01MP<br />
Design of Flight Test Configuration for High-speed Airbreathing Propulsion<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.7 - Propulsion / Solid Propulsion<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T411-01MP<br />
Hybrid propulsion evaluation for liquid booster application<br />
Whilst Hybrid Engine Technology has been around for many years, it has made significant improvements in recent years and<br />
now is a realistic option for low cost Expendable Launch Vehicle (ELV) boosters. The main objectives of this study are: - to<br />
perform a survey of the state-of-the-art to identify possible propellant combinations, their applications for a ELV booster<br />
application and a system trade-off; - to compare hybrid propulsion with current baseline solid boosters and to identify future<br />
technological investigation/research programmes; - a detailed review of Hybrid Rocket Engines should be performed to<br />
evaluate the state-of-the-art and potential applications. This would include a literature and market survey, and system trade-off<br />
studies toassess the potential advantages of using Hybrid Rocket Engines. The work should include the following: - Hybrid<br />
propulsion literature review of state-of-the-art (+ identification of possible propellants combinations, particularly to non-toxic<br />
combinations), assesment of potential applications, for future space / launcher, and def. of requirements related to the<br />
proposed booster; - mathematical models for the design and sizing of Hybrid Rocket Engines and a preliminary design of an<br />
Hybrid Rocket Engine system for each application based on two different technology level options (med/advanced propulsion<br />
assumptions); - analysis of a vehicle mission and and performance for the above two options and comparison to baseline<br />
data; - summary of the performance budget and identification of any technological critical item.<br />
Deliverables:<br />
Technical datapackage + matematical models.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: future launchers Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: -<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T413-01MP<br />
Experimental demonstration of opto-pyro systems for launcher applications<br />
Opto-pyro designates a technique whereby laser pulses distributed via optical fibres are used for initiation of explosives. This<br />
technique offers several advantages compared to the classical pyro system, which is based on electrical initiators and<br />
explosive cords. Previous preliminary studies of the intro<strong>du</strong>ction of this technology for the separation systems of Ariane 5<br />
have been carried out. In the present activity, the definition and investigation of other possible applications of the opto-pyro<br />
technology will be performed. In particular, such applications as stage separation for Ariane 5 and future RLVs, SRM ignition,<br />
ignition of RCS in RLVs, as well as possible use in satellite platforms, will be considered. In addition, investigations of an<br />
opto-pyrotechnic chain addressing key technologies and issues (optical source and fibres, signal distribution, sequencing and<br />
delays...) will be con<strong>du</strong>cted. An optimisation of the optical architecture will be performed. An experimental demonstration of<br />
the concept will be carried out through the testing of an opto-pyro platform, to verify the general design concept of the<br />
opto-pyrotechnic sub-system.<br />
Deliverables:<br />
Technical note. Experimental demonstration.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: future launchers Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-8140<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.7.1 - Propulsion Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MMM-956<br />
Journal bearings for turbopumps<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.8 - Aerothermodynamics (ATD)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T406-04MP<br />
CFD validation in CO2 environment<br />
The proposed study is related to the ground-to-flight methodology for planetary entry missions in atmosphere mainly<br />
composed of carbon dioxide and some other minor components. In frame of the CNES PREMIER program, related to Mars<br />
exploration facilities have been used to generate cold and hot CO2 flows. The Long shot facility (at VKI) features cold CO2<br />
and rather high Reynolds flows while the F4 facility (at ONERA) features high enthalpy and moderate Reynolds flows. Both<br />
facilities should be more carefully characterised in terms of actual flow conditions ahead of the models (as required when<br />
using advanced measurement techniques). This characterisation should be made in a close loop manner with numerical<br />
simulation of nozzle flow and the thermo-chemical models should rely on validation carried within other <strong>TRP</strong> work on "high<br />
speed kinetics". The extrapolation methodology will be first based on simplified approaches to compare the ground<br />
condition(s) to the real flight conditions. Codes based on computing the flow on the stagnation line will be used to investigate<br />
the main non-dimensional relevant parameters. Then the extrapolation methodology will rely on the 3D solvers using the same<br />
models.<br />
Deliverables:<br />
Experimental campaign reports. Mid-term report. Final report proposing the ground-to-flight proposed methodology.<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: TRL5-6 (facility validated) by<br />
TRL1<br />
TRL2-3<br />
2007-2008<br />
Application/Mission: Exomars Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-8094<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference: T406-09MP<br />
Development and qualification of in Flight Test Measurement (FTM) techniques:<br />
Title:<br />
Electron Beam Fluorescence fo Aerothermodynamic Applications<br />
Development and improvement of techniques for in-flight measurement of critical aerothermal properties and specific flow<br />
variables, both on-board and off-board hypersonic vehicles are key elements required for the future demonstrator vehicles.<br />
Smaller and more accurate sensors, as well as advanced non intrusive measurement techniques are to be developed. The<br />
development concerns detailed numerical sensitivity analysis as well as demonstration models assembly activities leading to<br />
integrated subsystem testing in relevant plasma facilities. The objective of this activity is to improve intrusive and develop the<br />
concept non intrusive diagnostic techniques for in flight ATD research. New developments promise an extension of these<br />
techniques to higher densities, better spectral resolution and higher sampling rates (to be, in the future, qualified in<br />
combination with well established temperature and pressure measurements techniques). The activity includes: 1. Emission<br />
spectroscopic improvements for ground based facility and flight testing - Emission spectroscopic data for CFD verification. 2.<br />
Improvements of pyrometry and infrared thermography methods for ground based facility and flight testing. 3. Improved and<br />
extending pressure range for EBF (Electron Beam Fluorescence). 4. Flow visualisation on N2 and/or NO(gamma) (CCD<br />
Camera) using EBF. 5. N2 density via visible light or X ray (photomultiplier /Xray scintillator). 6. N2 vibrational and rotational<br />
temperatures using EBF (spectrometer). 7. EBF for NO density (spectrometer/photomultiplier). 8. Prospective IR integration<br />
experiments in plasma conditions. 9. Comparison of the measured data with CFD calculation of the flow field.<br />
Deliverables:<br />
Technical note (incl. Test/Measurements results). Breadboarding.<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: TRL8 (in-flight<br />
TRL2<br />
TRL4-5<br />
demonstration) by 2008<br />
EXPERT (2008), Exploration, Future<br />
Application/Mission: Contract Duration: 17 months<br />
Launchers<br />
SW Clause : - Dossier0 Ref.: T-8100<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Development and qualification of in Flight Test Measurement (FTM) techniques: Nose &<br />
Title:<br />
Payloads<br />
Development and improvement of techniques for in-flight measurement of critical aerothermal properties and specific flow<br />
variables, both on-board and off-board hypersonic vehicles are key elements required for the future demonstrator vehicles.<br />
Smaller and more accurate sensors, as well as advanced non intrusive measurement techniques are to be developed. The<br />
development concerns detailed numerical sensitivity analysis as well as demonstration models assembly activities leading to<br />
integrated subsystem testing in relevant plasma facilities. The objective of this activity is to improve intrusive and develop the<br />
concept non intrusive diagnostic techniques for in flight ATD research. New developments promise an extension of these<br />
techniques to higher densities, better spectral resolution and higher sampling rates (to be, in the future, qualified in<br />
combination with well established temperature and pressure measurements techniques). The activity includes: 1. Emission<br />
spectroscopic improvements for ground based facility and flight testing - Emission spectroscopic data for CFD verification. 2.<br />
Improvements of pyrometry and infrared thermography methods for ground based facility and flight testing. 3. Improved and<br />
extending pressure range for EBF (Electron Beam Fluorescence). 4. Flow visualisation on N2 and/or NO(gamma) (CCD<br />
Camera) using EBF. 5. N2 density via visible light or X ray (photomultiplier /Xray scintillator). 6. N2 vibrational and rotational<br />
temperatures using EBF (spectrometer). 7. EBF for NO density (spectrometer/photomultiplier). 8. Prospective IR integration<br />
experiments in plasma conditions. 9. Comparison of the measured data with CFD calculation of the flow field.<br />
Deliverables:<br />
Technical note (incl. Test/Measurements results). Breadboarding.<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: TRL8 (in-flight<br />
TRL2<br />
TRL4-5<br />
demonstration) by 2008<br />
EXPERT (2008), Exploration, Future<br />
Application/Mission: Contract Duration: 17 months<br />
Launchers<br />
SW Clause : - Dossier0 Ref.: T-8100<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T406-12MP<br />
Preparation of an electrodynamic-heatshield flight experiment<br />
It is the objective of the present work to prepare a flight demonstration experiment by looking into the available magnet<br />
technology with regard to technical performance and cost consideration and by performing preliminary on-ground tests. The<br />
boundary conditions imposed by a reentry capsule and its launch vehicle shall be taken into account. The focus of this work<br />
will deal with the coil section (nose of the capsule), which must contain the supercon<strong>du</strong>cting coil and its magnetic screen.<br />
Deliverables:<br />
Experimental demonstration/modeling.<br />
Current TRL: - Target TRL: TRL1-2 Application Need/Date: TRL5 by 2015<br />
Application/Mission: re-entry vehicles Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7715<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T406-13MP<br />
Title:<br />
Advanced Methods for Hypersonic plasma - flow control<br />
The objective of the present proposal is to advance new techniques to control the flow within the hypersonic shock layer of<br />
space transportation systems entering planets or re-entering earth at hypersonic speeds. A promising very innovative concept<br />
is the one of controlling the flow pattern through electro-magnetic forces acting on the ionized component of the flow impacting<br />
the vehicle.<br />
This electro – magnetic interaction of the flow could potentially:<br />
• Re<strong>du</strong>ce locally the heat flux via shock standoff increase.<br />
• Increase wave drag thereby also re<strong>du</strong>ce heat load <strong>du</strong>e to re<strong>du</strong>ction of ballistic coefficient.<br />
• Be used to control the flow for stability and trimming resulting in simplification or elimination of RCS.<br />
• Manipulate black out periods and therefore optimize communication links.<br />
The purpose is to build up further on recent advances made in the HEAT and L2K facilities and to take advantage of the<br />
ongoing associated activities within the CIRA CAST and DLR programmes.<br />
The following activities are proposed :<br />
• Small scale experiments in HEAT and L2K thereby augmenting their expertise in this field including numerical rebuilding.<br />
• Developments of associated intrusive and non intrusive diagnostic measurement for later use in SCIROCCO.<br />
• Preparatory activities for SCIROCCO testing compatible with CAST.<br />
• Study on potential system impact for possible future application and in flight demonstration.<br />
Deliverables:<br />
Technical note<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2011<br />
Exploration and Science Planetary Entry<br />
Application/Mission: Contract Duration: 24 months<br />
and Earth Reentry missions<br />
SW Clause : - Dossier0 Ref.: T-7715<br />
Consistency with Harmonisation<br />
Roadmap: “Aerothermodynamics Tools”, 2007; Conclusions: 1st semester 2007<br />
Roadmap and Conclusions:<br />
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4.8.1 - Aerothermodynamics (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/MPA-001<br />
In-Flight Aerothermodynamic Measurements<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: 94/8.2.1.4, 03/MPA-002<br />
Title:<br />
Plasma Radiation Database<br />
Radiative heat fluxes represent a significant contribution to wall heat flux and are not sufficiently precisely evaluated with tools<br />
and databases presently available in Europe. The prediction of plasma emission and absorption is important for Earth<br />
atmospheric entries at high velocities (typical of Sample Return missions), for high velocity entries into Mars and Venus<br />
atmospheres (typically above 9km/s) and for entries in atmospheres where dissociation pro<strong>du</strong>ces strong radiators (e.g. Titan).<br />
Radiation plays also a major role in the thermal environment of solid rocket engines. A good knowledge of the radiative<br />
contribution to heat flux is already necessary in phase A and assessment studies, because of its large influence on the mass<br />
budget of the vehicle. <strong>ESA</strong> has initiated, under the Technology Research Programme (<strong>TRP</strong>) an initial development of a code<br />
and an experimental database for the determination of radiative heat flux: PARADE. This code is limited so far to some atoms<br />
and diatomic molecules, but should be extended to triatomic molecules such as CO2, major component of Mars atmosphere.<br />
PARADE new additions should be validated in order to become fully useful for the design of thermal protection systems. The<br />
objective of the study is to further develop and validate (by appropriate validation test when applicable) a code and to create<br />
an experimental database for thermal radiation of plasma (emission and absorption). Such a code should extend the present<br />
PARADE possibilities to include triatomic molecular species.<br />
Deliverables:<br />
Database model / notes.<br />
Current TRL: Algorith Target TRL:<br />
m<br />
Prototype<br />
Application Need/Date: TRL5 by 2009-2010<br />
ExoMars, Mars Sample return, or for<br />
Application/Mission: missions to Venus (EVE), NEO missions Contract Duration: 12 months<br />
(Marco Polo)<br />
SW Clause : - Dossier0 Ref.: T-7902<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.9 - Avionics and GNC<br />
<strong>TRP</strong> Reference:<br />
T408-01MX<br />
Modern Guidance Schemes for the Terminal Area Energy Management (TAEM) Flight<br />
Title:<br />
Phase of Reusable Space Transportation Systems<br />
To develop and validate novel guidance approaches and algorithms for the TAEM flight regime, which is critical for the<br />
development of future European reusable space transportation systems, and which will be needed for preceding experimental<br />
vehicles. During the TAEM phase, the guidance system aligns the vehicle with the runway, while controlling altitude and<br />
velocity. The proposed activity shall improve the knowledge of the TAEM phase by analysing typical spacecraft configurations<br />
and requirements for this phase, shall research novel guidance approaches for TAEM, which would enhance the degree of<br />
autonomy and reusability, and which would re<strong>du</strong>ce the operations costs, and shall include the testing and verification of<br />
algorithms on a validated software platform.<br />
Deliverables:<br />
GNC algorithms for the Terminal Area flight phase, verified on a validated software platform; Technical Report and Technical<br />
Notes, summarizing the analytical trades and <strong>document</strong>ing the key features and advantages of the selected guidance<br />
approach.<br />
Current TRL:<br />
Target TRL: Beta Application Need/Date:<br />
TRL1<br />
version<br />
FLPP demonstrators, Exploration<br />
Application/Mission: Contract Duration: 12 months<br />
missions<br />
SW Clause : Open Source Code Dossier0 Ref.: T-8077<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T408-06ES<br />
Title:<br />
Robust Multi-mission Navigator<br />
Hybridized navigation concept, using GPS-like signals to complement IMU information as well as air data sensor, laser<br />
altimeter/ranger and optical sensor data, is a promising solution for compensating drift errors and uncertainties of the<br />
gravitational field. A hybridized navigation solution is being studied in the frame of the on-going <strong>TRP</strong> study on "Aeroassist<br />
Technology for Planetary Exploration", nevertheless, some specific problems need to be investigated in details. In the light of<br />
the above considerations, the aim of the proposed activity is to develop a European multi-mission hybrid navigator breadboard<br />
that will be tailored for upcoming Earth entry vehicle demonstrator(s). The expected benefit is a highly integrated robust hybrid<br />
navigator breadboard with multi-mission capabilities ready for use in future space transportation and re-entry programmes.<br />
The hybrid navigator will exclusively be based on European technologies <strong>du</strong>e to strict export control licenses on US<br />
components. The study shall include the functional performance evaluation of three cases: launcher, aeroentry/reusable<br />
space transportation, multi-mission hybrid navigator.<br />
Deliverables:<br />
Nav. Breadboard. Hybridised nav. flight SW demo. Data package / summary report / abstract, incl. nav. sensor spec,<br />
hybridised nav. sys. prel. design, functional perform. evaluation (mentioned 3 cases); spec/baseline architecture; design; test<br />
results.<br />
Current TRL: Target TRL: Application Need/Date:<br />
FLPP demonstrators, Launchers,<br />
Application/Mission: Contract Duration: 18 months<br />
Exploration missions<br />
SW Clause : Open Source Code Dossier0 Ref.: T-8076<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.10 - Health Management System (HMS)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T410-01MC<br />
Health Monitoring system for TPS and Hot Structures<br />
Monitoring and evaluation of structural performance will play a key role in re<strong>du</strong>cing the overall operational cost associated with<br />
maintenance and refurbishment of reusable space transportation systems. Future launch vehicles will have to increase<br />
operational efficiency whilst maintaining or improving reliability. The objective of the proposed activity includes:- analyse and<br />
define system requirements in the TPS and Hot Structures Health Monitoring field (resulting in preliminary specifications of a<br />
Health Monitoring System suited to TPS and Hot Structures requirements).- Starting from the requirements on TPS and Hot<br />
Structures components a technological study on the HM techniques for both in-flight and on-ground inspection will be<br />
performed. Particularly the technology should include investigation of the loosening of joints connecting the panels with the<br />
structure and impact damages on the panels as well as temperature and strain monitoring and leak detection.<br />
Deliverables:<br />
System Requirements Document for TPS and Hot Structures Health Monitoring; Identification of associated system and<br />
components Specifications. Technology development plan.<br />
Current TRL: TRL0-1 Target TRL: TRL1 Application Need/Date: TRL5 by 2010-2012<br />
re-entry vehicle, RLV's, FLPP<br />
Application/Mission: Contract Duration: 12 months<br />
demonstrator<br />
SW Clause : - Dossier0 Ref.: T-8134<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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4.11 - Intelligent Space Systems Operation (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MXO-001<br />
Health Management System for Re-usable Space Transportation<br />
Health monitoring is a critical technology for the feasibility and cost effectiveness of future reusable or semi-reusable space<br />
transportation means (re-entry vehicles, re-usable launchers).<br />
However, nowadays health monitoring is limited to the design of sensors and detection methods that can be implemented on<br />
test items.<br />
A more systematic definition of health monitoring requirements is needed, which considers the maintenance strategy and a<br />
the trade-off between turnaround time and RAMS objectives.<br />
The goal of the activity is to determine the correct health monitoring requirements and the logic of implementation of a Health<br />
Monitoring System (HMS) studying its impact on the vehicle turnaround operations and costs. The activity shall develop and<br />
demonstrate processes for HMS design and optimisation, develop models and analysis means for a generic HMS<br />
architecture, demonstrate a HMS model against nominal and fault injection mission simulations.<br />
Deliverables:<br />
Notes. Models/analyses for a generic HMS architecture. HMS demonstration model.<br />
Current TRL: TRL1 Target TRL: Prototype Application Need/Date:<br />
Application/Mission: FLPP, Exploration missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-8075<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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5.- Telecommunication / Navigation<br />
5.1 - Conventional Fixed Telecommunication Service<br />
<strong>TRP</strong> Reference:<br />
ETM-101<br />
Surface Treatment and Coatings for the Re<strong>du</strong>ction of Multipactor and Passive<br />
Title:<br />
Intermo<strong>du</strong>lation Phase 2<br />
Objective of this activity is the evaluation of practical and stable coatings with extremely low secondary electron emission for<br />
re<strong>du</strong>ction of multipactor effect in RF components in space. The concept is based on the secondary emission suppression of<br />
rough surfaces or special morphologies. Inert or noble metal porous coatings will be used to achieve: optimum values, control,<br />
repro<strong>du</strong>cibility, homogeneity, and stability in air for the secondary emission and electrical con<strong>du</strong>ctivity. The activity will verify<br />
the good results achieved in the previous <strong>TRP</strong> activity on Surface Treatment and Coating for the Re<strong>du</strong>ction Multipactor<br />
Degradation in RF components (Ref: ETM-101 in 2000-2003 Plan), which has yielded several patents and 9 publications.<br />
Deliverables:<br />
Test Report on 10 further samples<br />
Current TRL: TRL2-3 Target TRL: TRL3 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Telecom, Navigation Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7829<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T503-03ET<br />
Title:<br />
RF breakdown in Multicarrier systems<br />
Multipactor is a RF breakdown phenomena occurring in space RF components. The consequences of this breakdown can be<br />
catastrophic for the mission of the satellite. In those payloads using multicarrier operation, the levels of risk of RF breakdown<br />
increases exponentially. The aim of this activity is to asses these rules and ensure that any theoretical analysis based on<br />
these rules can be considered valid, thus avoiding expensive test campaigns. A mo<strong>du</strong>lar software tool compatible with existing<br />
electromagnetic softwrae shall be pro<strong>du</strong>ced to evaluate and predict RF breakdown in multicarrier operation taking these<br />
theories into consideration. These two "rules" are described bellow: The "fringed effect" is related to the geometrical shape of<br />
the internal edges in the RF device. It is believed that this shape (sharp or smoothly curved) has a significant influence in the<br />
Multipactor behaviour of the component. However no investigations in this area have ever been completed. In multicarrier<br />
operation testing at such high levels is not always possible. Previous works indicated that, as long as the <strong>du</strong>ration of the<br />
multicarrier peak and the mode order of the gap are such that no more than twenty gap-crossing can occur <strong>du</strong>ring the<br />
multicarrier peak, then multipactor-generated noise should remain well below thermal noise. This rule is know as the "Twenty<br />
Gap-Crossing" rule and its theoretical confirmation plus test verification would imply a significant step in the understanding<br />
and mitigation of this destructive phenomena. It would also re<strong>du</strong>ce the amount of components needed for testing.<br />
Deliverables:<br />
Final report + detailed theoretical doc. Samples (possibly waveguide filters; design to reflect the theories investigated and<br />
tested). Test reports. Mo<strong>du</strong>lar SW tool.<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Telecom, Navigation Contract Duration: 18 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7829<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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5.2 - Engineering and Verification Tools & Techniques<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T506-01EE<br />
European Antenna Modelling Component Library - Telecommunications<br />
The library shall be based on existing tools, while being able to easily incorporate the implementation of any new algorithms<br />
developed to satisfy emerging antenna engineering needs. The present activity will focus on the development of components<br />
specific to Telecommunication missions. In particular it will be articulated in two components: a structural component to<br />
ensure the background activity to pursuit the common objective of bringing forward antenna modelling technology and tools<br />
and a thematic component, dedicated to specific needs.-The structural component will focus on: the Earth<br />
Observation-specific aspects,electromagnetic modelling data domain standardisation, geometrical CAD tuned to<br />
electromagnetic modelling needs for telecommunication specific antenna configurations.-The thematic components will focus<br />
on: refinement of reflector antenna analysis tools , multi-frequency multi-coverage synthesis, improvement of antenna<br />
interaction models.The present activity will be carried out as part of the global development of the "European Antenna<br />
Modelling Component Library" foreseen by the above Dossier.<br />
Deliverables:<br />
Software component library with relevant <strong>document</strong>ation. Validation hardware (satellite and antenna mock-ups)<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T506-02MC<br />
Title:<br />
Modelling of Porous Shells<br />
Porous materials, such as triaxial woven fabrics, are being employed in antenna technology <strong>du</strong>e to the significant mass<br />
re<strong>du</strong>ction and acoustic load relaxation. The drawback being the RF transparency, limiting the application of current ultralight<br />
technologies to the Ku frequency band. Therefore, a re<strong>du</strong>ction of hole size is needed and consequently the acoustic load case<br />
comes back to the scene. The objectives of this activity are:1.Vibroacoustic modelling of porous materials and triaxial fabrics,<br />
comprising material characterisation and a proce<strong>du</strong>re for implementation into Finite/Boundary-Element vibroacoustic<br />
simulation.2.Thermo-elastic modelling of porous/triaxial shell. Material characterisation and implementation into Finite Element<br />
simulation.<br />
Deliverables:<br />
Identification of relevant parameters (analysis + existing data). Thermo-elastic/acoustic/RF characterisation (coupons +<br />
samples). Finite Element and Boundary Element modelling proce<strong>du</strong>re. Correlation with sample tests.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 >=2009-2010<br />
Application/Mission: all spacecraft with reflectors) Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7750<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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5.3 - High capacity multi-beam systems<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T501-02EE<br />
Active multi-beam antenna concept using advanced very high order multilayer BFN<br />
The objective of this activity is the design, manufacturing and test of critical components for a very high order Analog Beam<br />
Forming Network (BFN) for future Ka band broadband multimedia telecommunication missions. A promising approach may<br />
consist in implementing an active lens able to generate a very high number of adjacent beams (>50). This system includes a<br />
fine antenna pointing electronic correction for surface shape/deployment inaccuracy compensation. This innovative concept is<br />
foreseen to provide improvement toward in-orbit performance tuning, implementation feasibility, manufacturing accuracy<br />
relaxation, high reliability <strong>du</strong>e to graceful degradation performance, low sensitivity to multipaction and PIM, and excellent<br />
power to beam flexibility. Such antenna architecture with high order BFNs represent a challenge and this activity will prove the<br />
capabilities of technology for their implementation. Advanced multilayer technologies and advanced design concepts and<br />
technologies are expected to be used leading to a compact and cost effective solution.<br />
Deliverables:<br />
Detailed design and critical breadboard.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Multibeam Telecom Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7746<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T501-04EE<br />
Development of high order propagation models for multimedia Satellite Communication<br />
Title:<br />
Systems<br />
The proposed activity is aimed to the development of models of high order statistics of radiowave propagation parameters<br />
relevant for Satellite Communication Systems operating at frequencies from 20 to 50 GHz. Existing models are mainly<br />
focused on the description of first order statistics of propagation parameters (like the atmospheric attenuation cumulative<br />
distribution function), but, because the design of advanced SatCom systems relies on Propagation Impairment Mitigation<br />
Techniques (PIMT) and on its integration with network control, additional information on higher order or conditioned statistics<br />
(e.g. fade <strong>du</strong>ration, fade slope, seasonal and diurnal effects, instantaneous and long-term frequency scaling, spectral<br />
propertied and spatial and time correlation, etc. ) are needed. As well issues related to exploitation of Ka Band for EO and<br />
Science missions data downlink require new models.<br />
This new activity shall start by a critical review of existing models based on current and expected system requirements (like<br />
the QoS - Quality of Service - issues or PIMT design) along with the existing dataset collected <strong>du</strong>ring propagation<br />
experiments. The main core of the activity shall be constituted by:<br />
• Collection of data from past propagation measurements.<br />
• A new experimental propagation campaign, based on existing satellite beacons.<br />
• A data analysis and model development activity.<br />
• A validation and testing activity for the assessment of the accuracy of new models.<br />
Deliverables:<br />
Propagation models / SW<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: SW operational by 2009<br />
Application/Mission: Satellite Telecommunication systems Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7916<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T501-06ET<br />
High Frequency SIGE MMICS for Converter<br />
The objective of the activity is the design, manufacturing and test of high frequency SiGe MMICs to be used in the next LO<br />
generation and up and downconverter units both for on board and user terminal applications. SiGe permits the implementation<br />
of very low cost mixed analogue/digital circuits that can significantly re<strong>du</strong>ce manufacturing costs of LO generation mo<strong>du</strong>les,<br />
frequency synthesizers and up and downconverter units. Low phase noise is another characteristics of SiGe HBT technology.<br />
On the user terminal area, there is a strong push towards extremely low recurrent costs. Frequency synthesizer has been<br />
identified as one of the cost drivers and SiGe technology has potential for significant cost re<strong>du</strong>ction<br />
Deliverables:<br />
High Frequency SiGe HBT MMICs to be used as building blocks on future LO generation and frequency converter units both<br />
for on board and user terminal applications.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Telecom Contract Duration: 22 months<br />
SW Clause : - Dossier0 Ref.: T-7830<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T501-07ET<br />
Title:<br />
High Reliability MEMS Re<strong>du</strong>ndancy Switch<br />
Micro Electro-Mechanical Systems (MEMS) technology has been quite successful in the demonstration of low loss, high<br />
frequency switches with the emphasis on a high number of ON/OFF cycles. However, very little is know about the reliability<br />
(failure and degradation mechanisms, ..) of such switches, specially when it comes to few cycles with may years between ON<br />
and OFF actuations, as for re<strong>du</strong>ndancy switches on board satellites. The aim of this activity is to design and realise a high<br />
frequency (up to a least Ka-band) low power re<strong>du</strong>ndancy switch, based on MEMS technology, with proven reliability i.e.<br />
including investigation and analysis of failure/degradation mechanisms.<br />
Deliverables:<br />
Demonstrator of MEMS re<strong>du</strong>ndancy switch. Identification and analysis of failure/degradation mechanisms.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Telecom, EO, Science, Navigation Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7832<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T501-08EE<br />
Innovative architectures for re<strong>du</strong>cing the number of controls of multiple beam<br />
Title:<br />
telecommunication antennas<br />
This study shall perform innovative design and radiation performances analysis (mainly Gain and maximum sidelobes/grating<br />
lobes levels) of different Array configurations including uniform and non-uniform elements spacing, overlapped subarrays and<br />
other techniques to identify achievable performances toward number of active controls. Based on these analyses, detailed<br />
design and definition shall be performed leading to BFN (Beam Forming<br />
Network) architecture, mass and technological constraints identification as well as performance achievable for the selected<br />
implementation.This study will cover all architectural trade-offs, the concept selection and a detailed design. Breadboarding<br />
activities will allow demonstrating the feasibility and performances of this innovative concept.<br />
Deliverables:<br />
Performances analysis of different arrays configurations.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL4 by 2009<br />
Application/Mission: Satellite Telecommunication systems Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7832<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Array Antennas<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T501-10ET<br />
High throughput highly re-configurable bent-pipe processor for access networks<br />
The proposed activity aims at the design, implementation and validation of the Proof of Concept (PoC) of a high throughput<br />
highly re-configurable and scalable digital processor for future bent-pipe satellite broadband access networks that meets these<br />
new challenging requirements in terms of flexibility and processed bandwidth (expected to be up to 50 GHz). The prototype<br />
shall demonstrate all the key functionalities of the processor (e.g. high bandwidth signal processing algorithms, channel to<br />
beam allocation flexibility, wideband digital beam forming, etc.) and assess in detail the use of cutting-edge digital<br />
technologies (e.g. 0.13 micro-m, new low power consumption ADC/DAC) needed for achieving efficient processing of the<br />
large bandwidths involved within the next generation of communication systems. For budgetary reasons the PoC will make<br />
extensive use of FPGA technology. The prototype shall be implemented at a laboratory breadboard level and is expected to<br />
work at re<strong>du</strong>ced scale in terms of processed bandwidth per beam and be scaled-down in terms implemented links. The PoC<br />
shall allow a thoroughly validation of the proposed architecture, signal processing algorithms and achievement of the<br />
performance requirements. Power and mass estimate for the final target technology shall be however performed. A real-time<br />
air interface simulator shall be developed for both up and downlink in order to provide the processor with the required IF and<br />
control signals. The simulator shall cover functions such as interference and propagation effects, satellite delays, network<br />
synchronization mechanisms, payload impairments, packet demo<strong>du</strong>lation, background signalling loading of the switch<br />
controller, etc.<br />
Deliverables:<br />
Processor Detailed Design Report PoC of a scaled-down version of the High Throughput Transparent Processor.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2009<br />
Application/Mission: Telecom Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7931<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T501-11EE<br />
Title:<br />
New concepts for <strong>du</strong>al-gridded reflectors (study)<br />
Dual-gridded reflector antennas allow the combination of two apertures in almost the same room that would be occupied by<br />
only one normal reflector. This is achieved by using polarisation sensitive grids printed on the reflector surfaces. This concept<br />
is extremely important <strong>du</strong>e to the accommodation constraints of the platforms and lead to very high polarisation purity.<br />
Ku-band <strong>du</strong>al-gridded reflectors are widely used today on commercial satellites. This activity deals with the study of possible<br />
technological implementations of <strong>du</strong>al-gridded reflectors for telecommunications applications in Ka-band. New concept and<br />
materials are mandatory <strong>du</strong>e to high transmission losses of the front shell (approximately 0.8 dB) when Ku-band technology is<br />
considered for Ka-band. It is proposed to follow this preliminary design activity by an ARTES-funded demonstration phase.<br />
Deliverables:<br />
Design of <strong>du</strong>al-gridded reflector antenna at Ka-band. RF and mechanical samples to be used as proof of concept.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2009<br />
Application/Mission: Satellite Telecommunication systems Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7832<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
T501-12ET<br />
Study of Enhanced digital transmission techniques for Broadband Satellite Digital<br />
Title:<br />
Transmissions<br />
Advanced digital techniques can be envisaged making use of dynamic signal pre-distortion at the mo<strong>du</strong>lator side combined<br />
with adaptive non-linear equalizer at the receiver in order to compensate both the amplitude and the ISI (Inter-Symbol<br />
Interference) distortions caused by the channel non-linearity. If digital pre-compensation and equalization techniques are<br />
used, the optimum operating point in terms of Baud rate may be shifted towards greater value of Bs/Bf while output back-off<br />
re<strong>du</strong>ced. This is particularly true if higher order mo<strong>du</strong>lations (such as 8PSK, 16/32-APSK) currently proposed by DVB-S2 are<br />
adopted. Efficiency gains in the order of 2 dB in terms of power efficiency and 20-30% in spectral efficiency are expected with<br />
affordable implementation complexity. A further step is represented mo<strong>du</strong>lation schemes with constant envelope like M-ary<br />
CPM (Continuous Phase Mo<strong>du</strong>lation) signals and re-assessment of their suitability to broadband satellite communications. In<br />
particular, their energy and spectral efficiency on linear channel shall be investigated and compared to more classical linear<br />
band-limited M-QAM mo<strong>du</strong>lations. Performance shall also be investigated for typical non-linear satellite channels to show the<br />
performance gain of these signals. New coding schemes employing CPM signals shall also be studied. Carrier and timing<br />
synchronization techniques that are able to work at the very low operative SNR of typical satellite transmissions in presence of<br />
powerful coding schemes, shall be studied and optimised. Overall coded mo<strong>du</strong>lation performance over typical satellite<br />
nonlinear channels shall be finally estimated through an accurate end-to-end simulator. Finally implementation complexity<br />
issues for the demo<strong>du</strong>lator and decoder shall be analysed and CPM complexity shall be compared with current state-of the art<br />
M-QAM demo<strong>du</strong>lator/decoders. This is a key issue as in the past adoption of CPM schemes was often discarded for<br />
high-speed applications because of the lack of maturity of digital signal processing technologies. The activity shall include: 1.<br />
technical report trading off different equalization techniques for the specific application showing the proposed innovative<br />
techniques as well as their performance results assessed through analysis and computer simulations; 2. the description and<br />
the performance of the selected coded mo<strong>du</strong>lation scheme over the linear and non-linear channel; 3. the gain w.r.t the more<br />
classical mo<strong>du</strong>lations shall also be assessed; 4. the description and the performance of the carrier and symbol timing<br />
synchronizers suitable for the selected mo<strong>du</strong>lation scheme for both the forward and the return channel; 4. an in-depth<br />
assessment of the equalizer complexity and feasibility study for the selected application scenarios; 5. a software package in<br />
MATLAB or C/C++ implementing the overall system simulation including the channel distortion elements (IMUX/OMUX and<br />
power amplifiers) and mo<strong>du</strong>lators and demo<strong>du</strong>lators with the proposed innovative techniques.<br />
Deliverables:<br />
Technical report. Selected mo<strong>du</strong>lation scheme description/performance/feasibility study; SW (MATLAB or C/C++).<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2008-2009<br />
Application/Mission: Telecom Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7923<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T501-14ET<br />
Broadband low-power ADC design & prototyping<br />
The present activty is in line with the DSM (Deep Submicron Microelectronics) initiative strategy paper (<strong>ESA</strong>/IPC(2006)88).<br />
The main object of this study is the development of a 10 bits broadband (500 MHz / ~1.500 Msps) Analog-to-Digital Converter<br />
(ADC) with low power consumption (~1W) for on-board digital processing applications.<br />
This activity shall encompass the following tasks:<br />
- Process selection: 1. Radiation effects and mitigation techniques, 2. Reliability, 3. Lifetime.<br />
- Architecture trade offs.<br />
- Design.<br />
- Layout.<br />
- Simulations post layout.<br />
- Prototype/s manufacturing.<br />
- Electrical testing and performances measurement.<br />
- Limited environmental tests (temperature / radiations).<br />
This activity will be continued in the NewPro program (doc. ref. <strong>ESA</strong>/IPC(2006)75, activity ref. NP10-01ED).<br />
Deliverables:<br />
Electrically characterised prototypes and preliminary environmental tests results. The prototype shall be as representative as<br />
possible of a flight model, including the manufacturing of the die but also the package (ceramic hermetic package).<br />
Furthermore, the manufacturer shall propose a business model definition for the qualified pro<strong>du</strong>ct.<br />
Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5/6 >2011<br />
TLC: on-board processing, SCI: science<br />
& remote sensing instruments, EO:<br />
Application/Mission:<br />
instruments, TLM&control, high-speed<br />
Contract Duration: 15 months<br />
rate data downlink.<br />
SW Clause : - Dossier0 Ref.: T-7891, T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>ESA</strong>/IPC(2006)88<br />
<strong>TRP</strong> Reference: T501-15ET<br />
Title:<br />
Broadband low-power DAC design & prototyping<br />
The present activty is in line with the DSM (Deep Submicron Microelectronics) initiative strategy paper (<strong>ESA</strong>/IPC(2006)88).<br />
The main object of this study is the development of a 12 bits broadband (500 MHz / ~1.500 Msps) Digital-to-Analog Converter<br />
(DAC) with low power consumption (~.6W) for on-board digital processing applications.<br />
This activity shall encompass the following tasks:<br />
- Process selection: 1. Radiation effects and mitigation techniques, 2. Reliability, 3. Lifetime.<br />
- Architecture trade offs.<br />
- Design.<br />
- Layout.<br />
- Simulations post layout.<br />
- Prototype/s manufacturing.<br />
- Electrical testing and performances measurement.<br />
- Limited environmental tests (temperature / radiations)..<br />
This activity will be continued in the NewPro program (doc. ref. <strong>ESA</strong>/IPC(2006)75, activity ref. NP10-02ED).<br />
Deliverables:<br />
Electrically characterised prototypes and preliminary environmental tests results. The prototype shall be as representative as<br />
possible of a flight model, including the manufacturing of the die but also the package (ceramic hermetic package).<br />
Furthermore, the manufacturer shall propose a business model definition for the qualified pro<strong>du</strong>ct.<br />
Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5/6 after2011<br />
TLC: on-board processing, SCI: science<br />
& remote sensing instruments, EO:<br />
Application/Mission:<br />
instruments, TLM&control, high-speed<br />
Contract Duration: 15 months<br />
rate data downlink.<br />
SW Clause : - Dossier0 Ref.: T-7891, T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>ESA</strong>/IPC(2006)88<br />
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5.4 - Mobile Communications<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T502-06EE<br />
Simulation of the satellite to indoor propagation channel at L and S bands<br />
The main objective of this activity is the characterisation through simulation of the propagation effects in the satellite to indoor<br />
channel at L and S frequency bands. This activity involves several tasks: Task 1: develop a precise 3-D characterisation of<br />
different types of buildings such as warehouses, office buildings, shops and shopping malls, factories, apartment blocks and<br />
single family dwellings taking into account the electrical properties of the different construction materials and elements. Task<br />
2: carry out simulations with a validated deterministic electromagnetic propagation model in all the previously generated<br />
buildings for different geometrical configurations (satellite elevation and azimuth and receiver position inside the building).<br />
Task 3: analyse the results of the simulations and develop a statistical propagation model for the satellite to indoor channel.<br />
Deliverables:<br />
The expected deliverable is a statistical propagation model for the satellite to indoor propagation channel at L and S bands.<br />
(SW IPR to <strong>ESA</strong> for operational activities (TBC))<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: SW operational by 2009<br />
Mobile Satellite Telecommunication<br />
Application/Mission: Contract Duration: 18 months<br />
systems<br />
SW Clause : - Dossier0 Ref.: T-46<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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5.5 - Navigation & Positioning<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T504-02EM<br />
Energetic Electron Environment Models for MEO<br />
New models will be constructed to take into account the temporal, spatial and spectral variations in electron fluxes at altitudes<br />
and inclinations relevant for Galileo. The NASA AE-8 model that is traditionally used for the electron flux predictions in the<br />
radiation belt environment is static, based on data collected in the 1960s and 70s, and hence badly outdated. New models<br />
taking into account the dynamic nature of the outer electron belt are therefore needed. The aim of this activity is to pro<strong>du</strong>ce<br />
such models utilising data from the <strong>ESA</strong> Standard Radiation Environment Monitor (SREM) instruments flying on Integral,<br />
PROBA-1 and the GSTB-V2. Electron measurements from other radiation monitors, including DoubleStar shall also be<br />
included, where applicable, utilising past <strong>ESA</strong>-sponsored data base developments, together with other observations and<br />
theoretical considerations. The models shall be WWW-based, and readily available for implementation in the SPENVIS<br />
system. Interfacing to Geant4-based software for radiation and charging effects analyses shall also be considered.<br />
Deliverables:<br />
WWW-based electron environment models for MEO orbits. These shall take into account the temporal, spatial and spectral<br />
variations in electron fluxes at altitudes and inclinations relevant for Galileo.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: SW operational by 2008<br />
Application/Mission: Navigation/Telecom Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-8033<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T504-05GN<br />
Satellite and station clock modelling for GNSS, link between physical models and<br />
Title:<br />
estimation / prediction processes<br />
The data transmitted by navigation satellites (GPS, Glonass, Galileo) include so-called pseudo-range measurements, which<br />
arise from a multiplication of the signal travel time and the velocity of light. The travel time is computed as the difference<br />
between time stamps at signal transmission by the spacecraft and signal reception by the (ground or low-earth orbiting)<br />
receiver. These time stamps are generated by two independently running clocks. For all applications of the data, whether<br />
real-time navigation or post-processed geodetic use, the relative offsets between these clocks, or both offsets to a common<br />
reference time, need to be known with a high precision. The clock offset estimation process is based on an epoch-by-epoch<br />
estimation of all clock offsets, not taking into account the physical behaviour of clocks. The clear advantage of this approach is<br />
that the process is insensitive to the erratic behaviour of some clocks, and indeed this method can be used successfully in the<br />
presence of the deliberate degradation of GPS signals known as Selective Availability. The disadvantage is that some<br />
valuable information is not used in the estimation process, namely that there are some highly stable clocks in the system, with<br />
known statistical properties. The proposed study should investigate which models of clock behaviour are available and how<br />
they can be implemented in the orbit and clock estimation systems currently used and under development at TOS-GN. The<br />
algorithms to be implemented should allow the user to select clock modelling as an option, and also allow a combination of the<br />
traditional epoch-by-epoch estimation process with the use of clock models.<br />
Deliverables:<br />
Model and <strong>document</strong>ation.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2008<br />
Application/Mission: GNSS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7943<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T504-08ET<br />
Next Generation Compact Atomic Clocks<br />
The current Galileo navigation payload is based on two different clock technologies, Rubidium (RAFS) and H-maser (PHM).<br />
While the PHM provides medium to long-term fractional frequency stability at least 5 times better than the RAFS (in the 1E-14<br />
level), this is achieved at the expenses of mass and volume (factor 6 and 12 higher respectively). Atomic clocks based on<br />
vapour-cell technology (like RAFS) are intrinsically more<br />
compact and easier to realize (i.e. lower cost) than their atomic beam counterparts (like PHM). In addition, their lifetime is not<br />
primarily limited by the supply of atoms. A number of new innovative clock schemes are being proposed, showing the<br />
capabilities to improve the stability of vapour-cell based clocks to the level of the current H-maser, with relatively minor<br />
modifications of the existing unit. The objective of this activity is to<br />
define, design, validate and test a new scheme for atomic clocks based on vapour-cell technology, providing a factor of two<br />
improvement with respect to current technology, fractional frequency stability below the 1E-14 level in a mass-volume<br />
envelope comparable to present RAFS, and compatible with the Galileo space environment. In a first Phase, the various<br />
schemes shall be reviewed and analysed, leading to the selection of the most appropriate one. In a second Phase, the<br />
selected scheme shall be implemented and validated at BB level.<br />
Deliverables:<br />
1 vapour-cell atomic clock breadboard.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Telecom, Navigation Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-8043<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T504-10ET<br />
Title:<br />
Development of Innovative Atomic Clock for Satellite<br />
High performance on-board atomic clocks are the core of a satellite navigation system such as Galileo. Each Galileo satellite<br />
will embark two different type of clocks: Rubidium (RAFS) and Passive Hydrogen Maser. While the performance of those<br />
clocks are fully meeting the today system requirements, next generation Galileo satellites would benefit of the use of higher<br />
performance clocks (in terms of fractional frequency stability), still compact (low power and mass) and able to operate in the<br />
Galileo space environment. A number of T&F laboratories are currently proposing a variety of new innovative clock concepts<br />
(e.g. cold atoms, CPT-maser, CPT-dark-line,), with the potentiality of improving significantly the stability performance, still in<br />
a reasonable mass-volume-power envelope. The objective of this activity is to identify and demonstrate (at demonstrator level)<br />
an innovative clock technology achieving at least a factor 2 improvement in fractional frequency stability with respect to the<br />
today demonstrated performances, still with mass-volume-power consumption budgets compatible with the Galileo payload<br />
accommodation, and able to operate in the Galileo space environment. In a first Phase, various innovative clock concepts<br />
shall be reviewed and analysed, in order to select the most promising one. In a second Phase, a demonstration model of the<br />
selected concept shall be assembled and tested, and a development plan (including the development and qualification of<br />
critical technologies) shall be proposed.<br />
Deliverables:<br />
Clock demonstration model.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: GNSS second generation Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-8043<br />
Consistency with Harmonisation<br />
Freq. & Time Generation - Space<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T504-11ET<br />
Signal Processing Techniques and Demonstrator for Indoor GNSS Positioning<br />
GNSS-based location based services represent one of the main applications of GNSS however the users of those services<br />
are located in severely handicapped environments for the reception of the GNSS signals (outdoor urban canyons and in-door<br />
environments).<br />
The objective of this activity is to develop a number of enabling technologies suitable for operation in those environments. The<br />
techniques include:<br />
• New signal processing techniques that allow to drastically re<strong>du</strong>ce the acquisition threshold (down to 15dB-Hz – normal<br />
outdoor value is 45dB-Hz) at a feasible implementation complexity and able to cope with strong multipath<br />
• Techniques for the detection of the EGNOS message down to a value of C/No around 25dB-Hz. EGNOS corrections will<br />
definitively improve the accuracy of indoor position computation. The reception of the EGNOS signal can be improved<br />
compared to other GNSS satellites since both the transmitter (GEO satellite) and the receiver (the speed of the receiver<br />
indoors is very re<strong>du</strong>ced) are static.<br />
• Efficient ways of transmitting the assisting information to the mobile<br />
• Integration of measurement taken from GNSS and cellular systems<br />
• Techniques for the exploitation of the Galileo pilot signals with longer codes. This characteristic of the Galileo will alleviate<br />
the costly time transfer of the GNSS time from the base station to the mobile, at the same time that it can improve the<br />
accuracy by an order of magnitude<br />
The techniques shall be implemented and demonstrated in a receiver prototype based on FPGAs and DSPs on the basis of a<br />
core mo<strong>du</strong>le containing a number of GALILEO, EGNOS and GPS channels. The core mo<strong>du</strong>le channels will be designed<br />
according to the HS-GNSS principle and receive via wireless LAN the information provided by the A-GNSS server to be<br />
developed within the activity.<br />
Deliverables:<br />
New techniques for indoor positioning using GPS and Galileo, Indoor GNSS receiver demonstrator, Assisted-GNSS server.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL6 by 2009<br />
Application/Mission: Hybrid Navigation Systems Contract Duration: 20 months<br />
SW Clause : - Dossier0 Ref.: T-7748<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T504-14ET<br />
Title:<br />
Evolutionary Navigation Systems<br />
Nowadays, there are navigation applications that could not be foreseen when GPS was developed in the 70’s. The<br />
improvement of semicon<strong>du</strong>ctor technology, communication systems, positioning techniques, etc. are continuously giving rise<br />
to new areas where satellite navigation systems can be applied with new and always more stringent requirements. The<br />
objective of this activity is to study the future (beyond Galileo) needs that users will demand from navigation systems and to<br />
identify the critical technologies and techniques that have to be developed. A complete exploration of user needs and<br />
associated technologies will be done, and special attention will be devoted to:<br />
• Requirements of multi-modal applications<br />
• Integrity and certification requirements<br />
• Local augmentations<br />
• Improvement of signal reception in indoor or dense urban environments, and adaptation of the navigation message.<br />
• Resilience to multipath propagation and non-intentional interference<br />
• Ability to selectively improve the performance in “hot spots”.<br />
• Use of new signal bands (e.g. C-band)<br />
• Interoperability with satellite and terrestrial communication systems.<br />
• High-accuracy application requiring three or more frequency ambiguity resolution and carrier-phase based extended range<br />
positioning techniques.<br />
Deliverables:<br />
Analysis of user requirement for future navigation systems. Documentation containing a preliminary evaluation of<br />
architectures, technology and techniques that need to be developed in order to satisfy those needs.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Galileo evolution program Contract Duration: 15 months<br />
SW Clause : - Dossier0 Ref.: T-8047<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T504-16MM<br />
Development of key Optical Clock technologies<br />
The development of a full optical clock has important bearing on Space Science, Navigation, Earth Science, Secure<br />
Communications, etc. Optical clocks in space are considered essential tools for the exploration the limits of contemporary<br />
phyics (e.g. general relativity). They would allow, for example, the direct observation of Gravitational waves, direct<br />
measurement of fundamental physics constants, redefinition of the second, etc; or provide highly accurate long-term (days or<br />
more) time referencing as needed for precise positioning and navigation (future Galileo satellites). Despite the various<br />
world-wide effort going into optical clocks for ground applications, no yet any serious effort has been initiated into the<br />
definition and development of a space-compatible optical clock. The activity here proposed will address the critical technology<br />
of the basic components of an optical clock (clock laser, atom/ion/molecule cooling unit, laser trapping unit, detection and<br />
measurement unit) with the aim of identifying a design suitable for space. Environmental aspects, as well as critical design<br />
and qualification issues will be addressed. The output of this actvity will be a breadbord of critical parts of an optical clock<br />
capable to prove the feasibility of optical clock in space.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012<br />
Space Science, Navigation, Earth<br />
Application/Mission: Contract Duration: 18 months<br />
Science, Secure Communications, etc.<br />
SW Clause : - Dossier0 Ref.: T-8043<br />
Consistency with Harmonisation<br />
Freq. & Time Generation - Space<br />
Roadmap and Conclusions:<br />
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5.6 - Satellite / Platform Technologies<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T505-04ES<br />
Low Cost Coarse Earth Sensor Development<br />
The objective of this activity is the design of a low cost (
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
5.6.1 - Antenna Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EEA-013<br />
Q/V Band Antenna S/S<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Q/V Band Antenna S/S: additional work<br />
The aim of this activity is to develop and pre-design critical technologies for Q/V band antennas in Medium Earth Orbit (MEO)<br />
or Geostationary Earth Orbit (GEO) missions. This study will be targeted to two main areas, the study and pre-design antenna<br />
solutions, including the development of required specific modelling tools and will also address the critical areas identifying<br />
potential solutions, trade-off and breadboard them, in order to prepare the ground for further consolidation work.<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MMM-946<br />
Hybrid mechanical-electronic pointing system<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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5.6.2 - On-Board Equipment Technologies (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
03/ETM-001<br />
SAW Filter Development (original activity: SAW resonator technology for L and S-band<br />
Title:<br />
space applications)<br />
Surface Accoustic Wave (SAW) quartz resonators are often used in Voltage Controlled Oscillator (VCO) with demanding<br />
phase noise requirements. However, the use of SAW resonator based VCOs (SAWR-VCO) has so far mainly been limited to<br />
frequencies below 1 GHz for very high Q applications. The use of SAW resonators at higher frequencies and on other<br />
materials has been demonstrated in the MATOPS program for the use in low-loss impedance element filters (IEF). For both<br />
SAW-IEF and SAWR-VCO the main goal in design of the resonators is to achieve high resonator Q-values.<br />
The proposed activity aims at investigating and improving SAW resonator technology for use in VCOs in the 1-2.5 GHz range.<br />
There are several space applications of low-phase noise VCOs in navigation and communication systems operating in this<br />
frequency range. The results will also be applicable for narrowband low-loss filters and SAW notch filters.<br />
In particular, the study will focus on:<br />
• Analysis of material and design limitations of high-frequency, high-Q quartz resonators; other materials, such as Langasite<br />
(with lower intrinsic material loss), or other low-loss wave modes (STW).<br />
• Evaluation of high-Q resonators design aspects.<br />
• Breadboarding (design and development) of a SAW resonator, including manufacturing and testing of critical components<br />
and technologies; evaluation of specific manufacturing processes issues.<br />
• Evaluation of possible applications of a SAW resonator in VCO.<br />
This activity is proposed as a special measure to Norway.<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SAW Filter Development (original activity: SAW resonator technology for L and S-band<br />
space applications)<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
97/XRF02<br />
Tool for high speed end to end system simulation<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EEP-009<br />
Characterization and modeling of Propagagation effect Q/V Band<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ETM-080<br />
Title:<br />
Cold Cathode TWT<br />
The aim of this activity is to develop a Breadboard of a cold cathode Travelling Wave Tube (TWT). Previous feasibility studies<br />
performed under <strong>TRP</strong> show that significant improvements of TWTs’ performances can be can be achieved by using cold<br />
cathodes. Recent advancements in cold cathodes capabilities coming from the commercial market of flat displays, give<br />
confidence that the technology is mature enough to be employed on microwaves tubes.<br />
Deliverables:<br />
Preliminary design, breadboard of the gun assembly and the design and breadboard of a cold cathode TWT.<br />
Current TRL: TRL2 Target TRL: TRL2-3 Application Need/Date: TRL6 >=2009-2011<br />
Application/Mission: Telecom payloads Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7746<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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5.7.2 - Telecommunication P/L (Source: <strong>TRP</strong> 2000-2003)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EEO-010<br />
Technology for optical payloads<br />
The advantageous use of optical technologies offers the possibility of implementing new payload architectures operating at<br />
very high bandwidths, and a technology shift similar to the transition from microwave inter-satellite links to optical ones. The<br />
mass, volume and power requirements can significantly be re<strong>du</strong>ced by applying advanced optical techniques and devices,<br />
including fiber, integrated and bulk optics. Breadboarding of selected technologies shall be performed. The study is<br />
complementary to <strong>TRP</strong> activity 94/2.1.6.5.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: Target TRL: TRL2 Application Need/Date: TRL5 >2008<br />
Application/Mission: Optical Beam Forming Networks Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7746<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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6.- Generic Technologies and Techniques<br />
6.1 - On-board Data Systems<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/EDP-001<br />
SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A)<br />
The first generation of high speed digital links controllers is based on the IEEE1355 standard which was the starting point to<br />
the definition of SpaceWire networks. They are used in very large number of <strong>ESA</strong> missions. However, the SMCS332 and<br />
SMCS116 devices are not fully compliant with the SpaceWire specification (e.g. they do not support time codes) and are<br />
implementing an initialisation state machine that leads to major operational constraints. Furthermore, they suffer from several<br />
design anomalies, discovered by first Users but today well characterised (e.g. w.r.t to interfaces in some sub-modes).<br />
Considering the situation, it required to upgrade the SMCS332 and SMCS116 to full SpaceWire compliance. This will allow as<br />
well to correct the identified anomalies and to secure the availability of such devices by pro<strong>du</strong>cing them on a more recent<br />
silicon process (e.g. migrating from MG1RT to MG2RT). An extensive validation campaign is included in the proposed activity.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL3 Target TRL: TRL5 Application Need/Date: TRL5 by 2007<br />
All missions (first possible application<br />
Application/Mission: Contract Duration:<br />
might be Cryosat 2)<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
36 months<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A): enhancement<br />
The first generation of high speed digital links controllers is based on the IEEE1355 standard which was the starting point to<br />
the definition of SpaceWire networks. They are used in very large number of <strong>ESA</strong> missions. However, the SMCS332 and<br />
SMCS116 devices are not fully compliant with the SpaceWire specification (e.g. they do not support time codes) and are<br />
implementing an initialisation state machine that leads to major operational constraints. Furthermore, they suffer from several<br />
design anomalies, discovered by first Users but today well characterised (e.g. w.r.t to interfaces in some sub-modes).<br />
Considering the situation, it required to upgrade the SMCS332 and SMCS116 to full SpaceWire compliance. This will allow as<br />
well to correct the identified anomalies and to secure the availability of such devices by pro<strong>du</strong>cing them on a more recent<br />
silicon process (e.g. migrating from MG1RT to MG2RT). An extensive validation campaign is included in the proposed activity.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL3 Target TRL: TRL5 Application Need/Date: TRL5 by 2007<br />
Application/Mission: All missions Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Conclusions: <strong>ESA</strong>/IPC(2003)32<br />
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<strong>TRP</strong> Reference:<br />
03/ESD-001<br />
Title: Rf Wireless Intra-Spacecraft Communications - Phase 1<br />
RF wireless techniques are being considered for on board short-range communications in view of the potential mass and<br />
power re<strong>du</strong>ction and for the added benefit of increasing functionality and flexibility in S/C design, construction and testing.<br />
From recent years, RF wireless systems have known a great development in in<strong>du</strong>strial, offices and home applications and<br />
offer a wide spectrum of mature pro<strong>du</strong>cts. The availability of high performance consumer-markets components make today<br />
RF an attractive approach for low mass on board-space communications for applications providing that EMC/EMI issues are<br />
adequately addressed at system level and shall be thoroughly investigated. This investigation will consider the space<br />
environmental aspects, in particular radiation, the spacecraft internal environment (in particular EMC/EMI) as well as the<br />
functional and operational aspects as a part of the on board data handling system (control and monitoring telecommand<br />
distribution/telemetry acquisition functions).<br />
The proposed activity deals with the use of optical wireless techniques for on board communications, and in particular will<br />
cover the following technology areas:<br />
• Functional and performance specifications for on board RF wireless communications for control, monitoring, command<br />
distribution and telemetry acquisition as part of the Spacecraft avionics for a set of typical mission scenarios (platform type,<br />
mission profile, orbit) and in line with relevant CCSDS standards<br />
• Identification of the most suitable system configuration and architecture for selected applications/scenarios<br />
• Identification and selection of commercial/in<strong>du</strong>strial RF wireless communications systems (protocols, components)<br />
• Performance/reliability assessment of technology, components and devices<br />
• Assessment of Qualification for components and devices<br />
• Evaluation and characterization of electronics equipment/component and their interfaces<br />
• Selection of a Test application case from the preliminary set of applications scenarios to be used as System demonstrator<br />
• Definition of a Flight Test Demonstration based on the above<br />
• Preliminary design of the RF wireless communication system<br />
• Critical component and subassembly design and developments including mixed digital-analog Asics<br />
• Development of Software tools for system analysis optimisation and computer aided design (link budget…)<br />
• Development of communication protocol and interface layers for selected configurations, operation and test environment<br />
software<br />
• Integration and Test of the Elegant bread-board of a complete RF wireless systems for the selected applications<br />
• Consolidated technology road map and proposal for a flight demonstration based on the demonstration system.<br />
Deliverables:<br />
Technical datapackage. Elegant BB.<br />
Current TRL: TRL2 Target TRL: TRL3 Ph1. Application Need/Date: TRL5 by 2009<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7756<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title: Rf Wireless Intra-Spacecraft Communications - Phase 2<br />
See Ph1. Description<br />
Deliverables:<br />
Technical datapackage. Elegant BB.<br />
Current TRL:<br />
Target TRL:<br />
TRL3<br />
TRL3-4<br />
PH2<br />
Application Need/Date: TRL5 by 2009<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7756<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
03/ESD-002<br />
Title: Optical Wireless-Intra-Spacecraft Communications - Phase 1<br />
Optical wireless techniques are being considered for on board short-range communications in view of the potential mass and<br />
power re<strong>du</strong>ction, EMI immunity, and for the added benefit of increasing functionality and flexibility in S/C design, construction<br />
and testing. Recent advances in optical Micro and Nano Technology, the availability of high performance consumer-markets<br />
Opto-electronic components make today optical unguided links a feasible valuable approach for low mass, low power, high<br />
data-rate on-board space communications. Furthermore, the increasing bandwidth’s requirements for Earth Observation and<br />
Telecom payloads, the possibility to handle multi-user configurations, and strict S/C EMI immunity and cross-talk<br />
requirements, make optical wireless a very valuable solution to be thoroughly investigated.<br />
This investigation will consider the space environmental aspects, in particular radiation (electronics, electro-optics and optics<br />
components), the spacecraft internal environment (topology, materials reflectance and absorption) as well as the functional<br />
and operational aspects as a part of the on board data handling system (control and monitoring, telecommand<br />
distribution/telemetry acquisition functions).<br />
The proposed activity deals with the use of optical wireless techniques for on board communications, and in particular will<br />
cover the following technology areas:<br />
• Functional and performance specifications for on board optical wireless communications for control, monitoring, command<br />
distribution and telemetry acquisition as part of the Spacecraft avionics for a set of typical mission scenarios (platform type,<br />
mission profile, orbit) and in line with relevant CCSDS standards<br />
• Identification of the most suitable system configuration and architecture for selected applications/scenarios<br />
• Identification and selection of commercial/in<strong>du</strong>strial optical wireless communications systems (protocols, components)<br />
• Performance/reliability assessment of technology, components and devices<br />
• Assessment of Qualification for components and devices<br />
• Evaluation and characterization of Opto-electronic equipment/component and their interfaces<br />
• Selection of a Test application case from the preliminary set of applications scenarios to be used as System demonstrator<br />
• Definition of a Flight Test Demonstration based on the above<br />
• Preliminary design of the optical wireless communication system<br />
• Critical component and subassembly design and developments such as fast IR repeater<br />
• Development of Software tools for system analysis optimisation and computer aided design (link budget…)<br />
• Development of communication protocol and interface layers for selected configurations, operation and test environment<br />
software<br />
• Integration and Test of the Elegant bread-board of complete optical wireless systems for the selected applications<br />
• Consolidated technology road map and proposal for a flight demonstration based on the demonstration system.<br />
Deliverables:<br />
Technical datapackage. Elegant BB.<br />
Current TRL: TRL2 Target TRL: TRL3 Ph1 Application Need/Date: TRL5 by 2009<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7756<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title: Optical Wireless-Intra-Spacecraft Communications - Phase 2<br />
Optical wireless techniques are being considered for on board short-range communications in view of the potential mass and<br />
power re<strong>du</strong>ction, EMI immunity, and for the added benefit of increasing functionality and flexibility in S/C design, construction<br />
and testing. Recent advances in optical Micro and Nano Technology, the availability of high performance consumer-markets<br />
Opto-electronic components make today optical unguided links a feasible valuable approach for low mass, low power, high<br />
data-rate on-board space communications. Furthermore, the increasing bandwidth’s requirements for Earth Observation and<br />
Telecom payloads, the possibility to handle multi-user configurations, and strict S/C EMI immunity and cross-talk<br />
requirements, make optical wireless a very valuable solution to be thoroughly investigated.<br />
This investigation will consider the space environmental aspects, in particular radiation (electronics, electro-optics and optics<br />
components), the spacecraft internal environment (topology, materials reflectance and absorption) as well as the functional<br />
and operational aspects as a part of the on board data handling system (control and monitoring, telecommand<br />
distribution/telemetry acquisition functions).<br />
The proposed activity deals with the use of optical wireless techniques for on board communications, and in particular will<br />
cover the following technology areas:<br />
• Functional and performance specifications for on board optical wireless communications for control, monitoring, command<br />
distribution and telemetry acquisition as part of the Spacecraft avionics for a set of typical mission scenarios (platform type,<br />
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mission profile, orbit) and in line with relevant CCSDS standards<br />
• Identification of the most suitable system configuration and architecture for selected applications/scenarios<br />
• Identification and selection of commercial/in<strong>du</strong>strial optical wireless communications systems (protocols, components)<br />
• Performance/reliability assessment of technology, components and devices<br />
• Assessment of Qualification for components and devices<br />
• Evaluation and characterization of Opto-electronic equipment/component and their interfaces<br />
• Selection of a Test application case from the preliminary set of applications scenarios to be used as System demonstrator<br />
• Definition of a Flight Test Demonstration based on the above<br />
• Preliminary design of the optical wireless communication system<br />
• Critical component and subassembly design and developments such as fast IR repeater<br />
• Development of Software tools for system analysis optimisation and computer aided design (link budget…)<br />
• Development of communication protocol and interface layers for selected configurations, operation and test environment<br />
software<br />
• Integration and Test of the Elegant bread-board of complete optical wireless systems for the selected applications<br />
• Consolidated technology road map and proposal for a flight demonstration based on the demonstration system.<br />
Deliverables:<br />
Technical datapackage. Elegant BB.<br />
Current TRL:<br />
Target TRL: TRL3-4 Application Need/Date:<br />
TRL3<br />
TRL5 by 2009<br />
(PH2)<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7756<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: 97/WSP01<br />
Title: Fast Transform DSP Coproc Ph. 2 & 3<br />
Floating point data representation is not a requirement for some applications and a performance increase about one order of<br />
magnitude w.r.t the ADSP21020 can be achieved by using a fixed-point co-processor. This is particularly true for small block<br />
size FFts, FIR filters and transforms in general. A configurable device with multiple parallel ALUs shall be developed in the<br />
frame of this activity. The ASIC will be very suitable as a stand alone computing unit for low level processing or as an<br />
accelerator when coupled to the ADSP21020.<br />
Deliverables:<br />
Technical data package. Breadboard.<br />
Current TRL: TRL2-3 Target TRL: TRL5/6 Application Need/Date: TRL5/6 by 2008<br />
Application/Mission: RF instruments e.g. SAR, altimeters Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7798<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ESD-006<br />
Design & verification of validation techniques for On-Board Microprocessors<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ESD-016<br />
Safeguard Data Recorder<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ESD-034<br />
Optical Wireless Data Transmission<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ESM-006<br />
High Speed Link Interconnect Network – Additional work<br />
The SpaceWire Router ASIC under development in this activity is based on the RMAP protocol, an extension of the<br />
ECSS-E50-12A standard. Owing to some protocol changes adopted by the international working group on RMAP, as well as<br />
to some functional problems in the current version of the SpaceWire Router design, not covered by the original requirements,<br />
some additional work is necessary. This activity will improve the component and will provide an interoperable, reliable and<br />
standard compliant ASIC. The activity shall include the following main tasks:<br />
- Router VHDL technical changes: 1. bit serial implementation of the reversed CRC, LSB first; 2. include a data CRC with<br />
value 0 when data field is empty; 3. correction of the link speed to the minimum authorized value in case a wrong command<br />
sequence would try to set it below; 4. allow the router to respond to 0 source address RMAP commands; 5. modification of<br />
one of the timeout conditions at the input ports; 5. modify accordingly the Validation SW.<br />
- VHDL test bed and test vectors modification accordingly to the router changes.<br />
- Verification of the new RTL model of the router.<br />
- Synthesis of a new RTL model for FPGA and ASIC technology.<br />
- Verification of new ASIC netlist.<br />
- Making of a new CIDL.<br />
- Reprogramming of the 5 router FPGAs.<br />
- New router FPGA validation exercise on single and double router test bed (shorter and simpler FPGA validation exercise,<br />
compared to the previous ones, where we only seek to validate that the changes to the netlist provide the expected functional<br />
changes).<br />
- Extension of the original WPs reserved for the basic router ASIC Validation to a full ASIC validation, as described in separate<br />
<strong>document</strong>.<br />
Deliverables:<br />
- Updated FPGA routers.<br />
- Updated FPGA router Data sheet.<br />
- Updated validation SW and related <strong>document</strong>s.<br />
- Report on the new FPGA router validation.<br />
- Extended ASIC router validation report.<br />
Current TRL: TRL1 Target TRL: TRL3/4 Application Need/Date: TRL4 by 2007<br />
Application/Mission: All spacecraft data handling systems Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-901 (2004 D0)<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETD-025<br />
Compact Data Processing Unit<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETD-028<br />
Integrated Payload Data Processing System System<br />
The objective of the activity is the integration and demonstration of the scalability of the on-board payload scalable super data<br />
signal processor. The system shall be used as well to support S/W development activities and will become a test bench that<br />
shall be integrated in ESTEC’s Image Laboratory. Applications listed in the mini-project definition shall be demonstrated on the<br />
system as well.<br />
After the completion of the original tasks, CCN2 has been placed for the updating of the RMAP already implemented in IPPM<br />
to the latest draft (draft E) of the SpW standard.<br />
In addition, in order to ovecome some technical functional limitation envisaged <strong>du</strong>ring the final test phase, CCN4 has been<br />
placed, having the following scope:<br />
* Replacement of faulty SpaceWire router with FPGA version of the SpW router 10x ASIC.<br />
* Modify memory interface between Leon2 processor and memory devices to achieve maximum operational speed 100MHz.<br />
The main tasks involved are: PCB rework, VHDL code refinement, PCB manufacturing, assembly and integration, FPGA<br />
fitting and post layout simulations, Test and validation Session.<br />
Deliverables:<br />
Demonstration model.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ETD-036<br />
Title:<br />
Next Generation Mass Memory Architecture<br />
The architecture and design of the current generation of Solid State Mass Memory (SSMM) is not able to cope with the further<br />
increasing data rate requirements from future payloads, nor with the dramatic technology evolution of the commercial DRAM<br />
technology. The commercial SDRAM used in today’s SSMM are soon expected to be obsolete. The PC marked already<br />
moved to newer and faster DRAM standards like DDR-SDRAM and DDR2-SDRAM. These new devices are expected to put<br />
some architectural constraints at memory bank level. This comprises amongst others new requirements on the readout<br />
circuits and possible new radiation intro<strong>du</strong>ced error modes in the read out and the more complex on chip addressing logic.<br />
Therefore <strong>du</strong>ring the course of the study a system analysis shall be performed and an architectural design for the next<br />
generation SSMM based on mature technology for space (memory, packaging, controller technology) and satisfying new<br />
DRAM standards and the emerging very high data rate payload requirements shall be developed.<br />
Deliverables:<br />
Breadboard.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5/6 by 2007<br />
Application/Mission: EO, SCI missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7797<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETD-038<br />
Space wire Controller Remote User<br />
The objective of this activity is to develop a SpaceWire Controller/Remote-User-Interface ASIC. The SpaceWire standard has<br />
been the subject of major revisions w.r.t. the initial definition based on the IEEE1355 Standard. The interface is compatible<br />
today with hot-plug-in and supports the generation and reception of time codes. Therefore a SpaceWire specific Controller and<br />
Remote-User-Interface must be designed and ported to a Radiation Tolerant technology. The purpose of this activity is hence<br />
to make such a device available to the User community as a standard pro<strong>du</strong>ct. The devices will also be made available to the<br />
participants of ETD-039.<br />
Deliverables:<br />
SpaceWire specific Controller and Remote-User-Interface demonstrator.<br />
Current TRL: TRL4 Target TRL: TRL5 Application Need/Date: TRL5 by 2006<br />
Application/Mission: Spacewire Networks Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7796<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ETD-039<br />
Title:<br />
TOPNET: Pilot Operation Implementation - Topnet Deployment<br />
The objective of this activity is to demonstrate the benefits of the TOPNET approach through early integration of actual<br />
hardware. For this purpose equipment supplier will be invited through an AO to participate by making their (existing)<br />
equipments available for the demonstration. Development of new equipments is not foreseen as part of the demonstration.<br />
Contract value will range between 50-150 KEeuro. The activity will utilise the tools developed under ETD-037.A and the<br />
controller developed under ETD-038.<br />
Deliverables:<br />
Pilot Demonstration<br />
Current TRL: TRL3 Target TRL: TRL5 Application Need/Date: TRL5 by 2008<br />
Application/Mission: all S/C, SCI, EO, in line testing Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7801<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-05ET<br />
Title:<br />
FPGA Based Generic Mo<strong>du</strong>le and Dynamic Reconfigurator<br />
In the framework of the on-board payload data processing reference system, the computing power is de-centralised and<br />
distributed in well-defined processing mo<strong>du</strong>les where the applications rely on. One of the major benefits of this architecture is<br />
to allow the independent technological evolution of the mo<strong>du</strong>les without affecting the architecture itself: objective of this<br />
activity is therefore to provide the system with new processing models that can be, on one side, painless inserted into the<br />
exiting architecture and, on the other side, not specifically designed for a particular need. In this way, words like equipment<br />
re-use or non-recurrent costs saving become realistic; but which hardware components can we use for such a development<br />
The most profitable solution is to develop this processing mo<strong>du</strong>le using an FPGA based design: this approach gives some<br />
flexibility <strong>du</strong>ring the definition and early validation phase as well as smooth porting of the demonstration to its flight version<br />
(using space qualified FPGAs).<br />
Deliverables:<br />
HW demonstrator, validated into the payload data processing reference system.<br />
Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5 by 2009<br />
Application/Mission: Exploration missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7802<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-08ES<br />
Next Generation Multi-purpose Microprocessors<br />
The prototypes of the AT697 of ATMEL (LEON2–FT) are already available for evaluation and advanced design of flight<br />
computer boards and the flight parts of the AT697 will be soon commercialised. The AT697 microprocessor is based on the<br />
LEON2 model and it offers a significant increase of performance (100 MIPS, million of instructions per second) with respect to<br />
the previous generation of the ERC32 microprocessor (25 MIPS for the TSC695). This new AT697 microprocessor will satisfy<br />
the newly and evenly increasing requests of performance for the new space missions. The development time of high<br />
performance microprocessors for space use (with Single Event Effects tolerance) is at least 5 years and consequently it must<br />
be largely anticipated. In a present contract the Agency is already preparing the next generation of general purpose of<br />
microprocessor with the target to offer an increase of performance in a ratio of 10 with respect to the last generation of the<br />
AT697 together with a higher flexibility of usage that is based on a multiple core approach that will be an enabler for a new<br />
class of system architectures and capabilities. The objective of that present activity is to adapt and to configure the new<br />
available commercial LEON3 model for its use in a high performance processor architecture suitable to space use and to<br />
validate that new architecture on FPGA (Field Programmable Gate Array). The previous experience with the development of<br />
the AT697 has shown that the implementation of a complex processor model using advanced silicon technology is not trivial<br />
and need also some anticipation work. The purpose of the proposed activity is to continue the present activity based on the<br />
LEON3 model with the objective to establish the appropriate design implementation methodology and select the appropriate<br />
design implementation tools, to make the necessary fine tunings of the architecture and the detailed design of the model that<br />
are required by the design implementation, and to pro<strong>du</strong>ce a silicon demonstrator using an advanced commercial silicon<br />
technology as close as possible of the target space technology for the final implementation and that will exhibit the full<br />
performance and that will be as much as possible representative of the functionality of the future space version of the next<br />
generation general purpose microprocessor. Microprocessor devices and evaluation boards will be made available to the<br />
European space community that can be used for familiarisation, evaluation, and consolidation of the specification of the next<br />
generation general purpose microprocessor pro<strong>du</strong>ct.<br />
Deliverables:<br />
Documentation and breadboard.<br />
Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL5 by2012<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7798<br />
Consistency with Harmonisation<br />
OBCDS - Microprocessors and Microelectronics<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-09ES<br />
Title:<br />
Validation and further development Spacecraft-Controller-on-a-Chip (SCOC)<br />
In the SCOC1 contract (13345/99/NL/FM), a prototype design (called SCOC1 from now on) and an evaluation board (BLADE)<br />
for the SCOC device has been developed by/with EADS-Astrium Vélizy. The final objective of the SCOC programme is to<br />
pro<strong>du</strong>ce an ASIC, available as off-the-shelf component to European In<strong>du</strong>stry, which will simplify the architecture of future<br />
OBDH systems. The device functionality shall be comprehensive such as to satisfy a large variety of system requirements, yet<br />
be scalable such as to be able to work in systems not using all of the features at re<strong>du</strong>ced power consumption. With the<br />
experience and lessons learned from SCOC1, the Definition and Architectural Design (updated/modernised Specification,<br />
verified RTL code) for an ASIC implementation (called SCOC2) shall be performed in the present contract. Manufacturing,<br />
in<strong>du</strong>strialisation and software development being subject to follow-up activities, this contract ends with an enhanced feasibility<br />
study (selection of, and synthesis into potential target technologies). The activity also includes the development of new IP s<br />
(e.g. AMBA bus monitors) or updating of existing IP s as appropriate. New IP s are also deliverable as separate IP's. The goal<br />
is to have at the end of this contract a verified RTL design, which is ready to be mapped into an ASIC.<br />
Deliverables:<br />
Updated SCOC-FPGA design database and development board; specification for SCOC-ASIC; demonstration report and<br />
SW/driver library; new or updated IP.<br />
Current TRL: TRL3 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2007<br />
Application/Mission: all S/C Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7799<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-20ET<br />
Development of a Mass Memory Mo<strong>du</strong>le with Embedded File System Support<br />
The Payload Processing System architecture is able to host a set of well defined mo<strong>du</strong>les (Processing, Storage, I/O)<br />
interconnected through a network. As far as storage mo<strong>du</strong>les are concerned, a first demonstrator of the concept was<br />
developed and manufactured (High Capacity Memory Buffer). Based on standard interfaces, the mo<strong>du</strong>le was designed in<br />
order to be very close in terms of functionality to a "solid state" disk providing basically to the User a sea of data blocks<br />
(random block mode) rather than emulating a tape recorder (LIFO/FIFO modes).Building on this, it appears clearly that the set<br />
of data blocks can be organised in a more flexible manner by embedding block allocation tables in the mass memory mo<strong>du</strong>le<br />
itself. Of course and ultimately, the link between a "file" as seen by the payload data system controller and block allocation<br />
tables shall be established by a well defined split of functions between the supervisor and the high capacity buffer. This<br />
activity will focus on the development of a mass memory mo<strong>du</strong>le embedding file system support following the concept outlined<br />
above.<br />
Deliverables:<br />
Two mass memory mo<strong>du</strong>les electrical/elegant breadboards<br />
Current TRL: TRL2-3 Target TRL: TRL4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: all S/C Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7797<br />
Consistency with Harmonisation<br />
Payload Data Processing<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-22ES<br />
Title:<br />
Synthesizable VHDL IP cores<br />
The objective is to develop Intellectual Property (IP) VHDL cores that meet the demands of future spacecraft architectures. If<br />
the VHDL cores can also be used in the commercial domain, the advantage of free distribution and user community feed back<br />
should be exploited. The actual cores to be developed need to be investigated at start of the activity. The activity shall be<br />
coordinated and maintain compatibility/compliance with standards established by previous developments (LEON/AMBA) and<br />
other new activities. Apart from completely new designs, the adaptation/improvement of existing IP's (or previous ASIC<br />
designs) shall be considered. The suggested VHDL IP cores to be developed are a Floating Point Unit for digital signal<br />
processing; improvement of inter-chip and inter-board interfaces (e.g. PCI, PCIX); ethernet controller; high speed<br />
telemetry/telecommand for CCSDS Advanced Orbiting Systems and Proximity Links; image Compression cores; Star Tracker<br />
Interface and Gyroscope Interface <strong>ESA</strong> shall retain ownership and full IP rights as to be able to use the delivered new IP<br />
cores for internal and external <strong>ESA</strong> or non-<strong>ESA</strong> projects, at <strong>ESA</strong> discretion. Special attention shall be given to the high quality<br />
of the User's Manual <strong>document</strong>s to be pro<strong>du</strong>ced for each IP Core, to guaranty maximum autonomy of the IP Core customers,<br />
and minimise the level of technical support requested to <strong>ESA</strong>.<br />
Deliverables:<br />
Synthesizable VHDL IP cores with User's Manual, and testbench <strong>document</strong>ation.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010-2012<br />
Application/Mission: all S/C Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7796<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T603-27ED<br />
Evaluation of Radiation Effects on Deep Sub-micron CMOS Technologies (Original<br />
Title:<br />
<strong>title</strong>:SEE Identification, Modelling & Severity assessment)<br />
Based on an extensive review of already published information, this activity will establish in a first instance specific<br />
vulnerabilities of deep submicron silicon technologies (target 90 nm CMOS). This first assessment will be based on modelling<br />
and simulating potential impacts of radiation effects on digital circuits, allowing to determine their severity (taking into account<br />
very low supply voltages and high operating frequencies). Then workaround techniques will be proposed and assessed in<br />
terms of feasibility taking into account all possible mitigation techniques at all levels. Finally a set of test structures shall be<br />
designed, demonstrating the models and the effectiveness of the proposed mitigation techniques on Silicon.<br />
Deliverables:<br />
Models (to derive impact on digital circuits and suitable mitigation techniques). Severity assessment of forecasted effects<br />
(SET FIT quantification for given design/rad environment). Test structures design.<br />
Current TRL: - Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7804<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-26ES<br />
Radiation Hardened by Design ASIC library qualification, procurement and maintenance<br />
This activity will give continuity and consolidate the results of two previous activities in which a<br />
Radiation-Hardened-by-design (layout design) Standard Cell library based on a commercial CMOS .18 micron library (from<br />
Virtual Silicon Technologies) and ASIC manufacturing process (UMC) has been developed, tested, and pre-qualified by<br />
means of two test-vehicles ASICs and a large DSP (>1Mgates) ASIC .<br />
This new proposed activity seeks to consolidate this library as a reliable and inexpensive new alternative to the very few<br />
library/foundry choices that exist in Europe to fabricate Rad Hard ASICs.<br />
Deliverables:<br />
Fully characterised and tested RHBD library.<br />
Current TRL: TRL3 Target TRL: TRL5 Application Need/Date: TRL5 by 2007<br />
Application/Mission: all S/C Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7795<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T609-08ET<br />
Massively Parallel Processor Breadboarding<br />
The demand for digital signal processing from on-board applications in earth observation, science and communication is<br />
continuously growing while the only available radiation hard DSP processor TSC21020F is today old technology and will<br />
disappear latest by 2007. It is not clear if there will be a follow on for this DSP as 32-bit DSP manufacturers are not numerous<br />
and are in general not interested in licensing their technology for a niche sector like space. The performance need of the<br />
applications lead today to a lot of ASIC developments for every new application in order to cope with the requirements. On the<br />
other hand FPGAs, which provide flexibility are not able to deliver the needed performance. The objective of this activity is to<br />
demonstrate, that new flexible processor architectures are capable to fill the gap between ASICs and FPGAs with respect to<br />
required flexibility, performance and budgets. These new flexible architectures are based on multiple DSP cores which can be<br />
internally rearranged (in parallel or in pipeline) by software command according to the algorithm requirements. The processor,<br />
once being available as customisable IP core (Intellectual Property), shall provide a high performance complement to FPGA<br />
technology for space applications as it can be tailored in a most efficient way and it shall be possible to transfer it at a later<br />
stage to radiation hardened technologies.<br />
Deliverables:<br />
BB incl. a commercial grade ASIC with new flexible multi DSP processor architecture demonstrating flexibility/performance. IP<br />
core of multi DSP architecture transferable to other ASIC processes. Programming tools (for appl. implement on the<br />
processor).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2009-2010<br />
Application/Mission: missions with high data rates e.g EO, Sci Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7742, T-7802<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T609-25ED<br />
Title:<br />
SpaceWire Network Bandwidth Performance Simulation Tool<br />
In a number of activities <strong>ESA</strong> has prepared the SpaceWire technology that allows to embark high speed data networks on<br />
board of future satellite systems. This new technology has become widely adopted not only by <strong>ESA</strong> missions but also by other<br />
agencies and in<strong>du</strong>stry. The design of the topology and routing tables of such a on-board network, which has to comply to the<br />
system requirements, is left today to the engineering judgement of the designer and can be only validated at a late stage<br />
<strong>du</strong>ring system testing. This task becomes more and more difficult when the complexity of the on-board networks increases.<br />
A simulation of such high speed on-board networks will allow to verify the performance requirements like latency and<br />
throughput and to verify the re<strong>du</strong>ndancy scheme. It will allow to optimise the routing tables and ensure that the designed<br />
network is non blocking. A simulation software for this task should configurable with the network topology, link, router, node<br />
characteristics and the network data load. The results of this simulation should provide a clear view on the network statistics<br />
and provide a validation of the chosen network topology already <strong>du</strong>ring the design phase<br />
Deliverables:<br />
Engineering software tool for modelling and performance assessment of High Speed On-board Networks.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL4 by 2007<br />
All payload data systems using high<br />
Application/Mission: Contract Duration:<br />
speed onboard networks<br />
SW Clause : Operational SW Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Payload Data Processing<br />
Roadmap and Conclusions:<br />
12 months<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T609-26ED<br />
OCP-IP building blocks for Space-SoC<br />
"Open Cores Protocol" (OCP) is an emerging standard set of requirements and tools that are being successfully applied to<br />
facilitate IP Cores reuse, easier integration and compatibility between different on-chip bus systems (CAN, AMBA, SpaceWire,<br />
I2C, etc). The activity would be about designing OCP-IP mo<strong>du</strong>les for our existing <strong>ESA</strong> IP Cores, so future space-SoC can<br />
make use of <strong>ESA</strong> OCP compliant building blocks.<br />
Deliverables:<br />
OCP-IP mo<strong>du</strong>les architecture.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL4 by 2007<br />
All spacecraft data handling systems /<br />
Application/Mission: Contract Duration: 10 months<br />
Space-SoC<br />
SW Clause : - Dossier0 Ref.: T-7799<br />
Consistency with Harmonisation<br />
On-Board Payolad Data Processing<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T609-27ED<br />
Title:<br />
Standardisation of spacecraft onboard communication services<br />
Until recently, standardisation efforts within the realm of onboard spacecraft have concentrated on physical interfaces and<br />
associated protocols. Such activities have been handled by the Consultative Committee for Space data standardisation (<br />
CCSDS) or the ECSS. Within these standardisation bodies emphasis is now being placed on the definition of communication<br />
services and protocols which allow independence from the underlying hardware and thus open up the possibility for software<br />
re-use across multiple missions. This has the potential to significantly re<strong>du</strong>ce spacecraft development times and associated<br />
costs. As part of the ongoing work of the Spacecraft Onboard Interface Services (SOIS) group within the CCSDS,<br />
recommendations for a suite of communication services are well advanced and will be made available in draft form before the<br />
end of 2006. In order achieve final publication, the draft recommendations must be prototyped and verified in a representative<br />
spacecraft environment. This activity will cover there required prototyping, integration and test on an existing <strong>ESA</strong> test-bed<br />
infrastructure. Results will be incorporated by <strong>ESA</strong> into the final CCSDS recommendation which will subsequently be adopted<br />
by <strong>ESA</strong> for potential application to all spacecraft projects. The software should take the form of reference libraries which can<br />
be made available for use by <strong>ESA</strong> projects.<br />
Deliverables:<br />
Software implementing the CCSDS defined services and protocols<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL4 by 2007<br />
Application/Mission: All spacecraft data handling systems Contract Duration: 12 months<br />
SW Clause : Operational SW Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
On-Board Payolad Data Processing<br />
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6.2 - Space System Software<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EME-012<br />
Component Oriented Development Techniques<br />
The objective of the activity is to put in practice for space flight software the various techniques used in the wider IT world in<br />
this domain: components, frameworks, model driven development and architecture, aspects features, etc. This includes the<br />
assessment of the state of the art, precision of the vocabulary used in the domain, impact on flight software where the<br />
hardware resources (memory / execution time) are limited, and development of a case study based on prototype generic<br />
architectures or building blocks.<br />
Deliverables:<br />
Component-based space architecture + its assessment in terms of performance and standardisation. (In view of using the<br />
prototype as <strong>ESA</strong> building block for future missions, operational SW is necessary).<br />
Current TRL: algorith Target TRL:<br />
Application Need/Date:<br />
prototype<br />
SW operational by 2009<br />
m<br />
Application/Mission: All missions Contract Duration: 9 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7671<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EME-014<br />
Compact Computer Core S/W<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: EME-017<br />
Title:<br />
Tools For The Pro<strong>du</strong>ction Of O/B Sw Running On New Generation Computers<br />
The objective of the study, is to prepare the software (SW) environment related to the new generation computer (based on<br />
Sparc V8). Priority will be given to the compiler and run-time system, then the debugger and the target simulator.<br />
Deliverables:<br />
SW breadboard<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational >=2007<br />
Application/Mission: All missions within LEON Contract Duration: 8 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-7743<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference: EME-100 (EME-011, T-<br />
Title:<br />
Effective Use of autocoded Comp.<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-28QQ<br />
Validation of Safety and Dependability Critical Software Componenets with Model<br />
Title:<br />
Based Requirements<br />
The validation of safety and dependability critical software components starts with ensuring that the requirements have been<br />
confirmed as fully testable and that they are complete and consistent. One approach that promises to facilitate the<br />
requirements definition process to achieve those three objectives is the use of models that can be analysed and simulated.<br />
Suitable models would need to be able to cope with incomplete and vague requirements at the early stages of a project’s<br />
definition and support the evolution towards formal or semiformal requirements at the end of the requirements definition<br />
phase. The simulations and analysis that would be possible on requirements models would support the preparation of high<br />
quality validation test suites.<br />
Deliverables:<br />
Technical notes (incl.: requirements models/quality requirements, and associated metrics; analysis techniques and simulation<br />
techniques for the requirements models; proof-of-concept through application to a case study).<br />
Current TRL: - Target TRL: Algorithms Application Need/Date: SW operational by 2010<br />
Application/Mission: all missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-1259<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T603-29SW<br />
System and Software Functional Requirements Techniques<br />
The activity will investigate how to integrate the two processes (system and software) through the use of complementary and<br />
integrable modelling technologies in phase A and B. The expected benefit is to arrive at the PDR with consolidated system<br />
functional requirements easily transferable to the software life cycle development. This will ensure a better continuity of the<br />
overall life cycle, from mission level modelling to software implementation through incremental model translation. The new<br />
method will complement the ASSERT results and both could be integrated in the long term in the CDF for final<br />
experimentation. The activity will include: (i) selection of a mission appropriate for mission level functional modelling and<br />
associated software requirements modelling. (ii) survey and selection of system and software modelling techniques (not<br />
limited to aerospace, but including also railway and automotive) (iii) implementation of the case study (iv) definition of the<br />
appropriate process and tools in reference with ECSS-E10Part1 and ECSS-E40Part1 (v) possible experimentation in the<br />
CDF.<br />
Deliverables:<br />
Suitable modelling methods, prototype environment, case study covering phase A and B.<br />
Current TRL: - Target TRL: Prototype Application Need/Date: SW operational >=2010<br />
Application/Mission: All missions Contract Duration: 15 months<br />
SW Clause : - Dossier0 Ref.: T-5224<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
On-Board SW<br />
<strong>TRP</strong> Reference: T607-01EM<br />
Title:<br />
Automation of the life cycle: automatic test generation<br />
The existence of more and more models of the system requirements allows to derive automatically sequences of test from the<br />
models. The issue is the selection of the tests which are appropriate for the test goal, and therefore the selection of the test<br />
goal itself. The selection criteria may be based on the test coverage, or on the activation of given internal states of the system,<br />
or selected use cases of the system that should be verified. The automatic tools will try to find all the test scenarios that oftwa<br />
the goal of the tests, either in a systematic way or through the use of statistic (statistical testing), or trying to achieve a<br />
coverage rate. The activity will select modelling languages on which automatic testing is possible, propose a test vector<br />
generator for given test goals, and give the process to use the tool. The activity will also investigate the statistical testing as a<br />
mean to target the test effort, precise its application to space oftware, and define how to use it in accordance with the<br />
software standards.<br />
Deliverables:<br />
Report (selection of appropriate modelling languages for automatic testing; testing criteria/statistics). Testing tool<br />
implementing the various testing policies. Report on adequacy of statistical testing with SW standards and a case study.<br />
Current TRL:<br />
Target TRL: Opeartional Application Need/Date:<br />
-<br />
tool /<br />
demontstrat<br />
SW operational >=2007<br />
ion<br />
Application/Mission: all space project Contract Duration: 12 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-5224<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T607-05EM<br />
Verification and Validation: Testing Object Orientation<br />
Object oriented languages are entering more and more into the space on-board software domain. Since the shy beginnings of<br />
object-based design using the HOOD method, a long way has lead us to the more frequent use of UML, C++ and Java<br />
languages on-board. This intro<strong>du</strong>ces powerful design features which express a lot in a small pattern. However, the associated<br />
code is also complex, and sometimes the selection of the piece of code to execute is made at run-time. It becomes extremely<br />
difficult to exhaustively test the overall software behaviour, as there may be too many combination and undeterminism. The<br />
goal of the activity is to investigate these specific OO features whose use makes testing very hard. The activity will propose<br />
solutions to overcome the problem. The solution ranges from proposing a clever and appropriate test policy specific to the<br />
feature, up to banning the use of the feature in a coding standard.<br />
Deliverables:<br />
Documentation with guidelines on testing object oriented on-board software and contribution to coding standards.<br />
Current TRL:<br />
Target TRL: Operational Application Need/Date:<br />
-<br />
tool /<br />
SW operational >=2007<br />
method<br />
Application/Mission: all space project Contract Duration: 12 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-5225<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T607-08EM<br />
Standardisation and Building Blocks: Standardisation watch and verification<br />
The activity aims at guiding, supervising, controlling and verifying the standardisation of the building blocks. It is a long term<br />
activity all along the standardisation period. It includes the creation and animation of a standardisation watch group involving<br />
in<strong>du</strong>stry members who will be in charge of defining what needs to be standardised, how it is standardised. It takes care of the<br />
maintenance of the standard. It steers the open source implementation, it guarantees the availability of the reference<br />
architecture, it decides on the deployment, and is responsible for organising the maintenance of the building blocks. It also<br />
includes the verification of the standards <strong>du</strong>ring their definition in terms of completeness and consistency between each<br />
others. This will be done with some dedicated tasks to verify specific technical aspects such as consistency of interface,<br />
completeness of the behaviour definition, data models, etc.<br />
Deliverables:<br />
System Model of a generic avionic architecture and a decomposition in building blocks.<br />
Current TRL:<br />
Target TRL: Beta Application Need/Date:<br />
-<br />
SW operational >=2009-2010<br />
version<br />
Application/Mission: all space project Contract Duration: 12 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7671<br />
Consistency with Harmonisation<br />
On-Board SW<br />
Roadmap and Conclusions:<br />
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6.3 - S/C Power<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EPB-001.C<br />
Development of Regenerative H2/O2 fuelcell<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: EPG-025<br />
Title:<br />
Solar Cells Testing Spasolab<br />
A five years contract (220kE/year) is proposed aiming at covering Spasolab 2003-2007 operational phase for supporting solar<br />
cell developments in the <strong>TRP</strong>.<br />
A list of Spasolab solar cell test laboratory capabilities is provided in the following:<br />
• Complete characterisation of space of Space Silicon and Gallium Arsenide solar cells (Type approval tests).<br />
• Development of test methods for the characterization of last generation photo-voltaic devices<br />
• Electrical characterization at panel and mo<strong>du</strong>le level.<br />
• Electrical and environmental characterization at coupon level.<br />
• Calibration of reference solar cells (primary and secondary standards).<br />
• Research and development activities (e.g. elaboration of specifications for new devices).<br />
Deliverables:<br />
Tested samples. Technical note, test results.<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: N/A<br />
Application/Mission: all space projects Contract Duration: 60 months<br />
SW Clause : - Dossier0 Ref.: T-7806<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Solar Generators<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
ESB-008.A<br />
Adaptation of terrestrial fuel cells for space applications<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ESG-007<br />
Title: Thin Film Solar Cells Ph. 3<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ESG-009<br />
Title:<br />
Reverse Bias Protection of GaAs Solar Cells<br />
The aim of this activity is to develop new methods for protecting single-junction and multi-junction GaAs solar cells in reverse<br />
bias conditions. Alternative methods shall be developed, based for instance on self-protected epitaxial structures. The new<br />
technique shall be demonstrated with the pro<strong>du</strong>ction of the first prototypes, which will tested and be evaluated.<br />
Deliverables:<br />
20 - 30 GaAs solar cells (demonstrators) with the newly developed protection technique and an evaluation report of old and<br />
new protection methods, including assessment at system level and costing.<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
ESG-010<br />
Development Of Interconnection Techniques For Thin Film Solar Cells<br />
The objective of this activity is the development of reliable thin-film cell interconnection techniques for space application. The<br />
activity will concentrate on CdTe solar cells, CuInSe2 (CIS) based solar cells, silicon and micromorph silicon solar cells.<br />
Deliverables:<br />
At least 1 development sample (mini mo<strong>du</strong>le) for each solar cell type shall be pro<strong>du</strong>ced.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Telecom, Science, EO Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7812<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ESG-017<br />
Flexible Blanket Technology<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ESP-003<br />
Solar Array Sizing tool for Phase A/B studies<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T505-11EP<br />
Advanced research and pre-development of new materials for space solar cells<br />
The aim of the project is to allow pre-development of new materials and concepts which will enable construction of solar cells<br />
with performance closer to theoretically possible values, such as multi-junction cells with an efficiency of >40%. This project<br />
will also aim to extend the alliance of the best European materials technology with European solar cell research groups and<br />
manufacturers. In this project, growth of new materials such as nitride based alloys will be researched in order to pro<strong>du</strong>ce<br />
material quality required for state of the art photovoltaic devices, in particular to facilitate multi-junction devices. Further<br />
research, needed into novel processing techniques and device concepts required to exploit the new materials, is not included<br />
in this proposal and it is recommended as follow-on activity.<br />
Deliverables:<br />
20 demonstration solar cells (using other materials as well as/instead of GaAs based alloys). Report which assesses the likely<br />
developments and applications of new space solar cells for missions until 2015.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Missions >=2020 Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7806<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T604-02EP<br />
Title:<br />
Advanced Lithium Batteries Evaluation<br />
The objective of this activity is to evaluate new advanced rechargeable lithium batteries offering energy density over 250<br />
Wh/kg. Such batteries could lead to mass and volume savings of spacecrafts.<br />
Lithium cells (graphite/LiCoO2 couple) offer today energy density around 180 Wh/kg. This electrochemical system is reaching<br />
maturity, with a limitation at about 200Wh/kg; therefore, to obtain a significant gain in energy density, it is necessary to study<br />
new electrochemical couples. The development of high energy density lithium batteries is driven by the terrestrial market, and<br />
studies on new electrode materials and new electrolytes are numerous.<br />
Positive electrode materials with higher capacity, also with higher potential (up to 5 V, i.e LiCoPO4) are studied by many<br />
groups. Negative electrode materials are also developed to replace the current graphite anode (i.e FeSi or FeSn can offer an<br />
energy 10 times greater). Lithium, the lightest and most energetic metal but highly reactive, can also replace the graphite<br />
anode. The use of such new electrode materials requires new electrolytes (i.e polymers, ionic liquids, plastic crystals, …).<br />
Some promising electrochemical systems are under investigation in Europe and elsewhere.<br />
This activity will include: a survey of the new electrodes materials and new electrolytes, identification of new electrochemical<br />
couples that could lead to the highest energy density, preparation of cells with the new materials, testing of the new cells.<br />
Deliverables:<br />
Report on the survey, various trade-off analysis following this survey, a technology dossier of the selected electrochemical<br />
systems, breadboard of the electrodes and cells, tests and tests report.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL8 by 2009<br />
Application/Mission: Applicability to all missions (>2010) Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7761<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
T604-03EP<br />
Title: Development of Next Generation GaAs Based Multi-Junction Solar Cells - 2<br />
The development of next generation multi-junction solar cells will facilitate higher power satellites and will enable new<br />
applications, mainly for telecommunications purposes. It will also contribute to an independent European supply of<br />
state-of-the-art multi-junction solar cells to <strong>ESA</strong> and European prime contractors at open market conditions. This activity has<br />
the following main objectives:<br />
1. Development of improved triple junction cells (>30% efficiency) and 4 / 5 junction solar cells, with target >32% efficiency at<br />
beginning of life (>41mW/cm2) and 90% remaining factor at end of life.<br />
2. Development of cheaper, lighter multi-junction cells on alternative substrates. Pre-qualification devices.<br />
Deliverables:<br />
30 samples of triple junction cells (efficiency >30%) and 80 samples of 4 or 5 junction space solar cells with a beginning of life<br />
efficiency greater than that of the best triple junction cells (target >32%), ready for qualification; target end of life performance<br />
of 90% of initial value; 100 samples of multi-junction space solar cells grown on alternative substrates (pre-qualification<br />
samples); data package detailing overall progress towards cost re<strong>du</strong>ction and performance improvement of multi-junction<br />
cells.<br />
Current TRL: TRL2 Target TRL: TRL2/3 Application Need/Date: TRL5 by 2009-2010<br />
Application/Mission: Applicability to all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7761, T-7806<br />
Consistency with Harmonisation<br />
Solar Generators & Solar Cells<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T604-05EP<br />
Title: Development of Next Generation GaAs Based Multi-Junction Solar Cells - 1<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7761<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T604-06EP<br />
Nanotechnology for Space Solar Cells<br />
Nanotechnology could permit a new degree of freedom for solar cell design (as already for other electronic components such<br />
as lasers) <strong>du</strong>e to the possibility to engineer quantum opto-electronic properties that are otherwise fixed for a given material.<br />
This project will develop ideas for new structures which use the structural design of a solar cell to tailor the absorption<br />
properties in an advantageous way, as already underway in Europe mainly for terrestrial applications and elsewhere in NASA<br />
funded projects for space].This study will consist of two phases: the first one will study of the feasibility of at least one design<br />
for incorporation of nanotechnology in solar cells for space applications, especially in relation to the technology to be<br />
developed. This is intended to involve collaboration between universities / research centers to intro<strong>du</strong>ce nanotechnology<br />
concepts and eg. a space cell manufacturer or other partner to contribute relevant experience of space requirements. The<br />
second phase will consist in the manufacturing and testing of demonstration devices to evaluate potential for space.<br />
Deliverables:<br />
Report on feasibility/potential benefit of nanotechnology for space photovoltaics. Demonstration model: 25 cells incorporating<br />
nanotechnology (such as quantum wells or dots, Bragg reflector layers etc.).<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Applicability to all missions Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7806<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Solar Generators & Solar Cells<br />
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<strong>TRP</strong> Reference:<br />
T604-07EP<br />
Efficient Low Cost Power Conversion for Standard and Advanced Fast Digital<br />
Title:<br />
Electronics<br />
In Europe, and in spite of the many development efforts performed so far, it is not possible to procure efficient, low cost<br />
converters as Off-The-Shelf (OTS) items readily available on the market and suitable for space missions.<br />
European users are therefore more and more considering the use of OTS converters from US, where market conditions exist<br />
to enable specialised companies to live on their converter pro<strong>du</strong>cts.<br />
The large commercial or military market-base of such companies allows them to propose OTS converters for space at<br />
competitive prices, when intermediate quality levels are offered (for example, class H hybrids according to MIL-PRF-38534<br />
specification).<br />
The present activity is aimed at establishing the initial steps towards the development and qualification of a European set of<br />
efficient, low cost, readily available OTS converters for standard and advanced digital electronics.<br />
The set of converters shall cover all the required output voltage ranges for digital equipments (very low voltages for advanced<br />
technologies – 2.5V and even 1.8V - and usual 3.3V and 5V for standard technologies).<br />
A couple of power levels (5W, 15W) shall envelope the typical applications required for payload users on board of the<br />
spacecraft, and the input voltage levels will be specified to cope with the regulated or unregulated bus standards around 28V<br />
or 50V.<br />
The initial development steps (to be covered under <strong>TRP</strong>) are the following:<br />
• definition and implementation of an COTS (Commercial Off The Shelf) EEE components policy for the specific application;<br />
• converter design, manufacturing and test (at prototype level);<br />
• basic verification on key performances in environmental conditions ( radiation verification, above all).<br />
The next essential steps to ensure that the final pro<strong>du</strong>ct will be effectively available on the market is manufacturing of<br />
representative QMs, and their qualification by an adequate and thorough test campaign (to be pursued later via a GSTP or<br />
other funding).<br />
Note that this second phase is essential for the success of the initiative.<br />
Important remark: The target markets for these converters are s/c payloads and not essential platform units (like PCU, PDU,<br />
CDMU, RTU, TX, RX).<br />
For essential platform units the proposed approach is deemed still too advanced, and the use of specific converter designs, to<br />
be developed on a case by case basis with space-grade EEE parts is still the preferred option.<br />
Note that European key players do recognise the power supply and conditioning of their essential platform units as a strategic<br />
asset for ensuring overall reliability, and therefore they have specific in-house converter development capabilities.<br />
Deliverables:<br />
• Definition and implementation of an OTS EEE components policy (using COTS) for the specific converter application;<br />
• Set of converter demonstrators showing the suitability of the selected design to cover the range of application.<br />
Current TRL: TRL1 Target TRL: TRL1-2 Application Need/Date: TRL5 by 2008<br />
Application/Mission: Applicability to all missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7811<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T604-08EP<br />
Integrated Current Limiter<br />
Solid state switch devices for bus protection purposes are strongly established in <strong>ESA</strong> missions. However, they are always<br />
implemented in discrete version. Cost and size may sensibly benefit of a integration of this function.<br />
A typical discrete current limiter usually requires typically 6 cm x 6 cm. An integrated solution may be probably implemented<br />
in 3 cm x 2 cm. Thus, current limiters size would be dramatically re<strong>du</strong>ced. S/C Power Distribution function may be re<strong>du</strong>ced<br />
from the 10 double Eurocard mo<strong>du</strong>les required for instance in Herschel and Planck satellites to only 2.<br />
This integration of a recurrent discrete design would also offer cost re<strong>du</strong>ction because the decrease in number of mo<strong>du</strong>les<br />
proportionally re<strong>du</strong>ces recurring MAIT costs. Furthermore, the re<strong>du</strong>ction of number of parts re<strong>du</strong>ces the procurement effort<br />
and overall components price, thus, decreasing furtherly the cost.<br />
Last but not least, re-utillisation of a pro<strong>du</strong>ct repetitively used with success in different missions shall also re<strong>du</strong>ce the<br />
development risks of the Power Distribution function within the spacecraft.<br />
With all this in mind, the objective of this activity should be the development of demonstration samples of a Standard<br />
Integrated Latching Current Limiter having a low recurrent price.<br />
Deliverables:<br />
Technical Notes, Demonstration samples<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
All <strong>ESA</strong> missions, very specially those<br />
Application/Mission: where miniaturisation is key <strong>du</strong>e to mass Contract Duration: 18 months<br />
budget constraints.<br />
SW Clause : - Dossier0 Ref.: T-7807<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Power Management and Distr. Units / Power Management<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T604-10EP<br />
Study of new Power Systems architectures for LEO missions<br />
The availability of new, promising, re-usable and efficient power system architectures are deemed to be very importat to bring<br />
mass/performances/cost improvements for LEO missions. In particular, the optimisation of energy more than power efficiency<br />
is a key factor to have light, performant and cost effective power systems for LEO missions.<br />
The study will concentrate on the revision of new power conversion tecnologies (S3R, S4R, step down MPPT, step up MPPT,<br />
etc) to identify the most suitable power system per class of applications in LEO (fixed/pulsed load; regular, dask/dawn or<br />
specific orbit, etc).<br />
The most promisting concept(s) will be further designed in detail with the explicit aim to get a mo<strong>du</strong>lar/re-usable system per<br />
class of LEO missions.<br />
A scaled demonstrator will be manufactured and tested to illustrate the concept(s).<br />
Deliverables:<br />
Technical Note, Demonstrator<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: LEO missions (not before 2015) Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7814<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Power Management and Distr. Units / Power Management<br />
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6.4 - S/C Environment & Effects<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/EMA-001<br />
Muon Telescope<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EMA-022<br />
Spacecraft Charging & Plasma Interaction Guidelines<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T602-01EM<br />
Solar Energetic Particle Environment modelling<br />
Solar protons with energies of the order of 1 to 100 MeV are generated sporadically at the solar corona, and in the solar wind<br />
by moving interplanetary shocks. They constitute an increasingly critical hazard for the design of interplanetary missions via<br />
their impact on optical components, solar arrays, electronics and humans, and are a significant hazard to Earth-orbiting<br />
missions. This activity will create new engineering models to address future needs, in particular: - ingest new data and to take<br />
into account recent advances in understanding the generation mechanism; enable automatic model update and establish<br />
community consensus; - rather than pro<strong>du</strong>cing only mission-integrated fluence for a given confidence level (for dose, solar<br />
array degradation), models will be designed to pro<strong>du</strong>ce new types of user pro<strong>du</strong>cts, including peak flux statistics, <strong>du</strong>rations of<br />
high flux periods, etc. (suitable for SEU rate and radiation background); - integrate databases of ion species and their fluxes<br />
into tools for SEU and background calculation so that past events and future scenarios can be simulated; - examine (limited)<br />
available data and improve physics-based shock-acceleration models to predict the expected event time profiles at non-Earth<br />
locations (near-Sun, Mercury, Venus, Mars,...) in order to get a realistic model of helio-radial variations to replace the (1/r^2)<br />
“rule of thumb” which leads to possibly over-severe environment specifications.<br />
Deliverables:<br />
Empirical model (solar proton fluence at 1AU) + update/maintaining method. Model extrapolationg + Fluxes model. Improved<br />
dose/SEU models (coupled with empirical). (SW IPR to <strong>ESA</strong> for operational activities (TBC)).<br />
Current TRL: - Target TRL: Prototype Application Need/Date: SW operational by 2008<br />
Application/Mission: Science, HME, EO, Telecom Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-10<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T602-02EM<br />
Radiation Effects on Advanced Technologies: Models and Software Ph.1<br />
This activity will evelop models in several critical areas, including:- Single Event Effects simulation and generic microdosimetry<br />
calculation capabilities for arbitrary materials and for modern complex (i.e. non-parallelepiped) device sensitive volumes. –<br />
Dramatically decrease simulation time for electron-bremsstrahlung total dose estimation in complex geometries by use of<br />
time-reversed Monte Carlo techniques;- New Non-Ionising Energy Loss and total dose simulation tools for future solar cells,<br />
glasses, CCDs, and materials;- Development of interfaces between CAD tools and Monte-Carlo tools- Extend the set of new<br />
Geant4 based models and engineering tools available to European space in<strong>du</strong>stry via the SPENVIS on-line system;- Develop<br />
new electromagnetic and hadronic physics models and other Geant4 kernel capabilities (e.g. geometry)Together, these new<br />
developments are aimed at enabling a clear increase in the use of Geant4 to a broad range of European space engineering<br />
applications.<br />
Deliverables:<br />
New, improved and easy-to-use radiation transport software, physics models, and auxiliary engineering tools and capabilities.<br />
(Open Cource Code / <strong>ESA</strong> IPR).<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational by 2008<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-19<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Radiation Effects on Advanced Technologies: Models and Software Ph.2<br />
This activity will evelop models in several critical areas, including:- Single Event Effects simulation and generic microdosimetry<br />
calculation capabilities for arbitrary materials and for modern complex (i.e. non-parallelepiped) device sensitive volumes. –<br />
Dramatically decrease simulation time for electron-bremsstrahlung total dose estimation in complex geometries by use of<br />
time-reversed Monte Carlo techniques;- New Non-Ionising Energy Loss and total dose simulation tools for future solar cells,<br />
glasses, CCDs, and materials;- Development of interfaces between CAD tools and Monte-Carlo tools- Extend the set of new<br />
Geant4 based models and engineering tools available to European space in<strong>du</strong>stry via the SPENVIS on-line system;- Develop<br />
new electromagnetic and hadronic physics models and other Geant4 kernel capabilities (e.g. geometry)Together, these new<br />
developments are aimed at enabling a clear increase in the use of Geant4 to a broad range of European space engineering<br />
applications.<br />
Deliverables:<br />
New, improved and easy-to-use radiation transport software, physics models, and auxiliary engineering tools and capabilities.<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational by 2008<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-19<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T602-03EM<br />
Development of a predictive discharge numerical model on solar panels<br />
There have been a considerable effort from CNES to elaborate credible mechanisms to explain electrostatic discharges on<br />
solar array. A campaign of laboratory test is currently being performed under EMAGS-2 project lead by <strong>ESA</strong> (Photovoltaic<br />
Generator section). Following this testing sequence, this new activity will consist in the development of a predictive numerical<br />
model to simulate the effects from primary and secondary arcs on various designs solutions (network and cells). This model<br />
can be validated by the laboratory test results. A comparison in between laboratory conditions and real environment conditions<br />
could then be performed. It is foreseen to be carry out this comparison by using the so called SPIS, the <strong>TRP</strong> funded<br />
Spacecraft Plasma Interaction System.<br />
Deliverables:<br />
Proved numerical model. Comparison with test results. Simulation software.<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational by 2008<br />
Application/Mission: EO, Telecom, Navigation Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7564<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T602-04EM<br />
Rapid prototyping toolkit for space environment engineering tools<br />
For space environmental analyses requiring the use of a spacecraft geometrical model <strong>ESA</strong> developed <strong>ESA</strong>BASE as a<br />
general modelling and analysis environment, in the 1980's. Although the original <strong>ESA</strong>BASE is aging and becoming difficult to<br />
maintain and use, the analysis capability is still very important both for <strong>ESA</strong> and the European space in<strong>du</strong>stry. As a means of<br />
investigating future options and problem areas, a small activity is currently developing a version of the important debris<br />
application of <strong>ESA</strong>BASE using modern software tools and methods. The key objectives of work in this area are to work<br />
towards adoption of international standards for data representation and models, harmonisation with related tools and<br />
standards in other disciplines, and use of commercial tools and utilities. This activity will validate and apply similar methods to<br />
those established in the debris development to cover all the other environmental (atomic oxygen, radiation, solar UV,<br />
contamination) applications as well. It will move away from proprietary components and instead use available open source or<br />
COTs software. The result will be a replacement of <strong>ESA</strong>BASE tools in various domains with open source desktop tools.<br />
Deliverables:<br />
A replacement of the <strong>ESA</strong>BASE tools in the various domains with opens source desktop tools.<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational by 2008<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-7765<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Radiation Test Facilities and Engineering Tools (UPDATED)<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T602-05MC<br />
Harmonisation of Thermal and Space Environment Analysis Software and Interfaces -<br />
Title:<br />
Exchange of Thermal Models via STEP-TAS<br />
Following successful mapping and roadmap definition meetings with national delegations and in<strong>du</strong>stry on the topic of<br />
“Harmonisation of thermal and space environment analysis software and interfaces” in 2002, a Steering Board with very good<br />
cross-in<strong>du</strong>stry representation was established in May 2003.<br />
This Steering Board has unanimously adopted the <strong>ESA</strong> proposed harmonised policy for thermal and space environment<br />
analysis software and interfaces which provides a solid basis on which to develop further these engineering tools and<br />
interfaces. More specifically, the Steering Board re-emphasised the need expressed by National Delegations for robust data<br />
exchange for thermal models.<br />
Objectives of the activity are the transfer of the STEP data exchange protocol libraries to Space Thermal Software and its<br />
S/W implementation. Furthermore, the activity will include demonstrations, evaluation and preliminary validation involving end<br />
users and the developers of the Space Thermal S/W. The activity will be led by an independent consultant for the overall<br />
management co-ordination.<br />
Deliverables:<br />
Software<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: SW operational (capability to<br />
exchange data / models<br />
S/W release<br />
among the different tools)<br />
>=2007<br />
Application/Mission: all <strong>ESA</strong> missions Contract Duration: 18 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-7594<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T602-06EM<br />
Title:<br />
Space Weather Warning for Space Systems<br />
The activity will investigate the detailed requirements and technologies to be deployed in an eventual operational "space<br />
weather for spacecraft" system, then perform prototyping. This should include sensor technologies, data analysis<br />
infrastructure (including distributed data centre technologies) and data-model fusion. System elements will be prototyped and<br />
deployed. Innovative techniques for direct observation of the sun, the interplanetary medium, and near-earth conditions will be<br />
investigated. Coupling observations and data resources with physics-based models of the interplanetary medium, disturbance<br />
propagation, and models of the magnetosphere, to predict hazardous conditions will be developed. Conditions will include:<br />
energetic solar particle event (SPE) arrival, magnitude and time-evolution at Earth; SPE's at non-Earth locations (for<br />
interplanetary science missions and Aurora); geomagnetic storm enhancements of the electron radiation belt and; hot plasma<br />
environments. Distributed "virtual" data centre architectures will be developed.<br />
Deliverables:<br />
System design, demonstration software, future development proposals.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: Sw operational by 2008<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-18<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T602-09EE<br />
Title: Investigation and analysis of very high energy accelerators for radiation simulation<br />
Very high energy ion accelerators (E/n ~1GeV) available in Europe will be investigated in detail. Programmes for their<br />
characterization for use in space applications will be prepared and executed, and experiments performed to investigate<br />
energy-related phenomena. Facilities currently used by agencies and in<strong>du</strong>stry pro<strong>du</strong>ce ions of relatively low energy, so that<br />
their ranges in typical components are limited. This is very unlike ions in space whose energies are so high that they can<br />
penetrate at least several cm of material. As a result there are many “range effects” where ions stopping in sensitive volumes<br />
deposit more than expected while others not reaching sensitive volumes do not contribute. Resulting effects calculations<br />
based on such data are incorrect and may explain discrepancies between in-orbit experience and pre-flight estimates. In<br />
addition, future manned programmes and increasing investigation of biological effects necessitates access to such machines.<br />
In addition to the detailed experimental investigation of these effects, detailed modelling of the processes will be undertaken,<br />
and comparisons made with results from “low energy” accelerators). The activity includes: 1. Analysis of existing and required<br />
facilities. 2. Experiments on effects in sub-100nm devices and simulation of beam interactions at sensitive node level. 3.<br />
Establishment and demonstration of new methods of analysis. 4. Development proposals.<br />
Deliverables:<br />
Technical notes. Test set-up's, simulation codes, results of the experimental activity.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: SW operational by 2008<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7637<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Radiation Test Facilities & Engineering Tools<br />
<strong>TRP</strong> Reference: T607-11EE<br />
Title:<br />
Rapid Reverse Monte Carlo and Ion Physics for Dose and SEE<br />
Recent consultations with in<strong>du</strong>stry, the harmonisation process, project applications and results of R&D activities indicate the<br />
need for specific physical attributes in radiation effects simulations In particular, a “reverse” (adjoint) Monte Carlo simulation<br />
for rapid, highly accurate total dose calculations is lacking in Europe and has been identified as a key simulation improvement<br />
capable of dramatically re<strong>du</strong>cing mass and design margins. Likewise the analyses of Single Event Effects (SEE) and<br />
Non-Ionising Energy Loss (NIEL) are becoming increasingly critical for a broad range of mission domains and have also been<br />
identified as priorities for simulation improvement. The underlying physics models utilised in present tools need to be updated<br />
and validated for engineering applications.<br />
This activity will focus on detailed radiation interaction physics modelling, including both theoretical and data-driven<br />
approaches, for incident particles, materials, and technologies typically encountered in a broad range of missions. The<br />
development shall include both prompt interactions (hadronic (~ion) and electromagnetic (e--) processing occurring at the<br />
site of the particle interaction) as well as effects at the semicon<strong>du</strong>ctor level (e.g. charge collection mechanisms). The<br />
resulting software shall be based on Object-Oriented technologies and implemented in the Geant4 particle transport toolkit,<br />
ensuring their availability to in<strong>du</strong>strial tools. Validation of the models shall be carried out by rigorous comparisons to existing or<br />
specially generated experimental accelerator data, other Monte Carlo codes and/or analytical methods.<br />
Deliverables:<br />
New radiation interaction physics models, aimed specifically at shielding and component engineering applications and<br />
implemented in the Geant4 particle transport toolkit<br />
Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Broad range of missions Contract Duration: 24 months (Ph1)<br />
SW Clause : Open Source Code Dossier0 Ref.: T-19; T-7765<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T609-14QC<br />
General Spacecraft Environment Monitor<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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6.5 - Space System Control<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MME-002<br />
Integrated-Optics Laser gyro Technology (IOLG) Ph.2B<br />
Gyros are essential sensors for inertial guidance and control. A new, very interesting gyro configuration is the<br />
Integrated-Optics Laser Gyro (IOLG) as proposed by Politecnico di Bari and U.Glasgow. The IOLG offers many potential<br />
advantages by integrating all the components on a single GaAs substrate. It comprises of a multiple quantum-well (MQW)<br />
microring laser, a coupled output optical waveguide with push-pull electro-optic mo<strong>du</strong>lator, a Y junction and a wide band<br />
photodetector all fabricated on the one GaAs substrate. The objective of the following activity is assessing the feasibility<br />
through breadboarding of an IOLG and test.<br />
Deliverables:<br />
Breadboard<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-01MM<br />
Title:<br />
Novel Optical Gyro Concept<br />
Initial <strong>TRP</strong> conceptual studies and breadboarding activities for an integrated-optical gyro (IOLG) sensor chip, integrating<br />
waveguides, SOA amplifiers, ring resonator, optical isolators, mo<strong>du</strong>lator, etc. with (external) laser diodes have shown the<br />
potential of novel opto-electronics techniques to provide novel gyro concepts of low/medium performance. Building upon this<br />
initial R&D study, the proposed activity intends to further the development effort towards novel gyro concepts for space<br />
applications. The following tasks are envisaged: critical evaluation of the IOLG concept/ initial results, trade-off among<br />
different novel concepts employing optical/photonic technology, e.g. : IOLG, Photonic crystals, quantum interferometry, etc.<br />
This work will be implemented in two phases, the first covering trade-offs among different novel concepts, followed by<br />
breadboarding of the most promising concept(s). The technology readiness level of this activity is TRL 3.<br />
Deliverables:<br />
BreadBoard<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: EO and Science Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7974<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-03ES<br />
Robust LPV Gain Sche<strong>du</strong>ling Techniques for Space Applications<br />
Gain-sche<strong>du</strong>ling is perhaps one of the most popular approaches to non-linear control design and has been widely and<br />
successfully applied in fields ranging from aerospace to process control. The traditional control design proce<strong>du</strong>re consists of<br />
decomposing a non-linear time-varying problem into a number (operating conditions) of linear time invariant sub-problems. To<br />
verify that the closed-loop system behaves as expected and required between the operating conditions, extensive simulations<br />
and analysis are needed. A recent gain sche<strong>du</strong>ling method, so-called Linear Parameter Varying (LPV) technique, address the<br />
issue of system parametrisation and directly offer an optimal solution. As the intermediate step of linearization and stationary<br />
control design is suppressed, the design verification effort is drastically re<strong>du</strong>ced. The aim of the proposed activity is to<br />
evaluate, benchmark and demonstrate the benefits in validation effort of LPV gain sche<strong>du</strong>ling techniques when applied to the<br />
design of robust controllers for uncertain time-varying systems. In addition, robust LPV-based controller design proce<strong>du</strong>res<br />
and tool(s) that interface with in<strong>du</strong>strial requirements will be developed. The expected benefits is a drastic re<strong>du</strong>ction in control<br />
design verification effort for non-linear time-varying systems.<br />
Deliverables:<br />
Robust LPV gain-sche<strong>du</strong>led control design toolbox including benchmark models and <strong>document</strong>ation (technical data package,<br />
summary report and abstract).<br />
Current TRL:<br />
Target TRL: Beta Application Need/Date:<br />
-<br />
version<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-7817<br />
Consistency with Harmonisation<br />
Roadmap: N/A<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-04ES<br />
Title:<br />
Robust Model Predictive Control (MPC) for Space Constrained Systems<br />
Model Predictive Control (MPC) is a widely used and well accepted controller design method in the process in<strong>du</strong>stry. The<br />
most appealing feature of this type of control is its ability to cope with constrained systems. Robust formulation of MPC<br />
problems which take into account model uncertainties are also available, and are subject of intensive current research.<br />
Furthermore, MPC can be combined with other control techniques such as H2/Hinfinity. Finally, the dramatically increasing<br />
available computer power give new interest in such computer intensive techniques as they can easily take into account<br />
actuator limitations, non-linearities or non-stationarity. The aim of the proposed activity is to evaluate, benchmark and<br />
demonstrate the benefits of robust Model Predictive Control on critical space mission scenarios, such as time-bounded<br />
manoeuvres, saturated control and terminal guidance that are difficult to address with classical techniques. In addition,<br />
real-time performance (CPU, memory, etc.) will be assessed, and robust MPC design proce<strong>du</strong>res and tool(s) that interface<br />
with in<strong>du</strong>strial requirements will be developed.<br />
Deliverables:<br />
Robust MPC control design toolbox including benchmark models and <strong>document</strong>ation (technical data package, summary<br />
report, and abstract).<br />
Current TRL:<br />
Target TRL: Beta Application Need/Date:<br />
TRL1<br />
version<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7817<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-10ES<br />
MEMS Rate Sensor<br />
The activity shall design and develop a 3 axis 'low accuracy' (5 deg/hr bias stability) MEMS based rate sensor suitable for use<br />
as a primary sensor on small sats, as an FDIR and acquisition sensor on EO and science missions and as a backup sensor<br />
for Telecoms applications. The unit shall have a target mass of less than 600g and a power consumption of less than 4 watts.<br />
A Demonstrator shall be breaboarded and tested to a level sufficient to demonstrate the packaging concept, performances,<br />
mass and power and to provide confidence in the environmental (vibration, TV and radiation) survivability. The activity may be<br />
continued in an optional program. Preliminary Specifications for the Flight System will be included in this tender.<br />
Deliverables:<br />
Breaboard and reports.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 by 2008<br />
Application/Mission: all missions Contract Duration: 15 months<br />
SW Clause : - Dossier0 Ref.: T-7818<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-11ES<br />
Title:<br />
Attitude Determination Tailored to Multiple Heads Star Tracker<br />
Star tracker partial or total occultation or blinding by the Earth or the Sun can prevent stellar information from being available.<br />
The MHST is minded as a unit where a unique computer can manage data from different Optical Heads (OH), providing better<br />
attitude restitution through sensor fusion and managing occultation. It follows that the use of such a unit leads to a design of<br />
an innovative FDIR at unit and AOCS subsystem level and requires a greater interaction between AOCS designer and unit<br />
supplier to achieve an optimal AOCS design for a given mission. The proposed activity shall support initial development effort<br />
at unit and AOCS level prior practical implementation within future missions. Constraints will be identified and performance<br />
analysed and validated, including the case of a gyroless AOCS.<br />
Deliverables:<br />
Detailed <strong>document</strong>ation and SW model. (Open Source Code at system level / Operational SW at subsystem level)<br />
Current TRL: TRL1 Target TRL: Prototype Application Need/Date: SW operational >=2007<br />
Application/Mission: EO and Science Contract Duration: 12 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7815<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-13ES<br />
Modern Control Techniques Applied to Satellite FDIR<br />
Although the currently implemented algorithms are responding rather adequately to large class of the mission requirements,<br />
advanced new FDIR techniques recently intro<strong>du</strong>ced through modern control theory need to be further explored. From a cost<br />
perspective it is not manageable to have everywhere fault re<strong>du</strong>ndant hardware and complex and costly ground operation<br />
intervention. Therefore it is more efficient to study the analytic model based on-line fault monitoring techniques that use<br />
measured data fed into a detection filter responding with a threshold signal in the face system anomalies.<br />
The design of such FDI filters can be done using estimation and filtering techniques such as Kalman filters. In many cases<br />
resi<strong>du</strong>al generation becomes problematic in off-nominal conditions leading to a high occurrence of false alarms which can lead<br />
to unnecessary complex operational interventions.<br />
Therefore robust filtering techniques originating from the as H-infinity, mu-, LMI as well as LPV theories provide a well founded<br />
framework for the development of future FDIR systems to better respond to unforeseen situations. The development of FDI<br />
filters using these methods need to be investigated with the overall objective of enhancing the detection and isolation strategy<br />
in terms of robustness.<br />
Another important field that needs to be investigated is the interaction and cascading of multiple failure modes and models.<br />
The proposed activity shall further include the implementation of selected algorithms. The evaluation of the associated<br />
performances and robustness shall also be combined with trade-off analysis con<strong>du</strong>cted within common and unambiguous<br />
testing scenario. Relevant test cases worth to be investigated are Lisa Pathfinder, Lisa and Gaia, agile and accuracy pointing<br />
satellites, Darwin formation flying facing thruster failures. Under that context, the definition of standardised benchmark<br />
developed typically under Matlab and Stateflow environment is also expected.<br />
Deliverables:<br />
Documentation and software.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2009<br />
Application/Mission: EO and Science Contract Duration: 18 months<br />
SW Clause : Open Source Code Dossier0 Ref.: T-7821<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-30EC<br />
Title:<br />
Sensor on a Chip Feasibility study and Avionics Evolution<br />
The technological feasibility of pro<strong>du</strong>cing an entire sensor on a chip (i.e. optics, detector, processing and digital interface) shall<br />
be investigated using digital sun sensor, star tracker and navigation or descent and landing cameras as examples. The<br />
feasibility investigation shall cover the integration of imaging, processing and data interface functions on the same silicon chip,<br />
the pro<strong>du</strong>ction and performance of useable optics with MEMS technology (e.g. wafer stacking and bonding for 3-D integration<br />
of MEMS optical systems with the electrical functions) and the integration of such an assembly with power conditioning<br />
electronics within a hybrid. Key technologies will be demonstrated by pro<strong>du</strong>ction and test of a dedicated prototype (e.g. of an<br />
optical system).<br />
The system aspects surrounding the use in space of a sensor on a chip concept shall be investigated at both sensor unit and<br />
system level. These investigations shall cover the packaging of the 'sensor on chip', the thermal implications of such a<br />
concept for externally mounted sensors, power supply options, mounting and alignment problems and data interface methods<br />
and techniques.<br />
With the results of the technology investigations, unit level studies and system impact studies, a development plan shall be<br />
written for AOCS sensors on a chip covering sun sensor, star tracker and navigation camera and descent and landing camera<br />
applications, giving realistic target requirements and highlighting all critical areas of outstanding technology devlopment.<br />
Deliverables:<br />
Demonstration model.<br />
Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL5 by 2012<br />
Application/Mission: All missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7799<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-36EC<br />
Future technology studies for APS Star Trackers<br />
The contractor shall investigate potential new star trackers technologies that may be of use in the future to further re<strong>du</strong>ce the<br />
cost while improving the robustness (dynamic conditions, straylight/blinding, false stars and radiation) and functionalities<br />
(sensing of moon or earth/asteroid/planet position for example, direct entry to tracking). These shall include the mandatory<br />
consideration of LCMS APS detector by Cypress (Fillfactory) -designed specifically for this purpose-, baffle construction<br />
materials, plastic lenses, black coatings, alternative construction techniques, single chip electronics (all processing in the<br />
same ASIC/FPGA), and wireless communication. In addition, the contractor shall be expected to propose further new<br />
technologies themselves. Technical evaluations shall be performed on each technology considered and all promising<br />
technologies breadboarded for further, more detailed, evaluation and, where appropriate, development plans to bring the<br />
technology to the correct maturity level shall be drawn up. The emphasis shall be on pro<strong>du</strong>ction cost lowering from a<br />
continued re<strong>du</strong>ction of the number of components, an easing of assembly, automated testing and cheaper construction<br />
techniques.<br />
Deliverables:<br />
Breadboards.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: All missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7815<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-38EC<br />
Enhanced CCD Star Tracker<br />
Since the intro<strong>du</strong>ction of the Autonomous Star Trackers in the 1990s, their popularity and use on space missions has steadily<br />
increased until today were these units are used on all classes of mission and are becoming the sensor of choice for almost all<br />
missions.<br />
The European space in<strong>du</strong>stry has been at the forefront of this technology development, indeed in 2000/2001 there were<br />
nearly 15 European companies developing or selling star trackers. This amount of competition was unsustainable and so, at a<br />
harmonisation meeting in 2001, it was decided to no longer support the development of CCD based star trackers and<br />
concentrate instead on targeted developments to pro<strong>du</strong>ce the next generation of star trackers based on APS detectors, these<br />
having the potential to allow lighter, more compact and cheaper Star Trackers that simultaneously offered higher robustness.<br />
In<strong>du</strong>stry was left to support itself for the CCD star trackers. This policy had the desired effect of re<strong>du</strong>cing the number of<br />
European Star Tracker manufacturers dramatically while simultaneously forcing manufacturers to improve their units and<br />
re<strong>du</strong>ce prices. Today there are 5 star tracker suppliers in Europe, each of whom have survived by being highly competitive on<br />
the world stage. With a manageable number of suppliers, a large proportion of each of these companies business now coming<br />
from outside Europe and there still being an expected overlap of 2 to 4 years between CCD based and APS based star<br />
tracker supply it is now time to resume providing support to maintain and improve the existing CCD based pro<strong>du</strong>ct lines.<br />
The Terma HE-5AS STR has been selected for Cryosat, Aeolus and the LPF missions. Following the loss of Cryosat at launch<br />
it is also expected to fly on Cryosat 2. Work performed now to secure the STR and improve its robustness, reliability and<br />
qualification status will therefore have a near term beneficial effect on several <strong>ESA</strong> missions.<br />
This policy was clearly expressed in <strong>ESA</strong>/IPC(2005)70 rev.1, calling for pro<strong>du</strong>ct improvements of CCD Star Tracker , mainly<br />
for recurring platforms. According to the outcomes of the 2005 Harmonisation Roadmap on AOCS Sensors and Actuators, the<br />
present activity aims at: ensuring the availability of the HE-5AS to <strong>ESA</strong> projects for at least the next 3 years; improving the<br />
robustness and ease of use of the HE-5AS within the scope of the existing electrical design limitations; improving the<br />
straylight and thermal design and the understanding of their interactions and dependencies on the s/c system and orbital<br />
environment. This will result in the following main three tasks: 1. Software improvements for Robustness and Reliability; 2.<br />
Component obsolescence and Europeanisation; 3. System level analysis and improvements. This measure is implemented in<br />
line with IPC(2005)30, rev. 1 (Formal review of the geographical distribution of contracts), calling for a DG's additional effort to<br />
improve the geographical return of certain countries, including Denmark.<br />
Deliverables:<br />
In-flight data analysis report; design improvements and trade off report; improved SW design report; SW Test<br />
plan/proce<strong>du</strong>res/report<br />
Current TRL:<br />
TRL3-4 Target TRL: Application Need/Date: TRL8 (in-flight demo on<br />
TRL5-6<br />
Cryosat-2) by 2009<br />
Application/Mission: All missions Contract Duration: 18 months<br />
T-25, T26, T-27, T-29, T-30,<br />
SW Clause : - Dossier0 Ref.:<br />
T-33, T-34, T-965<br />
Consistency with Harmonisation<br />
Conclusions: <strong>ESA</strong>/IPC(2005)70 rev.1<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-41EC<br />
System study to define European accelerometer development<br />
A number of space applications, such launchers, transfer vehicles, re-entry vehicles, landers, rovers, not only require angular<br />
rate, but also acceleration measurements. These applications require an Inertial Measurement Unit (IMU), combining gyro and<br />
accelerometers measurements, in order to provide these data to the spacecraft and rely today on US accelerometers.<br />
The development of a European accelerometer is highly desirable to guarantee non-dependence and better master IMU<br />
design and performance. A candidate for this accelerometer is MEMS technology, which now reached the level of maturity<br />
and reliability that makes it eligible for space applications.<br />
The proposed activity shall cover the first step before initiating such a development, which is to identify the accelerometer<br />
needs for space applications, both from a technical feasability and a market perspective. This technical feasability study shall<br />
be supported by simulations.<br />
The following tasks are expected:<br />
- Identification of accelerometer needs<br />
- Review of accelerometer market and trends<br />
- IMU performance study<br />
- Accelerometer preliminary specification, design and development plan<br />
The activity shall thus lead to select the performance grade of European accelerometer to be developed in priority, assess the<br />
feasibility with MEMS technology or another technology, and provide all inputs to make decision towards the development<br />
step.<br />
Deliverables:<br />
Accelerometer need for Space Applications, Review of accelerometer market and trends, IMU Performance Study and IMU<br />
algorithms, Simulation test plan and results, Accelerometer Technical Specification for Space Applications, Accelerometer<br />
Preliminary Design and Development Plan.<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2015<br />
Exploration (landers, re-entry vehicles,<br />
Application/Mission: Contract Duration: 12 months<br />
rovers,..)<br />
SW Clause : - Dossier0 Ref.: T-8006<br />
Consistency with Harmonisation<br />
AOCS Sensors, AOCS Actuators<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
6.6 - RF Payload System<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
ETP-029<br />
O/B SAR Calibration<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: ETT-059<br />
Title:<br />
Neural networks for radionavigation<br />
The objectives of this activity are to assess the use of neural networks for multipath mitigation, (building on previous <strong>ESA</strong><br />
activities and on available published results), select and propose a specific method/algorithm particularly suitable for use in<br />
conjunction with receivers used for positioning and attitude determination of spacecraft (limited, for the time being, to satellites<br />
in LEO and MEO orbits), and also to validate the approach by implementing it within a software breadboard and operating<br />
with real data collected from a selected source.<br />
Deliverables:<br />
SW breadboard<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008-2009<br />
Application/Mission: Navigation systems Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7822<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-14ET<br />
Frequency Flexible Synthesizer Breadboard suitable for O/B TTC<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Frequency Flexible Synthesizer Breadboard suitable for O/B TTC: additional work<br />
The overall objective of this activity is to analyse, design and breadboard a Frequency Flexible Synthesiser for space<br />
application. The S-band TT&C transponders for Near Earth applications represent the main target, but it can be suitable also<br />
for other applications for instance the X-band TT&C Transponders and the downlink Telemetry Transmitters.The Frequency<br />
Flexible Synthesiser shall allow programming the transponder for different RF channels. This can be applied on ground<br />
(before launch), but using a proper command in-flight as well. In-flight frequency agility becomes very useful in particular for<br />
spacecraft constellations, multiple launch solutions (to control in frequency diversity several spacecrafts <strong>du</strong>ring LEOP phase)<br />
and for secure link applications. This activity shall include the following main technical phases: architectural definition of the<br />
overall unit with particular emphasis on the frequency plan issues; design, breadboarding and testing of the frequency<br />
synthesiser; and design development plan (up to the flight model) including all the indications in terms of flight technologies,<br />
risk, sche<strong>du</strong>le and costs.<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-29ET<br />
Telecommand & Telemetry System Security<br />
This design study will include the following areas:<br />
1. Identification and evaluation of threats and vulnerabilities on current <strong>ESA</strong> Spacecraft Telecommand and Telemetry systems<br />
with an end-to-end perspective but with particular emphasis on the Space link and considering the particulars of various <strong>ESA</strong><br />
missions, e.g. Science, Earth Observation, Manned Space flight, Navigation, Telecommunications.<br />
2. Exploration and definition of technical concepts for security measures at the relevant CCSDS protocol layers to guarantee<br />
adequate levels of availability, authentication, confidentiality, integrity and non-repudiation; particular emphasis shall be given<br />
to: physical and coding layers where current <strong>ESA</strong>/ECSS standards make no provision for Security and denial-of-service<br />
(jamming) attacks or traffic analysis are a possibility; application, packet, segment and transfer layers for the definition of<br />
authentication and encryption protocols where generic concepts have been <strong>document</strong>ed by CCSDS but not standardised;<br />
particular implementations performed by <strong>ESA</strong> and other Agencies but either outdated or constrained by the particular mission<br />
and therefore, inadequate for future missions; Consideration of Operational aspects, e.g. key management; Consideration of<br />
Ground Networking aspects, e.g. outsourcing.<br />
3. Selection and detailed study for a case-study mission, e.g. Earth Observation.<br />
4. Derivation of security requirements for equipments and facilities on both Space and Ground Segments.<br />
Deliverables:<br />
Technical Notes<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2009<br />
Application/Mission: all programs Contract Duration: 15 months<br />
SW Clause : - Dossier0 Ref.: T-7827<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-31QC<br />
Title:<br />
Linearity Assessement of GaN Technology<br />
GaN offers the potential for realising state of art power performance. Previous <strong>ESA</strong> work programmes have shown that there<br />
is a requirement to investigate novel device structures to further enhance transistor performance. The aim of this activity is to<br />
optimise the GaN transistor structure (both physically and from a materials growth perspective) to achieve higher power<br />
performance through the intro<strong>du</strong>ction of device architectures known to enhance performance such as field plates, double<br />
hetero-junction channels, recess structures, graded channel doping and new vertical transistor structures. In particular, efforts<br />
will be undertaken to investigate the device and technology trade-off’s required to achieve simultaneous high linearity and high<br />
power added efficiency performance, along with undertaking an assessment of the intro<strong>du</strong>ction of the proposed techniques for<br />
improvement of device reliability and manufacturability. This work is an important requirement for future multi-carrier<br />
telecommunications transponders and if successful will allow world class device performance with increased power added<br />
efficiency and linear output power to be achieved compared with GaAs pHEMT technology.<br />
Deliverables:<br />
Technical notes, device samples, technology exploitation plan.<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010<br />
Improved performance power transistors<br />
Application/Mission: for use in EO, Telecomms, Navigation Contract Duration: 24 months<br />
and Science payloads<br />
SW Clause : - Dossier0 Ref.: T-7737<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T603-32ET<br />
Power/Efficiency flexibility of spaceborne SSPA using Doherty scheme associated to a<br />
Title:<br />
linearizer<br />
The Doherty configuration is an advanced design concept of SSPA which can provide instantaneous flat efficiency for a wide<br />
range of input / power range. Very interesting results have been obtained for the base station market where extreme<br />
requirements for linearity/power and efficiency are rewarded. This activity is aiming at demonstrating the applicability of this<br />
concept to spaceborne applications by using the most advanced semicon<strong>du</strong>ctor technologies allowing to focus on very high<br />
constant efficiency. The linearity performance in a range of 3 to 6dB of output power flexibility will represent a key point, and<br />
linearization schemes will be addressed to assure sufficient performance.<br />
Deliverables:<br />
RF amplifiers demonstrators. Standard design <strong>document</strong>ation. Test reports. Associated linearization scheme. Standard design<br />
<strong>document</strong>ation. Test reports.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Telecom Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7825<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-33ET<br />
Title:<br />
Solid State Isolators based on GaN technology<br />
This activity shall first concentrate on identifying ways to develop RF/microwave high power isolators based on solid state<br />
semicon<strong>du</strong>ctor GaN technology. In a second part, the demonstration of feasibility of isolators for space borne applications will<br />
be provided by designing and testing high power isolators aiming at shrinking both size/volume and mass of current ferrite<br />
based isolators used in SSPA equipments.<br />
Deliverables:<br />
Isolator breadboard. Design <strong>document</strong>ation. Test reports.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2012<br />
Application/Mission: Telecom, EO, Navigation Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-37ET<br />
Future Multipurpose TT&C Systems & Techniques<br />
The objective of this activity is to investigate, analyse and propose new TT&C Communication Systems looking to the overall<br />
end-to-end perspective for a broad range of possible missions (e.g. from Near Earth to Deep Space). The target is to devise a<br />
flexible tool-kit of solutions for both the on-board and ground system which can be embedded in highly reconfigurable<br />
hardware platform to adapt to the different mission needs. This approach will avoid the use of expensive ad-hoc solutions to<br />
cope with the different missions and will be leveraging on the advances in signal processing techniques and technologies.<br />
Stemming from the requirements envisaged for future TT&C applications (and for the different application fields: Science,<br />
Earth Observation, Navigation and Telecommunication), this activity shall investigate a flexible yet robust solution for TT&C<br />
tackling aspects such as: spectrum congestion (interference, spectral efficiency, frequency reuse...), on-board power<br />
efficiency (nonlinearity countermeasures), link security, mission adaptability etc....<br />
Deliverables:<br />
Analysis of curent/future application scenarios/req. Broad review of possible comm. link + ranging approaches. Identification<br />
of ref. scenarios, overall end-to-end perform. analysis + trade-off. Proposed solution benchmarking current approach.<br />
Current TRL: - Target TRL: TRL1-2 Application Need/Date: TRL5 by 2015<br />
Application/Mission: All missions Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7749<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-39ET<br />
Title:<br />
Design and Synthesis of a New Class of Receiver Filters<br />
With the increasing complexity of satellite payloads there is increased demand of miniaturized high performance receiver<br />
filters. This includes waveguide and planar filters. Current synthesis techniques assume close to lossless (high Q) networks<br />
which forces the filter to be reflective. If this restriction is removed a new degree of freedom is achieved and very high<br />
performance filter transfer functions can be acomplised utilising very low Q resonators. Initial estimations show that the for<br />
same size significant improved flatness and selectivity can be achieved over state of the art predistorted topologies.<br />
Deliverables:<br />
Circuit design tool and breadboard demonstrators<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL6 by 2011<br />
Application/Mission: All missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7908, T-7918<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
Page 162 of 227
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Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T603-40ET<br />
Evaluation and validation of electromagnetic software, test facilities and test standards<br />
Title:<br />
in Europe to predict and test RF breakdown and passive intermo<strong>du</strong>lation (PIM)<br />
This activity shall start with a survey among the European Space In<strong>du</strong>stry to identify the European needs in terms of<br />
prediction/simulation tools to avoid RF breakdown and PIM in space hardware. The next step of the activity is to propose a<br />
number of existing and available software packages best matching these requirements and recommend one of them as<br />
baseline in Europe for future software developments in the field. The selection shall be done comparing prediction data using<br />
the proposed packages with test results on a number of RF passive devices defined <strong>du</strong>ring the first phase of the study.<br />
To achieve this, the contractor shall also identify test facilities in Europe technically capable to perform high power RF tests<br />
(Power handling, Multipactor and Corona) and passive intermo<strong>du</strong>lation (PIM) on space hardware. A number of waveguide test<br />
samples shall be pro<strong>du</strong>ced and carried to the different test sites for the evaluation of their facilities and test proce<strong>du</strong>res. This<br />
activity has been proposed in the frame of the “power RF measurements” <strong>document</strong>, presented by <strong>ESA</strong> <strong>du</strong>ring the<br />
Harmonization meetings in 2004.<br />
Deliverables:<br />
Golden test samples for each frequency band. Documentation.<br />
Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5 by 2012<br />
Application/Mission: All missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7829<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Microwave Power Breakdown Modelling and Characterisation<br />
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6.7 - Electromagnetics Technology<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/EEA-001<br />
Quasi Optical Modelling<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/EEE-001<br />
Development of low frequency probes<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/EEE-002<br />
Instrumentation for injecting current shaped waveforms<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EEE-006<br />
Novel Techniques For General Antenna Characterisation In The Time Domain<br />
Beside frequency domain measurements allowing characterizing the device under test in its operational frequency domain,<br />
time domain measurements techniques are well known to provide additional information on the mismatches seen by a signal<br />
propagating in a guided circuit. The time domain performances dealing with large frequency bandwidth, this technique<br />
provides more qualitative measurements well suited for a diagnostic purpose.<br />
This activity deals with time domain measurement techniques to perform fast antenna radiation diagnostic. Time domain<br />
allows having in one acquisition a full signature of the antenna behavior which can be compared at different stages of<br />
environmental test sequence to identify potential hardware damage. This technique is particularly well suited as time gating<br />
allow rejecting parasitic reflections of the radiated signal and make possible measurements in reverberant situation (just<br />
before or after a Thermal vacuum test or a vibration test as compared to an ideal situation in an anechoic chamber). Re<strong>du</strong>cing<br />
test time and making possible in-situ measurements is of particular relevance for all kind of antennas used for Earth<br />
Observation, telecommunication and science. The interest is reinforced when multiple beams are required.<br />
The activity will address theoretical aspects together with implementation constraints to end-up with a demonstration phase to<br />
be performed on an existing antenna.<br />
Deliverables:<br />
Technical note on time domain interest for radiative measurements.<br />
Test proce<strong>du</strong>re<br />
Test report.<br />
Evaluation report on time domain for radiative measurements<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: SW operational by 2008<br />
Application/Mission: All missions with complex antennas Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-52<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: EEE-008<br />
Title:<br />
Spacecraft EMI control in the presence of composite materials<br />
Traditionally spacecraft construction has relied on metal or metal honeycomb structures that provide good shielding behaviour.<br />
The future use of composite materials will not have such performance from an Electro-Magnetic Compatibility (EMC) point of<br />
view and the consequences on the EMC performance of the system will have to be carefully evaluated in light of the actual<br />
performance of the composite material. The objective of this activity is to provide a characterisation of the shielding<br />
performance and the transfer impedance of target materials, develop measurement techniques, and develop necessary<br />
analytical tools for EMC performance evaluation.<br />
Deliverables:<br />
Technical note (characterisation of shielding performance and transfer impedance of target materials; development of<br />
measurement techniques). Analytical tools for EMC performance evaluation.<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: SW operational by 2008<br />
Application/Mission: All missions with complex antennas Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-53<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
ETM-192 / T-M-QCT-06<br />
Design of photonic crystals front-end (Photonic crystals: Material selection and<br />
Title:<br />
fabrication)<br />
Photonic Band Gap technology is a breakthrough, mainly <strong>du</strong>e to their ability to guide and control efficiently electromagnetic<br />
waves. As most fundamental components shall be soon available in PBG technology, a fully integrated receiver incorporating<br />
antenna, mixer, waveguides, LO injection and filtering in one unit could be developed in order to take full advantage of this<br />
technology. True integration of passive and active components can now begin to materialize using PBG technology leading<br />
towards the development of a complete system.<br />
In parallel, a PBG component in an ideal concept would be fully dynamic, reconfigurable and multifunctional and the<br />
association of PBG with other enabling technologies such as MST (Micro-Systems Technologies) and more specifically RF<br />
MEMS may allow completely novel EBG concepts and designs. Such a concept is clearly visionary, but the combination of RF<br />
MEMS with novel periodic structures such as PBG my allow prototyping (and probably patenting) innovative functional<br />
concepts to demonstrate adjustability of electromagnetic crystals. This would represent a fundamental change in the way<br />
systems are being designed today.<br />
Deliverables:<br />
Design <strong>document</strong>ation.<br />
Current TRL: TRL1 Target TRL: TRL1 Application Need/Date: TRL4 by 2012<br />
Application/Mission: Imaging Instruments EO / SCI Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-47<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-27EE<br />
Title:<br />
Secured link for TT&C antennas design phase<br />
This activity deals with the design of antennas for secure TT&C links using adaptive (including switching) antenna techniques.<br />
The activity shall consider identification of likely threat scenarios, trade-offs of adaptive antenna concepts, architectures and<br />
design, ground segment and other infrastructure impacts/requirements, interferer location techniques and adaptive antenna<br />
control including software and hardware requirements. The output of this activity shall be the design of the adaptive antenna<br />
system(s) together with analyses to investigate the antenna expected performance. Development plan for future hardware<br />
development.<br />
Deliverables:<br />
Adaptive antenna system(s) design and performances analysis. Future HW development plan.<br />
Current TRL: TRL1 Target TRL: TRL1-2 Application Need/Date: TRL3 by 2008<br />
Application/Mission: EO, Telecom Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7827<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T603-28EE<br />
RCS Quiet Zone Characterization at Millimetre Wavelengths<br />
The technique has been used at ESTEC from some time and has been verified against the traditional and more cumbersome<br />
technique. What is not known is how far up in frequency the RCS technique is applicable with today's technology. While radar<br />
system are known to exist at up to 100 GHz, can the present "traditional" mode of RCS quiet zone determination be applied<br />
The question of the practical limit must be addressed in addition to the question of can a similar technique be used at higher<br />
millimetre wavelength frequencies. The application of innovative thinking is required here to be able to verify range<br />
performance where mechanism and mechanical tolerances are in the same order of magnitude as the electrical wavelength.<br />
It should be noted that in the near future the ESTEC CPTR will increase its range of operation to 100 GHz while the smaller<br />
CATR will operate up to 300 GHz, in line with present and planned Science and Earth Observation missions as well as<br />
potential use in QV band telecommunications.<br />
Deliverables:<br />
Technical note, including the way forward to characterizing antenna test facility quiet zone quality.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL3 by 2008<br />
Application/Mission: EO, Science Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T605-01EE<br />
Title:<br />
Advanced System Level Con<strong>du</strong>cted Emission Analysis and Simulation for EMC<br />
The scope of this activity is to generate a high fidelity system noise model, based on time domain equipment measurements in<br />
both differential and common mode. The exploitation of time domain measurements will improve the results of previous similar<br />
activities, reliant on frequency domain data, where the phase information was not accounted for by definition. The system<br />
complexity will be managed by breaking down of the relevant elements at the various degrees of detail available. The<br />
equivalent noise model shall encompass several features: treatment of shielded and unshielded Non Uniform Multi-con<strong>du</strong>ctor<br />
Transmission Lines; non-linear Components; statistical treatment of the system's uncertainties; and Signal Processing<br />
capabilities addressing noise, mo<strong>du</strong>lations and Power Spectral Density. The system noise model will be demonstrated against<br />
measurements on selected case studies and shall prove the ability to handle any relevant con<strong>du</strong>cted emission and<br />
susceptibility.<br />
Deliverables:<br />
Technical note. System noise model.<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational by 2008<br />
Application/Mission: all missions Contract Duration: 18 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-50<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T605-13EE<br />
Advanced System Level Radiated Noise Analysis and Simulation for EMC<br />
The objective of this activity is to create a numerical tool to simulate radiated electromagnetic field in low Q cavities and<br />
examine radiated susceptibility at unit/subsystem and system level by means of hybrid methods (full wave solvers and<br />
transmission line theory) in time and/or frequency domain. Emphasis shall be given to the representation of the<br />
electromagnetic field where the interference actually occurs, i.e. inside the spacecraft.The following features will be examined:<br />
the randomness of the system, i.e. random field from sources in a closed environment, will be treated with the stochastic<br />
treatment of Maxwell equations; characterisation of the field-to-wire-coupling onto a non-uniform multi-con<strong>du</strong>ctor transmission<br />
line. In order to account for the uncertainties of any complex system that lead to severe fluctuations of the electromagnetic<br />
coupling, a probabilistic approach shall be implemented. The system noise model will be validated against measurements on<br />
selected case studies.<br />
Deliverables:<br />
Technical report, test mock-up and demonstration SW macros<br />
Current TRL: - Target TRL: S/W release Application Need/Date: SW operational by 2008<br />
Application/Mission: all missions Contract Duration: 18 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-50<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T607-10EE<br />
Title: European Antenna Modelling Component Library - Step 2<br />
Following the successful activity on the European Antenna Modelling Library for Telecommunication applications, this activity<br />
will to continue along the path established by extending the Library to cover new requirements of by Earth Observation,<br />
Science and Telecommunication missions. Typical needs include: refinement of reflector antenna analysis tools (for very high<br />
frequency and quasi-optics instruments), innovative methods for array design (for SAR's), fast parametric modelling of small<br />
antennas (to improve speed and accuracy) and improvement of antenna interaction models (distributed antennas, out-of-band<br />
response), adaptation of modelling tools for the use as diagnostic means in AIT/AIV campaign. Furthermore, in order to reach<br />
these objective within the multi-tool environment of the Library the activity will also further consolidate the Electromagnetic<br />
Data Exchange standard.<br />
Further steps are foreseen to cover further requirements of the different type of missions not compatible with the current<br />
budget allocation and to further consolidate the most innovative developments.<br />
Electromagnetic modelling tools are a key factor in the timely and cost effective development of satellite antennas. The<br />
availability of well-established and validated tools has been proven to re<strong>du</strong>ce costs and time to delivery by as much as 30%.<br />
Dedicated electromagnetic modelling tools are absolutely necessary for the successful development of European space<br />
antenna technology. Yet the expenditure in this area (about 5M over the past 10 years) has been small compared to the costs<br />
for breadboarding and mock-up testing of antennas on even a single satellite, and the potential for improvement has been<br />
exploited in a very limited way significantly re<strong>du</strong>cing the benefit for European Space In<strong>du</strong>stry.<br />
With direct relevance to Dossier 0 requirements, this proposal was elaborated and justified within the R&D dossier on Antenna<br />
Modelling and Tools Validation together with experts from user directorates who have approved and supported it as relevant<br />
and important for their future programmes. This action also fits the objectives of the reflector antenna harmonisation in the<br />
Telecom area.<br />
Deliverables:<br />
New antenna analysis mo<strong>du</strong>les for the European Antenna Modelling Library, using innovative techniques in advanced space<br />
antenna design software tools<br />
Current TRL:<br />
Target TRL: S/W Application Need/Date: SW mo<strong>du</strong>les operational by<br />
-<br />
mo<strong>du</strong>les<br />
2008-2009<br />
release<br />
All missions using antennas (reflector,<br />
Application/Mission: Contract Duration: 12 months<br />
arrays, TT&C and others)<br />
SW Clause : Operational SW Dossier0 Ref.: T-48<br />
Consistency with Harmonisation<br />
Telecommunication Antennas Reflectors<br />
Roadmap and Conclusions:<br />
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6.8 - System Design & Verification<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
EMM-004<br />
Virtual spacecraft design (Ph.1&2)<br />
The objective is to develop and apply the virtual design technology in the context of the spacecraft development process with<br />
the aim of shortening it and rendering it more cost-effective, facilitating the control of costs and risks.<br />
The approach is to develop a digital or “virtual” model of the spacecraft already in early phase B to support the specification<br />
and definition activities, and to evolve it to support design, AIT and operations phases. The programme of work shall<br />
concentrate on specific aspects of the development process, where experience shows substantial resources and risks are<br />
involved and where the virtual model technology can provide significant added value. Collaborative aspects shall be<br />
considered. An area of focus will be the AIT process, and its links to both the detailed design and the mission operation<br />
phases.<br />
These activities will be implemented in three steps: definition, implementation and demonstration.<br />
This innovative approach is required to increase the cost-effectiveness of the development process, because it helps<br />
optimising the design at system level, increasing the coherence between analysis, design, testing and operations, and<br />
contributes to the re<strong>du</strong>ction of the number of design iteration loops, test models and testing. In particular, improvements are<br />
expected in the following areas:<br />
• Design trade-offs at system level<br />
• Analysis of system operability issues<br />
• Assessment of engineering margins<br />
• Coherence between analysis and testing<br />
• Preparation and execution of AIT<br />
• Transition from AIT to operations<br />
This is necessary to be able to cope with the ever-increasing complexity of space missions under tight resource and time<br />
constraints and to boost European in<strong>du</strong>strial competitiveness in the global market.<br />
The innovative aspect consists in the way that the whole project is conceived, in a collaborative perspective, using digital<br />
models of the system as integral part of the design and verifications process, in full coherence with the use of hardware<br />
models, thereby optimising cost and sche<strong>du</strong>le, as well in the way for the involved parties (<strong>ESA</strong>, prime and subcontractors) to<br />
interact with each other.<br />
The following steps are foreseen:<br />
• Definition of an advanced process based on Virtual design technology<br />
• Procure and deploy the necessary collaborative tools and applications covering design and AIT phases for multi-partners<br />
projects, with particular emphasis on:<br />
- Model/Simulation-Based design<br />
- Virtual Mock-Up<br />
- Virtual AIT<br />
• Demonstrate the benefits and added value of the results by applying the approach in real project(s).<br />
Deliverables:<br />
VSD process definition; functional simulator and digital mock-up and associated <strong>document</strong>ation, test proce<strong>du</strong>res; lessons<br />
learnt and recommendations to projects. (Open source code to be delivered in agreement with GCC clause 42.4)<br />
Current TRL:<br />
-<br />
Target TRL:<br />
Project<br />
demonstrat<br />
ed in real<br />
project<br />
Application Need/Date:<br />
Application/Mission: All satellite projects Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7863<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
SW process operational<br />
>=2008<br />
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<strong>TRP</strong> Reference:<br />
T504-15SR<br />
Technology reference and proof of concept for a space based Automated Identification<br />
Title:<br />
System for maritime security<br />
The universal shipborne Automatic Identification System has been recently intro<strong>du</strong>ced by the IMO as a system for enhancing<br />
the safety of marine traffic at sea. Transmitters onboard the ships send signals which are received by other ships and<br />
onshore. The proposed activity is a technology reference and proof-of concept action aimed at analysing the feasibility of a<br />
space based system to collect the signals and thereby monitor ship traffic.<br />
The activity includes;<br />
• The analysis of the transmitted signal and its characteristics a range of orbit altitudes.<br />
• The analysis of the signal environment at satellite altitude for several conditions of ship traffic (number and relative location<br />
of transmitting ships).<br />
• The definition of satellite receiving systems and the establishment of performance models for quick trade-off a receiving<br />
system level and for insertion in the end-to-end performance simulator.<br />
• The definition of satellite concepts to accommodate the various receiving systems.<br />
• The set-up of an end-to-end simulation model including signal at transmission, propagation, reception at satellite level,<br />
considering relevant platform characteristics and orbit parameters.<br />
• The trade-off of options, orbit, satellite, receiving systems supported by simulations.<br />
• The selection of concepts and the allocation of performance requirements to the elements of the receiving chain.<br />
• The verification of the performance allocation by simulations with the end-to-end performance simulator.<br />
• The specification of the key technologies.<br />
• The outline of the plan leading to TRL-5 and further TRL-9.<br />
Deliverables:<br />
Report on Space-Based AIS implementation study<br />
Current TRL: TRL0 Target TRL: TRL3 Application Need/Date: TRL5 by end 2008<br />
Marine surveillance, EO (DCS), Security<br />
Application/Mission: demonstrators as <strong>ESA</strong>/C(2005)130, rev. Contract Duration:<br />
3 (signal intelligence).<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Roadmap: N/A<br />
12 months<br />
<strong>TRP</strong> Reference: T605-05AC<br />
Title:<br />
Grid-based distributed concurrent design (GDCD)<br />
The advantages of applying the Concurrent Engineering (CE) approach to the assessment and conceptual design of future<br />
space missions has been widely demonstrated <strong>du</strong>ring last years. The next step would be to remove the constraint of a<br />
centralized architecture (i.e. all specialists sitting physically in the same location). This activity proposes to develop a<br />
distributed model paradigm because the concept of Distributed Concurrent Design performed in a "Virtual Facility", i.e. design<br />
activities carried out concurrently but using geographically distributed resources, appears to be a natural evolution of the<br />
Design Centres concept. Grid technology will be the basis for the creation of such a "Virtual Facility", consisting of integrated,<br />
tool-oriented computing and communication systems to support scientific and engineering collaboration, removing barriers of<br />
geographic distance and time from research collaborations. This activity could start with the analysis of existing Grid-based<br />
collaborative and visualisation environments, like Access Grid or in SORS, and would continue with the design of a new<br />
distributed Concurrent Design Facility (CDF). As the last step a first prototype would be implemented. Two demonstrations will<br />
be carried out <strong>du</strong>ring this period, a first one to assess <strong>ESA</strong> internal capabilities and a second one to prove the concept (for<br />
technical reasons they might be organised without using GRID).<br />
Deliverables:<br />
Report on current Grid-based advanced collaboration environments; GDCD services specification, architecture and<br />
demonstration.<br />
Current TRL: N/A Target TRL: Prototype Application Need/Date: SW operational >=2008<br />
Application/Mission: all missions involving distributed teams Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7835<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T605-06MT<br />
Virtual AIV Techniques for Virtual Integration of a Satellite in the Test Facilities<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T605-15EM<br />
Title:<br />
Space System Reference Model<br />
The engineering data is at the heart of the advanced system engineering concepts like simulation-based design (also called<br />
virtual spacecraft approach). In order to allow for this approach to be successfully implemented, the simulation must be<br />
embedded in de design process, in a way that the design baseline can be translated automatically in an executable<br />
simulation. The virtual model must reflect the content of the engineering database and must be kept in pace with the with a<br />
"changing" design baseline. System characteristics can be represented as simulation models as well as database items.<br />
Also, simulation models must be "generated" from a reference "system" representation together with requirements and system<br />
data. The purpose of the activity will be: review ongoing initiatives in <strong>ESA</strong> and in<strong>du</strong>stry; select appropriate technology for<br />
implementation of data model; define semantics and populate the data model for a typical spacecraft; and demonstrate that<br />
design baseline, simulation and engineering databases can be rendered consistent and generated from the same data model.<br />
Deliverables:<br />
S/C data model semantics definition/population; demo model of design baseline/automatic simulation generation and<br />
feedback to ECSS standards.<br />
Current TRL: - Target TRL: Prototype Application Need/Date: SW operational >=2009-2010<br />
Application/Mission: all space projects Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7863<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T607-06EM<br />
System-Software Co-Engineering: Performance and Verification<br />
This activity will focus on the verification of the system properties at system and software level. The activity aims at defining<br />
the verification techniques and their environment: sche<strong>du</strong>lability analysis, network calculus, exhaustive verification of state<br />
machines, deadlock/livelock analysis, causality, performance, distributed workload, FMECA, SW-FMEA, etc. The use of<br />
existing commercial tools is encouraged, developing filters between the tools capturing the system description and the tool<br />
performing the verification. But specific development might be needed.<br />
Deliverables:<br />
Definition of the verification environment (lifecycle); identification of the commercial tools and needed developments;<br />
development of filters to the commercial tools; development of specific demonstration models and case study.<br />
Current TRL:<br />
Target TRL: Beta Application Need/Date:<br />
-<br />
SW operational >=2009-2010<br />
version<br />
Application/Mission: all space project Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-908<br />
Consistency with Harmonisation<br />
On-Board SW<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T607-09SR<br />
Concepts for future spacecraft architecture and development approaches<br />
The proposed activity will address the architecture of future spacecraft within the context of the overall mission architecture.<br />
This will be done for a set of strawman missions from various domains. The model requirements from the reference missions<br />
will be analysed and strawman mission architectures established. The focus would be on the spacecraft but considering the<br />
overall context. The experience with previous approaches, e.g. standardisation of full service mo<strong>du</strong>les (ERS-like), or mainly<br />
avionics (e.g. Flexbus) will be reviewed and lessons will be drawn. Experiences with standardisation / inter-operability in other<br />
domains will be analysed for applicability.<br />
The strawman mission will result in a series of strawman payloads which will provide context requirements for the spacecraft.<br />
The interfaces payload – platform will be addressed with the intention to establish the borders where appropriate to enhance<br />
efficiency. The availability of technology will be considered .<br />
Functional, operational and performance and other support analysis will be con<strong>du</strong>cted to define the blocks of the spacecraft<br />
architecture. Reasonable flexibility and expandability goals will be established from each block and the overall. Special<br />
attention will be paid to the need to be at the same time efficient by the effect of scale procurement of equipments and the<br />
compatibility with multiple supplying sources. Recurrence versus innovation will be traded-off and the potential implications of<br />
obsolescence addressed.<br />
The needs of the end-to-end command and control chain, including ground and space segment will be considered. from<br />
commanding at mission level, e.g. obtain an observation, to actual implementation by the onboard and ground systems so as<br />
to standardise development, testing, operation, training. Observability, commandability will be addressed.<br />
Operational modes will be analysed and the impact on the architecture established. Availability goals will be discussed and the<br />
impact on the architecture derived. Quality levels will be also addressed.<br />
Levels of standardisation / commonality will be identified / discussed considering also the implementation context.<br />
The concepts will be considered with <strong>du</strong>e regard to their implementation, i.e. considering the complete definition,<br />
development, verification and operation cycle. The process of handling requirements, system – software co-engineering,<br />
concurrent engineering, collaborative engineering, progressive verification, utilisation of end-to-end simulation, software<br />
simulators of increased fidelity, virtual spacecraft technologies will be addressed. The achievement of technology readiness<br />
levels, mainly in the area of payload shall be addressed for their impact on the development processes and features of the<br />
spacecraft architecture.<br />
This will be done with <strong>du</strong>e attention to the <strong>ESA</strong> environment and constraints and implications on the implementation of<br />
projects.<br />
Candidate architecture concepts and DD&V and operation processes will be identified and traded-off for agreed criteria. The<br />
selected concepts will be then applied to the strawman missions.<br />
Deliverables:<br />
Technical Note (trade-off, architecture, critical technologies,..)<br />
Current TRL: TRL0 Target TRL: TRL2 Application Need/Date: TRL5 by 2011<br />
Application/Mission: all space project Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Roadmap: N/A<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T607-12SW<br />
System of Systems analysis and design environment<br />
The boundaries of system design for space systems have changed significantly in the recent years. If it has been sufficient to<br />
provide single well defined pro<strong>du</strong>cts with a dedicated system in the past, the expectations of users shift towards services and<br />
support, with an entire functional chain required to provide these services. A system design needs to take into account various<br />
and partially divergent functions, to be implemented with space systems, processing and coordination functions on ground and<br />
service provision for the end user – who is not primarily interested in how a service is being established.<br />
This contextual approach requires integrating indivi<strong>du</strong>al systems originally designed for specific purposes, in order to get an<br />
optimal synergy between these elements. Examples are Earth Observation systems (geographical context and surveillance<br />
functions), communication networks (with space and ground components) as well as navigation services (with their respective<br />
spatial and potential local increment components). In the extreme we find systems like Global Earth Observation System of<br />
Systems (GEOSS) and the future Human Security SoS. In order to be able to enable a global analysis and trade-off of<br />
parameters, it is required to enhance existing development methods and tools on (indivi<strong>du</strong>al) system level to make them<br />
suitable to this system of systems.<br />
This activity shall define a methodology for the analysis and design of a system of systems. The required tools shall be<br />
prototyped and demonstrated for a multi-level system such as the combined GMES, Galileo and communication systems.<br />
The methodology needs to address hierarchical analysis approaches, based on proven and demonstrated methods from the<br />
classical system engineering domain. Languages such as UML/SysML and advanced approaches such as the “Virtual<br />
Spacecraft Design” need to be enhanced to be able to capture the increased complexity of such systems. A reference<br />
architecture for such a system shall be established.<br />
Supporting tools need to be prototyped. These tools need to support existing engineering and simulation paradigms as well as<br />
meta-modelling paradigms required for the methods identified above. The explicit support to performance modelling at the<br />
SoS level needs to be enabled with the proposed development, by providing elementary performance analysis blocks for the<br />
indivi<strong>du</strong>al systems.<br />
Deliverables:<br />
Three main types of deliverables are expected form this activity:<br />
1) A well <strong>document</strong>ed methodology for the analysis and design of a system of systems, addressing performance issues:<br />
Formal methods for system-level design and verification; Reference architecture.<br />
2) A support environment for this methodology, to establish relevant system and performance budgets and provide the<br />
elements for system-level trade-offs: System-level performance model building blocks; Architectural design tool for complex<br />
systems; ... .<br />
3) A demonstration prototype for an identified reference system.<br />
Current TRL: - Target TRL: Prototype Application Need/Date: SW operational >=2009<br />
Application/Mission: Security, GMES, GEOSS Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: New rqmt<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T607-13SW<br />
Monitoring and Control Data Modelling<br />
Data base development is on the critical path of many projects; a tool to efficiently generate a validated mission-specific data<br />
model, compatible with the applicable standards will greatly contribute to re<strong>du</strong>ce the development time and facilitate<br />
compatibility across project phases. To that purpose a data model for monitoring and control is needed. A user specification of<br />
an ontology (a data model that represents a domain and is used to reason about the objects in that domain and the relations<br />
between them) for the monitoring and control of space systems has been standardised in ECSS. The ECSS E-70-31 Standard<br />
specifies a set of "generic data" to be supported by any mission (any space system) and a set of "mission specific data" to be<br />
"tailored" for a given mission. The purpose of this activity is to study and develop tools able to formalise the specification of<br />
data required in the Spacecraft System Database in line with relevant ECSS standards. The end result will be an "Ontology<br />
modelling tool" based on the Object Role Modelling Methodology (potentially reusing the NORMA tool currently under<br />
pro<strong>du</strong>ction in academic establishments) able to:<br />
- support all modelling concepts and constraints (including tailoring rules) given in E-70-31 and E-70-32.<br />
- offer to mission users the capability to navigate through the tailoring rules (according to algorithms given in E-70-31), and<br />
tailor the ontology for their own missions (i.e. populating the tailoring variables).<br />
The tailoring being made, the ontology tool will automatically:<br />
- pro<strong>du</strong>ce the mission specific ORM data model.<br />
- allow users to add mission specific data<br />
- validate the overall ORM schema and pro<strong>du</strong>ce: the E/R and SQL data models for use in an RDBMS; the pro<strong>du</strong>ct data<br />
exchange interface specification (i.e. an XML schema for exchanging mission data, e.g. between different database systems).<br />
Deliverables:<br />
Data Model generation tool.<br />
Current TRL:<br />
Target TRL: Beta Application Need/Date:<br />
-<br />
SW operational >=2008<br />
version<br />
Application/Mission: All future projects Contract Duration: 15 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7292<br />
Consistency with Harmonisation<br />
GSSW (not specifically discussed at Harmonisation).<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T607-14SW<br />
Title:<br />
Building Block Approach for EGSE<br />
In the context of the ground segment software harmonisation activity performed by Critical Software (P) the standardisation of<br />
a number of interfaces has been addressed. The end result is a set of ICD's derived through the application of a formal<br />
modelling process. One of these interfaces (specified by Dutch Space as sub-contractor to Critical) concerns the<br />
interconnection of EGSE elements and simulators (known as SIM--EGSE-Interface). In order to validate the interface<br />
specification it is proposed to develop a prototype of the EGSE-SIM interface in the context of the EGSE reference facility<br />
located at ESTEC.<br />
The target shall be to achieve a low cost scalable and configurable EGSE that can be applied on any mission and supporting<br />
reuse of simulation building blocks.<br />
Deliverables:<br />
A prototype EGSE system integrating existing Central Checkout System and a SCOE/Simulator, compliant with the<br />
established ICD.<br />
Current TRL: - Target TRL: Prototype Application Need/Date: SW operational >=2009<br />
Application/Mission: All future projects Contract Duration: 12 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7292<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
GSSW (not specifically discussed at Harmonisation).<br />
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6.9 - Mission Control & Operations (GS Data Sys)<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
GI-001<br />
XML Framework<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
GSS-041<br />
InP X-Band Cryo LNAs<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T603-34GI<br />
Title:<br />
TC Authentication<br />
The Authentication scheme proposed as optional in the <strong>ESA</strong> Packet Telecommand protocol is no more considered secure.<br />
Telecommand Authentication is deemed as the minimum Security barrier that <strong>ESA</strong> spacecraft missions should implement.<br />
This study covers the definition of an updated Authentication scheme for the Packet Telecommand protocol.<br />
Deliverables:<br />
Updated authentication scheme for the packet TC protocol.<br />
Current TRL: Target TRL: S/W release Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : Operational SW Dossier0 Ref.: T-7836<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T603-35GI<br />
Security communications for SLE services<br />
Based on precedent System studies and the existing CCSDS Space Link Extension (SLE) transfer services and<br />
implementation by both <strong>ESA</strong> and NASA, this study aims at reviewing and upgrading the Security functions for missions where<br />
a high-level of Security might be requested.<br />
The Study will have to consider the available protocol and design the tools (e.g. protocols, encryption methodologies, etc.)<br />
needed to implement a high level of security that can be provided with ad hoc tailoring to a user mission. All the design<br />
choices shall be supported by Software breadboarding and simulation. The developed software shall be organized in form of<br />
Software Pro<strong>du</strong>ct (e.g. Library) for easy portability and integration in existing or proprietary software (sub)systems.<br />
Deliverables:<br />
Technical note, SW breadboard and simulation.<br />
Current TRL: Target TRL: S/W release Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : Operational SW Dossier0 Ref.: T-7837<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T605-07GI<br />
Title:<br />
Feasibility of Automated Regression Testing for Space Systems Operational Software<br />
The operational S/W used within space systems is constantly increasing its complexity. Furthermore, <strong>du</strong>e to standardisation<br />
and re-use of infrastructure systems, the expected lifetime of software components has also significantly increased. These<br />
trends have lead to a significant increase in the efforts required for system verification and validation, in particular to ensure<br />
integrity of previously validated functions (regression testing) when delivering a new version of the same software<br />
component/system. Currently, the vast majority of all testing activities, including regression testing, are performed based on a<br />
'manual' approach with the human in the loop. This is primarily <strong>du</strong>e to the fact that, in order to automate testing activities, a<br />
large effort has to be invested upfront for the definition of appropriate test data, test tools/harnesses, test proce<strong>du</strong>res and test<br />
outputs evaluation (pas/fail criteria). The proposed study should therefore demonstrate the feasibility and assess the benefits<br />
of adopting an automated approach for the execution of software systems regression testing. It will include the analysis of the<br />
specific features of space systems software components, with particular attention to the ground operations systems that are<br />
typically operated by humans via human-machine interfaces, and it will review the possible options offered by available<br />
technologies and commercial pro<strong>du</strong>cts for the preparation and automatic execution of systems regression testing. The<br />
selected approach shall be suitable for automated testing of all ground operations systems i.e. it shall not be bound to the<br />
specific implementation aspects of the indivi<strong>du</strong>al systems. A demonstration test environment will be set-up covering the<br />
automatic execution of functional and non-functional tests of selected software components. This prototype shall demonstrate<br />
the re-usability of the automated test cases when validating a new version of the same software component. Finally, it will be<br />
assessed the required effort for the set-up of the indivi<strong>du</strong>al test cases and evaluation of the potential benefits of the<br />
demonstrated approach. Special emphasis shall be given to the feasibility of identifying unambiguous pass/fail criteria for each<br />
test case, with particular reference to the non-functional tests.<br />
Deliverables:<br />
Technical <strong>document</strong>s (adoption of automated approach for execution of SW sys regression testing). Set-up of demonstration<br />
test environment + data/proce<strong>du</strong>res. Final report (assessment of the potential benefits / relevant recommendations).<br />
Current TRL: - Target TRL: Prototype Application Need/Date: SW operational by 2008<br />
Application/Mission: All missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T605-09GI<br />
N-Tier architectures applied to Ground Operations Systems<br />
The current generation of Ground Operations Systems used at ESOC is based on client-server architecture, which is more<br />
generically referred to as a '2-Tier' architecture. In particular in the telemetry processing subsystem, the current<br />
implementation leads to severe requirements about the procurement and maintenance of all H/W workstations, including the<br />
large number of users workstations. The purpose of this study is therefore to investigate the possible benefits that can be<br />
achieved by adopting 'N-Tier' architectures to Mission Control Systems. In particular, the 3-Tier architecture should be looked<br />
at for the most critical subsystems i.e. the telemetry processing, the commanding and the On-Board Software Maintenance<br />
(OBSM). The 3-Tier architecture consists of a data server, implementing the management of the data; an application server,<br />
implementing most of the data processing functionality and a client, supporting the visualisation of the processed data to the<br />
end user. It attempts to overcome some of the limitations of the 2-Tier architecture by enabling a complete separation of the<br />
data presentation, the data processing and the data management using distinct entities. The different tiers interact via<br />
standard protocols such as CORBA, HTTP or standard database protocols. The middle-tier servers are typically coded in a<br />
highly portable, non-proprietary language such as C++ or Java. Middle-tier functionality servers may be multithreaded and can<br />
be accessed by multiple clients, not necessarily all under manual user control, thus enabling the automation of user actions.<br />
The analysis phase of the study shall identify the most suitable technology to be used for N-Tier implementations of Ground<br />
Operations Systems in general (e.g. code language of the application servers, data storage technology, interaction protocols).<br />
The design phase shall cover the architectural design of 'new generation' monitoring and control subsystems heavily involving<br />
data processing and visualisation (at least telemetry processing, commanding, OBSM and Station Monitoring and Control).<br />
The prototyping phase shall migrate an existing subsystem to the 3-Tier architecture and the assessment phase shall evaluate<br />
the benefits of the 3-Tier architecture at system level (including scalability, portability, flexibility, maintainability and<br />
performance) and provide recommendations for the future generations of Ground Operations System infrastructure S/W.<br />
Deliverables:<br />
Under review ------------------ Technical doc. (outputs of the analysis activities). Architectural design <strong>document</strong> (3-Tier<br />
architecture of the MCS most critical subsys). Model implementation of the 3-Tier architecture (selected MCS subsys). Final<br />
report.<br />
Current TRL: - Target TRL: TRL2 Application Need/Date: N/A<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7842<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T605-17GI<br />
European Technology Harmonisation on Ground Systems Software - First Set of<br />
Title:<br />
Standard Interfaces<br />
The European Technology Harmonisation on Ground Systems Software is supported through standardisation of functions and<br />
interfaces. It has been agreed to broaden the scope of this harmonisation (initially Mission Control and EGSE) to include the<br />
other ground system components (Flight Dynamics, simulators, Data archiving and mission planning);A three-phase approach<br />
has been adopted (medium term strategy) with: phase 1(System level): define, with the user community, a common system<br />
standard architecture and common requirement for identified mo<strong>du</strong>les to become ECSS standards; Phase 2: Define standard<br />
interfaces between mo<strong>du</strong>les (to become ECSS standards); Phase 3: Contracts to re-engineer, as needed, solutions compliant<br />
with requirements and standard interfaces, re-using as far as possible existing pro<strong>du</strong>cts. In this proposal, phase 2, it is<br />
proposed to pro<strong>du</strong>ce the definition of the standard interfaces between the mo<strong>du</strong>les of the Ground Systems Reference<br />
architecture, which is key for the future work. Examples of standard interface definition are TM monitoring and Commanding,<br />
Operational Database, On-Board Software management function, Mission Planning System, although the final list of<br />
interfaces to be standardised and its priorities will be defined at the end of Phase 1 (March 2004). This proposal covers the<br />
first set of interfaces (i.e. 5). A second proposal will cover the remaining interfaces (See Proposal T605-18GI /<br />
TOS-GI-ETH-GSSW-002).<br />
Deliverables:<br />
A set of standard interface definition (to be detailed at the end of Phase 1) between the mo<strong>du</strong>les of the Ground Systems<br />
reference Architecture.<br />
Current TRL: Target TRL: TRL1-2 Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-7842<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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6.10 - Flight Dynamics & Navigation<br />
<strong>TRP</strong> Reference:<br />
T606-08GF<br />
Analysis of a Standardised Approach to the Emulation of the Highly Autonomous<br />
Title:<br />
Avionics Systems of Interplanetary S/ C<br />
The Avionics systems of the interplanetary S/C are highly autonomous and complex. In particular, they are designed to<br />
support uninterrupted operations for extended periods without ground support and they even guarantee the capability to<br />
autonomously point the antenna to the Earth and re-establish the link in case of any contingency . To achieve autonomy the<br />
ground station has to provide a large amount of commands and parameters to the Avionics system, which are normally time<br />
tagged and executed by an on-board command queue. Emulation tools play a key role in the generation of those command<br />
parameters. On one side they are used in the command generation chain, to actually pro<strong>du</strong>ce the parameters to be up-linked<br />
to the S/C. On the other side they are used as verification tools to predict and test the effect of command parameters in the<br />
S/C. Also they are a valuable tool to create awareness of the Avionics systems in the operations teams. The purpose of the<br />
study is to explore and breadboard models for standardisation of FD emulation tools for interplanetary S/C to achieve a<br />
development framework which can easily be re-used for future missions. In particular it is envisaged to create standard<br />
mo<strong>du</strong>les for Spacecraft dynamics models, propulsion systems models, avionics units and S/W models and FDIR models.<br />
Deliverables:<br />
Breadboard of the models for standardisation and final report.<br />
Current TRL: Target TRL: Prototype Application Need/Date: SW operational >=2008<br />
Application/Mission: Deep Space Missions Contract Duration: 8 months<br />
SW Clause : - Dossier0 Ref.: T-7820<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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6.11 - Mission Analysis & Space Debris<br />
<strong>TRP</strong> Reference: T605-08GA<br />
Title:<br />
Astro-toolbox: a toolbox for preliminary mission analysis<br />
This study aims at the definition of the required tools for preliminary mission analysis and design. It will be necessary a<br />
trade-off between the level of accuracy for a preliminary assessment and the computing time required. The study will also<br />
include an implementation of the defined methodology and approaches into a mo<strong>du</strong>lar software code and a verification of the<br />
Astro-toolbox on a number of selected test cases. The definition of the tools is necessary to identify all typical problems that a<br />
mission analyst commonly may encounter <strong>du</strong>ring a preliminary design (spiralling trajectories, multiple swing-bys, launch<br />
windows, orbit maintenance, HALO orbits,etc). The trade-off is necessary to define the most appropriate approaches and<br />
solution methods for the identified problems. The result obtained by each mo<strong>du</strong>le must be reliable (within a certain tolerance)<br />
even in case of quick assessment. The maximum error (or the tolerance) allowed for a preliminary study must be defined in<br />
relation to the computational effort. Due to the nature of the toolbox, and the required mo<strong>du</strong>larity, it is recommended to use<br />
Matlab (or equivalent) as programming language and development environment. Interface with other systems (excel, STK,etc)<br />
must be provided in form of appropriate output and input data format. A graphical interface is also required to help in the<br />
design and visualisation of the results.<br />
Deliverables:<br />
Technical Report, Demonstration Software.<br />
Current TRL:<br />
Target TRL: Beta Application Need/Date:<br />
-<br />
version<br />
Application/Mission: Mission analysis Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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6.12 - Ground Station System & Networking<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T606-01GS<br />
Two-layer servo concept with movable BWG mirrors<br />
In Deep Space operation at Ka-band, the pointing requirements are more demanding than for Near Earth missions. At<br />
present, the positioning of an antenna is carried out with a servo drive system for the elevation and azimuth axis. Due to the<br />
eigenfrequencies of the antenna structure, the involved masses and the limited torques at the output of the gearboxes<br />
provided by the main drive system, the compensation of pointing errors, position errors, is limited to slowly varying effects. For<br />
future deep space missions in Ka-band, <strong>du</strong>e to the delay to the spacecraft, the earth rotation and the small beam-width of the<br />
antenna, a beam squint between transmission and reception is necessary. This will require a moveable mirror system to<br />
generate a movable beam offset between transmission and reception. A Beam WaveGuide (BWG) system for the RF signal<br />
path consists of several mirrors. Movable mirrors would allow to compensate the errors <strong>du</strong>e to distinct faster varying effects,<br />
e.g. wind gusts. Such movable mirror would correct position errors detected by the encoders of main drives. The main drive<br />
itself cannot compensate the position error <strong>du</strong>e to the above-mentioned reasons. Such system would be particularly<br />
interesting, because the pointing errors <strong>du</strong>e to wind effects are the major source of position errors for the 35 m antenna.<br />
Taking into consideration the previous explanation, the purpose of this study is to design a servo system (including elevation<br />
and azimuth axis and a system of movable mirrors) and to identifying its critical areas, and also to develop a control system<br />
for the movable mirrors. Numerical simulations will be used to investigate the limits of the servo system regarding dynamic<br />
behaviour, position accuracy and response time.<br />
Deliverables:<br />
Study and design report with detailed dynamical analysis of the proposed design. Breadboard of a drive system for a movable<br />
mirror.<br />
Current TRL: TRL2 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2007<br />
Application/Mission: Deep Space Network Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-1108<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference: T606-02GS<br />
Title:<br />
Multipurpose Highly Stable System for Ground Station Characterisation<br />
There are two main needs for the proposed activity:<br />
precise time transfer among Deep Space Ground Stations;<br />
ability to measure the Allan deviation of large reflector antennas, such as the ones used to support Deep Space missions.<br />
Tracking requirements for future Deep Space missions demand accuracies that cannot be achieved with current tracking<br />
techniques. Planning ahead for future tracking methods that can meet these requirements, Delta Differential One-Way Range<br />
(DDOR) is included in the TT&C roadmap as a technique to be used in the future for more accurate tracking measurements.<br />
DDOR is a Very Large Baseline Interferometry (VLBI) technique that makes use of two or more distant Deep Space Stations<br />
in order to perform accurate spacecraft's angular position measurements. This technique requires very precise station<br />
synchronisation, which could be achieved by means of accurate time transfer. Additionally, radio science requirements of<br />
planetary missions call for extreme Allan deviation performances for Ground Stations. Deep Space missions time scales<br />
require the characterisation of the whole Ground Station and specifically of large mechanical structures in terms of electrical<br />
phase stability, which turns into tracking accuracy. At present there are no means to measure the contribution of the<br />
mechanical part of the antenna to the overall frequency stability of the ground station. In this context, the goal of this activity is<br />
to develop a system able to synchronize frequency standards from distant Deep Space antennas (like New Norcia and<br />
Cebreros) for DDOR measurements. This could be done by implementing a Ku-band link between the stations involved in the<br />
measurement. A small 3m (TBC) antenna transmitting/receiving in Ku-Band, together with a highly stable two-way time<br />
transfer processor and a highly stable link are required for this task. This system can also be used to characterise the stability<br />
of the antenna mechanics. An additional highly stable phase comparator mo<strong>du</strong>le is needed for this application.<br />
Deliverables:<br />
Breadboarded system for evaluation, final report, and test reports.<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: (Continuation in the 2008<br />
TRL2<br />
budget of <strong>ESA</strong> Investment<br />
Plan) TRL5 by 2012<br />
Bepi-Colombo; any mission using the<br />
Application/Mission: DSAs (e.g. Rosetta, MEX and VEX, Contract Duration: 18 months<br />
Herschel-planck, GAIA, SOLO, etc.)<br />
SW Clause : - Dossier0 Ref.: T-1108<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T606-06GS<br />
Title:<br />
Experimental InP Ka band cryocooled LNAs<br />
This study shall provide technological advancement in manufacturing Ka-band cryo Low Noise Amplifiers (LNAs), as required<br />
for <strong>ESA</strong> missions. The study will be composed of two main tasks. The first task is the development and pro<strong>du</strong>ction of InP (or<br />
GaAs with high In content) devices (TRTs or MMICs) suitable for low noise cryogenic applications. The second task is the<br />
development and pro<strong>du</strong>ction of cryogenic LNAs suitable to work in <strong>ESA</strong> Deep Space antennae. More detailed, the work to be<br />
performed is to derive suitable specifications for transistor manufacturers and to breadboard o cryo Ka-band LNA with the<br />
developed devices (either MMICs or TRTs) so that it can be tested the RF performance at cryo and ambient temperature.<br />
Deliverables:<br />
Breadboard of the designed LNA and <strong>document</strong>ation and recommendations for the pro<strong>du</strong>ction of the serial units.<br />
Current TRL: TRL3 Target TRL: TRL5 Application Need/Date: TRL5 by 2009<br />
Application/Mission: Deep Space Network Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7656<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T606-12GS<br />
Study and Breadboarding of a Sapphire Oscillator for Ultra-High Short-Term Station<br />
Title:<br />
stability<br />
A clear trend in Ground Station engineering is the search for better Ground Station stability, since it results in better tracking<br />
accuracy. Generically, frequency stability is characterized with two quantities: Phase Noise (short term stability) and Allan<br />
Variance (long term stability). Among possible frequency stability improvements in Deep Space Ground Stations, sapphire<br />
oscillators are the most promising option because they permit phase locking to other sources. This allows simultaneous use of<br />
sapphires and MASERs in a single Ground Station frequency reference. By doing so, the good qualities of MASERs and<br />
sapphire oscillators are combined for optimum performance. However, there are currently no sapphire oscillators deployed in<br />
any <strong>ESA</strong> station. Before this becomes a reality, there is a need to understand design, integration and maintenance related<br />
aspects. The purpose of this activity is to design and breadboard a sapphire oscillator that improves Ground Station frequency<br />
stability performance up to 100 seconds. This activity will be divided in two phases (Phases I and II).Phase I activities shall<br />
present a general overview of sapphire oscillators; identify doping materials for external element compensation; compare<br />
cryocooled sapphire oscillators versus more inexpensive compensated sapphire oscillators at higher temperatures; analyse<br />
different phase locking techniques between a hydrogen maser and a sapphire oscillator; evaluate different down conversion<br />
schemes from the sapphire output frequency to the Ground Station frequency distribution outputs; describe relevant<br />
monitoring and control parameters for sapphire oscillator operation; detail any remaining issue that is relevant for sapphire<br />
oscillator's operation; address sensitivity of sapphire oscillators to electromagnetic fields; and trade-off all decision factors and<br />
present the most suitable solution for a combined maser and sapphire oscillator source in <strong>ESA</strong> Deep Space Ground Stations.<br />
During Phase II of the study, a sapphire oscillator shall be breadboarded, together with the necessary PLL circuitry to phase<br />
lock it to a MASER standard. The breadboard unit shall allow for basic M&C communications via TCP/IP. An acceptance test<br />
shall be performed on the breadboard unit, in order to validate the performance (phase noise, allan deviation, phase locking to<br />
maser, sensitivity to magnetic fields, other EMC effects and M&C).<br />
Deliverables:<br />
Intermediate report (end of phase I); breadboard; final report.<br />
Current TRL: Target TRL: TRL4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Deep Space Network Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-1247<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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6.15 - Mechanisms & Tribology<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/MMM-001<br />
Self Contained Deployment Mechanism<br />
A SeCDeS (Self-Contained Deployment System),consisting of a motorized deployment system with a mechanism located in<br />
each of the panel hinge lines, is under development to reach a TRL4. The mechanism is simple, has low weight, and consists<br />
of a stepper motor connected to a gear box. All stepper motors are controlled from an electronic box located close to the root<br />
hinge of the spacecraft. The electronics are powered from a battery box also located close to the root hinge. The mechanism<br />
can easily be adapted to all types of mechanical hinges. This new system gives accurate panel synchronisation and the<br />
achieved SA cone angles are considerably re<strong>du</strong>ced compared to existing systems.<br />
The subject CCN shall address two issues identified in the course of the BB development:<br />
1. A miniaturized position sensor must be developed to achieve the BB performance. Sensor fundamentals and mechanical<br />
robustness as well as signal integrity and analog filtering techniques will be addressed as main objectives. An EM sensor will<br />
be built and tested.<br />
2. A worst case environmental test of the double stage Harmonic drive gear box must be performed to ensure that the<br />
gearbox behaves as expected within the specified temperature range [Operational -130 degC to + 116 degC, Survival -180<br />
degC to +116 degC].<br />
Deliverables:<br />
Miniaturized position sensor<br />
Current TRL: TRL1-2 Target TRL: TRL4 Application Need/Date: TRL5 by 2009<br />
Application/Mission: Solar Arrays Contract Duration: 9 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Self Contained Deployment Mechanism<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/MMM-002<br />
Integrated SADM+HDRM<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: 03/MNT-001<br />
Title:<br />
Mirco Nano Satellite Technologies<br />
The subject CCN shall address two issues identified in the course of the BB development<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-21MM<br />
Title:<br />
APSEE: Arc Phenomena in Space Environment & Equipment<br />
A miniaturized position sensor must be developed to achieve the BB performance. Sensor fundamentals and mechanical<br />
robustness as well as signal integrity and analog filtering techniques will be addressed as main objectives. An EM sensor will<br />
be built and tested.<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T601-36MM<br />
Unlimited resetable, no-shock Hold-Down and Release Mechanism (HDRM)<br />
A worst case environmental test of the double stage Harmonic drive gear box must be performed to ensure that the gearbox<br />
behaves as expected within the specified temperature range [Operational -130 degC to + 116 degC, Survival -180 degC to<br />
+116 degC]<br />
Deliverables:<br />
HDRM breadboard model with associated datapackage <strong>document</strong>ation.<br />
Current TRL: TRL1 Target TRL: TRL3-4 Application Need/Date: TRL5 >2009<br />
Low mass appendages, where access is<br />
Application/Mission: critical (e.g. optical payload mechanisms, Contract Duration: 18 months<br />
small reflectors, covers)<br />
SW Clause : - Dossier0 Ref.: T-7847<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Hold-down and Separation Systems<br />
<strong>TRP</strong> Reference: T601-47MX / MMM-960<br />
Title:<br />
Tribology Application Programme<br />
Within the identified funding limitations, the R&D activities proposed will address in detail all subjects from tribological design,<br />
analysis, to development and lifetime test demonstration of advanced tribological components and lubrication solutions. Tool<br />
developments to facilitate the design and analysis of bearings and its components (cages) under specialised conditions as<br />
experienced on Earth Observation payloads are included. Furthermore, moving electrical contacts, sizing for stiction and<br />
dynamic friction, and tribological solutions for miniaturised mechanisms components and development of special tribological<br />
coatings to re<strong>du</strong>ce payload and S/C cost for integration will be investigated.<br />
Deliverables:<br />
Tribological assessments, feasibility demonstrations of lubricants wrt. wear and lifetime performance, Software breadboard<br />
verifications of advanced lubricant solutions on key mechanisms components.<br />
Current TRL: - Target TRL: TRL3-4 Application Need/Date: N/A<br />
Application/Mission: all space missions Contract Duration: 60 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7846<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T608-31MM<br />
Title:<br />
Fully Variable Bearing Active Preload System<br />
The proposed activity aims at the development of a device that allows to actively control in-orbit the preload of ball bearings<br />
for applications requiring an extremely long life (e.g. Wheels, Pointing & Scanning mechanisms). The basic concept of<br />
bi-stable (one shot) operation, i.e. switching between high and low preload already proven in terms of concept, shall be<br />
extended to in-orbit full adjustment capability. Upon external command, it shall be possible to select a high preload and to vary<br />
a low preload setting within an appropriate range. Using a suitable target wheel as test bed, an engineering model of the<br />
preload adjustment device shall be designed, manufactured, integrated and tested in representative environment.<br />
Deliverables:<br />
Engineering Model (accompanied by Technical Data Package and further <strong>document</strong>ation).<br />
Current TRL: TRL3 Target TRL: TRL5-6 Application Need/Date: TRL5-6 in 2008<br />
Wheels, Pointing mechanisms,<br />
Application/Mission: Contract Duration: 18 months<br />
Scanning mechanisms<br />
SW Clause : - Dossier0 Ref.: T-7848<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-32MM<br />
Angular position sensor based on MEMS technology<br />
The purpose of this activity is to take benefit from existing MEMS devices already developed for ground application, and<br />
develop a MEMS angular position sensor suitable for space application. The targeted accuracy should be better than 0.1deg<br />
along 360 deg.<br />
Several non-contact technologies (Hall-effect, optical, micro-gyro, magnetic, ...) are potential candidates. First part of the<br />
activity should focus on possible design and the selection of the most appropriate technologies to achieve this MEMS position<br />
angular sensor with respect to space application needs and constraints.<br />
Second part of the project will be dedicated to the manufacturing and test of Engineering Model MEMS device to be validated<br />
in representative environment.<br />
Deliverables:<br />
Functional MEMS Angular sensor Engineering Models and associated datapackage <strong>document</strong>ation.<br />
Current TRL: TRL3 Target TRL: TRL5-6 Application Need/Date: TRL5-6 in 2008<br />
All mechanisms requiring angular<br />
position measurement (e.g. SADM,<br />
Application/Mission:<br />
EPPM, Pointing & scanning<br />
Contract Duration: 18 months<br />
mechanisms)<br />
SW Clause : - Dossier0 Ref.: T-7849<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
6.16 - Optics & Opto-Electronics<br />
<strong>TRP</strong> Reference:<br />
MMO-670<br />
Materials for Ultra-Stable Lightweight Optical Benches and Mirrors (old <strong>title</strong>: Ultra<br />
Title:<br />
lightweight Telescopes)<br />
Objective of the activity is the evaluation/development of material technologies for ultra-stable optical structures. The materials<br />
should be suitable for cryogenic applications (i.e. homogeneity, isotropy) and lightweight applications. In view of the<br />
development status reached for SIC100 (e.g. Herrschel), other materials shall be considered. During the course of this<br />
activity, a representative optical structure demonstrator (optical bench, mirror, telescope) shall be developed and extensively<br />
characterized. Alternative material or technologies (shell technologies) shall be considered.<br />
Deliverables:<br />
Material characterisation Data<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010<br />
Applicability (>2010) to SCI/EO missions<br />
Application/Mission: Contract Duration: 24 months<br />
(e.g. Darwin, MTG)<br />
SW Clause : - Dossier0 Ref.: T-731<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T507-06MM<br />
Title:<br />
Entangled photon source for Quantum Communications<br />
Absolute (=unbreakable) security is a mandatory requirement in many space applications (satellite remote control, GALILEO,<br />
etc). Quantum cryptography provides a scheme for the absolute secure distribution of cryptographic keys, guaranteeing such<br />
stringent level of secure communications. <strong>ESA</strong> has placed two parallel studies en<strong>title</strong>d "Quantum Communications in Space”<br />
in the General Studies Programme (GSP). These studies have identified novel concepts for space communication systems<br />
based on the principles of quantum physics, along with related demonstration experiments using available infrastructure (e.g.<br />
<strong>ESA</strong>’s Optical Ground Station). Such experiments require the development of a quantum communication optical terminal.<br />
The objective of this activity is to initiate the development of the key building blocks of such a quantum communication optical<br />
terminal by the development of an efficient entangled photon source mo<strong>du</strong>le that potentially could be used in space. Such a<br />
source is mandatory to perform fundamental tests of quantum physics and to implement quantum communication protocols<br />
based on entanglement (e.g. quantum teleportation, quantum dense coding). An entangled photon source can also be used<br />
as a single photon source.<br />
A complete quantum communication optical terminal in space would provide the capability of distributing entangled photon<br />
pairs to 2 separated receiver terminals (e.g. 2 Optical Ground Stations) simultaneously. Such a capability would be of great<br />
importance for absolute secure key distribution between widely separated points on Earth using the principle of quantum<br />
cryptography based on entanglement. Current terrestrial optical fibre networks limit the maximum separation of users to about<br />
100 km. Later developments of a complete quantum communication optical terminal would require further items such as:<br />
• Single photon detection mo<strong>du</strong>le<br />
• Faint laser source mo<strong>du</strong>le<br />
• Optical components for photon manipulation<br />
• Dual telescope opto-mechanical head<br />
• Data acquisition and classical communication channel.<br />
Deliverables:<br />
Experimental proof-of-concept demonstration of entangled photon source.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 >2010<br />
Security applications (satellite remote<br />
Application/Mission: Contract Duration:<br />
control, GALILEO, ..)<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
18 months<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T609-05MM<br />
Instrument concepts using dynamic diffraction gratings (ICDDG)<br />
The ongoing commercial development and exploitation of MEMS technologies has led recently to the availability of a new<br />
device type called "programmable micro diffraction gratings" (PMDG). Such devices are a key "enabling technology" for many<br />
potential applications in telecommunications (e.g. add-drop mutiplexers), Earth observation and remote sensing (e.g.<br />
reconfigurable correlation spectroscopy of trace and toxic species) etc. The possibilities are endless. As with all MEMS type<br />
devices one of the big advantages of PMDGs is their small size and programmability. In addition on first inspection they<br />
appear to be very robust. With mass pro<strong>du</strong>ction the unit cost will certainly decrease and their use for the construction of small<br />
but powerful sensor systems on micro or nano sats is a very attractive option. In this activity it is proposed to procure a PMDG<br />
device(s) from the US and to investigate its performance under laboratory conditions. In addition once it has been<br />
characterized and understood from an operational point of view, it will then be built into a breadboard spectrometer for<br />
functional testing. The breadboard spectrometer design will be optimized to take full advantage of the performance and novel<br />
characteristics of this US PMDG device.<br />
Deliverables:<br />
Fully characterized PMDGS devices<br />
Current TRL: - Target TRL: TRL2 Application Need/Date: TRL5 by 2011<br />
Application/Mission: Small EO missions, planetray research Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7861<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T609-16MM<br />
Title:<br />
Advanced Side-pumping Technique for Double Clad Fiber Lasers<br />
Double-clad fibre lasers allow for very improved pumping (optical to optical) efficiencies as well as higher absolute powers by<br />
maximizing the pump - active region overlap and matching to both pump and output wavelength. This activity is aimed to<br />
investigate an advanced side-pumping technique by using small coupling grooves in the cladding allowing elegant re<strong>du</strong>ndancy<br />
implementation of the pump system and system miniaturization.<br />
Deliverables:<br />
Laboratory test setup demonstrating the achieved pumping efficiency and absolute power of the proposed advanced pumping<br />
scheme.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: generic Lidar technologies Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7884<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T609-17MM<br />
Programmable optoelectronic adaptive lens<br />
Pro<strong>du</strong>ction of a lightweight, single element lens, consisting of a liquid crystal or electrochromic plate, dynamically controllable,<br />
to pro<strong>du</strong>ce the desired optical refracting properties. Useful in many instruments normally requiring heavy, multi-element lens<br />
systems, and capable of varying optical properties on command. This device would be particularly relevant for microsats and<br />
nanosats. This activity will study, analyse and then design and manufacture a liquid crystal or electrochromic plate, with a<br />
matrix of addressable pixels or rings, allowing the localised and programmable variation of refractive effect or the generation<br />
of Fresnel zones. In this way, any desired effective refractive behaviour profile can be generated, in a somewhat similar<br />
manner to a Fresnel lens. This would permit the emulation of various types of lens systems within a very lightweight and<br />
compact optical assembly. Variation in the optical properties of the lens would also be possible on a dynamic basis. The<br />
device could also serve as an adjustable attenuator for sources of differing brightness. Testing, characterisation and analysis<br />
would then follow, to allow a clear assessment of how to proceed for future development in this technology.<br />
Deliverables:<br />
Optoelectronic lens demonstrator.<br />
Current TRL: - Target TRL: TRL2 Application Need/Date: TRL5 >= 2010<br />
Application/Mission: all optical missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7855<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T609-23MM<br />
Programmable micro-diffraction gratings<br />
Programmable micro-diffraction gratings (PMDG) are on-chip-manufactured optical devices using micro-electro-mechanical<br />
system (MEMS) technology. Optical MEMS (MOEMS) devices are based on movable micrometric optical components and<br />
therefore provide large benefits in terms of mass, speed, low power consumption, size and ruggedness. In addition they have<br />
the potential to be available at low cost, since complete systems can be pro<strong>du</strong>ced using essentially standard technologies of<br />
the semicon<strong>du</strong>ctor in<strong>du</strong>stry.<br />
Basically, a PMDG device consists of a one-dimensional array of very thin and flat optical mirrors (100’s of micromirrors)<br />
whose vertical position can be electrically controlled (e.g. by electrostatic actuation). By adjusting all the relative mirror<br />
positions a grating can be generated for diffracting the incident light into a selected angle with any desired spectral response.<br />
For example, they can be adjusted to form a blazed grating or to match the absorption or emission spectrum of a molecule. A<br />
new type of extremely compact correlation spectrometers, very promising for Earth Observation and Science Exploration<br />
missions, can be built. Only one single photo detector is needed to build the spectrometer, which is a great advantage<br />
compared to fixed grating spectrometers requiring a detector - array. Since the mirrors can be moved in less than 0.1 ms,<br />
many different spectral responses can be generated in a short time period. Moreover, a PMDG device is reconfigurable (i.e.<br />
the optical transfer function is programmable), allowing the target species to be changed by remote control, which makes this<br />
device concept ideal for planetary exploration.<br />
PMDG can provide elegant solutions to a huge variety of spectroscopy applications (e.g. detection/identification of chemical<br />
species), hence enabling new Earth Observation and Science Exploration missions, e.g. for spectroscopy instruments<br />
on-board microsatellites, nanosatellites, micro-aerobots and micro-probes, envisaged for some of the Science & Planetary<br />
Exploration reference missions (TRM) like JEM (Jupiter Explorer Mission), IHP (Interstellar Heliopause Probe) and VEP<br />
(Venus Entry Probe). The development of this “enabling technology” will ensure a strategic leadership in competitiveness and<br />
independence to Europe.<br />
The objective of this activity is to design, develop and manufacture in Europe programmable micro-diffraction grating (PMDG)<br />
devices for spectroscopy applications and to deliver a proof-of-concept demonstrator of such a device, which shall be<br />
subjected to a functional performance verification test campaign for the on ground validation of the selected concept, with the<br />
goal of demonstrating the functional requirements (e.g. spectral resolution) and the expected improvements in terms of mass,<br />
size and power consumption. The Contractor shall also investigate environmental, reliability and packaging issues to support<br />
future space qualification stages.<br />
PMDG devices are presently commercially available in the USA as well as in Japan. The <strong>TRP</strong> activity “Instrument concepts<br />
using dynamic diffraction gratings, T609-05MM”, assesses experimentally the performance and capabilities of PMDG devices<br />
procured in USA and investigate novel instrument concepts based on PMDG device technology. The outcomes of this activity<br />
will be used for the proposed PMDG development activity.<br />
Deliverables:<br />
Technology data package; Executive summary report; Modelization tools (mathematical/numerical computer models);<br />
Samples and Proof-of-concept demonstrator of PMDG's for spettroscopy applications.<br />
Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2011<br />
Application/Mission: Small EO missions, planetray research Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7861<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
6.17 - Aerothermodynamics<br />
<strong>TRP</strong> Reference: T601-25MP<br />
Development of advanced models and acceleration of Monte Carlo methods for<br />
Title:<br />
simulation of rarefied gas dynamics<br />
The objective of this activity is to improve the DSMC tools for analysis and design of tree molecular and transitional fluid<br />
dynamic phenomena such as oftware plume contamination, plume interaction and heating, vehicle reentry and/or destruction<br />
ATD, satellite environment assessment, and Mems analysis (micro thrusters). The following taks will be done: - Development<br />
and implementation of advanced models for chemistry and relaxation (diatomic and polyatomic gases) that take into account<br />
the quantum nature of internal energy modes and vibration-dissocciation coupling. Verification and validation of developed<br />
models via comparisons with available experimental data- Creation of majorant frequency schemes based on master kinetic<br />
equation (MKE) for an implicit treatment of the collision processes.- Development hybrid approaches combining continuum<br />
and kinetic descriptions of the flow, kinetic schemes of gas dynamics should be used to facilitate the automatic domain<br />
decomposition and coupling of MC solution with continuum equations. A unified computer code should automatically switch<br />
between kinetic and continuum models to maximize computational efficiency and ensure numerical stability.- Creation of an<br />
object-oriented software (OOS) system using C++ language and based on RGDAS software. This OOS system should include<br />
above mentioned models and approaches and permit to compute 2D, axisymmetric and 3D plume flows and their interactions<br />
with the spacecraft; incorporates pre- and post-processing systems that enable the use by non-expert users; re<strong>du</strong>ces the time<br />
to set-up + run complex simulations from months to days.The proposed activity is aimed at the development of a single<br />
European DSMC code for realistic 3d configurations, physically accurate, for simulation of rarefied flows ranging from<br />
suborbital to ground-test-facility conditions. The code could be developed as a mo<strong>du</strong>lar, possibly object-oriented, program, in<br />
a open-source environment and with an open architecture which will allow maximum flexibility and mo<strong>du</strong>larity.<br />
Deliverables:<br />
European DSMC tool , open source , for simulation of rarefied and transitional flow phenomena.<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: SW operational by<br />
TRL2<br />
S/W release<br />
2007-2008<br />
all satellites / re-entry vehicles (high<br />
Application/Mission: Contract Duration: 12 months<br />
altitude); Exploration, EO, EOPP<br />
SW Clause : - Dossier0 Ref.: T-7901<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-28MP<br />
Title:<br />
Feasibility Demonstration of a European Space Propulsion Simulation Tool<br />
The purpose is to demonstrate, as an extension of an already existing common environment, a mechanical engineering<br />
simulation tool for transient multi-disciplinary systems and cycles (e.g. spacecraft systems, chemical and electrical propulsion<br />
cycles, ground support equipment & operations, ground/qualification tests,...) to be used by European space in<strong>du</strong>stries,<br />
research institutes and universities. Due to the intrinsic complexity of this activity, the feasibility of the concept should first be<br />
demonstrated, allowing:The proof of concept to couple several mechanical disciplines (fluid flow, thermal, machinery,<br />
electrical, chemistry...) into one single engineering analysis tool.The proof of concept to re<strong>du</strong>ced modelling of particular<br />
physical processes in space environments along with appropriate validation.The proof of concept to run in a temporally<br />
unsteady way a system and/or a cycle where the different demonstration models and discipline couplings are integrated.<br />
Deliverables:<br />
Demonstration model.<br />
Current TRL: - Target TRL: Prototype Application Need/Date: SW Operational by 2010<br />
Application/Mission: Launcher and satellite propulsion Contract Duration: 18 months<br />
SW Clause : Operational SW Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Roadmap: 2nd sem. 2004 - 1st sem. 2005<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T601-48MP<br />
Validation of aerothermo chemistry models for reentry applications<br />
Improvement of the measurement techniques associated with radiation spectral measurements in hypersonic shock tubes and<br />
plasmatrons. Performance of dedicated experiments using appropriate gases simulating planetary and earth reentry mission.<br />
Based on these validation experiments, improved physical models will be developed using ab initio modelling techniques<br />
consistent with the physics of flight. Here special support will be required from universities competent in the field. In a first<br />
phase emphasis will be put on post flight analysis of the Huygens mission. In a second phase , in addition to the shock layer<br />
radiation coupling activities, gas surface interaction experiments shall be performed for improved ablation, catalysis and<br />
oxidation modelling. Here experiments shall be performed in solar furnaces and at universities where specific expertise exists<br />
on gas surface recombination modelling as well as in plasmarons to obtain catalysis and oxidation data on a set of<br />
preselected materials used as TPS for planetary and earth exploration vehicles.<br />
Deliverables:<br />
Improved and demonstrated physical models for inclusion into aerothermodynamic and thermal protection system design tools<br />
for application in space vehicle design associated with planetary entry as well as high speed earth reentry missions.<br />
Current TRL: Target TRL: S/W release Application Need/Date: TRL5 >2011<br />
Application/Mission: re-entry applications, explorations Contract Duration: 24 months<br />
SW Clause : Operational SW Dossier0 Ref.: T-7897<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-49MP<br />
Hypersonic facility instrumentation enhancements for improved flight extrapolation and<br />
Title:<br />
scaling<br />
It is proposed to demonstrate the capabilities which hot hypersonic wind tunnels can offer to current and future programmes<br />
associated with re-entry. What in<strong>du</strong>stry is interested in most when performing design work is the influence of high-temperature<br />
effects not only on thermal and mechanical loads but, in particular, on forces and moments in order to have a sound data base<br />
for the choice of trajectory, material and so forth. The assured knowledge of such properties would also allow to further<br />
validate computational prediction methods and models. A suitable approach is to perform some kind of standard model<br />
testing, i.e. using – if possible – the same test model in all wind tunnels. Two models should be considered, one which allows<br />
to measure pressure and temperature (heat transfer), and one to determine forces and moments (giving priority to the latter).<br />
These data would permit cross checking for validation of prediction methods. After consultation with in<strong>du</strong>stry a suitable lifting<br />
body, such as the HALIS model (which <strong>du</strong>plicates exactly the lower surface of the US ORBITER), and the ballistic model<br />
EXPERT shall be selected. In order to better demonstrate and clarify the effect of high temperatures on e.g. forces one should<br />
consider carrying out experiments also in classical cold hypersonic wind tunnels using the same models. The activity shall<br />
include: well characterized ground based hypersonic facilities, improved nozzle calibrations thanks to the development of<br />
advanced instrumentation enabling full hypersonic free stream nozzle calibration; testing of the EXPERT and HAlIS<br />
configuration in these high enthalpy facilities will provide a unique opportunity to study real gas effects thereby consolidating<br />
the uncertainties associated with windtunnel to flight extrapolation and scaling.<br />
Deliverables:<br />
Facilities characterization. Improved nozzle calibrations.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 >2009<br />
all re-entry missions; launcher,<br />
Application/Mission: Contract Duration: 24 months<br />
exploration, ..<br />
SW Clause : - Dossier0 Ref.: T-7904<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
6.18 - Propulsion<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
98/YPE01<br />
SMART- 1 EPS Flight Equipment<br />
The Electric Propulsion Subsystem (EPS) provides primary propulsion onboard of the <strong>ESA</strong> SMART-1 spacecraft, which is the<br />
first of the Small Missions for Advanced Research and Technology (SMART) in the <strong>ESA</strong> Horizon 2000 plan. The EPS is<br />
supposed to demonstrate the use of electric propulsion as a primary source and under variable input power conditions.<br />
The EPS is composed primarily of a Xenon storage tank, a pressure regulation unit, a flow control unit, a power processing<br />
and control unit, propellant pipework, electrical harnesses, and electric thruster(s). The thrusters that can either be gridded ion<br />
thruster(s) or a Hall plasma thruster(s), The thruster alignment mechanism is not included and is under the direct responsibility<br />
of the SMART-1 Prime Contractor. In addition to the delivery of the SMART-1 EPS hardware, the contract includes also the<br />
assembly, the integration, the verification, on the spacecraft, as well as the support to the Prime Contractor for the<br />
environmental testing and flight operation support. This procurement is to be placed in one single stage starting from the<br />
development phase up to the flight phase. The design definition study phase has been performed at <strong>ESA</strong> and has been used<br />
to prepare the EPS technical specifications, which are part of the Request For Proposal (RFP). The SMART-1 design is based<br />
largely on existing electric propulsion system, currently developed for North-South station keeping of Geostationary<br />
telecommunication satellites. The development required is therefore limited to the adaptation of an existing system to the<br />
SMART-1 needs as specified in the technical specification.<br />
The activity was initiated in the frame of a previous <strong>TRP</strong> workplan. The current activity will cover an additional work package.<br />
Deliverables:<br />
Demonstrator; Technical Report<br />
Current TRL: TRL3 Target TRL: TRL4-5 Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: GAD 3.10<br />
Title:<br />
Investigation Into MEMS - MEOMS Packaging<br />
Micro Electronic Mechanical Systems (MEMS), commonly called micro-machines, are micron-sized devices that can sense or<br />
manipulate the physical world. MEMS are actual mechanical systems that are created via a process called micro machining.<br />
Due to the growing demand of miniaturised components, manufacturers are being forced to come up with technological<br />
breakthroughs in order to satisfy this demand. MEMS are a combination of mechanical and electrical features in a very small<br />
package.<br />
MEMS are used in medicine, transportation, in<strong>du</strong>strial and consumer pro<strong>du</strong>cts, and most commonly for accelerometers in<br />
automotive air bags. The rapid increase in demand for communications has promoted the development of optical switching<br />
applications where high-speed broadband networks, expanding service capabilities, are needed, thus leading to the Micro<br />
Optical Electronic Machines (MOEMs). These need both improved optical and electrical interfaces as well as more<br />
time-efficient ways to make fiber connections. This is driving the need for new packaging solutions. Protection is a key<br />
element in packaging MEMS and MOEMs because corrosion, moisture, and debris can prevent the devices from working.<br />
Each device must be hermetically sealed in order to prevent the devices from becoming contaminated. The proposed activity<br />
will investigate the MEMS – MEOMS Packaging technologies.<br />
Deliverables:<br />
Technology assessment.<br />
Current TRL: TRL2-3 Target TRL: TRL5-6 Application Need/Date: TRL5/6 by 2008<br />
Application/Mission: all missions Contract Duration: 24 month<br />
SW Clause : - Dossier0 Ref.: T-7753<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
MPC-842<br />
Title: Green Propellants Phase 2<br />
The present activity is the phase 2 of a wider study aiming at providing information / data to support a decision on future<br />
investments in the technology of non toxic propellants to support decisions on possible hardware development initiatives.<br />
During phase 1 a compilation and synthesis of knowledge related to the use of green propellants and identification of open<br />
technological issues requiring further investigations was undertaken.<br />
The complete study (Ph.1&2) includes the analysis of the potential application of non toxic propellants for spacecraft and<br />
upper stage propulsion and resulting technological needs; it addresses cost-effectiveness and quality issues and involves<br />
proof of concept experimental investigations.<br />
In order to maximize the effectiveness and broadness of the study, the Ph.1 of the project has been carried out in parallel with<br />
two different companies. Owing to the encouraging results of Ph.1 and in order to exploit to the outmost the potential of the<br />
two involved contractors, the Ph.2 will be carried out by both companies teamed up.<br />
Based on the conclusions of Ph.1 which lead to the selection of attractive propellant combinations, the Ph.2 focus will be on<br />
the improvement of the basic knowledge aspects, (e.g. performance, ignition, combustion characterisation, material<br />
compatibility, sooting) through experimental/test activities using European test benches (ONERA, DLR, TUM) as well as study<br />
activities (definition of engine concepts, updating of Ph.1 critical technologies in light of test results) of LOX and N2O<br />
combined with Propane, Propylene and MAPP.<br />
Deliverables:<br />
Technical Note. Proof of concept experimental investigations (lab. Level).<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2015<br />
Application/Mission: all missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7741<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MPC-850<br />
Hydrogen Storage Technologies<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Page 194 of 227
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MPE-878<br />
New Grid System for Ion Engines (additional activities)<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T505-02MP<br />
Title:<br />
Development of a High Thrust Density cusped Plasma Thruster<br />
The Highly Efficient Multistage Plasma Thruster (HEMPT) has demonstrated an excellent confinement of the plasma within<br />
the ceramic channel walls by means of permanent periodic magnetic multi cusp field system that re<strong>du</strong>ces essentially the<br />
ceramic wall losses and erosion. This activity shall investigate the potential of this technology for high power thrusters and will<br />
focus on the following tasks: Phase I: Interface Definition and Functional Optimization on Prototypes. The Contractor shall<br />
create a functional analytical and numerical model of the thruster. The Contractor shall define as simple as possible<br />
mechanical, electrical, and thermal interfaces for the thruster with self-contained heat evacuation capability. The Contractor<br />
shall confirm the design and functional potential for very substantial mass and cost re<strong>du</strong>ction for thruster and associated<br />
subsystem units. The Contractor shall optimize the thruster design through definition and realization of performance test<br />
campaigns on an evolving series of demonstrators. Phase II: Characterization and Design demonstration on Models. The<br />
Contractor shall assess the widest operational range w.r.t. thrust and specific impulse. The Contractor shall demonstrate the<br />
functional analyses with test results. The contractor shall quantify the thruster operation reliability, the performance stability,<br />
and the lifetime capability. The Contractor shall define and perform an environmental test program on engineering models to<br />
verify their engineering design compatibility with overall launch and flight conditions.<br />
Deliverables:<br />
Technical note/Breadboarding/Test results for at least one HEMPT (capable to operate at thrusts higher than 300mN and<br />
lower than 1N).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 >2009<br />
Exploration and science missions<br />
Application/Mission: (>2012) will be the main objectives for Contract Duration: 24 months<br />
this technology<br />
SW Clause : - Dossier0 Ref.: T-1035<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T505-09MP<br />
Hall-effect Thruster with Multi-Sectional Con<strong>du</strong>ctive Walls<br />
An interesting approach to enhance HET efficiency consists in an innovative discharge channel architecture based on<br />
segmented con<strong>du</strong>cting walls. A variable channel width can contribute to decrease the ion losses at the walls and improve the<br />
ion flow focusing (re<strong>du</strong>cing erosion and sputtering problems), while the use of con<strong>du</strong>ctive materials with low secondary<br />
electron emission yield (with respect to more traditional ceramic insulators) can lead to significant increases of thruster<br />
efficiency (up to 80%, especially for high discharge voltages). The Contractor shall design a high-power HET with a<br />
multi-segmented (at least three) con<strong>du</strong>ctive channel. In addition, the Contractor shall improve the control of the potential along<br />
the channel, either by changing the relative position of the con<strong>du</strong>ctive floating sections to the distribution of the magnetic field,<br />
or by imposing with external power supplies their electric potential. This can contribute to re<strong>du</strong>ce the beam divergence and the<br />
near-wall potential drop, responsible for channel sputtering and erosion. The Contractor shall also incorporate a mo<strong>du</strong>lar<br />
magnetic system to be able to optimise the magnetic configuration. The Contractor shall manufacture a prototype a perform a<br />
complete characterisation test campaign and determine the operational limits of the technology. The Contractor shall<br />
instrument the test facility to be able to quantify the decrease of erosion with respect to standard discharge channels.<br />
Deliverables:<br />
Functional Design Assessment and Justification Report. Design <strong>document</strong> for a high-power HET with multi-segmented<br />
con<strong>du</strong>ctive channel. Demonstrator Characterisation.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 >2009<br />
High power telecommunication missions<br />
(>2012) and interplanetary missions for<br />
Application/Mission:<br />
Exploration and science (>2012) will be<br />
Contract Duration: 24 months<br />
the main objectives for this technology.<br />
SW Clause : - Dossier0 Ref.: T-8119<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-02MP<br />
Title:<br />
Development of advanced EP Thruster characterisation diagnostics<br />
The objectives of the proposed activity are to develop and test Telemicroscopy and Thermographic diagnostic systems<br />
capable of being used for both Hall-effect oftware and Gridded ion engine systems operating with variable Isp and<br />
propellants. In addition to the diagnostics analysis techniques/software tools are also required for the interpretation of test<br />
data. This activity will be accomplished in two phases: Phase 1: Design and development of diagnostics; telemicroscopy<br />
diagnostic design and demonstrator manufacture; thermographic diagnostic design and demonstrator manufacture;<br />
Development of data analysis techniques/SW. Phase 2: Experimental characterisation of HET and Gridded thrusters;<br />
Experimental characterisation of HET/GIE Software in number of European facilities; Analysis of results and comparison<br />
between facilities.<br />
Deliverables:<br />
Advanced diagnostic systems and tools ready to be used in European EP test facilities.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 >2009<br />
Application/Mission: All missions using EP thrusters Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T601-17MP<br />
Development of a Circular Slit Field Emission Thruster<br />
Slit emitter field-emission electric propulsion systems have significantly improved their performances in terms of controllability<br />
and reliability over the last few decades. The desired higher emission levels would require a 25cm total slit. This considerable<br />
length can be achieved either with a cluster of several short linear emitters, or developing a single circular emitter with a radius<br />
of about 4cm. The circular configuration would present several advantages. First of all, it would eliminate emission wing<br />
effects; these perturbations were observed since the earlier works on field-emission, and counteracting measures were taken<br />
intro<strong>du</strong>cing field suppressors or complex compensating negative electrode geometries. A co-axial configuration would<br />
certainly enhance thrust homogeneity and help localizing the thrust vector. Besides, the assembly would be more compact,<br />
and the localization of the various subcomponents (heater, reservoir and feeding lines) could be optimised. Finally, the<br />
neutralizer could be ideally placed on the center axis of the oftware , thus providing optimal neutralization of the ion beam and<br />
re<strong>du</strong>ced divergence angles. The purpose of the proposed activity is: Assess the technological complexity involved in the<br />
manufacturing and machining process of a 1um wide, 25cm long circular slit emitter; Design a complete circular slit 5mN<br />
FEEP assembly (including neutralizer); Manufacture a breadboard model; Perform a complete characterization test campaign.<br />
Deliverables:<br />
Technology assessment report. Design report for a 5mN circular slit FEEP model. Thruster breadboard model.<br />
Characterization test reports.<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 >2009-2010<br />
Application/Mission: EO, Science, .. Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-1013<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-31MP<br />
Title:<br />
Advanced Technologies Demonstrator for Very High-Power Hall-Effect Thrusters<br />
Future Hall-effect SW (HET) generations are technology limited: magnetic circuit, permanent magnets, high temperature<br />
materials, erosion resistant discharge channel, etc...Current high-power HET developments could simultaneously benefit from<br />
these new technologies in terms of mass, volume, lifetime, and performance. This activity will consist on: Phase I: Preliminary<br />
design of a 25 kW Hall-effect oftware (HET) using available scaling rules based on constant plasma density inside the<br />
acceleration channel. Functional analyses and performance simulations will be done to generate the expected performance<br />
envelop in discharge voltage and xenon mass-flow-rate. Based on the results of preliminary mechanical and thermal analyses<br />
it will be identified the technological improvements that would be required to manufacture and test a realistic 25 kW HET<br />
demonstrator while minimising mass, volume, and ceramic channel erosion. Phase II: Trading-off the various potential<br />
technologies and associated manufacturing and assembling issues, solutions to the technological improvements identified in<br />
Phase I will be proposed. In order to be able to test these new technologies, it is proposed to integrate them a smaller-scale<br />
SW as a demonstrator (5 kW power level). The use of a smaller demonstrator solves the problem of available vacuum test<br />
facilities and allows to put forward the added value of these new technologies for current power-class HETs. A specific test<br />
campaign shall be defined and performed for each of the technologies to be demonstrated.<br />
Deliverables:<br />
Technical note (prel. design/performance report and mechanical/thermal analyses for 25 kW HET; critical technol./manuf.<br />
processes; updated design + critical technol. for 5 kW demonstrator; technology demo test plan/results). Demonstrator.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 >2009<br />
High power telecommunication missions<br />
(>2012) and interplanetary missions for<br />
Application/Mission:<br />
Exploration and science (>2012) will be<br />
Contract Duration: 24 months<br />
the main objectives for this technology.<br />
SW Clause : - Dossier0 Ref.: T-968<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T601-42MP<br />
Development of a fuel/oxidiser compatible diaphragm<br />
The Propellant Expulsion Device (PED) as an alternative to propellant management device (PMD) shows advantages form<br />
cost, reliability and general system complexity stand point. Currently such a device is not available in Europe. The interest of<br />
this new proposal is both in the need to provide European space in<strong>du</strong>stry with autonomy with respect to the international<br />
competition and in the compatibility of the proposed material with both Hydrazine and bi propellants which would provide a full<br />
H/W commonality between the two main storable propulsion technologies used in Europe.The proposed activity is focused in<br />
developing a material which is compatible with both hydrazine (N2H4) and its derivatives (MMH, UDMH) and the oxidiser<br />
(MON, NTO) and it is suitable for manufacturing of diaphragms and bladders for spacecraft.<br />
Deliverables:<br />
Demonstration of material formulation feasibility, demonstration of diaphragm manufacturing feasibility and development<br />
testing.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 >2011<br />
All satellites prop. / GMES (e.g. Sentinel<br />
Application/Mission: Contract Duration: 24 months<br />
2,3,4)<br />
SW Clause : - Dossier0 Ref.: T-867<br />
Consistency with Harmonisation<br />
Vessels & High Press Tanks<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-25QC<br />
Reliability of MEMS based pressure sensors<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-27QC<br />
Methodology for complex Micro-Propulsion Systems Space Validation<br />
The overall objective of this 12 months preparatory activity is prepare a formal validation/pre-qualification of these complex<br />
micro-systems via GSTP4 in 2005 by using a representative pre-Qualification Model (pre-QM). The idea is to build a<br />
consortium regrouping the suppliers of complex micro-systems, the final users and <strong>ESA</strong> to obtain consensus for approval of<br />
the approach to be taken for validation/pre-qualification.<br />
The results of these discussion will be reported in technical <strong>document</strong>s that will be distributed to other potential interested<br />
parties like other final users (EADS ST, Alenia, Surrey, ...) or NSAs (SNSB, ASA, ASI, CNES, DLR...) and a Round Table will<br />
be organised to obtain consensus for approval of the approach to be taken for validation of the complex micro-systems via<br />
GSTP4 in 2005 and 2006 (Proposals QCT.LM.GSTP05&06).<br />
Deliverables:<br />
Process <strong>document</strong>ation, critical analysis report, test structures description. Evaluation/reliability testing definition, results and<br />
analysis. Final report. Representative test structures, >1 sample of each critical component.<br />
Current TRL: TRL3 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2009<br />
Application/Mission: microsatellites Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-857<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T609-22MP<br />
Title:<br />
Innovative Gas Storage in Satellites<br />
The overall objective of the proposed work is to develop and verify a Breadboard Demonstrator (BD) for a generic<br />
compression and storage system for space applications. The compressor is based on metal hydride (MH)technology with<br />
integrated thermal control system. The system is specifically targeted towards compression and storage for regenerative fuel<br />
cell systems, but adaptable to other space and terrestrial applications, both for hydrogen, oxygen and other gases where<br />
compression and storage are required.<br />
Deliverables:<br />
Compression & Storage System, Breadboard Demonstrator.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Application: all satellites Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7574<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
6.19 - Structures & Pyrotechnics<br />
<strong>TRP</strong> Reference:<br />
MCS-001<br />
Title: Ultra light Structures - Phase 1<br />
The space community has clearly expressed an interest in lightweight inflatable structures, as a very feasible candidate for<br />
deployment and structural support of large appendages such as solar arrays, sun-shields and reflectors, needed for the next<br />
generation scientific and commercial spacecraft. Previous inflatable structures technology programmes of the European<br />
Space Agency have demonstrated the potential of complex inflatable structures (such as antennas and sunshields), and this<br />
combined with the above defined need, justifies actions foreseen to be taken in this area.<br />
The new interest for inflatable structures is fully explained by the perspectives they offer: with a lower mass and stowed<br />
volume, they may prevent the use of larger expensive launchers. Furthermore, they may offer new capabilities (large<br />
reflectors, large solar arrays, solar sails), which will open a new era in the space exploration. One can indeed imagine small<br />
satellites with large communication antennas, and increased on-board power <strong>du</strong>e to large solar arrays made possible by<br />
inflatable structures.<br />
In order to further mature the inflatable structures towards a spacecraft application, a number of significant technological<br />
problems need to be solved. The final demonstration that such technologies are mastered and ready for a flight programme<br />
implementation is especially difficult. Indeed, for most of them, a validation on ground is not sufficient, or simply impossible.<br />
Therefore, steps to demonstrate feasibility of concept have to follow the logical approach of analysis, ground testing and finally<br />
a flight test demonstrator.<br />
It is the intention that this activity to:<br />
- proof maturity of the relevant technology developments;<br />
- select a flight demonstrator concept, considering not only technical requirements but also launch constraints;<br />
- complete the detailed design of the flight demonstrator;<br />
- manufacture and ground test prove the flight demonstrator (combined analysis and testing).<br />
A successful completion of this program will thus pave the way for a future European inflatable structure flight demonstration<br />
mission. Flight test would be proposed as part of the GSTP.<br />
Deliverables:<br />
Technical datapackage. Demonstrator.<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.: T-617<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title: Ultra light Structures - Phase 2&3<br />
The space community has clearly expressed an interest in lightweight inflatable structures, as a very feasible candidate for<br />
deployment and structural support of large appendages such as solar arrays, sun-shields and reflectors, needed for the next<br />
generation scientific and commercial spacecraft. Previous inflatable structures technology programmes of the European<br />
Space Agency have demonstrated the potential of complex inflatable structures (such as antennas and sunshields), and this<br />
combined with the above defined need, justifies actions foreseen to be taken in this area.<br />
The new interest for inflatable structures is fully explained by the perspectives they offer: with a lower mass and stowed<br />
volume, they may prevent the use of larger expensive launchers. Furthermore, they may offer new capabilities (large<br />
reflectors, large solar arrays, solar sails), which will open a new era in the space exploration. One can indeed imagine small<br />
satellites with large communication antennas, and increased on-board power <strong>du</strong>e to large solar arrays made possible by<br />
inflatable structures.<br />
In order to further mature the inflatable structures towards a spacecraft application, a number of significant technological<br />
problems need to be solved. The final demonstration that such technologies are mastered and ready for a flight programme<br />
implementation is especially difficult. Indeed, for most of them, a validation on ground is not sufficient, or simply impossible.<br />
Therefore, steps to demonstrate feasibility of concept have to follow the logical approach of analysis, ground testing and finally<br />
a flight test demonstrator.<br />
It is the intention that this activity to:<br />
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- proof maturity of the relevant technology developments;<br />
- select a flight demonstrator concept, considering not only technical requirements but also launch constraints;<br />
- complete the detailed design of the flight demonstrator;<br />
- manufacture and ground test prove the flight demonstrator (combined analysis and testing).<br />
A successful completion of this program will thus pave the way for a future European inflatable structure flight demonstration<br />
mission. Flight test would be proposed as part of the GSTP.<br />
Deliverables:<br />
Technical datapackage. On-ground breadboard and demonstrator.<br />
Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL5 by 2010<br />
all spacecrafts (next step should be flight<br />
Application/Mission: Contract Duration: 24 months<br />
demonstration)<br />
SW Clause : - Dossier0 Ref.: T-617<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MCS-002<br />
Electro Active Polymer Actuator<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T505-06MC<br />
Title:<br />
Active Structures for Large Solar Array Panels<br />
A major challenge in designing structures for large solar arrays is the requirement for high fundamental frequencies and the<br />
ability to withstand considerable launch loads. The highest stresses in the structure often occur <strong>du</strong>e to resonances in the<br />
frequency range of the launch loads. Active structures (e.g. actuated by piezo ceramics) can dampen resonances by<br />
closed-loop control. The objective of this activity is to develop S/A panel structures with closed loop control of their dynamic<br />
behaviour.<br />
Deliverables:<br />
Concepts assessment, trade-off and selection. Detailed design of breadboard control system. Detailed design of breadboard<br />
model. Manufacturing and performance test of breadboard. Definition of plan for intro<strong>du</strong>ction into future projects. Development<br />
plan.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010-2012<br />
solar array structures, other large and<br />
Application/Mission:<br />
flexible structures.<br />
Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-555<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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<strong>TRP</strong> Reference:<br />
T601-05MC<br />
Derivation of satellite equipment design and test specifications from random vibration<br />
Title:<br />
environments<br />
Recent experiences from several <strong>ESA</strong> satellite projects show that the approach conforming to ECSS standard E-10-03A<br />
results to requirements frequently contradicting spacecraft hardware measurements. As a result, there is a request from space<br />
in<strong>du</strong>stry and equipment manufacturers that the current approach for the derivation of equipment design and test load<br />
specifications needs to be reviewed and possibly improved. This is the subject of the proposed activity. The objective is to<br />
derive an adequate approach for the specification of equipment quasi-static design loads and random vibration test inputs. At<br />
the same time it will update and improve the currently applied approach derived by Intespace in the 1980’s. This would include<br />
the establishment of a relevant database containing acoustic test results from various spacecraft projects. Also the new<br />
approach will be implemented in a user-friendly tool based on e.g. an Excel spreadsheet. Description of sub-activities and<br />
Planning:1. Review of satellite project <strong>document</strong>ation concerning acoustic test results. Test data collection and preparation for<br />
database supporting the spreadsheet application. 2.Implementation of a limited number of complementary panel tests with<br />
various configurations (e.g. size, mass loading). 3.Development of a rationale for the correlation of equipment unit quasi-static<br />
design and random vibration test loads. 4. Development of the spreadsheet lay-out (preferably Excel) with a flow chart and a<br />
self-explaining user guide. Implementation of the calculation process. 5.Rationale for the reliability of the specification with<br />
probability of the loads compared to the acoustic test data basis.<br />
Deliverables:<br />
User guide, design methodology description.<br />
Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: TRL5 >2008<br />
Application/Mission: all spacecraft/payloads Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-562<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T601-09MC<br />
Establishment of satellite mechanical shock design and verification guidelines<br />
In the past several studies have been performed dealing with different aspects of the mechanical shock problems such as<br />
shock source investigation, shock absorption, shock testing, shock analysis, shock transmission. Although the state of the art<br />
for shock environment prediction and verification in spacecraft have not yet reached the maturity of other environmental<br />
disciplines, recent advances in prediction techniques environment verification and test execution bring a better understanding<br />
of this environment. The experience, gained over the past years, shall be <strong>document</strong>ed as guidelines in order to make this<br />
expertise available for <strong>ESA</strong> community. Two guidelines are proposed: - Guideline for shock environment prediction “Establish<br />
the specification, from LV I/F to unit I/F, resulting in definition of the equipment specification”. –Guideline for the qualification of<br />
units and for the test execution” Equipment Design verification, including SDRA in support to design / qualification, including<br />
testing, including correlation and usage of test results for analytical assessments and qualification purpose “In order to get the<br />
guidelines the following tasks will be done: review of satellite project and study <strong>document</strong>ation concerning mechanical shock;<br />
write the handbook’s chapters with comprehensive presentation of available know-how (shock sources, shock transmission,<br />
equipment sensitivity, shock test facilities, shock specification, shock analysis); and write guidelines/rules and prepare a<br />
release process for the guidelines/rules (working groups/sessions under control/with <strong>ESA</strong>/companies experts).<br />
Deliverables:<br />
Guidelines / handbook.<br />
Current TRL: - Target TRL: TRL5 Application Need/Date: TRL5 >2008<br />
all spacecraft / equipment subject to<br />
Application/Mission: Contract Duration: 12 months<br />
shock tanks<br />
SW Clause : - Dossier0 Ref.: T-562<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T601-11MC<br />
Assessment and Improvement of Dynamic Test Data<br />
Dynamic testing of spacecraft structures and components plays a crucial role in the qualification of the spacecraft as well as<br />
the validation of corresponding dynamic models. Recent studies (RTMVI, Real Time Modal Vibration Identification, EDIS,<br />
Enhancements of Dynamic Identification for Spacecraft) have provided new methods and tools allowing efficient use of test<br />
data to improve the model validation process by considering base reaction measurements, real-time modal characterization<br />
and the use of stochastic analysis to intro<strong>du</strong>ce inherent uncertainty or scatter in the models. These new methods allow a<br />
much greater understanding of the model validation process, yet for the moment have focused primarily on the model in terms<br />
of its capabilities and limitations in representing the physical structure – with little emphasis being placed on the<br />
representativity of the test data itself. The objective of this study is to assess and improve the quality and representativity of<br />
test data by intro<strong>du</strong>cing a set of testing proce<strong>du</strong>res, methods and controls to be used <strong>du</strong>ring test preparation, execution and<br />
post-test analysis and control. Description of sub-activities: review of state of the art in spacecraft testing; development of<br />
improved pre-test methodology and proce<strong>du</strong>res; development of improved post-test proce<strong>du</strong>res and data validation methods;<br />
validation using available spacecraft (“piggyback” application); and final assessment.<br />
Deliverables:<br />
Documentation of proce<strong>du</strong>res.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 >2008<br />
Application/Mission: all spacecraft subject to vibration testing Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-7578<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-14MC<br />
Title:<br />
Random Vibration Environment derivation by Vibro-acoustic simulation<br />
F.E. & SEA numerical simulations methods have been employed to derive the Random Vibration Environment (g2/Hz & grms)<br />
at equipment I/F <strong>du</strong>e to the launch acoustic load. Refined methods to derive also the I/F force (N2/Hz & Nrms) are requested<br />
by Projects in order to avoid both the System over-design and the equipment delta qualification. A parametric analysis, taking<br />
into account not only the mass but also location, panel configurations, boundary conditions and acoustic parameters, would<br />
provide higher confidence in typical random vibration specifications. The objective of this activity is the derivation of the<br />
Random Vibration Environment in terms of I/F acceleration and forces levels <strong>du</strong>e to the Launch Acoustic Load; to provide<br />
analytical and numerical proce<strong>du</strong>res based on FEA and SEA and design guidelines; the identification of driving parameters by<br />
analysis; and the definition of correlation proce<strong>du</strong>res with test data.<br />
Deliverables:<br />
Documentation of proce<strong>du</strong>res, mathematical models.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 >2008<br />
Application/Mission: all spacecraft / equipment. Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-562<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
T601-46MC<br />
Vibro-Acoustic Analysis & Test methods for Large Deployable Structures<br />
Classical rigid solar array vibro-acoustic modelling, analysis and test correlation has been developed up to a certain maturity,<br />
however such methods are not directly transferable to thin film structures, closely packed radiators, SAR antennas etc. and<br />
hence the vibro-acoustic FEM/BEM analysis, testing and their correlation of large-area light-weight structures need further<br />
development. The objective of this activity is to define a Finite Element and Boundary Element modelling methodology and<br />
tuning for mechanical loads applied to thin, flexible deployable structures, studying deterministic and random techniques,<br />
taking into account fluid structure interactions, non-linear behaviour, effect of thin airgaps, effect of membrane stretching etc;<br />
and the development of instrumentation techniques for subsystem vibration and acoustic testing. It will also include the testing<br />
and correlation of a full size structural model, representative of vibro-acoustic parameters. Several tasks have been defined:<br />
state-of-the-art review on analysis and testing methods; implementation of modelling technique in FEM/BEM code; definition<br />
of analysis/test methodology; parametric breadboard design and test plan; and analysis, test and correlation of vibration and<br />
vibroacoustic loads.<br />
Deliverables:<br />
Documentation and breadboard.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 >2010<br />
solar array structures, deployable<br />
Application/Mission: radiator structures, deployable flat Contract Duration: 18 months<br />
antenna structures etc.<br />
SW Clause : - Dossier0 Ref.: T-7896<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
T601-50MC<br />
Advancement in Thermo-Elastic Distortion Verification Methods for spacecraft<br />
Title:<br />
structures<br />
The objectives of the proposed activity are the following:<br />
- Improvement of materials modeling, especially composites and other advanced materials.<br />
- Improvement of numerical simulation of materials, components and assemblies of structures by using existing FEM software<br />
tools, but including in the mathematical models the specific aspects of materials and components. This shall consider<br />
non-linear and stochastic analysis.<br />
- Application of new measurement and monitoring techniques, such as ESPI (Speckle interferometry), laser radar and optical<br />
fibre sensing (Bragg grating), thermography...<br />
The activity will consist of two phases:<br />
Phase 1<br />
- short review of current state of the art with regard to analysis, control and test methods;<br />
- Modeling of composite materials, components, joints and assemblies. Typical hypothesis, such as the linearity of thermal<br />
expansion, shall be investigated, as well as the effects of anisotropy and large temperature ranges;<br />
- Measurement of material properties on coupons, including expansion coefficients, stiffness, thermal con<strong>du</strong>ctivity and all<br />
relevant parameters identified previously;<br />
- Verification of simulation tools and methods on coupons and joints;<br />
- Establishment of measurement uncertainty requirements and stochastic character of simulation tools;<br />
- Establish guidelines for predicting thermo-elastic distortions. In addition to methodologies for improved modeling, these<br />
guidelines shall also consider making recommendations on the need to perform material and component level tests;<br />
Phase 2<br />
- Definition of a breadboard representative of the complexity of a scientific instrument.<br />
- Modeling and prediction.<br />
- Stochastic (and non-linear) analysis<br />
- Definition of test set-up and selection of measurement technique<br />
- Correlation<br />
Where necessary, updating of guidelines established in Phase-1, and extension of guidelines to include recommendations on<br />
performance of system level test verification methods.<br />
Deliverables:<br />
Design and verification guidelines; test coupons and breadboard; modeling proce<strong>du</strong>res.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010-2012<br />
Application/Mission: Engineering tools applicable to all S/C Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-543<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
<strong>TRP</strong> Reference: T605-11MC<br />
Title:<br />
Non-Contact Measurements of Membranes<br />
Inflatable Space Structures very often include a stretched membrane. Static and dynamic measurements of such membranes<br />
<strong>du</strong>ring testing remain a challenge <strong>du</strong>e to detrimental added mass and stiffness of the classical instrumentation. The objective<br />
is to develop a non-contact method for measuring static and dynamic shapes of membrane spacecraft structures. This implies<br />
the review and evaluation of available methods; the selection and development of an innovative method; the demonstration on<br />
a breadboard model.<br />
Deliverables:<br />
Documentation and breadboard.<br />
Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
Application/Mission:<br />
thin membrane structures, including<br />
inflatable structures (e.g. schields,<br />
booms, solar sail); EO/Sci missions.<br />
Contract Duration:<br />
12 months<br />
SW Clause : - Dossier0 Ref.: T-7896<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Reference:<br />
T605-12MC<br />
Improvement of force limited vibration testing methods for equipment/instrument unit<br />
Title:<br />
mechanical verification<br />
The mechanical vibration testing approaches (sine and random) currently applied to satellite equipment / instrument units are<br />
in general very conservative and might result to severe over-testing of the units compared to real flight environments. The<br />
reasons for this are the different interface conditions applicable to the system and the test configuration (when the unit is<br />
hard-mounted to the shaker table). Consequently these test approaches lead also to over-design of the units and therefore<br />
significant mass penalties. Force limited vibration testing has been intensively investigated in NASA since many years. The<br />
methods aim at establishing interface force estimates for the case when the unit is mounted on a flexible satellite support<br />
structure rather than the shaker and to limit the test input for the unit test to these force estimates. The experiences in force<br />
limited vibration testing are still very limited in Europe. Further investigations of this subject should increase the relevant<br />
knowledge base and should contribute to the establishment of an <strong>ESA</strong> mechanical testing handbook covering the specific<br />
aspects of force limited vibration testing. The objectives are to investigate the influence of the support structure mechanical<br />
impedance on the random vibration environment and the execution of unit random vibration test on electro-dynamic shakers;<br />
to identify relevant methods to more accurately derive the interface force limits (e.g. direct measurement at system level,<br />
semi-empirical, analytical) and to assess their respective accuracy; to develop simplified but nevertheless adequate models<br />
for the simulation of coupled system conditions; to verify the developed approaches by analytical and experimental means<br />
(representative of existing equipment structures) and to establish the relevant input for the <strong>ESA</strong> Mechanical Testing<br />
Handbook.<br />
Deliverables:<br />
Technical notes (incl. identification of methods to more accurately derive the interface force limits, models for the simulation of<br />
coupled system conditions, verification of the developed approaches by analytical and experimental means).<br />
Current TRL:<br />
Target TRL:<br />
Application Need/Date: TRL5 (operational method)<br />
TRL2<br />
TRL3<br />
by 2008<br />
Application/Mission: Engineering toolsapplicable to all S/C Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-562<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T605-20MC<br />
Advancement of Mechanical Verification Methods for non-linear spacecraft structures<br />
For the purpose of spacecraft structure design development and verification by analysis the structures are in general a-priori<br />
assumed to behave linear. Analytical predictions include static & dynamic analyses at satellite level but also launcher/satellite<br />
coupled dynamic loads analyses (CLA) to predict flight loads for specific satellite configurations. However, experience has<br />
shown that spacecraft structures can exhibit highly non-linear behaviour (e.g. <strong>du</strong>e to backlash, joint gapping, rattling) and the<br />
consequences of their dynamic effects can significantly affect the design verification proce<strong>du</strong>res, in particular: to properly<br />
evaluate flights loads with linearised models used in the CLA; the general performance of dynamic verification tests; to<br />
demonstrate adequate coverage of non-linear dynamic effects in satellite verification tests. As a result, the presence of such<br />
effects in spacecraft structures increases significantly the complexity of the mechanical verification process (analysis and<br />
testing).The main objectives of this activity are: to review satellite design and verification test <strong>document</strong>ation in order to<br />
identify relevant structure verification problems related to non-linear dynamic effects; to develop strategies for handling<br />
non-linear dynamic effects within linear CLA models and to adequately convert the related CLA predictions into dynamic<br />
verification test specifications; to analytically investigate the impact of spacecraft structure non-linearities on the verification<br />
test performance (including non-linear dynamic effects resulting from e.g. shaker); to verify the proposed approaches with a<br />
bread-board model (using available space hardware as far as possible); and to finally establish guidelines and<br />
recommendations for the identification of potential structural non-linearities, the assessment of their effects and how to treat<br />
them <strong>du</strong>ring the spacecraft structure design and development and the verification test phase.<br />
Deliverables:<br />
Documentation and breadboard.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2010<br />
Application/Mission: Engineering tools applicable to all S/C Contract Duration: 20 months<br />
SW Clause : - Dossier0 Ref.: T-543<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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6.20 - Thermal<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MCT-694<br />
MST Compressor for JT cooler<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: MCT-698<br />
Title:<br />
Mini And Micro Heat Pipes<br />
In order to re<strong>du</strong>ce volume and mass, there is a clear tendency for S/C electronics to go to denser packing of high dissipating<br />
units, while at the same time the heat dissipation of such units increases. To avoid hot spots, to optimise the thermal design<br />
and to keep the junction temperatures of critical components within acceptable limits, the use of mini & micro heat pipes can<br />
greatly improve the thermal design. For terrestrial applications the use of mini and micro heat pipes has shown to strongly<br />
improve the thermal design of electronic components (e.g. laptops, amplifiers). Such mini and micro heat pipes are judged to<br />
also be very beneficial for the thermal design of spacecraft units (e.g. high dissipating electronic units) and mini/nano satellites<br />
where small high-efficient thermal devices will allow to improve and optimise the design. The objective of this activity is to<br />
develop mini/micro heat pipes for use onboard spacecraft, taking advantage of the terrestrial heritage to the maximum extent<br />
possible; to build heat pipe demonstrators and to submit them to a full performance test programme.<br />
Deliverables:<br />
Fully tested heat pipe demonstrators with associated technical <strong>document</strong>ation.<br />
Current TRL: TRL2-3 Target TRL: TRL4 Application Need/Date: TRL5 by 2012<br />
High dissipating units on S/C (telecom,<br />
Application/Mission: EO, science); minisatellites; small telecm Contract Duration: 24 months<br />
platform.<br />
SW Clause : - Dossier0 Ref.: T-7875<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Heat Pipes & Two phase loops<br />
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<strong>TRP</strong> Reference:<br />
Title:<br />
MCT-700<br />
Regenerator Technology for 10-100K Stirling and Pulse Tube Coolers<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: MCT-701<br />
Title:<br />
Maxi compressor for low temperature cooler<br />
Objective of the proposed activity is the development of a compressor compatible with the 10K cooler and various other<br />
coolers.<br />
A demonstration model of the 10K Cold-finger has already been developed by Astrium UK for the US Air Force, using up to<br />
now 4 existing compressors. However for space applications, one large single compressor is required.<br />
The proposed compressor will be based on the design for the Miniature Pulse Tube cooler compressor currently developed by<br />
Astrium/RAL. The activity will cover the design, manufacture and test of a breadboard model of a large cooler compressor.<br />
The build standard will be such as to support full performance evaluation and verify capability to survive launch and operate in<br />
either a Space Station or satellite environment.<br />
The possible utilization of this large compressor goes beyond the 10K Cooler, as an example it can also work as a basis for<br />
other systems, e.g. a Large Heat Lift Pulse Tube cooler.<br />
The proposed activity will be followed by a 400kE GSTP project, called “Development of a 10K Cooler EQM”, referred to as<br />
G00/B46.MCT-003, aiming at developing a 6-10K cooler, with a cooling power of 45 mW at 10K and a zero load temperature<br />
of 6K (goal 4K). This latter activity will be based on the previous developments of the proposed Maxi Compressor and the<br />
previous work on 10K coolers. Future Earth Observation and Scientific instruments (e.g. XEUS) will benefit from this project.<br />
Deliverables:<br />
Technical datapackage (design, manufacture and test). Breadboard model of a large cooler compressor.<br />
Current TRL: TRL2-3 Target TRL: TRL5 Application Need/Date: TRL5 by 2012<br />
cooling of science and earth observation<br />
instruments as well as of future<br />
Application/Mission:<br />
telecommunication payloads<br />
Contract Duration: 27 months<br />
(Supercon<strong>du</strong>ctor applications)<br />
SW Clause : - Dossier0 Ref.: T-7876<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
MCV-882<br />
Thermal Concept Design Tool<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : Open Source Code Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-24MC<br />
Title:<br />
Novel, Composite Wicks (for two-phase loops)<br />
The present generation of capillary wicks used in two-phase loops suffer from a number of limitations. It is therefore necessary<br />
to improve the wick design by looking into new methods to pro<strong>du</strong>ce wick structures (e.g. based on the lost wax method), to<br />
develop methods to reach a graded porosity wick or to investigate methods to pro<strong>du</strong>ce composite wicks consisting of e.g. an<br />
outer layer of fine pore size metallic wick with an inner core of plastic wick assuring a thermal decoupling. Based on such<br />
novel type wicks, current limitations of two-phase loops (limited pumping capabilities under 1-g, need for subcooling, etc.) can<br />
be solved. This activity will develop novel types of wick structure for the next generation two-phase loops, perform an<br />
extensive trade-off taking into account all possible wick materials and wick pro<strong>du</strong>cing methods, supported by experimental<br />
activities, and test selected wick structures in a realistic two-phase loop.<br />
Deliverables:<br />
Established manufacturing method for novel wicks, tested wick structures, associated <strong>document</strong>ation.<br />
Current TRL: TRL1-2 Target TRL: TRL4-5 Application Need/Date: TRL5 >2009<br />
Application/Mission: Telecom, EO, Science Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7874<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T601-39MC<br />
Title:<br />
Cryogenic Harness for Detector Arrays<br />
There is a major need to re<strong>du</strong>ce the cryogenic cooling power needed by a detector array, leading to significant re<strong>du</strong>ctions in<br />
payload mass, power and complexity. This in turn leads to a corresponding re<strong>du</strong>ction in the susceptibility of detector arrays to<br />
EMI and microphonics. Current cryogenic harnesses have a number of problems. The electrical requirements on future<br />
harnesses will be the same as for current ones. However, new harnesses will need to carry much larger numbers of signals,<br />
and have higher immunity to the presence of magnetic fields. In addition, there has been no significant attempt to model the<br />
harness architecture and accurately predict the coupled electromagnetic and thermal performance of the harness. This activity<br />
focus on the design, development and testing of a cryogenic harness using new materials and manufacturing techniques. It<br />
will also develop an electrical/thermal model to support the design. The final harness will also be tested with S-Cam 4 at<br />
ESTEC.<br />
Deliverables:<br />
Fully tested harness plus associated <strong>document</strong>ation, delivered for further testing with S-Cam 4 at ESTEC SCI.<br />
Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: TRL5
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
6.22 - Components<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
03/QCT-001<br />
Evaluation Thermistors<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: GAD 2.06 A<br />
Title:<br />
Design And Evaluation Initiative For Rad Tolerant Components<br />
ST Microelectronics has been for long the leading European manufacturer for space qualified radiation tolerant standard logic<br />
pro<strong>du</strong>cts. In order to make use of their far greater technological capabilities being among the top 10 semicon<strong>du</strong>ctor<br />
manufacturers world wide, this initiative shall support the evaluation of commercial technologies & processes in the ST<br />
foundry and the radiation hardening of a series of selected linear and digital components currently unavailable as space level<br />
pro<strong>du</strong>ct from European sources.<br />
Deliverables:<br />
Samples. Technical note, test results.<br />
Current TRL: TRL3-4 Target TRL: TRL5-6 Application Need/Date: TRL5 by 2009<br />
Application/Mission: all missions Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.: T-255<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: GAD 2.06.D<br />
Title:<br />
Study Of RF Compression & Overdrive on Components<br />
The objective of this activity will be to get a better understanding of the effect of RF overdrive and compression on microwave<br />
devices, identify derating recommendations and derive safe operating area for some European devices. To this end, a set of<br />
RF life testing will be carried out, associated with advanced electrical characterisation and in-situ monitoring. Modeling of the<br />
effect and degradation mechanism will be contemplated.<br />
Deliverables:<br />
Samples, test results, derating requirements, procurement specifications<br />
Current TRL: TRL3-4 Target TRL: TRL5-6 Application Need/Date: TRL5/6 by 2009<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-283<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference: GAD 3.04<br />
Title:<br />
Testing of Chip Scale Package (CSP)<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: GAD 4.02<br />
Title:<br />
HDI demonstration Mo<strong>du</strong>le with CSP / ECR32 MCM Validation<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
QCA-004<br />
Utilisation of the Proton Irradiation Facility (PIF) for Components Studies<br />
Deliverables:<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: N/A<br />
Application/Mission: all missions Contract Duration: 60 months<br />
SW Clause : - Dossier0 Ref.: T-7888<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
QCA-005<br />
Utilisation of the Radiation Effects Facility (RADEXF) for Components Studies<br />
The Heavy Ion Irradiation Facility (JYFL) at the Department of Physics of the University of Jyväskylä, Finland, has been<br />
utilised by <strong>ESA</strong> for several extended radiation test campaigns in the last years. First to determine the principle capabilities<br />
and suitability of this facility to support irradiation tests on EEE components and then in a comparative programme to perform<br />
a correlation between several European and US accelerator facilities. These test campaigns have been increasingly<br />
successful and pro<strong>du</strong>ctive, confirming its high energy beam quality and usefulness for EEE component testing. Following the<br />
approach established for other <strong>ESA</strong> radiation test facilities (HIF (B) and PIF (CH)) it is proposed to utilise JYFL as a state of<br />
the art test facility providing urgently needed complementary test capabilities and additional test capacity to <strong>ESA</strong> and the<br />
European Space In<strong>du</strong>stry.<br />
After a short (1 year) set-up phase JYFL shall provide under the proposed contract (five years contract, 110kE/year) at least<br />
480 hours of beam time per year specifically for the characterisation and testing of EEE components. This shall include the<br />
cost of 240 hours of priority beam time for <strong>ESA</strong>, associated support, maintenance and nominal test area upgrades. These<br />
240 hours will be primarily utilised by <strong>TRP</strong> activities related to component research and development. In addition it will<br />
reserve a minimum of 240 hours of extra beam time for <strong>ESA</strong> projects and European Space In<strong>du</strong>stry users at preferential<br />
hourly rates (subject to separate purchase orders).<br />
Deliverables:<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: N/A<br />
Application/Mission: all missions Contract Duration: 60 months<br />
SW Clause : - Dossier0 Ref.: T-7888<br />
Consistency with Harmonisation<br />
N/A<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: QCT-006<br />
Title: Component for high power conditioning applications (SiC, GaN, )<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-01QC<br />
Radiation Test methodology for Optocouplers Devices for Space Applications<br />
Following the results of the "opto2000" study, several unresolved issues need to be further investigated: identification of the<br />
main degradation mechanism in the different parts of the optocoupler; identification of possible annealing effects in<br />
non-ionizing degradations; and comparison between protons and sequential neutrons/dose irradiations on the same devices.<br />
Deliverables:<br />
Documentation and reports.<br />
Current TRL: TRL3-4 Target TRL: TRL5-6 Application Need/Date: TRL5/6 by 2009<br />
Application/Mission: all missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-256<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-05QM<br />
Carbon Nanotube based composite Material<br />
Nanotubes have many potential applications, making use of either 1 indivi<strong>du</strong>al nanotube (electronic device) or an important<br />
amount of nanotubes (thermal, electrical, mechanical applications). Taking into account that mastering the distribution of the<br />
nanotube will enable many of the potential applications and that distributing nanotubes is a pre-requisite for any other<br />
application, this study aims at developing means to: a) Distribute evenly small volume fraction of nanotubes into a matrix<br />
(random orientation). This would increase cristallinity of a resin, strengthen a metal or bridge micro-cracks in a ceramic. b)<br />
Align high volume fraction of nanotubes into a matrix. Very high specific mechanical properties, very high thermal<br />
con<strong>du</strong>ctivity... could be achieved with such materials. The matrix could possibly be organic, metallic or even ceramic. The<br />
adequate distribution of the nanotubes will be assessed by microstructural investigation, elastic constant measurement, depth<br />
sensing indentation, electrical con<strong>du</strong>ctivity, coefficient of thermal expansion or any other suitable indirect measurement<br />
method.<br />
Deliverables:<br />
Technical notes; Samples of evenly distributed nanotubes into a matrix; Sample of aligned nanotubes (into or out of a matrix).<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010-2012<br />
high demanding applications (structural,<br />
Application/Mission: Contract Duration: 18 months<br />
thermal, electrical)<br />
SW Clause : - Dossier0 Ref.: T-1435<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
Carbon Nanotube based composite Material: additional testing<br />
Nanotubes have many potential applications, making use of either 1 indivi<strong>du</strong>al nanotube (electronic device) or an important<br />
amount of nanotubes (thermal, electrical, mechanical applications). Activity T608-05QM aims at developing means to: a)<br />
Distribute evenly small volume fraction of nanotubes into a matrix (random orientation). b) Align high volume fraction of<br />
nanotubes into a matrix. The original activity budget allowed only 2 materials to be investigated. However, the first phase of<br />
the contract has shown that this is insufficient, <strong>du</strong>e to the large number of candidate materials. Therefore, a first CCN has<br />
been placed to perform evaluation and characterisation of a third material. In addition, a second CCN is proposed to work on<br />
the processing of SiC matrix reinforced with carbon nanotubes and address the possibility offered by the high electrical<br />
con<strong>du</strong>ctivity measured.<br />
Deliverables:<br />
Technical notes; Samples of evenly distributed nanotubes into a matrix; Sample of aligned nanotubes (into or out of a matrix);<br />
SiC matrix reinforced with carbon nanotubes.<br />
Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010-2012<br />
High demanding applications (structural,<br />
Application/Mission: Contract Duration: 18 months<br />
thermal, electrical)<br />
SW Clause : - Dossier0 Ref.: T-1435<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-24QC<br />
WALES: Wafer Level Encapsulation for micro-Systems<br />
WALES Wafer Level Encapsulation for micro-Systems will first address the possible lid materials to be used for 0-level<br />
packaging (or equivalent lid material when no formal lid is expected). Associated mounting/gluing/soldering techniques and<br />
interfacing materials (solder, polymers) will be reviewed and selected. This exercise will de done both for Non-RF<br />
micro-systems and for the specific case of RF MEMS for which packaging is known to have significant influence on the device<br />
performance.<br />
Last but not least, WALES will assess the need for associated getters to be processed or reported <strong>du</strong>ring wafer level<br />
encapsulation. The contractor will perform a survey to identify and justify the need for getter, the types of micro-system<br />
requiring such getter will be listed as well as the type of getter needed and solutions on how to procure/process and<br />
implement this getter into the 0-level encapsulation. Demonstration by minimum processing will be required.<br />
Deliverables:<br />
Documentation (0-level packaging concept, lid, assembly materials for RF/non-RF systems). >20 wafer-level packaged<br />
devices (10 RF, 10 Non-RF, 5 from each fabrication batch); >3 samples of a wafer-level packaged micro-system containing a<br />
getter.<br />
Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5/6 by 2008<br />
Application/Mission: all missions Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.: T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T608-28QC<br />
Title:<br />
MEMSRAD: MEMS sensitivity to space RADiation<br />
The work to be carried out <strong>du</strong>ring MEMSRAD will be split into 3 separate sub-tasks to be performed. The first responsibility<br />
will be to write the basic requirements for testing MEMS devices. Both MOTS (MEMS Off The Shelf) and micro-systems still in<br />
the open research shall be addressed. The purpose of this specification is to define the requirements for testing<br />
semicon<strong>du</strong>ctor based MEMS devices, including sensing elements and microelectronic circuits. The scope includes detailed<br />
discussion of the charged particle environment in space, the physics of radiation effects on MEMS devices and materials,<br />
including Total Ionising Dose (TID) effects, Single Event Effects (SEE) and displacement damage effects. The outcome of this<br />
work will result in a general radiation evaluation guideline. However, because the different requirements of each project give<br />
rise to very different guidelines, no attempt shall be made here to specify or quantify formal technical requirements in terms of<br />
radiation tolerance and associated pass/fail criteria. This <strong>document</strong> shall contain information regarding radiation effects<br />
prediction and general radiation test methods related to the MEMS. The <strong>document</strong> shall be submitted to in<strong>du</strong>stry, other NSAs,<br />
research centres for approval. A one-day Round Table shall be organised to discuss the <strong>document</strong> and obtain consensus for<br />
approval. <strong>ESA</strong> will then decide how this <strong>document</strong> shall be formalised (ESCC specification or ECSS Level 3).<br />
Deliverables:<br />
Draft Guidelines for MEMS radiation testing requirements, test campaigns plans/reports. Public./present. at radiation/MEMS<br />
workshop/conferences (RADECS, NSREC, <strong>ESA</strong> MNT Round table...). Prep./implem. of obtained results on ESCIES. Final<br />
Report.<br />
Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: N/A<br />
Application/Mission: all S/C Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-267<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-29QC<br />
Radiation testing of candidate microelectronic components for space applications<br />
Radiation Effects on semicon<strong>du</strong>ctor components are process and design dependent. New component types and<br />
representative test structures for new process technologies or incorporating novel design techniques are tested in ground<br />
facilities for their behaviour under the influence of radiation.<br />
Deliverables:<br />
Radiation test data on Single Event Effects, Total Ionising Dose and Displacement Damage Susceptibility of semicon<strong>du</strong>ctor<br />
components foreseen for space applications. Associated test methods and capabilities.<br />
Current TRL: TRL3 Target TRL: TRL4-5 Application Need/Date: TRL5/6 by 2009<br />
Application/Mission: all S/C Contract Duration: 36 months<br />
SW Clause : - Dossier0 Ref.: T-267<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T608-34QM<br />
Title:<br />
Performance benchmarking of European GaN epitaxial wafer suppliers<br />
The objective of this activity is the assessment and benchmark comparison of the RF and reliability performance of GaN<br />
HEMTs manufactured using European epitaxial wafer sources.<br />
GaN is a strategic technology that has the potential to revolutionise next generation space based payloads. Applications<br />
include miniaturised high power electronic equipments (e.g. solid state power amplifiers, X-ray detectors, highly robust<br />
receiver front-ends, local oscillator sources for mm-wave/sub mm-wave radiometers) that are capable of operating at extreme<br />
temperatures or in harsh environments. The availability of high quality epitaxial wafer material is a prerequisite for pro<strong>du</strong>cing<br />
high performance devices. <strong>ESA</strong> has previously funded epitaxial wafer development work through IMEC (Athena and Epi-GaN<br />
programmes). An independent assessment and benchmarking exercise is now needed to assess the performance of IMEC<br />
material against other European suppliers. This will allow <strong>ESA</strong> to prioritise future investments needed to establish a European<br />
supply chain for GaN component technology.<br />
It is hence proposed for this activity that GaN epitaxial wafers (fabricated on SiC substrates) will be procured from European<br />
suppliers and from a state of art US/Japanese source to allow comparison of wafer performance within Europe and the rest of<br />
the world. Device fabrication will be undertaken by a single company using a common process control monitor and transistor<br />
test mask for each wafer. DC measurements and RF measurements (small signal and large signal) will then be made to<br />
derive basic performance parameters. This will be followed by a preliminary reliability assessment, with the aim of identifying<br />
likely causes of failure mechanisms. Upon completion, this work will allow identification of the optimum wafer supply route<br />
within Europe and allow <strong>ESA</strong> to independently assess the performance of the epitaxy suppliers in Europe. The data gathered<br />
from this work will be used to launch a major reliability improvement and technology transfer initiative involving manufacturing<br />
in<strong>du</strong>stry. Therefore this proposed <strong>TRP</strong> activity will form the foundation route for establishing a space qualified GaN component<br />
supply chain by 2009-2010. The following tasks are foreseen:<br />
1.- Wafer procurement and test mask design; 2.- Device processing; 3.- DC and RF assessment; 4.- Preliminary reliability<br />
assessment; 5.- Analysis and benchmarking of results.<br />
Deliverables:<br />
Hardware samples, test results, technical notes comparing and contrasting the results obtained from European epitaxial wafer<br />
suppliers. Requirements specification for Wafer supplies to target.<br />
Current TRL: TRL2 Target TRL: TRL5 Application Need/Date: TRL5 =< 2009<br />
Supported through CTB microwave<br />
Application/Mission: Contract Duration: Contract <strong>du</strong>ration 12 months<br />
component work<br />
SW Clause : - Dossier0 Ref.: T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-36QC<br />
SRAM based FPGA for space applications<br />
Contrary to antifuse type Field Programmable Gate Arrays (FPGA), SRAM based types offer the possibility of in-system<br />
reconfiguration. Radiation hardened FPGA types using SRAM based configuration programming are currently being<br />
intro<strong>du</strong>ced /developed for space applications by the European manufacturer Atmel. While the prospects of exploiting this<br />
additional flexibility potential for re-configurable payload systems are seriously being considered there is still very limited<br />
experience with the safe utilisation of these features. This activity shall determine (1) if current Pro<strong>du</strong>ct Assurance<br />
requirements and practices for on board SW reconfiguration are applicable and sufficient for FPGA configuration data or if<br />
modified/additional provisions are required and (2) which methods and requirements are applicable to establish conformance<br />
of specific and dynamic FPGA reconfigurations with fixed system constraints <strong>du</strong>ring the application development process.<br />
The effectiveness of the proposed method(s) and requirements shall be suitably demonstrated.<br />
Deliverables:<br />
Study report and draft requirements<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: TRL8 by 2009-2010<br />
Application/Mission: All missions Contract Duration: 12 months<br />
SW Clause : - Dossier0 Ref.: T-7795, T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
On-Board Payolad Data Processing<br />
<strong>TRP</strong> Reference: T608-37QC<br />
Study of long term parametric drifts of EEE components for inclusion in component<br />
Title:<br />
detail specifications and worst case analysis<br />
Worst case analysis is a typical requirement of the <strong>ESA</strong> projects and is based on the known drift of EEE components <strong>du</strong>ring<br />
the mission life. These drifts are important as they help establish the system performance parameters with in the given<br />
mission profile. However, the attempted to re-validate the current drift values cited in the <strong>ESA</strong> PPS 01 301 and include these<br />
in the Worst case analysis standard envisaged that the values listed are based on a series of assumptions and activation<br />
energies that may not be applicable today. Additionally, as an outcome of an ECSS working group on how to approach the<br />
calculation of the Worst Case limits, it emerged that, inspite of <strong>ESA</strong> listing some drift paremeters in their specifications,<br />
in<strong>du</strong>stry wished to use other figures and for some technologies(drift parameters are technology, process and in some cases<br />
even manufcaturing line dependent) there was no easily obtainable referenece data. With the present activity it is now<br />
proposed to launch a study that determines what data resides with space/aerospace/automotive/commercial procurement<br />
agent, user and manufacturer. This study will then take existsing available data and provide clear dirt formulae for use in an<br />
ECSS standard. In addition where data does not exist it will define the missing program of work.<br />
Deliverables:<br />
Technical note (incl. reviewed - consistent - data to submit to ECSS for approval and inclusion in the ESCC abd ECSS<br />
<strong>document</strong>s). Work plan for missing data retrieval.<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: TRL9 by 2010<br />
Application/Mission: All missions Contract Duration: 24 months<br />
SW Clause : - Dossier0 Ref.: T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-38QC<br />
Survey of available micro and nanotechnology<br />
Nanotechnology is an advanced technology that has received a lot of attention for its ability to make use of the unique<br />
properties of nanosized materials. Nanotechnology is capable of manipulating and controlling material structures at the nano<br />
level (a nanometer is equal to one millionth of a millimeter) and offering unprecedented functions and excellent material<br />
properties. Nanotechnology consists of the “top-down approach” and the “bottom-up approach.” In the former approach, the<br />
sophistication of fine processing technologies, such as semicon<strong>du</strong>ctor manufacturing, can lead to the processing of nanosized<br />
fine structures. In the bottom-up approach, self-organization properties inherent in materials can be utilized to assemble<br />
nanosized fine structures from the atomic or molecular levels. Nanotechnology, including nanostructured material metrology to<br />
accurately determine physical properties at the nanolevel, is considered a strategic technological area that goes beyond<br />
conventional technologies, potentially leading to a paradigm shift in new in<strong>du</strong>strial technologies.<br />
Nanotechnology is regarded world-wide as one of the key technologies of the 21st century. Nanotechnological pro<strong>du</strong>cts and<br />
processes hold an enormous economic potential for the markets of the future. The pro<strong>du</strong>ction of ever smaller, faster and more<br />
efficient pro<strong>du</strong>cts with acceptable price-to-performance ratio has become for many in<strong>du</strong>strial branches an increasingly<br />
important success factor in the international competition. The technological competence in nanotechnology will be a<br />
compelling condition to compete successfully with better proce<strong>du</strong>res and pro<strong>du</strong>cts on high technology markets in the future.<br />
Due to its interdisciplinary cross-section character, nanotechnology will affect broad application fields within the ranges of<br />
chemistry/materials, medicine/life sciences, electonics/information technology, environmental and energy engineering,<br />
automotive manufacturing as well as optics/analytics and precision engineering in various ways. The convergence of different<br />
fields like microelectronics, chemistry, physics, and biology will permit to create the emerging nanoscale functions in coming<br />
years.<br />
The future European space missions should get benefit of this fantastic 21st century Nanotechnology revolution. In particular<br />
the future evolutions of the coupling of micro and nano world interdisciplinary applications pushes towards the possibility of<br />
development of “Smart Systems”.<br />
The CTB MNT Working Group has proposed to carry out a technology survey on Nanotechnology. The so established position<br />
paper will be a strategic <strong>document</strong> for the development of Nanotechnologies for space sector, including the technological and<br />
in<strong>du</strong>strial perspective, the state of the art outside and inside the space sector, the impacted in<strong>du</strong>strials sectors, the potential<br />
contribution of nanotechnologies, the axes of collaboration to favour development of nanotechnologies, i.e. technological key<br />
issues and competence centers well positioned in the field of interest, a “Nanotechnology Roadmap”.<br />
Major tasks will include: 1.Survey of Nano technologies on : Structural materials, Sensors, Nanoelectronics and Computing; 2.<br />
Identification of potential applications for space sector: transportation vehicles, space crafts, pay loads, probes, etc.; 3.<br />
Elaboration of preliminary requirements ; 4. Identification of potential manufacturers for Nano technologies; 5. Establishment<br />
of First “Nanotechnology Roadmap for European space applications”.<br />
The roadmap should in particularfocus on short/mid/long term issues. At short mid term (
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-39MC<br />
Nanotube re-inforced structural materials for spacecraft applications<br />
With strength and stiffness properties several 100 times better than that of steel and con<strong>du</strong>ctivity better than copper, Carbon<br />
Nanotubes (CNT) have extraordinary intrinsic electrical and mechanical properties making them potentially attractive materials<br />
for use in lightweight spacecraft structures and subsystems. Research on the possibility of using such materials for improving<br />
the properties of known materials such as Carbon Fiber Reinforced Plastics (CFRP), has been performed, and the results<br />
indicate that some improvement is indeed possible.<br />
The objectives of the proposed activity are to identify and investigate possible improvement of spacecraft structural materials,<br />
near term as well as long term. For what concerns near term the work shall focus on the reinforcement of the CFRP resin<br />
material. Realistic improvements shall be defined based on literature data and specially manufactured test samples, and shall<br />
address improvements related to:<br />
- tensile, compressive and shear (ILS) strength;<br />
- stiffness;<br />
- structural damping;<br />
- failure mechanisms;<br />
- con<strong>du</strong>ctivity;.<br />
Relevant manufacturing methodologies shall be investigated and <strong>document</strong>ed.<br />
For what concerns long term, (>2015) possible applications of CNT in spacecraft structures shall be evaluated. This shall<br />
include the identification of possible new materials, e.g. development of new CNT reinforced fibres and resins, and their<br />
possible application areas, including highly loaded spacecraft structures, lightweight flexible deployable and inflatable<br />
structures, membranes etc.<br />
In addition, the perspective of availability of CNT for European activities shall be considered taking into account the required<br />
European non-dependence target, and a related survey <strong>document</strong> shall be pro<strong>du</strong>ced.<br />
Deliverables:<br />
Overview of CNTs and their application as reinforcing element in CFRP structures, test reports, test specimen.<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5/6 >2010<br />
Application/Mission: All spacecraft missions Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-1435<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
Not directly linked to harmonised technology.<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-42ET<br />
Deep-Sub-Micron ASIC technology assessment and High-Speed-Serial-Links design<br />
The present activty is in line with the DSM (Deep Submicron Microelectronics) initiative strategy paper (<strong>ESA</strong>/IPC(2006)88).<br />
The activity aims at assessing deep submicron (i.e. 90 nm or below) Application-Specific-Integrated-Circuits (ASIC)<br />
technology with higher density chips and lower power consumption for on-board processing applications. Together with the<br />
ASICs’ core processing capabilities it is mandatory to improve the efficiency of data transportation (between ASICs, boards<br />
and equipments) by mean of embedded High-Speed-Serial-Link (HSSL). The design of ~10Gbps HSSLs with the selected<br />
ASIC process is a contextual objective of this activity.<br />
The activity shall encompass feasibility study, assessment and trade-offs of the following key issues:<br />
- Processes trade offs and selection.<br />
- Radiation evaluation (complementary tests): 1. Heavy ions, heavy protons and total dose effects; 2. SEE and SET<br />
characterisation; 3. Displacement damage; 4. Radiations effects on high k dielectric.<br />
- Reliability: 1. Electro migration; 2. Life time.<br />
- Proposal for hardening techniques in order to cope with radiation and reliability issues: 1. Enhancement at process level; 2.<br />
Enhancement at layout and cells design level; 3. Identification of the library cells requiring a redesign; 4. Identification of the<br />
work involved in order to harden the selected cells or eventually design new ones (clock tree buffers …); 5. Assessment CAD<br />
tool flow to support rad-hard library (hardened clock-tree network, TMR, etc.).<br />
- High speed serial links: 1. Assessment of the selected process to offer embedded high speed serial links able to provide a<br />
10 Gbps data rate while minimising power consumption (300mW per transceiver) and area; 2. Performance and architecture<br />
trade offs; 3. Design of the transceiver IP and implementation of the hardening techniques studied previously; 4. Layout; 5.<br />
Simulation post layout.<br />
- Preliminary study to define packaging options.<br />
- Sustainability of the space business (manufacturing costs, process lifetime, etc.): 1. The manufacturer shall propose a<br />
business model for future development activities and identify NRE and RE costs; 2. The manufacturer shall propose a<br />
sustainable model related to space business and guaranty access and support to the technology at fair conditions.<br />
Deliverables:<br />
Radiation and reliability reports, design rule recommendations, preliminary design and simulation report on HSSL, roadmap<br />
for the packaging technology, business model definition.<br />
Current TRL: TRL2-3 Target TRL: TRL3-4 Application Need/Date: TRL5/6 >2011<br />
TLC: on-board processing, SCI: science<br />
& remote sensing instruments, EO:<br />
Application/Mission:<br />
instruments, TLM&control, high-speed<br />
Contract Duration: 18 months<br />
rate data downlink.<br />
SW Clause : - Dossier0 Ref.: T-7742<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>ESA</strong>/IPC(2006)88<br />
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12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-43QC<br />
GaN Reliability Enhancement and Technology Transfer Initiative (GREAT2)<br />
An overall strategy paper towards implementing a coherent plan for gallium nitride (GaN) component and technology<br />
development was presented at the 233rd meeting of the IPC (Ref: <strong>ESA</strong>/IPC(2006)89). Key to this strategy and the subject of<br />
this procurement plan is the establishment of an independent European supply chain for GaN microwave power components<br />
that European space in<strong>du</strong>stry can access.<br />
Gallium nitride is clearly an emerging, but yet immature technology within Europe. At present, there is no commercial GaN<br />
component supply chain in Europe to satisfy the needs of space in<strong>du</strong>stry. The proposed activity is therefore based on a<br />
step-wise approach, allowing verification and assessment of results. Fundamental is the decision to initially limit the early<br />
development of materials and device techniques towards microwave payload technology. A further overriding consideration for<br />
space application is the need to demonstrate and improve the reliability of GaN based devices. The activity will address <strong>du</strong>al<br />
objectives:<br />
• Improvement of GaN device reliability for space application<br />
• Establishment of an independent European component supply chain for discrete transistors and MMICs.<br />
This <strong>TRP</strong> activity is planned to last 2 years and will focus on the required initial characterisation, modelling and process<br />
developments. These tasks will be supported by a follow on program of work, to be implemented through NewPro (Ref:<br />
<strong>ESA</strong>/IPC(2007)75, Activity : NP10-11QC), that will address the establishment of the process demonstration, technology<br />
in<strong>du</strong>strialisation and performance evaluation.<br />
The program of work will be broken down into several distinct tasks with phases and a defined target at the end of each<br />
phase. Continuation through GSTP/NewPro funding will depend upon these <strong>TRP</strong> targets being met. Table 1 in<br />
<strong>ESA</strong>/IPC(2007)75 indicates the program of work, including the planned GSTP/NewPro activities, in order to give a clearer<br />
overall work break down description.<br />
Task Breakdown Description for <strong>TRP</strong> funded work items<br />
1) Thermal characterisation of GaN devices.<br />
Accurate measurement of transistor channel temperature is required to derive reliability information and to determine the safe<br />
operating area for application in space. Infra-red or numerical simulation techniques are commonly used to derive channel<br />
temperature information and can give inaccurate results <strong>du</strong>e to poor geometrical resolution or inaccurate model parameters.<br />
The objective of this task is to investigate the use of micro-Raman measurement techniques in order to obtain high accuracy<br />
channel temperature and electric field measurements for GaN power transistors.<br />
2) GaN HEMT theoretical modelling and optimisation for space application.<br />
The objective of this activity is to use Monte-Carlo simulation techniques (or other appropriate modelling tools) to analyse and<br />
optimise GaN HEMT device performance. After successful “calibration” and agreement with measured results, the intention is<br />
to use this technique as a predictive tool to guide future device processing and physical structure developments to optimise<br />
operating frequency, breakdown voltage, output power and reliability.<br />
3) GaN HEMT design and fabrication for improved reliability.<br />
At present the reliability of wide bandgap active devices from European sources is unacceptable to allow operation in space.<br />
This task will undertake iterative, and closely linked, development steps to improve material quality and device design/process<br />
optimisation along with direct assessment of the effect upon reliability. This approach will allow a feedback loop to be<br />
established where incremental improvements in reliability are fed back to growth/processing engineers helping to guide further<br />
process/material improvements as required. This program will demonstrate improved GaN device reliability such that<br />
acceptably low FIT rates for space based operation are repro<strong>du</strong>cibly achieved.<br />
4) Space compatible MMIC process technology development.<br />
The objectives of this work item are to identify the techniques required to enhance the reliability, repro<strong>du</strong>cibility and<br />
performance of microstrip based GaN MMICs. The improvements will occur through an optimisation of front-side and<br />
back-side MMIC processing. Failure accelerating conditions and accelerating mechanisms shall be investigated and the<br />
threshold limits for onset of failure modes identified and eliminated (or managed). This approach will allow identification of the<br />
optimum processes required to achieve good manufacturing repro<strong>du</strong>cibility and allow the planned pro<strong>du</strong>ction transfer to<br />
manufacturing in<strong>du</strong>stry to occur more rapidly.<br />
5) Initial developments GaN epitaxy.<br />
The objective of this task is to develop and implement techniques to (i) assess the quality of substrates procured from external<br />
sources (prior to commencing GaN epitaxy) and to (ii) characterise “as-grown” epitaxial wafers such that the best wafers can<br />
be pre-selected prior to commencing device processing. Key objectives are to define the substrate procurement<br />
specifications, to define the substrate quality assurance metrics and the use of appropriate test methods to measure substrate<br />
quality.<br />
Deliverables:<br />
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1) Device test results, Calibrated channel temperature measurement approach that can be used within GREAT2.<br />
2) Calibrated device simulations; Recommendations on optimum device structures to concentrate development efforts.<br />
3) Identification of key parameters effecting reliability; Demonstration of materials growth and processing steps required to<br />
eliminate failure mechanisms; Discrete power transistor samples.<br />
4) Establishment of baseline GaN MMIC foundry process; Preliminary PID <strong>document</strong>ation, Reliability measurement data on<br />
test characterisation vehicles (TCV’s).<br />
5) Establishment of substrate and epitaxy specification criteria required for pro<strong>du</strong>ction transfer, implementation of fast and<br />
non-destructive analysis techniques, technical notes.<br />
Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5/6 >2009<br />
Telecoms, EO, Navigation and Science<br />
Application/Mission: Contract Duration: 24 months<br />
payloads requiring HPA’s<br />
SW Clause : - Dossier0 Ref.: T-7826, T-7736<br />
Consistency with Harmonisation<br />
<strong>ESA</strong>/IPC(2006)89<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T-M-QCT-02-MT<br />
Title:<br />
MTSL Lab<br />
Microelectronics Support Laboratory Frame contract (CCN).<br />
Deliverables:<br />
Technical notes,<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: N/A<br />
Application/Mission: all missions Contract Duration: 60 months<br />
SW Clause : - Dossier0 Ref.: N/A<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T-S-QCA-02-08<br />
Utilisation of the Heavy-ion Irradiation Facility (HIF) for Components Studies<br />
The availability of the Heavy Ion Irradiation Facility has been demonstrated to be of paramount importance for <strong>ESA</strong> projects<br />
and the European Space in<strong>du</strong>stry as recently again proven by the urgent and successful SEE characterisation of 19 device<br />
types for the XMM project. <strong>ESA</strong>’s continuing support of HIF will remain an instrumental asset for the European Space effort.<br />
The objective of this activity is to maintain, upgrade and keep the HIF operational. To provide 240 hours of free beam time<br />
per year on a priority basis for the purpose of the <strong>ESA</strong> lead irradiation campaigns. Additionally, a minimum of 240 hours of<br />
beam time will be made available to <strong>ESA</strong> in<strong>du</strong>strial contractors, research institutes and other interested users. All campaigns<br />
are supported by a qualified physicist and control room staff. A minimum of eight campaigns shall be sche<strong>du</strong>led per year<br />
covering four 100-hour periods and four 24-hour periods, more or less evenly spread throughout the year.<br />
Deliverables:<br />
Tested samples. Technical note, test results.<br />
Current TRL: N/A Target TRL: N/A Application Need/Date: N/A<br />
Application/Mission: all missions Contract Duration: 60 months<br />
SW Clause : - Dossier0 Ref.: T-7637<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
N/A<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T-S-QCT-02-FZ4<br />
Micro-Optical Electromechanical Systems (MOEMS) Delta Space Qualification<br />
Methodology (Critical evaluation techniques for micromachined devices)<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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6.23 - Materials & Processes<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
(03/)EEA-002<br />
Metamaterials for Space<br />
Deliverables:<br />
Current TRL: Target TRL: Application Need/Date:<br />
Application/Mission:<br />
Contract Duration:<br />
SW Clause : - Dossier0 Ref.:<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T608-04QM<br />
Assessment of the reliability of High Density Integrated Boards (HDIs) for future space<br />
Title:<br />
use<br />
The need for smaller, high performance electronic equipments (higher density, new components) requires new layout with<br />
finer circuit line, narrow track spacing and thinner copper tracks. Some components can't be today assembled using the<br />
current design. The HDI technology (50 to 150 mm) will allow using such components. This study will evaluate the feasibility of<br />
manufacturing reliable HDI boards. In order to do that, the requirements in terms of manufacturing facility to enable the<br />
fabrication of such boards will be defined and the second part of the activity will demonstrate the concept by performing<br />
testing on test coupons according to ECSS-Q-70-10.<br />
Deliverables:<br />
Feasibility and test reports; HDI boards and application for space use.<br />
Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: All projects Contract Duration: 18 months<br />
SW Clause : - Dossier0 Ref.: T-4981<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
N/A<br />
Page 224 of 227
<strong>TRP</strong> Work Plan 2005-2007<br />
Description of Activities<br />
TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
T608-12QM<br />
Study of the impact of the power meshed plane on electromagnetic behaviour of<br />
Title:<br />
electronic boards (PCBs).<br />
To improve the adhesion between the successive layers, and thus the reliability of PCBs, a qualified manufacturer is willing to<br />
replace full planes by meshed planes in PCBs. These modifications will impact the electromagnetic behaviour of electronic<br />
equipment. The goal of the study is to evaluate, in large frequency band (up to 3 GHz), the impact of meshed plane on the<br />
radiated emission, the signal integrity and the crosstalk. The study will consist on a bibliographic research on the topic, an<br />
experimental study of comparative measurements between configuration with full plane and with meshed plane; and a<br />
theoretical study in order to modelise the effect of meshed plane on electrical characteristics.<br />
Deliverables:<br />
Reports and <strong>document</strong>ation.<br />
Current TRL: TRL1 Target TRL: TRL1-2 Application Need/Date: TRL5 by 2010<br />
Application/Mission: All projects Contract Duration: 15 months<br />
SW Clause : - Dossier0 Ref.: T-7894<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
N/A<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-15QM<br />
Test and validation of contamination models through ground experiments modeling<br />
Contamination can have a major detrimental impact on space systems. Its assessment is performed through physical models<br />
of contaminant emission, transport and effects. At system level contamination can only be assessed through numerical<br />
modeling, <strong>du</strong>e to the complexity of a whole spacecraft. Unfortunately, the models and numerical tools under use have not yet<br />
been physically validated. A first reason is the difficulty and cost of flight experiments. A second reason was the inability of the<br />
old contamination software (<strong>ESA</strong>BASE/OUTGASSING) to model ground experiments. This second problem has now been<br />
solved by the new software COMOVA, developed in a QMC-EMA mini project which was completed in 2000 (this new code<br />
also incorporates improved deposition models). It is thus now both possible and necessary to validate this new code and its<br />
physical models through ground tests. The proposed action consists in:- gathering ground data involving outgassing,<br />
deposition, re-emission. They can be existing VBQC data (with reemission) or a new dedicated experiment involving more<br />
complex transport paths.- modelling these ground experiments with COMOVA and comparing data and simulation- improving<br />
the modelling, either simply by improving the extraction of the deposition and re-emission parameters from basic experiments,<br />
or if necessary by improved the physical models implemented in COMOVA.<br />
Deliverables:<br />
Proposal for ground testing of a complex structure in a large facility; model of the structure outgassing and contamination<br />
characteristics; test and critical comparison of model and experiment (and adaptation of model if needed).<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010<br />
modelling contaminants for optical<br />
Application/Mission: Contract Duration: 12 months<br />
satellite, such as GAIA, JWST, AEOLUS<br />
SW Clause : - Dossier0 Ref.: T-855<br />
Consistency with Harmonisation<br />
Not directly linked to harmonised technology.<br />
Roadmap and Conclusions:<br />
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<strong>TRP</strong> Work Plan 2005-2007<br />
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TEC-SB/7935/dc<br />
12/Feb/09<br />
<strong>TRP</strong> Reference:<br />
Title:<br />
T608-30QM<br />
Joining technology to bond Carbon to Carbon in stable sandwich structures<br />
Selection of a technology to bond Carbon to carbon for ultrastable structure - verification of the soundness of the technology<br />
at sample level.<br />
Deliverables:<br />
Trade off, Technical notes, Test plan, sample manufacturing, test report.<br />
Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010<br />
very stabe structures / optical benches /<br />
Application/Mission: telescope supports; missions coming Contract Duration: 15 months<br />
after LISA<br />
SW Clause : - Dossier0 Ref.: T-4878<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
<strong>TRP</strong> Reference: T608-33QM<br />
Title:<br />
Radiation stable optical adhesives<br />
High-tec., high performance optical adhesive and gluing process for optical assemblies exposed to high intensity radiation<br />
(visible, IR, UV, X-ray, gamma-ray,...). Typical applications are transparent silicone adhesives in solar cell assemblies (SCA)<br />
to bond cover glasses onto solar cells. Recent developments in shifting the spectral cut-off of cover glasses to shorter<br />
wavelength (e.g. CMO) to gain power output of the SCAs, does accelerate the degradation of the adhesive. Moreover there is<br />
a trend to re<strong>du</strong>ce the thickness of the cover-glass thus increasing penetration of radiation into the adhesive. Currently, only<br />
one US manufactured adhesive is exhibiting adequate long term stability. The applications are not limited to SCAs, and cover<br />
any payload that require gluing of optical components that are exposed to high intensity irradiation.<br />
Deliverables:<br />
Technical notes, Test plan, sample manufacturing, test report, test samples tested in relevant environment.<br />
Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2011<br />
future GEO spacecraft (high power<br />
output), long lifetime, mass saving<br />
thanks to thiner coverglasses);<br />
Application/Mission:<br />
interplanetary missions (solar panels<br />
Contract Duration: 24 months<br />
pointing sun >> high intensities); high<br />
power optical systems<br />
SW Clause : - Dossier0 Ref.: T-5326<br />
Consistency with Harmonisation<br />
Roadmap and Conclusions:<br />
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