european space agency industrial policy committee ... - emits - ESA

SUMMARY
EUROPEAN SPACE AGENCY
INDUSTRIAL POLICY COMMITTEE
ESA/IPC(2010)51
Att.: Annexes
18 February 2010
(English only)
GENERAL SUPPORT TECHNOLOGY PROGRAMME
GSTP-5 ELEMENT 1 WORK PLAN/PROCUREMENT PLAN
(Complete list of Activities Approved)
INFORMATION NOTE
This information note presents the complete list of activities that constitute the
present GSTP-5 Element 1 Work Plan and Procurement Plan as approved by
previous IPCs (including up to IPC 256th of January 2010).
Activities currently in the Work Plan can be grouped, according to their status, as
follows:
- Activities already procured or in procurement, for which support was received
during 2009, are the ones marked as 2009 in Annex 1.
- Activities for which support has been received during 2010 or not supported
yet, are the ones marked as 2010 in Annex 1.
REQUIRED ACTIONS
Delegations are invited to take note of this complete list of Activities Approved for
GSTP-5 Element 1 Work Plan and Procurement Plan.

ESA/IPC(2010)51
Page 2
KEY TO TABLES
The GSTP Work plan is presented along the following headings:
– EARTH OBSERVATION
– SCIENCE / ROBOTIC EXPLORATION
– HUMAN SPACEFLIGHT
– SPACE TRANSPORTATION & RE-ENTRY TECHNOLOGIES
– NAVIGATION
– GENERIC TECHNOLOGIES
Each activity is given a programmatic reference, which will remain unchanged until
completion. Additional planning elements associated with each of the activities are:
Budget: The total Contract Authorisation (CA) values are given in KEURO, at
yearly economic conditions.
Procurement Policy:
C Open Competitive Tender (Ref. Article 5.1 ESA Contract Regulations)
C(1) Activities in open competition limited to the non-Large-System Integrators
(LSI).
C(2) Activities in open competition, where a significant participation of non-LSI is
requested.
C(3) Activity restricted to SMEs & R&D organisations, preferably in cooperation.
C(4) Activities in open competition, subject to SME subcontracting clause
C(R) Competition is restricted to a few companies, indicated in the "Remarks''
column; (Ref. Article 5.2 ESA Contract Regulations)
DN/C Direct Negotiation/Continuation; the contract will be awarded in direct
negotiation being the immediate continuation of a previous activity with the
same contractor (Ref. Article 6.1.C ESA Contract Regulations)
DN/S Direct Negotiation/Specialisation; the contract will be awarded by direct
negotiation in implementation of a defined industrial policy or resulting from a
sole supplier situation; (Ref. Articles 6.1.A, D, F ESA Contract Regulations)
Further details of the applicability of industrial policy measures can be found in
documents ESA/IPC(2001)29 and ESA/IPC(2005)87,rev.4

Together with the activity description the following information is reported:
ESA/IPC(2010)51
Page 3
Deliverables: Provides a short description of the tangible outcome, e.g.,
breadboard, demonstrator, S/W, test data. A final report is
standard for every activity.

ANNEX I
GSTP-5 Element 1 Work Plan & P.P.
Complete List of Activities Approved

ESA/IPC(2010)51
Annex 1, Page 1
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
Theme 1.- EARTH OBSERVATION
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G511-001MM Vanadium dioxide High-resolution Uncooled Bolometer Array 1,000 C1 ESA/IPC(2009)5,add.1
G511-002EE X/Ka band data transmission antenna qualification model 750 C ESA/IPC(2009)5,add.1
G511-003EE Airborne demonstrator for combined CIWSIR/GOMAS 2,000 C ESA/IPC(2009)5,add.1
G511-004EE Light weight, very stable rotating reflector antenna 500 C ESA/IPC(2009)5,add.1
G511-005ET On-Wafer Measurements to 300 GHz 450 C1 ESA/IPC(2009)5,add.1
G511-006GN Phase centre calibration of GNSS antennas in LEO 250 C ESA/IPC(2009)5,add.1
G511-007ET High-power W-band LO source 950 C ESA/IPC(2009)5,add.1
G511-008ET Integrated Tile Demonstartor 3,000 C ESA/IPC(2009)5,add.1
G511-009EE Low mass Calibration load demonstrator 500 C2 ESA/IPC(2009)5,add.1
G511-010EE Very large space antenna aperture - demonstration model 2,000 C ESA/IPC(2009)5,add.1
G511-011EE Multi Frequency high resolution GEO-sounder Demonstrator 2,000 C ESA/IPC(2009)5,add.1
Large aperture, ultra-stable, push-broom antenna with
G511-012EE
frequency-multiplexed beams
1,000 C ESA/IPC(2009)5,add.1
G511-013EE Cross Correlator ASIC development 650 C ESA/IPC(2009)5,add.1
Reliability study and space evaluation of European planar Schottky
G511-014QC
diode
350 C1 ESA/IPC(2009)5,add.1
High power narrowband lasers for laser cooling applications in Atom
G511-016MM
Interferometry
350 C1 ESA/IPC(2009)5,add.1
G511-017MM Monolithic filter on detector dye integration technologies 500 C1 ESA/IPC(2009)5,add.1
EES Ka band High Data Rate Payload Data Transmitter
G511-018ET
Engineering Model
1,500 C1 ESA/IPC(2009)5,add.1
G511-019GI Parallel computing for fast TM processing during short passes 150 C1
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
ESA/IPC(2009)5,add.1
G511-020ET Membrane circuits for high frequencies 400 C ESA/IPC(2009)5,add.1

ESA/IPC(2010)51
Annex 1, Page 2
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G511-021GR
Preparation of an advanced standalone error prediction module for
SAR interferometry (PEPSI)
200 DN/C TUD (DK) ESA/IPC(2009)5,add.1
Automated Service Builder for Semantic Service Oriented
G511-022GR
Architectures (ASB)
400 C1 ESA/IPC(2009)5,add.1
Automatic, Semantic Image Information Mining from Time Series of
G511-023GR
VHR images (ASIM)
200 DN/S MEEO (I) ESA/IPC(2009)5,add.1
G511-024GR Decision Support and Real Time EO Data Mangement (DREAM) 2,500 C1 ESA/IPC(2009)5,add.1
The EO Image Librarian: EO image and geoinformation intelligence
G511-025GR
search engine (EOLib)
2,000 DN/C DLR (D) ESA/IPC(2009)5,add.1
G511-026GR European Service Support Environment Enhancements (ESE) 2,000 DN/C Spacebel (B) ESA/IPC(2009)5,add.1
G511-027GR
New Sensors Study for Soil Mapper Application and SSE
Integration (NSS)
150 DN/S
DMC International Imaging
(UK)
ESA/IPC(2009)5,add.1
G511-028GF Open-standard Online Observation Service (O3S) 500 C1 ESA/IPC(2009)5,add.1
G511-029GF Ontology Based EO Search (OBEOS) 320 C1 ESA/IPC(2009)5,add.1
G511-030GR Rapid Response Support Server (RARE) 720 C1 ESA/IPC(2009)5,add.1
G511-031SF Development and Testing of the AGGA-4 Device. Phase 2 650 DN/C
Astrium (D) Output may
lead to ESA Operational
SW (special attention on
contracts subclause 42.8)
ESA/IPC(2009)5,add.2
Integrated MEOS LiNbO3 Mach-Zehnder interferometer for
G511-032MM
spectrometry in the 0.5 to 5 micron spectral region
500 DN/C Carlo Gavazzi Space (I) ESA/IPC(2009)5,add.3
G511-033GS Prototype of 26 GHz receiver for EO 1,000 C ESA/IPC(2009)5,add.4
Design of S/K-Band Ground Station Antenna (13-15m aperture) for
G511-034GS
LEO application
800 C ESA/IPC(2009)5,add.4
Prototype of K-Band Ground Station Antenna (6m aperture) for LEO
G511-035GS
application
1,000 C ESA/IPC(2009)5,add.4
Total 1.- EARTH OBSERVATION 9,820 21,420

ESA/IPC(2010)51
Annex 1, Page 3
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
Theme 2.- SCIENCE / ROBOTIC EXPLORATION
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G512-001MM B-BOLD (BOLD continuation) 1,000 DN/C IMEC (B) ESA/IPC(2009)5,add.1
G512-002MC Hybrid Cryostat Demonstrator 700 C ESA/IPC(2009)5,add.2
G512-003EC
Precise Gravitational Modelling of Planetary Moons and NEO (Near
Earth Objects) Asteroids
350 C
Total 2.- SCIENCE / ROBOTIC EXPLORATION 350 1,700
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
ESA/IPC(2009)5,add.2

ESA/IPC(2010)51
Annex 1, Page 4
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
Theme 3.- HUMAN SPACEFLIGHT
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G513-001MM Micro laser beam scanner 600 C1 ESA/IPC(2009)5,add.1
Investigation on microcompounds in MELiSSA - PHASE2
G513-002MC
(BELISSIMA2)
1,500 C3 ESA/IPC(2009)5,add.1
G513-003MC Water Network Corrosion 250 C3 ESA/IPC(2009)5,add.1
Preliminary estimation of energy balance of a closed life support
G513-004MC
system - Application to MEliSSA
250 C3 ESA/IPC(2009)5,add.1
G513-005MC Process Aeration Device 250 C3 ESA/IPC(2009)5,add.1
G513-006MM Biochemical Analyser Technology (BIOCAT) 350 DN/C
Embedded System
Engineering GmbH (D)
ESA/IPC(2009)5,add.1
G513-007MM A self standing bioreactor for biological samples 300 C1 ESA/IPC(2009)5,add.1
G513-008MM Respiratory Sensor System - Optimisation and Combination 200 C1 ESA/IPC(2009)5,add.1
G513-009MM MEMS based Gas Chromatograph/Mass Spectrometer 500 C1 ESA/IPC(2009)5,add.1
G513-011MM Enhanced Autonomous Cultivation System 350 C1 ESA/IPC(2009)5,add.1
G513-012MM Enhanced Virtual Reality Stimulator 600 DN/C SAS (B) ESA/IPC(2009)5,add.1
G513-013MM Tactile Training 250 C3 ESA/IPC(2009)5,add.1
G513-014MM Bone and Muscle Modelling 350 C3 ESA/IPC(2009)5,add.1
G513-015MM High-precision Implantable Intra-arterial Drug Delivery Device 600 C1 ESA/IPC(2009)5,add.1
G513-016MM 3D Bioreactor 300 C1 ESA/IPC(2009)5,add.1
Blood pressure, flow and temperature sensor inserted via a
G513-017MM
vascular stent
400 C1 ESA/IPC(2009)5,add.1
G513-018MM Diagnostics for Nucleation Detection 350 C3 ESA/IPC(2009)5,add.1
G513-019MM Nanowire Biosensor 250 C1 ESA/IPC(2009)5,add.1
G513-020MM Compact - 80ºC Freezer 500 C ESA/IPC(2009)5,add.1
Development of a Lithium ion cell optimized for low temperatures
G513-023EP
(-20°C )
400 C1 ESA/IPC(2009)5,add.1
G513-024SW Authoring environment for interactive 3D procedures 300 C2 ESA/IPC(2009)5,add.1
G513-025EC One-axis inertial MEMS sensor development 1,900 C2 ESA/IPC(2009)5,add.1

ESA/IPC(2010)51
Annex 1, Page 5
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
Development of Thermal Insulation for Planetary Landers and
G513-026MC
Rovers
350 C ESA/IPC(2009)5,add.1
Mechanically Pumped Heat Transport Loop for Planetary Landers
G513-027MC
and Rovers
400 C1 ESA/IPC(2009)5,add.1
G513-029MM Detector arrays for Imaging Lidar systems 800 C1 ESA/IPC(2009)5,add.1
G513-030SW Autonomous and remote operations reference facility for robotics 600 C2 ESA/IPC(2009)5,add.1
G513-033MC Additional Unit for Increased Water Loop Closure 500 C1 ESA/IPC(2009)5,add.1
G513-034MC Air Sampler Unit 450 C1 ESA/IPC(2009)5,add.1
G513-035MC Determination of Biomass in Complex Bioprocesses 400 C1 ESA/IPC(2009)5,add.1
G513-036MC Development of Methane Recovery Assembly 400 C1 ESA/IPC(2009)5,add.1
G513-037MC Feasibilty Study for Manned BIORAT Campaign 150 C ESA/IPC(2009)5,add.1
G513-038MC High Performance Pressurized Structure 400 C ESA/IPC(2009)5,add.1
G513-039MC Higher Plant Canopy Evaluation 450 C ESA/IPC(2009)5,add.1
G513-040MC Inflatable Container for Life Support Waste Water 450 C ESA/IPC(2009)5,add.1
G513-041MC MELiSSA Pilot Plant 1,500 C ESA/IPC(2009)5,add.1
G513-042MC Plant Stress Detection Unit 550 C2 ESA/IPC(2009)5,add.1
G513-043MC Waste Preparation Unit 600 C1 ESA/IPC(2009)5,add.1
G513-044MC Wet Oxidation Unit 600 C1 ESA/IPC(2009)5,add.1
G513-045MC MELISSA Space Adaption Phase 3: Moon base Life support 300 C ESA/IPC(2009)5,add.1
G513-046MC MELISSA Genetic charcaterisation Phase 3 550 C1 ESA/IPC(2009)5,add.1
G513-047MC Axenicity control within MELISSA compartment 2 and IV a 450 C1 ESA/IPC(2009)5,add.1
G513-048MC Recycling of tissues and packaging wastes phase 1 450 C1 ESA/IPC(2009)5,add.1
Total 3.- HUMAN SPACEFLIGHT 2,550 18,550

ESA/IPC(2010)51
Annex 1, Page 6
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
Theme 4.- SPACE TRANSPORTATION & RE-ENTRY TECHNOLOGIES
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G514-002ED Safety oriented reference architectures for man tended systems 1,000 C ESA/IPC(2009)5,add.1
Delta-Development of SEPCORE based Heatshield for Earth Entry
G514-003MC
Capsule of Sample Return Missions
500 C ESA/IPC(2009)5,add.1
G514-004MC Development of Secondary Protections for Hot Structures 250 C ESA/IPC(2009)5,add.1
G514-005MP Enhancement of Plasmatron operating capabilities 700 C ESA/IPC(2009)5,add.1
G514-006MP Prediction methods for propellant management devices 1,500 C ESA/IPC(2009)5,add.1
G514-007MP ESPSS: European Space Propulsion System Simulation 500 C1
Open Source SW
(special attention on
contracts clause 42)
ESA/IPC(2009)5,add.1
G514-008MP Kinetic shock tube for radiation data base for planetary exploration 2,000 C1 ESA/IPC(2009)5,add.1
G514-009EC Fault Tolerant Flight Control System Components 600 C ESA/IPC(2009)5,add.1
G514-010MC Methodology for analysis/test correlations of an SRM 300 C ESA/IPC(2009)5,add.1
G514-011MP Aerodynamics of decelerators : parachutes and ballutes 250 C ESA/IPC(2009)5,add.1
Advanced Self-blocking Electro-Mechanical System Development
G514-012SN
and Ground-to-Flight Qualification
6,500 DN/C Sabca (B) ESA/IPC(2009)5,add.3
G514-013MM Fibre Bragg Grating Experiment - SHEFEX 2 250 DN/C MPB (CND) ESA/IPC(2009)5,add.4
Qualification of a new white antistatic coating for thermal protections
G514-015QE
of launchers
130 DN/S MAP (F) ESA/IPC(2010)5
Total 4.- SPACE TRANSPORTATION & RE-ENTRY TECHNOLOGIES 2,700 11,780

ESA/IPC(2010)51
Annex 1, Page 7
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
Theme 6.- NAVIGATION
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G516-01MM Photonic micro-navigator for microsatellites 600 C1 ESA/IPC(2009)5,add.1
G516-02GN GNSS processing strategies for LEO constellations 300 C1 ESA/IPC(2009)5,add.1
G516-03GN Improved radiation modelling for GNSS satellites 400 C1 ESA/IPC(2009)5,add.1
Total 6.- NAVIGATION 1,300

ESA/IPC(2010)51
Annex 1, Page 8
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
Theme 7.- GENERIC TECHNOLOGIES
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G517-001MM Voice Coil Motor Qualification Model 150 DN/C Cedrat (F) ESA/IPC(2009)5,add.1
G517-002MM Piezo new sources materials, piezoceramics motor qualification 400 C1 ESA/IPC(2009)5,add.1
G517-003MM Compact Magnetic Bearing for High-Speed Rotor 150 C ESA/IPC(2009)5,add.1
G517-004MM Advance material for ball bearings 300 C ESA/IPC(2009)5,add.1
G517-006MM Multi wafer hybrid integration: Robotics IMU II 500 C ESA/IPC(2009)5,add.1
G517-007MM Testbed For Telemanipulated Satellite Servicing 600 C ESA/IPC(2009)5,add.1
G517-008MM Virtual testbed 400 DN/C
Trasys (B) Output may
lead to ESA Operational
SW (special attention on
contracts subclause 42.8)
ESA/IPC(2009)5,add.1
G517-009MM Haptic Control 1,500 C2 ESA/IPC(2009)5,add.1
G517-010MM Ground Control Station For Autonomy 600 C2 ESA/IPC(2009)5,add.1
G517-011SW Automatic testing improvement 300 C2 ESA/IPC(2009)5,add.1
G517-012SW Customisation of the ASSERT Framework to industrial environment 200 C1
Edisoft(P) Open Source
ESA/IPC(2009)5,add.1
G517-013SW On Board operating system Upgrade for Leon 300 DN/C SW (special attention on
contracts clause 42)
Critical Software (P)
ESA/IPC(2009)5,add.1
G517-014SW Qualification of xLuna operating system 300 DN/C
Open Source SW (special
attention on contracts
clause 42)
ESA/IPC(2009)5,add.1
Implementation and Demonstration of RF testing approaches for
G517-015EE
reduced antenna/payload AIT/AIV
750 C1 ESA/IPC(2009)5,add.1
Implementation and Demonstration of EMI/EMC approaches for full
G517-016EE
development cycle support and reduced AIT/AIV.
500 C1 ESA/IPC(2009)5,add.1
G517-017EC Reaction Wheel Drive Electronics Improvements 700 DN/C Bradford Engineering (NL) ESA/IPC(2009)5,add.1
G517-018EC Low cost, portable sensor GSE 350 C2 ESA/IPC(2009)5,add.1
G517-019SW Industrialisation of the HW-SW Codesign toolset. 500 C2 ESA/IPC(2009)5,add.1

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Annex 1, Page 9
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G517-020ED SpW RTC Software Library and Tools 300 C1 ESA/IPC(2009)5,add.1
G517-021ED TOPNET 2nd Generation 500 DN/C University of Dundee (UK) ESA/IPC(2009)5,add.1
G517-022EP Constant Power charging of Li ion batteries for LEO missions 200 C ESA/IPC(2009)5,add.1
G517-023QM ADHESIVE TAPE FOR HIGH POWER LASER INSTRUMENTS 300 C ESA/IPC(2009)5,add.1
G517-024QM Joining of composites materials 300 C1 ESA/IPC(2009)5,add.1
G517-025QM Crimping of thermally stable structures with Shape memory rings 200 C ESA/IPC(2009)5,add.1
G517-026QM Light weight steel structures 250 C1 ESA/IPC(2009)5,add.1
G517-027QM
Development of electroless Silver platting on Ni/Cu coated
substrates.
200 C1 ESA/IPC(2009)5,add.1
G517-028QM Processing of Al-Mg-Sc high strength alloys. 400 C2 ESA/IPC(2009)5,add.1
G517-029QM Development and characterisation of Titanium alloy hollow-spheres. 250 C1 ESA/IPC(2009)5,add.1
Development and characterisation of advanced metal matrix
G517-030QM
composites.
250 C1 ESA/IPC(2009)5,add.1
G517-031QM Validation testing of Glare 1 to space qualification levels 200 C ESA/IPC(2009)5,add.1
G517-032QC Polymer Tantalum capacitor (very low ESR) 400 C1 ESA/IPC(2009)5,add.1
Definition of displacement damage test guidelines for bipolar
G517-033QC
devices
350 C ESA/IPC(2009)5,add.1
Evaluation of worst case condition for the Single Event Effect test of
G517-034QC
power MOSFET
300 C ESA/IPC(2009)5,add.1
G517-035SW Java on-board software implementation, case study 450 C1
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
Open Source SW
ESA/IPC(2009)5,add.1
G517-036SW Establishment of model reference library 350 C (special attention on
contracts clause 42)
ESA/IPC(2009)5,add.1
G517-037SW Adaptation and Demonstration of MBSE for a real project 2,000 C2 ESA/IPC(2009)5,add.1
G517-038SW System Architecture modelling tool 400 C2 ESA/IPC(2009)5,add.1
G517-039SW System of Systems design environment 750 C ESA/IPC(2009)5,add.1

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ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.)
Open Source SW
Document
G517-040SW End-to-end performance simulation framework 500 C (special attention on
contracts clause 42)
ESA/IPC(2009)5,add.1
Development and validation of a generic System of Systems
G517-041SY
Concurrent Engineering Model
600 C1 ESA/IPC(2009)5,add.1
Process optimization & pre-qualification activities for multi-junction
G517-043EP
cells on thin germanium substrates
400 C1 ESA/IPC(2009)5,add.1
G517-044EC HAS Active Pixel Sensor detailed annealing behaviour investigation 200 DN/C Cypress (B)
ASTOS (D) Output may
ESA/IPC(2009)5,add.1
G517-045EC Extension/Deployment of the European Mathematical NLP-solver 200 DN/C
lead to ESA Operational
SW (special attention on
contracts subclause 42.8)
ESA/IPC(2009)5,add.1
Highly Available COTS based computer, Step2 (Prototyping and
G517-046ED
validation)
800 DN/C EADS Astrium (D) ESA/IPC(2009)5,add.1
High Performance COTS based computer step2 (Prototyping and
G517-047ED
validation)
800 DN/C EADS Astrium (F) ESA/IPC(2009)5,add.1
High Reliability COTS based computer step2 (Prototyping and
G517-048ED
validation)
800 DN/C Thales Alenia Space (I) ESA/IPC(2009)5,add.1
G517-049QM Upscaling of ultra-stable bonding process of ultra-stable materials 750 DN/C Thales Alenia Space (F) ESA/IPC(2009)5,add.1
Establishment of a commercial GaN epitaxial production facility in
G517-050QC
Europe
2,000 C1 ESA/IPC(2009)5,add.1
G517-051QC GREAT - Validation of space compatible GaN foundry process 1,000 C1 ESA/IPC(2009)5,add.1
G517-052QC Improved quality large diameter SiC substrates
Characterization and reliability assessment of RF MEMS switches
2,000 C1 ESA/IPC(2009)5,add.1
G517-053QC and switching matrix built on LTCC (Low Temperature Cofired
Ceramic)
300 DN/C Thales Alenia Space (I) ESA/IPC(2009)5,add.1
Demonstration of the ESCC Assembly & Test House (ATH)
G517-054QC
Capability Approval approach for EEE components.
500 C ESA/IPC(2009)5,add.1
G517-055QC IESD effects on glob-top assemblies 300 C ESA/IPC(2009)5,add.1
G517-056SW Verification of operational concepts for human-robot interaction 800 C ESA/IPC(2009)5,add.1

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ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G517-057QC
Reliability assessment of a MEMS-based isolation valve for
propulsion systems
250 C1 ESA/IPC(2009)5,add.1
G517-058QM Nano-hybrid transparent materials 400 C1 ESA/IPC(2009)5,add.1
G517-059QM
RTM processing of novel high temperature high radiation resistant
resin
300 C1 ESA/IPC(2009)5,add.1
G517-060SW Data Modelling using ASN.1 300 DN/C
EADS Astrium (F) Open
Source SW (special
attention on contracts
clause 42)
ESA/IPC(2009)5,add.1
G517-061SW Dynamic Translation based on-board processor emulator 350 C ESA/IPC(2009)5,add.1
On-Board Computer Simulator architectures and I/F to system test
G517-062SW
benches
350 C ESA/IPC(2009)5,add.1
Automatic generation of database applications from a domain
G517-063SW
ontology
750 C ESA/IPC(2009)5,add.1
G517-064TC Virtual Reality for AIV 320 DN/C TERMA (DK) ESA/IPC(2009)5,add.1
Automated layup of Thermoplastic Composites for space
G517-065MC
applications
500 C ESA/IPC(2009)5,add.1
G517-066MC CAD Based Modelling for Space Thermal Analysis 150 C1 ESA/IPC(2009)5,add.1
G517-067EE ESD transients monitor 500 C ESA/IPC(2009)5,add.1
G517-068MP Low cost PED propellant tank 600 C ESA/IPC(2009)5,add.1
G517-069MC Medium-Power Loop Heat Pipe 200 C1 ESA/IPC(2009)5,add.1
G517-070MC Multistable Composite Structures 250 C ESA/IPC(2009)5,add.1
G517-071MC New Concepts for Advanced Structural Sandwich Panels 350 C ESA/IPC(2009)5,add.1
G517-075GS Ka-band klystron power amplifier prototype 750 C ESA/IPC(2009)5,add.1
Improved Autotrack and search performance for ESTRACK
G517-076GS
Antennas
300 C ESA/IPC(2009)5,add.1
G517-077GS Holography System for Deep Space Antennas 500 C ESA/IPC(2009)5,add.1
G517-078GS High Accuracy Reflector Panel 300 C ESA/IPC(2009)5,add.1
Development of an RF test bed for high power testing of ground
G517-079GS
station feed systems.
300 C ESA/IPC(2009)5,add.1

ESA/IPC(2010)51
Annex 1, Page 12
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G517-080GS
Demonstration of simultaneous transmission and reception of data
in Ka-Band
500 C1 ESA/IPC(2009)5,add.1
G517-081GI Ground-Station Automation and Off-line operations 300 C
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
ESA/IPC(2009)5,add.1
G517-082GI Combinatorial Optimization for Scheduling Applications 400 C1 ESA/IPC(2009)5,add.1
G517-083GI
Integrated development and validation environment for operations
automation
400 C1
G517-084GI Ubiquitous alert and operations monitoring system 400 C1
G517-085HS
Integrated Monitoring & Diagnostic of End-to-End Communication
Link
350 C1
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
ESA/IPC(2009)5,add.1
ESA/IPC(2009)5,add.1
ESA/IPC(2009)5,add.1
G517-086GS Deep space receiver for support during superior solar conjunctions 300 C1 ESA/IPC(2009)5,add.1
G517-087GI
G517-088MM
G517-089SY
Operational Data Off-line Analysis, Correlation and Reporting
System
Development of core technological elements in preparation for
future Optical Atomic Frequency Standards (OAFS) and clocks
(OAC's) in space
Demonstration of a Vision based System for Formation Flying and
Rendez-vous
400 C
G517-090SY SYMPHONY 200 DN/C
Output may lead to ESA
Operational SW (special
attention on contracts
subclause 42.8)
ESA/IPC(2009)5,add.2
3,000 C ESA/IPC(2009)5,add.3
500 DN/C DTU (DK) ESA/IPC(2009)5,add.3
Jotne EPM (N) Open
Source SW (special
attention on contracts
clause 42)
ESA/IPC(2009)5,add.3

ESA/IPC(2010)51
Annex 1, Page 13
ANNEX I: Complete List Approved Activities GSTP-5 Element 1 Work Plan / Procurement Plan
GSTP-5 Title Budget (K€) Proc. Remarks (Company DN, IPC Reference
Reference 2009 2010 Policy SW Clause, etc.) Document
G517-091QC Assessment of AAC System-in-Package (SiP) technology 700 DN/S
Ångström Aerospace
Corporation (S)
ESA/IPC(2009)5,add.4
G517-092EC ASTRO-APS Productionisation 1,500 DN/C Jena Optronic (D) ESA/IPC(2009)5,add.4
G517-093EC STR OGSE (Optical Ground Support Equipment) Development 350 C ESA/IPC(2009)5,add.4
G517-094EP Towards performance guaranteed Ge substrates 1,600 DN/S Umicore (B) ESA/IPC(2009)5,add.4
High-Dynamic Absolute Nanometric Optical Encoder technology for
G517-095MM
space (DANOE)
100 C ESA/IPC(2009)5,add.4
G517-096EC W40 Reaction Wheel Capacity Improvements 350 DN/S Bradford Engineering (NL) ESA/IPC(2010)5
Experimental Investigation of Key Technologies for a Turbine Based
G517-096MP
Combined Airbreather-Rocket Engine: Phase II
500 DN/C REL (UK) ESA/IPC(2009)5,add.5
G517-097MP Microdisturbance sources and characterisation 250 C ESA/IPC(2010)5
G517-098EP Reaction Wheel DC-DC Converter Upgrade 300 DN/S Bradford Engineering (NL) ESA/IPC(2010)5
Total 7.- GENERIC TECHNOLOGIES 9,500 39,420

ANNEX II
Detailed Descriptions of the Activities

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Theme 1.- EARTH OBSERVATION
ESA/IPC(2010)51
Annex 2, Page 1
Ref. Number: G511-001MM Budget: 1,000 K€
Activity Title: Vanadium dioxide High-resolution Uncooled Bolometer Array
Description: Development of a 2-D uncooled detector array of high performances (high spatial
and thermal resolution) breadboard to a higher maturity level (~EQM) targeting
the concrete needs of the selected mission at that timeIt had been repeatedly
demonstrated that VO2 / VOX as the resistive material has superior
characteristics to any other presently used thermal sensing element suitable for
an imaging array (especially w.r.t. 1/f noise). Exploiting the ultimate performance
capability of uncooled imagers will allow several missions to adopt this technology
rather than having to resort to expensive and ressources-extensive cryogenic
photon detectors. It is of extremely high interest to develop a detector for space,
taking advantage of the consortium's business plan to provide devices for airborne
and terrestrial markets.
Deliverables: Full-scale breadboard of EQM maturity
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Ref. Number: G511-002EE Budget: 750 K€
Activity Title: X/Ka band data transmission antenna qualification model
Description: The objective is to realise a Prequalification of an X/Ka band AntennaData
volumes to be transmitted for scientific missions are large and rationalisation of
the links is appropriate, with more orbiters around the planet. Earth based stations
have the complete planet inclusive all orbiters potentially in their main beam.
Consequently a High Gain Antenna is needed and a preparation for that is
recommended. With knowledge in house (Cassini antenna, a 4 m antenna made
in Europe for Nasa is 10 years old) and progress in technology an X - Ka band
antenna is proposed for development by ESA. A pre qualification model for an
X-Ka band antenna is to be realised in this activity
Deliverables: Prequal Model X-Ka band antenna
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
Next Interplanetary Satellite Program

ESA/IPC(2010)51
Annex 2, Page 2
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-003EE Budget: 2,000 K€
Activity Title: Airborne demonstrator for combined CIWSIR/GOMAS
Description: The objective of this activity is to implement the combined CIWSIR/GOMAS
sounder instruments and demonstrate with an airplane campaign the validity of
the concept.
The present study deals with the implementation and flight of the (sub)mm wave
instrument on-board of an airplane. The follwoing tasks are included:
a) consolidation and adoption of instrument requirements for an airplane;
b) identification of potential instrument platforms;
c) identification of potential partners/cooperation approaches;
d) detailed assessment of instrument accommodation and interface requirements
on selected platforms;
e) instrument update;
f) definition of algorithms for instrument performance verifications;
g) performance consolidation of the selected design on the selected platform;
h) design, development and ground testing of the airborne demonstrator;
i) flight campaign.
Deliverables: Airborne demonstrator
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
Gomas \ CIWSIR, GEO-sounder. Specifically for Numerical weather prediction
and Nowcasting (very short term weather forcasting)
Ref. Number: G511-004EE Budget: 500 K€
Activity Title: Light weight, very stable rotating reflector antenna
Description: One of the identified radiometer concepts for Post-EPS missions is the
millimetre-wave cross-track scanner. Because of the demanding horizontal
resolutions, especially at low millimetre-wave frequencies, and the 90-deg off-set
angle (simple scanning geometry), relatively large reflector antennas are needed
(around 1m). A large and heavy reflector together with a 10-years mission
requirement puts a too high stress on the scan mechanism. If we want to reduce
the risks of a scan mechanism failure it is clear that light-weight reflector
technologies are needed, which can provide sufficient stability at near
submillimetre-wave frequencies.
This objective of this activity is to demonstrate a low mass 1-m class reflectors for
millimetre-wave and near submillimetre-wave frequencies. The application is a
cross-track scanner for LEO Earth Observation mission (Post-EPS), using
frequencies from 20 to 220 GHz. A trade-off shall be made between various
reflector technologies, e.g. CFRP and ceramics, and the objective is to achieve
the lowest possible mass while complying with the general stability and surface
accuracy requirements. After the trade-off, the most promising technology shall be
selected and further detailed design and analysis is needed to optimise its
properties. Finally, by critical breadboarding and testing of representative RF and
thermo-mechanical samples, the technology/design shall be improved.
Manufacturing and testing of a prototype reflector (around 0.5 m) shall be
performed.
Deliverables: RF, Thermo-mechanical representative samples, reflector prototype
Current TRL: TRL3 Target TRL: TRL4 Duration: 15 Months
Application /
Timeframe:
Post-EPS. More specifically for the Microwave Sounder that is identified as one of
the three high priority observation missions. It will provide continuity of data.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 3
Ref. Number: G511-005ET Budget: 450 K€
Activity Title: On-Wafer Measurements to 300 GHz
Description: Setting up a service for for on-wafer measurements at frequencies up to 300
GHzOn-wafer testing facilitates the development of mm-wave hardware, as the
testing can be done at chip/circuitboard level, without the additional complexity of
the waveguide interfaces. Especially in the development of LNAs and monolithic
mixers and multipliers on-wafer testing is indispensable. In previous activities
on-wafer measurement capabilities of MilliLab were developed for 220 GHz. This
activity aims to take benefit of the development of test equipment to frequencies
above 300 GHz, and develop a measurement service that is available European
companies. Setting up an on-wafer test facility, investigation of the calibration,
measurement error and DUT (device under test) mounting issues, setting up a
measurement service, definition of accuracies and requirements to the DUT.
Deliverables: Report. Measurement service available to European companies
Current TRL: TRL2 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
measurement infrastructure / ASAP
Ref. Number: G511-006GN Budget: 250 K€
Activity Title: Phase centre calibration of GNSS antennas in LEO
Description: To define and set up an application to calibrate a LEO satellite GNSS antenna in
orbit, by processing of real GNSS data. This will lead to a more realistic and
accurate calibration than can be achieved on ground.The antenna calibration
requires high-accuracy orbit determination of both the GNSS constellation(s)
used, and the LEO spacecraft. This activity will define optimal algorithms to
perform this calibration, and establish the achievable accuracy of the phase centre
calibration in space by implementing a prototype application in existing software. It
can be extensively tested on existing GNSS antennas of operational satellites in
LEO.
Deliverables: Activity report and a working prototype implementation of the S/W with
documentation.
Current TRL: TRL3 Target TRL: TRL7 Duration: 12 Months
Application /
Timeframe:
Can be applied as soon as available (e.g. Metop-2, GOCE)

ESA/IPC(2010)51
Annex 2, Page 4
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-007ET Budget: 950 K€
Activity Title: High-power W-band LO source
Description: To develop a broad-band W-band LO source with Watt-level output powerW-band
LO source with high output power is needed in several space-borne instruments,
and increasingly also in terrestrial applications. Power level of 100 mW was
reached in the past GSTP activity using GaAs technology. Today technology
selection is wider (e.g. GaN), and much higher power levels (0.5 to 1 W) are
feasible with European SSPAs. Technology selection for SSPA MMICs. Design,
fabrication and testing of two iterations of MMICs the LO source, including
frequency multipliers and power amplifiers. Integration of the MMICs and other
circuits into a LO module. Final test.
Deliverables: Report, hardware demonstrators
Current TRL: TRL2 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
Post-EPS, Ciwsir, Tandem, Laplace, EVE, FIRI / 2011

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 5
Ref. Number: G511-008ET Budget: 3,000 K€
Activity Title: Integrated Tile Demonstartor
Description: Design, manufacturing and test of integrated front-end tile demonstrator based on
advanced technologies for high coverage Active Array SARNew concepts for SAR
allowing high resolution and simultaneously wide swath will significantly improve
performance compared to existing concepts, while high resolution can be traded
against radiometric accuracy by multi-looking if desired. Pencil beams in range,
formed in the digital domain, improve signal to noise ratio and keep Tx power
within reasonable limits. In order to implement those concepts new front-end
architectures are required separating beam forming functionality from transmit and
receive functionality. The beam forming would lead to significantly increased
wiring density, reasonably manageable only in centralised solutions.
Depending on the outcome of the study “Advanced SAR Instruments based on
Digital Beam Forming” the details of the tile demonstrator will defined. This study
will finish in 2008. Two possible outcomes can be anticipated: Separated transmit
and receive functionality (bistatic operation) or a classical (monostatic case)
front-end solution with much simplified T/R modules without beam forming
functionality.
Significant advantages in front-end mass due to simplified thermal design and
integrated beamforming solutions are expected in both cases.
The activity shall include:
- Overall design of the tile breadboard demonstrator in consisting of
- Electrical design: Radiator, Front-end and beam former design.
- Thermal design
- Mechanical design showing integrated mass saving solutions
- Local oscillator and chirp signal generation.
- Test in a representative proof-of-concept environment
Future European SAR instruments based on active arrays, e.g.
ESA Sentinel 1 follow on significantly benefit from this new architecture.
Deliverables: - Integrated tile demonstrator breadboard
- Documentation
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
By 2014

ESA/IPC(2010)51
Annex 2, Page 6
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-009EE Budget: 500 K€
Activity Title: Low mass Calibration load demonstrator
Description: Radiometer instruments need hot and cold calibration measurements to achieve a
high radiometric accuracy. Cold calibration is usually done by looking into cold
space, but for the hot calibration a special load is needed. An absorber type of
load is used as a typical hot calibration target. However, if not only the feeds but
also the reflector has to be included in the hot calibration measurement the
absorber can become quite large (comparable to reflector aperture size).
Therefore, it is very important that for future radiometer instruments with relatively
large reflector sizes (e.g. Post-EPS) the mass of the hot load needs to be
minimised in order to be compliant with the instrument mass requirement.
The objective is to demonstrate by breadboarding low-mass calibration loads.This
activity is aimed at achieving low mass 0.5 to 1-m class of hot calibration targets
for future passive remote sensing instruments. Full use shall be made of activities
already performed. TA critical assessment shall be made of derived driving
parameters. A detailed design and analysis shall be performed of at least two
promising solutions where low mass and small volume is a driver. Finally, a
prototype hot calibration load shall be designed, manufactured and tested over the
full range of frequencies in a representative thermal environment.
Current TRL: TRL3 Target TRL: TRL4 Duration: 15 Months
Application /
Timeframe:
Post-EPS \ 2011
Ref. Number: G511-010EE Budget: 2,000 K€
Activity Title: Very large space antenna aperture - demonstration model
Description: The objective of this activity is the development of a P-Band SAR antenna partial
Engineering Model sufficiently representative to demonstrate the mechanical
behaviour, including deployment, together with the RF performances. The design
is expected to be based on the TRP development related to Biomass Earth
Explorer candidate. This activity is concerned with the development of a
demonstrator model for an unfurlable/deployable P-band antenna. The
Engineering Model shall be sufficiently representative with full mechanical,
including in stowed and deployed configuration, and demonstrate deployment and
RF capability. This development is necessary within the framework of the Biomass
Earth Explorer Mission development. The implementation of this activity is
conditional on the selection of the BIOMASS mission.
Deliverables: Antenna partial Engineering Model design , assembly and RF test. DD&T plan for
remaining actions up to flight antenna.
Current TRL: TRL2 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
BIOMASS \ 2012

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 7
Ref. Number: G511-011EE Budget: 2,000 K€
Activity Title: Multi Frequency high resolution GEO-sounder Demonstrator
Description: Microwave and (sub)millimeter wave atmospheric sounders provide information
on the distribution of radiation emitted by the atmosphere from which vertical
profiles of temperature and humidity through the atmosphere may be obtained.
Current generation of sounders are embarked on-board low Earth orbit (LEO)
satellites for providing primarily meteorological data for numerical weather
forecasting, and on the second level global observations for climate monitoring.
Across-track scanning of the antenna beam enables to achieve a wide
measurement swath exceeding 2000 km. Sufficient spatial resolutions can be
achieved around the nadir with a relatively small antenna size (around 1 m
diameter). However, due to the rapidly increasing incident angle for off-nadir
observations, the spatial resolution is greatly degraded towards the swath edges.
The global coverage is achieved by the combination of high ground-projected
speed of the spacecraft on polar LEO combined with the rotation of the Earth.
Continuity of data over tens of years is strongly supported by meteorological and
climate communities. Geostationary observations, unlike those from LEO
satellites, have the key potential advantage to provide continuous coverage of the
same region, which is essential for nowcasting. The basic requirements for
atmospheric sounding are high vertical resolution and measurement accuracy. In
contrast to LEO microwave sounders in operation today, the proposed GEO
instrument uses many more channels that range in frequency from 89 GHz
through to 874 GHz. Observations in microwave (MW) region, going up to
sub-millimeter-wave frequencies, are less affected by the presence of clouds than
TIR observations, and are used as complements those observations.
The objectives of this activity is to adapt/implement the GEO-sounder instruments
and demonstrate with an test campaign the multi frequency and high spatial
resolution performance of the concept.Several activities are being or have been
planned for demonstration of the GEO-sounder concept. The objective of the
present study is to combine mechanical and RF efforts and to demonstrate the
multi-freqeuncy and high spatial resolution performance of the (sub)mm wave
instrument.
a) consolidation and adoption of instrument requirements;
b) determining mechanical and RF interfaces
c) implementation of multi-frequency receivers and long baselines.
d) instrument integration;
e) definition of algorithms for instrument performance verifications;
f) performance consolidation of the selected design;
g) test campaign.
Deliverables: airborne ready GEO sounder demonstrator
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
Post-EPS, Gomas \ 2011

ESA/IPC(2010)51
Annex 2, Page 8
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-012EE Budget: 1,000 K€
Large aperture, ultra-stable, push-broom antenna with
Activity Title:
frequency-multiplexed beams
Description: The primary aim of PREMIER is to explore processes controlling the composition
of the mid/upper troposphere and lower stratosphere. The secondary aim is to
explore processes controlling the composition of the lower troposphere/boundary
layer and link to higher layers. To do this, PREMIER will measure IR and
millimetre-wave emitted radiation.
The mission objectives will be fulfilled by performing observations with three
distinct measurement techniques. One of them is a push-broom mm/sub-mm
(324- 504 GHz) wave limb sounder.
The objective of this activity is to ensure that the antenna which is one of the key
subsystems fulfils the stringent requirements.
A second objective is to maintain the technological lead that Europe has in
reflector antenna technology.This activity will be targeted to the following main
areas:
• review requirements and preliminary design
• Address critical technological areas identifying potential solutions.
• Perform critical breadboard development up to antenna level
The activity will start with a carefull assessment on the mechanical accuracy and
stability requirements.
This activity will identify and select the mechanical, thermal and technological
solutions and antenna architectures required to achieve the necessary accuracy
and stability for reflector antennas. These solutions/architectures will have to be
demonstrated by critical breadboarding .
Special emphasis shall be placed on the multi-fequency multiplexing.
A development plan to bring this technology to flight level should be provided.The
implementation of this activity is conditional on the selection of the PREMIER
mission.
Deliverables: Antenna EQM
Current TRL: TRL2 Target TRL: TRL3 Duration: 24 Months
Application /
Timeframe:
Sentinel 4, 5 premier \ 2011

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 9
Ref. Number: G511-013EE Budget: 650 K€
Activity Title: Cross Correlator ASIC development
Description: The objective of the current activity is to demonstrate by breadboarding the ASICS
needed in the GEO-sounder instrument and to enhance the European know-how
in this field.Current generation of Microwave atmospheric sounders are embarked
on-board low Earth orbit (LEO) satellites for providing primarily meteorological
data for numerical weather forecasting, and on the second level global
observations for climate monitoring. A cross-track scanning of the antenna beam
enables to achieve a wide measurement swath exceeding 2000 km. Sufficient
spatial resolutions can be achieved around the nadir with a relatively small
antenna size (around 1 m diameter). However, due to the rapidly increasing
incident angle for off-nadir observations, the spatial resolution is greatly degraded
towards the swath edges. The global coverage is achieved by the combination of
high ground-projected speed of the spacecraft on polar LEO combined with the
rotation of the Earth. Continuity of data over tens of years is strongly supported by
meteorological and climate communities. Geostationary observations, unlike those
from LEO satellites, have the key potential advantage to provide continuous
coverage of the same region, which is essential for nowcasting. The basic
requirements for atmospheric sounding are high vertical resolution and
measurement accuracy. In contrast to LEO microwave sounders in operation
today, the proposed GEO instrument uses many more channels that range in
frequency from 89 GHz through to 874 GHz. Observations in microwave (MW)
region, going up to sub-millimeter-wave frequencies, are less affected by the
presence of clouds than TIR observations, and are used as complements to those
observations.
This activity deals with breadboarding the ASICS needed in the GEO-sounder
instrument.The GeoMS instrument level requirements will be translated to a cross
correlator detailed requirement specification. The overall cross correlator design
will be developed in parallel as ASIC level design is started to enable a concurrent
design and optimisation process. Based on the cross correlator design and the
preliminary design results, the design goals for the cross correlator ASIC will be
derived. A scaled version of the cross correlator ASIC will be designed, produced
and tested. The test results will be analysed and system implications evaluated.
Deliverables: ASIC Design, tested samples
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
GOMAS \ 2011

ESA/IPC(2010)51
Annex 2, Page 10
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-014QC Budget: 350 K€
Activity Title: Reliability study and space evaluation of European planar Schottky diode
Description: Based on previous development and European state of the art Schottky diode, in
Europe, the aim of this activity is to assess and improve the quality and reliability
of the selected Schottky diode manufacturer for Millimeter and sub millimeter
application; Mixer and Multiplier This includes: characterisation of process and
parameter (DEC, TCV, RIC), determination of product reliability (life time),
establish space quality level production capabilities, Schottky diode technology is
considered to be the corner stone of all millimetre and sub millimetre instruments.
Indeed, Schottky diode technologies are used for mixer and frequency generation.
Today, the Europe is fully dependent of US source (VDI). These products required
for European space mission on technology capability that is not in the current
mainstream. As a consequence in order for Europe to maintain acces to high
frequency components ESA must support the industrial Schottky diode processes.
his component is essential for detection (mixer) and frequency generation
(frequency doubler), and Europe is fully depending on US Schottky diode to cover
our needs. This is a key component for future Earth Observation and planetary
exploration
Deliverables: Fully characterized schottky, documented production capability, PID, Schottky
demonstrator
Current TRL: TRL2 Target TRL: TRL6 Duration: 36 Months
Application /
Timeframe:
By 2010
Ref. Number: G511-016MM Budget: 350 K€
Activity Title:
High power narrowband lasers for laser cooling applications in Atom
Interferometry
Description: The task here is to prepare reliable high power laser cooling sources for
applications in Rb and Cs based Cold atom interferometers.The realisation of cold
atom interferometers in space for Earth Gravity applications will require the
development of a flight compatible sensor system. The cold atom sensor system
comprises atom production, cooling lasers followed by the atom launching,
splitting and re-combining of the prepared atoms. This first activity will focus on
the laser cooling laser systems, and due to the resonance cooling transitions in
Rb and Cs being located in the same spectral region as lasers used for optical
preparation of Rb and Cs atomic clocks some commonality of approaches can be
adopted. The major difference will be the required linewidth and the power.
Deliverables: Compound semiconductor based laser-cooling sources for Rb or Cs based cold
atom interferometers
Current TRL: TRL2 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
Atom Interferometry for Earth Gravity Post-GRACE type missions

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 11
Ref. Number: G511-017MM Budget: 500 K€
Activity Title: Monolithic filter on detector dye integration technologies
Description: Evaluation of potential filter materials and direct-deposition processes directly on
the detector for (one of) the main technologies (Si, InGaAs, MCT), Si being the
priority.
A two-phased contract shall be foreseen:
1. Establishing feasibility through a comprehensive study
2. Proof of concept demonstration only if feasibility of at least one solution is
evidentA recurring problem in multi-/hyper-spectral imagers is the (stripe) filter
accommodation where strongly performance-degrading optical cross-talk, fringing
as well as mechanical robustness are everlasting issues. This activity shall
investigate the feasibility of directly processing optical filters onto the detector die.
While depositing optimized AR coatings (even as a variable wedge across the
array) can be considered standard procedure, the feasibility of such direct process
is far from obvious for a narrow-band optical filter. Apart from optical
performances (bandwidth, out-of-band rejection), compatibility of the process with
the underlying detector itself must be considered.
Deliverables: Proof of concept demonstration
Current TRL: TRL2 Target TRL: TRL3 Duration: 24 Months
Ref. Number: G511-018ET Budget: 1,500 K€
Activity Title: EES Ka band High Data Rate Payload Data Transmitter Engineering Model
Description: The development of an engineering model for a high data rate telemetry
transmitter and receiver chain demonstrator in the Ka-band (25.5-27 GHz)The
Ka-band (25.5-27 GHz) has been allocated for the high rate payload telemetry of
Earth Exploration Satellites and for the Near Earth Space Research satellites.
Currently, all Earth Observation Payload Data Transmission’s system are using
the EES X-band frequency allocation and it is expected that within the next ten
years this band will be severely congested. Coming missions also require very
high data rates that cannot be accommodated in the EES X-band allocation.
System studies are ongoing in ESA in preparation for the transition to Ka-band
operation;
The activity shall comprise:
The development of a transmitter EM, this unit shall be modular and able to
handle data rates of up to 1 Gbps (at least). Trade-offs on architecture shall be
performed.
The investigation of the elements of the receiving chain: LNA, downconverter and
demodulator. The activity requires the development of an engineering model of
the critical ground station equipment identified.
Deliverables: Transmitter Engineering Model and Critical Ground Station Equipment
Current TRL: TRL1 Target TRL: TRL5 Duration: 16 Months
Application /
Timeframe:
All future EO missions \2012

ESA/IPC(2010)51
Annex 2, Page 12
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-019GI Budget: 150 K€
Activity Title: Parallel computing for fast TM processing during short passes
Description: The Earth Observation Satellites download their stored House Keeping data at a
high rate during very short passes. The Mission Control System is not able to
cope with such a rate and this leads to cumbersome storage and re-playing
processes. The result is that the stored TM is only available for display much after
the pass. The objective of this study would be to analyse whether SCOS-2000 TM
processing can be modified to use parallel computing in order to increase as
much a possible the processing speed, and eventually cope with the mass
memory dumps TM in real-timeThe study has two phases. In a first phase the
problem is analysed and a technical solution derived for the parallelisation of the
tasks related with the TM processing (Packetiser, distributor, Behaviour Limit
Checker, Saved Synthetic Parameter calculation, Storing into the archive). In a
second phase, a prototype is developed, covering at least the packetiser and
injection into the archive.
Deliverables: Proof-of-concept prototype source code, executable and test data
Current TRL: TRL2 Target TRL: TRL5 Duration: 12 Months
Application /
Timeframe:
Future EO missions
Ref. Number: G511-020ET Budget: 400 K€
Activity Title: Membrane circuits for high frequencies
Description: To develop integrated Schottky circuits on thin membranesThe roadmap for the
development of European Schottky technology is based on the principle that, if
possible, the main development effort, leading to the industrialisation for the main
applications at 300 to 500 GHz frequency range, would be largely funded by EC,
and that complementary development actions are taken by ESA. Technology for
the higher frequencies, up to THz, is the most challenging and least developed,
and pre-development of integrated Schottky structures for these applications is
being carried out in a current TRP activity. The aim of the present GSTP activity is
to continue that development by concentrating on integrated circuits on a
membrane, so that Schottky devices also for the highest frequencies reach
sufficient maturity for subsequent industrialisation.
Deliverables: Report, hardware demonstrators
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
Post-EPS (MWI), Ciwsir, Tandem, Laplace, EVE, FIRI / 2011

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 13
Ref. Number: G511-021GR Budget: 200 K€
Preparation of an advanced standalone error prediction module for SAR
Activity Title:
interferometry (PEPSI)
Description: The objective of the work is twofold.The primary objective is to develop an
advanced stand-alone error prediction module for SAR interferometry, based on
data-dependant statistical models for the major error sources, namely
atmospheric propagation and phase unwrapping.
Secondly, since an interferometric processor capable of interfacing with an error
prediction module was delivered to ESA during a previous project, support for a
selection of recently available and previously unsupported SAR sensors within this
processor is envisaged.
Concerning the standalone error prediction module, the main tasks of the activity
are:
1. Error prediction framework mathematical formulation and implementation. The
InSAR processing algorithm assumptions should allow application of the
framework to the products of several available and commonly used InSAR
software packages.
2. Development of a statistical model for atmospheric propagation errors, capable
of using data from numerical weather prediction models and/or other satellite
sensors (e.g. imaging spectrometers).
3. Development of a statistical model for phase unwrapping errors. The model
should be scene and processor dependent, i.e. the predicted error should be
sensitive to the unwrapping difficulties of the scene and to the complexity of the
unwrapping algorithm used. Possibly, the magnitude of multiple-cycle errors
should be estimated, using external data if needed (e.g. a coarse DEM for height
measurement, or speckle/feature-tracked range offsets for displacement).
Concerning the support of recent and previously unsupported sensors within the
interferometric processor, it is proposed to choose three of these from the
following list, upon project start and in agreement with the Technical Officer:
Radarsat-1, Radarsat-2, ALOS-PALSAR, TerraSAR-X, COSMO-SkyMed.
Support should be provided for the Single Look Complex products, in slant range
geometry.Within the current state of the art, interest for the proposal's primary
activity is elicited by the fact that currently several InSAR processors are available
to the scientific community, but the derived height and displacement products are
generally not accompanied by a quality measure (error standard deviation) which
accounts for the major error sources, i.e. atmospheric propagation and phase
unwrapping. The InSAR scientific community would therefore benefit from the
availability of a stand-alone error prediction module, capable of keeping these
error sources into account. An interferometric processor and a simpler Error
Prediction Module (EPM) were delivered by the applicants during a previous
GSTP funded project "Preparation of Interferometric SAR processor (COISP)".
The EPM could be operated within the interferometric processor as well as a
standalone program.
The secondary objective of this proposal is aimed at making the interferometric
processor delivered in the previous project, as well as the advanced EPM which
can be operated within it, useful to a broader range of users, by including support
for recently available sensors.
Compared to the activity proposed above, the error prediction framework
developed in the previous project requires broadening, in order to be compatible
with a larger range of InSAR processing algorithms. Furthermore the
data-dependence degree of the models must be increased significantly,
particularly concerning atmospheric error prediction. Concerning phase
unwrapping, the main open challenge lies in developing and testing an algorithm

ESA/IPC(2010)51
Annex 2, Page 14
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
capable of predicting the likelihood of multiple-cycle errors.
Deliverables: 1. Advanced standalone error prediction software for InSAR.
2. Support for a minimum of three new sensors (to be chosen with the Technical
Officer at project start) within a previously developed InSAR processing software.
Current SW
Readiness Level: Prototype
Application /
Timeframe:
Justification for DN:
Target SW
Readiness
Level:
S/W Release Duration: 24 Months
Applicable to the "Architectures and standards" EO User Segment "Mission".
2010
This activity is a follow up of the work developed by Technical University of
Denmark under a previous GSTP activity, G104-39GD, "Preparation of
Interferometric SAR processor - COISP", funded by GSTP-4 with 200 K€
(contract number 19482).
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 15
Ref. Number: G511-022GR Budget: 400 K€
Automated Service Builder for Semantic Service Oriented Architectures
Activity Title:
(ASB)
Description: The objective is, within Service Oriented Architectures (SOA), to assess the
feasibility and to develop the principles (fundations) of a technology allowing a
generic system to answer new user needs by taking the existing services and
automatically composing them together in order to deliver the expected, new
service.
The activity is divided into two threads:
* a study thread, that aims at defining the principles allowing such automated
service builder to work (design task);
* a demonstration thread, that aims at implementing a technology demonstrator,
for confirming feasibility and for identifying needs for new enabling standards.
Nowadays, there is a trend for exposing services via the principle of Service
Oriented Architecture. The composition of these services to build new processing
chains (workflows) capable to meet user needs remains an expert's task. The idea
is to take immediate advantage of new services that are created/added and hence
shorten the time before the user needs can be met, to better exploit existing
infrastructures and to foster new synergies. Such technology would allow
developers to concentrate on the implementation of SOA building blocks services
that afterwards can be freely combined, even in ways not anticipated, to meet
user needs not known in advance. The technology would therefore provide a layer
of “problem solving” on top of the supporting infrastructure, and can be seen as
the exploitation of Knowledge Engineering techniques, Semantic and Ontological
techniques and Artificial Intelligence techniques (problem solving) on top of SOA
functional blocks.
Status of the art includes:
- Various research and prototype developments of Semantic Service Oriented
Architecture (SSOA) applications.
- Emerging standards for semantically enabled services.
Deliverables: Feasability study report, Software prototype, Initial recommendations for enabling
standards.
Current SW
Readiness Level:
Application /
Timeframe:
Target SW
Readiness
Level:
Prototype Duration: 18 Months
Applicable to the "Knowledge and semantics" EO User Segment "Mission". All
services, related to any EO mission and also to non-EO data, published according
to the supported standards will benefit from the results of this activity. End 2010

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-023GR Budget: 200 K€
Activity Title:
Automatic, Semantic Image Information Mining from Time Series of VHR
images (ASIM)
Description: The objective of this activity is to extend the approach of the Image Information
Mining - Time Series (IIM-TS) TRP project to the automatic extraction of
information from Very High Resolution (VHR) images through the implementation
of an automatic land cover change / land use classification system based on the
application of the SOIL MAPPER® software to VHR satellite data. It implies three
main steps:
- implementation within the Knowledge-centred Earth Observation (KEO: TRP
project) environment of a Feature Extraction Processor (FEP) based on the SOIL
MAPPER® VHR software package for image pre-classification
- application of this FEP to a time series of VHR satellite images to create and
validate the preliminary classification maps
- development, implementation and test of a fully automatic multi-temporal land
cover change / land use classification system based on time series of preliminary
classification maps.
The final system, in a prototype version, will be linked to the time series
visualisation tool developed in the framework of the IIM-TS project.
Land cover change / land use analyses are normally performed on the basis of
semi-automatic processing systems that involve subjective interpretation by a
human operator. The application of human-based technologies to large amount of
VHR data is extremely time consuming and provides often subjective results. The
proposed activity is based on the adaptation and use of a registered software
named SOIL MAPPER® that allows overcoming both time constraints and
subjective interpretation. Its implementation within KEO will make available an
efficient component capable to extend the results that can be expected from the
IIM-TS project.
The MEEO SOIL MAPPER® is an innovative, state-of-the-art,
application-independent, rule-based pre-classifier of Remote Sensing (RS)
images and is based on spectral prior knowledge exclusively. It allows processing
multispectral Top-Of-Atmosphere calibrated mid-to-very-high resolution satellite
images to generate a preliminary classification map where each pixel is
associated with one semantic label belonging to a discrete set of spectral
categories (each spectral category is linked to a semantic meaning). In its mid and
high resolution versions, SOIL MAPPER® has been already applied to other ESA
projects (KEI, CARD) and is available on the Service Support Environment (SSE:
result of other GSTP projects) portal for free of charge use until May 31st, 2009.
In this proposed activity SOIL MAPPER® output maps are used to develop a fully
automatic land cover change / land use classification system.
Deliverables: KEO FEP Module, Documentation, Prototype
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Justification for DN:
Target SW
Readiness
Level:
Prototype Duration: 9 Months
Applicable to the "Information extraction and data fusion" EO User Segment
"Mission". Specific optical VHR EO missions will benefit from the results. Second
half 2009
MEEO (I) has the property rights for the SOIL MAPPER® tool and has the
required expertise to implement this activity based on the previous work they
have developed in other TRP contracts.
Non-competitive tendering is justified according to Article 6.1. a) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 17
Ref. Number: G511-024GR Budget: 2,500 K€
Activity Title: Decision Support and Real Time EO Data Mangement (DREAM)
Description: The recent programmatic efforts in EO have addressed the use of EO data for the
delivery of services with particular emphasis for global phenomena. This has been
an opportunity for the evolution of standards and technologies needed to fill the
gaps in data identification, satellite tasking and to a certain extent, as well data
delivery. The progress made outlines as well some gaps existing in more closely
addressing the requirements of specific users needing to rely on multiple data
sources and having to take decisions in short timeframe.
This project shall address all the issues which arise when decision support
systems need to exploit information based on EO data which may be acquired
and made available within a pre-defined time window. This includes: analysis of
avaiable data in the archives, feasibility analysis of the satellite acquisition in the
area(s) of interest, identification of the "best" patchwork of acquisitions and set up
of contingencies. The project shall address scenarios including the dynamic
transfer of EO data towards the decision support system.
The overall architecture of the decision support system shall be based on two
conflicting) requirements:
- an open service oriented architecture
- an advanced IT secure architecture
The requirements for the DREAM project shall be defined together with EUSC
which is the owner of business cases very similar to the one described. The
DREAM project should be able to exploit the know how acquired at ESA and
European industry on the management of complex workflows in order to support
the automated execution of complex tasks. The DREAM project should be able to
capitalise on the work done in defining standards for feasibility analysis of sensor
tasking within the Heterogeneous Missions Accessibility project and on the
Service Support Environment developed by Spacebel in previous GSTP activities,
Deliverables: The DREAM prototype shall deliver a beta verion of the decision support system,
after at least six months of persistent demonstration and test.
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Target SW
Readiness
Level:
Beta Version Duration: 24 Months
Applicable to the "Architectures and standards" EO User Segment "Mission".s.
2011

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-025GR Budget: 2,000 K€
The EO Image Librarian: EO image and geoinformation intelligence search
Activity Title:
engine (EOLib)
Description: In support to EO image and geoinformation intelligence, the EO Image Librarian
objective is to identify a path towards a next generation EO search engine and
value adding tools capable to create "live" products tuned to user needs.
The areas to be addressed include:
- Image content interpretation (also through multi-resolution clustering on
N-dimensional spaces of user selectable features), categorisation, semi-automatic
annotation with geo-referencing (supported by other data sources) and semantic
representation
- Combined use of low, medium and high resolution images
- Natural language user’s inquiry understanding, also through refinement
dialogues
- Interactive, semantic, user friendly and domain specific searches for content in
distributed archives of EO images and time series
- Identification, extraction, categorisation and semantic representation of related
geospatial information from distributed GIS / maps repositories, Internet, photos,
specific documentation, etc.
- Dynamic associations of both information types through ontologies
- Suggestion of most appropriate products and alternatives also through advanced
visualisations
- Dynamic creation of specific products tuned to user needs
The tasks to be performed in order to reach the objective while addressing the
above areas include
- Identify relevant use cases
- Analyse similar implementations in EO and other domains
- Study existent and identify missing methods / technologies
- Define an architecture capable to combine the selected methods / technologies
- Implement a prototype, by combining existing methods / technologies and
developing the missing ones, capable to provide the key functions
- Assess the prototype with key users and verify performances
- Define the steps and the additional developments needed to implement an
operational systems
In order to speed-up development, EOLib will be based on the outputs of the
Knowledge-based Information Mining (KIM) and Knowledge-centred Earth
Observation (KEO) TRP projects. The correctness of this approach is supported
by the new solutions for better products under formulation at DLR thanks to the
KIM / KEO instance (under operational validation) interfaced with the TerraSAR-X
archive. The EO Image Librarian will be a
new system and flavour of tools that in continuation of KIM and KEO will give
solutions to automating the mining (extraction) of information from EO archives
that can lead to knowledge discovery and the creation of actionable intelligence
(exploitation). The EO Image Librarian is more than just an extension of data
mining principles to images. It will extract information and aggregate it from of
multi-mission EO images and other non-image sources, e.g existing maps, GIS, in
situ information and measurements, text description, Internet resources, etc.
Thus, new algorithms and tools will extract relevant features from multiple data
sources, structure this information, identify objects and automatically record and
analyse their interrelationships to learn their behaviour so as to be able to detect
relevant information. The methods are integrated in systems, which can be
operated using intelligent interfaces able to correlate the information content of the
images with the relevant goals of the application.
The users will have at their disposition tools for the definition of specific goals
using semantics. The problem of the large dimensionality, which for
computationally efficient data analysis is of primary concern, is solved using

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 19
pre-extracted representative features instead of raw images.
The goal is to have machines more closely interacting at human conceptual levels
(i.e.: automate the human remote sensing analyst). Unlike the respective hard
computing methods, soft computing may cope with problems that deal with
imprecision, uncertainty and learning, and are better candidates to construct
systems and models which are simple, applicable, user-friendly, and fast.
Deliverables: Updates on relevant implementations and methods / technologies, Use cases and
architecture, New outputs, Prototype, Prototype assessment results, Suggestions
for future steps
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Justification for DN:
Target SW
Readiness
Level:
Prototype Duration: 24 Months
Applicable to the "Information extraction and data fusion" and "Knowledge and
semantics" EO User Segment "Mission", Mid 2011
This activity is a direct continuation of the work developed by DLR (D) and
ACS (I) in several previous TRP activities, "Knowledge Driven Information
Mining in Remote Sensing Image Archives" (contract number 15469),
"Knowlege Centred Earth Observation" (contract number 18345) and "Image
Information Mining - Image Time Series" (contract number 20433).
Participation of other subcontractors as INDRA (E) and ARC (A) is envisaged.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-026GR Budget: 2,000 K€
Activity Title: European Service Support Environment Enhancements (ESE)
Description: Previous GSTP projetecs lead to the development of an environment for
orchestrating EO and GIS services which has proven to be a breakthrough tool
both for developers and the Agency alike which is exploiting it as Service Support
Environment (SSE). However the evolution of technologies requires the design
and prototyping of a next generation of such environment in order to address
several technological and organisational challenges:
Among the topics to be addressed at organisational level there is the requirement
to support:
- Service Level Agreement (SLA) management issues and challenges in a Web
Services environment by an automatic support to SLA specification, creation and
monitoring on a distributed environment.
- simplify and or automate the dynamic design and customisation of Graphical
User Interfaces addressing customer or project specific visualisation needs
including 3D techniques, embedding of portlets in thematic portals, and seamless
integration with collaborative environmants.
- dynamically discover and support user and data acces policies defined by
service providers and data owners.
On the technogy side it is as well necessary to address a combination of
consolidating technologies on the configuration and performance management of
high end performant systems (like hot redundancy) as well as an evolution of
more basic architectural elements like the version 2 of the Service Oriented
Architecture
Deliverables: 1. Demonstration systems
2. Target system specifications and implementation documentation
3. Report and recommendations
Current SW
Readiness Level: Prototype
Application /
Timeframe:
Justification for DN:
Target SW
Readiness
Level:
Beta Version Duration: 30 Months
Applicable to the "Architectures and standards" EO User Segment "Mission". Mid
2011
This activity is a direct continuation of the work done by the industrial team led
by Spacebel (B) in the previous GSTP activity G104-35GD, "Enhanced
Services Infrastructure Technology (ESIT)", funded with 2.1 M€ by GSTP-4
(ESA contract 18971). It is recomended to continue the work with the same
industrial team: Spacebel and GIM.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 21
Ref. Number: G511-027GR Budget: 150 K€
Activity Title: New Sensors Study for Soil Mapper Application and SSE Integration (NSS)
Description: The objective of the activity is to analyse and test how DMC sensors can profit
from the automated SOIL MAPPER® pre-classifier and the Service Support
Environment (SSE).The tasks to be performed include:
- Proof of concept of accuracy and efficacy, progressing to full integration of DMC
data models and characteristics into the SOIL MAPPER® fully automated
pre-classification tool, for current and future DMC missions.
- Analysis of outputs and services possible with SOIL MAPPER®.
- Study and documentation of interfaces required for integration into SSE along
the lines of the Heterogeneous Mission Accessibility (HMA) effort.
- Test services implementation.
Automatic classification tools are not common and are dificult to realise effictively.
DMC data is suitable for the purpose (as proven by similar implementations of the
classification tool).
In the context of ongoing developments of ESA interfaces to the Disaster
Monitoring Constellation, it is prudent to ensure the data is supported.
Deliverables: Data package inputs to and outputs from the SOIL MAPPER® tool, available for
public assessment (data package including source DMC imagery, related product
manual and SOIL MAPPER® method description), Test services published in
SSE, Specifications for SSE environment integration for future HMA interface
development work. TRL6 by 2010
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Justification for DN:
Target SW
Readiness
Level:
Prototype Duration: 12 Months
Applicable to the "Information extraction and data fusion" EO User Segment
"Mission". Applicable in particular to DMC sensors and services as pre-emptive
developments to complement the HMA integration activities. End 2009
DMC International Imaging (UK) is the sole supplier of DMC data and MEEO
(I) owns the property rights of the SOIL MAPPER® tool and has deep
expertise on implementations of SSE services based on this tool. It is
recommended to procure this activity in direct negotiation with the industrial
team consisting of DMC International Imaging and MEEO (I).
Non-competitive tendering is justified according to Article 6.1. a) of the
Contracts Regulations.

ESA/IPC(2010)51
Annex 2, Page 22
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-028GF Budget: 500 K€
Activity Title: Open-standard Online Observation Service (O3S)
Description: A family of specifications of the Open Geospatial Consortium (OGC) currently
under evolution is addressing the access, visualisation, and exploitation of
observations and EO data. These specifications shall be implemented in the form
of O3S demonstration services and shall be verified and validated in an
international endeavour. An "in-network processing" solution combined with
intelligent caching shall be furthermore demonstrated in O3S for the handling of
data resources and processing capabilities which are distributed in the Internet.
Mechanisms will be implemented where small algorithms can be transferred and
applied to large volumes of data in a way saving bandwiths and optimizing
resource utilization.An active participation in the OGC discussion and specification
processes shall be part of the O3S activity.
The O3S technical solutions and implementations will be communicated and
cross-checked with the GIGAS Coordination and Support Activity in the EU 7th
Framework Programme (GIGAS stands for "GEOSS, INSPIRE, GMES an Action
in Support").
Satellite archives such as ESA's Envisat MERIS repositories or Member State
archives (such as Pléiades to which Austria holds defined mission access rights)
are candidates for which the services shall be demonstrated in the project.
The project is designed in response to emerging requirements for (re-)opening
Earth Observation satellite data archives and for applying (re-)processing to the
(historic series of) data to generate global change parameters (e.g. the so called
"essential climate variables") and to carry out mapping and topographic activities
with the goal "to understand better, in order to react better" in the future
management of our environment.
The Austrian space industry and ARC in particular have, from the early days on,
been actively involved in OGC standards setting. The O3S project described here
shall further ramp-up Austrian contributions to OGC standardization by performing
well-selected reference implementations of Web service interoperability standards
for online (satellite) data access and Web mapping.
The primary OGC standard to be implemented in O3S is the Web Coverage
Service (WCS) (ref. 1). Currently several extensions of the WCS are discussed
within OGC. These extensions include a ProcessCoverage operation also called
Web Coverage Processing Service (WCPS) (2), transaction operations to ingest
data to the WCS (3), a JPEG 2000 and the related streaming protocoll JPIP
coverage format extension (4) (5), an asynchronous GetCoverage operation (6),
etc.
References to specifications are:
(1) Web Coverage Service (WCS) Implementation Standard, Version 1.1.2 from
2008-03-19, OGC Document: 07-067r5
(2) Web Coverage Processing (WCPS) Implementation Standard - proposed draft
-, Version 1.0.0 from 2008-04-29, OGC Document: 08-068
(3) Web Coverage Service (WCS) — Transaction operation extension, Version
1.1.3 from 2008-04-21, OGC Document: 07-068r2
(4) WCS 1.1 Application Profile for JPEG 2000 Coverage Encoding, 1.0 from
2007-11-28, OGC Document: 07-145
(5) WCS 1.1 Application Profile for JPIP Coverage Encoding, 1.0 from
2007-11-28, OGC Document: 07-146
(6)
https://portal.opengeospatial.org/twiki/bin/view/WCSrwg/AsynchronousGetCovera
geResponses

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
There has been no related previous TRP/GSTP activity.
ESA/IPC(2010)51
Annex 2, Page 23
Deliverables: Demonstration systems, Target system specifications and implementation
documentation, Report and recommendations
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Target SW
Readiness
Level:
Beta Version Duration: 18 Months
Applicable to the "Architectures and standards" and "Information extraction and
data fusion" EO User Segment "Missions". End 2010.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-029GF Budget: 320 K€
Activity Title: Ontology Based EO Search (OBEOS)
Description: The high number of Earth Observation missions is producing a tremendous
amount of sensor specific images archived in ESA infrastructure (HARM) that
need a long term strategy for archiving and ease of use. The project aims to
define a semantic concept study and to implement an EO Ontology based Service
Oriented framework prototype, able to take into account specific questions meant
to support the evolution of complex data sets into user useful specific information
(i.e., which geographical area across Europe has an ozone level above a given
threshold for more than a week in a row and over a period of 10 years? or which
SAR data set is available to perform slow-moving landslides interferometry
assessment? ). The ontologies will be used in order to created models upon which
intelligent queries can be applied. The prototype
will be verified through two example use cases:
1. Air Quality Monitoring (based on Envisat SCIAMACHY and GOME sensors)
2. Landslides Monitoring (based on ERS and Envisat radar data and
interferometric technology)1. Ontology for EO Concept Study
A concept study will be done for the definition of semantics based on the
production of simple but innovative metadata files which contains statistical
information. The creation of strategy and prototype will focus upon SCIAMACHY
and GOME sensors for the air quality monitoring and upon Envisat and ERS radar
data for landslides monitoring.
The study will provide an analysis of the existing data in order to provide an
ontology based solution that will define:
•the approach of the ontological model (single, multi, hybrid).
•the type (domain, hierarchical, etc) of the ontologies that will be used,
•the methodology that will be followed for the ontologies development and
•the language that will be used in order to model the development.
The second milestone of the study is to create a pool of ontologies that can be
used for the definition of the metadata. The ontologies will be used as semantic
wrappers upon which the SOA solution will be based.
2. EO-Ontology System Design
and
3. EO-Ontology based Service Oriented framework prototype implementation:
The Ontology based Service Oriented framework will enable the definition and
development of software instances of the produced ontologies (as web services).
This set of web services will act as an application server to higher levels. Thus the
proposed software solutions will:
1. Use ontologies and semantics to define the specifications of the services
2. Associate the semantic definition of the concepts to the repositories using
intermediate ontologies.
3. Use a set of design time (Concepts and Services designer) and run time
components (Administration Server, Publication Server) to develop integration
components
The two tasks will design and implement this prototype.
4. User engagement, Dissemination and promotion
The main objectives of Task 4 are to assess the user acceptance of the products
and services, to further analyse the servicing capacity with a sustainability
analysis and to promote the project achievements in the user community. Part of
the activity will be a prototype demonstration workshop.
Deliverables: EO-Ontology Concept Study, EO-Ontology Concept System Design, EO-Ontology
based Service Oriented framework prototype, Demonstration Workshop and
dissemination activities outcomes, Managerial documentation (according to
ECSS)

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Target SW
Readiness
Level:
ESA/IPC(2010)51
Annex 2, Page 25
Prototype Duration: 14 Months
Applicable to the "Knowledge and semantics" EO User Segment "Mission". In
principle the proposed technology is applicable to all kinds of EO data, in
particular for EO data with a high temporal frequence. However, the main goal is
to enable a conceptualized search access for the full exploitation of ESA EO
missions archives. End 2010
Ref. Number: G511-030GR Budget: 720 K€
Activity Title: Rapid Response Support Server (RARE)
Description: The objective of the Rapid Response Support Server is to allow the rapid
integration, at the semantic level, of relevant EO products with actual ground data
from the affected area and related background knowledge for a specific incident.
The tasks will include design and implementation of features permitting:
1. Semantic integration of EO data and ground data as well as background
information (infrastructure data, civil engineering data, power and gas lines etc.).
Such integration can be rapidly done only by providing beforehand ontologies for
the EO data, as well as early designs for ontologies relevant to the application
domain (for example to different disaster, humanitarian, environment, crisis or
security incidents).
2. Advanced queries (including natural language queries), inferencing, prediction
and data presentation using the data semantics.
3. Data presentation and delivery in various formats, including formats suited for
hand held applications.
It should be possible to quickly set-up the Rapid Response Support Server in
cases of natural disaster, humanitarian crisis or security crisis, basing it on a
semantically rich description of the event to be supported. This semantic
information linked to the specific application domain will make data utilisation
(including EO products) easier.
The project can benefit from experience gained other activities like the SATOPI
GSTP project.
Deliverables:
Relevant information sources include INSCRIT, INSPIRE, OASIS
Software prototype, Technical Report
Current SW
Readiness Level:
Target SW
Readiness
Level:
Prototype Duration: 24 Months
Application / Applicable to the "Knowledge and semantics" EO User Segment "Mission".
Timeframe: Applications concerned with disaster / crisis handling might benefit from the
results. End 2010
Long experience in Topic Maps and related knowledge management

ESA/IPC(2010)51
Annex 2, Page 26
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-031SF Budget: 650 K€
Activity Title: Development and Testing of the AGGA-4 Device. Phase 2
Description: The development of the first AGGA (Advanced GPS/GLONASS ASIC) device was
initiated in 1995. The current version of the AGGA chip, the AGGA-2, is being
used by several European industries and is the key component of the Global
Navigation Satellite System (GNSS) instruments flying on a large number of EO
missions. Under a previous ESA activity, additional functionality has been added
to the AGGA-2 device, including the capability to process new GNSS (Galileo and
modernized GPS) public signals, as well the integration of more functionality
on-chip (e.g. LEON micro-processor among others). This VHDL design is known
as AGGA-3. In a follow up TRP/EOP activity, an update of the AGGA3 design is
being done (AGGA4) in order to comply with the latest Galileo signals and to
maximise number of channels in a chip. The output includes review of
specifications, architectural design, breadboarding with FPGA, and firmware
software.
The objective of this activity is to manufacture and test the AGGA-4 ASIC
component capable of processing Galileo and GPS Modernized signals fulfilling in
particular the needs of atmospheric sounding by radio occultation (which requires
multiple GNSS capability) and for Precise Orbit Determination (POD).
The main tasks foreseen are: detailed design; feasibility study of ASIC; layout,
manufacturing and testing of ASIC samples. This Activity builds up on the output
a previous TRP/EOP activity "Development and Testing of the AGGA-4 Device",
where the specification and architectural design of AGGA-3 will be updated in
order to comply with the latest changes in the Galileo signals. This activity also
takes advantage of the verification on an FPGA breadboard and firmware done in
previous tasks of the above contract.
Deliverables: ASIC samples as well as the VHDL design model. As for previous AGGA designs,
the IPR remain vested on the Agency. No breadboard is to be produced or
delivered.
Current TRL: TRL3 Target TRL: TRL4 by 2010 Duration: 7 Months
Application /
Timeframe:
Justification for DN:
2011 – New developments of miniaturised GNSS receivers will need the AGGA-4
ASIC component in GNSS instruments, e.g. for radio occultation on Post-EPS (to
fly it in 2018) and for Precise Orbit Determination (POD) on earlier satellites.
This activity is a direct continuation of the work being developed by Astrium
GmbH in the phase 1 of this activity (contract 16831, rider 1), funded with 900
K€ by TRP and EOP. In addition, the participation of ATMEL (D,F) as
subcontractor is required as this company is the only supplier of space
application integrated circuits (ASIC) in Europe.
Non-competitive tendering is justified according to Articles 6.1. c) and 6.1.a) of
the Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 27
Ref. Number: G511-032MM Budget: 500 K€
Integrated MEOS LiNbO3 Mach-Zehnder interferometer for spectrometry in
Activity Title:
the 0.5 to 5 micron spectral region
Description: Recent technological progress achieved on low loss LiNbO3 waveguide
technology and integrated MZI have shown that a micro-optical-system MZI can
be designed and built to engineering and radiometric standard (mass, power,
sensitivity and spectral resolution) of applicability to spectrometry requirements of
the kind found in missions like Sentinels 4/5 or as the candidate Earth Explorer
mission TRAQ. The development could be also applied to planetary exploration
missions. This proposed activity will cover the design, development and test of
MZI spectrometer. The following subsystems will be devoloped into a
representative instrument: Front-end optics, solid-state LiNbO3 Interferometer,
detection, and Control/Driving electronics
Deliverables: Instrument demonstrator to TRL 4/5 of the MZI Spectrometer
Current TRL: TRL3 Target TRL: TRL5 by 2012 Duration: 30 Months
Application /
Timeframe:
Justification for DN:
Future remote sensing requirements for Planetology Spectrometry and Earth
Observation.
Continuation of previous TRP and ASI funded activities.
Non-competitive tendering is justified according to Articles 6.1. c) of the
Contracts Regulations.

ESA/IPC(2010)51
Annex 2, Page 28
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G511-033GS Budget: 1,000 K€
Activity Title: Prototype of 26 GHz receiver for EO
Description: Develop a first prototype of on-ground receiver for signals in the 25.5 to 27 GHz
frequency band.
Tasks:
1- Functional critical analysis of the technical specifications
2- Architectural definition and analysis of the receiver
3- Receiver prototype design
5- Receiver prototype development
6- Receiver prototype validation & testing.
This prototype will require the integration of commercial components where
available, and possible development of other modules that are not available in
these frequencies or with the required bandwidth.
The prototype will include at least:
a- Direct ADC from L band input signal
b- Adaptive band equalisers to reduce group delay effects
c- High data rates up to 1 Gbps
d- Demodulation of advanced modulations like Variable Coding Modulation VCM,
4D-TCM and other modulation techniques in approved or in-preparation CCSDS
and ETSI standards, and its corresponding coding schemes.
e- Capabilitiy for decoding Turbo codes, Punctured parallel Turbo codes, Serial
Turbo codes , Product codes and LDPC codes.
f- Fast signal acquisition
g- Local M&C interface embedded in the receiver
h- Remote M&C interface through LAN.
i- Capability for local storage of received TM for a long period
j- Capability to deliver the received TM data trough a high speed LAN
k- Increased reliability by redundant power supplies and Hard disk has to be
analysed.
A concept for the transmitter to be used as test equipment shall also be
envisaged. The resulting prototype shall be industrialised in a follow-on activity.
Deliverables: Breadboard of a receiver
Current TRL: TRL2 Target TRL: TRL4 by 2011 Duration: 18 Months
Application /
Timeframe:
Earth Observation missions would need to move to 26 GHz band in the near
future, due to higher data rate and wider bandwidths required, and the congestion
of X band. Meteosat Third Generation (MTG) and Sentinel 4 are already good EO
candidates to move to this band. Moreover the receiver is also of application in
other stations (34 meters) for Science, where already the EUCLID mission
(orbiting in L2) will take benefit of the wider bandwidths available in the 26 GHz
band.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 29
Ref. Number: G511-034GS Budget: 800 K€
Design of S/K-Band Ground Station Antenna (13-15m aperture) for LEO
Activity Title:
application
Description: Design a 13-15m ground antenna for transmitting in S-Band and receiving in
S/K-Band (K-Band: 25.5 to 27 GHz). The design will include the integration of
commercial components, where available, and development of critical items that
are not available, e.g. multifrequency feed and dichroic mirrors. The design will
include part of the structural model of the antenna, integration with the LNA, etc. A
strategy for the simulation testing shall be established. The design and the
breadborded items shall be industrialised in a follow-on activity together with the
13-15m antenna.
Deliverables: Design of a 13-15m ground station antenna operating in S/K-Band (receive and
transmit) and breadboarding of critical items.
Current TRL: TRL2 Target TRL: TRL4 by 2011 Duration: 18 Months
Application /
Timeframe:
Earth Observation, partially applicable to Near Earth for Science
Ref. Number: G511-035GS Budget: 1,000 K€
Activity Title:
Prototype of K-Band Ground Station Antenna (6m aperture) for LEO
application
Description: Develop a first prototype of ground station antenna (6m aperture) for receiving
signals in K-Band (25.5 to 27 GHz frequency band). This prototype will require the
integration of commercial components where available, and possible development
of other modules that are not available in these frequencies. The prototype will
include part of the structural model of the antenna, integration with the LNA, etc. A
strategy for the simulation testing shall be established. This resulting prototype
shall be industrialised in a follow-on activity.
Deliverables: Prototype of a 6m ground station antenna operating at 26 GHz (receive only).
Current TRL: TRL2 Target TRL: TRL4 by 2011 Duration: 24 Months
Application /
Timeframe:
Earth Observation, partially applicable to Near Earth for Science

ESA/IPC(2010)51
Annex 2, Page 30
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Theme 2.- SCIENCE / ROBOTIC EXPLORATION
Ref. Number: G512-001MM Budget: 1,000 K€
Activity Title: B-BOLD (BOLD continuation)
Description: Develop the Solar-blind technology - whose potential is being proven very
successfully - further to a more mature and full-scale, large area 2D detector
breadboard. The schedule is presently driven by the need to provide a solid
fall-back solution for the presently baselined (but not initiated….) APS detector for
Solar Orbiter.During the still on-going very ambitious and aggressive activity "
BOLD", development of epitaxy, test-structures and costly accelerator tests have
established the feasibility and potential performance of a) AlN as the optimum
material and b) two promising diode technologies, yielding world-wide state-of art
results. A technology demonstrator of modest dimensions will be the oucome. As
an immediate follow-on, a full-scale detector breadboard on an optimized ROIC
shall be developed and evaluated under representative conditions.
Deliverables: Full-scale demonstrator breadboard, representative of a flight model for EUI on
SOLO
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months
Justification for DN:
This activity is a direct continuation of the work developed by the contractor in
the GSTP-3 activity A19.MMM-001, "Development of Optically Blind
Detectors: BOLD" , contract number 19947, funded with 770K€.
Non-competitive tendering is justified according to Article 6.1.c of the
Contracts Regulations.
Ref. Number: G512-002MC Budget: 700 K€
Activity Title: Hybrid Cryostat Demonstrator
Description: The objective is to develop a small hybrid cryostat compatible with European
launchers to provide a vibration free cryogenic environment in orbit and verify
operations at breadboard level
Small sfHe (superfluid Helium) cryostats, which would be sufficient for in-orbit
operations do not provide sufficient capacity to survive the launch on European
launchers, since no late access is possible. Hybrid Cryostats (e.g.
sfHe-solidHydrogen) offer the possibility to create a cold environment before
launch, therefore minimising the loss of Helium during LEOP. Based on the sfHe
cryostats already build (Herschel/ISO), all elements for building such a crystat
should be available, but there is no experience in Europe, how such cryostats can
be conditioned (i.e creating solid hydrogen ) and how this can be performed at the
launch pad, to gurantee that the time between last acces and actual launch does
not lead to crystat conditions which could lead to a loss of mission. A small hybrid
cryostat shall be developed and build at breadboard level. Cryostat operations
required for a future flight/launch campaign shall be tested and compatibility with
current European launch operations shall be verified.
Deliverables: Breadboard,documentation, verifed procedure for ground tests and launch
campaign.
Current TRL: TRL2 Target TRL: TRL4 by 2012 Duration: 24 Months
Application /
Timeframe:
Generic applicability to Sciences missions e.g. Spica

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 31
Ref. Number: G512-003EC Budget: 350 K€
Precise Gravitational Modelling of Planetary Moons and NEO (Near
Activity Title:
Earth Objects) Asteroids
Description: The main objective of this activity is to develop precise gravitational models of
planetary moons and asteroids target of the subject missions: i.e. the asteroid
2001 SG286, Enceladus, Titan, Jupiter, and Europa.
Deliverables: S/W Prototype
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
The models will be threefold:
• Models for mission analysis tools and techniques. These models are accurate
and medium size computational intensive and will provide gravity field data for
ESA and Industry astrodynamics tools.
• Models for operations and ground control. These models are very accurate and
high size computational intensive. They will provide gravity field data for
spacecraft maneuvering capability. They will be typically installed in an operational
ground segment control center.
• Models for on-board autonomous orbit and attitude propagation. These models
are realively accurate and low size computational intensive. They will provide
gravity field data for on-board autonomous spacecraft maneuvering capability.
The proposed activity will include:
(1) Detailed gravity fields functional, operational, performance, environment, etc.
requirements use;
(2) analysis and trade-off of various gravity field models for the 3 above mentioned
concepts;
(3) baseline definition and identification of models for the 3 areas identified above;
(4) performance validation through simulations.
Target SW
Readiness
Level:
Beta Version Duration: 18 Months
Science missions as Dark Energy, PLATO, SPICA, Marco Polo, XEUS, Cross
Scale, Rosetta, Bepi Colombo, TANDEM, and Laplace

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Theme 3.- HUMAN SPACEFLIGHT
Ref. Number: G513-001MM Budget: 600 K€
Activity Title: Micro laser beam scanner
Description: A micro laser beam scanner for planetary exploration instruments (3D robotic
vision, lidar, laser pointing for spectroscopy) shall be designed, manufactured and
tested under relevant environmental conditions.Future robotic missions will make
use of 3D-vision systems, docking sensors and imaging Lidars, which all require
a laser beam scanning mechanisms. For planetary exploration, the volume and
weight is a critical issue. Today these mechanisms are heavy or are being
avoided altogether for reliability reasons. However, very small devices having low
moving masses have the potential to be extremely robust. Making use of MEMS
technology, an aggressive miniaturization (low volume and weight, low power
consumption) effort shall be undertaken to push robustness and reliability to high
level. This technology (including materials and material analysis methods) is in a
reasonably mature stage, so that robust high performance solutions can be
envisaged already today. The main concern so far has been the robustness of
MEMS devices despite the fact that in theory devices based on smaller masses
(such as MEMS) have an increased robustness. Improved structural analysis
methods (like adequate x-ray sources) offer today a much higher degree of
understanding of the structural breaking phenomena. Emerging highly robust and
elastic materials (amorphous metals for instance) also contribute to a significant
MEMS reliability improvement.
Deliverables: 3 Laser Scanners including optical system (laser beam fed by optical fiber),
scanning mirror element, driver electronic.
Current TRL: TRL3 Target TRL: TRL6 Duration: 24 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 33
Ref. Number: G513-002MC Budget: 1,500 K€
Activity Title: Investigation on microcompounds in MELiSSA - PHASE2 (BELISSIMA2)
Description: Objective is to study the behavior and the effects of micro-compounds (trace
elements, hormones, pharmaceutical drugs, plasmids) within the liquid phase of
the MELiSSA loop, and to define and test associated countermeasures.Over the
past years of the MELiSSA project, priority has been given to the study of the 6
main chemical elements (C,H,N,O,S,P). Although studies of these main elements
have still to be pursued, the influence and modeling of smaller concentration
elements, of chemical (i.e. Ni, Cu, Na,..) or microbiological nature (i.e. plasmids)
has to be taken into account, as well as the toxicology of external agents
(pharmaceutical drugs, hormones). The investigations to be performed are mainly:
the identification of limitation and/or toxicity thresholds, the growth kinetics
influence and modeling, the study and selection and validation of
countermeasures. As these investigations require numerous toxicity and
contamination tests, potentially lethal for micro-organisms, a micro-MELISSA loop,
simplified to the liquid phase and consequently more adapted to these
investigations, had to be built. In the frame of BELISSIMA 1, the building phase
has been partially achieved (limited to compartment 1 and 2) and therefore testing
campaigns have been limited to the available hardware. Within the present activity
(i.e. BELISSIMA2), the assembly of the mini-MELiSSA loop shall be completed
and studies pursued according to the overall objective of BELISSIMA.
Also, the strong synergies with terrestrial water treatment research related to
bacterial breakthroughs and accumulation of chemicals (drugs, endocrine
disruptors, metabolites etc.) will be studied.
Deliverables: Completed mini-MELiSSA loop with appropriate instrumentation, proven
technologies, comprehensive test data, improved knowledge
Current TRL: TRL3 Target TRL: TRL5 Duration: 36 Months
Application /
Timeframe:
2015/2025 Huma Exploration-Life Support / Preparation for Exploration

ESA/IPC(2010)51
Annex 2, Page 34
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-003MC Budget: 250 K€
Activity Title: Water Network Corrosion
Description: The objective is to study and assess interactions between potable water
containing silver and space vehicle water loop, and provide recommendation
concerning material selection for future manned spacecraft water network.In the
context of manned space mission, consumables for the crew, mainly oxygen,
potable water and food, are required to have a long shelf life. In order to meet this
long shelf life, stringent quality requirement have to be met, and a remnant biocide
(i.e. silver for Russian water and iodine for American water) is added to the
potable water, preventing micro-organisms development. Maintaining the
concentration of biocide all along water shelf life is thus of outmost importance.
Experience gained during ATV launch campaign, supported by literature review,
demonstrates interactions between water containing silver biocide and water
containers and tubing occur. This interaction leads to gradual biocide depletion
and drift of water quality. In order to prevent this biocide depletion, understanding
of the interactions/corrosion is needed. This knowledge will allow providing
recommendations concerning material selection for manned spacecraft potable
water loop.
Deliverables: Technical documentations, test plan, test results.
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
2010 (ATV, ISS, ISS extension, Exploration)
Ref. Number: G513-004MC Budget: 250 K€
Activity Title:
Preliminary estimation of energy balance of a closed life support system -
Application to MEliSSA
Description: The relevance of closed life support system is highly depending of their degree of
closure for an associated energy cost. Within this study it is proposed to
investigate method to quantify energy cost of closed life support systems, as well
as to perform mathematical simulation.Almost by definition, closed life support
system will include biological processes, use direct Sunlight, and the inputs
substrate is highly depending of the recycling processes including crew. Based
on the existing design of the current MELiSSA lop, and the associated
metabolisms of the selected organism, it is proposed to review and study methods
to quantify the energy cost of a closed life support system.
Deliverables: Technical Reports, including simulation results and generic tools for further
simulations.
Current SW
Readiness Level: Algorithms
Application /
Timeframe:
Target SW
Readiness
Level:
simulation Duration: 24 Months
2015: Tools for futures ECLSS systems study Surface base (i.e. Moon, Mars
bases)

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 35
Ref. Number: G513-005MC Budget: 250 K€
Activity Title: Process Aeration Device
Description: The objective is to study, design and develop an efficient aeration device for
processes, which allow significant energy reduction.In the context of closed loop
Life Support Systems, one of the most important steps is the Nitrogen oxidation.
Generally, This oxidation is performed by nitrifying micro-organisms that require
oxygen. Supplying oxygen to the microbial community has been identified as the
main operating cost of this nitrification process. In order to further optimize this
process, reduction of energy demand is required and improvement of the
efficiency of the aeration device is necessary.
Deliverables: Technical documentations, test results, aeration device.
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
2015 (ISS extension, Exploration)
Ref. Number: G513-006MM Budget: 350 K€
Activity Title: Biochemical Analyser Technology (BIOCAT)
Description: To upgrade the developed technology enabling detection of very low
concentrations of molecules (at Pico molar level or below) and single cell
organisms in aqueous solution (1 cell or bacteria or spore/ ml) and on solid
support. Define sampling and sample conditioning technologies for the samples to
be analysed with BIOCATThe existing technology is presently able to detect a
known fluorescent molecule down to picomolar concentrations. The planned
activity will extend the range of molecules to be detected to a range of
autofluorescent biomarkers (keeping the high sensitivity). Furthermore it will
address sampling and conditioning technologies to extend the application within
liquid samples and to enable its application range to samples on/in solid surfaces.
In the ideal case the technology will be applicable to solid surfaces without or
minimal prior treatment and mechanical contact, thus allowing the fast scanning of
large surface areas.
Deliverables: Breadboard
Current TRL: TRL3 Target TRL: TRL5 Duration: 12 Months
Application /
Timeframe:
Justification for DN:
TRL 8 by 2012, Next, MSR, Outer Planet Missions.
For tools and S/W target date should be earliest the date by which the S/W and
tools are to become operational.
This activity is a direct continuation of the TRP activity "Biochemical Analyser"
funded with 150 K€ and performed successfully by Embedded System
Engineering.
Non-competitive tendering is justified according to Articles 6.1.c of the
Contracts Regulations.

ESA/IPC(2010)51
Annex 2, Page 36
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-007MM Budget: 300 K€
Activity Title: A self standing bioreactor for biological samples
Description: To develop a multifunctional biological bioreactor in which cells can be controlled,
observed and maintained.For biological experiments in space, special devices are
needed to be able to culture the samples (cells and tissues) with small or no effort.
This activity shall develop a new generation of self standing bioreactors which will
be able to maintain the cells over a long period in microgravity, so long term
experiments will be possible. Observation of the samples will be possible, due to
an open see through frame and the onboard microscope, therefore live imaging
will be possible. The important factors O2, CO2 and the temperature will be
controlled on the bioreactor itself, therefore no special environment, like an
incubator is needed and will safe a lot of space. The bioreactors developed so far
were only capable in controlling a few of these parameters, therefore this activity
would be a improvement on existing technology which can help biological
research in space. Bioreactors like this could give answers to biological questions
about for example bone research, cytoskeleton activities, tissue development,
blood proliferation etc.
Deliverables: A self standing incubation bioreactor in which the samples can be observed and
controlled via hardware.
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 37
Ref. Number: G513-008MM Budget: 200 K€
Activity Title: Respiratory Sensor System - Optimisation and Combination
Description: Optimise the already-proven technology of thin-film based flow, O2 and CO2
sensors
- Reduce the power consumption and optimise the thermal control of the sensors
(combine all sensors on same substrate)
- Consolidate main-stream solution
- Include measurements of relevant complementary parameters required for
establishing respiratory indexes
- Integrate H2 measurements
- ValidationThin-film based technologies to measure respiratory parameters
(flow-rate, oxygen concentration, carbon dioxide concentration) using a direct,
main stream sensor have been developed and validated under previous ESA
activities. The activity demonstrated that it is possible to measure
above-mentioned parameters with a device weighting in the range of 1 Kg, which
represents a very good improvement compared to the other devices working on
other principles. The technology is now fully validated for off-line analysis
(respiratory flow derived towards the measuring system) and for a system where
each parameter is measured by a separated sensor with own thermal control
system. For obtaining a full performance of the system, it is now necessary to
optimise the sensor integration and to consolidate the measurement in the main
stream (measurements directly in the air flow). The tasks identified to update the
system include:
- Improve the thermal regulation (this will likely require a thermal modeling of the
system)
- Combine all the sensors on one substrate (will reduce power consumption and
create more stable conditions to the thermal regulation law)
- Consolidate the main-stream solution (includes performing the required
analyses, refine the design of the sensor parts and head to minimise the dead
spaces
- Define and implement measurements of additional parameters used in the
analysis of the respiratory function (such as heart rate, humidity, ambient
temperature and pressure…)
- Integrate the H2 measurements
- Integrate those changes in a breadboard and validate the breadboard.
Deliverables: Validated demonstrator
Current TRL: TRL3 Target TRL: TRL4 Duration: 16 Months
Application /
Timeframe:
Human space flight and exploration - medical diagnostics technologies. Outcome
of this activity will also be integrated into the product line of Medisoft, which is a
Belgian SME manufacturing and commercialising medical devices.

ESA/IPC(2010)51
Annex 2, Page 38
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-009MM Budget: 500 K€
Activity Title: MEMS based Gas Chromatograph/Mass Spectrometer
Description: The objective of this activity is to achieve a fully functional breadboard of a
miniaturised Gas Chromatograph and Mass Spectrometer system for in-situ
chemical analysis in harsh environment based on MEMS technology.Gas
chromatographs in conjunction with a spectral mass analyser for the identification
of organic and inorganic compounds have been flown or are flying already on
several space missions, e.g. Huygens and Rosetta, and are in the process of
being built and qualified, as for the Mars Science Lab (NASA) and for ExoMars
(ExoMars). These instruments are already miniaturised and optimised in terms of
mass and power consumption to a high extent. MEMS based technology however
offers a potential to further reduce resource consumption and cost. This would
enable for instance environmental monitoring using a swarm type of mission. As
for applications in human spaceflight, the potential of MEMS based devices is the
increased mobility.
Deliverables: Breadboard
Current TRL: TRL2 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
TRL 8 by 2013, missions NEXT, MSR, Outer Planet Missions

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 39
Ref. Number: G513-011MM Budget: 350 K€
Activity Title: Enhanced Autonomous Cultivation System
Description: The objective of the activity is to enhance the capabilities of the existing
(Canadian) flight hardware e-ERISTO to allow cultivation and observation of larger
cell agglomerates as eg fish eggs.The successful flight hardware eERISTO has
been flown in the shuttle and in the fully automated FOTON mission (Foton M3).
Its media storage capabilities and controlled delivery made it an appreciated
experiment platform for a variety of biological experiments like bone cell
experiments. The inclusion of the following features would give a wide range of
new experiments the possibility to use a flight proven hardware for their
experiments. Presently already an experiment dealing with the development of
fish eggs identified in the D/HME MAP-Programme is very interested in this
hardware. :
- the addition of live observation (when a cell culture is in progress) would give the
possibility to visualise and therefore analyse the experiment evolution while it is
still in µgravity. This improves scientific value and information as the analysis or
observation will be immediate and will allow the scientists to react on time to e.g.
cope with the development of adverse conditions and hence save the cell
cultures. Moreover for specific types of cell cultures (e.g. fish eggs), on-line
observation would allow the scientists to perform real time analysis of cell
development as in the lab.
- a variable size of the bioreactor part to accommodate different numbers and
sizes of cells or organisms as well as a permeable bioreactor wall material
allowing for gas exchange with the environment; this would open up the use of the
facility to new types of cell cultures, e.g. fish eggs.
Tasks of this activity will include:
- Developing of a new pathway, (inner layer of the eERISTO unit) including the
possibility of permeability and variable volume of the bioreactor and the
accommodation of the visualisation/ monitoring unit
- Adjusting and testing interfaces for communication
- Developing GSE tools (software) based on existing tools
- Testing and validation
Deliverables: New pathway including permeable bioreactors and monitoring unit fitting into
existing eERISTO unit and Ground Support equipment, documentation
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-012MM Budget: 600 K€
Activity Title: Enhanced Virtual Reality Stimulator
Description: Objective of this follow-on activity is the improvement of the existing Virtual Reality
Stimulator (VRS) demonstrator by the update of hardware and software, the
integration of new stimulations (3Dsound) and features e.g. stress and workload
measurement and integration of stimulation based learning support for
accelerated learning procedures (feedback loop). The update includes improved
reponse time measurement and use of other electrophysiological signals (EEG,
EOG, EMG and ECG) into the feedback loopThe Virtual Reality Stimulator is a
multi-purpose experiment platform for cognitive neurophysiology developed in the
scope of the TRP program. It gives the opportunity to explore neuroscience and
cognitive aspects in a complete controlled environment (e.g. 3D mazes) with
defined stimulations (like aural, visual, mechanical stimulations). The stimulator
gives an experiment editing and execution platform allowing the user the full
editing and execution spectrum needed for cognitive neuroscience research. It
allows for sub-millisecond accurate reaction time measurements and supports the
measurement of electrophysiological signals such as EEG, EOG, EMG and ECG.
n the scope of this activity the stimulator will be updated to be more flexible to be
able to optimise the stimulation and environment scenarios for different
experiments, this will also include hardware and software updates to reflect new
technology advances. As main part the Stimulator will be improved with new
features including:
- Enhanced reaction time measurement (including voice recognition)
- Integration of new stimulations and environments as e.g. exact 3D audio
stimulations
- Integration of a neurophysically driven training for accelerated learning
- Integration of biofeedback loop to allow for e.g. studying response to stress and
workload
- Adding and optimising haptic feedback and stimulation (including software hand
representation), eye tracking and see-through capabilities
The present activity can in addition have applications in the medical training field:
to train or to maintain skills necessary for medical staff on interplanetary trips or
sited on moon/Mars posts.
Deliverables: Technology demonstrator - Validation data
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Justification for DN:
This activity is a direct continuation of the work developed by SAS (B) in the
TRP activity T307-09MM, "Virtual Reality Simulator" and funded with 300 K€.
It is recommended to continue the development with the same contractor.
Non-competitive tendering is justified according to Article 6.1.c of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 41
Ref. Number: G513-013MM Budget: 250 K€
Activity Title: Tactile Training
Description: The objective of this activity is to develop a training tool to enhance
countermeasure training in the sense of motivating the astronaut through
competition and entertainment and also assessing the performance. At the same
time this system will give the opportunity to train different tactile demanding tasks
easily as e.g. tasks to be carried out in the glove-box. Output will be a technology
demonstrator with tailored software.Countermeasures in space take a high toll in
crew time, in addition are the exercises mostly composed of endless repetitions of
the same movements. This is true as well for different training task which are
asking for highly specialised movements (e.g. assembling of a Biolab experiment
inside the glove box). Both can be eased with a game-like approach. Scientific
studies have proven games as a very good instrument to train special tasks as
e.g. laparoscopic tasks used for medical health care - this approach can be
extended to tasks under the glove box.
In addition such a system can be easily used to divert trainings routine by adding
entertainment and feedback into normal countermeasure activities and
instruments and be used to assess the performance while exercising these
countermeasure devices.
Games providing these features are on the low price commercial market and
could be adapted and advanced for the use in space.
To achieve the twofold goal of the activity (to have an example training program
for a specialised task and the integration into a countermeasure exercise) the
activity will integrate the following tasks:
- Identify possible training tasks
- Develop training program for one task based on a game console like approach
- Develop set-up for integrating system into an example countermeasure activity
- Develop countermeasure (game based) program for diverting exercises and
analysing the performance level
- Integrate it in existing countermeasure devices
Deliverables: breadboard including software
Current TRL: TRL3 Target TRL: TRL5 Duration: 12 Months
Application /
Timeframe:
N/A

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-014MM Budget: 350 K€
Activity Title: Bone and Muscle Modelling
Description: The objective develop of this activity is the development of a new modelling
method to investigate effects on bones and muscles under microgravity through
detailed modelling of muscle activity and bone loading. The outcome is
customised software including detailed models for bone and muscle assessment
and countermeasure optimisation.Bone and muscle degradation is a major
concern in human spaceflight. Until now empiric approaches have been used to
develop countermeasures and to assess degradation. Anybody presents a
systematic tool to improve and develop countermeasures and life science
instrumentation by providing a physical / visual model to analyse or optimise
countermeasure hardware or generally tasks (e.g. EVA tasks) in space.
It has proven its feasibility in an ESA funded activity where a countermeasure
device was integrated as well as a stress map of the leg is built to assess the
stress force in the bone (visible in a Finite Element Model). In this ‘map’ it is visible
where stress forces are acting on the tibia bone and how those are different in
microgravity and 1g conditions.
Building upon these results a model for the use in space shall be developed
where comparisons between space and 1g are easily visible and optimisation
algorithms make it possible to see the best configuration for dedicated
countermeasure devices or tasks.
Therefore the activity will extend the bone FEM model and stress map to the most
important bones validate it and analyse the degradation on them.
These results will then be used to optimise tasks (including a countermeasure
exercise) for optimal muscle and bone loading.
Tasks in particular will include:
- Optimisation of FEM model for material properties (including density)
- Extension of the model to include the most important bones (attached correctly
to the muscle model)
- Analysis of countermeasure devices / exercises (e.g. specific EVA task) for
assessment of muscle activity and bone stress
- Validation of model (comparison of results with experimentally registered bone
demineralisation if possible)
- Assessment if and how more dynamic features can be included in the mode
l(e.g. muscle fatigue).
Deliverables: customised modelling software including models and verification of model
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
countermeasure development - 2010

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 43
Ref. Number: G513-015MM Budget: 600 K€
Activity Title: High-precision Implantable Intra-arterial Drug Delivery Device
Description: Develop a high-precision drug delivery device, which can be implanted in mice.
The device will be able to be controlled and activated via telemetry, thus suitable
for biological experiments in mice during space missions.Drug development,
preclinical research and biological research rely on animal experimentation. Only
a small proportion of drugs can be given to animals via their food, the greater part
necessitation either injections or implantable drug delivery pumps. To date the
available and widely used implantable drug delivery devices are driven by osmotic
pressure and have major limitations: they give only continuous flow at a given
non-controlled rate, offering thus no possibility to give boluses at specific times or
periodic drug delivery, which is required to studying pharmacokinetics; they are
quite inaccurate; and they cannot be programmed or controlled once inserted in
the animal. There is therefore a great need for a precise, telemetrically controlled
and versatile implantable drug delivery pump. The aim of this activity is to develop
a developed a high-precision, telemetrically controlled, implantable intra-arterial
drug infusion device where High-concentration drugs can be stored within the
implant and the dosing is low so that drug delivery can take place over long
periods (weeks to months or years). The device should be small in size to be
implanted in small animals (e.g mice), controlled telemetrically, high-precision
bolus administration, dosing independent of load (i.e., arterial pressure at distal
end of delivery catheter), externally programmable/activated for continuous,
periodic or user-defined drug administration, MRI safe and compatible
Deliverables: breadboard
Current TRL: TRL3 Target TRL: TRL6 Duration: 24 Months
Application /
Timeframe:
Urgently needed in the context of animal experiments in space. Flight of MIS on
FOTON/BION in 2012

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-016MM Budget: 300 K€
Activity Title: 3D Bioreactor
Description: Objective is the development of an advanced 3D bioreactor system to maintain
living cardiovascular tissue under controlled physiological conditions for
cardiovascular and pharmaceutical research and development.Research and
development on pharmaceutical biotechnology, evaluation of cardiovascular
intervention and therapy, and medical devices and sensors on earth and in space
is so far based on output from patient and animal studies. In addition and/or as an
alternative to animal experiments a significant part of the cardiovascular R&D
currently conducted with animals can be carried out using bioreactors. Although
bioreactors provide an environment to keep tissue alive, the efficacy is strongly
determined by subjecting the tissue to physiologically representative loading. This
project aims at developing a sophisticated bioreactor which is capable of
maintaining living cardiovascular tissue under well-controlled hemodynamic
conditions. Existing technology from in-vitro and ex-vivo modeling of the
cardiovascular system is used and advanced to develop an ex-vivo circulatory
system. Physiology is restored within the system using a nutritive oxygenated
perfusion medium, sophisticated modules for hemodynamic pre- and afterload
settings and an integrated flow circulation. Such a setting provides well-controlled
circumstances (uniformity and efficiency), accurate assessment of the intervention
or treatment applied and can replace a number of animal experiments. The
system offers a test bench for (new) medical devices and sensors, drugs
(treatment) and intervention strategies. Moreover, tissue interaction and
responses such as remodeling under microgravity conditions can be examined
with the system. The work within the project includes research, development,
validation and evaluation of the circulatory system components, and application to
vascular tissue and valves. Future applications may include also controlled cell
culturing, proliferation, differentiation and tissue engineering among others.
Deliverables: A bioreactor demonstrator system which is capable of maintaining living tissue for
R&D in the field of (patho)-physiology, pharmaceutics, and medical device and
sensor technology.
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
Needed as a tool for preparation of long term human mission for prediction of long
term effects of microgravity without usin invasive methods on astronauts.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 45
Ref. Number: G513-017MM Budget: 400 K€
Activity Title: Blood pressure, flow and temperature sensor inserted via a vascular stent
Description: Objective is the development of a miniaturised sensor system, on an expandable
stent, to be inserted in small animals, for evaluation of the change of
hemodynamic state in zero gravity conditions based on nanotechnology
methods.In long duration spaceflight it is necessary to continuously monitor
pressure, flow and temperature for the evaluation of the change of hemodynamic
state. Individual sensors have been developed already. The challenge is to
significantly reduce the size and weight of the sensors to implant them and access
them remotely. Therefore, this activity aims to develop a combined pressure, flow
and temperature sensor on a single, flexible chip, powered and sensed
non-invasively, with existing wireless RF-technology, applied to a vascular stent
that can be implanted in small animals. The existing measurement techniques
need to be advanced for the specific application inside a stent. The single sensor
must be attached to a stent without breaking and loosening. The proper
positioning of the sensor will necessitate a more sophisticated deployment
technique than applied with a conventional stent. This method of sensing multiple
parameters on a single chip attached on a deploying stent offers the possibility of
non-invasive long-term experiments regarding evaluation of hemodynamic
responses to e.g., drugs or exercise under zero-gravity conditions. The activity
shall focus on the design, manufacture, integration, calibration and test of the
breadboard.
Deliverables: A wireless sensor on a stent, including implantation techniques for invasive
monitoring and evaluation of (changes in) hemodynamic state
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
2011 FOTON/BION mission with MIS

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-018MM Budget: 350 K€
Activity Title: Diagnostics for Nucleation Detection
Description: Objective is to demonstrate techniques devoted to the detection of the early stage
of crystallisation (nucleation) from solutionThe scientific community currently
involved in ESA sponsored microgravity experiments on solution crystallisation of
protein, have expressed interest in the study of the mechanisms that lie behind
the formation of the very first aggregates of molecules or nanoparticles. This is an
interesting but yet quite poorly understood aspect of crystallisation, due also to the
stringent experimental problems. That is because the detection of the properties
(size, degree of cristallinity etc) by optical means are not so straightforward. The
typical size of critical nuclei usually lies below the resolution of imaging
techniques. On the other hand, light scattering techniques that are sensitive up to
nanometric length scales, collect light from scattering volumes that are very small
(e. g. l) if compared with a typical sample volume of the order of a few ml. The
activity shall identify a technique or a combination of techniques and demonstrate
its ability to encompass the detection of nanometric entities over the entire sample
volume (typically a few ml). The samples of interest can be proteins, zeolites or
colloidal solutions. The activity shall be finalised by representative measurements
on a Model Experiment.
Deliverables: Calibrated operational demonstrator, S/W, test data. Final documentation
containing representative measurements, the manual for the instrument including
its calibration and s/w description.
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
PCDF experiments. For techno push technology, earliest best estimated date to
have this techno at TRL5/6.
Ref. Number: G513-019MM Budget: 250 K€
Activity Title: Nanowire Biosensor
Description: The objective of this proposal is to fabricate and demonstrate electrochemical
Silicon NanoWire (Si-NW) label-free sensors with enhanced sensitivity for virus
and/or DNA diagnostics. For label-free applications, electrical biosensors are
more favorable than other types. In this family of sensors, the basic electrical
parameters of a Si-NW field effect transistor coated with appropriate probe
molecules are modified due to the probe-target binding chemical reaction.
Primarily, the interaction of target biomolecules with immobilised probes on the
Si-NW induces a charge concentration that affects the conductance of the
transducer (i.e. the Si-NW FET). Nanoelectronic devices offer a major
improvement in terms of sensitivity and lower limit of detection. Furthermore, it
has been demonstrated that nanoelectronic devices can be used to trade-off
between biosensor's settling (response) time and the minimum detectable
concentration. The demonstrator will comprise a linear array of sensing elements
(each sensing element is a Si NW transistor) and PDMS microfluid channels that
allow controlling the flow of the biological material above functionalized Si NWs.
Deliverables: demonstrator, breadboard, test results
Current TRL: TRL2 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
Biology and Physiology research, microbial detection for research and exploration

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 47
Ref. Number: G513-020MM Budget: 500 K€
Activity Title: Compact - 80ºC Freezer
Description: The objective is to develop a compact -80 C freezer breadboard suitable for
upload and download of biological samples to and from the ISS in particular
compatible to transport not using the STS (Shuttle).Since Columbus is attached
to the ISS, more biological experiments will performed in this facility. Biological
samples need certain constant temperature to maintain their viability. So far the
freezer in the shuttle for the upload of the samples can only freeze down to -20 C
with accuracy of +10 C in certain conditions. Cells are less viable in these
temperatures because certain processes still continue and cells have the risk to
go into apoptosis, regulated cell death. Under these conditions there is a high risk
that a lower concentration of cells or even no living cells arrive in orbit,
jeopardizing the quality of the experiment. This might result in discrepancies from
the ground control measurements or even total loss of the whole experiment. To
compensate for that, scientist need to take corrective measures by changing their
procedures (e.g. in the TRIPLELUX experiment) which still fosters high
uncertainty for cell viability. This activity will develop an -80 C freezer
breadboard for flexible upload/download of biological samples, to ensure the
viability of the cells. This freezer is mainly aimed at transport with SOYUS type
carriers and has to be therefore compact and low in power consumption to be
compatible with the constraints.
Deliverables: -80 C freezer breadboard for a save upload of biological samples.
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
as early as possible to support the scientific operation of EMCS, BIOLAB, Kubic
etc presently on board ISS/Columbus.
Ref. Number: G513-023EP Budget: 400 K€
Activity Title: Development of a Lithium ion cell optimized for low temperatures (-20°C )
Description: The objective of this activity is to develop lithium ion cell optimised for low
temperature performance (i.e. below -20 C) by selecting the electrolyte and
electrodes most suitable for such conditions.Some space applications would
benefit from the improvement of the Li ion technology at low temperatures, such
as exploration missions (rovers). Different factors influence low temperature
performances of Li ion cell like electrolyte conductivity, cell design, electrodes
thickness, separator porosity.
As shown in preliminary in-house activities in the ESBTC, present cells do have a
rather poor low temperature performance, but small modifications to the
electrolyte will result in significant improvement in terms of available energy
density, cycle life and degradation, in benefit to terrestrial applications as well.
In a first phase a low temperature Li ion cell will be developed after selection of
the electrolyte, electrodes materials, processes. The second phase will be the full
characterisation of the prepared cells by tests. In a third phase, some
environmental tests will be performed in order to detect any show-stopper for
COTS cells, and development needed to prepare a space version of the cell will
be elaborated.
Deliverables: Technical Notes, Test Plan, Test Report, Final report, Space cell Development
Plan, Cells
Current TRL: TRL4 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
All exploration missions e.g. Mars Sample Return and following exploration
missions

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-024SW Budget: 300 K€
Activity Title: Authoring environment for interactive 3D procedures
Description: Design and development of an authoring environment that can build 3D interactive
procedures Manual procedure viewers are developed based on a paper legacy.
Non-textual procedure representation has not yet been deployed in the human
spaceflight domain, mainly due to the lack of good authoring tools. Tasks foreseen
are
- familiarization with space station procedures and on-board computer based
training material
- familiarization with CAD/CAM outputs and digital human mannequin
technologies
- development of an authoring environment for 3D procedures based on the
existing prototype
- Demonstration of the product by preparation and evaluation of a sample set of
3D procedures
Deliverables: Software environment for human spaceflight procedure authoring
- ECSS E40 compliant documentation
Current SW
Readiness Level: prototype
Target SW
Readiness
Level:
release Duration: 12 Months
Ref. Number: G513-025EC Budget: 1,900 K€
Activity Title: One-axis inertial MEMS sensor development
Description: Design, manufacturing and testing of a one-axis inertial MEMS sensor combining
the accelerometer, the gyro and the processing, power and interface functions into
two co-packaged chips..The activity aims at designing, manufacturing and testing
a miniaturized MEMS sensor that can provide one-axis rates and accelerations for
a rover, micro and nano satellite and some EDL applications. This will be
achieved by integrating a one-axis MEMS gyro and a one-axis MEMS
accelerometer together within the same chip and incorporating all support and
interfacing functions on a co-packaged ASIC. A full EM shall be produced and
tested. This activity is a follow on to the feasibility demonstrator activity.
Deliverables: One-axis inertial sensor prototype
Current TRL: TRL3 Target TRL: TRL5 Duration: Months
Application /
Timeframe:
TRL5 by 2012

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 49
Ref. Number: G513-026MC Budget: 350 K€
Activity Title: Development of Thermal Insulation for Planetary Landers and Rovers
Description: The objective is to develop and characterise high efficiency thermal insulations
suitable for Mars/Lunar lander and rover surface missions.Planetary surface
missions are mainly driven by power consumption due to the long diurnal cycles
and the harsh environmental conditions. Thermal insulation for planetary missions
(to planets with atmosphere) differ from classical spacecraft MLI due to the
potential use of e.g. aerogel, open foam and glass fibre. The insulation can be
constructed with a combination of materials in order to increase performance for
both the cruise phase and surface operations. The performance of the insulation
is dependent on the atmospheric composition, temperature, pressure, gravity. The
insulating materials will need to be applied directly on the lander/rover
external/internal walls, fitted to an electronic box or instrument, wrapped around
electrical cables or applied to mechanisms. Such insulation concepts may be
required to withstand multiple installation and removal cycles without performance
degradation and particle shedding. Furthermore, surface missions have stringent
planetary protection requirements as well as demanding contamination control. All
these requirements could eliminate existing high efficiency materials due to
inherent characteristic (e.g. particle shedding, cracking, brittleness). In order to
reach high performance insulation concepts responding to all these requirements,
the following steps are proposed:
- Issue specifications for the insulation based on Mars/Moon surface mission
requirements.
- Review available materials and insulation concepts in view of these
specifications.
- Perform measurements if material properties are missing
- Select insulating materials and define concepts/lay-up/packaging in order to fulfil
all the mission requirements and to cover all applications (rigid, flexible, etc.) and
perform a complete trade-off
- Build breadboards and perform characterisation tests
- Define roadmap for the adaptation/improvement of existing or for the
development of new materials and concepts, if and where needed.
Deliverables: Material characteristics of basic insulation materials
Definition of thermal insulation concepts
Breadboard(s) and tests results of such concepts
Roadmaps for adaptation of existing or development of new materials
Current TRL: TRL2 Target TRL: TRL4 Duration: Months
Application /
Timeframe:
TRL 8 by 2012

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-027MC Budget: 400 K€
Mechanically Pumped Heat Transport Loop for Planetary Landers and
Activity Title:
Rovers
Description: The objective is to develop a mechanically pumped heat transport loop in order to
provide a temperature control technology for a planetary lander or rover during the
launch (in case RHU's or RTG's are used) and the cruise phase. Furthermore,
such a mechanically pumped loop can also be used for the planetary surface
phase of the mission to regulate the internal Lander/Rover temperatures.The
thermal control concept of future planetary landers and/or rovers will face very
demanding requirements to provide temperature control starting at launch up to
and including the surface operation on the planet. Due to the very limited available
power resulting from the long diurnal cycles and the harsh environment, RHU
and/or RTG might have to be used and will provide a constant heat load during
the complete lifetime.
Currently two technologies to provide such a temperature control - capillary
pumped and mechanically pumped systems - are under consideration for such
applications.
For capillary pumped systems different design options exist in Europe and an
adaptation to the use in planetary missions seems possible.
Mechanically pumped loops could provide an alternative technology with different
advantages/disadvantages.
As mechanically pumped loops for such potential applications have not yet
reached a similar maturity, the following activity is proposed:
- Issue specifications for a mechanically pumped loop based on Mars/Moon
surface mission requirements in terms of power consumption, working fluid,
operating temperature, material capability, mass, leakage and operational life.
- Review available technologies and materials in view of these specifications.
- Design a mechanical pump loop system concept
- Build a breadboard and perform characterisation tests
- Define roadmap to adapt/improve existing or to develop new technologies,
where needed.
Deliverables: Specification for MPL
MPL concepts and breadboard test results
Roadmaps for adaptation of existing or development of new
components/technologies
Current TRL: TRL2 Target TRL: TRL4 Duration: Months
Application /
Timeframe:
TRL 8 by 2013

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 51
Ref. Number: G513-029MM Budget: 800 K€
Activity Title: Detector arrays for Imaging Lidar systems
Description: This activity shall focus on the development of advanced detector arrays for
Imaging Lidar sensors. Imaging Lidars (Light detection and ranging), or in other
words three-dimensional imagers, are considered a key enabling technology for
the missions envisaged in ESA’s Space Exploration Programme. Typically
Imaging Lidars rely on scanning mechanisms that are still bulky and often
considerably heavy for space missions (like robotic exploration of the solar
system). On going ESA activities focus on the development of Imaging Lidar
sensors that shall implement APD (Avalanche Photodiode Arrays) detector arrays.
However the number of pixels of this array (256 pixel detectors) is still small for
the required FoV (Field of View) and spatial resolution for the applications in mind.
A scanner mechanism is still required (however with relaxed scanning
performance when compared with a single detector system). Large-format APD or
SPAD arrays as well as novel CMOS detector arrays with in-pixel intelligence
(such as recently emerging using cw modulation techniques) - depending on the
application (available signal levels) - are the prime candidate technologies for the
detector as the critical component in the next generation of imaging lidars.
This activity shall study and develop novel detector arrays to be implemented in
future Imaging Lidar systems.
1) Review, analysis and trade-off of novel detectors array technologies for
Imaging Lidars.
2) Perform precursor experiments and delta development activities concerning
detector arrays technologies.
3) Design, manufacturer and testing of a detector array for Imaging Lidar sensors.
Deliverables: Novel detector arrays for imaging LIDAR applications
Current TRL: TRL3 Target TRL: TRL5 Duration: Months
Application /
Timeframe:
TRL5 by 2015

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-030SW Budget: 600 K€
Activity Title: Autonomous and remote operations reference facility for robotics
Description: Develop a reference facility for robotics remote operations
This facility shall allow the validation of operational concepts for future robotic
missions and provide the basis for operational simulators to support operations
during the flight phase for the development of operation plans and their validation,
assisted by intelligent planning agentsIn order to allow the proper testing of
operational concepts and consolidation of requirements for robotics teleoperations
this facility shall provide the virtual environment (simulation and interface) to allow
the easy modelling of future robotic missions.
In order to be able to support the design and operations at an early stage, an
easily configurable and modular framework needs to be established, able to
model and simulate complex robotic missions. These missions need to expose the
same operational interfaces as the real system and shall allow the link to an
operational front-end for these missions.
In order to support the operations, planning assistants, visualisation possibilities,
monitoring capabilities need to be basic functions of this reference facility.
The development steps will include:
• Overall architecture / framework definition
• System simulation architecture and reference models (generic models)
• Modelling environment to instantiate mission scenarios
• Operational front-end with command and control functions
• Planning modules
• Visualisation options for planning and monitoring purposes (VR)
Deliverables: Reference facility for teleoperations
Test and development environment at ESTEC
Current SW
Readiness Level: Prototype
Application /
Timeframe:
Target SW
Readiness
Level:
Remote robotics mission / 2010-2015
Beta Duration: 24 Months
Ref. Number: G513-033MC Budget: 500 K€
Activity Title: Additional Unit for Increased Water Loop Closure
Description: The objective of this activity is to study, develop, manufacture and test a urea
transformation unit for increased water loop closure.The following tasks shall be
performed:
- Perform a in-depth characterisation of the core processes
- Design and manufacturing of a breadboard unit for experimental verification
supported by relevant analyses
- Performance of comprehensive test programme
Deliverables: Technical documentation, design, test results, urea transformation unit including
instrumentation and interfaces with membrane based filtration system.
Current TRL: TRL2 Target TRL: TRL4 Duration: 30 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2012

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Ref. Number: G513-034MC Budget: 450 K€
Activity Title: Air Sampler Unit
Description: The objective of this activity is to design, build and test a functional demonstration
breadboard of an air sampler for microbial identification.
The following tasks shall be performed:
- Design of breadboard unit based on previously selected core technologies,
supported by relevant analyses and taking into account the interfaces with the
microbial identification unit
- Manufacturing of BB unit
- Performance of comprehensive test programme
Deliverables: Functional breadboard and technical reports
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2010
Ref. Number: G513-035MC Budget: 400 K€
Activity Title: Determination of Biomass in Complex Bioprocesses
Description: The objective is to validate a method and associated hardware for the monitoring
of biomass for the monitoring of biomass in complex bioprocesses, in the
perspective of accurate and robuste control of the bioprocess.
Tasks included in the proposed activity cover extensive data collection on
biomass concentration in complex bioprocesses to develop and validate a
relevant method of biomass determination. Associated hardware will be
developed and validated in relevant environment.
Deliverables: Biomass determination method, design files, developed hardware, validation tests
report,
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2015
Ref. Number: G513-036MC Budget: 400 K€
Activity Title: Development of Methane Recovery Assembly
Description:
The objective of this activity is to study, develop, design, manufacture and test a
breadboard of a Methane pyrolysis unit for the ARES system.
Deliverables: Technical documentation, design, breadboard hardware and breadboard test
results
Current TRL: TRL3 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2015

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-037MC Budget: 150 K€
Activity Title: Feasibilty Study for Manned BIORAT Campaign
Description: The objective of this activity is to assess the feasibility and give recommnedations
to test BIORAT technology during a short manned isolation test. Within this study
it is proposed to investigate the feasibility and establish main recommendation for
a one month manned campaign, with total air closure, using BIORAT technolgy as
a precursor of MELiSSA loop.
Deliverables: Reports
Current TRL: TRL2 Target TRL: TRL3 Duration: 12 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2015
Ref. Number: G513-038MC Budget: 400 K€
Activity Title: High Performance Pressurized Structure
Description:
Improve the structural restraint concept for inflatable pressurized structures For
the current high pressure, inflatable structures developments, the structural layer
is built using circumferential and meridional restraints, around an internal core.
This implies a complex manufacturing and assembly procedure and analytical
verification. In this activity, it is proposed to study an alternative structural layer
concept, which would reduce its mass, manufacturing costs and ease its
numerical analysis. The activity should encompass a design phase, supported by
analyses and completed by a test of a breadboard. The results of this study would
mainly be relevant for habitats, airlocks and docking connectors, but could also be
used for radiation shielding structures or fluid containers.
Deliverables: design files, test documentation for breadboard test, Development Plan
Current TRL: TRL2 Target TRL: TRL3 Duration: 18 Months
Application /
Timeframe:
Human exploration - habitat / all inflatable modules/habitats etc
Ref. Number: G513-039MC Budget: 450 K€
Activity Title: Higher Plant Canopy Evaluation
Description: The objective of this activity is to study, develop and test the main functions of an
evaluation tool fo a ahigher plant canopy. Technology state-of the art, concept
definition, main functions testing will be performed in the course of the study in
order to give recommendation on a preliminary design of procedure and hardware
for monitoring a whole canopy.
Deliverables: Conceptual design, functional breadboard, tests documentation
Current TRL: TRL3 Target TRL: TRL4 Duration: 30 Months
Application /
Timeframe:
Human exploration - life support / By 2015

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 55
Ref. Number: G513-040MC Budget: 450 K€
Activity Title: Inflatable Container for Life Support Waste Water
Description: The objective of this activity is to study, design, manufacture and test a ground
prototype of an inflatable container for LSS waste water.
Taking into account current ESA studies in structure and manned spaceflight (i.e.
IHAB), a concept of a generic inflatable wastewater container will be studied.
Trade-off addressing the structure, material selection, and design will be
performed. Within this study the characteristics of life support wastewater (pH,
temperature, presence of particles, etc.) as well as the space environment
characteristics (reduced gravity, mass, deployment,..) will be considered. A
ground prototype will be designed, manufactured and tested.
Deliverables: Technical documentation, test documentation, design files, ground prototype
Current TRL: TRL2 Target TRL: TRL3 Duration: 24 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2015
Ref. Number: G513-041MC Budget: 1,500 K€
Activity Title: MELiSSA Pilot Plant
Description: The objective of this activity is to demonstrate and validate regenerative life
support systems on ground.
Due to high interaction between all recyling loops (i.e. water, air, food,…) and
current technological advancement, there is an inreased requirement to perform
integrated tests. This activity will concentrate on the following tasks:
- study and development of interface technologies between all MELiSSA
compartments (i.e. separation technologies, technologies for specific extraction of
contaminants..),
- integration of interfaces and test
- development and implementation of quality assurance and quality control, in the
perspective of a full integration of the MELiSSA loop.
Deliverables: Design reports, proven technologies, technical documentation, test reports,
developed hardware, improved knowledge
Current TRL: TRL3 Target TRL: TRL4 Duration: 36 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2015

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-042MC Budget: 550 K€
Activity Title: Plant Stress Detection Unit
Description: The objective of this activity is to study and test the accommodation of a stress
detection unit within the MELiSSA higher plant compartment. Optimisation and
testing of the critical functions of the hardware will be performed in view of further
integration in the MELiSSA Higher Plant Compartment. The following tasks shall
be performed:
- Trade-off of possible accommodation concepts using previously selected
technologies taking into account all interfaces with the existing MELiSSA higer
plant compartment
- Design of breadboard unit supported by relevant analyses
- Manufacturing and integration into higher plant compartment
- Performance of comprehensive test programme
Deliverables: Accommodation study, Breadboard, test documentation
Current TRL: TRL3 Target TRL: TRL4 Duration: 30 Months
Application /
Timeframe:
Human exploration - life support / By 2015
Ref. Number: G513-043MC Budget: 600 K€
Activity Title: Waste Preparation Unit
Description: The objective of this activity is to study, design and manufacture a fully automated
waste preparation unit for further waste degradation.The following tasks shall be
performed:
- Trade-off of possible technologies taking into account all interfaces with waste
collection units and waste degradation units (MELiSSA first compartment)
- Design of unit supported by relevant analyses
- Manufacturing and integration
- Performance of comprehensive test programme
Deliverables: Design files; tests documentation; fully automated waste preparation unit,
including interfaces with waste collection unit and waste compartment
Current TRL: TRL3 Target TRL: TRL6 Duration: 30 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2015

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 57
Ref. Number: G513-044MC Budget: 600 K€
Activity Title: Wet Oxidation Unit
Description: The objective is to study, design, manufacture and test in a relevant environment
a continuous or semi-continuous pilot prototype of a wet oxidation unit including its
instrumentation and all interfaces with the waste compartement of MELiSSA.The
following tasks shall be performed:
- A sizing/scale-up based on the technology selected during previous activities
- A study and design of all interfaces with the waste degradation unit (MELiSSA
first compartment)
- Design of complete unit supported by relevant analyses
- Manufacturing and integration
- Performance of comprehensive test programme
Deliverables: Technical documentation, design, test results, wet oxidation unit including
interfaces with the waste compartment and control system.
Current TRL: TRL2 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
Human exploration - life support / Preparation for Exploration / 2015
Ref. Number: G513-045MC Budget: 300 K€
Activity Title: MELISSA Space Adaption Phase 3: Moon base Life support
Description: To define a MELiSSA loop recommended design for a Life Support module of a
manned Moon base. A considerable amount of basic research and engineering
data has been and continues to be generated by the MELISSA partnership. The
time is now appropriate for preliminary sizing of space systems. Based on
previous work phases, which leads up to a preliminary concept, it is now proposed
to establish a recommended design for a Life support module within a Moon base
inspired from MEliSSA technologies. Main target will be total closure of air and
water loop, as well as 40 % closure of the food loop.ALISSE criteria will be used
for trade-off and final evaluation of the recommended design
Deliverables: Reports/ design
Current TRL: TRL3 Target TRL: TRL4 Duration: 24 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G513-046MC Budget: 550 K€
Activity Title: MELISSA Genetic charcaterisation Phase 3
Description: In this phase it is proposed to built on the experience gained within phase 2 and to
focus now on the definition and validation of procedures to monitor/detect stress
expression in MELiSSA compartments II and IVa in order to build
recommendations for on-line stress detection technology Containing microbial
processes, MELiSSA system can be subject to genetic evolution as a
consequence to stress exposure. Consequently, a robust control of the overall
system requires the detection of any change of the process nature (i.e. genetic
evolution).Within this third phase, as a follow-up from the 2nd phase, we propose
to finalise the stress related gene expression study of compartment II and IV a,
then to establish and validate procedures associated to a continuous stress
detection monitoring. Requiremenst for an on-lin sensors will be finally
established.
Deliverables: Tests Documentation, scientific reports, sensor requirements
Current TRL: TRL2 Target TRL: TRL3 Duration: 30 Months
Ref. Number: G513-047MC Budget: 450 K€
Activity Title: Axenicity control within MELISSA compartment 2 and IV a
Description: To develop and test sensors for axenicity control of MELiSSA compartment II and
IV aWithin MELGEN 2 activity , methods to monitor the axenicity of compartments
II and IV a have been tested and validated. Requirements for the relevant sensor
have been established. Within this activity it is proposed to finalise trade-off for the
technological solutions, and to design, construct and test the sensor. This
development will include all steps from sample collection up to detection.
Deliverables: Trade-off report, Design files, tests documentation, Breadboard
Current TRL: TRL2 Target TRL: TRL3 Duration: 24 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 59
Ref. Number: G513-048MC Budget: 450 K€
Activity Title: Recycling of tissues and packaging wastes phase 1
Description: To evaluate the feasibility of thermophilic transformation of housekeeping and
packaging waste into monomersIn order to maintain cleanliness and hygiene in
manned habitats, strict housekeeping procedures are applied. These procedures
imply the use of biocide/fungicide impregnated wipes, which composition varies
from cellulose to polyester. After use, these wipes have to be discarded and
consequently add up to the mission wastes. The same applies to the main part of
food packaging. In order to reduce wastes mass, as well as launch mass,
recycling of these specific wastes shall be envisaged. The feasibility of
transformation of these wastes into simple molecules (i.e. monomers) needs to be
assessed and a wipe and packaging production system (i.e polymerisation) has to
be studied, defined and tested. This activity will focus on assessing the feasibility
of wipes and packaging degradation into monomers. The typical composition of
these wastes will be determined and a prototype treatment system will be defined,
assembled and used to assess the feasibility of thermophilic degradation of such
waste material.
Deliverables: Technical documentation, prototype thermophilic degradation system design files
and hardware, tests results
Current TRL: TRL2 Target TRL: TRL3 Duration: 36 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Theme 4.- SPACE TRANSPORTATION & RE-ENTRY TECHNOLOGIE
Ref. Number: G514-002ED Budget: 1,000 K€
Activity Title: Safety oriented reference architectures for man tended systems
Description: Implementation of the core "building blocks" of the safety oriented reference
architecture, in particular of the TM-TC, I/O and buses as defined by the pilot
activity on Safety oriented reference architecture TRP (SD4) and complemented
by the Fault Tolerant Computer, step 2, activity that shall make available the
prototype of the FT computer to build up a reference avionics test-bench
(ironbird).
This test bench will allow to perform full scale implementation (hardware and
software) and validation of on board processing chain on representative hardware
(function and performance) corresponding to selected “use case” mission that
shall be provided by the projects (space transportation, launcher). To implement
the I/O and on board communication/data acquisition/ main system peripherals
support of the reference architecture.
To perform the integration of the Fault tolerant computer with the I/O and systems
peripheral (space link interface, mass memory…)
To develop a “Development and Test “support system that shall have the
capability of emulating the necessary stimuli as necessary to test/validate the
application software as well as to exercise the fault tolerance/avoidance
capabilities of the system by injecting faults and record results of automated test
sequences.
To develop service layer software and test applications software representative of
future mission scenarios (performances, RAMS requirements)
Deliverables: Reference test bench for man tended safety oriented architecture
including Test and development environment to support fast prototyping/proof of
concept exercises
Test report and test analysis
Recommendations for any delta evolution of equipment under evaluation towards
final flight implementation
Roadmap towards certification
Current TRL: TRL3 Target TRL: TRL7 Duration: 24 Months
Application /
Timeframe:
TRL 6 in 2011.
Continuation of TRP item T401-016ED (Safety oriented reference architecture
for man rated systems)

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 61
Ref. Number: G514-003MC Budget: 500 K€
Delta-Development of SEPCORE based Heatshield for Earth Entry Capsule
Activity Title:
of Sample Return Missions
Description: The objective is to develop, build (breadboard) and test a heatshield system for
the Earth entry capsule of a sample return mission (e.g. Mars, comets, asteroids)
based on the SEPCORE concept. The ablative material developed in a parallel
activity (under TRP) shall be considered. A typical entry environment is
characterised by peak heat fluxes of 15-20MW/m2 and heat loads up to
200MJ/m2.
The work to be performed within this activity includes:
o Review of the results from the previous activity and definition of required
concept modification for a sample return application.
o Verification of representative large scale manufacturing capabilities.
o Development and qualifiaction of a suitable mounting technology of the ablative
TPS to the hot structure.
o Breadboard design, manufacturing and testing under representative conditions
(15-20MW/m2).
Deliverables: Breadboard, documentation
Current TRL: TRL2 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
Sample return missions, e.g.MSR or Marco Polo
Ref. Number: G514-004MC Budget: 250 K€
Activity Title: Development of Secondary Protections for Hot Structures
Description: The objective is to develop and verify a secondary protection system to be placed
underneath a hot structure (e.g. leading edge) with the aim to mitigate the risk of a
catastrophic failure in case of a damaged outer structure (e.g. micrometeorid or
debris impact).
The development shall be based on a ceramic foaming-up system developed in a
previous TRP. In this activity the following tasks shall be performed to raise the
TRL: Step 1: Improvement of material manufacturing process; manufacturing of
about 50 test samples; performance of extensive plasma wind tunnel tests,
extensive flame tests and key mechanical tests.
Step 2: Evaluation of test results and establishment of a preliminary design data
base. Analytical estimation of mass budget for a potential vehicle (e.g. IXV) and
assessment of residual risk after implementation of the measure.
Step 3: Design, manufacturing and test of a demonstrator (larger dimensions,
including insulation and ceramic layer).
Deliverables: Material samples, breadboard demonstrator, documentation
Current TRL: TRL2 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
Human entry missions, e.g. CSTS

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G514-005MP Budget: 700 K€
Activity Title: Enhancement of Plasmatron operating capabilities
Description: o The contractor shall organize, plan and realize the necessary improvement and
adaptation for the Plasmatron facility concerning the power supply hardware with
the aim to improve steadiness of the flow .
o The contractor shall design a dedicated supersonic nozzle for the VKI
Plasmatronm to enhance the aerothermodynamics testing capabilities of the
facility. He should ensure the testing procedure in new testing configuration
allowing off-stagnation point studies.
o The contractor shall harmonize the suitable measurement techniques to support
the extended studies for new testing configuration. He should pay attention to the
assessment of the measurement techniques used for the qualification of the new
capabilities of the Plasmatron facilities.
. The contractor shall adapt/develop the CFD tools for supersonic plasma flows
corresponding to the new operating capabilities and testing configuration.
o The contractor will also adjust the data-processing tools previously develop for
analysis of experimental data. He should also set-up the methodology for ground
testing duplication of real flight conditions tailored to the improved Plasmatron
facility.
o The new operating envelope of the Plasmatron facility should be re-defined
showing the enhancement of its testing capabilities. He could also point up the
complementarities through a standard comparison with current high enthalpy
facilities.
o The contractor shall properly address the flight extrapolation methodology in
relation with the new potentialities of the Plasmatron facility and use EXPERT and
IXV as examples.
Deliverables: technical notes, experimental adat and analysis
Current TRL: TRL4 Target TRL: TRL6 Duration: 36 Months
Application /
Timeframe:
All earth reentry vehicles, planetary probes , future launchers and debris analysis .

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 63
Ref. Number: G514-006MP Budget: 1,500 K€
Activity Title: Prediction methods for propellant management devices
Description: Objective of this activity is the provision and validation of a software environment
that allows to predict the effects of fluid sloshing in tanks on the space craft
dynamics.
Fluid sloshing in tanks can be generated by, e.g. attitude control manoeuvers and
leads to time depedent forces and moments acting on the satelite until the
sloshing
is dissipated by friction.. A further consequence is the large uncertainty related to
the fuel position in tanks, endangering uninterupted fuel supply to the engine, if
the fuel mass is temporarily not covering the engine feeding pipe inlets in the tank
due to large scale sloshing motion.
This software shall incorporate engineering models, e.g. for the flow in PMDs of
different types, or the effects of diaphrams or membranes placed on the free fuel
surface, as necessary. It shall also offer the possibility of validating advanced
sloshing models against linearized models, e.g. spring mass-damper-systems for
the simulation of the effects of fuel sloshing on the space craft dynamics. For
practical applications, especially for space craft with a large percentage of fuel
mass, e.g. ATV, the system shall provide the possibility to couple the flow
solution to a six-degree-of-freedom model of the space craft dynamics.
Deliverables: Software / manuals / technical reports and numerical data from validation
Current TRL: TRL4 Target TRL: TRL6 Duration: 24 Months
Application /
Timeframe:
All future missions and space craft that use PMDs as capillaty devices or
membranes
Ref. Number: G514-007MP Budget: 500 K€
Activity Title: ESPSS: European Space Propulsion System Simulation
Description: A first version of the ESPSS-library is in the make, forming the first basis of an
European tool. On this basis, the tool will be extended with advanced component
modelling related to tanks, lines with their components (filters, valves, pumps,…),
multi-phase and combustion for both steady and unsteady phenomena.GSTP
Detailed model description, implementation and validation based on experiments
for particular
Components of European make such as valves, igniters, thrusters,….
Deliverables: technical notes and experimental and numerical database
Current TRL: TRL3 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
Propulsion systems/launchers

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G514-008MP Budget: 2,000 K€
Activity Title: Kinetic shock tube for radiation data base for planetary exploration
Description: The objective of the present activity is to investigate high temperature gas
dynamics as they are involved in hypervelocity planetary re-entry. Development of
advanced physical modelling, as thermo-chemical non-equilibrium and radiation,
is a key point for design of probes and vehicles for planetary mission. However
only little database are available to consolidate the models elaborate, and such
activity demand a complete procedure from the instrumented facility to the
modelling implementation in the data processing. Thus such development require
experimental results based on dedicated set-up like shock tubes suitable for
re-entry condition duplication. Moreover if the shock tube facility represent a
convenient tool for the accurate replication of very high speed re-entry conditions
(> 10km/s) it should also be able to complement studies carry out in plasma
facilities and classical hypersonic wind tunnels. Attention must be focus as well on
adapted optical diagnostics together with appropriate data processing techniques
and efficient numerical tools.
All these elements should be integrated for a proper validation process of current
physical models used to describe high temperature effects on re-entry flows and
help to built-up efficient tools for vehicle design. Establishement of a European
shock tube dedicated to kinetic studies for high temperatures (more than 6000K).•
The contractor shall qualify and assess the experimental set-up for re-entry
condition duplication.
• He shall adapt the appropriate measurement techniques for fast measurements
and optical diagnostics with dedicated calibration.
• The contractor shall investigate up-to-date thermo-chemical non-equilibrium
studies including collissional-radiative models and integrate activities on radiation
modelling.
• The contractor shall develop in parallel numerical tools to data process the
experimental results and set-up validation process for physical modelling studies.
• The contractor should propose physical model validation activity based on
measurements collected on the tools and techniques previously set-up. This
validation should also aims to the cross comparison of shock tube and plasmatron
spectroscopic results. A dedicated shock tube shall be developped and
instrumented. Tests will be performed for various gas mixtures, to provide
specrally resolved emission and absorption spectra, as a minimum. More
advanced techniques shall also be assessed, and if possible demonstrated.The
obtained results will be compared with documented results.
Deliverables: Technical notes
Current TRL: TRL3 Target TRL: TRL5 Duration: 36 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 65
Ref. Number: G514-009EC Budget: 600 K€
Activity Title: Fault Tolerant Flight Control System Components
Description: To develop and validate the core components of fault tolerant flight control
systems (FTCS): fault detection and identification, active system restructuring,
reconfigurable flight controller, reconfigurable flight path planning, on-line system
identification, and mission adaptation.
To integrate the core components and demonstrate the functionality of each
component of the FTCS architecture for a given reference mission.Currently ESA
and national agencies are evaluating various concepts of reusable launch
vehicles. One of the critical elements for such future systems is represented by
the guidance, navigation and control system, which is responsible for piloting the
vehicle along a reference trajectory. To address the goal of increasing vehicle
safety and reliability, there is now a significant interest in reconfiguration
technologies for flight control systems. The reconfiguration problem, both at
subsystem and system levels, e.g. landing to alternate site in case of
abort/contingency cases, is one of the most important and challenging aspects for
future reusable space transportation vehicle. Over the last years, a number of
researchers have developed reconfigurable control systems (inner-closed-loop)
for a variety of flight vehicles, and promising results were obtained for systems
with sufficient control actuation redundancy. As this approach is not sufficient for
future reusable launch vehicles, due to their minimal suite of control actuators, a
guidance system (outer-closed-loop) with reconfiguration capabilities is also
required to satisfy vehicle and control constraints and to achieve a safe abort.
In the light of the above consideration, the aim of the proposed activity is to
develop and validate the core components of fault tolerant flight control systems
able to fly a variety of vehicle types in multiple scenarios, as well as handle
dispersions, failures and abort requirements in a robust fashion. Special attention
will be given to the development of advanced control concepts that require
minimum ground effort for retuning and analysis. Specific tasks to be performed
include:
- Analysis and trade-off of fault tolerant flight control system architectures for
safety critical ssytems
- Review and evaluation of reconfigurable guidance and control methods
- Detailed design of the most promising fault tolerant flight control system
components
- Development and validation of the reconfigurable flight control system
components
- Adaptation of existing performance simulator for the analysis and robustness
performance assessment of fault tolerant flight control systems for representative
failure cases
Deliverables: Technical Documentation
Simulation Test Data
Validated FTCS core components
Current TRL: TRL1 Target TRL: TRL3 Duration: 18 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G514-010MC Budget: 300 K€
Activity Title: Methodology for analysis/test correlations of an SRM
Description: The objective is to develop a methodology based on tests and analysis that allows
a proper modelling of the SRM dynamic vibratory behaviour during flight.In view of
performing accurate dynamic analyses of launchers that use SRM propulsion,
relevant dynamic models of the SRM and the dynamic load cases (ignition and
pressure oscillations during the flight) are required. The scope of this study is to
develop a methodology based on tests and analysis that enables the definition of
adequate dynamic SRM models and adequate dynamic load cases for the SRM
flight events. This methodology will be comprised of:
• A finite element approach towards the modelling of the SRM structure that
includes a solid propellant model and an associated damping methodology.
• An analytical/numerical methodology related to the modelling of the dynamic
load cases (the SRM dynamic model also allows the introduction of specific
dynamic excitations).
• A test methodology and measurement plan, which will involve specific test
requirements on the dynamic identification of the SRM (thrust profile,
accelerations & modeshapes), on the dynamic identification of adjacent structures
of the firing tests facilities etc.
• A methodology dedicated to the correlation of the SRM models and the dynamic
load cases for the launcher dynamic analysis.
Remark: The first 2 bullets are related the modelling of the SRM and dynamic load
cases, whereas the latter 2 bullets are linked to the analysis/test correlation of the
firing tests.
Deliverables: analysis methodology, documents
Current TRL: TRL2 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
Beneficial if results are derived in parallel with the VEGA development. Also
relevant for next solid based launcher, VEGA upgrades etc.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 67
Ref. Number: G514-011MP Budget: 250 K€
Activity Title: Aerodynamics of decelerators : parachutes and ballutes
Description: The performance of Down Load Systems (DLS) especially the deployment of
supersonic parachutes have recently shown to be inadequately mastered (
lessons learned Genesis). Note that even subsonic deployment is still today
without risk ( lessons learned USV) . The expertise on supersonic parachute
deployment resides mainly ( with the exception for Huygens ) in Russia and in the
US.
The objective of the present activity is to improve the knowledge of high speed
decelerators (parachutes, ballutes etc...); to prepare experimental windtunel
campaigns in order to set up appropriate data bases useful for parachute design
and analysis tool validation ( e.g. PASDA) ; testing of high speed decelerators, in
particular with respect to their deployment and their stability in similated flight
conditions. Range of deployments of interest: Mach numbers 2 up to 7..The
contractor shall perform the following activities :
• Review state of the art in parachute design and analysis and address the
limitations and short coming of the Agency PASDA tool especially for the
supersonic regime.
• Propose experimental strategy taking into account agency needs, select
appropriate wind tunnel models for trans- and supersonic windtunnel testing.
• Improve PASDA tool by enhancing engineering routines for supersonic DLS
deployment and perform validation exercise using present new experimental data
base
• Apply updated tool to some agency defined test cases such as e.g. EXPERT
and Huygens
• Provide synthesis and recommendations to expand PASDA tool to include other
type of decelerators such as ballutes, inflatable systems or other types of drag
chutes.
Deliverables: Wind tunnel test data, CFD Solutions, Technical notes,
Test Articles, Test Data, updated PASDA
Current TRL: TRL2 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
All earth reentry vehicles, planetary probes: the early opening of a decelerator is
needed when the thin atmosphere of a planet (Mars) does not provide a
sufficiently intense hypersonic braking (e.g when the mass of the vehicle
increases and the diameter of the hypersonic shield is limited by the fairing of a
launcher) . It is also necessary even for Earth entry vehicle when additional
stability is required at high Mach number.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G514-012SN Budget: 6,500 K€
Advanced Self-blocking Electro-Mechanical System Development and
Activity Title:
Ground-to-Flight Qualification
Description: The objective of the activities is the design, development, manufacturing and
ground qualification of an advanced self-blocking electro-mechanical system, to
be flight qualified through the IXV flight opportunity as flap control system (FpCS),
therefore fulfilling the performance and interfaces requirements needed for the
compliance with the IXV project.
Deliverables: 1. Documentation including: technical specification, design definition, design
justification, product assurance, interface control, test specifications, test
procedures, test reports, analysis reports, inspection reports, verification reports,
mechanical and thermal mathematical models, functional simulation model
2. Hardware and software development, qualification and flight models. Since the
flap control contributes to the overall vehicle control strategy, it is necessary to
integrate the flap control software into higher level system verification loops.
3. Necessary Ground Support Equipments.
Current TRL: TRL4 Target TRL: TRL8 by 2012 Duration: 30 Months
Application /
Timeframe:
Justification for DN:
Launchers, Atmospheric Re-entry, Space Transportation
Continuation and consolidation of SABCA technology heritage in actuators
systems for space transportation systems. In particular contracts C15919,
C16437, and C22323 funded by GSTP with 4M€.
Continuity with previous IXV project phase-0/A/B/C1 activities.
Non-competitive tendering is justified according to Articles 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 69
Ref. Number: G514-013MM Budget: 250 K€
Activity Title: Fibre Bragg Grating Experiment - SHEFEX 2
Description: Optical fiber sensor technology is not sensitive to ElectroMagnetic Interferences
(EMI) and can monitor the temperature up to 2000ºC (sapphire Fiber) and up to
1050ºC with standard telecom FiberBragg Grating. In a previous GSTP-4
activity, the feasibility of a fiber sensor for monitoring the TPS up to 1050ºC was
demonstrated. The Fiber was packaged to optimize the contact with the TPS with
maximum heat transfer to the sensor, whereas the fiber line outside this region is
packaged so as to better protect the fiber from the heat and increase its reliability
and lifetime. The stability of the fiber response was demonstrated over a period of
a few days compared to a maximum 10 minutes needed for the reentry.
The objective of the activity is the design and manufacture of a Fibre Bragg
Grating (FBG) sensor equipment to measure the high temperature environment of
the thermal protection system during re-entry. This equipment is envisaged as a
passenger experiment on the SHEFEX 2 re-entry vehicle.
A passenger experiment will be manufactured and qualified for the SHEFEX 2
re-entry vehicle. Three fiber lines will be built and installed on the SHEFEX 2 tile
to monitor the high temperature environment. An Interrogation module based on
the PROBA 2 FSD (Fiber optic Sensor Demonstrator) development will handle the
data acquisition, the conversion of optical to optoelectronic signal and the
temperature measurement The Interrogation module will be modified to comply
with the vibration and heat requirements during Reentry. The tasks include the
qualification (thermal cycling and vibrations).
Deliverables: 1.- Three Fiber lines and their installation on a SHEFEX tile
2.- Interrogation Unit (Flight)
3.- Interface, Control Document
4.- User Manual Document
5.- Space Environmental Testing Results
Current TRL: TRL5 Target TRL: TRL7 by 2011 Duration: 18 Months
Application /
Timeframe:
All re-entry missions including IXV, ARV upgrade, Mars sample return mission.
Continuation of GSTP-4 activity G408-10MP "Advanced Flight Measurement
Techniques for Aerothermodynamics - Fiber Optic High Temperature Sensors
for Reentry Vehicle Design and Qualification" (contract 20873 funded with
300K€) to establish the feasibility of the technology for re-entry TPS
Justification for DN: monitoring. In addition it builds on MPB's existing hardware developments that
are to be flown on PROBA 2.
Non-competitive tendering is justified according to Articles 6.1. c) of the
Contracts Regulations.

ESA/IPC(2010)51
Annex 2, Page 70
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G514-015QE Budget: 130 K€
Qualification of a new white antistatic coating for thermal protections of
Activity Title:
launchers
Description: At the present time, a white antistatic coating called Mastic As is applied on
thermal protections (TP) of launchers. This coating has been developed by CNES
for Ariane 4 and still used for Ariane 5.
The Mastic As coating being not compliant with the new European environment
regulations (REACH, ROHS, VOC regulation …), CNES and industry have
developed a new formulation. This new product is also independent to North
American technology (ITAR and EAR regulations).
At the same time, new TP called Prosial LS are under qualification by Astrium ST
(for VOC limitation reasons).
The main objectives of this activity is to qualify the new coating on these new TP.
The qualification tests will be performed on the system Prosial LS + new Mastic
As in co-operation with the implicated industrials.
Besides, it is considered to qualify the new Mastic As on the TP of VEGA.
The qualification program includes tests such as :
- thermo-optical measurements
- outgassing test
- thermal ageing tests (damp humidity, salt spray, thermal cycling…)
- natural ageing (in Guyana)
- industrial setting (handling, projection, repairing…)
Deliverables: Qualification of different TP/coating combinations; Qualification of industrial
setting.
Current TRL: TRL3 Target TRL: TRL8 by 2011 Duration: 12 Months
Application /
Ariane 5 and VEGA
Timeframe:
MAP is the only European company making space proven thermal control
coatings.
Justification for DN:
Non-competitive tendering is justified according to Article 6.1. a) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Theme 6.- NAVIGATION
ESA/IPC(2010)51
Annex 2, Page 71
Ref. Number: G516-01MM Budget: 600 K€
Activity Title: Photonic micro-navigator for microsatellites
Description: The objective of this activity is to develop an micronavigator system based on
photonic technologies for use by microsatellitesThe present actvitity shall develop
accelerometers based on micro-photonic technologies that can be integrated in a
photonic chip to provide the necessary functionality for an inertial navigator
microsatellites
Deliverables: A prototype of a photonic micronavigator at TRL-5
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Ref. Number: G516-02GN Budget: 300 K€
Activity Title: GNSS processing strategies for LEO constellations
Description: Improve methods for precise orbit determination of LEO satellites and especially
constellations of such satellites using GNSS receiver dataPrecise orbit
determination for low-Earth orbiting satellites can be based successfully on
ground-based measurement systems (SLR, Doris), GNSS data processing or both
combined. Other techniques are possible when several LEO satellites are orbiting
in formation or independently of each other. Models and algorithms have been
defined, for example, based on differencing data between transmitting satellites,
receiving satellites, ground antennas and/or consecutive data epochs. This activity
will start with an overview of existing methods from literature, and investigate the
feasibility of implementing these concepts in existing operational or prototype
software. Several concepts may be implemented in a prototype manner, and
tested using data from existing LEO satellites with on-board GNSS receivers.
Deliverables: Activity report and a prototype implementation of the S/W with documentation.
Current TRL: TRL3 Target TRL: TRL7 Duration: 18 Months
Application /
Timeframe:
Will be of benefit for the SWARM mission

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G516-03GN Budget: 400 K€
Activity Title: Improved radiation modelling for GNSS satellites
Description: To improve further on the radiation pressure modelling in high-precision orbit
determination for navigation satellites.Among the forces affecting GNSS satellite
motion, and therefore orbit determination accuracy, the radiation pressure force is
considered the one with the largest remaining uncertainty. The most performing
models used nowadays are purely empirical, and consist in estimating a number
of coefficients of constant or cyclic acceleration components. This has the
disadvantage that other perturbations or error sources are partly absorbed in this.
A dedicated activity is proposed to analyse the empirical models in more detail,
and in parallel to explore models based on detailed geometry / radiation flux
interaction.
Deliverables: Activity report and a prototype implementation of an improved radiation pressure
model with documentation.
Current TRL: TRL3 Target TRL: TRL7 Duration: 18 Months
Application /
Timeframe:
Can be applied as soon as available (GPS), and of particular value for Galileo
High-Accuracy applications.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Theme 7.- GENERIC TECHNOLOGIES
ESA/IPC(2010)51
Annex 2, Page 73
Ref. Number: G517-001MM Budget: 150 K€
Activity Title: Voice Coil Motor Qualification Model
Description: The purpose of this activity is to consolidate the development obtained with the
"Voice Coil Motor Engineering Model" activity towards the QM and Flight
application Model.Following the "Voice Coil Motor Engineering Model" activity and
based on the achieved results, the purpose of this activity is to consolidate this
development towards the QM and Flight application Model by means of the
Design, Manufacturing, Assembly, Integration and fully Testing, including life test
a Qualification Model for the identified project(s) and application(s).
Deliverables: Qualification model
Current TRL: TRL6 Target TRL: TRL7 Duration: 12 Months
Application /
Timeframe:
Applications involving voice coil motors, 2010
This activity is a direct continuation of the work developed by Cedrat in the
GSTP-4 activity G609-39MM, "Voice Coil Motor Engineering Model" funded
with 120 K€ under ESA contract 21295. It is then recommended to continue
Justification for DN: the development with the same contractor.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.
Ref. Number: G517-002MM Budget: 400 K€
Activity Title: Piezo new sources materials, piezoceramics motor qualification
Description: The purpose of this activity is Designing, Manufacturing, Assembly, Integration
and fully Testing, including life test, of an EQM (Engineering and Qualification
Model) based on the new piezo material identified and validated by
CNES.Referring to the CNES presentation during the mapping meeting, this
activity concerning Piezo motor has been proposed in the following context:
- In the past decade, CNES and ESA worked together to qualify a piezo source
and number of flight applications were developed (characteristics so appreciated
for high precision instruments)
- ESA also funded piezo rotating motor study at CEDRAT company (F)
- Years of CNES R&D activities at CEDRAT company make piezo actuators
solutions available for space applications (amplified actuators, lot evaluation
process…)
- Good complementarities with NOLIAC (NW) as European ceramic supplier
=> Need to prolong evaluation work performed under CNES funding by an ESCC
standard at ESA level.
The purpose of this activity is to Design, Manufacturing, Assembly, Integration and
fully Testing, including life test, of an EQM (Engineering and Qualification Model)
based on the new material identified and validated by CNES.
Deliverables: Qualification model
Current TRL: TRL3 Target TRL: TRL6 Duration: 12 Months
Application /
Timeframe:
All piezo electrical motors applications, 2009

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-003MM Budget: 150 K€
Activity Title: Compact Magnetic Bearing for High-Speed Rotor
Description: Development, design, manufacturing and testing of a compact passive/active
magnetic bearing system, which can support a high-speed rotor for potential use
in a small reaction wheel. Specific emphasis shall be given on low-cost and
low-complexity solutions.In the context of a potential speed increase in order to
reduce the mass and size of future reaction wheels, the life of mechanical
bearings (typically ball bearings) becomes very critical. In previous activities, both
active and passive magnetic bearings have been investigated for high-speed rotor
suspension in long-life applications. For cost & complexity reasons, passive
magnetic bearings are often preferred, however for very high speed, the low
mechanical strength of currently available permanent magnets restricts the
maximum size of the bearing, hence their stiffness.
A rotor using Magnetically Loaded Composite (MLC), exhibiting high strength
together with adequate magnetic properties, is currently being developed in other
ESA activity titled “New Material for High Speed Rotor”. The new rotor material
and design could overcome the current size restrictions of passive magnetic
bearings. It is therefore required to develop a passive/active magnetic bearing that
can be used in combination with the innovative rotor and a compatible electric
motor, for verification of the concept using an appropriate hardware prototype.
Deliverables: Magnetic bearing breadboard model (compatible with a high-speed rotor
developed under another ESA contract), Technical data package,
computer-based simulation models and test data files
Current TRL: TRL2 Target TRL: TRL5 Duration: 12 Months
Application /
Timeframe:
Magnetic bearing suspension for small reaction wheels and other compact
rotating assemblies, e.g. scanners in scientific instruments (need date after 2011)
Ref. Number: G517-004MM Budget: 300 K€
Activity Title: Advance material for ball bearings
Description: To qualify the Cronidur 30 as relevant material for space ball bearings
manufacturing.Most of the European space ball bearings are made of 440C that is
sensitive to stress corrosion cracking (table2). The Cronidur 30 has previously
been assessed and shown very good performances with respect to stress
corrosion cracking but also with respect to other specific ball bearing critical
performances. Furthermore, above 250°C the 440C is loosing its main
characteristics, therefore the Cronidur 30 is the only solution for high temperature
bearings. This material should be officially validated for space use.
Deliverables: Validation of the Cronidur 30 as standard material for space appliucation.
Current TRL: TRL4 Target TRL: TRL8 Duration: 18 Months
Application /
Timeframe:
The targeted applications are all mechanisms relying on ball bearings for cryo
until hot temperature. This is the only candidate/solution for Bepi Colombo
mechanisms.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 75
Ref. Number: G517-006MM Budget: 500 K€
Activity Title: Multi wafer hybrid integration: Robotics IMU II
Description: The goal of this activity is to develop an integrated micro localisation platform
based on inertial platform (3-axis solid-state gyro + 3 accelerometer) with a digital
serial bus interface (e.g. CAN). The platform shall be specifically designed for use
in navigation for planetary robotics applications where mass is extremely critical
and there is a wide spectrum of mechanical noise. The effort of the activity will be
on very tight integration of ESA-developed sensors and interface/processing
circuitry aiming to total mass below 200 gr.The activity shall continue from the
point reached by the TRP activity “Multi wafer hybrid integration: Robotics IMU I”
to increase the TRL level in order to arrive to level 6. Hence design and
manufacturing activities will be followed by testing in relevant environment.
Deliverables: Design and manufacturing files, Test Reports, Final Report, Breadboard
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Ref. Number: G517-007MM Budget: 600 K€
Activity Title: Testbed For Telemanipulated Satellite Servicing
Description: Future satellite servicing missions need adequate preparation. The proposed
activity aims at the implementation of a testbed, which allows ground testing of
critical mission phases like the capturing of a client satellite or the stabilization of
the coupled system via telemanipulation/telepresence technologies.The activity
shall investigate, design, implement and a testbed, which allows ground testing of
critical mission phases in the task of capturing a free-flyer.
The testbed shall be implemented on the basis of the existing EPOS facility.
The activity shall also develop a demonstration showing either capturing of a
client satellite or the stabilization of the coupled system via
telemanipulation/telepresence technologies
The activity shall as minimum be composed of the following tasks:
1. Requirement and test Definition
2. Architectural Design
3. Implementation
4. Test and demonstration
Deliverables: Study and design documentation, reports and video material for demonstration,
hardware added to EPOS, software.
Current TRL: N/A Target TRL: N/A Duration: 18 Months
Application /
Timeframe:
No ESA mission foreseen/2010-2020

ESA/IPC(2010)51
Annex 2, Page 76
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-008MM Budget: 400 K€
Activity Title: Virtual testbed
Description: The subject activity will provide means to build rapid prototypes, to visualize
different mission scenarios, to simulate and visualize subsystems and to simulate
and test mission time-lines.
The virtual testbed will be based on previously developed VR- and simulation
technology. It will include physics simulation, interfaces to state of the art
modelling and simulation software (e.g. Modelica/20Sim/SCILAB/Matlab) and an
interoperation logic, which supports collaboration between multiple users over the
Internet.
The testbed could be used to support engineering decisions and concurrent
engineering through simulation and visualization of test scenarios. VR-testbed
support H&W-in- the-loop scenarios, i.e. virtual models can replaced by H/W.
The system will enable crew and staff training already at early stages of a
development.
During a mission it can be deployed as an advanced man machine interface
based on “Projective Virtual Reality” and serve a powerful tool for the presentation
of mission results.
The proposed activity aims to develop and (or) integrate a suite of tool that can be
used to support the initial design phase of robotics system. The tool will cover the
environment and A&R control and dynamic modeling, the kinematic/ path planning
specifications aspects, the activity specification, the simulation of the overall
activities and the performances evaluation.
While it is the intention to build on exist tools for contact dynamic (Teleman), soil
interaction (3DROV), 3D realistic modeling (3DRM & VIMANCO), activities
specifications (DREAMS, FORMID) these tools need to be integrated and
extended to cover for instance system dynamic, performances evaluation as well
as interface needs for more specialized tools.
The tool shall support interfaces such that modeling inputs/ outputs to others more
specialized tools can be done via existing standard (e.g. STEP, VMRL, XML,…).
Deliverables:
Finally, during the activity, the Contractor shall evaluate needs for embedding
such a tool in the ESTEC CDF and support the its integration to it.
Study and design documentation, reports and user manual, software.
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Justification for DN:
This activity is a continuation of the previous development done by Trasys in
the frame of ESA contracts (Teleman, 3DROV, DREAMS) and requires the
expertise developed by the contractor in those activities.
Non-competitive tendering is justified according to Articles 6.1. a) and c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 77
Ref. Number: G517-009MM Budget: 1,500 K€
Activity Title: Haptic Control
Description: The activity aims at developing a haptic interface to allow intuitive and user
friendly use of a remote robot agent. The main objective is to study new
algorithms able to control a remote robot, taking into account transmission delays.
ESA has developed a concept for teleoperation of anthropomorphic robot agents
by means of arm Exoskeletons. ESA has internally developed its own exoskeleton
and also promoted through R&D the development of an industrial one.
ESA has manifested the use of exoskeletons as primary way to command the
SPERO facility proposed for installation on the Columbus/ ISS. Within SPERO,
an exoskeleton will be initially an experiment itself.
An Exoskeleton is in principle the most intuitive interface to operate robot arms.
However to operate correctly it needs to be complemented by additional
teleoperation devices and operated with suitable control algorithms.
The proposed activity aims at integrating the ESA Exoskeleton developments,
with other teleoperation devices (such as stereo goggles, head/neck/eye trackers)
into a testbed to allow experimentation on haptic telemanipulation in presence of
communication restrictions.
The testbed will allow preparation of the proposed SPERO experiment.
The activity shall as minimum be composed of the following tasks:
1. Requirement and experiment Definition
2. Architectural Design
3. Implementation
4. Experiment tests and demonstration
Deliverables: Study and design documentation, user manual, hardware (to complement existing
ESA hardware) and software.
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
SPERO facility on Columbus/ 2010

ESA/IPC(2010)51
Annex 2, Page 78
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-010MM Budget: 600 K€
Activity Title: Ground Control Station For Autonomy
Description: The goal of this activity is to build up on previous ESA developments to produce a
ground control station capable to interact with an autonomous controller in order
to prepare and validate the autonomous “behaviour” of the controller and monitor
and analyse the execution results.
In the course of several years ESA has developed a number of technologies for
producing control stations for robotics. In particular A-DREAMS is a framework for
building control station supporting programming, monitoring and teleoperation of
robot manipulators, 3DRM a geometric and kinematic simulator, 3DROV a physics
based rover simulator, MUROCO/FORMID a robot programming specification and
verification tool, TAPAS a task planning tool.
All these technologies constitute a solid base for the implementation of a control
station for autonomous robots, the subject of this proposal. Such control station
shall have the ability to:
1) program the basic “behaviors” (tasks and underlying actions),
2) validate formally the behaviors for safe execution
3) compose the behaviors into plans (timelines) compatible with available
resources (e.g. time, energy, bandwidth, mass memory)
4) simulate and validate the plans
5) upload the plans into a target robot system
6) monitor the execution of the plan (on the base of differed telemetry)
7) update underlying models on the base of telemetry
The activity shall design, implement and demonstrate in a relevant test the
proposed control station. In particular the activity shall as minimum be composed
of the following tasks:
1. Requirement and test Definition
2. Architectural Design
3. Detailed design
4. Implementation
5. Test and demonstration
Deliverables: Study and design documentation, test reports and user manual, software.
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 79
Ref. Number: G517-011SW Budget: 300 K€
Activity Title: Automatic testing improvement
Description: Following the TRP on automatic testing, consolidate and extent the technology to
other modelling languages and with more capabilityconsolidate the tool from
Leirios based on the use of UML and OCL with the Borland tool.
- investigate the possibilities with other modelling languages such as Scade,
Matlab, or with more usual tools such as Rhapsody
- select a set of modeling language and industrialize the tool
- refine the process previously defined to take into account the variety of
languages
- perform a representative case study
Deliverables: new version of tools
- new version of the process
- case study
Current SW
Readiness Level:
Beta version
Target SW
Readiness
Level:
Release Duration: 18 Months
Ref. Number: G517-012SW Budget: 200 K€
Activity Title: Customisation of the ASSERT Framework to industrial environment
Description: Customisation of the ASSERT framework to real industrial environment.The
ASSERT project has delivered a set of prototypes to support a new development
process ensuring the preservation of properties from early SW system
specification down to the final implementation.
This activity will have to prepare the use of the ASSERT toolset on operationnal
projects by customising the toolset to a specific industrial environment. Such a
customisation will for example include specific modelling tool preselected by the
industry or adaptation to a particular middleware or operating system to replace
the ASSERT generic one.
Deliverables: Development environment; commercialisation plan; case study
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
Generic for all missions in phase B / 2011

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-013SW Budget: 300 K€
Activity Title: On Board operating system Upgrade for Leon
Description: To upgrade the existing RTEMS operating system to the Leon 3 and new
generation of micro-processors. Processors. Provide support to European industry
in the use and maintenance of such operating systemPorting the On board
Operating System to Leon-3 and new generation of space microprocessors
Qualification of the OS for selected mission profiles
Supporting the application of the operating system in space projects, including the
support to remove deficiencies
Deliverables: maintained operating system for LEON 3 and for NGMP
Current SW
Readiness Level:
Justification for DN:
Beta version
Target SW
Readiness
Level:
Release Duration: 18 Months
The work proposed in this activity is a direct continuation of two previous
GSTP activities, G607-07EM, "Cross development environments: Operating
systems - RTEMS", funded by GSTP-4 with 250K€ and G607-10EM, "Real
Time operating System (RTEMS) tasking monitoring tool", funded by GSTP-4
with 100 K€, (ESA contract 21141). Following the successful work by Edisoft,
it is proposed to procure this activity in direct negotiation with the same
contractor.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contract Regulations

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 81
Ref. Number: G517-014SW Budget: 300 K€
Activity Title: Qualification of xLuna operating system
Description: A Linux-like operating system allows for easy development and execution of
non-critical onboartd applications alongside with critical ones. This facilitates for
instance the development of software by scientists and principal investigators to
control their onboard experiments.
The objective of this activity is to qualify the pre-existing product called
xLuna.Today the product is ready but is not enough mature for be embarked on a
satellite computer.
Critical Software is porting ExoMars rover application on xLuna for a
demonstrator. In the meantime particular attention is dedicated to increase the
performances and to reach source coverage with basic tests.
The purpose of this GSTP is to qualify this product to fill the gap and be compliant
with the new ECSS E 40 and Q 80, now in version C, for SW used in space
missions
The work to be carried out under this GSTP is structured as follows:
1. consolidate the existing design documents
2. generate a test plan compatible with ECSS-E-40 and ECSS-Q-80 for critical
SW.
3. implement the test suite
4. execute the tests and provide the reports.
The work will be performed on new LEON 3 microprocessor also to verify
performance in comparison of old LEON 2
Deliverables: Qualification test suite (SW + Documentation).
Final version of xLuna (source code and executable).
Current SW
Readiness Level:
Justification for DN:
Beta version
Target SW
Readiness
Level:
Release Duration: 24 Months
This activity is a direct continuation of a previous activity done by Critical
Software for the development of the xLuna operating system (contract 19715
funded with 280 K€).
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-015EE Budget: 750 K€
Implementation and Demonstration of RF testing approaches for reduced
Activity Title:
antenna/payload AIT/AIV
Description: To implement testing methodologies for antenna/payload end-to-end RF testing at
satellite levelThe increasing complexity and stringent performances required in RF
instruments and payloads demands more and more that RF functional verification
be performed on the integrated satellite under the most realistic operational
conditions. As a consequence and in order to minimize the cost and duration of
test campaigns it is necessary to develop advanced RF test methodologies.
Extending testing to end-to-end performance requires a significant departure from
traditional techniques, mostly based on CW tests (Continuous Wave tests, i.e.
using non-modulated single frequency input signals) under (simulated) worst-case
conditions, in favor of methods that expose antennas, instrument or payload to
realistic operational conditions, in terms of signals, power levels, etc.
Following the results of previous studies it is necessary to extend existing test
facilities to cover the new needs have to be explored, taking into account the
different type of performance figure required for system-level assessment. At the
same time to keep the overall testing time within acceptable limits, it is needed to
develop performance interpolation procedures using existing accurate EM
modelling capabilities to achieve complete functional characterization from a
reduced number of measurements. Starting form the result of the precursor TRP
activity, advanced instrumentation and test beds shall be studied and
implemented in a reference facility. The testing methodologies shall then be
refined and consolidated, fixing the criteria to establish the "performance sampling
and interpolation rules" to be used in common cases and defining the procedures
for the use of the relevant antenna modeling tools as interpolators. Finally the new
methodologies will be demonstrated on selected realistic configurations.
Deliverables: Validated methodology implementation and reference facility, including modelling
tools
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
Advanced AIT methods 2012

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 83
Ref. Number: G517-016EE Budget: 500 K€
Implementation and Demonstration of EMI/EMC approaches for full
Activity Title:
development cycle support and reduced AIT/AIV.
Description: To implement new methodologies to perform EMC testing at satellite level The
complexity and stringent performances of most satellites demand reliable and
complete EMI/EMC assessment during the full development cycle, in particular
before final integration and verification at system level.
Also worst-case testing at unit level does not always provide the right answer and
there is need for verification under the most realistic operational conditions.
New testing methods as well as advanced modelling tools to support full-life cycle
EMI/EMC assessment are necessary to cover these needs with the objective of
minimizing the cost and duration of test campaigns at satellite level while ensuring
design optimization.
The activity shall consolidate the results obtained in the TRP precursor activity
and result in the implementation of new methodologies for EMC testing under
realistic conditions enabling the application of best practices across the full
development cycle. The development will start with the definition of generic EMC
models suitable for the purpose, then advanced instrumentation and test beds will
be studied and implemented in a reference facility, also including validated
simulation tools with adequate features. The resulting methodology will finally be
demonstrated on selected realistic configurations.
Deliverables: Validated methodology implementation and reference facility, including modelling
tools
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
Advanced AIT Methods/2012
Ref. Number: G517-017EC Budget: 700 K€
Activity Title: Reaction Wheel Drive Electronics Improvements
Description: Provide a mass and cost reduction with simultaneous improvement of
performance of the existing reaction wheels in 15 to 40Nms range.Reaction wheel
drive electronics are still relatively massive and frequently based on old designs.
There is room to improve these with the introduction of full digital control, digital
interfaces which can significantly reduce parts count, improve reliability,
performance (i.e. the addition of a wheel speed loop) and mass (via
re-packaging).
Deliverables: - updated and tested WDE
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Q2 2011
Timeframe:
This activity is a direct continuation of the work developed by Bradford
Engineering in the GSTP activity G603-47EC, "Reaction wheel product
transfer support", funded with 1.6 M€ by GSTP-4. It is recommended to
Justification for DN: continue the development with the same contractor.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

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Annex 2, Page 84
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-018EC Budget: 350 K€
Activity Title: Low cost, portable sensor GSE
Description: Design and production of a new set of STR GSE that is low cost and easily
portable for the purposes of AOCS open/closed loop testing.STR GSE is typically
expensive and unweildy. Within this activity, a STR supplier shall develop, in
co-operation with Primes, a specification for a new STR GSE (EGSE and OGSE)
and shall develop a compact, low cost and user friendly set of GSE to meet these
requirements. This new GSE shall be manufactured and tested and then offered
with future STRs. This contract shall aim to match the recent advances in sensor
developments with similarly significant advances in the EGSE and OGSE for
those sensors. Miniature APS based units shall be targeted. The goal is to
develop a fully functional EGSE / OGSE that is easily portable, has very low
recurring cost and can be used both in stand alone mode and to facilitate closed
loop, robustness and sign testing of the units.
Deliverables: - Full set of STR GSE
Current TRL: TRL3 Target TRL: TRL6 Duration: 12 Months
Application /
Timeframe:
Q1 2010
Ref. Number: G517-019SW Budget: 500 K€
Activity Title: Industrialisation of the HW-SW Codesign toolset.
Description: Industrialisation of the HW-SW Codesign toolset developed in the context of the
TRP activityAs a result of the TRP activity on HW-SW codesign, a prototype of a
new toolset integrated in the ASSERT environment has been produced. This
toolset complements the ASSERT process to handle the HW-SW partitioning,
co-simulation and co-generation. This activity will have to improve the maturity of
this toolset up to the level of a tool usable on an operational project. The maturity
level will have to be confirmed with a full implementation of a significant case
study.
Deliverables: The ASSERT Development environment completed with a mature support to
HW-SW co-design.
- A complete set of guidelines and user guides to use the new environment
- A case study entirely developed with the new toolset,
- Lessons learned from the experience and proposals for extensions or
recommendations for use on operational projects,
- A commercialisation plan and spin-off opportunities
Current SW
Readiness Level: Prototype
Target SW
Readiness
Level:
Release Duration: 24 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 85
Ref. Number: G517-020ED Budget: 300 K€
Activity Title: SpW RTC Software Library and Tools
Description: Development on a set of software libraries and software development tools for the
SpaceWire Remote Terminal Controller (SpW RTC)ESA has developed a system
on chip called SpaceWire Remote Terminal Controller (SpW-RTC). The
SpW-RTC device includes an embedded Leon2 FT microprocessor with FPU, two
SpaceWire links, two CAN bus interfaces, ADC/DAC interfaces for analogue
acquisition/conversion, standard interfaces and resources (UARTs, timers,
general purpose input output). This device has a quite wide range of potential
uses in the field of spacecraft instrument control and payload data processing. In
order to further facilitate the application of this ASIC in flight programs a set of
software libraries and tools needs to be developed beyond the tools that are
existing today.
Deliverables: A validated set of software libraries and software development tools for the
SpaceWire Remote Terminal
Current SW
Readiness Level: prototype
Target SW
Readiness
Level:
full operational Duration: 18 Months
Ref. Number: G517-021ED Budget: 500 K€
Activity Title: TOPNET 2nd Generation
Description: Development of SW and HW for the implementation of the Second Generation of
the successful TOPNET concept.The TOPNET Pilot Implementation Activity
proved the usefulness of the TOPNET concept. Many improvements were
suggested by ESA and/or industry during the previous activity. Objective of this
proposal is first of all to implement all the new features, in order to make the tools
more close to an industrial product. A further objective is to extend the TOPNET
concept, having in mind the SOIS architecture, to introduce further Data Link
Layers besides SpaceWire.
Deliverables: IP Tunnel SW, IP Tunnel HW (SpaceWire and other Data Link Layers)
Current SW
Readiness Level:
Justification for DN:
Beta version
Target SW
Readiness
Level:
Full operational Duration: 18 Months
This activity is a direct continuation of the work developed by University
Dundee (UK) in a previous activity "TOPNET: Protocol Definition" funded with
500 K€ by TRP and 250 K€ by GSTP-3.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-022EP Budget: 200 K€
Activity Title: Constant Power charging of Li ion batteries for LEO missions
Description: The objective of this activity is to evaluate the impacts of constant power charging
on the cycle life of Li ion batteries for LEO applicationsIn LEO applications, high
power is available when getting out of eclipse. This available power could be used
to charge the battery at constant power, implying to charge the battery with a
higher current at the beginning of the charge. But the usual charge profile of Li ion
batteries is constant current-constant voltage. So the impacts of constant power
charging on the cycle life of the Li ion battery have to be evaluated by testing and
modeling to show if the Li ion battery can meet LEO mission requirements with
such charging conditions.
In a first phase, the charge profiles will be defined for different LEO missions
based on the outputs of the previous ESA activity "Study of new power systems
architecture for LEO missions" and the test plan will be described. In a second
phase, a life test will be initiated with constant power charge and in parallel a
reference test with usual charge profile (constant current-constant voltage) will be
started. In a third phase, the test results will be compared and by modeling the
influence of the charge process will also be assessed.
Deliverables: Technical Notes, Test plan, Test reports, Final report
Current TRL: TRL5 Target TRL: TRL6 Duration: 24 Months
Application /
Timeframe:
LEO missions (Earth observation)
Ref. Number: G517-023QM Budget: 300 K€
Activity Title: ADHESIVE TAPE FOR HIGH POWER LASER INSTRUMENTS
Description: To validate an adhesive tape which is compatible with the laser induced
contamination requirements for high power laser instruments operating in
vacuumHigh power laser instruments operating in vacuum place stringent
requirements on the use of adhesive materials in close vicinity to the optical
components. The interaction of the laser beam with the outgassing products from
the material can cause deposition of organic layers on the optic, and resulting
performance degradation, even if the material conforms to standard outgassing
requirements for space use. Adhesive tapes often need to be applied during AIT
activities, for example to install sensors during environmental testing, or to prevent
parts of the electrical harness from crossing the optical path. The risk is enhanced
if the tape is added at a late stage of integration, and it is not possible to
implement additional contamination control measures on the hardware e.g.
bake-out. Moreover, if the tape can be pre-conditioned, it is difficult to store and
supply tape using standard methods e.g. on a roll. To limit the risk of laser
induced contamination, an appropriate adhesive tape selection needs to be made,
processing/conditioning parameters need to be investigated and a storage /
supply method for the conditioned tape needs to be implemented.
Deliverables: Material survey according to current knowledge of laser induced contamination
effects Investigation of risk reducing processing parameters (e.g. bake-out,
conditioning), Laser induced contamination testing, Mechanical testing (adhesive
strength). Development of storage and supply methods
Current TRL: TRL4 Target TRL: TRL6 Duration: 24 Months
Application /
Timeframe:
TRL6 by 2010/11 (for Earthcare)

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 87
Ref. Number: G517-024QM Budget: 300 K€
Activity Title: Joining of composites materials
Description: The aim of the proposed activity is to review and characterise different joining
techniques for composite materials such that size constraints of e.g. autoclaves
are circumvented. Examples of possibly successful routes are welding of
thermoplastic composite materials or electron beam welding of thermosets. The
integrity of the joined materials shall be assessed by sample testing. Composite
materials are attractive for launchers due to their excellent stiffness to weight ratio.
One drawback though is that most composite materials are manufactured in
autoclaves which naturally limits the size achievable of the resulting launcher
component.
Deliverables: Part 1: Assessment of materials joining techniques
Part 2: Characterisation of joining efficacy by sample testing and feedback to
processing conditions
Part 3: Synthesis of work performed
Current TRL: TRL3 Target TRL: TRL5 Duration: 30 Months
Application /
Timeframe:
TRL 6 (?) by 2013
Ref. Number: G517-025QM Budget: 200 K€
Activity Title: Crimping of thermally stable structures with Shape memory rings
Description: To use shape memory alloy rings to produce crimp joints between Invar and
silicon carbide.Invar and silicon carbide have a matched CTE making them
compatible for cryogenic applications. The joints between the materials are
complicated because the CTE of fastener systems are not compatible which
means that complicated joints must be designed to allow for the mismatch.
Crimping the Invar would make this joint much easier to fabricate. A shape
memory alloy ring would allow the joint to be made and unmade by the application
of heat.
Deliverables: Breadboard for cryogenic testing
Current TRL: TRL1 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
All cryogenic misiosn using large thermally stable structures eg SPICA / 2010

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-026QM Budget: 250 K€
Activity Title: Light weight steel structures
Description: Production of steel structures with lower weight than existing designsAluminium
structures are usually made up of individually components machined from larger
billets. The size of the original billets means that the heat treatment is not optimal
throughout the structure. Steel allows structures to be deep drawn and
hydro-formed which can produce structures with very thin walls where only
stiffness is required and thicker walls at joints. These technologies have been very
well demonstrated in the packaging industry for drinks cans and by the sports
industries for high performance bicycles. The specific stiffness of steels is slightly
better than aluminium and titanium and there is a significantly wider variety of
alloys available. An appropriate alloy should be selected and used to produce a
thin walled breadboard using deep drawing and hydro-forming technologies.
Deliverables: Breadboard available for vibration testing
Current TRL: TRL2 Target TRL: TRL6 Duration: 24 Months
Ref. Number: G517-027QM Budget: 200 K€
Activity Title: Development of electroless Silver platting on Ni/Cu coated substrates.
Description: To develop a stable electroless silver deposition process on a defined and well
mastered under-layer. To address the compatibility of this deposited silver with the
base materials used in non-structural applicationsDevelop stable electroless silver
coating bath and establish a processing window for obtaining thick deposits of
several micrometers on top of electroless Ni and/or Cu. To test the coating
behaviour when it is deposited on classical substrate such as aluminium.
Deliverables: Process window, test samples, test reports, test data.
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
All missions for e.g. waveguides and antennae.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 89
Ref. Number: G517-028QM Budget: 400 K€
Activity Title: Processing of Al-Mg-Sc high strength alloys.
Description: To evaluate the possibility of using new high strength aluminium alloys in space
application and address the benefit of advance processing techniques applied to
this new alloy.Phase 1: Characterisation of alloys based on the Al-Mg-Sc system
with respect to space applications and assessment of welded joints. Phase 2:
application of advanced processing of the Al-Mg-Sc alloys;
single-point-incremental-forming and multi-points forming techniques.
Rationale: Machining out from a bulk block of metal leads to distortion of the
hardware during the machining. Having processes allowing making complex parts
without spring-back effects and other distortion would be of benefit and allow more
freedom in making small series production. Therefore process limits for the new
processes applied to advanced alloys has to be established
Deliverables: Test samples, test reports, material data and breadboard, process limits for the
new processes applied to advanced alloy.
Current TRL: TRL2 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
All satellites.
Ref. Number: G517-029QM Budget: 250 K€
Activity Title: Development and characterisation of Titanium alloy hollow-spheres.
Description: To transfer the technology of pure Ti hollow-spheres to stronger alloy Ti6Al4V. To
characterise the mechanical behaviour and the physical properties of the
developed hollow-spheres. To assess the manufacturing limits of these
hollow-spheres (e.g. bonding, scaling-up, coating, machining).The pure Ti
hollow-sphere manufacturing process has been developed in previous ESA
activities. One conclusion has been that the obtained material is the best energy
shock absorption existing. Another conclusion has been that tremendous
improvement (200%) could be achieved by using Ti alloy instead of pure Ti.
Beside, such material could be used is many applications.
Deliverables: Test samples, test reports, test data and processing window.
Current TRL: TRL1 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
mars sample return, Marco-polo, hard-landing missions

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-030QM Budget: 250 K€
Activity Title: Development and characterisation of advanced metal matrix composites.
Description: To develop advanced metal matrix composite that comply with the general space
requirements. To assess the manufacturing limits of the selected materials. (e.g.
bonding, scaling-up, coating, machining).Selection of advanced metal matrix
composite systems. Development and of these composite systems, assessment
of the processing possibilities – mechanical, physical and corrosion resistance
characterisation of the developed materials.
Rationale: Structural metals (Ti, Steel, Al) are roughly all equivalents in terms of
specific stiffness. Metal matrix allows a further increase of the stiffness metal
based materials with increase in performance of several tens%.
Deliverables: Test samples, test reports, test data and processing window.
Current TRL: TRL3 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
All projects.
Ref. Number: G517-031QM Budget: 200 K€
Activity Title: Validation testing of Glare 1 to space qualification levels
Description: The objective is to demonstrate the mechanical and physical properties of Glare 1
coupons under thermal cycling and constant high and low temperatures. Also
humidity testing and outgassing tests are part of the programme.Six different
types of Glare are produced. Glare 1 consists of AA7475-T761 with glass fibre
reinforced FM906 epoxy (High strength Glare), and the AA2024-T3 with glass
fibre reinforced FM94 epoxy (Glare 2 to Glare 6).
The most used Glare type with the AA2024-T73 with the FM94 epoxy system is
cured at 120C and has as a consequence a maximum temperature usage with is
well below the standard space qualification temperatures.
The Glare 1 epoxy system cures at 180C and shows promises for the required
test temperatures. The data on Glare 1 in for space required temperature domain
is very limited.
Deliverables: Test data to show the capability of Glare 1 at temperatures between -150 and
+150 C
Current TRL: TRL4 Target TRL: TRL5 Duration: 12 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 91
Ref. Number: G517-032QC Budget: 400 K€
Activity Title: Polymer Tantalum capacitor (very low ESR)
Description: This program of work is planned in order to develop a very low ESR and high
voltage (50V) tantalum capacitor in Europe for space application.
The polymer solid tantalum capacitors use a new technology replacing the MnO2
material for the cathode by a doped polymer with a higher electric conductance in
order to reduce the equivalent series resistor and then enhance the electrical
characteristics versus frequency. In the future this new technology could replace
the type II ceramic capacitors used for power output filtering for example in the
output filtering stage of the DC-DC converters, and especially when the
multi-anode configuration is used.This Technology is actually only use for
commercial terrestrial application (and therefore reliability data is limited) and
limited to low rated voltage (16V max). It should be more surge robust and not
subject to the ignition failure mode by the use of polymer in place of MnO2 for the
cathode.
This activity can be shared in 3 parts:
1/ an evaluation of the current capability of the selected manufacturer should be
performed. It will show the potential weakness of the product and will determine
the main improvement path for obtaining high voltage reliable capacitors suitable
for space application
2/ Based on the previous results this part of the activity will consist of the selection
of technological developments that will allow increasing the rated voltage of the
capacitor. Samples will then be manufactured with the new technology/process.
3/ a new evaluation of the obtained final components will be performed to assess
the improvement and confirm the new rated voltage.
Deliverables: evaluation of the current polymer tantalum capacitor, high voltage polymer
capacitor samples
Current TRL: TRL3 Target TRL: TRL4 Duration: 36 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-033QC Budget: 350 K€
Activity Title: Definition of displacement damage test guidelines for bipolar devices
Description: To date there is no ESA test guideline/procedure for displacement damage. An
overall programme has been initiated to generate an ESCC displacement damage
test guideline to fill this gap. As part of this programme funding has been secured
to establish displacement damage test guidelines for 2D imaging devices and
detectors and an activity is ongoing to establish displacement damage test
guideline for optocouplers. The objective of this activity is to produce a
displacement damage test guidelines for bipolar based devices for inclusion in the
general ESCC displacement damage test guidelineDisplacement damage test and
design guidelines for bipolar devices shall be established. Additional irradiation
test campaigns may by initiated to cover the following issues:
- lot to lot variation
- effect of annealing
- effect of bias
- sensitivity to displacement damage of BiCMOS devices
In addition Proton testing and combined neutron + TID tests shall be performed on
selected candidates to establish the best way to get a realistic worst case value of
combined TID and displacement damage degradation following ground based
testing
Deliverables: WP1: Management. WP2: Study report WP3: Irradiation Test plan. WP4:
Irradiation Test Report WP5: Data analysis report, test guideline and design
guideline documents
Current TRL: TRL4 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
The database and guidelines need date is mid-2010

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 93
Ref. Number: G517-034QC Budget: 300 K€
Evaluation of worst case condition for the Single Event Effect test of power
Activity Title:
MOSFET
Description: SEE tests employing highly penetrating heavy-ion of radiation hardened power
MOSFET have shown increased destructive SEE sensitivity with increasing heavy
ion range.
These results have cast doubt on manufacturer test data currently in use by the
European space industry (major ESA projects have been affected by this issue).
However, minimum ion range requirements have not been clearly established.
Therefore, there is a risk to unnecessarily over-specify test requirements. The
objective of this study is to define realistic minimum ion range requirements and
inject the results in an updated ESCC25100 "SEE Test Method and Guidelines".
The objective of this activity is to define a realistic (compared to actual space
environment) worst case test condition for the Single event Effects (SEE) test of
power MOSFETsSeveral hardened and non hardened power MOSFETs covering
the voltage range from 100 to 500V will be selected and procured. Parts will be
tested at different test facilities with different ion species and ion range
(penetration depth). Based on test results, minimum ion range will be established
for each voltage range (100V, 200V, 400V, and 500V). The resulting data is
subsequently analysed and formatted suitable for inclusion in the ESCC25100.
Deliverables: Final report including data analysis, establishment of minimum ion range
requirements and a suitable chapter on the subject for inclusion in ESCC25100
Current TRL: TRL4 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
mid-2010

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-035SW Budget: 450 K€
Activity Title: Java on-board software implementation, case study
Description: Assess the efficiency and suitability of using JAVA as the next generation
on-board real-time software programming language by implementing a
representative test case.In previous ESA contracts Real-Time JAVA VM’s have
been developed for the ERC32/LEON microprocessors. In order to demonstrate
the suitability and maturity of the RT-JAVA technology for space application a
representative on-board software application shall be implemented. As testcase
shall a spacecraft central software data management function be selected. It shall
include the most commonly used PUS services compatible to the ECSS-E-41A. It
shall replace the current data management software of the Eagle-Eye virtual
spacecraft implemented in the D/TEC Avionics LAB on the ATB-SVF. It shall
further be integrated with the autocoded AOCS software such that it together
forms a new implementation of the Eagle Eye Virtual Spacecraft on-board
software.
The implementation shall be assessed on production productivity overall suitability
as the future real time programming language for spacecraft applications.
The Avionics end-to-end Testbench is a D/TEC Avionics System facility providing
a simulator implementation of a fictitious low earth orbit satellite ‘Eagle Eye’, which
includes the platform on-board software for Data Management and AOCS and the
avionics and environment simulation models. The E2E-AST lab facility is meant
for technology validation and demonstration.
Deliverables: full Java Data Management System on-board software, integrated with the AOCS
software and integrated on the D/TEC Avionics system laboratory (Avionics
End-ro-end Testbench).
- Design documentation of the JAVA software and its integration on the ATB-SVF
- Product technology assessment reports.
Current SW
Readiness Level: algorithm
Target SW
Readiness
Level:
Prototype. Duration: 18 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 95
Ref. Number: G517-036SW Budget: 350 K€
Activity Title: Establishment of model reference library
Description: Develop a database and initial population of space system simulation
modelsBased on the portability standard and a reference architecture the
structure of a library shall be defined and implemented to host reference
simulation models for the use and exchange between all stakeholders in the
space domain.
The structure of the database shall be based on the reference architecture
developed under other ESA activites. A concept needs to be defined and
implemented which allows the central management and maintenance of the
library, ensuring proper access control and compliance with the corresponding
standards (such as the simulation model portability standard).
An initial population of this library shall be developed, and support for "open"
models as well as models with IPR issues has to be demonstrated.
Deliverables: Model library with reference models
Current SW
Readiness Level: Prototype
Target SW
Readiness
Level:
Beta version Duration: 18 Months
Ref. Number: G517-037SW Budget: 2,000 K€
Activity Title: Adaptation and Demonstration of MBSE for a real project
Description: Quantify benefits of MBSE-based methods for space projects by performing
phase B activities as shadow engineering in parallel with a selected missionBased
on the results of previous, ongoing and planned activities to define a model-based
systems engineering (MBSE) based approach for space systems and to develop
the necessary support tools and interface standards, its benefits need to be
quantified through the application in a real project.
In order to have the most realistic quantification of the benefits of the methods
used, it is necessary to apply the methods and tools in a real project. To allow a
benchmarking exercise it will be necessary to perform shadow engineering in
parallel to a selected project, with a (partially) separate engineering team and
access to the same data and requirements. This covers mainly the activities
performed in phase B.
To minimize any impact on a project schedule and programmatics, this activity
needs to be run independently from a programmatic point of view. However,
agreements need to be made on technical level to guarantee the transparency of
data and processes between the two engineering teams.
Programmes to be considered as potential cases include missions in the IAP
(Integrated Applications Programme), Sentinel 4 and 5 (precursor), exploration,
Cosmic vision of the Space Situation Awareness (SSA) initiative.
All relevant system databases, models and simulations shall be developed to
support the design process and allow the full design verification of the selected
mission.
Deliverables: Verified system design for the selected mission, comparable with the baseline
phase B process
Current SW
Readiness Level:
Target SW
Readiness
Level:
Duration: 24 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-038SW Budget: 400 K€
Activity Title: System Architecture modelling tool
Description: Develop a system architecture modelling environment on the VSD model and
processThe ongoing activity on Virtual Spacecraft Design prototypes tools to
support the model-base systems engineering process (MBSE). These tools
provide the interface on system level to define, analyse and modify the
architecture of space systems, interfacing to engineering disciplines through
mechanisms using a central engineering database.
Based on the tools and interfaces demonstrated, there is the need to reinforce the
interface layer towards the system and project engineers of a project. These tools
shall allow a system engineer to directly access the relevant functionality of the
environment supporting the MBSE development process. This tool shall be based
on graphical representations and views meaningful to the system engineer and
not rely on SW-centric notions (such as UML, SysML), but translate the MBSE
internal representation into system engineering concepts consistent with the
underlying metamodels and concepts. The tool shall hide the complexity of the
overall system design reflected in the database and synthesise the design to a
level adequate for architectural analysis and system engineering integration and
control tasks.
A specific emphasis shall be put in support to process definition and monitoring
within this tool suite. The resulting tool will be integrated in the overall engineering
environment for the MBSE.
Deliverables: Modelling tools
Consolidated Interface definitions
Current SW
Readiness Level: Prototype
Target SW
Readiness
Level:
Beta Duration: 18 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 97
Ref. Number: G517-039SW Budget: 750 K€
Activity Title: System of Systems design environment
Description: Consolidate and tailor a System of System (SoS) Design environment for an
Agency projectOngoing activities prepare the methods and tools required for the
analysis and design of System of Systems with space components. A prerequisite
of the operational use of these methods in the context of future SoS programmes
of the Agency (e.g. the IAP programme, GMES / GEOSS follow-on…) is the
provision of a stable environment and a repository of all known and relevant
assets of such a System of systems.
On the basis of developed prototypes it will be required on one hand to strengthen
the framework, and on the other hand to produce relevant models for the system.
The levels to be addressed include technical, programmatic and strategic,
focusing on the interface with external partners (on all these levels). An expert
team needs to be set up to support the design and analysis phases for the
programme managers and to maintain the repository, reflecting the inherent
changes of interfaces and external assets in these programmes.
Deliverables: Consolidated (operational) SoS analysis and design environment
Reference repository of relevant assets
Current SW
Readiness Level: alpha
Target SW
Readiness
Level:
release Duration: 24 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-040SW Budget: 500 K€
Activity Title: End-to-end performance simulation framework
Description: Develop a generic framework and integrate representative simulation models for
mission performance analysesTo justify and verify the correctness of the design of
space systems it has become common practice to go beyond so-called system
simulators, addressing the technical performance of the system, to mission
performance simulations, addressing the end users of a mission rather than the
engineering / implementation level. They also provide the necessary synthetic
mission product for the timely development of higher level products and / or
additional services.
These tools have often been ad hoc developments, integrating existing scientific
and engineering performance models. To be able to capitalize on past
developments and to ensure that future modelling efforts are reusable across
missions it is necessary to define a suitable architecture and interfaces for a large
class of future Agency missions. It has to be analysed to what extent different
instrumentation can be combined in a common architecture, considering the
inherently different logic of active vs. passive space instrumentation, and
instruments for which the performance is mainly driven by the available (static)
environment (data-driven simulations), and those requiring the dynamics of the
system.
After the definition of this architecture and its scope, a corresponding SW
framework will be implemented and an initial population with relevant existing
models will be done. A clear ICD will be produced as requirements document for
future model developments
Deliverables: Framework for end-to-end performance simulations
Reference models for space instrumentation
ICD for future model developments
Current SW
Readiness Level: Algorithm
Target SW
Readiness
Level:
Alpha release Duration: 24 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 99
Ref. Number: G517-041SY Budget: 600 K€
Development and validation of a generic System of Systems Concurrent
Activity Title:
Engineering Model
Description: Development of a tool for the definition and validation of a new System of
Systems (SoS) architecture based on existing and planned mission models for
use in the CDF-like environment. The tool will be based on the outputs of the GSP
activity “Modelling and simulation for system of systems” which will define the
prototype software reference models.Analyse and implement the
recommendations derived from the GSP activity on System of System and related
CDF test cases
- Establish the tool specifications enabling a generic approach and use of the
softwwre
- Evolve and develop the SoS custom models (output of the GSP activity
Modelling and simulation for system of systems) into a stable generic model
including dynamic validation capabilities for performances, operational and
reconfiguration aspects
- Demonstrate the generic SoS software tool for application in a concurrent
engineering environment CDF-like using test case(s).
Deliverables: Modelling tool + associated documentations
Current SW
Readiness Level: Algorithm
Target SW
Readiness
Level:
Beta Version Duration: 12 Months
Ref. Number: G517-043EP Budget: 400 K€
Activity Title:
Process optimization & pre-qualification activities for multi-junction cells on
thin germanium substrates
Description: The objective is to adapt solar cell manufacturing processes to the use of thinner
(nominally 80micron) germanium wafer substrates. Note that this technology is
needed for the next generation of 30% cell.Thin (80-100µm) Ge substrates have
been developed by Umicore in the frame of ESA contracts (eg. ‘Improved Manu.
Technology for Ge Substrates’). In order to benefit from this improvement, solar
cell manufacturers have to optimize their production processes to produce triple
junction solar cells using these lower weight Ge substrates with the same yield
and performance as currently achieved for cells on thicker (140 µm) germanium
substrates.
Deliverables:
Activities will involve process trials using a statistically significant number of
wafers (of the order of several hundred) in order to demonstrate that satisfactory
yields can be envisaged.
200 solar cells produced from Ge substrates with reduced thickness (approx. 80
microns)
Current TRL: TRL3 Target TRL: TRL5 Duration: 12 Months
Application /
Timeframe:
Telecom, terrestrial market/a.s.a.p.

ESA/IPC(2010)51
Annex 2, Page 100
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-044EC Budget: 200 K€
Activity Title: HAS Active Pixel Sensor detailed annealing behaviour investigation
Description: To determine via test all key factors affecting the annealing behaviour of this
APS.The evaluation programme has shown the high temperature annealing
behaviour of these devices in biased and un-biased conditions. However, there is
a strong interest from users to know the annealing behaviours, for both biased
and non-biased detectors, at lower temperatures. This activity shall take a number
of detectors and subject them to both TID and proton irradiation. The annealing
behaviour under different conditions (biased, unbiased) and at various
temperatures (10, 40, 70, 125 deg C) shall be examined and the effects vs anneal
time shall be monitored.
Deliverables: - Final Report
Current TRL: TRL7 Target TRL: TRL8 Duration: 9 Months
Application /
Q4 2009
Timeframe:
This activity is the continuation of the work done by the Cypress BV (B) under
a previous GSTP activity, G601-57EC, "Next Generation APS" (Contract
19384), funded with 1.1 M€ by GSTP-4.
Justification for DN:
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.
Ref. Number: G517-045EC Budget: 200 K€
Activity Title: Extension/Deployment of the European Mathematical NLP-solver
Description: The objectives of this activity are to adapt the ESA's Universal Non-Linear
Programming Solver (NLP) for optimization problems in other domains than
trajectory optimization. In a previous ESA activity, it is being developed a
Non-Linear Programming (NLP) mathematical solver based on Sequential
Quadratic Programming (SQP). The intended primary use was at the time of this
activity for trajectory optimization. This activity will realized the adaptation of this
solver to areas different than trajectory optimization, like for example: spacecraft
structures optimization, optimization of launcher stages, optimization of fabrication
of ASIC component, etc.The activity will define and develop the modifications of
the European NLP-solver to be used by ESA to optimise antennas, discrete
structures, aerodynamic profiles, lay-out of electronic components on a chip, and
to support electromagnetic field modelling.
Deliverables: Software algorithms and the corresponding API (application Program Interface) for
the upgraded solver. A set of technical notes describing the solver aplicability to
ESA''s optimization problems in all areas of interest. An interface (document and
software) with client software that require optimization engines.
Current TRL: TRL5 Target TRL: TRL7 Duration: 10 Months
Justification for DN:
This activity is a direct continuation of the work developed by ASTOS (D)
together with Skysoft (P), University Birmingham (UK), University Coimbra (P),
and Steinbeis (D) in a previous GSTP activity, G603-45EC "Non-Linear
Programming Solver for Space Trajectory Optimization", funded with 445 K€
by GSTP-4. It is recommended to continue the development with the same
team.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 101
Ref. Number: G517-046ED Budget: 800 K€
Activity Title: Highly Available COTS based computer, Step2 (Prototyping and validation)
Description: The objective of the activity is to manufacture and test in representative
environment the prototype of a COTS based highly available computer.The
activity is a direct continuation of a GSTP 4 activity "Highly available COTS based
computer step 1" that had been covering the trade-off and specifications up to
PDR level. This new activity shall consist in performing the detailed design and
manufacturing of the COTS based computer prototype (EQM) as specified in the
step 1 and including the testing (environment/radiation) to validate the
effectiveness of the fault avoidance/tolerance capabilities of the design with a
special emphasis on the system resilience to transient effects (SEU, SET,MEU).
Deliverables: Prototype (EQM) including the relevant test and development support system, test
application software and models, test and validation data with the identification of
any potential improvements to be implemented on the final product.
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
Justification for DN:
TRL 6 in 2011
This activity is a direct continuation of a previous GSTP activity, G302-03ESa
"COTS based space borne computer 2 - HiAv", with EADS Astrium (D),
funded with 400 K€ in GSTP4 (contract 21864). It is then recommended to
continue with the same contractor.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ESA/IPC(2010)51
Annex 2, Page 102
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-047ED Budget: 800 K€
Activity Title: High Performance COTS based computer step2 (Prototyping and validation)
Description: The objective of the activity is to manufacture and test in representative
environment the prototype of a COTS based high performance computerThe
activity is a direct continuation of a GSTP 4 activity "Highly Performance COTS
based computer step 1" that had been covering the trade-off and specifications up
to PDR level. The emphasis is put on the capability of the COTS to provide a high
processing load and in this case substantially above the current capabilities of
standard rad-tolerant microprocessor although tolerating limited interruption of
service for the purpose of fault recovery and as such targeting applications where
the high processing capability is privileged onto other aspects such a availability
or reliability (see harmonization 2003 and 2006 dossier for the introduction to the
category of systems based on RAMS considerations).
This new activity shall consist in performing the detailed design and manufacturing
of the COTS based computer prototype (EQM) as specified in the step 1 and
including the testing (environment/radiation) to validate the effectiveness of the
fault avoidance/tolerance capabilities of the design with a special emphasis on the
system resilience to transient effects (SEU, SET,MEU).
Deliverables: Prototype (EQM) including the relevant test and development support system, test
application software and models, test and validation data with the identification of
any potential improvements to be implemented on the final product.
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
TRL 6 in 2011
Timeframe:
This activity is a direct continuation of a previous GSTP activity, G302-03ESb
"COTS based space borne computer 2 - Payload", with EADS Astrium (F) and
Carlo Gavazzi (I), funded with 300 K€ by GSTP4 (contract 21862). It is then
Justification for DN: recommended to continue with the same industrial team.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 103
Ref. Number: G517-048ED Budget: 800 K€
Activity Title: High Reliability COTS based computer step2 (Prototyping and validation)
Description: The objective of the activity is to manufacture and test in representative
environment the prototype of a COTS based high reliability computer.The activity
is a direct continuation of a GSTP 4 activity "High Reliability COTS based
computer step 1" that had been covering the trade-off and specifications up to
PDR level. This new activity shall consist in performing the detailed design and
manufacturing of the COTS based computer prototype (EQM) as specified in the
step 1 and including the testing (environment/radiation) to validate the
effectiveness of the design.
Deliverables: Prototype (EQM) including the relevant test and development support system, test
application software and models, test and validation data with the identification of
any potential improvements to be implemented on the final product.
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
Justification for DN:
TRL 6 in 2011
This activity is a direct continuation of a previous GSTP activity, G603-37ES
"Computer for reliability oriented missions", with an industrial team led by
Thales Alenia (I), funded with 300 K€ by GSTP4 (contract 21863) . It is then
recommended to continue with the same industrial team.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.
Ref. Number: G517-049QM Budget: 750 K€
Activity Title: Upscaling of ultra-stable bonding process of ultra-stable materials
Description: To demonstrate the viability of the output of TRP activity ( Joining technology to
bond Carbon to Carbon) dealing with bonding of ultra-stable materials.The
adhesive material and the bonding process developed within TRP will be applied
on a breadboard having roughly dimensions of a square meter, i.e. compatible
with the requirements of future missions. The obtained breadboard will be tested
according to a test programme derived from the qualification programme of the
ultra-stable instrument support panels used in GOCE but taking the requirements
of future missions into account.
Deliverables: Test samples, test reports, test data and a breadboard of about 1 m2 that will be
used for performing tests.
Current TRL: TRL2 Target TRL: TRL6 Duration: 24 Months
Application /
Timeframe:
Justification for DN:
Eddington baseplate or equivalent exo-planet mission - Next generation missions
of GMES - High temperature missions as solar probe instruments( Bepi Colombo
or Solar Orbiter) - Interferometry base structures carrying several telescopes -
Darwin.
This activity is a direct continuation of a previous TRP activity, T608-30QM
"Joining technology to bond carbon to carbon in stable sandwich structures",
with an industrial team led by Thales Alenia (F) and including Politecnico
Torino (I). It is then recommended to continue with the same industrial team.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ESA/IPC(2010)51
Annex 2, Page 104
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-050QC Budget: 2,000 K€
Activity Title: Establishment of a commercial GaN epitaxial production facility in Europe
Description: ESA is currently benchmarking under the capabilities of European GaN epitaxial
suppliers. The majority of potential European suppliers are still at the research
institute level or are volume suppliers with track record in other material systems
and have not established their production facilities in Europe. A program of work is
required to assist in the funding of technology transfer from the R&D level towards
a true commercial production facility. Discussions are already ongoing with a
number of suppliers and options for joint funding schemes are being investigated.
ESA seed funding is needed to stimulate this transfer.Similar to SiC substrate
supply, an activity on this topic is absolutely essential to build an ITAR free
European industrial capability. The availability of the GaN epitaxial starting
material is a key building block that ultimately determines device performance and
reliability. This and the related item on SiC will provide the missing links to
establish a fully European ITAR free supply chain from substrates to materials
growth through to device processing. The epitaxy approach would also investigate
inclusion of CVD grown diamond layers close to the active device channel for
more effective heat removal. If successful this approach could revolutionise the
power performance achievable which is currently thermally limited.
Deliverables: Epitaxial wafers, Establishment of a non-dependant European production supply
chain for GaN epitaxy
Current TRL: TRL2 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
Generic applicability to all missions. Future EO programs (e.g. Sentinels,
COREH20), and future Telecommunication satellites and Science missions (e.g.
Solar Orbiter)
Ref. Number: G517-051QC Budget: 1,000 K€
Activity Title: GREAT - Validation of space compatible GaN foundry process
Description: Within GREAT (TRP and GSTP) it was originally planned to undertake an activity
to validate the performance of the GaN foundry process developed in Europe,
through design and demonstration of relevant component functions and to
stabilise/enhance the design rules issued by the European foundry. However, this
part of the program has had to be suspended since the full financial envelope was
not made available by the German and Belgium delegations. A follow-on Phase 3
program of work is needed to independently validate the stability of the processes
developed and to assess their performance for space use. If successful this
activity shall also provide and include a preliminary space evaluation of the
foundry processes developed for future listing in the EPPL. Unless this activity is
undertaken it will not be possible to fully assess the suitability of the processes
developed on GREAT for space application.Foundry access will be given to
independent teams outside of the GREAT consortium to evaluate the design
rules, process stability and performance achievable. Demonstration designs will
be fabricated, as per the original SOW in GREAT and tested to ensure suitability
for use in space.
Deliverables: Hardware (prototypes, test samples), experimental test results, reliability data,
fully documented foundry design guide and libraries, preliminary space
evaluation/qualification test plan, preliminary de-rating guidelines.
Current TRL: TRL2 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
Generic applicability to all missions. Future EO programs (e.g. COREH20), and
future Telecommunication satellites and Science missions (e.g. Solar Orbiter)

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 105
Ref. Number: G517-052QC Budget: 2,000 K€
Activity Title: Improved quality large diameter SiC substrates
Description: This activity is planned in order to improve the quality and size of SiC substrates
fabricated in Europe. High quality SiC semi-insulating substrates are required to
allow fabrication of GaN components and SiC diodes for RF payloads, high
voltage dc-dc converter sub-systems and for developing electronic components
that are capable of operating in harsh environments (temperature, radiation etc ..).
Activity on this topic is absolutely essential to build an ITAR free European
industrial production capability. High substrate quality is important as it strongly
affects device reliability. Moving to larger wafer size, 10cm diameter and above,
is essential to achieve commercially competitive prices for SiC and GaN based
components. A high reliability basic process technology for GaN components is
being performed under other ESA activity. However, the substrate material for this
development is procured from a single US supplier for which the risk of becoming
ITAR product is now almost a reality. In order to achieve the ultimate objective of
an independent European supply chain it is mandatory to develop a space
qualified source of SiC substrates in Europe. This is also relevant for other SiC
technology applications and can have further stimulating effects.The primary focus
shall be to minimise wafer bow, reduce micropipe density and eliminate impurities
that are known to adversely affect reliability. Targeted outputs from this work shall
be judged through (i) successful use of European SiC substrates on GREAT and
(ii) Establishment of a production supply chain in Europe.
Deliverables: SiC substrates with 10cm (or greater) diameter for processing in GREAT
(TRP/GSTP), establishment of a European production supply chain
Current TRL: TRL3 Target TRL: TRL5 Duration: 28 Months
Application /
Timeframe:
Generic applicability to all missions. Future EO programs (e.g. COREH20), and
future Telecommunication satellites and Science missions (e.g. Solar Orbiter)

ESA/IPC(2010)51
Annex 2, Page 106
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-053QC Budget: 300 K€
Characterization and reliability assessment of RF MEMS switches and
Activity Title:
switching matrix built on LTCC (Low Temperature Cofired Ceramic)
Description: The objective of this activity is to perform the functional characterisation and the
reliability assessment of RF MEMS switch matrix built on LTCC.A 2x2 RF MEMS
switch matrix built on LTCC from is candidate for a flight demonstration on
Alphasat.
Taking into account this context, in the frame of the proposed activity, the
following work will be performed on this device:
• The functional characterization (RF, switching speed, actuation voltage…).
• Definition of a Space evaluation test plan relevant to telecom satellite application
(lifetime, drift and ageing, vibration and shock, temperature, radiation,
EMC/ESD…).
• Fabrication of samples and performance of the evaluation testing.
• Upon acceptance of the evaluation test plan and depending on the evaluation
test results, ESA will consider listing the technology in the EPPL-Part-II (European
Preferred Part List).
Deliverables: Sample devices, Technical notes, final report and final presentation
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
Justification for DN:
Alphasat technology demonstration payload in 2011. Targeted applications:
compact reconfigurable receivers in telecom payloads and MEMS-based TDL
(Tapped Delay Line) for SAR (Synthetic Aperture Radars).
This activity is a direct continuation of a previous ARTES activity, "Very large
order switch matrices using MEMS technology", with an industrial team led by
Thales Alenia (I), funded with 720 K€ by ARTES-5. It is then recommended to
continue with the same industrial team.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 107
Ref. Number: G517-054QC Budget: 500 K€
Demonstration of the ESCC Assembly & Test House (ATH) Capability
Activity Title:
Approval approach for EEE components.
Description: This ESCC project aims to secure a long term increment in Europe’s capacity to
provide the space industry with a significantly extended range and variety of
available EEE components. The intention is to introduce a systemic qualification
methodology through the definition of a European ATH. The latter is usually
defined as a small or medium size company proposing a back-end packaging or
test service for wafers/dice manufactured by another entity.
The need stems from the strength of European semiconductor know how on the
one hand and the disjointed capacity dedicated to space high reliability
components production on the other. The outcome will be matched competences
that will be better prepared to meet the demands of future space projects.
The ESCC defines one quality level, therefore components provided through
ATHs will meet all the ESCC requirements and demonstrate an equivalent quality
to current ESCC qualified products together with long term availability at
competitive costs. It is not intended to duplicate existing ESCC products and this
approach could address, among others:
- Markets not already covered or outside the scope of possible ESCC
qualifications (e.g. manufacturers not interested by a Hirel, low volume production)
- Technology gaps strategic to European needs such as fast analogue/digital
converters and next generation microprocessors
- Diminishing or obsolete references only available under wafer/die form
- Semiconductor foundries proposing only wafer runs or intending to outsource
back-end activities.
- RF components (e.g. the 2 GaAs foundries listed in the EPPL do not have
packaging capabilities) Tasks to be completed will include:
- Develop requirements and criteria for the assessment and evaluation of
established standard semiconductor technologies for long term reliability including
specific constraints for space applications (e.g. radiation),
- Validate wafers/dice acceptance requirements and criteria for procurement,
- Validate and finalise the ESCC documentation establishing the space quality and
technical requirements for ATH activities,
- ESCC evaluation of a selected component or family of components.
Deliverables: Validated new and/or updated ESCC specifications for the management of future
ATH activities and ESCC Qualification of ATH products.
Completed ESCC evaluation of a component/component family manufactured by
an ATH and the related semiconductor technology.
Current TRL: N.A. Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
Most space missions.

ESA/IPC(2010)51
Annex 2, Page 108
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-055QC Budget: 300 K€
Activity Title: IESD effects on glob-top assemblies
Description: The objective is to define an analysis and experimental program in order to
quantify the Internal Electrostatic Discharge effects (IESD) susceptibility of a
Glob-top assembly.Dielectrics having a resistivity above 1012 Ohm?cm under
radiation can have a tendency to build-up electrostatic charges due to their
intrinsic low leakage rate. This charge accumulation could cause discharge when
the local electric field exceeds the dielectric strength of the material or, between
dissimilar surfaces, a critical potential. The discharge amplitude and duration is
function of the charge deposited. This problem falls in the domain of the so called
Internal Electrostatic Discharge (IESD) effects. It is also to be considered that the
resistivity has a tendency to increase with aging in orbit. So the potential threat
increases during the spacecraft mission. In the case of Glob-top assemblies we
have dielectric resin layer directly on the bare dies and wire bonds, which due to
the integration scale are becoming more and more ESD sensitive to lower voltage
levels. The contractor shall:
• Define a test plan to simulate the aging in orbit of the glob-top resin
• Measure resin resistivity and dielectric breakdown after accelerated ageing and
vacuum bake of the resin.
• Make an analysis for GEO orbits to determine the worst case electron flux
arriving at the Glop-top assembly. In addition other orbits regime can be
considered like MEO, PEO and planetary missions to Jupiter, Saturn and Mars(?).
• Prepare resin samples (including aging and vacuum baking) and the
experimental set-up to detect the discharge events and measure pulse amplitude
and duration under electron beam.
• Make electron beam tests on the resin with beam energy at: 100KeV, 500KeV,
1Mev, 2MeV and 3MeV. Electron beam fluxes shall be in the range from 0.1 to
1.0 pA/cm2. Flux vs. energy shall be derived by the above worst case electron
flux analysis.
• Implement margins on the collected experimental data to design a worst case
scenario electron beam test on actual glob-top assembly (i.e. worst environment,
least shielding). The testing shall foresee the DUT under maximum operative
rating conditions.
• If anomalous functioning is observed perform detailed investigation, and
simulation if deemed necessary, to confirm the cause was an IESD event.
• Identify all the prevention (if not possible mitigation) techniques to avoid (or to
lower to an acceptable level) the IESD risk.
Deliverables: Detailed Test Report and recommendations
Current TRL: TRL3 Target TRL: TRL5 Duration: 12 Months
Application /
Timeframe:
2009-2010

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 109
Ref. Number: G517-056SW Budget: 800 K€
Activity Title: Verification of operational concepts for human-robot interaction
Description: Define operational concepts and knowledge interchange requirements in a
heterogeneous environment, requiring close interaction between humans and
robots in a self-contained collaborative team. These concepts need to be tested
and consolidated in a simulated environment.In some of the scenarios for future
lunar/planetary exploration purely robotic missions are followed by crewed
missions. These missions will rely on the robotic infrastructure which has been
built up, but will require different interactions between this infrastructure and the
human, since the agents need to collaborate more closely together. In a
teleoperating context the robots are executing orders / achieving goals in an
autonomous way, they will have to interact with the human on a more
collaborative level in order to form a team and achieve the common goals. The
role for robots will shift from an exploration more towards a field support and
service function.
Traditional autonomy concepts need to be enhanced to allow knowledge sharing
on semantic level between the agents. Similar challenges are known from e.g. the
mining industry, the off-shore sector and nuclear industries (operations in complex
& hostile environments).
After an initial survey of operational concepts from other domains with similar
operational constraints as space (such as mining, underwater exploration, nuclear
installations), an analysis will performed of applicability of these concepts to the
domain of human spaceflight. This analysis needs to be based on an operational
scenario of a future mission, incorporating robotic and human agents in a
collaborative environment on a lunar/planetary surface.
Based on the results, an operational concept will be defined, based on the
knowledge exchange and task-sharing between the (human and non-human)
members of the team. An increased situational awareness needs to be achieved.
The necessary interfaces and interaction modi need to be defined, taking into
account the limited resources available for space missions. Goal oriented planning
support concepts as well as monitoring functions need to be integrated. The
operational concept must also include support for reactive planning.
In order to evaluate and consolidate the operational concepts, a simulation
environment needs to be defined to support the execution of a scenario. Using a
demonstration with (ideally) some robotic equipment in the loop the benefits and
limitations of collaborative approach shall be quantified and drivers for operational
developments shall be identified.
Deliverables: • Definition of Operational concept for human-robotic interaction
• Specification of the interface (knowledge, human-machine interface) between
human and robots in a collaborative environment
• Architectural design for demonstration testbed
• Detailed design of testbed
• Prototype of testbed
• Evaluation report
• Detailed design for operational layer for robots
Current SW
Readiness Level: Algorithm
Target SW
Readiness
Level:
Alpha Release Duration: 33 Months

ESA/IPC(2010)51
Annex 2, Page 110
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-057QC Budget: 250 K€
Reliability assessment of a MEMS-based isolation valve for propulsion
Activity Title:
systems
Description: During this activity, the contractor will perform the reliability assessment of a
MEMS isolation valve for satellite propulsion systems. The device shall
demonstrate zero-leakage, resistance to Space environment and a high reliability
on the long term.A small and light-weight MEMS isolation valve for satellite
propulsion systems has been developed previously in the GSTP activity
To enable the use of this component in Space application with an increased
confidence, reliability testing is proposed in this activity.
Task 1:
• PA/QA documentation of the device (Description, PID, existing test data, etc).
• Market study, including Space and terrestrial applications.
• Identification of potential end-users/partners and flight opportunities.
Task 2:
• Preparation of a test plan according to the requirements of a relevant mission
profil or else according to generic Space requirements (i.e. telecom mission).
• Manufacturing of engineering models
Task 3:
• Performance of the reliability testing on engineering models
• Analysis of the testing results to deduce potential weaknesses and limitations,
and necessary design or processing improvements.
The contractor will also deliver sample devices to ESA for the performance of a
construction analysis in ESTEC laboratory.
Deliverables: Technical notes for each task
Hardware samples
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 111
Ref. Number: G517-058QM Budget: 400 K€
Activity Title: Nano-hybrid transparent materials
Description: This study aims to find a replacement for silverised FEP, a well-known and widely
used flexible second surface mirror based on the transparent property of FEP.
The reason for that replacement is that space retrieved hardware from the Hubble
Space Telescope (HST) showed that this material badly degraded and has been
severely attacked after being seven years in orbit. The combination of organic and
inorganic materials leads to a class of so-called nano-hybrid materials. Such
hybrid materials offer properties that cannot be found in the individual material
alone because a wide variety of functional groups can be added that enable to
tailor individual material properties. Therefore, the aim of this study shall be the
development of a highly transparent material in combination with a high radiation
resistance (Proton, electron, UV, VUV, X-ray etc.) and good handling flexibility.
Deliverables: Part 1: Review of radiation resistant moieties and experimental manufacturing of
hybrid materials for screening investigation application
Part 2: Screening Investigation on radiation resistance and down selection of
hybrid material composites
Part 3: Materials testing in relevant space environment leading to a pre-qualified
status
Part 4: Market study and proposal for industrial scale up of production
Current TRL: TRL2 Target TRL: TRL4 Duration: 24 Months
Application /
Timeframe:
TRL 6 in 2013
Ref. Number: G517-059QM Budget: 300 K€
Activity Title: RTM processing of novel high temperature high radiation resistant resin
Description: The aim of the activity is to assess and optimise the processing of a newly
developed resin by RTM processing. This resin is deemed to have extremely
attractive properties in terms of temperature performance as well as radiation
resistance. Challenges are the high temperature required for processing and the
exact process window optimisation.The Materials Physics and Chemistry Section
is currently assessing a set a ultra high resistant materials based on novel
Polyimides. One of the resins under investigation is RTM processible which
implies that complex shapes could be manufactured. The material has a high spin
off potential for other high temperature industries.
Deliverables: Investigation and optimisation of processing window for RTM processing
Characterisation of thermal endurance and thermo-mechanical properties on
materials test samples
Synthesis report
Current TRL: TRL2 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
TRL 6 by 2012

ESA/IPC(2010)51
Annex 2, Page 112
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-060SW Budget: 300 K€
Activity Title: Data Modelling using ASN.1
Description: Based on the previous GSTP (System Software Co-Engineering: Data Modelling
Technologies), the goals are to (i) consolidate and extend data modelling
technologies and tools to an industrial level and (ii) make building blocks out of the
data models in a consistent way that is compliant with both the PUS standard and
System Databases formats.
The activity will consist in making an industrial tool-chain out of the ASN.1
technology that was prototyped and validated earlier by ESA and Prime space
industry, and to apply it on a realistic case study. Training material will also be
required so that any space company will be able to make use of the resulting
tools. The ASN.1 Environment will be free of charge and will ensure European
independence on data modelling key technology. The tool-chain will consist of (i)
a space pre-qualified ASN.1 compiler with compact binary encoders (based at
least on PER, ECN and/or PER EI standards), (ii) an automatic ICD generator, (3)
automatic code generators for functional modelling languages to automatically
make use of Data models and (4) an adaptive programming layer to help users
work with complex data models.
Deliverables: Industrially-useable Data Modelling Toolchain
- Use case: Data Models of the PUS standard
- Training material
Current TRL: TRL4 Target TRL: TRL6 Duration: 18 Months
Justification for DN:
The work in this activity is a direct continuation of the work initiated by the
industrial team composed by EADS Astrium (F) and Semantix Information
Technologies (GR) in a previous GSTP activity, G607-12EM,
"System-software co-engineering: Data modelling technologies," funded with
300 K€ by GSTP4 (ESA contract 20467). It is recommended to procure this
activity in direct negotiation with the same industrial team.
Non-competitive tendering is justified according to Article 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 113
Ref. Number: G517-061SW Budget: 350 K€
Activity Title: Dynamic Translation based on-board processor emulator
Description: The software emulation of the new generation of microprocessors used for Space
application does at best reach 30% of real-time when it is based on instruction
emulation. New and promising dynamic translation technology opens the scope
for achieving a factor 10 in performance.
Precursor studies have demonstrated the feasibility of using this technology also
for emulating real-time applications, where the focus is on an accurate I/O
performance model and on the need of being able to integrate the emulator into
an overall system simulator
The objective of this activity is to build and characterise a dynamic translation
based emulator for the LEON micro-processor that supports an I/O representative
emulation model.
Design and develop a generic LEON emulator using the dynamic translation
technology. Focus the emulation model to be real-time representative at the
I/O-level. Assess the performance of this architecture.
Assess the system representiveness and impact of this approach on the
verification functions and its suitability to support the software and system
verification and validation.
Demonstrate the capability in context by prototyping a representative test case
using the Avionics LAB ATB-SVF.
The ATB-SVF is a D/TEC Avionics LAB facility providing a simulator
implementation of a fictitious low earth orbit satellite, including platform on-board
software for Data Management and AOCS and the avionics and environment
simulation models. The ATB-SVF facility is meant for technology validation and
demonstration.
Deliverables: The deliverables are
- The beta version of the LEON dynamic translation emulator
- The emulator integrated with the ATB-SVF
- Performance characterisation based on test case executing on the ATB-SVF.
- Assessment of its suitability for use within Software and Validation Facilities and
potentially Operations simulators.
Current SW
Readiness Level:
Algorithm/
Prototype
Target SW
Readiness
Level:
Beta Version Duration: 12 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-062SW Budget: 350 K€
Activity Title: On-Board Computer Simulator architectures and I/F to system test benches
Description: Modern On-Board Computers (OBC) contains in addition to the processor a high
number intelligent peripherals in the form of ASIC’s, FPGA’s or integrated as a
System-on-chip solution. In order to create a representative simulation model of
the OBC it is necessary to integrate accurate functional models of these
peripherals together with the processor emulator. These peripheral functional
components may be proprietary provided by the hardware supplier or may be
developed specifically within the simulator context.
The OBC emulation / simulation models need to reflect this evolution and enable
the correct representation towards the rest of the avionics system.
The concept is undergoing technical feasibility assessment in the frame of the
Leon-SVF contract. The output of this contract shall be taken into account for the
consolidation of the architectural and interface specification foreseen in this
activity.
The objective of this activity is
• to consolidate the OBC simulator architecture, taking into account the ability to
integrate functional simulation components provided potentially by third parties in
a performance effective way;
• to consolidate the standardised interface to the functional simulation
components;
• to implement a representative prototype of the architecture, and characterise the
performance of the interface to a system test bench.
Develop the architecture for a complete OBC simulator, comprising the processor
and all its closely integrated interface functions. The activity shall take into
account the Functional Component Plug-in Protocol (FCPP) which has been
defined in the Leon-SVF contract.
Revise/consolidate relevant lower level model interfaces that allow performance
efficient integration of models and take into account that building blocks may be
delivered from the third party vendors.
Define the relevant interface to the system test bed, compliant to the standard for
simulation model portability (ECSS E40-07). Prototype the architecture and
characterise the performance of the OBC / system test-bed interface using the
D/TEC Avionics LAB on the ATB-SVF.
Assess the limitations of architecture for SW and system verification and
validation.
The ATB-SVF is a D/TEC Avionics LAB facility providing a simulator
implementation of a fictitious low earth orbit satellite ‘Eagle Eye’, which includes
the platform on-board software for Data Management and AOCS and the avionics
and environment simulation models. The ATB-SVF lab facility is meant for
technology validation and demonstration.
Deliverables: • The definition of the reference architecture for OBC simulator, including the
definition of the functional component interface protocol (FCPP)
• Interface definitions and characterisation OBC simulator within the system
testbed.
• the simulator prototype integrated on the D/TEC Avionics LAB ATB-SVF
• Assessment of usability and perormance for Software and system verification &
validation
Current SW
Readiness Level: Algorithm
Target SW
Readiness
Level:
Prototype Duration: 12 Months

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 115
Ref. Number: G517-063SW Budget: 750 K€
Activity Title: Automatic generation of database applications from a domain ontology
Description: This objective of this activity is to substantially improve the quality, availability and
efficiency of monitoring and control databases for use in AIT through the
application of state-of-the-art database engineering methods and tools.
It will demonstrate how, from a formally defined Ontology (the means to model a
domain of knowledge) of Monitoring and Control Data how database software
applications can be automatically produced”. Output will be a means to define
validated data models and DB applications that fulfil AIT needs for any mission
across the development life cycle, according to current and emerging standards
(ECSS, CCSDS, OMG).
ORM (Object Role Modelling) is a formal methodology and related tools that have
been successfully used by the Agency for formally specifying conceptual schema
of information systems related to AIT. In previous ESA activities, the ORM
methodology and a related tool is being extended to allow expressing ontologies
related to the Space System domain according to ECSS standards.
From a given ontology, the automatic generation of data models to be instantiated
within a data base management system, the automatic generation of software
application compliant to these models, including MMI, export/import facilities have
been demonstrated. The consolidation and development of the ontology tool and
the generator of database application software will be further developed and
consolidated by validating them using mission data.
Deliverables: A database development platform based on the ontology tool
An information system derived using the development platform and validated
against real mission data.
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Target SW
Readiness
Level:
All mission starting phase B from 2012
release Duration: 18 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-064TC Budget: 320 K€
Activity Title: Virtual Reality for AIV
Description: Improve the use of Virtual Reality in the Assembly, Integration and Verification
phase reducing cost and risk of Phase C/DDuring 2004-2007 a TRP activity called
"VRAIV Virtual Reality for AIV" has been performed. In this activity, it has been
developed a software tool which is open source and dedicated to the Virtualization
of AIV procedures. The documentation has been delivered to the ESTEC library
and is available to European Industry. This tool is now at prototype level and has
been used for some pilot projects (EXPERT re-entry test bed Payloads AIV, Large
Space Simulator upgrades of servomotors).
With this activity it is foreseen to add functionalities to the existing VRAIV tool,
among them: improve the automatic AIV procedure generation, allow for the
complete virtual generation of the AIV documentation of a project starting from a
database linked to the S/C Model database, improve the virtualization of AIV
procedure and the process of generation, modification, execution and reporting of
AIV procedures, improve the link with existing CAD tools.
The aim is to reach a full operation and validated tool which can be linked to the
Virtual Spacecraft Design (VSD) framework as a tool dedicated to the AIV phase.
Deliverables: Design and validation of VRAIV tool
Current TRL: TRL3 Target TRL: TRL9 Duration: 16 Months
Justification for DN:
TERMA (DK) has been the developer of VRAIV in a previous TRP contract
(number 18775).
Non-competitive tendering is justified according to Article 6.1. a) and c) of the
Contracts Regulations.
Ref. Number: G517-065MC Budget: 500 K€
Activity Title: Automated layup of Thermoplastic Composites for space applications
Description: Rapid, cost effective manufacturing out-of autoclave for large CFRP structures.
Manufacturing of thermoplastic composites using automated tape laying machine,
with integrated heating for melting and consolidation of the composite directly
during the layup, has a great potential to reduce manufacturing costs, schedule
and risk. Thermoplastic resins is a promising alternative both with respect to
performance as well as for practical reasons such as longer shelf life of raw
materials, less environmental impacts compared to conventional resin systems
etc. By using automated layup featuring integrated heating and consolidation
during layup, there is no need for autoclaves to consolidate the material and melt
the resin. The significantly increased shelf and workshop life of the material
contributes to reduce the risks during manufacturing. The proposed study is to
develop and manufacture and test a demonstrator corresponding to a major space
structure using this technique. The technology is existing but is not yet
implemented into space structures.
Deliverables: documentation, demonstrator structure
Current TRL: TRL3 Target TRL: TRL5 Duration: 24 Months
Application /
Timeframe:
launcher and spacecraft structures

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 117
Ref. Number: G517-066MC Budget: 150 K€
Activity Title: CAD Based Modelling for Space Thermal Analysis
Description: The graphical modelling environments that exist today for space thermal analysis
have grown from small applications designed to visualise geometry used for
calculation of radiative exchange factors and heat fluxes. As these niche tools
have matured the developers have tried to improve the modelling environment,
and to provide all the modelling functionality desired by users, whilst also
developing the core functionality of their tools; namely the radiative kernel.
Considering the limited resources of the developers, and the limited number of
users of the tools, this has proved to be a difficult task and, as such, the current
tools are often cumbersome to use and lack the interactivity and functionality of
dedicated modelling environments, such as:
o Computer Aided Design (CAD) modelling environments e.g. CATIA, Autodesk
Inventor
o Computer Aided Engineering (CAE) modelling environments e.g. SAMCEF
Field, MSC Patran
The basic premise of this proposal is that developers of niche software, such as
software for space thermal analysis, can concentrate on developing and improving
the core of their tools, specifically the radiative and thermal solvers, and provide
modelling capabilities in the form of plug-in applications for dedicated CAD/CAE
modelling environments.
This type of approach has several clear advantages:
o Only the core solvers of the tool, and the interface with the modelling
environment, need to be developed and maintained
o The solvers can be independent from the modelling environment and can be
embedded in different modelling tools by developing different interfaces
o All of the functionality of the CAD/CAE modeller is available to the thermal
engineer e.g. parametric and adaptive design, solid modelling, meshing
The objective of the proposed activity is to develop a prototype plug-in application
for a commercial CAD/CAE modelling tool. The plug-in shall permit the user to
carry out all aspects of the thermal analysis process from within the CAD/CAE
modelling environment. The actual solution of the thermal and radiative problems
shall be carried out by existing thermal solvers and the transfer of data between
the modelling environment and the solvers shall be completely seamless and
invisible to the user. The post-processing and visualisation of results should also
be possible from within the modelling environment.
A second key theme and objective of the proposed activity is the use of
component based modelling and smart components. Smart components are 3D
CAD parts that are available for the thermal engineer to drag-and-drop into their
model. These smart components not only describe the geometrical and mass
properties of the physical object, but also have a pre-defined thermal behaviour.
Thus the user can drag-and-drop smart components from a library or palette and
quickly build a fully parameterised thermal model. The use of such smart
components has clear benefits in terms of reducing modelling errors, increasing
productivity and allowing the engineer to focus on the design rather than the
modelling aspects.
In order to limit the scope of the activity, a pre-defined usage scenario is
envisaged which focuses on subsystem and instrument design.
Deliverables: (a) Prototype space thermal analysis S/W plug-in for a CAD/CAE tool
(b) Demonstration library of smart components for space thermal analysis

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Current TRL: TRL3 Target TRL: TRL6 Duration: 12 Months
Application /
Timeframe:
All space missions
Ref. Number: G517-067EE Budget: 500 K€
Activity Title: ESD transients monitor
Description: A monitor will be developed to measure the amplitude and characteristic
time-scales of electrostatic discharge (ESD) transients directly in spacecraft
electrical systems. The operation will be verified by realistic irradiation
experiments looking at both surface and internal charging. The result will be the
monitor equipment itself and the characterization of realistic ESD transients to be
used in defining requirements for ESD testing of future systems. The output of the
activity will be a protoflight model of the monitor that could be further developed to
become a standard device to measure ESD transients in operational satellites.
Deliverables: Protoflight model of ESD transient monitor. Results of laboratory experiments
using ESD transients monitor developed.
Current TRL: TRL1 Target TRL: TRL6 Duration: 24 Months
Application /
Timeframe:
All GEO and MEO missions, also Jupiter/Saturn missions
Ref. Number: G517-068MP Budget: 600 K€
Activity Title: Low cost PED propellant tank
Description: The SPF of Titanium alloys is a well proven technology for aeronautical
structures, and can guarantee a final lightweight product with a low cost
manufacturing technology. The PED technology applied to bi-propellant systems,
will enable flexible fulfilment of spacecraft and launcher upper stage missions
implying complex manoeuvres and attitude control tasks that are in general not
allowed or affected by operational constraints using the currently available
technology in Europe; surface tension Propellant Management Device (PMD). In
addition the PED technology is earmarked to provide appreciable cost advantages
over the mentioned currently available PMD solution. The objective of this
program is to increase the TRL of the described technologies to a maturity level
adequate to demonstrate the PED tank concept suitability with a prototype
demonstration in a relevant environment. Task1: definition of tank functional and
environmental target requirements. Task2: preliminary design of at least two
alternative tank concepts compatible with bladder or diaphragm PED solution.
Task3: development of a manufacturing process for diaphragm/bladder. Task4:
manufacturing of a suitable batch of diaphragm/bladders and development testing
in a mock up tank model. Task5: manufacturing of tank shells by SPF (super
plastic forming). Task6: development of tank system manufacturing process: parts
welding and integration. Task7: manufactured prototype acceptance including
representative functional and environmental testing. Task8: preparation of tank
manufacturing file
Deliverables: Documentation relevant to the identified tasks.
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
LV upper stage bi-propellant storable propulsion systems, Small-medium
Bi-propellant spacecraft, Space exploration missions, Orbit transfer vehicles.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 119
Ref. Number: G517-069MC Budget: 200 K€
Activity Title: Medium-Power Loop Heat Pipe
Description: The objective is to design, manufacture and test a medium power, medium size
Loop Heat Pipe at development level.
The activity shall consist in either scaling up the existing mini LHP or the
scaling-down of the high power and large size LHP, resulting in a medium size,
medium power LHP for an operating range of 30 to 200 W for e.g. instrument
thermal control. Such a medium size LHP shall then be designed, manufactured
and extensively tested.
Deliverables: Development model(s) of medium-power LHP; complete set of technical
documents incl. design, test and test evaluation documents
Current TRL: TRL3 Target TRL: TRL5 Duration: 18 Months
Application /
Timeframe:
EO, Science, Exploration, Telecom
Ref. Number: G517-070MC Budget: 250 K€
Activity Title: Multistable Composite Structures
Description: The objectis of this study is to explore the possibility of using asymmetric
composite laminates in spacraft applications. Typical applications of composite
materials in spacecraft are all based on a design having quasi-isotropic properties
keeping the mass as low as possible. This typically results in symmetrical layups
of CFRP laminates having zero curvature. Asymmetrical laminates with non-zero
curvature and showing multistable behaviour might have interesting applications
in deployable structures, thermal control systems (deflecting or focusing IR
radiation), latches, safety mechanisms, valves, etc. The advantage of these
laminates is that there is only the need to spend energy to transition from one
state to the other. Initial feasibility studies for use of multistable structures in
space applications. Phase 1: Identification of space application and respective
requirements, review of state of the art of multistable composites. Development of
accurate models to predict the multistable shapes, optimization, propose actuation
solution, manufacturing and test on sample level, demonstrator proposal (2-3
different concepts/applications). If the sample tests are promising, a Phase 2
should be initiated. Phase 2: Design, analysis and manufacturing of the
demonstrators. The envisaged demonstrator structure will be representative of the
applications. The demonstrator tests will include basic performance tests, as well
as functional tests, also under different thermal, moisture environments. Phase 2
will be concluded by the evaluation of test results and an update of possible space
applications.
Deliverables: 1. Materials samples, 2. Breadboard, 3. Demonstrator
Current TRL: TRL2 Target TRL: TRL3 Duration: 18 Months
Application /
Timeframe:
all spacecraft missions

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-071MC Budget: 350 K€
Activity Title: New Concepts for Advanced Structural Sandwich Panels
Description: New materials, mechanical configurations and processes developed within other
domains of engineering, allow for advanced concepts not yet implemented in
space applications. Foam cores enable either thermal isolation or in the opposite
case an improved thermal/electrical conductivity, depending on the parameters.
Chiral core types of honeycomb cores would offer the possibility to manufacture
large-curvature plates with negligible effect of the core, while offering other
capabilities, such as shape controllability. The consideration of transmission
losses and dielectric constants within the materials and configurations is
mandatory, e.g., in the transmission mode of antenna designs. In general, the
implementation of these and other new materials and structural concepts shall
result in a beneficial optimisation of sandwich structures for several applications.
The objectives of this activity are: 1. Study new materials and configurations for
honeycomb cores for different applications (ultrastable sandwich structures,
antenna reflector sandwich structure, composite material thermal radiators, solar
array substrates and RF transparent sandwiches), 2. Manufacture and test
breadboards for the applications, 3. Development of insert applications (e.g. use
of composite inserts developed in Europe, 4. Verification procedures, 5.
Demonstrator testing.
Deliverables: Study on new concepts, Samples and breadboards, Mathematical models,
Demonstrator testing.
Current TRL: TRL2 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
All spacecraft missions

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 121
Ref. Number: G517-075GS Budget: 750 K€
Activity Title: Ka-band klystron power amplifier prototype
Description: 1) Analyze and determine the way to implement the Ka-band uplink with special
focus on the phase stability and Allan deviation (ADEV) performance.
2) Develop a Ka-band transmitter compatible with the movable feed requirements
of the Ka Aberration subsystem starting from the Ka Band KPA (Klystron Power
Amplifier) developed by ASI (that does not consider the movable feed)The
contractor shall perform a trade off between the different architectures to
implement the Ka-band KPA (Klystron Power Amplifier) compatible with a
movable feed for compensating the Ka-band aberration. Architectures ranging
from fixed Ka up-converter plus KPA and flexible waveguide, to the feed to
moveable KPA plus up-converter connected with rigid waveguide to the feed (plus
intermediate and others envisaged by the contractor) shall be analysed and their
performances evaluated in terms of power handling, reliability, phase stability,
Allan deviation, etc.
breadboard developed for ASI, in order to meet the specific requirements of ESA
(specially concerning phase stability and feed movement). A prototype
representative of a production unit shall be manufactured and tested with the final
objective (if the rest of elements are available) of mounting the prototype in ESA
Cebreros station to validate on site the overall performances of the Ka transmit
subsystem.
The activities to be executed are:
* Trade off between the different architectures to implement the Ka-band KPA.
Special focus on performances on power handling, reliability, phase stability, Allan
deviation shall be considered.
* Design, manufacturing and test of a KPA prototype representative of an
operational production unit (HW plus design documentation, test results and user
documentation)
Deliverables: KPA prototype, Design and test documentation
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
Bepi-Colombo radio science experiment: TRL 8 by 2013, Future Cosmic Vision
missions with Ka-band uplink

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-076GS Budget: 300 K€
Activity Title: Improved Autotrack and search performance for ESTRACK Antennas
Description: Enhancement of the search approach leading to reduced search times at
X/Ka-band in the Deep Space environment. Development, implementation and
validation of additional features and functionalities for ESTRACK Antenna Control
Units. Improvement of the Autotrack performance for LEO spacecrafts at
X/Ka-band.The Antenna Control Units (ACU) in the 15m and 35m stations of ESA
ESTRACK network are key components ensuring the required pointing and
tracking performances. Starting from the current status of development it is
proposed to develop the ACU further in order to implement additional
functionalities and features with the aim to:
- improve the autotrack performance. The current autotrack controller concept is
not suitable for LEO spacecraft operated at Ka-band due to the large position
errors in case of high accelerations (high elevation passes). Pre-studies have
indicated a very promising way to improve the tracking accuracy for such cases
leading also to a benefit at S/X-band.
- improved search leading to shorter search time, which are in particular important
for X/Ka-band and in the Deep Space environment, where the antenna beam is
smaller.
- allow auto-tuning of the controller parameters
- improve the tracking performances by e.g. employing accelerometers at reflector
and subreflector level (already installed in ESA Deep Space antennas), as
additional feedback information in the tracking control loops in order to achieve a
better wind gust disturbance rejection
Deliverables: ACU with additional features and functionality integrated and tested in an
ESTRACK station
Current TRL: TRL5 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
ESTRACK stations/when available

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 123
Ref. Number: G517-077GS Budget: 500 K€
Activity Title: Holography System for Deep Space Antennas
Description: Extension, implementation and validation of holography system developed for
VIL-4 Ka-band antenna for ESTRACK Deep Space AntennasA holography
system, which measures the reflector accuracy of the VIL-4 Ka-band antenna, has
been developed already. The holography measurements are based on the
simultaneous reception of the downlink signal of a geostationary spacecraft with
the antenna under test (AUT, here deep space antenna) and the reference
antenna. From the measurement results (amplitude delta and phase delta
between both antennas), the surface accuracy of the antenna reflectors (AUT) can
be derived.
The available system should now be extended for its usage at the ESTRACK
deep space antennas. In particular the measurement approach has to be refined
and the signal acquisition unit has to be adapted to the downlink equipment used
within the deep space antennas. The reference antenna delivered in the frame of
the VIL-4 holography development will be used also for the deep space antenna
measurements.
The deep space antennas are equipped with movable sub-reflectors. The
extended holography system will be able to optimize the sub-reflector position with
respect to maximum G/T.
Deliverables:
As the CEB DSA is already mechanically prepared to host a holography system,
the validation shall take place at CEB.
Holography measurement system including hardware and software required carry
out reflector surface accuracy measurements.
Current TRL: TRL5 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
ESTRACK deep space stations/when available

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-078GS Budget: 300 K€
Activity Title: High Accuracy Reflector Panel
Description: Development of a new reflector panel design for DSA3 with improved
performances compared to DSA1 and DSA2ESA plans to establish a third Deep
Space Antenna similar in design to the already existing antennas in New Norcia
and Cebreros. With the experience gained from the New Norcia antenna, the
accuracy requirements for the reflector panels were tightened for the Cebreros
antenna in order to achieve the overall desired performances in the Ka-Band. Due
to schedule constraints, the approach chosen at that time was to keep design
changes to the minimum compared to the New Norcia panels. The only
modification in the design was the addition of insulation of the panel backside in
order to limit the thermal gradient across the panel thus limiting its deformation
due to thermal loads. Although this approach is working satisfactorily for
Cebreros, the following aspects could become critical for the next DSA.
- Reflector surface accuracy marginally fulfilled for Cebreros, for more severe
thermal environments this could no longer be the case.
- Due to the additional weight of the insulation, the improvements achieved in the
thermal behavior were partially compensated by a higher gravitational deformation
in Cebreros
- Long-term stability of the insulating material, cost in case of refurbishment
- The chosen approach is only reducing one contributor in the overall surface
accuracy budget, with a different approach like change of panel materials, change
of panel manufacturing technologies or change of the panel design more
contributors could eventually be reduced.
- Furthermore it is expected that with newer manufacturing technologies now
available, highly stable panels can be produced at reasonable cost.
It is thus proposed to develop a new reflector panel design aiming to improve the
performance of the next DSA reflector panels with the following scope of work:
Review and Consolidation of Draft specification already elaborated
Technology Survey and Panel Design Trade-off
Detailed Design of a DSA 3 Representative Reflector Panel
Manufacturing of Prototype
Prototype Validation
Deliverables: Prototype reflector panel
Current TRL: TRL5 Target TRL: TRL6 Duration: 12 Months
Application /
Timeframe:
ESTRACK stations/when available

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Annex 2, Page 125
Ref. Number: G517-079GS Budget: 300 K€
Activity Title:
Development of an RF test bed for high power testing of ground station feed
systems.
Description: Develop and validate an RF test bed for high power testing of ground station feed
systems.Feed systems composed by dichroic mirrors and radiating horns
operating up to 100 KW will be required in the next future for Deep Space
Missions application. It is presently not feasible testing the feed systems in
anechoic chambers (absorbing panels are not able to handle very high power).
Currently the testing is performed by radiating directly into the sky. In Europe is
not possible to perform direct radiation tests due to frequency and power
restrictions thus very often such a tests have to be performed outside Europe at
very high costs.
It is thus proposed to develop an RF test bed for high power testing of ground
station feed systems with the aim to develop a compact structure that can be
used/integrated into any European anechoic chamber. With such a test bed all the
RF high power transmitted by the feed system will be focused into water cooled
dummy load. Additional measured will be adopted to reduce the thermal noise into
the receive chain.
In order to achieve this overall objective the following activities are envisaged:
Requirements analysis
Design of RF test bed
Manufacturing of hardware
Assembly, integration and validation of test bed in X-Band (Deep Space Mission
band)
Deliverables: RF test bed for high power tests in X-Band usable in an anechoic chamber
Current TRL: TRL3 Target TRL: TRL6 Duration: 18 Months
Application /
Timeframe:
As soon as available, since some of the X-band RF components is already
available for testing

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-080GS Budget: 500 K€
Demonstration of simultaneous transmission and reception of data in
Activity Title:
Ka-Band
Description: Integrate beam waveguide mechanisms and RF elements developed under TRP
into one of our Deep Space Stations and validate them in an operational
environment. Future Deep Space Missions are expected to simultaneously
transmit and receive in Ka-Band.
At these frequencies antenna gains are higher than for the currently used S- or
X-Band thus the beam widths are very narrow, in the order of 20-30mdeg. These
small beam widths in combination with the long distances involved in Deep Space
Missions require to have a variable squint between the receive and transmit
beam.
This beam squint is necessary due to the relative movement of S/C and ground
station while the RF waves are propagating between both, similar to a hunter
targeting ahead when trying to hit a moving object.
In the frame of preceding TRP study two prototype mechanisms have been
developed and tested at breadboard level that allow to move BWG elements and
thus to realize the beam squint necessary for a simultaneous transmission and
reception in Ka-Band. Parallel to that also Ka-Band RF elements (dichroic mirrors,
feed) have been developed and tested component level.
The GSTP activity now proposed aims to integrate the developed these RF
elements and prototype mechanisms into one of ESA ESTRACK Deep Space
Antennas (Cebreros) and to demonstrate the overall concept and validate all
elements in an operational environment.
In order to achieve this overall objective the following activities are envisaged:
- Software upgrade/modification of the controller of the prototype mechanisms to
communicate with the Antenna Front End Controller
- Corresponding adaptation of the Antenna Front End Controller software
- Physical integration and alignment of the RF elements, the prototype
mechanisms and the related controller in the DSA
- Commissioning and testing of the new system, demonstration of the concept.
The on-site activities will have to be performed without interfering with operational
passes.
Deliverables: Ka-Band beam waveguide elements (feed, dichroic) mounted on beam waveguide
mechanisms and integrated into one of ESA´s Deep Space Antennas (Cebreros)
Current TRL: TRL3 Target TRL: TRL6 Duration: 24 Months
Application /
Timeframe:
Future deep space missions using Ka-Band transmission and reception like e.g.
Bepi 2013

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Ref. Number: G517-081GI Budget: 300 K€
Activity Title: Ground-Station Automation and Off-line operations
Description: The main objective of this study is to identify a scenario for automated
Ground-Station. Based on the scenario, the study shall focus on the required
functionality that would support automation and allow the provision of TC and TM
off-line services.This study aims at analyzing possible scenarios for automated
operations such that the control-centre would not need to be permanently
connected. Typically, this kind of operation is needed for missions having short
Passes over the Stations (e.g. Earth Observation): automation would allow
optimal provision of services. The following capability should be considered:
- automatic configuration of the Ground-Station and capability;
- off-line telecommanding allowing the control centre to download in advance the
stack of Telecommands required for one or more passes, and subsequent
transmission of time-tagged Telecommands to the Spacecraft, with guarantee of
delivery
- capability to automatically receive, store and prepare off-line transmission of
Telemetry to the control centre;
- capability to automatically acquire the signal and track the spacecraft.
. capability to automatically execute mission configuration and spacecraft
acquisition tasks to cope with short passes (typically, Earth Observation
spacecraft).
The study shall as well look into automatic recovery in case of problem: loss of
signal, retransmission of Telecommands.
Finally the study shall identify the information required for post-pass analysis and
correction of possible misbehavior.
The Study shall produce a prototype implementing an initial set of functions.
Tasks to be performed:
1.- Identification of the various possible scenarios and possible operational
approach; this includes the definition of the Protocols (within the SLE services) for
off-line TC services and for operations reporting.
2.- Identification of the existing functions that would be affected;
3 - Analysis of the recovery capability that would be required.
4.- Prototype implementation, with the objective of demonstrating operational
impacts.
Deliverables: 1.- Technical notes and other supporting documents reporting about the technical
outputs of the study, in particular including recommendations for an approach to
the layout of such a concurrent collaborative environment.
2.- S/W prototype of infrastructure supporting the feasibility of the approach.
Current TRL: TRL1 Target TRL: TRL6 Duration: 12 Months
Application /
Timeframe:
Targeted missions shall be low earth orbiting mission characterized by (very)
short passes over the Stations (presently this is the case for GOCE). This is a
technology push Study. Best estimated date is 2010.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-082GI Budget: 400 K€
Activity Title: Combinatorial Optimization for Scheduling Applications
Description: Applicability of combinatorial optimization approach for scheduling purposes and
in particular for the efficient allocation of ground station passes.
The combinatorial optimization approach is not only linked to the allocation of
ground station passes, it could also be applied in other domains, as example for
payload operations where scientific opportunities or usage of channels would
have to be allocated in an optimal way.
Expected benefits:
- best use of ESA ground station assets and resources for the benefit of the ESA
and non-ESA user community,
- increase in efficiency for mandatory planning processes within ESA mission
operations,
- better and faster service and access for ESA mission operations
customers.Satellite operations require ground stations, from which the
communications (Telemetry, Telecommand and Tracking) with the spacecraft can
be conducted. The identification of the ground station passes to be selected is still
primarily a manual process, which seems to be the case as well for several other
Space Agencies.
It is obvious that this manual process of selecting station passes becomes easier
when more ground stations are available or when spacecraft dedicated ground
stations are used. However, maintaining a larger network of ground stations has a
cost implication. The optimal and automated allocation of ground station passes
would require less ground antennas and furthermore less scheduling effort.
It is proposed that a combinatorial optimization approach for the efficient
allocation of ground station passes is applied.
It is proposed to study various methods in the area of combinatorial optimization
including aspect as:
- relaxation based mixed-integer approach providing lower and upper optimality
bounds,
- fast branch-and-bound and branch-and-cut algorithms,
- advanced enumerative schemes,
- constraint programming techniques,
- acceleration by polyhedral and general cutting plane techniques.
For the selected method there should be mathematically founded guarantee that a
feasible solution will be found under the assumption that one exists. In case there
is no feasible solution then approximate solutions will have to be computed
according to user specified priorities.
The selected method should be able to cope with additional requirements such as:
- treatment of larger number of satellites and ground stations,
- fast check if requests by additional customers can be satisfied,
- efficient short term and long term prediction capabilities,
- effective re-optimization for real-time changes e.g. of user requirements or
availability of resources.
Deliverables: Study report and a prototype software for the selected method
Current TRL: TRL1 Target TRL: TRL6 Duration: 15 Months
Application /
Timeframe:
Optimization of ESTRACK ground stations scheduling. 3rdQ 2010

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Ref. Number: G517-083GI Budget: 400 K€
Integrated development and validation environment for operations
Activity Title:
automation
Description: The objective of this activity is to enable the efficient production of formalised
procedures supporting the spacecraft operations automation. The added value of
the pre-operational implementation that will be delivered is in the capability to
define and completely validate automation procedures within one single
environment.Now that generic tools supporting the deployment of operations
automation are available, the main effort to actually automate the spacecraft
operations will be in the definition and validation of the automation procedures.
The objective of this activity is therefore to provide the users with a
pre-operational implementation of a comfortable environment which supports the
definition and just-in-time validation of the automation procedures. The intention
here is to bridge the gap between procedures definition and procedures validation
in the run-time execution environment. It is envisaged to capitalise on the existing
generic products used by all missions at ESOC to define procedures (MOIS), to
execute them automatically (MATIS), to interface with the automated system
(SMF) and to simulate the behaviours of Ground Data Systems (SIMSAT and
GSTVi).
Deliverables: S/W demonstrator supporting the capability to efficiently set-up a test-bed for
automation procedures and the actual execution of automation validation
activities.
Current TRL: TRL4 Target TRL: TRL6 Duration: Months
Application /
Timeframe:
These elements can be very generic as automation procedures and the
automation interface to ground infrastructure are defined according to standards.
The intention is to integrate an operationally qualified version into the ESOC
Automation Infrastructure and to make it available to future missions as from year
2011.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-084GI Budget: 400 K€
Activity Title: Ubiquitous alert and operations monitoring system
Description: Previous studies have provided an analysis of technologies compatible with
mobile phones to implement a 'remote operators alert system'. While the analysis
has proved the feasibility of the approach, a formal validation of the different
technologies involved has yet to be done in the various operational environments,
covering both spacecraft and ground station operations. In addition, it is required
to extend the monitoring capabilities of remote operators by enabling them to
access the most relevant operational data in order to properly handle the received
alerts.The increase of the space segment autonomy and the need to reduce the
running costs of spacecraft operations have recently lead to the adoption of
operations concepts that do not rely on the continuous presence of operators in
the control rooms. Similarly, on the side of ground stations control, an increasing
level of automation is being implemented, thus enabling the relaxation of the
continuous monitoring approach adopted so far. However, a full deployment of
'lights-out' operations of space systems can only be achieved by a) having a
monitoring system that can trigger an alarm in case of problems, b) having a
system to contact on call engineers in case of anomalies and c) enable the alerted
operator to properly assess the status of the controlled system and thus react to
the received alert (e.g. accept, forward, disregard).
The monitoring of the controlled system status (spacecraft or ground station) and
associated alarms generation is already part of the relevant control system (the
Spacecraft Control System or the Station Computer). However, the functionality to
notify alerts to on-call personnel and to enable their remote access to the
operational data is still missing.
A previous GSTP study successfully demonstrated the feasibility of a number of
technologies to implement these tasks. The deployment and roll-out of such a
system, however, cannot be done unless a thorough validation in the relevant
operational environments is performed. This study will perform such validation. In
addition to this, the capability to collect and visualise a minimum set of essential
data on personal (ultra-light) devices that can communicate via standard mobile
networks will be implemented and demonstrated. This will require the definition of
highly portable and optimized data visualization and presentation techniques
which enable the remote operator to acquire an appropriate amount of details
using devices of very limited size. The security implications of such an application
will also be carefully assessed.
Deliverables: The study will deliver a pre-operational demonstrator of a remote alert and status
monitoring application, enabling access to essential operational data via ultra-light
personal devices (of the size of a mobile phone).
Such prototype will be based on deliverables of the previous study but will extend
it to cover:
• Capability to notify alerts received from any critical ground data system related to
spacecraft and ground segment control
• Capability to visualize remotely the operational status of the controlled system on
ultra-light devices
• Capability to
The study will also cover the system installation and deployment such to test the
deliverables in the relevant operational environment. This includes ESOC’s
networks reserved to operations, ESOC office network, the public GSM network
and probably the Internet. The validation campaign will be based on a real mission
(GOCE).
Current TRL: TRL3 Target TRL: TRL6 Duration: 12 Months
Application /
Timeframe:
GOCE will be the first mission to apply the concept. Several validation tests shall
be done in parallel with GOCE routine operations (end of 2009).

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Ref. Number: G517-085HS Budget: 350 K€
Activity Title: Integrated Monitoring & Diagnostic of End-to-End Communication Link
Description: The objective of this project is to implement a pre-operational prototype
application that monitors in near real-time the complete communication link in
order to detect anomalies and interruption of services in the various elements and
to support the identification of the root cause.The end-to-end communication link
consists of many different elements that are managed and operated separately.
Starting at the spacecraft, going over the ground-stations to the ground
communication network, the NIS, to the control centre and finally to the operator's
console and to the archives, the complete chain is managed by different control
units and responsibility is split. No end-to-end situation awareness is available in
one single monitor and in case of degradation or disruption of service the root
cause analysis is not straight forward.
Relevant data will be automatically collected in near real-time from available
interfaces and/or repositories. The data will then be analyzed using appropriate
technologies such as machine learning and other artificial intelligence techniques.
The data will be processed and compiled in order to present to the user a global
view of the status of the end-to-end communication link through a graphical user
interface.
This activity is a continuation of the TRP study CESADS, which addressed the
end-to-end communication link in the case of ENVISAT with an early prototype
system.
The proposed study consists of two phases:
- Phase 1: System design and prototype implementation using prepared data sets
offline
- Phase 2: Application of the prototype system in the real environment using
available data sources at infrastructure level in near real-time
Deliverables: Software prototype
Current SW
Readiness Level:
Application /
Timeframe:
System
architecture
available for the
case of ENVISAT
Applicable to all missions
Target SW
Readiness
Level:
Multi-mission
pre-operational
prototype
Duration: 21 Months

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-086GS Budget: 300 K€
Activity Title: Deep space receiver for support during superior solar conjunctions
Description: To develop and test a receiver which is optimum in a channel where Rician
fluctuations are dominant, which is the typical scenario applicable to deep space
missions during superior solar conjunctions.Deep space missions incur
periodically in superior solar conjunctions, i.e. phases during which the
telecommunication link between Earth and Spacecraft transits through the solar
plasma. This is causing impairments to the quality of the link, in terms of
amplitude and phase fluctuations, spectral broadening and other effects, in turn
causing loss of telemetry on ground reception side. The impact is significant in
terms of science data return, which is interrupted for periods of time ranging
between days and weeks, depending upon the level of solar activity. The deep
space receivers of the ground stations are generally optimized for reception of
signals through Gaussian channels, i.e. channels where the unique perturbation is
given by additive Gaussian noise, with generally assumed flat power spectrum.
However the Gaussian model is not adequate for describing the
telecommunication channel during a superior solar conjunction: in such phase a
Rician model describes more effectively the amplitude and phase scintillation
effects which are observed, and which are due to the transition of the
communication signals through inhomogeneous plasma medium.
The objective of the proposed work is to study receivers which are optimum in a
Rician channel, and which can be used during a superior solar conjunction to
improve as much as theoretically achievable the quality of the telemetry reception.
Work in this direction has been made in mobile telecommunications; however, this
technology has to be introduced in deep space communications, especially for the
ESA deep space network.
The input to the activity is a large set of data, representing the downlink signal
transmitted by an ESA Deep Space Spacecraft (Venus Express) and received at
ESA deep space ground stations during a superior solar conjunction. The signal is
recorded in open loop by using a wide bandwidth, covering the whole telemetry
spectrum.
As part of the study, a software receiver is designed, developed, and tested over
the recorded data. The selection and procurement of the COTS hardware platform
where this software will run efficiently is also part of this development.
The receiver is designed taking in to account the characteristics of the
telecommunications channel, and its performances are compared with the
performance of the available “standard” deep space receiver, suitable for a
Gaussian channel and acting on the same data.
The output from the study consists of the prototype receiver, of demonstrated
superior performances in respect to the standard deep space receiver, as well as
all associated documentation. The prototype has a sufficient level of operability
allowing its use during a subsequent solar conjunction of a deep space mission,
for validation of its superior performance during an operational support.
Deliverables: Prototype software receiver, including the hardware platform. All associated
documentation (survey of literature, design, architectural definition, testing)
Current TRL: TRL2 Target TRL: TRL6 Duration: 15 Months
Application /
Timeframe:
The proposed development is required for all ESA deep space missions, for use
during superior solar conjunctions. It is of particular use for BepiColombo, due to
the low separation angle from the Sun experienced during the whole in-orbit
phase.

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Ref. Number: G517-087GI Budget: 400 K€
Activity Title: Operational Data Off-line Analysis, Correlation and Reporting System
Description: The Mission Control System infrastructure at ESOC supports the storage of
mission operations data in dedicated archives designed in order to manage
specific types of data, namely the Packet Archive (PARC), the Engineering Data
Archive (DARC) and the File Archive (FARC). Generic user applications support
the retrieval and visualisation of this data but not their post-processing nor any
sort of correlation between heterogeneous data (e.g. commands, events,
monitoring parameters, configuration variables). This represents a significant gap
in the support of mission data systems as there is an increasing demand of a
powerful off-line environment where operational data can be analysed in order to
support the following main use cases (non-exhaustive list): i) troubleshooting and
investigations of operational events; ii) evaluation of space and ground systems
performance; iii) generation of periodic and specific reports. Another important
driver is the fact that access to the data analysis environment shall be granted
from operational areas as well as from non-operational areas, either co-located
with the mission operations center (e.g. ESOC offices) or remotely connected via
Internet.
This activity will concentrate on the design and pre-operational implementation of
an off-line environment supporting the analysis and reporting of operational data.
The use cases to be supported will be identified in detail by involving a
representative group of end users. User interface mock-ups will be produced such
to demonstrate the possibilities offered by the candidate architecture and
technology. It is envisaged that the final architecture will include at least the
following main components: i) data interface, supporting the access to the relevant
storage of the operational data transparently and with high-performance; ii) data
post-processing, supporting the generation of e.g. statistics and/or derived
engineering data simplifying the data analysis and reporting; iii) data analysis tool,
supporting among others the visualisation and correlation of heterogeneous data
in integrated displays and iv) data reporting tool, supporting the generation of
reports embedding the outputs of the data post-processing and/or of the data
analysis tools.
The main tasks of the activity are:
1) Identification of the main ‘use cases’ related to the post-processing and
analysis of operational data;
2) High-level architectural design of the off-line environment supporting the
access, post-processing, analysis and reporting of all relevant operational data;
3) Selection of the most appropriate technologies supporting the
implementation of the main components (e.g. data post-processing, data analysis,
data reporting);
4) Implementation of the main components forming the off-line data analysis
and reporting environment;
5) Pre-operational deployment of the activity deliverables.
Deliverables: Pre-operational implementation of an extensible off-line environment supporting
the analysis and reporting of operational data. This includes documentation as
well as S/W deliverables.
Current SW
Readiness Level: N/A
Application /
Timeframe:
Target SW
Readiness
Level:
Pre-operational
software
Duration: 18 Months
The outputs of this activity are expected to be used as part of the development of
the new generation of EGOS data systems infrastructure, to be used by all ESOC
missions in the 2011-2020 timeframe.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-088MM Budget: 3,000 K€
Development of core technological elements in preparation for future
Activity Title:
Optical Atomic Frequency Standards (OAFS) and clocks (OAC's) in space
Description: The principal objective of the proposed activity is to enhance the technological
readiness levels of the main sub-system elements of an OAF, to levels that are
compatible with the engineering and performance requirements of proposed future
space programs and thus to enable the realisation of future flight hardware. To
accomplish this objective and to cover anticipated possible performance
requirements a development strategy of 4 (four) individual OAFS is proposed that
will cover the expected performance envelope for possible future missions. The
emphasis of these developments will be in the choice of engineering approaches,
configurations, lay-out and design which are compatible with space qualification
requirements. An additional, essential and important part will be definition and
execution of the necessary tests to validate the space compatibility.
The technologies that need to be developed with the objectives above are those
required for the the implementation of four Clock types:
1. Single trapped Sr+ ion clock
2. Cold atomic Sr lattice clock
3. Al+ ion clock based on quantum entanglement
4. Cold atomic Hg lattice clock
Each of these will require four principal sub-systems elements comprising
a) the preparation of the transition (quantum absorber) either in the single ion or
lattice.
b) the clock state interrogation with an ultra narrow linewidth frequency stable
laser
c) frequency counting using an optical frequency comb
d) frequency dissemination and comparison.
The scope of the proposed activity is primarily confined to Clock type 1 (Sr ion)
but is organized into two Work Units that uncover the development synergies of
some of the laser, and other technologies, common to both Sr+ (ion) and Sr lattice
(neutral) clocks:
Work Unit 1: addresses the following technologies, sub-system elements:
- Sr ion trap package development
- Fiber delivery and wavelength/frequency diagnostics
Work Unit 2: addresses the following technologies, subsystem elements:
- Development of Cooling and auxillary diode lasers
- Development of Clock Laser (LO)
- Fiber delivery systems
- Stabilising reference cavity implementation
- Environmental control electronics
- Clock algorithms
- Component integration
Practically everything in Work Unit 2 has development synergies in both the Sr+
and Sr lattive clocks. These synergies shall be clarified in order to prepare for a
subsequent development focussing on the Sr lattice clock.
Deliverables: Core technlogy elements for a space-compatible Optical Clock tested and verified
in a relevant environment
Current TRL: TRL2 Target TRL: TRL4 by 2013 Duration: 36 Months

Application /
Timeframe:
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Science (Cosmic Vision), Earth Science (Gravity field mapping, High performance
Time distribution (GEO), Navigation)
Ref. Number: G517-089SY Budget: 500 K€
Activity Title:
Demonstration of a Vision based System for Formation Flying and
Rendez-vous
Description: The objective of this activity is to demonstrate a Vision Based System (VBS) for
Formation Flying and Rendez-vous missions. Such system will follow the initial
demonstration performed on the PRISMA mission. This system has the potential
be a valid alternative to the combination of RF and coarse optical metrology. Also,
being a single integrated system, it has advantages in terms of accommodation
and resources requirements.
The activity will include the following main tasks:
1. System configuration, design consolidation and performance analysis of the
VBS system.
2. Manufacture and assembly of the VBS system.
3. Verification and validation of the VBS system for the PROBA 3 mission
4. Integration of the VBS system on PROBA 3 and system validation
Deliverables: Phase B output (configuration, performance analysis, system requirements and
preliminary design). All deliverables required by a project in Phase C/D/E1.
Current TRL: TRL4 Target TRL: TRL6 by 2013 Duration: 36 Months
Application /
Timeframe:
Justification for DN:
The subject activity is aimed specifically at the Proba-3 application for FF and also
Rendez vous demonstration. The technology is also applicable to a range of
science and exlporation missions where knowledge of relative position and
attitude of two bodies at various ranges is required.
The time frame for the Proba-3 development requires technology maturity (TRL5)
and Phase B to be demonstrated at completion of project Phase B
This activity is a continuation of the demonstration on the Swedish mission
PRISMA. It will also capitalise on the advanced mission and system design of
PROBA 3 as well as rendez vous studies in the frame of the Space
Exploration program. It is related with the previous activities performed on the
DTU star tracker. It is indeed proposed that the Vision Based Sensor is
merged with the star tracker in order to remain compatible with the limited
resources available in a small spacecraft.
Activity to be included in the Special Initiative Scheme.
Non-competitive tendering is justified according to Articles 6.1. c) of the
Contracts Regulations.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-090SY Budget: 200 K€
Activity Title: SYMPHONY
Description: The activity aims at evaluating the new OCDS tool (Open Concurrent Design
Server) developed under a previous ESA contract for its implementation in a
concurrent engineering facility.
In particular, two major work packages are foreseen:
• the extension of the OCDS tool (supporting CDF - Concurrent Design Facility)
data-exchange to extend its use. This involves:
- the adaptation of the data-model and the functional and user interface with
requirements management tools, to integrate requirement and performances
management, and associated tools.
- the prototyping of the management, storage and exchange of configuration
(CAD) data within the data-base and the selection of a simplified representation of
the geometry suitable for early phases data-exchanges.
- the prototyping of the management, storage and exchange of mission profile
data-files (mission time-line, spacecraft attitude and trajectories, associated space
geometry data and analysis results data).
• The evolution of the tool to support the management of the project across
different entities while ensuring industrial confidentiality of data. This leads to
extend the functionalities of the OCDS tool:
- import/export of models through open standards (xml scheme based on the
ECSS-E-TM-10-25A) either of a complete project or a part of this project (such as
subsystem).
- development of a "stand-alone" solution to have a light implementation dedicated
to a use by a single user (typically for small companies or laboratories in charge of
a small part of the project).
Deliverables: OCDS additional modules and related documentation; Technical reports
Current SW
Readiness Level: Algorithm
Application /
Timeframe:
Justification for DN:
Target SW
Readiness
Level:
2010; Various applictions in CDF type facilities.
Software Release Duration: 12 Months
This activity is a direct continuation of the previous GSTP-4 contract 20982,
developed by Jotne EPM (N) and funded with 500K€.
Activity to be included in the Special Initiative Scheme.
Non-competitive tendering is justified according to Articles 6.1. c) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
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Ref. Number: G517-091QC Budget: 700 K€
Activity Title: Assessment of AAC System-in-Package (SiP) technology
Description: The objective of the activity is the technical assessment and validation of
Ångström Aerospace Corporation (ÅAC) advanced System-in-Package (SiP) for
generic space application.
ÅAC is developing a technology for high density packaging of electronics, using
silicon or ceramics substrates multilayers. Active components are reported as
naked dies by flip-chip, and passive components are SMD. ÅAC has
demonstrated the miniaturisation of several electronic systems using this
technology in the frame of research activities, and three SiP modules have been
integrated and will be flown on a demonstration satellite. To enlarge its portfolio,
ÅAC is also developing the stacking of several of these substrates, using
through-silicon-vias for interconnections.
However, this SiP technology is still in an early industrialisation stage (TRL2/3)
and it has introduced several processes that are not used in standard Space
electronics. Therefore reliability in relevant environment needs to be assessed to
validate the technology for our application. The activity proposed here will cover
the assessment of ÅAC SiP technology for future generic need in ESA
programmes.
Task 1: Review of requirements and critical analysis of the SiP technology
Task 2: Preparation of the SiP technology Evaluation
Task 3: ÅAC manufacturer category 2 validation
Task 4: Technological Assessment testing
Task 5: CTA (Circuit Type Approval) of the MCC design
Task 6: Definition of Flight lot manufacturing flow, screening & Acceptance
criteria, for the MCC
Task 7: Performance of the LAT (lot acceptance test) on the MCC
Task 8: Compilation of results
Deliverables: Documentation, including at least: tailored requirements technical notes,
evaluation test plan, PA/QA documentation, audit report, evaluation testing report,
MCC Design Report, CTA report, manufacturer category 2 validation report,
frozen SiP PID (Process identification document) for flight production, LAT plan,
and final assessment report clearly highlighting the processes from ÅAC
technology that can be considered as generically suitable for space applications
and those which could only be validated for specific (planetary rover) applications.
Hardware samples: at least 2 representative samples for Construction Analysis
(initial Capability Validation), 1 EM MCC from Task 5, and 1 FM MCC from Task
7.
Current TRL: TRL2 Target TRL: TRL5 by 2011 Duration: 24 Months
Application /
Timeframe:
The closest potential Space application for ÅAC SiP technology is planetary
exploration rovers, as it enables the fabrication of highly miniaturised electronic
modules. Using this technology, the TRP project “Motion control chip” (ESA
contract 21737) and the intended “Multi wafer hybrid integration: Robotics IMU”
TRP project (TRP reference T713-066MM) are aiming at developing miniaturised
electronic modules for robotics, taking Exomars rover as a reference mission.
However, more generic need will probably develop when ÅAC starts offering
commercially their service to other part manufacturer or designer.
The activity proposed here is “techno push”, and the best estimated date to have
this technology at TRL5/6 is 2011.
In the longer term, this technology could benefit other projects, which have a high
miniaturisation need.
Non-competitive tendering is justified according to Article 6.1. a) of the
Justification for DN:
Contracts Regulations.

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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-092EC Budget: 1,500 K€
Activity Title: ASTRO-APS Productionisation
Description: The objective of this activity is complete the development of the ASTRO-APS STR
with the implementation of the required power supply and data interface options,
the upgrade of the software with the lessons learnt from the 'Future technologies
for APS STR' TRP contract and the design changes required to adapt to new
ASIC and processing packaging types. In addition, the MAIT approach for the
STR will be updated also in line with the lessons learnt from the 'Future
technologies for APS STR' and a new plastic baffle option will be tested.
Deliverables:
The activity is needed in order to increase the applicability of the unit to future
missions and to demonstrate several technology advances.
EQM STR, Final Report and data package.
Current TRL: TRL8 Target TRL: TRL8 Duration: 18 Months
Application /
Timeframe:
The proposed activity is applicable for all future ESA missions requiring a STR.
The ASTRO-APS is a Jena Optronic product and Jena Optronic were the
contractor for the pre-cursor activity (contract 20781, "Future Technologies for
APS STR" funded with 590K€ in TRP).
Justification for DN:
Non-competitive tendering is justified according to Articles 6.1. a) and c) of the
Contracts Regulations.
Ref. Number: G517-093EC Budget: 350 K€
Activity Title: STR OGSE (Optical Ground Support Equipment) Development
Description: Realtime, realistic optical stimulation of a STR can bring many benefits to both the
STR supplier and to the end user. In order to fully realise these benefits the optical
stimulator must fullfill a number of key requirements that until recently have been
unsupportable by currently available technology:
- Realistic representation of the real sky, including star size, magnitude,
distribution and dynamic range
- Realtime update of the display at sufficiently high rate (>100Hz) to be able to
accurately simulate s/c movements.
- Realtime update of the display to include realistic modelling of non-stellar effects
(e.g. solar event induced SEU, asteroids, other s/c, earth, moon)
- Be sufficiently compact and lightweight as to enable attachement to the STR with
any orientation wrt the local vertical, without inducing driving structural
requirements on the STR.
- Be capable of being synchronised to the STR integration
- Be vacuum compatible
- Be wireless
The technology to achieve these aims now exists and it is time to upgrade the
design of the existing OGSE to be able to meet these requirements and allow full
real time closed loop testing of the STR and its robustness even while on the s/c.
Deliverables: Prototype OGSE
Current TRL: N/A Target TRL: N/A Duration: 15 Months
Application /
Timeframe:
All missions requiring a STR.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 139
Ref. Number: G517-094EP Budget: 1,600 K€
Activity Title: Towards performance guaranteed Ge substrates
Description: The objectives of the activity are as follows:
1. In-depth study of the root cause of stochastically occurring quality issues on
Germanium substrates.
2. Quantification of the chemical and geometrical nature of an epi-ready
Germanium substrate. Scientifically measuring the shelf-life and determining
optimal storage conditions of an epi-ready substrate.
3. Developing a tool that is capable of measuring and accurately binning all
different light scattering defects on a substrate larger than 0.5 micron, without
jeopardising the epi-ready nature of the substrate.
4. Investigating a yet more accurate detection technique for the presence of
transition metals in Germanium substrates
5. Implementing the necessary changes in production and quality control and
qualifying it with the customers, leading to a product of superior quality.
III-V multi-junction solar cells have taken the lead in today’s solar cell market for
space. The higher manufacturing costs in comparison with silicon solar cells are
overcompensated due to the significantly higher efficiencies and higher radiation
hardness.
For a long time, the quality of the Germanium substrate - which also forms the
subcell of todays state-of-the-art III-V triple-junction cell - was not the limiting
factor in further improving the mean efficiency of a production batch. However, the
quality of the substrate needs to be brought to a next level, in order to allow the
solar cell manufacturers to produce next generation triple junction cells with a high
enough yield. This is also related to the fact that the solar cell fabrication is
nowadays under such a high control that quality issues of the Germanium
substrate are immediately recognized by efficiencies of the solar cells being below
the lower end of the normal distribution.
Thus, the focus of this activity will be on quality improvement and this on 3 facets.
First of all, it is mandatory to investigate in detail customer complaints related to a
limited number of recurring quality concerns on the Germanium wafers. As both
the occurrence and the number of affected substrates within a bad lot is low, it’s
impossible to fully examine these within a commercial context. But as every
occurrence heavily interferes with the normal production flow, both at the solar cell
and substrate manufacturer level, the issues need to be resolved in order to allow
the industry to raise the quality standards to a next level.
Secondly, it’s necessary to scientifically quantify the only non-measurable
specification of a substrate, it’s epi-readiness. At the end, this is one of the most
important specifications for the customer: proper growth is only achievable on an
epi-ready surface. Today, epi-readiness is controlled by a naked eye inspection,
leaving room for large deviations. In order to quantify it, it’s necessary to
understand the evolution of the chemical and geometrical status of the substrate
within each production step. There is also a need for a dedicated tool that can
quickly scan substrates and discriminate between light scattering defects that are
in or on the surface (pits vs particles). Together with tests on shelf life and
packaging, it should be possible to find a scientifically sound definition of an
epi-ready Ge substrate.
Thirdly, a number of impurities, most often transition metals, are fast diffusers in
Germanium and have a detrimental impact on minority carrier lifetime. Although
they’re today present in quantities below detection limit of routinely used analysis
techniques, it’s not excluded that a number of issues are related to these
impurities. For this, it’s necessary to investigate other detection techniques that
would allow for a higher detection resolution for these impurities (detection limit
below 1012/cm-3). Secondly, there is a need to investigate how these impurities
behave during standard production and solar cell growth and might lower overall

ESA/IPC(2010)51
Annex 2, Page 140
ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
solar cell performance.
Deliverables: Triple-junction cells on Germanium wafers containing trace amounts of metallic
impurities (at least 10 solar cells);
Substrates alleged to be bad by customers (minimum 500 pcs);
Substrates fully characterised in terms of pits/particles for features larger than 0.5
microns (minimum 10 wafers);
Set of substrates manufactured and packaged based on improved processes
towards an epi-ready wafer (minimum 200pcs);
Set of solar cells grown/defined on wafers with optimised processes (at least 10
solar cells);
Reports;
Current TRL: N/A Target TRL: N/A Duration: 36 Months
Application /
Timeframe:
Next generation space solar cell
Non-competitive tendering is justified according to Articles 6.1. a) of the
Justification for DN:
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 141
Ref. Number: G517-095MM Budget: 100 K€
Activity Title:
High-Dynamic Absolute Nanometric Optical Encoder technology for space
(DANOE)
Description: Combining all the attractive features in a position encoder such as high-resolution,
absolute, compact, high-speed is a real challenge today. An optical absolute
position encoder technology has the potential to combine all these attractive
features. Nanometric resolution can be established using dedicated optical
sensor, a transmissive scale, LED illumination, without the need for optics
(shadow-imaging). Optic-less shadow-imaging permits compact design and major
cost reduction. Note that the detectable displacement is several hundred times
smaller than the wavelength of the light and only 10 times larger than the diameter
of the silicon atom. High-speed opto-ASIC implementation proved that sampling
frequency of such an encoder may exceed 1 MHz.
Coarse absolute position measurement is obtained by decoding the subsection of
the Manchester code (typically 8-14 bits), which is seen at a given position by the
sensor. Fine relative position measurements is attained by Fourier analysis-like
processing of the regular grating. Robustness, precision and very high resolution
is guaranteed by heavily oversampling the pattern (typically 8-16 pixels per
pattern period) and relying on the phase information which is distributed in the
entire image among hundreds or thousands of pixels. The combination of the
coarse and the fine measurements yields very high-resolution absolute position,
typically 16-30 bits for rotary or linear encoder.
This activy aims at:
a) Identifying the two most promising space applications in which the optical
encoder technology can be used the best.
b) Developing a technology demonstrator.
Tasks:
1. Identification of potential space applications needing high accuracy position
sensors.
2. Definition of the high accuracy position sensors technical specifications for the
space applications identified before.
3. Trade-off of the two most promising applications.
4. Identification of the "space compatible" technologies for the selected optical
encoder.
5. Design of the demonstrator
6. Manufacturing and testing of the demonstrator
7. Summary of the reached performances and development plan.
Deliverables: Technical notes and documentation describing the selected space applications
and the technical specifications of the high accuracy position sensor for these
applications; the trade-off of the two most promising applications; performances to
be reached; laboratory demonstrator reaching the expected performances; and
development plan.
Current TRL: TRL3 Target TRL: TRL4 by 2011 Duration: 12 Months
Application /
Timeframe:
All kinds of applications in need of high accuracy positioning.

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Ref. Number: G517-096EC Budget: 350 K€
Activity Title: W40 Reaction Wheel Capacity Improvements
Description: The objective of this activity is improve the Reaction Wheel Assembly (RWA) of
the W40 reaction wheel currently provided by Bradford Engineering.
In particular the activity shall cover the investigation, design and demonstration of
a Torque capacity increase from 0.2 to 0.4Nm, the possibility and limitations on
the increase of the momentum capacity from 40Nms to 60Nms and shall also
improve the design of the Reaction Wheel Assembly cover. The design
improvements shall be demonstrated and qualified by test via the upgrade of
existing hardware with the mentioned improvements.
In addition to the above improvments to the RWA, the feasibility of implementing a
wheel speed control loop in the Wheel Drive Electronics (WDE) shall also be
investigated. The function shall be designed and its performance limitations
derived. The function will be demonstrated via implementation and test in the
FPGA of a breadboard WDE
Deliverables: Final report
Current TRL: N/A Target TRL: N/A Duration: 12 Months
Application /
Timeframe:
Justification for DN:
The proposed activity will allow Bradford Engineering's reaction wheels to be
offered for use on a wider range of platforms and to a wider range of customers. It
will also allow greater levels of agility intermediate between those achievable with
current reaction wheels and those achievable with CMG.
This activity is targeted at upgrading the capacity of a specific Bradford
reaction wheel. As it is targeted at a specific equipment and model only
Bradford are able to perform the work.
Non-competitive tendering is justified according to Article 6.1. a) of the
Contracts Regulations.

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 143
Ref. Number: G517-096MP Budget: 500 K€
Experimental Investigation of Key Technologies for a Turbine Based
Activity Title:
Combined Airbreather-Rocket Engine: Phase II
Description: In Phase 1 of this GSTP activity the design and development of the pre-cooler is
being undertaken together with elements of the test rig required to test the
pre-cooler. The development in Phase 1 has completed the pre-cooler design
and the manufacture of all the matrix tubes and associated modules, frost control
equipment and fixtures but did not address the assembly of the pre-cooler nor its
integration onto the test engine facility and subsequent testing.
Phase 1 also covered the investigation of oxidizer cooling of the combustion
chamber and the development of a pressure-compensating nozzle design and
both of these activities are currently underway. The remaining area of key
technology, the intake, however, was addressed in Phase 1.
Phase 2 of the programme is designed to complete the activities enabling the
pre-cooler to be assembled and tested. During this phase, the experimental
investigation of key technologies for a turbine based combined air-breather-rocket
engine, covers demonstration of pre-cooled engine with frost control, thrust
chamber and nozzle concept, variable air intake geometry and implementations
and functional issues of achieved developments in aerospace programmes
specifically the demonstration of pre-cooled engine with frost control (REL) air
intake.
The demonstration of the operational feasibility of the pre-cooler shall consist of
the assembly of the pre-cooler and then integration on the test engine facility
completed during Phase 1 (cooling loop and jet engine system). Following this a
series of tests shall be performed in which the pre-cooler operation will be
demonstrated. These tests shall be performed with ambient air at different
relative humidities in order to demonstrate the control of frost build-up by the
pre-cooler.
Deliverables:
The contractor is expected to contribute with an additional budget of approx. 1,100
K€, to be confirmed during the negotiation meeting.
Technical notes describing test rig, test procedure, test data and analysis;
Experimental database.
Current TRL: TRL3 Target TRL: TRL4 Duration: 18 Months
Application /
Timeframe:
Airbreathing engines for future launchers and aerospace vehicles

ESA/IPC(2010)51
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ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
Justification for DN:
Dedicated precooled airbreathing engine cycle within Europe is only available
at and developed by REL (UK). Other R&D in this field are performed outside
Europe (e.g. Atrex and S-engine in Japan). A problem with deep pre-cooling in
a humid atmosphere is the formation of frost on the tube surface which quickly
(3 – 7 seconds) blocks the narrow passageways within the tube matrix.
Reaction Engines has developed an effective means of preventing the
formation of frost, referred to as the ‘frost control mechanism’. This
mechanism was developed entirely with private investment and remains
Commercial in Confidence to the Company. This point is crucial in the viability
of the concept and the proposed frost control technology proposed needs to
be demonstrated adequately.
Furthermore, this phase 2 activity is a direct continuation of the work alredy
developed in the phase 1 activity, under ESA contract 22219 (funded by TRP
with 500K€ and by GSTP-4 with 500K€).
Non-competitive tendering is justified according to Article 6.1. a) and c) of the
Contracts Regulations.
Ref. Number: G517-097MP Budget: 250 K€
Activity Title: Microdisturbance sources and characterisation
Description: Microvibration is becoming a critical issue to more and more ESA missions (e.g.
Sentinel2, MTG…). The Reaction Wheels required for the attitude control for
these missions are also one of the key micro-vibration sources. This activity is
intended to investigate and assess all of the contributors to reaction wheel
microvibrations, to characterise these by test, determine their likely variability due
to launch and environmental conditions and to seek for ways both to reduce their
contribution and to provide a likely in orbit vibration spectra with a high degree of
confidence.
From the test results, a model of the disturbance spectra will be produced and
delivered.
Deliverables:
Such an activity will prove highly useful to a number of current and future ESA
missions and will also be of great benefit to reaction wheel providers to assist in
the improvement of their wheels.
Final report including test results; technical data package; microvibration
disturbance model
Current TRL: N/A Target TRL: N/A Duration: 12 Months
Application /
Timeframe:
The proposed activity will provide much needed information for all current and
future missions with critical micro-vibration requirements

ANNEX II: Description Activities GSTP-5 Element 1 Work Plan
ESA/IPC(2010)51
Annex 2, Page 145
Ref. Number: G517-098EP Budget: 300 K€
Activity Title: Reaction Wheel DC-DC Converter Upgrade
Description: The objective of this activity is improve the DC-DC convertor within the W18 and
W40 ranges of reaction wheels produced by Bradford Engineering and currently
selected for Bepi Colombo mission and in consideration for a number of other
ESA missions. The current DC-DC convertor design originates in the late 1980s
and was targetted at 28V primary power with external switching only. It is not
capable to support other configurations and requires updating.
This activity will design a new modular DC-DC convertor for the reaction wheel
capable of being configured to support various different configurations in common
use in the market today. The new DC-DC convertor will be manufactured and
subjected to qualification level testing as part of a Wheel Drive Electronics.
The performance of the reaction wheel is closely linked to that of the DC-DC
convertor and power conditioning electronics of the Wheel Drive Electronics and
as such form an integral part of the equipment.
Deliverables: Final Report; Ground Qualified Wheel Drive Electronics with new DC-DC
convertor
Current TRL: N/A Target TRL: TRL6 by 2011 Duration: 12 Months
Application /
Timeframe:
Justification for DN:
The proposed activity will allow Bradford Engineering's reaction wheels to be
offered for use on a wider range of platforms and to a wider range of customers.
This activity is targeted at upgrading the DC-DC convertor of the Bradford
reaction wheels as discussed during the Harmonisation process for AOCS
sensors and actuators. As it is targeted at a specific equipment and model
only Bradford are able to perform the work.
Non-competitive tendering is justified according to Article 6.1. a) of the
Contracts Regulations.