LIST OF INTENDED INVITATIONS TO TENDER 2002 - emits - ESA

ESA/IPC(2002)11,Rev.25 

Paris, 02/12/2002 

(Original: English) 

INDUSTRIAL POLICY COMMITTEE 

LIST OF INTENDED INVITATIONS 

TO TENDER 

2002 

OPEN AND RESTRICTED COMPETITIVE 

TENDERS 

Produced by ESRIN/ADM-IMA


Page 2 

We draw the attention of the users to the fact that this document 

will be updated on a monthly basis on EMITS. 

ESA/IPC(2002)11 

dated 15-Feb-2002 

ESA/IPC(2002)11,REV.1 





dated 07-Mar-2002 


dated 15-Mar-2002 


dated 04-Apr-2002 


dated 12-Apr-2002 


dated 03-May-2002 


dated 08-May-2002 


dated 13-Jun-2002 

ESA/IPC(2002)11,REV.10 dated 02-Jul-2002 

ESA/IPC(2002)11,REV.11 dated 22-Jul-2002 

ESA/IPC(2002)11,REV.12 dated 01-Aug-2002 


ESA/IPC(2002)11,REV.14 dated 19-Aug-2008 



ESA/IPC(2002)11,REV.17 dated 06-Sep-2002 




ESA/IPC(2002)11,REV.21 dated 09-Oct-2002 

ESA/IPC(2002)11,REV.22 dated 18-Oct-2002 

ESA/IPC(2002)11,REV.23 dated 06-Nov-2002 

ESA/IPC(2002)11,REV.24 dated 18-Nov-2002 

Potential tenderers are invited to notify their interest in the 

intended ITT’s using the Interest Firm Function (IFF) in EMITS. 



Page 3 

INTRODUCTION 

1. The list of ESA intended invitations to tender is issued for the attention of 

the Delegations and of Industry. The list refers to the ITT’s to be issued 

by ESA. Information on ITT’s to be issued by CNES or by Prime Contractors 

is also given. 

Money values are expressed in Kilo EUROs. The yearly conversion rates are 

shown in para.4 hereafter. Being a planning document, the list is issued 

under the reservations normally attached to documents of that nature and 

is subject to monthly updatings on EMITS. 

2. Additional general information on this list may be obtained from the 

Contracts Department, Mrs Deneuwelaere, at ESA Head Office. Particular or 

technical information on a given action may be obtained from the Technical 

Officers whose functional coordinates, names and place of work are indicated 

at the top of the relevant sheets of the attached document. For complete 

addresses and references, please see page 3. 

3. Before consulting the list, please make sure that you have read and 

understood the attached glossary explaining the various terms and codes used 

in this document (see page 4, 5 and 6). 

4. CONVERSION RATES (2002) 

It is to be noted that the conversion rates in relation to the EMU currencies 

were irrevocably fixed on 31 December 1998 by the Finance Ministers of the EU, 

and their corresponding values are indicated below. 

The conversion rates for currencies other than the EMU ones have been calculated 

on the basis of the average rates for the last six-month period of 2000. 

One EURO is worth : (EURO = European Currency Unit) 

1 EURO = 1.71908 Australian Dollar 

1.37804 Canadian Dollar 

0.57788 Cypriot Pound 

7.46164 Danish Krone 

261.61492 Hungary Forint 

108.02255 Japanese Yen 

8.10857 Norwegian Krone 

0.62364 Sterling 

9.06485 Swedish Krona 

1.53081 Swiss Franc 

0.89814 Us Dollar 



Page 4 

NAMES AND ADDRESSES OF ESA ESTABLISHMENTS 

ESA, European Space Agency, Head Office 

8-10 rue Mario Nikis 

F-75738 PARIS CEDEX 15 

Tel.:33-1-53697654 

Fax.:33-1-53697560 

ESA/CST, Centre Spatial de Toulouse 

18, avenue Edouard belin 

F 31401 TOULOUSE CEDEX 4 

Tel.:33-561-273131 

Fax.:33-561-282802 

ESOC, European Space Operations Centre 

Robert Bosch Strasse 5, 

D-64293 DARMSTADT 

Tel.:49-6151-900 

Fax.:49-6151-90495 

ESRIN, European Space Research Institute 

Via Galileo Galilei 

I 00044 FRASCATI 

Tel.:39-06-941801 

Fax.:39-06-94180280 

ESTEC, European Space Research and Technology Centre 

Keplerlaan 1 

NL-2201 AZ NOORDWIJK ZH 

Tel.:31-71-5656565 

Fax.:31-71-5656040 



Page 5 

GLOSSARY OF THE TERMS USED IN THE LIST OF INTENDED INVITATIONS TO TENDERS 

1. ACTION REF. 

This reference is constituted by a seven-digit number : 

the two first digits indicate the year of the initial announcement 

(95 for 1995, 96 for 1996, 97 for 1997, 98 for 1998, 99 for 1999, 

00 for 2000, 01 for 2001, 02 for 2002, etc.) 

the third digit indicates the type of tender envisaged : 

- 1 for open competitive tenders, 

- 2 for restricted competitive tenders, 

- 3 for non competitive tenders 

(Note : restricted tenders are invitations to tender "restricted to 

potential tenderers selected by the Agency" on the ground that "either the 

supplies or the services required are of such a special nature that it 

limits the capacity to provide them to few potential tenderers or the 

Industrial Policy Committee has given a directive or guideline for such a 

restriction") 

the fourth and the fifth digits, directly associated with the third one, 

constitute identification codes allocated to the responsible Technical 

Officers. The name and coordinates of each Officer are indicated at the 

right-hand top of each sheet. 

the sixth and seventh digits constitute the number of the action, in the 

natural sequence, for each Technical Officer. 

The six digits ACTION REF.number may be followed by the symbol Nn 

(N standing for New action introduced in the revision n of the list) 

2. SUBJECT OF ACTION 

Each action is defined by a title and, whenever 

possible, by a short description of the activity under consideration. This 

information may be completed by references to the relevant ESA programme 

documents such as the Technological Research Programme (TRP), the Advanced 

Systems and Technology Programme (ASTP), the General Studies Programme (GS), 

the General Support Technology Programme (GSTP), the European Microgravity 

Research Programme (EMIR), the Advanced Research in Telecommunications 

Systems Programme (ARTES) and the Advanced Systems and Telecommunication 

Equipments Programme (ASTE). 

3. BUDGET & PROGRAMME REFERENCE 

The BUDGET REFERENCE is composed of two terms : 

- a two (or three)-digit number which is the code of the Budget Output 

to which the contract which will result from the action under consideration 

is intended to be directly charged, 

- the abbreviated designation of the Budget Output 

The PROGRAMME REFERENCE is the reference number of the action under 

consideration within the Programme 

4. SPECIFIC PROVISIONS 



Page 6 

This information gives an indication of the restrictions on tendering : 

i) for the open competitive tenders, the States whose Industry is allowed to 

participate in the tender concerned are indicated. In principle, participation 

is limited to potential tenderers in the States participating in the 

Programme/Output to which the invitation to tender refers 

ii) for the restricted competitive tenders, the potential tenderers are 

indicated, followed by the symbol of their nationality 

(Note : Competition may be limited to certain countries or restricted to few 

firms following decisions of Member States concerning specialisation or 

measures to improve selectively industrial returns) 

The following symbols are used : 

- MS : Member States, i.e. Belgium (B), Denmark (DK), France (F), Germany (D), 

Italy (I), the Netherlands (NL), Spain (E), Sweden (S), Switzerland (CH), the 

United Kingdom (GB), Ireland (IR), Austria (A), Norway (N), Finland (FIN) and 

Portugal (POR). 

- CN : Canada, Cooperating State 

5. TT. TYPE OF TENDER 

The message indicated under this heading is one of the following : 

- C : for open competitive tenders, 

- CR : for restricted competitive tenders, 

- DN : for non competitive tenders (direct negotiations) 

6. Q. Indicates the Year and the Quarter during which the ITT is 

planned to be issued, on two lines. 

7. PP. PROCUREMENT PROPOSAL 

The message indicated under this heading is one of the following : 

- YAC : the submission of a PP to Adjudication Committee (AC) is required 

- YIPC : the submission of a PP to Indus.Policy Committee (IPC) is required 

- NO : the submission of a PP to AC/IPC is not required 

- DAC : the submission of a PP to AC has been done 

- DIPC : the submission of a PP to IPC has been done 

8. PRICE. The limits of the PRICE are given in KEUROs. 1KEURO = 1,000 European 

Currency Units, the conversion rate of the EURO into national currencies 

is given in page II. 

9. STATUS. The meaning and implications of the terms used under that heading 

are as follows : 

- INTENDED : The action is planned but the internal preparation of the ITT 

has not yet started. 

- INITIATED : the ITT is under preparation. The reference number of the ITT 

is shown 

- ISSUED : the ITT has formally been published. 

- COMPLETED : the proposals have been received. 

- AWARDED : a contract has been awarded 

- CANCELLED : the action is withdrawn from the Programme and the ITT which 

was already issued is cancelled 

- DELETED : the action is withdrawn from the Programme before any ITT has 

been issued 



Page 7 

- REASSIGNED: a change has occurred in terms of : either responsibility 

(responsibility for the action being switched to another service) or 

type of tender either at the ESA Management initiative or in execution 

of an AC/IPC decision, for cases qualified for procurement proposals 

following the submission to these Committees 

- POSTPONED : the action is delayed until following programme year(s) 

- RE-ISSUED : ESA has decided to re-publish the ITT 

- ON HOLD : actions which are intended but where there is a possibility 

that they are not issued. 



Page 8 

Important message (applies to selected ITT s, as indicated in each ITT): 

------------------------------------------------------------------------------- 

The Agency is planning to issue an invitation to tender (ITT) for this activity 

in the course of this year. In the preparation of the ITT the Agency wishes to 

consult with interested industries in order to ensure that the Agency s 

statement of work is well focussed and that the ITT meets the needs of industry 

and the demands of the relevant markets. Industry is therefore invited to 

submit a dossier including: 

- Relevant available products and services, together with their 

characteristics; 

- The company s competitive position, and business objectives in this field; 

- How the intended procurement would help the company to achieve their 

business objectives; 

- Comments and suggestions for the preparation of the technical requirements. 

The dossier will be treated confidentially within ESA. Please submit it to 

the ASTE Programme Office, where it will be restricted to the team involved 

in the preparation of the ITT for the relevant activity. The information will 

be used to refine the scope of the activities and the applicable technical 

specifications. ITTs for ASTE activities are addressed to all Participating 

States of ARTES, i.e. all ESA member states, Canada and Portugal. Costs of 

activities carried out in a given state are charged against the contribution 

of that state to the ASTE Programme. Bidders are requested to make sure that 

their and their sub-contractor s delegations have confirmed, in due time, 

their willingness to support the activity in question. Attached to the cover 

letter accompanying their proposal, bidders shall therefore submit a 

statement signed by the delegate(s) representing the country in which the 

Prime Contractor (and if applicable, his Sub-contractor) reside(s), 

authorising the Agency to fund the proposal price from its (their) 

contribution to the ASTE Programme. 



Page 9 

CHANGED ITEMS 

The list that follows shows items, present in this booklet revision, 

that have changed the Action Reference number: 

02.226.01 changed to 02.126.03 

00.129.25 changed to 02.329.12 

02.153.45 changed to 02.353.18 

01.160.67 changed to 02.160.25 

02.160.16 changed to 02.360.19 

01.187.04 changed to 02.1ET.04 

01.195.01 changed to 02.195.01 

01.1EE.22 changed to 02.129.06 

02.1EP.04 changed to 02.3EP.03 

00.1ES.15 changed to 02.3ES.08 

01.1ES.03 changed to 02.3ES.05 

01.1QC.09 changed to 01.3QC.13 

97.1WA.02 changed to 02.3EM.06 



Page 10 

Ref. No. Title, summary and other information TT Q PP Price 

02.1AE.03 LONGER-TERM ACTIONS ON EO SERVICES (2-3) 

N4 

A total of 2-3 Longer-Term actions shall be started. These actions shall 

establish market acceptance of key EO-based services. The EO-based services 

shall take into account the capabilities that will shortly become available 

with Envisat. Each action shall be carried out for a limited number of 

marketable EO-based services associated with one of the thematic areas 

proposed by industry as follows :- - Water resources management, 

- Institutional disaster management services, - 1 additional EO thematic area 

defined by Industry. For each action, the following activities will be 

carried out :- - Fully integrate EO-based services of the Value-Adding 

industry into an established portfolio of operational geo-information 

services currently being provided to a large & stable group of existing users 

by a Market Owner. - Work in close co-operation with key authoritative users 

in assessing the benefit of EO-based geo-information, achieving market 

acceptance & growing the commercial sales of EO-based information. - Develop 

relationships within the EO supply chain to improve its functioning in the 

context of global markets. Each Longer-Term action will have a 

well-established long-term market potential and associated industrial 

investment, evidenced by a viable business plan. The ESA-sponsored activities 

will address issues, which industry or customers alone cannot reasonably 

resolve. The Longer-Term actions shall be carried out with companies drawn 

from the EO Value-Adding sector, Market Owners providing existing 

geo-information services & key potential customers. 

ESRIN EARTH AND ENVIRONMENT MONITORING FROM SPACE - D/EEM 

EO APPLICATIONS DEPT / EEM-A 

EXPLOITATION DEVELOPMENT & PROJECTS DIVISION / EEM-AE 

Responsible: MR DOHERTY 

Budget Ref.: 100779 - EOEP Data Exploitation/Market Dev 

C 02 

Q2 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+A+N+FIN+CDN 

Programme Ref.: LT_2002_1 

Status: 

02.1AE.06 DEVELOPMENT OF S/W TOOLS FOR ASAR COMMERCIAL 

EXPLOITATION 

DIPC > 500 

N4 

ESRIN 

1 Longer-Term action shall be started. This action shall take as input the 

results of an on-going activity within the EOMD program to define the 

business model to be adopted and the S/W functionality required for S/W tools 

to facilitate the commercial exploitation of Envisat ASAR. This study shall 

complete in the second quarter of 2002. The following activities will be 

carried out :- - analyse the defined S/W functionality and specify, design, 

implement, test, validate and deliver ASAR commercial S/W tools. - analyse 

the defined business model and implement the recommended scheme for access, 

distribution and exploitation of these S/W tools. 

EARTH AND ENVIRONMENT MONITORING FROM SPACE - D/EEM 

EO APPLICATIONS DEPT / EEM-A 

EXPLOITATION DEVELOPMENT & PROJECTS DIVISION / EEM-AE 


Budget Ref.: 100779 - EOEP Data Exploitation/Market Dev 

C 02 

Q4 


Programme Ref.: LT_2002_2 

Status: 

DIPC > 500 



Page 11 


02.1AE.12 STAGE 1 - SERVICE CONSOLIDATION ACTIONS OF THE 

EARTHWATCH GMES SERVICES ELEMENT (GSE) 

N13 GSE will be implemented in two partially overlapping stages • Stage 1: 

Consolidation of priority services and their user bases; preparation of the 

mid-term programme review • Stage 2: Setting up of service centres & delivery 

of operational services (for the implementation sequence see Annex 1 hereto). 

This procurement will address Stage 1. The services to be delivered under 

GSE are driven by EU environmental and security policies. They will make best 

use of the available EO systems (satellites ground segments and value-adding) 

and will also help establish the longer-term needs for future operational EO 

systems that can deliver policy-relevant information for the benefit of 

Europe’s citizens.The present state-of-art in Europe is that various 

companies, and institutions have already developed small-scale demonstration 

services, prototypes or elements thereof for specific application areas. Many 

have been funded under R&D programmes of ESA, individual member states or EC. 

Although none of these is today fully mature, robust or operational, they are 

the pre-cursors, upon which future GMES services will be developed. 

Considerable further long-term developments, scaling up and integration at 

European-level will be carried out within GMES in order to match end-user 

needs for services of sufficient operational performance, reliability, 

availability and affordability. The end users will be actively involved in 

this whole process to a degree that has not previously been achieved. They 

will have to refine their information and service needs in detail throughout 

the development and actively ensure via continuous testing & validation, that 

the adaptations and evolutions implemented genuinely respond to user 

needs.The scope of this procurement is to select and perform the necessary 

consolidation activities for a first set of GMES Services. In the first 

instance, this will start from the initial list of the thematic priorities 

that were spelled out by the GMES stakeholders ("A European Approach to GMES 

- towards meeting users needs"). As part of their proposal, bidders are 

invited to demonstrate the "maturity" of the specific service or service 

elements they propose to consolidate, with respect to the GMES Service 

assessment criteria agreed by PBEO and listed in the "GSE Public Information 

Note" (available on-line at http://earth.esa.int/gmes). This will be assessed 

as part of the technical evaluation of each proposal.It will be mandatory for 

each contract, that clearly assigned end-users take the lead on relevant work 

packages, including operational requirements, service-level definition, 

quality assurance, performance analysis, product & service validation, 

user-base definition, promotion & benefits analysis and sustainability 

assessment.Each contract of this procurement will deliver a complete set of 

consolidated technical and operational specifications for a specific GMES 

thematic service, including the associated user requirements, validations, 

cost-benefits analysis, case-use studies and promotional material. The 

total procurement will thus provide ESA with a full set of specifications for 

several (10-15) different GMES services. This will form the basis for stage 2 

of the programme. 

ESRIN 

DIRECTORATE OF EARTH OBSERVATION PROGRAMMES - D/EOP 

EO APPLICATIONS DEPT / EOP-A 

EXPLOITATION DEVT AND PROJECTS DIVISION / EOP-AE 


Budget Ref.: 100690 - Earth Watch - GMES 

C 02 

Q3 

Spec. Prov.: B+F+D+I+NL+E+S+CH+GB+A+N+FIN+CDN+GR 

Programme Ref.: 

DIPC > 500 



Page 12 

Status: ISSUED 1-4302 

02.1AE.13 DATA USER PROGRAMME PHASE II - 3RD CALL FOR PROPOSALS 

N22 

ESRIN 

The 3rd Invitation to Tender on the Data User Programme (DUP) Phase II will 

call for the development of two demonstration projects: -SLAM (Service for 

Landslide Monitoring) for major Italian and Swiss Institutional Users. - BeGO 

(Gorilla Natural Habitat Monitoring Service) in support to the UNESCO’s World 

Heritage Convention. The objective of the SLAM procurement is to develop an 

end-to-end service chain for the provision of Slope Instability products, 

derived from Earth Observation (EO) satellite imagery data, that will support 

the work of end-user governmental organisations in their institutional 

mandate of risk forecasting and prevention. Three SLAM products and services 

are required to be developed and demonstrated during the project: (1) 

Landslide Motion survey, (2) Landslide Displacement Monitoring and (3) 

Landslide Susceptibility Mapping. The BeGO project aims at developing 

user-oriented information products, based on EO technology, to support the 

implementation of the World Heritage Convention. In particular the project 

focuses on the development of base maps to support the work of the different 

national and international organisations involved in the conservation and 

monitoring of gorillas. These base maps will be used by UNESCO to promote the 

creation of local GIS systems to support conservation efforts. 



EXPLOITATION DEVT AND PROJECTS DIVISION / EOP-AE 


Budget Ref.: 100652 - Data Users Programme - Second Period 

C 02 

Q4 

Spec. Prov.: B+I+CH+NL 



DIPC > 500 



Page 13 


98.1CA.27 Q/V-BAND FRONT-END EQUIPMENT FOR FUTURE SATELLITE 

COMMUNICATIONS 

Future high capacity communication satellite systems will make increasing use 

of inter-satellite links, to allow for fully meshed communication within a 

single satellite network but also for extension into the global communication 

network infrastructure (GII). The proposed new-generation satellite systems 

include the use of V-Band frequencies for intersatellite, and Q-Band for 

space-to-ground links. The development of a number of front-end equipment for 

these frequencies is required. The first development to be initiated in 2000 

will be a Q/V-band receiver. 

ESTEC APPLICATION PROGRAMMES - D/APP 

TELECOMMUNICATION DEPT / APP-T 

ARTES & NEW PROJECTS DIVISION / APP-TN 

Responsible: MR SANDBERG 

Budget Ref.: 100415 - ARTES 5 ASTE 3 

C 01 

Q4 

Spec. Prov.: B+F+D+I+E+NL+S+CH+IRL+A+N+FIN+POR+CDN 

Programme Ref.: ASTE GI 4.2 

Status: EX ITEM 97.1CS.04 TO BE RE-ISSUED 1-3940 

98.1CA.36 INVESTIGATION OF HIGH FREQUENCY PROPAGATION 

IMPAIRMENTS 

DIPC > 500 

ESTEC 

The purpose of this activity is to convert existing Olympus receivers to the 

frequencies used on ITALSAT, deploy and operate these receivers to collect 

data at 20/40 and 50 GHz and use the results for refining the propagation and 

interference prediction methods. 

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Important message: please read page 8. 

APPLICATION PROGRAMMES - D/APP 





C 02 

Q2 

Spec. Prov.: B+F+I+E+NL+S+CH+IRL+A+N+FIN+CDN+POR 

Programme Ref.: ASTE FB 2.2 

Status: EX ITEM 96.1TS.02 

DAC 200-500 



Page 14 


98.1CA.43 COMMERCIAL MICROELECTRONICS FOR COMMUNICATION PAYLOADS 

This activity will study and select design techniques and packaging 

techniques to improve the performance of commercial microelectronics for use 

in the space environment to be more competitive with U.S. technologies. A 

design will be implemented using the selected techniques and the performance 

will be verified under radiation. In order to optimise the outcomes of this 

activity a partnership between an equipment manufacturer and a semiconductor 

manufacturer will be established to carry out the work. 

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ESTEC 






C 01 

Q4 


Programme Ref.: ASTE CS6.1 

Status: EX ITEM 97.1CS.07 ON HOLD 1-3353 

DAC 200-500 



Page 15 


99.1CA.04 HIGH EFFICIENCY SSPA FOR ACTIVE PHASED ARRAYS 

SSPA’s are strategically important for future mobile communication, UMTS/ IMT 

2000. Exploiting the switched mode concept demonstrated under ASTE activity 

NM 4.3 could be a break-through for the satellite transmit front-end and give 

a leading edge to European industry. The amplifier performance achieved in 

this activity is well beyond the state-of-the-art technology; the high 

efficiency will lead to significant power saving, and ultimately lower system 

cost in next-generation mobile satellite communications. Satellite payloads 

for the next generation mobile communication, UMTS or IMT 2000, will be 

equipped with Active Phased Array Antennas (AAA) composed of hundreds of 

Transmit/Receive Modules (TR Modules), each containing a Solid State Power 

Amplifier (SSPA). Apart from the arrays themselves the SSPA’s are the most 

critical elements in the RF front-end of these advanced mobile payloads. 

Their Power Added Efficiency (PAE) and linearity are essential parameters in 

the end-to-end system which determine the feasibility of the overall concept 

and the system complexity. The so-called "switched mode" concept, employing 

harmonic matching allows improvement of these parameters and is therefore one 

of the most promising amplifier candidates which will be exploited in the 

proposed activity. Preliminary work on this concept, focused on terrestrial 

applications, has been performed under ASTE activity NM 4.3 by Hirschmann 

(A). Prototype amplifiers were built and tested with excellent efficiency 

(PAE > 70 %), high power gain, good linearity and improved reliability, which 

demonstrates the feasibility of the switched mode concept. The amplifier 

appears to be appropriate for single carrier operation, and due to its 

intrinsic linear performance, also for multi-carrier applications. The main 

objective of the proposed activity is to develop a space qualified product in 

modular fashion to make the amplifier easily adaptable to different 

applications and a range of RF power levels (from 1 W to 20 W). Since 

harmonic matching will be frequency limited, it is necessary to investigate 

the extreme upper limits with today’s device technology. 

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ESTEC 






C 02 

Q2 


Programme Ref.: ASTE MS 4.1 

Status: INITIATED 1-3619 

DIPC > 500 



Page 16 


99.1CA.06 ON-BOARD EQUIPMENT FOR SUPERCONDUCTOR BASED SATELLITE 


High temperature super-conducting (HTS) materials, operating at temperatures 

in the order of 77K, were discovered in 1986 and have made possible the 

potential wide application of microwave circuits, based on HTS technology, to 

communication devices. In particular, single stage cryo-coolers are 

sufficient to support the HTS application to communication satellite 

payloads, fostering therefore a potential breakthrough in this market 

segment. HTS technology is competitive on size and weight reduction of 

communication payloads, since HTS devices themselves are extremely compact 

with respect to conventional components. However, HTS based end-to-end 

communication satellite systems would only be competitive if extremely 

compact and lightweight cryo-coolers are used possessing a reliability 

compatible with a 15 year satellite lifetime and a very high efficiency (for 

low electrical power demand). At present the best cryo-cooler efficiency is 

of the order of 15 We/Wt for a heat rejection to a 300K environment. This 

severely limits the size of the HTS payload that can be effectively installed 

and prevents high dissipative HTS systems from becoming competitive. The 

solution to this restriction would be to provide a much colder environment, 

say 150K, in which the HTS devices could operate. Such an environment would 

even make passive cryo-cooling a viable option which would enormously 

increase the competitiveness of this technology. To achieve such an 

environment for the HTS devices would necessitate a radical change to the 

presently accepted communications satellite concept. An innovative design 

would be necessary which not only provided a "cold" satellite for the HTS, 

but also provided the more usual environment for the other traditional 

supporting satellite platform equipment. A study is currently being initiated 

under ARTES-1 in order to confirm the potential of this approach, which may 

then significantly expand market opportunities for HTS technology in space. 

This study will identify the availability of qualified components, equipment 

and subsystem items as well as identifying the critical technology 

development needs. Based on the result of the ARTES-1 study and assuming its 

positive outcome, it is proposed under this ASTE activity to develop the 

identified critical technologies for selected on-board applications, 

including cryogenic coolers and the HTS devices themselves. In the first 

phase prototypes of the "cold" satellite payload equipment and, to the extent 

possible, required platform features for these applications will be designed, 

manufactured and tested. In the second phase the equipment will be built and 

tested to Engineering Qualification Model level. 

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ESTEC 






C 02 

Q4 


Programme Ref.: ASTE CS 11.4 

Status: 

DIPC > 500 



Page 17 


00.1CA.08 NEW-GENERATION KA-BAND TWTA 

This activity is to develop to EQM level a new-generation TWTA at Ka-band to 

prepare for the requirements of future Ka-band missions. Features of this new 

TWTA are: * high output power (200 W) * High efficiency * constant RF/DC 

power efficiency over a range of output power * Built-in linearity 

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C 02 

Q2 



Status: 

00.1CA.10 "PRIVATE MOBILE SATELLITE RADIO" NETWORKS FOR SAFETY 

AND SECURITY RELATED APPLICATIONS 

DIPC > 500 

ESTEC 

Several mobile communication applications for data as well as voice exist 

which require: * Gap-free geographical coverage country wide * A large number 

of user stations, each of which with rather low average traffic * High 

availability and low response time These applications tend not to be served 

adequately by public networks due to both geographical coverage and 

availability limitations. Therefore, dedicated terrestrially-based networks 

are generally used. A satellite-based network seems to be an attractive 

solution from both the technical and economical point of view to provide a 

gap free geographical coverage. The objective of the work is to make a 

detailed survey of requirements and current solutions for this type of 

applications in co-operation with prospective end users. With the results of 

this survey, a feasibility study will be performed. If this indicates a 

potential market, a preliminary system design will be performed, and a 

service demonstrator implemented. This demonstrator will likely be based on 

existing technology and system elements. 

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C 02 

Q2 



Status: 

DIPC > 500 



Page 18 


00.1CA.18 LOW COST SOLAR ARRAYS 

The activity aims at developing solar array configurations compatible with 

the use of low cost solar cells such as amorphous silicon cells. Standard 

rigid supporting structures are too heavy for this type of very thin cells 

thus new lightweight structural designs will be developed as well as flexible 

solar array configurations like the Olympus solar array. Phase 1 will cover 

the definition of array configurations, supported by elementary testing to 

demonstrate the compatibility between the solar cells and the structures. 

Phase 2 will cover detailed design and qualification at component level, and 

phase 3 manufacturing and testing of a full wing. 

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C 02 

Q2 



Status: 

00.1CA.21 FIBRE OPTIC GYROS (FOG) 

DIPC > 500 

ESTEC 

The proposed activity aims to build a three-axis gyro system for 

geostationary communication satellites, for normal and emergency modes. After 

an initial trade-off study on mass, volume internal redundancy and cost, an 

engineering qualification model of a fibre gyro assembly will be designed and 

built. ****************************************************************** 

****************************************************************** 







C 02 

Q2 



Status: 

DIPC > 500 



Page 19 


00.1CA.26 COAXIAL CABLES AND CONNECTORS FOR L/S-BAND HIGH-POWER 

PAYLOADS 

1) The ease of installation has made the use of coaxial cables very popular 

in modern communication systems. One of the major sources of Passive 

Intermodulation Products (PIM) may be the coaxial cables and the associated 

connectors due to non-linear properties at microwave frequencies resulting 

from insufficient contact pressure. The goal of the study is to achieve 

cables designed and manufactured with tougher mechanical construction and 

connectors that are reliably sealed and provide good electrical performance 

over the long term. 2) The development of RF flexible assemblies (connector 

and cable) capable to handle high power signals, both pulsed and CW will be 

pursued at several frequency ranges for operation in space. Several 

connectors will be investigated (SMA, TNC, N-type and K-type). Low insertion 

and return loss and venting of the assembly to eliminate the risk of Corona 

will all be considered. 

****************************************************************** 

****************************************************************** 


ESTEC 






C 02 

Q2 



Status: 

DAC 200-500 



Page 20 


99.1EE.01 QUANTUM WELL INFRARED PHOTOCONDUCTOR ARRAYS 

N12 

ESTEC 

00.1EE.02 

ESTEC 

Thermal-infrared Earth-observation instruments need generally spectral 

channels near 12 microns for accurate temperature measurements. At this 

wavelength, long HgCdTe arrays developed for pushbroom instruments show 

technological limitations, leading to performance non-uniformities and the 

need to segment the array in butted modules. Quantum Well Infrared 

Photoconductor (QWIP) detectors have recently emerged as a promising 

alternative to the more established infrared detector technologies such as 

HgCdTe or InSb at the expense of a slightly lower operating temperature, 

AlGaAs/GaAs superlattices can be used to produce large detector arrays with 

high uniformity, at a wavelength adjustable in the mid- and thermal-infrared 

ranges, and at a lower cost due to the maturity of GaAs technology. The 

objective of the proposed activity is to demonstrate the capabilities of QWIP 

technology with a long linear array (ie 512 or 1024 elements) in the 

11.5-12.5 micron spectral band. 

TECHNICAL & OPERATIONAL SUPPORT - D/TOS 

ELECTRICAL ENGINEERING DEPT / TOS-E 

ELECTROMAGNETICS DIVISION / TOS-EE 

Responsible: MR ROEDERER 

Budget Ref.: 100061 - Techno Res/Core Activities 

C 02 

Q3 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+IRL+A+N+FIN+POR 

Programme Ref.: TRP 97/XAO08 

Status: EX ITEM 99.1XA.05 ISSUED 1-3647 

CHARACTERISATION AND MODELLING OF PROPAGATION EFFECTS 

IN 20-50GHZ BAND 

The new telecom systems have requirements that cannot be presently assessed 

by available propagation models. This study will develop and validate 

propagation and frequency co-ordination models and characterise the 

propagation channel in the frequency band 20 to 50 GHz. 






C 02 

Q2 


Programme Ref.: TRP EEP-009 

Status: 

NO 100-200 

DAC 200-500 



Page 21 


01.1EE.01 LASER DOPPLER INTERFEROMETRY MISSION FOR EARTH GRAVITY 

The objectives of the activity shall be: - to determine the scientific 

objectives of a laser Doppler interferometry mission capable to monitor the 

variations of the Earth’s Geoid over a long period of time, - to perform a 

preliminary definition of the Laser Doppler Interferometry mission (mass of 

spacecraft, distance between spacecraft, altitude of orbit altitude, altitude 

drop, duration of mission, etc.) capable to meet the scientific objectives, 

and to derive the required set of ranging performances and characteristics 

for the laser Doppler metrology system, - to study a suitable Laser Doppler 

metrology system, assess its critical problems areas, and define a technology 

development programme addressing the critical technical and technological 

issues, - to refine the definition of the Laser Doppler interferometry 

mission and produce a very first design of the spacecraft with all the 

necessary functions for its proper operation. 

ESTEC 





Budget Ref.: 100060 - General Studies 

C 02 

Q2 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+IRL+A+N+FIN+POR+CDN 

Programme Ref.: GS 01/S42 

Status: 

DIPC 200-500 



Page 22 


01.1EE.02 ASSESSMENT OF THE VALIDITY RANGES OF MICROWAVE 

INTERACTION MODELS 

The amount and the complexity of present and future microwave measurements 

(multi-incidence, multi-polarisation, passive interferometric, bi-static, 

polarimetric) makes the use of surface (land / sea) interaction models 

critical for the understanding of the signal and the development of inversion 

algorithms for applications. Such interaction models have been studied for 

years and are available for a wide range of surface types (bare soils, 

vegetation, ice, sea). However, their validity range is most of the time not 

clearly defined and is re-discovered when experimental data are acquired. 

This validity range of interaction models is however critical, especially as 

some of the models recursively use the results of others (e.g. models to 

simulate the emissivity of surfaces are based on models for bistatic 

scattering coefficients). Issues such as large incidence angle, energy 

conservation jeopardise the results of such complex models. The intended work 

consists in analysing the electromagnetic validity of the existing 

interaction models. For each kind of model (land, sea, surface, volume), 

validity criteria should be derived based on the electromagnetic hypothesis 

required by the model. These electromagnetic criteria should in a further 

step be converted into requirements on the surface description. Issues such 

as energy conservation in radiative transfer, scattering at grazing angles 

and its impact on emissivity simulations, coherent and incoherent 

contributions in the scattering, should be investigated based on theoretical 

developments as well as on controlled experimental measurements. A 

comprehensive repository of microwave models able to predict most types of 

interactions should be built, including conclusions on the errors expected in 

the model-based simulations. This is a necessary step to enable a safer use 

of interaction models for prediction or retrieval. 

ESTEC 






C 02 

Q3 




DIPC 100-200 



Page 23 


01.1EE.04 FREQUENCY MONITORING AND PROPAGATION EXPERIMENT 

PACKAGE 

Relevance: - Measuring the intensity of the earth man-made electromagnetic 

emission in orbit and to assess its effect on satellite performance 

integrity. - Monitoring that frequency allocations are respected. - 

Performing ionospheric propagation experiments, using intentional emitters 

already existing on ground, in order to characterise de facto the propagation 

channel and validate the inherent channel models that are presently used for 

planning satellite systems (see Rec. ITU-R P.531-5 ). The scope of this 

proposal is to study the feasibility of a payload capable of carrying out the 

mission described in the paragraph II, requiring limited spacecraft 

resources, in order to be attractive for mini-satellite applications. The 

payload is meant to cover the bandwidth 9 MHz - 40 GHz and concerns two 

sensor technologies that are anticipated to provide the cheapest solution in 

terms of spacecraft resources: a) An electro-optical sensor based on a Mach 

Zehnder modulator, which measures time domain E-fields with bandwidth up to 1 

GHz. The signal detected is sampled with an A/D converter and, subsequently, 

the FFT is performed giving the spectral content of the field detected; b) A 

TEM-fed parabola operating in the range 1 GHz - 40 GHz and above, connected 

via a semi-rigid coaxial cable to a RF receiver emulating the function of a 

spectrum analyser. The obtained data shall be then telemetred to the earth. 

Both the above-described sensor technologies described are already existing 

and available, but they have been used for domains of applications other than 

space. Regarding the fast data acquisition for the electro-optical sensor, it 

is worth mentioning that D/TOS-EEE has designed a 1 Giga Sample Per Second 

(GSPS) data acquisition system for space application that is presently fully 

operational is situ with the DDE experiment. In addition to the design of the 

payload and to the definition of the spacecraft resources that would be 

needed, the study shall cover also a minimum of mission analysis and 

eventually inverse algorithm that could be applied to perform the ranging. 

Please refer to the excerpt of the mentioned ITU recommendation for a deeper 

insight on the utility of this experiment. 

ESTEC 






C 02 

Q2 


Programme Ref.: GS 01/A35 

Status: 

DIPC 200-500 



Page 24 


01.1EE.06 SYSTEM APPLICATIONS AND REALISATION OF NOVEL 

DEPLOYABLE ANTENNA CONCEPTS FOR FUTURE DEVELOPMENT AND 

TEST 

In the current ARTES-5 Programme, the Agency is intending to develop a large 

deployable reflector Antenna to be used for Mobile Telephony Missions and 

Satellite UMTS. These antennas operating in either L- or S- Band will be 

capable of achieving aperture sizes of up to 25 metres. Beyond this specific 

development there are a number of possibilities to use deployable antennas 

for future missions, both for realising large apertures on large satellites 

or for realising moderate aperture sizes on small satellites within a small 

launcher envelope. For instance, D/APP is considering the in-orbit 

demonstration of telecommunication payloads on small satellites utilising EQM 

equipment from their technology development programmes. In addition to 

reflectors there are a number of other solutions, such as artificial 

dielectric lenses, reflect-arrays and deployable arrays that could be 

considered for future missions. The study shall consist of an assessment of 

future mission possibilities, for a range of satellite sizes, a range of 

novel antenna solutions shall be studied and the deployment methods as well 

as the electrical performances shall be traded-off and assessed. 

Opportunities for in-orbit demonstration and shall be studied and defined, 

including ISS and the application as an enabling technology for payload 

demonstration on small telecommunication or earth observation missions using 

for example a SMART type satellite. The output will be the definition of the 

design and development plan, including in orbit demonstration and test of the 

most promising concepts. 

ESTEC 






C 02 

Q2 


Programme Ref.: GS 01/N17 

Status: 

DIPC 100-200 



Page 25 


01.1EE.09 FAST OPTICAL RATE SENSOR - ENHANCEMENT OF EXISTING 

STAR SENSOR OPERATIONAL MODES 

Star sensors, used for attitude measurement on many spacecraft, have an 

additional, but limited ability to cope with and measure angular slew rates 

due to spacecraft rotations. Beyond a very few degrees per second, current 

sensors lose their ability to either tolerate or usefully measure these 

rates. The activity will: 1. Study of hardware and algorithm adaptations to 

existing star sensor designs needed to provide capability of slew rate 

measurement at significantly higher rates than currently possible; 2. 

Implementation of identified adaptations in hardware and software, to 

validate and evaluate fast rate performance; 3. Testing of performance in 

dynamic conditions. Type of tender C(2) - activities in open competition, 

where a significant participation of non-primes is requested. For additional 

information please go to EMITS news "Industrial Policy measures for 

non-primes, SMEs and R&D entities in ESA programmes". 

ESTEC 





Budget Ref.: 100947 - GSTP Phase 3 

C 02 

Q2 

Spec. Prov.: B+I 

Programme Ref.: GSTP-3 G00/B31.EEO-029 

Status: 

DIPC > 500 



Page 26 


01.1EE.10 OPTICAL BEAM FORMING AND DISTRIBUTION NETWORK (OBFDN) 

FOR PHASED ARRAYS 

The evolution of telecom (and radar) antennae has clearly been from single 

transmitters (and/or receivers) to active arrays combining high flexibility / 

reconfigurability and reliability via fault tolerance and redundancy. It is 

the significant cost, weight & volume and the limitations in size x bandwidth 

of electronic Beam Forming and Distribution Networks (BFDN) which has 

prevented their widespread use in space. These disadvantages are elegantly 

overcome by realizing the BFDN functions in optical technology. World-wide 

developments of photonic control of phased arrays have produced several 

architectures/solutions for different classes of requirements and have 

reached a considerable level of maturity. Significant advances have been 

achieved in industry especially in components technology needed to build 

optical beam forming systems with truly competitive performance, and to take 

this technology out of the laboratory into the field: - Optical phase locked 

loop transmitters based on semiconductor diode lasers, with phase noise 

performance fully compatible with QPSK satcom systems standards and also with 

turnkey peration (frequency acquisition, lock monitoring, etc.); - GaAs 

photonic integrated circuits for optical beam forming control, incorporating 

phase and amplitude weighting and 16-way signal distribution; - 

Opto-electronic integrated circuits for loss-less signal splitting; - GaAs 

modulators specially designed for integration into receive/transmit modules, 

i.e. with RF and optical interfaces at opposite ends of the chip without 

compromising RF performance up to 20GHz; - Highly compact optical receivers 

for integration into phased array antenna structures; - Computer interfaces 

and software algorithms for beam control. The objective of the present 

activity is to develop a technology demonstrator OBFDN for a > 200 element 

phased array. The activity is divided in three main tasks: - System study / 

selection of best suited scheme given actualized specifications; - 

development of a specific breadboard/engineering model; - preparation of a 

roadmap for future space-qualification. 

ESTEC 






C 02 

Q2 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/D57.EEO-014 

Status: 

DIPC > 500 



Page 27 


01.1EE.11 OPTICAL A/C CONVERTER FOR SPACE APPLICATIONS 

Analog-to-Digital Converters (ADC) are employed in large numbers in satellite 

payloads. ADCs are required for processing signals either received from 

ground (standard telecommunications uplink signals) or generated by onboard 

instruments. Commonly the ADCs processing the uplink telecomm signals operate 

at the transponder bandwidth (BW) of 36 MHz at sampling rates of about 2.5 

times this of the higher frequency to be sampled (for threshold sampling). 

For higher resolution (8 or more bits) the sampling rate has to increase 

correspondingly reaching 1 Gsps. Current electronic ADCs operate at 

frequencies up to several hundreds of Msps limited in BW and in resolution by 

the clock signal jitter. For higher sampling rates and resolution other 

approaches have to be employed. High frequency instruments as well as high 

throughput communications uplinks require sampling at multigigasamples rates. 

Optical ADCs are developed for applications in defense systems. Adaptations 

can be made for their applications on space-borne platforms targeting 

primarily in achieving optical sampling of very weak signals received from 

ground. Optical technologies can provide immense advantages including:- Ultra 

low jitter clock source using mode-locked lasers of femtosecond pulses; - 

Very high sampling rates up to 100 GHz using optical modulators and WDM 

techniques; - Serial to parallel conversion for input to the quantizer with 

the possibility of extending also in other functions. Such a performance is 

beyond what is currently achieved by any kind of electronic ADC. The power 

consumption of the entire device can potentially be kept in lower than the 

electronic counterparts levels if it is designed to serve a particular 

frequency band as it is the case for space applications (and as opposed to 

broadband operation from kHz to GHz).The objective of this activity is to 

examine new techniques of implementing an ADC based on photonic technologies 

and develop a space application-specific prototype. Photonics will be 

considered for most of the functions involved in the ADC (the clock, 

sampling, serial to parallel input conversion for the quantizer etc). The 

photonic ADC will operate in many Gsps sampling rate demonstrating ultra-low 

clock signal jitter, and low driving RF input required for the optical 

sampler. Type of tender C(1) - activities in open competition limited to 

non-primes. For additional information please go to EMITS news "Industrial 

Policy measures for non-primes, SMEs and R&D entities in ESA programmes". 

ESTEC 






C 02 

Q2 

Spec. Prov.: 


Status: 

DIPC 200-500 



Page 28 


01.1EE.12 MULTIGIGABIT OPTICAL BACKPLANE INTERCONNECTIONS 

Optical backplane technology can accommodate any future requirement in 

interconnections and without any EM interference. The technology has received 

the attention of the computer manufacturing industry while the space industry 

has already identified optical backplanes as the enabling interconnection 

technology for high bit rates requirements such as in SARs and digital 

processors. The result of these activities is the development of low cost 

devices (such as VCSE lasers) which can readily be used for high BW 

interconnections. The proposed activity will push further the development 

effort to a space-qualified for space-specific application prototype and 

investigate novel approaches such as multiwavelength interconnection. High 

resolution scientific instruments like the Synthetic Aperture Radars as well 

as high speed digital processor in communications are expected to operate at 

data rates in excess of 1 Gbps. Current architectures based on IEEE standards 

employ links which are limited to transfer rates at some hundreds of Mbps. 

New interconnection technologies have to be adopted able to convey data at 

Gbps speed and be EM interference resistant. The objective of this activity 

is to demonstrate the applicability of optical backplane interconnections 

operating at speeds of several Gbps in space-specific electronic modules. The 

activity will study all the technological and interfacing issues including 

heterogeneous integration, parallel interconnection through Wavelength 

Division Multiplexing and prepare a prototype using space-worthy 

technologies. 

ESTEC 






C 02 

Q2 

Spec. Prov.: B 


Status: 

DIPC 200-500 



Page 29 


01.1EE.13 MICROPHOTONIC BEAM FORMING NETWORK FOR SPACE-BORNE 

PHASE ARRAY ANTENNAS 

Photonic technologies are EMI free and can accommodate very high bandwidth. 

They are also lightweight and low power consumption devices. For these 

reasons they have been considered for applications in space-borne BFNs. 

Microphotonic devices based on Spatial Light Modulators or 

Microeletromechanical Mirror Matrices can form a very compact BFN able to 

provide many meters of true time delay with a delay resolution of 1mm. In 

addition these devices can be reconfigurable very fast, as required in earth 

scanning radar applications. BFN constitutes a new application for these 

technologies that are currently under intense development due to their 

potentials as switches in fiber optic backbone networks. The space industry 

has developed in the past SLMs matrices as an RF/IF circuit switch. The 

objective of this activity is to demonstrate the feasibility of achieving 

agile beam forming using microphotonic technologies in a very compact and low 

power configuration. The activity will study possible alternatives based on 

Spatial Light Modulators and Microelectromechanical Mirror Matrices -MMMs and 

will lead to a prototype of a beam forming network tailored for space phased 

array antennas. The activity shall also demonstrate the space-qualification 

of MMMs. 

ESTEC 






C 02 

Q2 

Spec. Prov.: 


Status: 

DIPC > 500 



Page 30 


01.1EE.14 OPTICAL LINKS FOR THE SPACEWIRE INTRA-SATELLITE 

NETWORK STANDARD 

Fiber optics can essentially accommodate any required data throughput. They 

are also inherently lightweight, flexible in handling, low power consumption, 

are not affected by EMI and have the capacity of accommodating many 

individual parallel connections in a single fiber through wavelength division 

multiplexing. The need for separate cables for each connection in the 

intra-satellite network leads to high degree of parallelism in connectivity 

which in turn results in massive cabling. Consequently, there is a great 

scope in exploring the benefits of adopting fiber optics as the preferred 

transmission medium not only for the high speed links (where they are the 

only solution) but also for the lower bit rates links when the mass, size and 

power consumption are taken into account. The space community has already 

identified the limitations associated with the use of copper cables and 

initiatives aiming at incorporating fiber optics in the intra-satellite 

network standards have been taken primarily in the USA. Given that ESA 

currently leads the effort for a unified standard for intra-satellite 

networks, there is great scope in running an activity that will cover all the 

issues of introducing fiber optic links in a more generalised way than other 

similar standards. The objective of this activity is to study the 

implementation issues of using optical fiber links in a SpaceWire compliant 

intra-satellite network. A prototype of an opto-electronic transceiver 

interface based on the SpaceWire standard (including physical connection and 

logical signal formatting aspects) will be built, and Gbps transmission will 

be demonstrated. Compact and potentially inexpensive transceiver interfaces 

will be manufactured. The activity will also study the possible extension of 

fiber optic cabling in lower communication rate links with respect to 

potential mass, size, physical flexibility and power consumption advantages 

over copper cabling. Techniques like wavelength division multiplexing will be 

investigated as a means to significantly reduce the massiveness of cable 

parallelism dictated by copper connections. 

ESTEC 






C 02 

Q2 

Spec. Prov.: 


Status: 

DIPC 200-500 



Page 31 


01.1EE.20 PHOTONIC DEVICES FOR MULTI-APERTURE FIBER-LINKED 

A multi-aperture fibre-linked imaging interferometer is one of the most 

promising design options for a low-cost realisation of large aperture 

space-based telescopes. The objectives of this activity are to determine a 

first optical layout design of a multi-aperture fibre-linked imaging 

interferometer fully implemented in "integrated optics", to study and 

assess, through experimental investigations, the best integrated-optic design 

of all the optical functions of this optimum optical layout and the various 

methods and means to up-convert coherently an infrared (IR) signal, and 

launch it into a fibre. Another aim is to refine the "integrated optics" 

optical layout design of the multi-aperture fibre-linked imaging 

interferometer, and elaborate a development programme leading to the 

demonstration of a new generation of low-cost, large aperture space-based 

telescopes. Type of tender C(2) - activities in open competition, where a 

significant participation of non-primes is requested. For additional 



ESTEC 

01.1EE.21 

ESTEC 






C 02 

Q3 


Programme Ref.: TRP EEO-037 


TUNABLE FREQUENCY STABILISATION SCHEME 

The object of this activity is to develop a tuneable, highly stable, 

feeder/oscillator as a building block for a high-energy solid state laser 

system (cf. miniproject). Sub-activities include The evaluation of the 

different stability requirements and tuning range, identification of a 

unified approach and the development of one (or two if two technologies 

identified/ needed) breadboard demonstrators of the scheme(s). Furthermore, a 

detailed design of the breadboard should be completed. Type of tender C(1) - 

activities in open competition limited to non-primes. For additional 








C 02 

Q2 




DAC 200-500 

DAC 200-500 



Page 32 


01.1EE.22 SMART PANORAMIC OPTICAL SENSOR HEAD 

By designing a sensor head with a "smart retina", it is possible to employ a 

simpler, lightweight panoramic lens, and then to correct the inevitable 

distortions and image degradations by means of processing the detector 

array’s image data. The aims are to design, build a breadboard demonstration 

smart panoramic optical head and to validate the principle for a range of 

sensor applications. Type of tender C(2) - activities in open competition, 




ESTEC 

01.1EE.23 

ESTEC 






C 02 

Q2 



Status: CHANGED TO 02.129.06 

MEASUREMENT OF VERY LOW SIDELOBE ANTENNAS 

Increasingly Earth Observation and astronomy missions are requiring highly 

accurate measurements of the performance of very high efficiency antennas 

with very low side lobes. The objective of this activity is to assess the 

implications of using existing facilities and antenna measurement techniques 

for the measurement of such antennas, taking into account the necessary 

required accuracy for the measurements, the possible facility error sources 

and techniques to either minimise or compensate for these errors. 






C 02 

Q2 


Programme Ref.: TRP EEE-003 


DIPC 200-500 

NO 100-200 



Page 33 


01.1EE.24 NOVEL TECHNIQUES FOR GENERAL ANTENNA CHARACTERISATION 

IN THE TIME DOMAIN 

Time domain measurements techniques developed for wide band antennas, can be 

extended to further exploit the capabilities of pulsed antenna measurements. 

This would include direct measurement of chirped antennas and the measurement 

of the pulse response of an antenna in a Compact Range. This activity 

consists of the identification of existing pulsed antenna measurement 

techniques and their limitations, the definition of tools needed for 

characterising, both the pulsed operation of the antenna and the measurement 

of chirped antennas, and the implementation and testing of a typical pulsed 

antenna. 

ESTEC 

01.1EE.25 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP EEE-006 

Status: 

SPACECRAFT EMI CONTROL IN THE PRESENCE OF COMPOSITE 

MATERIALS 

Traditionally spacecraft construction has relied on metal or metal honeycomb 

structures that provide good shielding behaviour. The future use of composite 

materials will not have such performance from an Electro-Magnetic 

Compatibility (EMC) point of view and the consequences on the EMC performance 

of the system will have to be carefully evaluated in light of the actual 

performance of the composite material. The objective of this activity is to 

provide a characterisation of the shielding performance and the transfer 

impedance of target materials, develop measurement techniques, and develop 

necessary analytical tools for EMC performance evaluation. Type of tender 

C(2) - activities in open competition, where a significant participation of 

non-primes is requested. For additional information please go to EMITS news 

"Industrial Policy measures for non-primes, SMEs and R&D entities in ESA 

programmes". 






C 02 

Q2 



Status: 

DAC 200-500 

DAC 200-500 



Page 34 


02.1EE.01 TECHNOLOGIES FOR OPTICAL PAYLOADS 

The advantageous use of optical technologies offers the possibility of 

implementing new payload architectures operating at very high bandwidths, and 

a technology shift similar to the transition from microwave inter-satellite 

links to optical ones. The mass volume and power requirements can 

significantly be reduced by applying advanced optical techniques and devices, 

including fiber, integrated and bulk optics. Breadboarding of selected 

technologies shall be performed. The study will be complementary to TRP 

activity 94/2.1.6.5. Type of tender C(2) - activities in open competition, 




ESTEC 

02.1EE.03 

ESTEC 






C 02 

Q4 



Status: 

Q/V BAND ANTENNA SUBSYSTEM FOR MEO-GEO MISSIONS 

The aim of this activity is to develop and pre-design critical technologies 

for Q/V band antennas in Medium Earth Orbit (MEO) or Geostationary Earth 

Orbit (GEO) missions. This study will be targeted to two main areas, the 

study and pre-design antenna solutions, including the development of required 

specific modelling tools and will also address the critical areas identifying 

potential solutions, trade-off and breadboard them, in order to prepare the 

ground for further consolidation work. Type of tender C(4) - activities 

subject to SME subcontracting clause. For additional information please go to 

EMITS news "Industrial Policy measures for non-primes, SMEs and R&D entities 

in ESA programmes". 






C 02 

Q4 


Programme Ref.: TRP EEA-013 

Status: 

DAC 200-500 

DAC 200-500 



Page 35 


02.1EE.05 NON-VOLATILE OPTICAL MEMORY 

One major problem in Solid State Recorders (based on Dynamic Random Access 

Memories (DRAMs)) is the necessity for keep-alive power. The main attraction 

in any alternative optical memory offering very high densities is a feature 

of non-volatility. The aims of this activity are to assess the 

maturity/suitability of non-volatile optical storage technologies for space 

use and identify the best candidate for a future pilot flight demonstrator. 

The latest developments in holographic storage and magneto-optical devices 

should be assessed in order to identify the best candidate technology. A 

test-set up shall be developed, in order to evaluate performance and identify 

critical areas of the candidate technology. 

ESTEC 

02.1EE.06 

N3 

ESTEC 






C 02 

Q4 



Status: 

MEMS TECHNOLOGY FOR TERMINALS AND SATELLITE ANTENNAS 

In recent years, micro electromechanical systems (MEMS) have gained the 

interest of the microwave community, and have been used to realise innovative 

phase shifters, on-chip passive components for wireless applications, and 

their applications to re-configurable antennas have been proposed. The 

objective of this activity is to assess potential advantages and limitations 

of MEMS for antennas of a broad range of space related applications in the 

medium to long term. (Satellite antennas and (mobile) user terminals). 

Sub-activities include bread-boarding of critical components and definition 

of a demonstrator model. 






C 02 

Q4 




DAC 200-500 

NO 100-200 



Page 36 


02.1EE.07 GEO ATMOSPHERIC SOUNDER TECHNOLOGY PROJECT 

N21 

ESTEC 

The primary advantage of remote sensing from GEO orbit, as opposed to 

Low-Earth (LEO) orbit, is that continuous monitoring is possible over a large 

area of the Earth’s surface and atmosphere, which allows the observation of 

real-time events. A preliminary review of potential (GEO) missions, based on 

preferred geophysical parameters, gave consideration to three main 

application areas for GEO sounding: numerical weather prediction, climatology 

and nowcasting. In contrast to LEO microwave sounders in operation today, the 

proposed "straw man" GEO instrument uses many more channels ranging 

potentially in frequency from 89 GHz through to 874 GHz. From GEO orbit, the 

best sounding technique would appear to be the use of spectroscopy / 

interferometry in the Thermal Infra-Red (TIR) spectral region as it implies 

an aperture of reasonable size even for high horizontal resolution. However, 

the quality of TIR observations sharply degrades in cloudy areas, preventing 

useful retrieval of atmospheric parameters for weather models. Observations 

in the microwave region, going up to submillimeter-wave frequencies, are less 

affected by the presence of clouds, and can be used to fill the gaps of TIR 

observations as described above. Due to the large aperture size required to 

achieve a reasonable horizontal resolution, its use so far has been 

restricted to the case of LEO satellites. The main challenges are the 

realisation of the antenna with a size compatible with the required spatial 

resolution (40 fold increase in the distance to the Earth as compared to the 

LEO) and the implementation of two-dimensional scanning necessary in the 

absence of a relative spacecraft-Earth movement. Furthermore, the wide 

frequency range is challenging from the point of view of focal plane assembly 

and receiver technologies. The objective of this activity is the design, 

manufacturing, and demonstration by test of these innovative enabling 

technologies for accurate observation at significant spatial resolution with 

microwave and (sub)millimetre-wave sensors from GEO. The activity will be 

conducted in 2 phases, with the first phase comprising of definition of a 

concept, trade-offs and preliminary design. Phase 2 will include detailed 

design, critical breadboarding, and manufacturing integration and test. In 

order to promote innovation, it is foreseen to place 2 parallel contracts for 

phase 1 followed by a selection by the Agency of the most promising 

instrument concept for demonstration in phase 2. Type of tender C(2) - 

activities in open competition, where a significant participation of 



programmes". 






C 02 

Q4 



Status: 

DIPC > 500 



Page 37 


02.1EE.08 SOLID STATE PHASE CONJUGATION AND CHOCOLATE: RADIATION 

TESTING AND EVALUATION 

N24 

ESTEC 

EEO-003: As the laser transmitter energies increase, so do the wavefront 

aberrations; for high-energy lidar. The object of this activity is to develop 

an all-solid state phase conjugating mirror suitable for high-energies as a 

building block of a Nd:YAG SS laser system. The work will consist of material 

research and development of a breadboard. A comprehensive material test 

program in order to assess the suitability of the selected materials for use 

in the space environment will be carried out within activity T-M-QCA-08-04 as 

part of the same tender. T-M-QCA-08-04: Little or no radiation test data is 

available on solid-state PCM materials. It is therefore necessary to initiate 

an early irradiation test program in order to assess the suitability of these 

materials for use in the space environment. The main objective of this 

activity is to irradiate and characterize ionization and displacement damage 

effects in solid-state phase-conjugating mirrors (PCM) / materials for 

spaceborne laser systems (primarily lidar). Sub-activities include: Device 

selection, pre/post-irradiation characterisation, irradiation (with protons, 

electrons, gamma rays) and a comprehensive evaluation. The activity will be 

combined with EEO-003 into one tender. 






C 02 

Q4 


Programme Ref.: TRP EEO-003; T-M-QCA-08-04 

Status: EX ITEM 00.1EE.01 

DAC > 500 



Page 38 


00.1EM.01 EFFECTIVE USE OF AUTOCODED COMPONENTS FOR ON-BOARD 

EMBEDDED REAL-TIME COMPONENTS 

The objective of the study is to provide, as end products, constructive 

guidelines and flight worthy artefacts (in the form of e.g. code extraction 

templates) that enable the effective use of auto-coded software components 

for new-generation on-board (O/B) embedded real-time systems. Subtasks 

include: the establishment of an architectural model that auto-coded software 

components should adhere to, with emphasis on their integration into a larger 

software architecture (e.g. PUS based) and on the control of the real-time 

behaviour of the resulting system concept; the demonstration of code 

generation templates compliant with the architectural model and a case study 

combining various code production means. 

****************************************************************** 

****************************************************************** 

Note : This activity is subject to the clause encouraging the participation 

of SMEs (Small & Medium Enterprises) as subcontractors. SMEs interested to 

participate are invited to mark their interest by activating the "Express 

Interest" button that appears at the bottom of the "Intended Invitation to 

Tender" and "Invitation to Tender" masks for the corresponding activity, and 

to select the "full visibility" option, in order that their interest is known 

by other potential bidders. Moreover, all interested bidders (SMEs in 

particular) are encouraged, when expressing interest, to indicate, under the 

new "specialisation" field, the parts of the work that could be 

satisfactorily performed by them. This can be substantiated by also including 

URL addresses in the "specialisation" field, which will become active to 

further readers. For more information, see EMITS News dated 3 December 2000. 

ESTEC 



MATHEMATICS & SOFTWARE DIV / TOS-EM 

Responsible: MR MORTENSEN 


C 02 

Q2 


Programme Ref.: TRP EME-011 


DAC 200-500 



Page 39 


01.1EM.01 DISTRIBUTED CONCURRENT DEVELOPMENT 

The objective of the study is to analyse the feasibility of using emerging 

technology, e.g. distributed interactive simulation and computer based 

collaborative engineering tools to support concurrent developments in order 

to improve the efficiency (time and cost) and the quality of the development 

activities. In particular it should be demonstrated how the following 

problems could be alleviated: - late realisation of system problems, e.g. 

during AIV, due to lack of early interface testing; - duplication of testing 

and simulation infrastructures related to the one and the same project; - 

effort in unsuccessful reviews . Taking into account the following practical 

constraints: - confidentiality issues; - computer security issues, including 

fire-wall policies; - performance and Quality of Service characteristics of 

commercially available networks. It is expected that by using distributed 

interactive simulation techniques, and other distributed collaborative 

engineering methods and tools (sharing of work space, videoconferencing and 

others), the companies involved in the development of space systems can 

implement early testing without the need to cross deliver products at a time 

where they are not mature. Also, interaction between industry and ESA should 

benefit from these techniques, since documentation, as the one used to 

support reviews, are often delayed with respect to the technical solutions 

already implemented, and seldom complete. The feasibility of using 

distributed simulation and other distributed collaborative engineering 

techniques to support typical ESA reviews, (in particular PDR and CDR) shall 

be analysed for the benefit of conducting more efficient reviews. The 

activity should cover design, development, test & qualification and review 

tasks. Workbreakdown: * review outcome of listed references (list to be 

completed); * identification of specific tasks in the development process 

(mainly phases B/C/D) that can benefit from concurrent engineering; * review 

of existing tools and technology to support distributed, collaborative 

engineering; * identification of process changes to accommodate for 

distributed concurrent engineering; * analysis of tangible benefits; * 

demonstration on the basis of existing infrastructure and selected tasks 

(optional); * summary of recommendations on the process, methods and tools 

and types of mission where benefits can be maximised; * provision of input 

for a follow-on TRP activity to develop a demonstrator. 

ESTEC 






C 02 

Q2 



Status: 

DIPC 100-200 



Page 40 


01.1EM.06 COMPONENT ORIENTED DEVELOPMENT TECHNIQUES 

The objective of the activity is to assess the state of the art in the field 

of Component based development, to clarify the various denomination and 

techniques, and to investigate their use for Space software development. In 

particular, current reusable architectures are candidates to be turned into 

components. The activity will carefully analyse the impact of component-based 

development on the performance of the code itself, in particular if it has to 

be embedded into flight hardware where execution time and memory size are 

limited. The end product will be a component-based space architecture and its 

assessment in terms of performance and standardisation. Type of tender C(2) - 




programmes". 

ESTEC TECHNICAL & OPERATIONAL SUPPORT - D/TOS 





C 02 

Q2 



Status: 

01.1EM.07 COMPACT COMPUTER CORE SOFTWARE ARCHITECTURE FOR ON 

BOARD SCALABLE SUPER DSP SYSTEM 

NO 100-200 

ESTEC 

The objective of the activity is to produce a distributed software 

architecture based on characterised communication services allowing pieces of 

software to communicate, or even migrate between processors. A trade off 

shall be made between the flexibility of the architecture and its timeliness 

properties. Sub-tasks of this activity include the analysis of the proposed 

hardware architecture and application requirement, detailed design and 

development of the software characterization of the communication services, 

schedulability analysis, reconfiguration scenario. An initial integration 

test plan with test scenario shall also be developed. Type of tender C(2) - 




programmes". 






C 02 

Q2 



Status: 

DIPC 200-500 



Page 41 


01.1EM.08 DATA MANAGEMENT SOFTWARE FOR MASS MEMORY BASED PAYLOAD 

PROCESSORS 

During the course of this study the embedded software (S/W) for the next 

generation Solid State Mass Memories (SSMM) will be designed, implemented and 

tested, conformant with the software requirements established by the System 

Design phase activity. 






C 02 

Q2 


Programme Ref.: TRP EMS-008 


01.1EM.09 COMPACT MAINTAINABLE OPEN REAL-TIME KERNELS 

DAC 200-500 

Critical software is a close domain where the cost increases exponentially 

with the criticality level. In order to decrease part of the cost or even to 

make feasible certification of real-time kernels, it is necessary to have a 

very small kernel with a deep visibility. The objective of the study is to 

make available as an Open Source, a compact kernel for critical space segment 

software. Type of tender C(3) - activities in open competition, restricted to 

SMEs and R&D entities. For additional information please go to EMITS news 


programmes". 






C 02 

Q2 




01.1EM.10 TOOLS FOR THE PRODUCTION OF O/B SW RUNNING ON NEW 

GENERATION COMPUTERS 

NO 100-200 

ESTEC 

The objective of the study is to prepare the software (SW) environment 

related to the new generation computer (based on Sparc V8). Priority will be 

given to the compiler and run-time system, then the debugger and the target 

simulator. Type of tender C(3) - activities in open competition, restricted 

to SMEs and R&D entities. For additional information please go to EMITS news 


programmes". 






C 02 

Q2 



Status: 

NO 100-200 



Page 42 


01.1EM.13 SPACECRAFT CHARGING AND PLASMA INTERACTION GUIDELINES 

During the course of this activity an active (i.e. www-based) handbook on 

spacecraft charging will be developed. In particular methods shall be 

defined, data and guidelines provided, in order to create analysis tools. 

Major tasks include: review of the basic of spacecraft plasma interactions, 

definition and specification standards for simulation and simulation 

environment to be performed according to each known problems, specification 

of test procedures. 






C 02 

Q2 


Programme Ref.: TRP EMA-022 


01.1EM.14 SIMULATION MODEL REPOSITORY 

NO 50-100 

ESTEC 

During the life-time of a spacecraft project variety of subsystem models are 

being developed, in support of both design and operation activities. It is 

currently very difficult, if not impossible, to reuse existing models for two 

main reasons: i) a lack of information on what has been developed and is 

available; ii) the absence of a standard interface for calling these models. 

An Agency-wide model repository with a set of well-defined access rules and 

configuration management procedures will allow for these obstacles to be 

overcome and efficiently promote model reuse. The Industry contributing to 

this repository will have access to the totality of the models it contains 

and will be able to reuse them in space projects, therefore saving 

development costs for simulation applications. The objective of the study is 

to define a spacecraft model repository which will provide the projects with 

a choice of subsystems and environment application models not linked to a 

particular spacecraft or simulation tool (general-purpose). The study will 

address in particular the following aspects: architecture, configuration 

management procedures, access rules. The study will also start to populate 

the repository with existing models (orbit, dynamics, AOCS). The models 

introduced into the repository are expected to follow the API (Application 

Program Interface) standards established under a TRP study. 






C 02 

Q2 

Spec. Prov.: IRL 

Programme Ref.: GSTP-3 G00/H70.9B-ES215 

Status: EX ITEM 98.113.01 INITIATED 1-3474 

DIPC 200-500 



Page 43 


01.1EM.16 APPLICATION OF STEP TECHNOLOGY FOR SPACE ENVIRONMENT 

TOOLS 

Space environment analysis often requires coupled treatment of geometry and 

orbit (eg computing atomic oxygen fluences, debris impacts, contamination, 

radiation, solar UV). Reliance on custom tools is very expensive and 

inefficient. New non-space technologies are being developed, especially based 

on the Standard for the Exchange of Product Data (STEP) which offers a way to 

develop space-specific applications with the maximum use of commercial tools. 

This activity will perform research into the requirements of space 

environment analysis tools, study the necessary data structures, define an 

implementation using STEP tools, and develop a prototype including some of 

the existing space. 






C 02 

Q2 

Spec. Prov.: F 

Programme Ref.: GSTP-3 G00/H69.MMS-740 

Status: TO BE RE-ISSUED 1-4063 

02.1EM.01 OBJECT-ORIENTED TECHNOLOGIES APPLIED TO REAL-TIME APP. 

NO 100-200 

ESTEC 

The objective of the activity is to assess and compare the suitability and 

maturity of the Object Oriented technologies of On-Board Real Time Software. 

There shall be a case study based on Java, which integrates not only a 

language, but also a complete system with an interpreter. Another subactivity 

will include elements as real time brokers and application encapsulation 

techniques. Criteria for evaluation are defined to provide an assessment of 

the technologies used. It shall include the performance of the resulting 

software (size, execution speed, etc.), security and simplicity of 

implementing changes, easiness of development and covers also all aspects of 

testing. Type of tender C(4) - activities subject to SME subcontracting 

clause. For additional information please go to EMITS news "Industrial Policy 

measures for non-primes, SMEs and R&D entities in ESA programmes". 






C 02 

Q4 


Programme Ref.: TRP EMS-100 

Status: 

DAC 200-500 



Page 44 


02.1EM.02 SPACE WEATHER APPLICATIONS PILOT PROJECT 

N5 

ESTEC 

Previous studies of space weather applications have identified a large set of 

user requirements regarding space weather services in Europe. Space Weather 

refers to solar-terrestrial conditions, which can disrupt techno1ogies (power 

distribution grids, communications, navigation, spacecraft, aircraft 

avionics, etc.) or cause hazards to humans (astronauts, aircraft crew). The 

studies have focussed on applications and analysed benefits of a space 

weather applications programme and potential space segments for supporting 

associated services. While the science of space weather is both interesting 

and necessary for underpinning applications in the long terms, the past 

activities, and the subject of this procurement, are the investigation of the 

needs for a space weather applications programme within Europe. The objective 

of the proposed procurement is to develop and extend the user community 

through limited development of targeted services, provided by a network of 

service providers, supported by a common infrastructure and using data from 

existing assets. Through this service and community development a clear 

long-term view of the potential for space weather applications should be 

established. In parallel, the economic and other social benefits of the 

services and their long-term relevance will be assessed in a reliable way. 

The results will be used to support decision making on European involvement 

in space weather applications. The activity will be placed through a main 

contract which provides for the structure and common tools to be employed, 

and supervises the work of up to 15 service provision projects, placed as 

sub-contracts. These co-funded projects will be selected by means of an 

Announcement of Opportunity and involve development of service-provider - 

end-user relationships. Projects funded via other means can also be 

considered for integration in the network. The development of informatics 

facilities and communications and execution of supervisory and analysis tasks 

related to the various projects will be performed through a single contract. 






C 02 

Q2 


Programme Ref.: GS 02/L30 

Status: 

YIPC > 500 



Page 45 


02.1EM.03 AUTOMATIC CODE GENERATION 

N10 

The objective of this mini project is to bring the autocoding technology to 

the level required for space segment engineering, by improving or clarifying 

several aspects: • The technology, as proposed by tool vendors, needs to be 

adapted to space on-board software requirements, in terms of open 

architecture, timeliness properties, code visibility,• The software lifecycle 

incl. test phases, • The subsystem lifecycle. The actual possibility to skip 

tests steps in the software lifecycle is closely linked to the quality of the 

code generator, The notion of qualification or certification needs to be 

defined and analysed. The end products of the mini project include adapted 

tools, methodology guidelines and software product assurance requirements for 

the use of automatic code generation in space segment software. Type of 

tender C(1) - activities in open competition limited to non-primes. For 

additional information please go to EMITS news "Industrial Policy measures 

for non-primes, SMEs and R&D entities in ESA programmes". 






C 02 

Q3 



Status: 

02.1EM.04 DEVELOPMENT OF RADIATION SHIELDING AND EFFECTS PHYSICS 

MODELS 

YIPC > 500 

N12 

ESTEC 

Crew radiation hazards are mission critical and ultimately limiting. 

Radiation hazards in interplanetary space are dominated by cosmic rays and 

solar particles and the secondary particles generated by their interactions 

with shielding of the vehicle or planetary surface habitat. Methods for 

calculating the penetration and production of secondaries depend on complex 

physics models of nuclear interactions, which need improvement. The Geant4 

toolkit, under development by CERN, other high energy physics laboratories 

and ESA, is a state of the art framework for developing efficient and 

flexible tools. Special developments are needed for planetary manned missions 

in the domain of cosmic ray shielding and effects, particularly concerning 

heavy ion fragmentation and particle transport in manned vehicles/habitats 

shielding and in biological tissue. The objective of the activity is the 

development, implementation and validation of physics models in the Geant4 

software toolkit for analysis of proton and heavy ion shielding, secondary 

production and biological effects. 





Budget Ref.: 100580 - AURORA 

C 02 

Q4 

Spec. Prov.: B+F+I+NL+E+CH+GB+A+POR+CDN 



DAC 100-200 



Page 46 


02.1EM.05 RADIATION EXPOSURE AND MISSION STRATEGIES FOR 

INTERPLANETARY MANNED MISSION 

N12 

The radiation hazard to crew is critical to the feasibility of manned 

missions. To protect crew, shielding must be designed, the environment must 

be anticipated and monitored, and eventually a warning system must be put in 

place. Because of the strong influence on the mission and the vehicle/habitat 

designs a detailed investigation of environments and effects in example 

scenarios and designs will be made including a review of the hazards and 

their sources and the environment specified. Shielding and secondary 

radiation production processes will be analysed considering geometries 

materials and the radiation sources. The necessary shielding will be designed 

in various scenarios and the effects identified, particularly for examples of 

the vehicle and surface habitat designs. Definitions of the requirements for 

improved environment, shielding and effects tools will be made. 






C 02 

Q4 




03.1EM.01 SEE FOR SPACE PALMTOP APPLICATIONS 

DAC 200-500 

N24 

ESTEC 

Palmtops are currently being considered as a promising HW platform for a 

number of operations aboard the ISS. There limited size, weight, and power 

consumption, together with their increasing computing and storage 

capabilities make them very attractive for applications where proximity of a 

laptop is not possible or practical. Also they are seen as a complementary 

tool to astronaut operations, for applications such as ODF (Open Development 

Framework) procedure viewers. In addition, a wide range of satellite-related 

services like GPS, Internet and mobile wireless communications are starting 

to be available on palmtops. That would make this an attractive tool to boost 

Astronaut’s efficiency.However, both application domains (ISS and ground) 

will demand extensive software development tools, which are not available on 

the market. Proper SW infrastructure like basic libraries, software 

development tools, etc. will be required.Therefore, it is proposed to 

investigate an adaptation/extension of the existing ESA SEE (Single Event 

Effect) core technology to support new application domain. An approach based 

on Scripting technologies is highly recommended.In particular, the activity 

shall prepare/adapt a software development infrastructure for Space Palmtop 

Devices in which SEE issues are addressed. The activity shall also produce a 

breadboard of a Space Palmtop Device with simple software application 

demonstrating the use of the infrastructure. 






C 03 

Q1 



Status: 

NO 100-200 



Page 47 


03.1EM.02 ON-BOARD MODEL CHECKING 

N24 

Autonomous systems are able to sense their environment in order to take 

decision according to the current situation. In principle, the decision 

results into a set of actions that should not harm the satellite. However, 

when the decision is taken by a fault recovery mechanism, or even more 

generally, it is safer to verify that the set of actions will not put the 

satellite into a hazardous situation. In order to do so, it is possible to 

build a model of the states of the satellite, and to verify that when the 

actions are put on the model, the resulting state is still safe. This is 

called model checking. There are several model checking techniques on ground. 

However, very few have been embedded on board. The purpose of the activity is 

to exercise on a small but representative case study, model checking 

techniques to be embedded, and to verify that their performance in terms of 

memory size, response time and predictability are compliant with space 

on-board software requirements. 






C 03 

Q1 



Status: 

03.1EM.03 ON-BOARD THEOREM PROVER 

NO 100-200 

N24 

ESTEC 

Formal methods are very efficient for a targeted application. Most of 

on-board software can be covered by behavioural formal methods (synchronous 

for AOCS or asynchronous for Data Handling and FDIR). Another part of the 

software, generally based on algorithm or data manipulation, cannot make use 

of behavioural methods. Instead, it would benefit from the logical formal 

methods, based on theorem proving. The last trend in the formal method world 

is to merge the two techniques to improve their efficiency. This activity 

aims at demonstrating the approach of combined logical formal methods on part 

of on-board software (where efficient) and a behavioural formal method for 

the rest of the software. 






C 03 

Q1 



Status: 

NO 100-200 



Page 48 


02.2EM.01 VIRTUAL SPACECRAFT DESIGN 

N21 

ESTEC 

The objective is to develop and apply the virtual design technology in the 

context of the spacecraft development process with the aim of shortening it 

and rendering it more cost-effective, facilitating the control of costs and 

risks. 






CR 02 

Q4 

Spec. Prov.: ASTRIUM, ALCATEL, ALENIA 

Programme Ref.: TRP EMM-004 

Status: 

DIPC > 500 



Page 49 


02.1EP.02 SOLAR ARRAY DESIGN AND TECHNOLOGY DEVELOPMENT FOR MARS 

EXPLORATION MISSIONS 

N12 

ESTEC 

The differences between the Mars environment and the common orbital 

environment in which the solar arrays are used mean that the standard solar 

array configuration cannot be used for operation on Mars. The critical 

differences between the two environments having strong impacts in the solar 

array design and technology are the dust deposition, atmospheric pressure 

(less than 1 % of the Earth pressure, wind mechanical loads and peroxide-rich 

soil which, in combination with water vapour, may produce corrosion. The R&D 

activity shall include solar array configuration analysis and technology 

development able to operate in the Mars environment, experiments and bread 

board manufacturing and pre-qualification finalised to the reduction or the 

complete removal of the dust on the solar array surface and mathematical 

modelling for the prediction of the solar array performances in the Mars 

environment 



POWER AND ENERGY CONVERSION DIVISION / TOS-EP 

Responsible: MR PEROL 


C 02 

Q4 




DAC 200-500 



Page 50 


02.1EP.03 SOLAR CELL DEVELOPMENT FOR MARS EXPLORATION MISSIONS 

N12 

ESTEC 

The differences between the Mars environment and the orbital environment in 

which the solar cells are most commonly used impose a development activity to 

optimise the behaviour of the solar cells for the operations on Mars. The 

critical differences between the two environments having strong impacts in 

the solar cell are the solar intensity and spectrum modified by dust, 

indirect sun light, low temperature operation and radiation environment. Two 

different types of solar cells can be considered as the best candidates for 

the Mars operation as a function of the selected mission: silicon LILT (Low 

Intensity Low Temperature) Solar Cells and GaAs based solar cells. Silicon 

LILT cells have been developed, qualified (ESTEC contract) and produced for 

the ROSETTA mission. Since for Mars the LILT requirement is different from 

the ROSETTA, the cell shall be optimised (e.g. increase of the efficiency and 

lighter design) for this environment. The existing GaAs multi-junction solar 

cells could promise in the Mars environment a better performance than the 

Silicon ones, they are very sensitive to variations of spectral insolation 

conditions, to changes in the optical system due to dust effects or varying 

of angles of incidence. A possibility for improvement is to develop low band 

gap tandem solar cells less sensitive to the blue part of the spectrum.The 

possible candidates for the martian mission, based on III-V compound, can 

be:GaAs/Ge single junction with a passive or an active Ge substrate, GaAs on 

Ge dual junction solar cells and multi-junction GaAs solar cells based on low 

band gap III-V compounds. The R&D activity shall include the mathematical 

modelling finalised to the optimisation of the solar cell structure 

simulating the solar cell performances in the Mars environment, technology 

development and test to optimise the solar cells structure and study and 

experiments to predict the cell performance in the Mars environment 






C 02 

Q4 




DAC 200-500 



Page 51 


02.1EP.04 UPGRADE OF LARGE AREA PULSED SOLAR SIMULATOR 

N14 

ESTEC 

02.1EP.05 

N21 

ESTEC 

The ESTEC Large Area Pulsed Solar Simulator (LAPSS) was designed for the 

accurate electrical performance characterization of solar arrays based on 

single-junction (Sj) solar cells (i.e. Silicon & GaAs) in the beggining of 

the 80’s. Solar cell types based in multi-junction (Mj) technologies are 

gradually replacing Sj solar cells in the space photovoltaic market due to 

their higher performances. Therefore, the objective of the proposed work is 

to upgrade the current LAPSS facility at ESTEC, in order, to perform accurate 

electrical performance characterization of solar arrays based on Sj and Mj 

solar cells. 





Budget Ref.: 100952 - Investment 

C 02 

Q3 



Status: CHANGED TO 02.3EP.03 

ADVANCED LITHIUM POLYMER BATTERY EVALUATION 

Rechargeable lithium cells with solid polymer electrolyte are potentially 

attractive for space applications because of their flexible geometry, 

inherent ruggedness, and capability to operate at higher temperatures. The 

proposed study contract has two objectives: *) to identify space applications 

where the use of lithium polymer batteries would be most beneficial; *) to 

evaluate the status of European suppliers of this technology, which is 

already finding its way into potable devices such a mobile phones. Following 

a positive outcome of these two aspects a separate hardware development 

activity will be initiated. 






C 02 

Q4 


Programme Ref.: TRP EPB-001 

Status: 

NO 100-200 

DAC 200-500 



Page 52 


00.1ES.04 PIEZO-ELECTRIC MOTORS AND LINEAR ACTUATORS, DRIVE 

ELECTRONICS 

With the advent of small spacecraft missions, a need exists to develop 

miniature activation devices for use on such programmes. One technical area 

which appears to offer the possibility of low mass/low power actuators is 

that utilising piezo-electric technology, which is now being dramatically 

exploited in the commercial camera field. Based on requirements defined by 

spacecraft electrical interfaces and the drive power needs of piezo-electric 

motors and linear actuators, the objective of this activity is to design, 

breadboard manufacture and test two types of excitation power supplies for 

such mechanisms. The activity would commence by studying various 

implementation approaches for the required AC driving power supply, taking 

into account specific constraints with respect to the applied voltage level 

and excitation frequency. Based on a trade-off and evaluation study, one of 

the design concepts evaluated for the piezo motor and one of the design 

concepts evaluated for the linear actuator would then be selected for 

breadboarding and testing. 

****************************************************************** 

****************************************************************** 













ESTEC 



CONTROL DATA & POWER DIVISION / TOS-ES 

Responsible: MR CREASEY 


C 02 

Q2 


Programme Ref.: TRP ESS-005 

Status: 

DAC 200-500 



Page 53 


00.1ES.05 DESIGN AND VERIFICATION OF VALIDATION TECHNOLOGY FOR 

ON-BOARD MICROPROCESSORS 

The activity will identify, develop, and verify the techniques and the tools, 

which are required for the validation of modern microprocessors. The tools 

for the defined validation techniques will be implemented and shall be 

verified by appropriate methods to be defined. The tools shall be designed 

such that it is generic enough to be used with a wide range of 

microprocessors. Then a demonstration of the use of the defined validation 

techniques and tools shall be done by applying them to a microprocessor with 

known faults and to a newly designed microprocessor. 

****************************************************************** 

****************************************************************** 













ESTEC 

00.1ES.07 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP ESD-006 

Status: 

SAFEGUARD DATA RECORDER 

During the course of this activity a demonstrator of a safeguard data 

recorder, which shall allow to store safeguard/context data with a high 

reliability, including during spacecraft power shortage, will be designed and 

developed. The demonstrator shall be tested versus all the different 

operation and failure scenarios. The activity will cover both the needs of 

having modules that can be plugged as element in a standard computer, 

connected to a rather simple controller (emergency TM), be part of an hybrid 

design with a mix of volatile (for high capacity) and non-volatile (critical 

data) memory or as a fully-integrated stand-alone safeguard recorder. 






C 02 

Q3 




DIPC 200-500 

DIPC 200-500 



Page 54 


00.1ES.11 SUPPORT FOR THE DISTRIBUTION ON ON-BOARD CONTROL 

SERVICES 

The main objective of this activity is to build the architectural 

infrastructure (concept and software artifact) that enables the distribution 

of on-board control services compliant with the PUS - Packet Utilisation 

Standard (now to become an ECSS-E-70 standard) across platform and payload 

processors. The activity shall: - assess ways of distributing PUS services 

across on-board processing units for use in platform and payload control; - 

address issues of real-time bus communications (eg: bus selection, analysis 

of real time communication on selected bus); - build on the OBOSS-II end 

products (architectural model; Ada and C software artifacts); - construct a 

comprehensive library of reusable services in C for use on RISC and DSP 

platforms. 

ESTEC 

00.1ES.15 

ESTEC 






C 02 

Q2 

Spec. Prov.: DK+IRL 

Programme Ref.: GSTP-3 G00/B36.ESD-014 

Status: 

CONTROL DRIVING ELECTRONICS FOR CRYO-COOLERS 

Qualification of a Drive Electronics for CRYO-Coolers. The activity consists 

in designing, manufacturing and testing a new electronic unit to control a 

CRYO-Cooler with the aim of having a more performing unit avoiding problems 

encountered in the past. The need is to have a second supplier for this type 

of unit. 






C 02 

Q2 

Spec. Prov.: E 

Programme Ref.: GSTP-3 G00/B46.ES-I-073 

Status: CHANGED TO 02.3ES.08 

DAC 200-500 

DIPC > 500 



Page 55 


01.1ES.03 HIGH PERFORMANCE ON-BOARD COMPUTER FOR CRITICAL 

APPLICATIONS 

Past experience has shown that there is a significant inertia between the 

availability of a new processor chip and its implementation at project level. 

It is then important to give the opportunity to industry to have an early 

hands-on experience on the new chip. Considering the fact that the LEON is a 

synthesisable core, companies can eventually integrate it as a core in a 

custom design product for specific projects. The objective of this activity 

is to Hands-on validation of the LEON (Sparc V synthesisable core) 

architecture by industry for developing high performance OBC for critical 

applications, making use of the on chip implemented fault tolerance 

functions. It will be a multiple companies activity focusing on different 

application for use of the new processor. Depending on the outcome of open 

competition, a parallel contract might be placed. Type of tender C(2) - 




programmes". 

ESTEC 






C 02 

Q2 

Spec. Prov.: F+I 


Status: CHANGED TO 02.3ES.05 

DIPC > 500 



Page 56 


01.1ES.04 FPGA OPEN VHDL LIBRARY 

One of the major event in the space industry in the past years has been the 

introduction of FPGA devices suitable for space applications. According to 

the market projection in the coming year more dense programmable logic will 

become available for space application. The objective is to design of a VHDL 

cores ’open’ library aimed at the integration in FPGA with emphasis on the 

minimisation of glue logic for nano/micro-control and interfacing. Proof of 

concept by design and development of an FPGA. Following main tasks are 

envisaged: 1 Interface cores; 2 nano/micro-controller core. The proposed 

activity aims to the design of a nano-microprocessor core of 4 or maximum 8 

bit designed to require the minimum of resource such as to be synthesized in 

one FPGA with the use of maximum 50% of the internal chip gates. This will 

allow to greatly extend the use of FPGA to more complex control function 

contributing to the cost reduction of the equipment design. Depending on the 

outcome of open competition, a parallel contract might be placed. Type of 

tender C(4) - activities subject to SME subcontracting clause. Type of tender 

C(1) - activities in open competition limited to non-primes. For additional 



ESTEC 






C 02 

Q2 

Spec. Prov.: IRL+FIN 


Status: 

DAC 200-500 



Page 57 


01.1ES.05 MAXIMUM POWER POINT REGULATOR - MPPR 

This newly proposed MPPR could be considered as a MPPT (maximum power point 

tracker) with increased capabilities. In fact it can predict solar array’s 

maximum power point and the power margin between maximum power point and 

operating point. The following phases are envisaged: Phase 1, a number of 

different PWM converter topologies shall be reviewed and analysed, for 

selecting then the two most suitable converter topologies (i.e. a buck 

converter of the V-to-V type and a buck/boost converter of the I-to-V type); 

Phase 2, the design and manufacture of elegant breadboards (i.e. two 

conductance controllers) and integration of the two conductance controllers 

into an elegant MPPR breadboard shall be performed; Phase 3, the MPPR 

capability shall be demonstrated by testing according to an ESA agreed test 

procedure. For that purpose, two solar array simulator breadboards (Voc=70V, 

Pmax=400W) will be given on loan by ESA. Type of tender C(1) - activities in 

open competition limited to non-primes. For additional information please go 

to EMITS news "Industrial Policy measures for non-primes, SMEs and R&D 

entities in ESA programmes". 

ESTEC 






C 02 

Q2 

Spec. Prov.: B+DK+FIN 

Programme Ref.: GSTP-3 G00/B39.ESS-001 


DAC 200-500 



Page 58 


01.1ES.06 SMART BATTERY MANAGEMENT 

Traditionally battery systems are faced with wear-out or damage by overcharge 

mechanisms which in conjunction with capacity fading due to operational 

lifetime, requires the batteries to be oversized in order to accommodate the 

needed capacity by the end of the mission. These features have an adverse 

impact on the overall launch mass. This activity aims at the development of 

an innovative and superior method for managing the new Lithium-Ion batteries 

so as to efficiently control the charge and discharge of this particular type 

of battery, this resulting in much better control than present charging 

principles. This new method will have to guarantee that batteries are never 

over-discharged or overcharged, even during fast recharge modes. In addition 

the Smart Battery Management development also needs to embrace the necessary 

cell bypass techniques to ensure cell voltage balancing within the battery 

assembly. In adopting these battery management approaches, it is expected 

that certain degradation effects will be substantially reduced which should 

enhance battery lifetime, even after a large number of charge/discharge 

cycles. This reduction of these degrading effects has the potential to be 

translated into a battery weight reduction with an economic and mission 

safety benefit. These benefits are foreseen to be the cost reduction of 

satellite development, launch and operation based on launch mass reductions 

achieved by the use of lightweight energy systems, and increased capability 

based on battery cell durability and lifetime. 

ESTEC 

01.1ES.08 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/B40.ES-I-149 


BB EPC FOR X-BAND POWER AMPLIFIER 

Pulsed X-band radars have not yet made use of modern power supply technology. 

The objective is to build a breadboard EPC for a X-band power amplifier, 

reducing mass by 40 % compared with ERS and Radars using EPCs and to increase 

power conversion efficiency to above 90%. The activity will be split in two 

phases, a design phase and a breadboard phase. The planning should be 

co-ordinated with the X-band RF development. Type of tender C(1) - activities 

in open competition limited to non-primes. For additional information please 

go to EMITS news "Industrial Policy measures for non-primes, SMEs and R&D 







C 02 

Q2 


Programme Ref.: GSTP-3 G00/B41.ESP-016 

Status: 

DAC 100-200 

DIPC 200-500 



Page 59 


01.1ES.09 INTEGRATED MODELLING SOFTWARE DEVELOPMENT 

The challenges facing future missions do not lie exclusively in the 

development of component hardware and real-time software. Work is also needed 

to advance the state-of-the art in software tools for analysis and design. 

Existing specific analysis tools cannot evaluate the impact on optical 

performance from controlled optics, structural dynamics, and thermal 

response, which are important considerations for future very high accuracy 

pointing systems. To investigate these critical relationships, DYNOPTIX has 

been developed and enables end-to-end modeling of complex optomechanical 

systems (including optics, control, structural dynamics). The objective of 

this activity is to develop additional third partie softwares I/Fs (CODE V - 

Multi-body simulation package, thermal analysis software) and design & 

analysis tools, e.g. Monte Carlo simulation, improve vizual-isation 

capabilities, implement a model management and configuration control, and 

produce DYNOPTIX release 3.0 software tool. DYNOPTIX was originally created 

as a concurrent engineering modelling software tool to assist in the early 

design phases of multidisciplinary systems; release 2.0 was developed under 

the TRP 1994-96 on "Attitude Measurement Transfer Systems". The activity is 

structured in two phases: Phase I starts with the analysis of the required 

performance improvements of the current release of DYNOPTIX, the definition 

of all the necessary algorithms and user’s requirements related to the new 

release of DYNOPTIX, the identification of the client/server implementation 

procedures for third partie software I/Fs, and the definition of both 

software tool architectural design and S/W verification & validation. Phase 

II includes software tool detailed design and coding, the system testing for 

demonstration and verification of the new functionalities through a selected 

reference mission, and the conduct of acceptance tests of DYNOPTIX release 

3.0. 

ESTEC 






C 02 

Q2 

Spec. Prov.: B+IRL 

Programme Ref.: GSTP-3 G00/H69.ESC-006 

Status: 

DAC 100-200 



Page 60 


01.1ES.13 HIGH SPEED HIGH CAPACITY MASS MEMORY 

During the course of this activity the modules and the architecture for the 

next generation Solid State Recorder that make use of the latest 

semiconductor memory technologies in the next solid state mass memory will be 

designed and developed, in order to achieve ’cheaper, better and faster’ 

equipment and to meet the much more demanding requirements of the next 

missions (>1 Gps, >500 Gbits). The modular SSR design relying on the selected 

memory device shall be validated via the development of a demonstrator, 

including the related test equipment. 

ESTEC 

01.1ES.14 

ESTEC 






C 02 

Q2 



Status: 

REVERSE BIAS PROTECTION OF GAAS SOLAR CELLS 

The aim of this activity is to develop new methods for protecting 

single-junction and multi-junction GaAs solar cells in reverse bias 

conditions. Alternative methods shall be developed, based for instance on 

self-protected epitaxial structures. The new technique shall be demonstrated 

with the production of the first prototypes, which will tested and be 

evaluated. The deliverables of this project are 20 - 30 GaAs solar cells 

(prototypes) with the newly developed protection technique and an evaluation 

report of old and new protection methods, including assessment at system 

level and costing. Type of tender C(1) - activities in open competition 

limited to non-primes. For additional information please go to EMITS news 


programmes". 






C 02 

Q2 


Programme Ref.: TRP ESG-009 

Status: 

DIPC 200-500 

NO 100-200 



Page 61 


01.1ES.16 IMPROVEMENT OF FLEXIBLE BLANKET TECHNOLOGY FOR 

STANDARD AND THIN-FILM SOLAR CELLS 

No advances in flexible technology have been made in Europe during the last 

years and since future solar array concepts strongly focus on flexible 

blanket technology, in order to remain competitive in this area, this 

activity demands new proposals for various flexible blanket concepts 

utilising thin film solar cells as well as standard solar cell assembly type 

elements. Interfaces between flexible blanket assemblies and 

deployment/stowage mechanism shall be defined and concepts for power and 

signal harness, grounding for protection against ESD shall be developed. 

Envisaged range of the deployable solar generator concepts shall cover the 

range between 3 kW and 20 kW. Type of tender C(2) - activities in open 

competition, where a significant participation of non-primes is requested. 

For additional information please go to EMITS news "Industrial Policy 


ESTEC 

01.1ES.18 

ESTEC 






C 02 

Q2 



Status: 

SOLAR ARRAY SIZING TOOL FOR PHASE A/B STUDIES 

The goal for the proposed activity is to develop a parametric database which 

can be used both for sizing solar arrays in the frame of phase A and B 

studies, and assess the correctness of the design proposed by bidders during 

tender evaluation. The sizing tool shall have the possibility of adding the 

results of specific sizing cases also after having been developed, in order 

to increase its versatility and usefulness. There should be a built-in 

interpolation capability in order to approximate sizing cases not exactly 

represented in the database. On the basis of a specification to be 

established by ESA, a parametric design tool for solar array sizing shall be 

developed preferably in EXCEL format (to guarantee its maximum portability 

and easiness of use). Relevant sub activities are foreseen include; agreement 

on the preliminary specification, solar array sizing tool development and the 

approval of some specific designs that have been already established. Type of 









C 02 

Q2 


Programme Ref.: TRP ESP-003 

Status: 

NO 50-100 

NO 50-100 



Page 62 


01.1ES.20 OPTICAL/WIRELESS DATA TRANSMISSION 

The interest for ’wireless’ on board data communications arises from the need 

for reducing the on-board harness and for the improved integration and system 

reconfiguration capability that it brings. Despite not being a new idea, it 

is only to-day that the appearance of off-the-shelf standards in industry and 

telecommunications make it a cost-effective option by concentrating the 

effort on the space specific aspects only. It includes the definition of a 

convergence level between existing and proven protocols at transport layer 

and the ESA application support standards. The activity shall focus on two 

complementary aspects of the on-board data communications on board a S/C. 1) 

Low to medium speed, high availability for control and monitoring tasks, 

complemented if needed by local sensor bus (to connect to many miniature 

sensors e.g. thermal ) at user interface level. 2) High speed mainly to 

connect few high throughput instruments as a booster to the bandwidth limited 

system control bus. In both cases the activity shall provide a consolidated 

proof of concept and cover the system reconfiguration capability. Type of 

tender C(1) - activities in open competition limited to non-primes. Type of 

tender C(4) - activities subject to SME subcontracting clause. For additional 



ESTEC 

01.1ES.21 






C 02 

Q2 



Status: 

ADAPTATION OF TERRESTRIAL FUEL CELLS FOR SPACE 

APPLICATION 

DIPC 200-500 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP ESB-008 

Status: EX ITEM 01.3ES.04 

NO 100-200 



Page 63 


02.1ES.01 THIN FILM SOLAR CELLS PHASE 2 AND 3 

After many years of research, thin-film solar cells are now entering into the 

production phase offering reliable low-cost mass-production components. The 

objective of this activity is to adapt the existing thin-film solar cell 

concepts to space requirements by delta-development efforts and evaluate 

their performance under space conditions. 20/30 samples are expected for each 

selected technology. The activity will be implemented in following phases: 

Phase 1: Evaluation of candidate cells; Phase 2: Delta-development of space 

components. Phase 3: Test and final evaluation. Parallel contracts may be 

placed for Phase 2 and 3. Type of tender C(1) - activities in open 

competition limited to non-primes. For additional information please go to 



ESTEC 

02.1ES.02 

ESTEC 






C 02 

Q2 




DEVELOPMENT OF INTERCONNECTION TECHNIQUES FOR THIN 

FILM SOLAR CELLS 

The objective of this activity is the development of reliable thin-film cell 

interconnection techniques for space application. The activity will 

concentrate on CdTe solar cells, CuInSe2 (CIS) based solar cells, silicon and 

micromorph silicon solar cells. At least 1 development sample (mini module) 

for each solar cell type shall be produced. 






C 02 

Q2 



Status: 

DIPC > 500 

NO 100-200 



Page 64 


02.1ES.03 LIDAR-BASED RELATIVE NAVIGATION, GUIDANCE AND CONTROL 

TECHNOLOGIES 

N12 

ESTEC 

02.1ES.04 

N12 

ESTEC 

As part of the Aurora Exploration Programme a number of robotic missions are 

expected in the next years to initiate the exploration of the solar system. 

These missions will require robotic systems that can navigate, land, avoid 

hazards (smart precision landing), and perform as well autonomous 

interplanetary rendezvous and capture (sample return). The objectives of the 

study is to establish readiness, detailed design, technology development 

needs, simulation tools and overall performance assessment for robust 

LIDAR-based relative navigation, guidance and control systems. Both smart 

precision landing, with retargeting capabilities, and autonomous 

interplanetary rendezvous and capture shall be considered. 






C 02 

Q4 




PLANETARY ASCENT VEHICLE NAVIGATION, GUIDANCE AND 

CONTROL SYSTEM 

A sample return mission (Mars, Venus, etc.) requires, among others, the use 

of lander technologies to safely reach the surface and planetary ascent 

vehicle to carry the sample into the Orbiter orbit. The planetary ascent 

vehicle (PAV) is subject to severe design constraints. In addition to the 

usual premiums on weight, volume, and budget, the PAV must operate somewhat 

autonomously after being subjected, unattended, to a severe environment for a 

long period. As a result of these and other constraints, the PAV has a unique 

challenge in its design, especially for the navigation, guidance and control 

system. The activity shall include the analysis of the mission and system 

requirements, GNC engineering, analysis, trade-off and selection of candidate 

guidance and control algorithms, trajectory analysis and optimisation, 

demonstration of robustness performance through Monte Carlo simulation of 

candidate guidance and control algorithms for planetary ascent vehicle 






C 02 

Q4 




DAC 200-500 

DAC 200-500 



Page 65 


02.1ES.05 ROBUST ONLINE CONTROL CUSTOMISATION TECHNIQUES FOR 

PLANETARY SPACE VEHICLE 

N12 

ESTEC 

02.1ES.06 

N12 

The future exploration of space will require highly capable space vehicle 

that can quickly assess the situation and react to changing events. As 

conservative control techniques are not adapted to meet these challenging 

mission requirements, there is a strong need to develop robust online control 

customisation techniques for implementation into advanced GN&C systems. The 

activity shall include the development of an integrated design and simulation 

framework for robust non-linear control, fault detection, reconfiguration and 

trajectory generation. As a minimum, this includes algorithms and software 

modules development for combined Linear Parameter Varying (LPV) / Receding 

Horizon Control (HRC), Non-linear Dynamic Inversion (NDI) / Model Predictive 

Control (MPC) control techniques, and for generation of real-time, robust 

trajectory envelopes. The design synthesis of candidate non-linear 

controller(s), and module software development and implementation 

(Matlab/Simulink), shall be carried out and benchmarking of performance 

robustness shall be performed. 






C 02 

Q4 




AURORA AVIONICS ARCHITECTURE SYSTEM DEFINITION 

The proposed activity shall consist in the definition of an Aurora avionics 

reference architecture suitable to support different exploration missions. 

The architecture shall allow to the maximum extend, re-use of the recurrent 

hardware and software between these different missions. It shall be based on 

a core of mission independent functions, including as a minimum the S/C 

controller (CPU, TM-TC, reconfiguration) and a standard peripheral extension 

that shall be used to connect the mission dependent peripherals. The mission 

dependent functions shall be mission-tailored when possible e.g. by 

pre-developing most common peripherals elements, mass memory and support 

payload processor being typical cases. On board communication standards 

(CCSDS ’SOIF’) and standard application layer services for data handling 

interfaces that shall effectively ease the portability of the application 

software between missions. In terms of program, the level of 

development for this initial activity shall reach the ’Preliminary Design 

Review’ status of the overall Aurora Avionics Architecture development. 

DAC 100-200 

ESTEC 






C 02 

Q4 




DAC 200-500 



Page 66 


03.1ES.01 MISSION EXECUTION CREW ASSISTANT 

N21 

ESTEC 

For long duration mission (> 1 year), the concept of crew autonomy versus 

ground control is likely to undergo drastic changes: *) crew for its own 

motivation and satisfaction needs to be closely involved into the decision 

making process; *) for cost reasons, staffing for flight control maybe 

reduced as opposed to conventional shuttle/ISS missions (large number of 

real-time flight controllers). Object of this activity is to design and 

develop a crew assistance tool for mission planning and execution (Mission 

Execution Crew Assistant), to allow the crew to schedule and make conscious 

decisions for short and mid term activities. The devised crew assistant is 

regarded as a complementary tool for mission support in order to optimise the 

ground/crew task sharing in a long duration mission scenario. Type of tender 




programmes". 






C 03 

Q1 



Status: 

DIPC 200-500 



Page 67 


00.1ET.07 NEXT GENERATION MASS MEMORY ARCHITECTURE 

The architecture and design of the current generation of Solid State Mass 

Memory (SSMM) is not able to cope with these emerging payload requirements 

nor with the dramatic technology evolution. Therefore during the course of 

the study a system analysis shall be performed and an architectural design 

for the next generation SSMM based on mature technology for space (memory, 

packaging, controller technology) and satisfying the emerging payload 

requirements shall be developed. 

ESTEC 

00.1ET.08 

ESTEC 



PAYLOAD SYSTEMS DIVISION / TOS-ET 

Responsible: MR COIRAULT 


C 02 

Q2 


Programme Ref.: TRP ETD-036 

Status: 

X-BAND NEAR EARTH TRANSPONDER: ENGINEERING MODEL 

A specific frequency band has been allocated in the 8GHz region (X-Band) by 

the regulators for spacecraft at altitudes up to 2 million km, which includes 

all earth orbiters as well as lunar orbits and libration point orbits, but 

excludes Deep Space orbits. Thus a new development is envisaged with the 

objective to lean as much as possible upon the experience in transponders of 

european industry and available technology (the design could be partly 

derived either from existing S-Band Near Earth transponders or from the 

X-Band Deep Space Transponder). The activity would include: - Design for new 

frequency bands, specifically in filtering, local oscillators, frequency plan 

and spurious analysis; - Wideband modulators (bandwidth efficient): new 

missions require TM data rates of the order of Mbits/second or even higher; - 

Design for different Doppler/threshold requirements. Two phases are foreseen: 

Phase 1: Detailed Design Documentation, Phase 2: Critical items breadboard(s) 

and Demonstration Model Transponder. 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/A22.ETT-053 

Status: 

NO 100-200 

DIPC > 500 



Page 68 


00.1ET.09 COMPACT PROCESSING AND STORAGE UNIT 

The Agency has initiated the development of Processing Modules and Storage 

Modules which are currently being implemented on board for Experiments such 

as Rosetta Osiris, Virtis and likely to be implemented on Corot, First / 

Planck, etc. The effort has to be pursued towards the development of a 

compact processing and storage unit which will be seen as a generic unit. 

Starting from the above mentioned existing modules, the objective is to 

develop a compact payload data processing and storage unit as a stand alone 

equipment based on highly integrated technology. The design, the 

implementation and the choice of components shall be such that this unit 

shall be able to withstand the environmental constraints of an EQM (targeted 

towards PROTEUS type of missions). The compact Processing and storage Unit 

shall provide from 20 to 200 M0PS and typically 32 Gbits of storage with 

interfaces adapted to low and medium size platforms (PROTEUS class). This 

unit shall be suitable for executing Payload data processing as well as 

Payload command and monitoring functions. 

ESTEC 

00.1ET.10 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/B38.ETD-038 

Status: 

DSP TECHNOLOGY FOR NICHE SPACE, INDUSTRIAL AND HARSH 

ENVIRONMENT 

Developments performed in the previous TRP/GSTP period led to the 

availability of three major elements: A radiation tolerant Floating Point DSP 

(TSC21020), IEEE1355 (also called SpaceWire) compatible communication 

controllers and high capacity memory buffers. These technologies have been 

identified as being of interest for non-space industrial applications. Hence 

cross fertilisation schemes should be supported. The objective are: - to 

identify synergies with harsh environments applications (eg mining, robotics, 

nuclear), - to develop niche applications, which might be not directly 

related to space, - to involve Small and Medium Enterprises (SME), - to 

develop EGSE equipment that helps the promotion/usage of the above building 

blocks or technologies (eg SpaceWire), - to develop innovative 

applications/technologies not yet identified in detail today. 






C 02 

Q2 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/B38.ETD-044 

Status: 

DAC 200-500 

DIPC 200-500 



Page 69 


00.1ET.11 INTEGRATED RECEIVER FRONT-END 

New fabrication technologies (eg deep photo-resist micromachining, membrane 

technology) allow completely new structures for mm and sub-mm receivers. Some 

of these technologies are being explored in on-going activities. This 

activity aims to continue these developments, and cover also membranes that 

offer exiting possibilities for low-loss transmission line circuits. Special 

emphasis is placed on the integration of the semiconductor devices in the 

receiver block. The objective is to develop integrated receiver front-end 

using state-of-the-art micromachining technologies together with planar 

devices, and demonstrate excellent performance. 

ESTEC 

00.1ET.12 

ESTEC 






C 02 

Q2 

Spec. Prov.: B+IRL 

Programme Ref.: GSTP-3 G00/B38.ETM-179 

Status: 

DIAL-A-SAT: TERMINAL PROTO-FLIGHT MODEL 

The objective of this activity is the design, development, qualification and 

testing of a complete proto-flight Inmarsat terminal suited for a 

demonstration mission of the Dial-A-Sat concept; the complete terminal should 

be embarked on-board a qualified spacecraft. The mini-project is aimed to the 

co-ordination of several activities for the design, development, 

qualification and testing of a complete proto-flight Dial-A-Sat/Inmarsat 

terminal. The activities in the different areas (system aspects, terminal, 

antenna and physical/protocol interface with the small S/C) must be tightly 

co-ordinated in view of a successful and timely proto-flight terminal 

development and demonstration mission. 






C 02 

Q2 

Spec. Prov.: F+IRL 

Programme Ref.: GSTP-3 G00/I71.ETC-019 

Status: 

DAC 200-500 

DIPC > 500 



Page 70 


01.1ET.02 KU-BAND SSPA FOR ALTIMETER 

The topographic altimeter instrument requires advanced equipment with low 

mass and size. The advanced development of a solid state power amplifier for 

topographic altimeters is important to enable European manufacturers to 

successfully supply this critical hardware to future projects. The objective 

is to develop of a breadboard-model of a 50 W Ku-band SSPA for utilisation in 

a topographic altimeter. The design will utilise state-of-the-art 

transistors (power P-HEMTs) and advanced assembly, integration and packaging 

technologies. The development is aiming at a unit with minimum mass and size, 

good electrical performance, in particular high power added efficiency, and 

high reliability in all the operating conditions. Also, the design will take 

into account production requirements and limitations to enable low cost of 

the final flight unit. 

ESTEC 

01.1ET.03 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/A01.ETM-114 

Status: 

DSP BASED DATA COMPRESSION REGULATION/FORMATTER 

This subject is the follow-on of an already engaged ESA study. It concerns 

the implementation in space application of the data rate regulation 

associated to a wavelet compression algorithm (FDRC). It shall also concern 

the coding and the formatting of the data (PRDC). The implementation of such 

an algorithm shall be foreseen on space qualified target and therefore, DSP 

module based on TCS21020 shall be adequate. The aim of this study is to 

provide new generation standard product for data compression and data 

formatter for space applications. Type of tender C(4) - activities subject to 

SME subcontracting clause. For additional information please go to EMITS news 


programmes". 






C 02 

Q2 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/B38.ET-I-038 

Status: 

DIPC 200-500 

DIPC > 500 



Page 71 


01.1ET.04 MODELLING AND DEMONSTRATORS OF ADVANCED ASSEMBLY, 

INTEGRATION, INTERCONNECT AND PACKAGING TECHNIQUES 

Under the Space Component Steering Board initiative, European novel 

technologies for assembly, integration, interconnect and packaging of highly 

integrated microwave hardware will be evaluated to assess their reliability 

for space applications. These novel structures introduce new type of 

transmission lines, transmission media and discontinuities and, therefore, 

affect the microwave performance of the various functions implemented. The 

objective is the modelling of microwave circuits implemented using new 

transmission lines, transmission media and discontinuities, evaluated for 

space applications under the SCSB initiative. In particular technologies such 

as flip-chip assembly, multi-layer substrates and mm-wave packages will be 

addressed. The modelling will be proved by the realisation of demonstrator 

functions. 

ESTEC 

01.1ET.05 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/D57.ETM-187 

Status: 

HIGHLY RELIABILITY DESIGN FOR SSPAS 

Recent in-orbit failures, reliability studies and a preliminary activity 

under TRP has shown the strong dependence of the reliability of solid state 

power amplifiers (SSPAs) on operating conditions. In particular typical 

operating signals for space SSPAs are not the same at which the reliability 

of the active devices is evaluated. The objective is the development of 

design tool(s), which can link physical and test data of SSPAs active 

microwave devices to design limits and conditions in order to optimise 

overall SSPA performance (output power, efficiency) while maximising 

reliability, for various typical satellite operating signals (e.g. 

multi-carrier, phase modulated, etc.). Main tasks envisaged are: - link of 

physical and test data to failure conditions; - link of reliability safe area 

to non-linear microwave design tools; - design, manufacturing and test of a 

demonstrator (single stage SSPA), including RF life-test. 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/H69.ETM-089 

Status: 

DIPC > 500 

DAC 100-200 



Page 72 


01.1ET.08 NOVEL RETRIEVAL ALGORITHMS FOR ALTIMETRY 

This activity shall investigate novel retrieval algorithms for altimetry in 

both the space-based and the airborne configurations. Tasks are to include a 

trade-off between different options for retrieval, and the simulation of 

performance over synthetic surfaces leading to the selection of an optimum 

algorithm. Type of tender C(1) - activities in open competition limited to 



ESTEC 

01.1ET.09 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP ETP-111 

Status: 

COLD CATHODE TWT 

The aim of this activity is to develop a Breadboard of a cold cathode 

Traveling Wave Tube (TWT). Previous feasibility studies performed under TRP 

show that significant improvements of TWTs’ performances can be can be 

achieved by using cold cathodes. Recent advancements in cold cathodes 

capabilities coming from the commercial market of flat displays, give 

confidence that the technology is mature enough to be employed on microwaves 

tubes. The expected outputs of this activity are a preliminary design, 

breadboard of the gun assembly and the design and breadboard of a cold 

cathode TWT. Type of tender C(2) - activities in open competition, where a 









C 02 

Q2 


Programme Ref.: TRP ETM-080 

Status: 

NO 100-200 

DIPC 200-500 



Page 73 


01.1ET.13 ADVANCED 40/50GHZ O/B SOLID STATE BUILDING BLOCKS 

This activity involves the breadboarding of key critical solid state building 

blocks needed for the implementation of the different microwave/millimetre 

wave equipment necessary for future Q/V band payloads for broadband 

communication satellites. The activity shall give special attention to 

Monolithic Microwave Integrated Circuits (MMICs) and advanced packaging and 

die attach technologies. Advanced MMIC processes and packaging technologies 

shall be used to obtain best performance. 

ESTEC 

01.1ET.14 

ESTEC 






C 02 

Q2 



Status: 

DESIGN OF PHOTONIC CRYSTALS FRONT-END 

The objective of this activity is to perform the electromagnetic modelling, 

design and bread-boarding of an photonic band-gap front-end. This activity 

encompasses a study of new transmission line structures, the integration of 

semiconductor devices Photonics Band Gap crystals and the application of 

filters. Specifically the interaction with an antenna developed under EEA-009 

shall be addressed. A selected structure will be modelled, designed, 

bread-boarded and tested. Type of tender C(4) - activities subject to SME 

subcontracting clause. For additional information please go to EMITS news 


programmes". 






C 02 

Q2 



Status: 

DIPC > 500 

DAC 200-500 



Page 74 


01.1ET.15 NEURAL NETWORKS FOR RADIONAVIGATION 

The objectives of this activity are to assess the use of neural networks for 

multipath mitigation, (building on previous ESA activities and on available 

published results), select and propose a specific method/algorithm 

particularly suitable for use in conjunction with receivers used for 

positioning and attitude determination of spacecraft (limited, for the time 

being, to satellites in LEO and MEO orbits), and also to validate the 

approach by implementing it within a software breadboard and operating with 

real data collected from a selected source. Type of tender C(3) - activities 

in open competition, restricted to SMEs and R&D entities. For additional 



ESTEC 

01.1ET.16 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP ETT-059 

Status: 

INTEGRATED PAYLOAD DATA PROCESSING AND STORAGE SYSTEM 

The objective of this activity is the integration and demonstration of the 

scalability of the on-board payload scalable super data signal processor. The 

system shall be used as well to support S/W development activities and will 

become a test bench that shall be integrated in Estec’s Image Laboratory. 

Applications listed in the mini-project definition shall be demonstrated on 

the system as well. Type of tender C(2) - activities in open competition, 









C 02 

Q2 



Status: 

DAC 200-500 

DAC 200-500 



Page 75 


01.1ET.20 COMPACT DIGITAL PROCESSING UNIT S/W DEVELOPMENT 

On the basis of an existing operating system and currently developed 

libraries, the objective of this activity is to create an application 

oriented development environment for the On-Board Scalable Super-DSP System. 

The main activity shall be integration oriented. Interfaces to existing tools 

and libraries shall be specified, developed and validated. Type of tender 




programmes". 

ESTEC 






C 02 

Q2 



Status: 

NO 100-200 



Page 76 


01.1ET.21 IN ORBIT AUTOMATICALLY ASSEMBLED LARGE APERTURES 

(INOAA) 

Microwave radiometers, real-aperture radars and optical systems, require 

large antennas to synthesise narrow beams and achieve good spatial 

resolution. Inflatable, mesh antennas and single-piece telescopes, have been 

used to fit big collecting apertures inside the launcher fairing but their 

size has limits imposed by the technology and performance requirements, and 

ultimately by the envelope of the fairing itself. There is a need to break 

out such limits in deployed aperture size. This is the purpose of the present 

activity, in which three specific scenarios are put forward for study: (a) a 

LEO microwave interferometric radiometer; (b) the XEUS mission and, (c) a GEO 

Earth Observation instrument. The IN-Orbit Automatically Assembled (INOAA) 

large aperture concept would consist of a large antenna or telescope made up 

of several fragments which would be launched into space in different launches 

and then assembled together automatically in orbit. The fragments of the 

INOAA radiometer would ideally be identical and self-powered. They would have 

the capability of GNSS self-flying towards an assembly point in space at a 

given GNSS assembly time. The fragments would then enter a formation-flying 

mode (relative navigation) and finally would perform a GNSS-fully-based 

rendez-vous and docking, assembling the INOAA large structure. Once docked 

the fragments would establish RF and/or optical links for telemetry among 

them as well as data transfer for distributed processing as needed. Such 

distributed processing would accomplish the (a) LEO interferometric 

processing of the signals from all antenna elements, (b) the XEUS single 

telescope function or (c) the operation as a single GEO instrument, depending 

on the scenario. A distributed approach would also be applied to the 

communications to ground for some of the scenarios, where several links, one 

per fragment would be established. Attitude and positioning of the INOAA 

large structure would be kept using the GNSS-based AOCS system of each 

fragment. They would in turn ensure active dumping of the flexible modes of 

the large structure where necessary. A demonstration of relative navigation 

using ATV could be proposed within this activity. 

ESTEC 






C 02 

Q3 




DAC 100-200 



Page 77 


01.1ET.24 SOFTWARE TECHNIQUES TO CIRCUMVENT SEE ASPECTS 

The objective of this activity is to analyse the effect of Single Event Upset 

on the electronic, to consider the potential failures of the software, and to 

propose ways of either protect the software or recover from the failure. The 

activity is organised as follows: 1. A preliminary step is the 

characterisation of the component under radiation to understand the hardware 

behaviour when radiation is received, and to identify the main classes of 

errors. For each class (register hit, memory hit, etc.) the sequence of 

events between the hit itself and the moment its effect enter into the 

software must be described precisely. 2. From the previous analysis of the 

machine behaviour, the (unambiguous) machine profile, just after the hit, 

must be defined, for each class. This will allow at run-time to recognise 

which error has occurred. 3. For each class, a recovery solution must be 

proposed, ranging from a brutal reset to more refined solution (task/process 

re-initialisation, re-execution of a bloc of code, etc). 4. Compiler-based 

solution could be investigated. It is possible in some cases to maintain the 

run-time checksum of blocs of executed instruction, and to compare it to the 

stored reference checksum. The compiler must generate a specific code 

achieving this purpose. The end product is, for a given commercial component, 

the classification of the effects of radiation, and for each class, the 

software technique allowing to detect it, protect it or recover from it. Type 

of tender C(1) - activities in open competition limited to non-primes. For 



ESTEC 

01.1ET.25 

ESTEC 






C 02 

Q2 

Spec. Prov.: FIN 

Programme Ref.: GSTP-3 G00/D57.ETD-033B 

Status: 

RADIATION PERFORMANCE CROSS.EVAL.DSP 

The objective of this activity is to perform a radiation characterisation 

on-ground of the commercially available ADSP21060/65 processors and 

alternative implementations based on the use of reconfigurable programmable 

logic devices in terms of total ionizing dose and Single Event Effects. Type 

of tender C(1) - activities in open competition limited to non-primes. For 








C 02 

Q2 


Programme Ref.: GSTP-3 G00/D57.ETD-033C 

Status: 

DIPC 200-500 

DIPC 100-200 



Page 78 


01.1ET.26 DSP FLIGHT DEMO 

The objective is to perform an in-flight radiation characterisation of the 

DSP21060/65 using the same test set-up as previously used for the on-ground 

test programme. The preparatory phase comprises the planning, design and 

implementation of the flight demonstration HW and SW, mainly consisting of 

the adaptation of the previously developed elements for on-ground 

characterisation/testing in accordance with the requirements of a suitable 

in-orbit technology test bed. Duration 1 year. The start and duration of the 

in-orbit demonstration will depend on the identification of a suitable 

technology test bed and flight opportunity. Flight cost are not part of this 

activity. Type of tender C(1) - activities in open competition limited to 



ESTEC 

01.1ET.27 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/D57.ETD-033C 

Status: 

NEXT GENERATION DSP FOR SPACE APPLICATIONS 

The activity is split in the following tasks: - Survey of existing DSP 

technologies and future trends following the developments of 

micro-processors; - Survey of requirements for space use and finding 

synergies with the automotive and other harsh environments applications; - 

Recommendation for adaptation of a selected DSP technology to work in high 

radiation and harsh environments. Type of tender C(1) - activities in open 









C 02 

Q2 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/D57.ETD-033A 

Status: 

DIPC 100-200 

DIPC 100-200 



Page 79 


02.1ET.01 MODULAR SIGNAL GENERATION AND DETECTION FOR FUTURE SAR 

INSTRUMENTS 

The modular concept for signal generation and detection will be analysed in 

detail and a proper optimisation will be carried out using performance 

simulation of the basic building blocks and elements (Microwave Monolithic 

Integrated Circuit MMICs, boards, etc.) to arrive to a final, detailed 

design. Analysis of and optimisation based on detailed designs of MMICs and 

of signal and detection boards will be completed along with a final detailed 

design. Type of tender C(2) - activities in open competition, where a 




ESTEC 

02.1ET.02 

ESTEC 






C 02 

Q4 


Programme Ref.: TRP ETP-190 

Status: 

NEW RADIOMETER CONCEPTS - PROOF OF CONCEPT: NEW 

RADIOMETER CRITICAL TECHNOLOGIES 

ETP-153 - New radiometer concepts: During the course of this study the 

concept for an instrument and a demonstrator will be defined and critical 

technologies/building blocks identified. ETP-192 - Proof of Concept: New 

Radiometer Critical Technologies: The study will focus on proof-of-concept 

for critical technologies/building blocks for MAST including the design, 

breadboarding and possibly performance testing. Type of tender C(2) - 




programmes". 






C 02 

Q4 


Programme Ref.: TRP ETP-153; ETP-192 

Status: 

DAC 200-500 

DIPC > 500 



Page 80 


02.1ET.03 NEXT GENERATION MASS MEMORY DEMONSTRATOR INTEGRATION 

In this particular activity of the mini-project, the integration of the 

demonstrator shall be performed. Furthermore a representative application 

(including data processing and transmission examples) shall be implemented 

and demonstrated. Type of tender C(2) - activities in open competition, where 

a significant participation of non-primes is requested. For additional 



ESTEC 

02.1ET.04 

N9 

ESTEC 






C 02 

Q4 



Status: 

GROUND PROCESSOR WITH SCALABLE DSP ACCELERATORS 

A spacecraft part of an end to end system where payload data is processed 

on-board, de-ciphered by the ground control station and catalogued, archived 

and distributed by the user interface. Until now every party involved 

develops its tools separately using mostly different hardware and software 

environments. DSP’s for on-board data processing have their terrestrial 

counterparts. Ground processors can be made of these DSP’s in a scalable 

fashion for use by the Ground Control Stations and the Archiving Facilities. 

A ground processor with scalable DSP accelerators shall be developed to 

demonstrate the feasibility to be used by the parties involved in a 

spacecraft end-to-end system. The activity comprises: - Development and 

implementation of a Demonstrator for a Ground Processor with scalable DSP 

accelerators; - Demonstration of feasibility for a Ground Station performing 

payload data de-multiplexing and Fast delivery processing (with ESOC); - 

Demonstration of feasibility for a Processing and Archiving Facility 

performing: * Biomass estimation using L-band fully 

polarimetric/interferometric SAR data; * Calibration and geometrical 

correction of SAR images (activity with ESRIN); * Data reduction for TeraByte 

data bases (activity with Villafranca). Type of tender C(1) - activities in 









C 02 

Q2 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/F65.ETD-041 

Status: EX ITEM 01.187.04 

DAC 200-500 

DIPC > 500 



Page 81 


02.1ET.05 TOPNET: SPACEWIRE CONTROLLER/REMOTE USER INTERFACE 

DEVELOPMENT 

N10 The objective of this activity is to develop a SpaceWire Controller / 

Remote-User-Interface ASIC. The SpaceWire standard has been the subject of 

major revisions w.r.t the initial definition based on the IEEE1355 Standard. 

The interface is compatible today with hot-plug-in and supports the 

generation and reception of time codes. Therefore a SpaceWire specific 

Controller and Remote-User-Interface must be designed and ported to a 

Radiation Tolerant technology. The purpose of this activity is hence to make 

such a device available to the User community as a standard product. Type of 




ESTEC 

02.1ET.06 

N21 

ESTEC 






C 02 

Q4 



Status: 

ASSESSMENT OF THE FEASIBILITY OF AN OPTICAL LINK FOR 

DEEP SPACE MISSION 

Scope of this activity is to analyse the performances of an optical link for 

missions within the solar system. In this frame the overall system 

architecture shall be outlined and its performances compared versus the 

classical RF approach. In the last years more often deep space missions have 

required the implementation of multi-frequency links. The extension of the 

above concept up to the optical frequencies (including multi-frequency link 

approach based on integrated RF-Optical systems) is a step that needs to be 

investigated in the frame of this study. 





Budget Ref.: 100975 - Corporate and Admin Costs - D/TOS 

C 02 

Q4 




YIPC 200-500 

NO < 50 



Page 82 


03.1ET.01 HIGH PERFORMANCE RESILIENT COMPUTER FOR AUTONOMOUS 

ROBOTICS 

N21 

ESTEC 

Autonomy requires massive processing power that is not available in nowadays 

space-qualified processors, nor it will be for some time. On the other hand, 

leading civil/military processors and processing modules, though providing 

the numerical power needed for autonomy, cannot work reliably in the harsh 

space environment. ESA has defined in co-operation with Industry reference 

architecture for payload processing. The architecture decomposes the global 

payload data processing system in nodes interconnected by high-speed serial 

links (IEEE1355/SpaceWire). This architecture may easily integrate 

heterogeneous processors, thus providing the ideal framework for combining 

the environmental ruggedness of space processors (e.g. ERC32) with the shear 

computing power of industrial/military processors. The activity aims at the 

development of an environmentally sound O/B controller for autonomous 

robotics missions. Technology (Middleware) will be developed to combine ERC32 

processors, rad-hard DSPs, COTS processors/DSP and heterogeneous RT operating 

systems in a high-performance / high-reliability processing mode (e.g. 

processor farm). The object is to achieve a system that is both highly 

reliable and very powerful at the expense of some acceptable operational 

discontinuity. The activity shall produce a breadboard of high performance 

computer system, composed of COTS/Space-Qualified hardware in which the 

desired characteristics (high computing power and high resilience) are 

demonstrated. Type of tender C(2) - activities in open competition, where a 









C 03 

Q1 



Status: 

DIPC > 500 



Page 83 


01.2ET.01 HBV DEVICES AND MMICS 

This activity aims to develop this technology further by integrating matching 

elements on the same chip, and investigating advanced multiplier structures. 

Transferring Heterostructure Barrier Varactors (HBV) devices on quartz or 

metal substrate can greatly improve the thermal characteristics and power 

capability of the devices. The main object of this activity is to develop 

discrete and monolithic HBV devices with increased bandwidth and power 

handling capabilities for mm and sub-mm frequency multipliers. Moreover, the 

fabrication process for HBV devices shall be evaluated with respect to 

process control, and resulting components shall be evaluated in order to 

understand lifetime and reliability constraints and failure mechanisms. 

ESTEC 






CR 02 

Q2 

Spec. Prov.: IEMN F,; CHALMERS UNIV OF TECHNOLOGY - 

MICROWAVES INSTITUTE (S) 


Status: 

NO 100-200 



Page 84 


02.1GA.04 PHASE A STUDY ON EXPERIMENT INSERT FOR RESEARCH ON THE 

CNES DECLIC FACILITY 

N5 

ESTEC MANNED SPACEFLIGHT & MICROGRAVITY - D/MSM 

MICROGRAVITY AND SPACE STATION UTILISATION DEPT / 

MSM-G 

ISS UTILISATION & MICROGRAVITY PROMOTION DIVISION / 

MSM-GA 

Responsible: 

Budget Ref.: 100162 - EMIR-2 Extension 

C 02 

Q2 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB 



02.1GA.05 SCIENTIFIC AND OPERATIONAL SUPPORT 

NO 100-200 

N10 

ESTEC 

MANNED SPACEFLIGHT & MICROGRAVITY - D/MSM 


MSM-G 

ISS UTILISATION & MICROGRAVITY PROMOTION DIVISION / 

MSM-GA 

Responsible: MR HEPPENER 

Budget Ref.: 100154 - ELIPS; 100154 - ELIPS; 100554 - ISS 

C 02 

Q4 

Utilisation 

Spec. Prov.: 



YIPC > 500 



Page 85 


01.1GF.03 ULTRASOUND DIAGNOSTICS PHASE B/C/D 

ESTEC 



MSM-G 

MICROGRAVITY FACILITIES FOR COLUMBUS DIVISION / MSM-GF 

Responsible: MR REIBALDI 

Budget Ref.: 100165 - MICROGR./FACIL.-COLUMBUS (MFC) 

C 02 

Q4 

Spec. Prov.: LIMITED TO D+F+B+CH+I 



DIPC > 500 



Page 86 


02.1GM.01 PHASE A/B FOR EMCS EXPERIMENTS 

N22 

The phase B/C/D of the European Modular Cultivation System (EMCS) has been 

initiated in 1997 as part of the EMIR-2 program. The EMCS is a multi-user 

facility for biological research, mainly in botany, in the International 

Space Station (ISS). Its flight will be in the US module Destiny and its 

utilisation will be on the basis of a cooperative agreement between ESA and 

NASA. The launch of the EMCS is presently scheduled for July 2004. In order 

to carry out the EMCS experiments, hardware, experiment timelines, and 

procedures need to be developed. The EMCS experiment development process is 

considered complex, therefore a phase A/B is required before entering into 

phase C/D. For each of the selected experiments the phase A/B will be 

composed of a feasibility study (phase A) and a preliminary design study 

(phase B), including breadboarding as required. The phase B will also result 

in a cost and schedule estimation for the subsequent phase C/D. 



MSM-G 

MANNED MICROGRAVITY PAYLOADS DIVISION / MSM-GM 

Responsible: MR RIESSELMANN 

Budget Ref.: 100161 - EMIR-2 

C 02 

Q4 

Spec. Prov.: LIMITED TO B+DK+D+I+N 



02.1GM.02 PHASE B0 FOR AN ICAPS/IMPF RESEARCH FACILITY 

DAC 200-500 

N24 

ESTEC 

This procurement proposal covers the effort to re-verify the overall 

requirements compiled in Phase A for the IMPF/ICAPS facility to be operated 

in the Columbus Laboratory, to analyse to which extent these requirements are 

already reflected in the studies performed by Industry, to establish a 

conceptual design of the facility in general, and to analyse and design 

critical areas in such detail to allow experts to judge the feasibility of 

the proposed facility, and to establish a sound price estimate for Phase C/D 

of the facility. 



MSM-G 



Budget Ref.: 100154 - ELIPS 

C 02 

Q4 

Spec. Prov.: 


Status: 

YIPC > 500 



Page 87 


02.3GM.08 INCREASE EXPOSE CONTRACT VALUE TO COVER ITS RELOCATION 

FROM AN EXPRESS PALLET TO COLUMBUS 

N1 

ESTEC 



MSM-G 



Budget Ref.: 100162 - EMIR-2 Extension 

C 02 

Q4 

Spec. Prov.: KAYSER THREDE GMBH (D) 


Status: 

DAC > 500 



Page 88 


01.1GU.01 STANDARD PAYLOAD DISPLAY SOFTWARE DEVELOPMENT 

The ISS utilisation scenario foresees very limited crew time for payload 

training and payload flight operations. This calls for effective and 

efficient operations support software, e.g. laptop procedures, displays and 

navigation facilities, to achieve maximum science return.Laptop software devt 

on-going today is mainly carried out in dedicated programmes, e.g. in devt 

programmes of the payload facilities, such as MFC. However, payload displays 

devts on the ISS require co-ordination and standardisation to a considerable 

extent, specifically for Columbus. If adopted, this approach would allow to 

use many recurrent features of the software devt processes across the various 

ESA sponsored devts (e.g. MFC programme) which bears potential for more 

cost-effective production and qualification of the crew interface. The 

proposed activity includes an analysis of in-orbit crew activities and 

payload operations, support to payload devt with tools and processes,devt of 

standard display software components and a configurable framework for an 

integrated laptop display as well as elaboration of relevant procedures. This 

approach will promote a common ’look & feel’ across the payload complement, 

at the same time reducing the risk and costs,which would otherwise arise by 

individual devts. The output of the proposed activity produces qualified and 

standardised flight software components, based on a consolidated 

specification of payload laptop software, making use of devts which have 

already taken place under ESA R&D funding. The developed processes, software 

and displays operational verification shall be applied to a real flight 

payload application, such as the Protein Crystallisation and Diagnostic 

Facility. It is foreseen that the products can also be used in ground user 

workstations. 

****************************************************************** 

****************************************************************** 

Note : The subject procurement shall be restricted to Non-primes. To 

encourage the involvement of SME’s in innovative technology developments, the 

SMEs subcontracting clause measure shall be applied. SMEs interested to 

participate are invited to mark their interest by activating the "Interest 

Function Key" that appears at the bottom of the "Intended Invitation to 








further readers.For more information, see EMITS News dated 3 December 2000. 

ESTEC 



MSM-G 

SPACE STATION UTILISATION DIVISION / MSM-GU 

Responsible: MR ANDRESEN 

Budget Ref.: 100554 - ISS Utilisation 

C 02 

Q2 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+N 


Status: 

DAC > 500 



Page 89 


02.1GU.04 MISSION INTEGRATION FOR ESA EXTERNAL PAYLOADS AT 

COLUMBUS EXTERNAL PAYLOAD FACILITY (EPF) 

N22 The subject procurement activities will cover the following: *) 

Procurement/development of Columbus External Payload Adapters (CEPA’s, incl. 

Active FRAM and Adapter Plate) and Transport Container; *) Analytical 

integration of External P/L at Columbus EPF, P/L integrated analysis and 

mission analysis (eg mechanical, thermal, P/L data sets collection and 

submittal, P/L integration documentation preparation, integrated P/L ICD’s 

review, etc.); *) Physical integration and verification/testing of External 

Payloads at Columbus EPF by means of the Columbus Rack Level Test Facility. 

ESTEC 



MSM-G 




C 02 

Q4 



Status: 

DIPC > 500 



Page 90 


02.1GU.05 DEFINITION, DEVELOPMENT & IMPLEMENTATION OF THE 

MONITORING, CONTROL AND COMMANDING SYSTEM FOR THE 

DECENTRALISED PAYLOAD INFRASTRUCTURE 

N22 

ESTEC 

One of the main elements of the decentralised payload operations 

infrastructure is constituted by the core technical system accommodated in an 

FRC, namely the Monitoring, Command and Control (MC&C) System for the USOCs. 

This system is providing essential functionality to interface with the 

payload facilities, FRC Databases, and technical systems on the FRC side on 

the one hand. On the other hand the MC&C system provides the required 

connectivity to the Operational Centres for the ISS which are already 

existing (e.g. POIC) or under development, such as the Columbus Control 

Centre (Col-CC), through existing or to be provided communications 

installations and required for commanding of and telemetry processing for ESA 

payloads. The present procurement proposal concerns the design definition, 

development, and integration at the USOCs of the Monitoring, Command and 

Control System for European USOCs. This shall cover the following main 

elements: *) Design Definition of the MC&C; *) Development of generic and 

common Telemetry Processing Tools; *) Development of the Command Tool for 

USOCs; *) Development of the Operational Payload Database Tool; *) 

Development of required application software; *) Integration and interface 

testing of the elements; *) Deployment at the USOCs; *) Support to 

Procurement of Communications Equipment ; *) Management. As the main output 

of this procurement, all existing USOCs shall be outfitted, integrated and 

tested with the required Monitoring, Command and Control Systems and 

capability that corresponds to the relevant level of the Centre’s 

responsibility and interfaces with the standard communications infrastructure 

of the Agency (IGS Phase-2), that is developed as part of the Columbus 

Control Centre development. 



MSM-G 




C 02 

Q4 



Status: 

DIPC > 500 



Page 91 


99.1JP.07 DESIGN TOOL FOR ATMOSPHERIC MISSIONS 

The Agency is now considering two Earth Explorer related to Atmospheric 

Physics and DYnamics, the Earth Radiation Mission (ERM) and the Atmospheric 

DYnamics Mission (ADM). In addition there are two sets of proposals for Earth 

Watch, Atmospheric SOunding with GPS/GLONASS signals (Atmospheric Profiling 

Earth Watch =APEW), and measurements of wind profiles (Wind Watch =WW). In 

addition studies on the European component of the future American- European 

Joint Polar System (JPS) have to start soon. Some of the observations of the 

ERM and the ADM will become operational as Earth Watch. Future JPS elements 

are not expected to be single large satellites with all instruments on the 

same platform, but rather clusters of small satellites. A design tool is 

required that allows to estimate performance for various system arrangements. 

The tool should be comprehensive, all effects relevant to the observations, 

and modular, so that new effects, sensors and clusters can be introduced. The 

tool would allow to see the effect of flying the Wind Watch at different 

orbits with different co-locations with the other operational meteorological 

satellites and thereby allow to design the Earth Watch mission profile, ie 

number and arrangement of satellites, orbits and maintenance strategies, and 

provide the inputs for satellite design and satellite - ground interfaces. 

The tool would also allow to analyse the potential for operationalisation of 

the ERM observations directly or of the enhanced interpretation capability 

acquired by co-location of currently planned imagers and sounders. The tool 

would allow to design the mini-satellite clusters that would provide the 

required operational performance for the next operational meteorology Earth 

Watch. 

ESTEC 


FUTURE PROGRAMMES DEPT / EOP-F 

FUTURE PROGRAMMES & TECHN STUDIES DIVISION / EOP-FP 

Responsible: MR TOBIAS 


C 02 

Q2 



Status: 

DAC 100-200 



Page 92 


02.2MC.02 IN ORBIT MANUFACTURE, ASSEMBLY AND SERVICING AT ISS IN 

SUPPORT OF XEUS 

N21 

ESTEC 


MANNED SPACEFLIGHT PROGRAMME DEPT / MSM-M 

COF PROJECTS DIVISION 

Responsible: MR THIRKETTLE 

Budget Ref.: 100558 - STEP 

CR 02 

Q4 

Spec. Prov.: SPACE APPLICATIONS SERVICES NV (B); VERHAERT 

DESIGN & DEVELOPMENT NV (B); DUTCH SPACE BV (NL) 



DAC > 500 



Page 93 


00.1MP.01 EVALUATION OF GREEN PROPELLANTS FOR SPACE APPLICATION 

The aim of this activity is to provide information / data to support a 

decision on future investments in the technology of non toxic propellants 

leading to hardware development. A compilation and synthesis of knowledge 

related to the use of green propellants such as H2O2 and identification of 

open technological issues requiring further investigations will be 

undertaken. The potential application of H2O2 for spacecraft and upper stage 

propulsion (monopropellant, bipropellant, hybrid) and resulting technological 

needs shall be analysed. The study should also address cost-effectiveness and 

quality issues and will involve proof of concept experimental investigations 

(lab. Level: catalytic decomposition, combustion with hydrocarbon fuels, 

combustion characteristics and products, etc.). 

ESTEC 


MECHANICAL ENGINEERING DEPT / TOS-M 

MATERIALS & PROCESSES DIV / TOS-MP 

Responsible: MR FELICI 


C 02 

Q3 


Programme Ref.: TRP MPC-842 

Status: 

DIPC 200-500 



Page 94 


01.1MS.02 OPERATIONS PREPARATION AND PLANNING SYSTEM PHASE C/D 

The execution level planning represents the final phase in the International 

Space Station (ISS) distributed operations planning process, in which the 

operations requirements and mission objectives are translated into executable 

timelines of on-board and on-ground activities. It is now required to 

continue the system development so as to be able to support the planning of 

the various ESA elements operations (i.e. ATV, Columbus) due to start in the 

first quarter of 2003. The contract is expected to start with the necessary 

post System Requirement Review work and will follow with typical phase C/D 

tasks, including production, verification and qualification of the system. A 

first period will lead to the Critical Design Review (CDR), which will 

provide the detailed definition of the system components and their 

interfaces. The second period will see the system production, integration and 

test. The contract will be considered completed when the OPPS system is fully 

integrated within the ESA MSM Ground Segment. At this point, the OPPS system 

will be delivered to the Exploitation Program Industrial Operator who will 

operate and maintain it for the entire ISS operations duration. 

ESTEC 


ISS EXPLOITATION PREPARATION DEPT / MSM-E 

OPERATIONS MANAGEMENT DIVISION / MSM-EO 

Responsible: MR CHESSON 

Budget Ref.: 100551 - ISS COF 

C 02 

Q3 



Status: INITIATED WITH 02.1MS.01 1-4280 

DIPC > 500 



Page 95 


02.1MS.01 EXECUTE LEVEL PLANNING OPERATIONS PREPARATION 

The Execute Level Planning represents the final phase in the International 

Space Station (ISS) distributed operations planning process, in which the 

operations requirements and mission objectives are translated into executable 

timelines of on-board and on-ground activities. The ESA Execute Level 

Planning Function develops the planning products necessary to execute the 

operations of the European activities on-board the ISS. An integrated 

Operations Preparation & Planning System (OPPS), composed by several software 

applications, will assist the ESA Planning Team (EPT) in the accomplishment 

of its planning tasks. In order to be able to support the planning of the 

various ESA elements operations, the Agency needs to put into place by 2003 

an operationally qualified planning system and its associated certified 

planning team of operators. The development phase of the planning system will 

cover the development of the software applications themselves (see item 

01.1MS.02). It was envisaged at that time, that the operation of the system 

developed would be directly handed over to the Exploitation Programme 

Industrial Operator. Since then, it has been considered more efficient to 

combine this development phase with the preparation of the planning team 

required to operate these tools, such as to be in a position to transfer an 

operational system to the Exploitation Programme Industrial Operator. 

Additionally this approach will enable the Agency to cope with any delays in 

effecting this transfer without impact on the performance of the planning 

tasks required by its participation to the ISS program. The subject of the 

present procurement is therefore the preparation phase for the planning team 

and would cover activities such as: * further definition and writing of the 

operational documentation; * implementation of the training plan; * support 

ESA in the monitoring of the planning system development; * refinement and 

implementation of interfaces with all external users; * support and prepare 

for the ATV first mission and Columbus first increments; * support ESA in the 

various ISS Planning forums. This phase will be concluded with the acceptance 

of the planning system and the certification of the planning team. 

ESTEC 





Budget Ref.: 100551 - ISS COF 

C 02 

Q3 



Status: INITIATED WITH 01.1MS.02 1-4280 

DIPC > 500 



Page 96 


02.1MS.04 ATV CARGO BAGS 

N25 

ESTEC 

The subject of this ITT will be the procurement, manufacturing and delivery 

of a complete set of Cargo Transfer Bags for the ATV. These bags will be 

manufactured on the basis of the NASA Cargo Transfer Bags design and used for 

the ATV cargo items packaging for flight as well as for payload storage. The 

delivery of the first batch of bags is needed for August 2003. Beyond the 

manufacturing of the first set of bags, the ITT will require the bidders to 

provide a commitment for follow on production, including price, for the 

following ATVs. The resulting contract will be placed by ESA or by the 

Industrial Operator for the Exploitation Programme. This will be decided 

after the selection process. The ITT will also address the combination of the 

bags procurement as such, with a commercial project consisting of branding 

and sponsorship opportunities for industries interested in corporate 

promotion by association with this product. 





Budget Ref.: 100552 - ISS ATV 

C 02 

Q4 




NO 200-500 



Page 97 


02.1MX.01 MAN MACHINE INTERFACE TECHNOLOGIES 

N10 

Health management is a critical technology for the cost effectiveness of 

reusable launchers. A global approach to the health management of the vehicle 

is therefore needed. Up to now and particularly in Europe, this has been 

limited to the monitoring function and furthermore in a non-integrated way, 

ie structural health monitoring separated from engine health monitoring. The 

innovative approach is characterised by the following keywords: integrated 

and intelligent. "Integrated" stands for putting all together the available 

pieces of such system taking into account all structural health, engine 

functional and structural health, vehicle functional health, flight-ground 

segments, and so forth. "Intelligent" means adding functions like prognostics 

and therapy that translate in the ability to identify real-time corrective 

actions and/or operational limitation to guarantee the completion of the 

mission in a safe condition. In order to do this, new system architectures 

(parallel computing and software technologies) are required. The present 

activity deals with feasibility analysis, system definition and real time 

aspects. 


MICROGRAVITY DEPT / MSM-M 

CRV PROJECT DIVISION / MSM-MX 

Responsible: MR CAPORICCI 


C 02 

Q3 

Spec. Prov.: 

Programme Ref.: GSTP-3 C51.MSML-016 

Status: 

02.1MX.02 ADVANCED DIAGNOSTICS FOR COMBUSTION CHAMBER 

DIPC > 500 

N10 

ESTEC 

Laser-based combustion diagnostic systems appear to be a promising way to 

analyse a high-pressure rocket engine injector flow field. This activity aims 

at the definition and development of advanced combustion diagnostic methods 

based on spontaneous Raman scattering, coherent anti-Stokes Raman Scattering 

(CARS), or other laser-based techniques, and at their application to the flow 

measurement during a hot-fire, high-pressure test of single-element 

injectors, to obtain temporally and spatially resolved information on gaseous 

species. International co-operation may be envisaged for this activity. 






C 02 

Q3 

Spec. Prov.: 


Status: 

DIPC > 500 



Page 98 


03.1MX.01 HEALTH MONITORING FOR RE-USABLE SPACE TRANSPORTATION 

N24 

Health monitoring is a critical technology for the feasibility and cost 

effectiveness of future reusable or semi-reusable space transportation means 

(re-entry vehicles, re-usable launchers). However, nowadays health monitoring 

is limited to the design of sensors and detection methods that can be 

implemented on test items. A more systematic definition of health monitoring 

requirements is needed, which considers the maintenance strategy and a the 

trade-off between turnaround time and RAMS objectives. The goal of the 

activity is to determine the correct health monitoring requirements and the 

logic of implementation of a Health Monitoring System (HMS) studying its 

impact on the vehicle turnaround operations and costs. The activity shall 

develop and validate processes for HMS design and optimisation, develop 

models and analysis means for a generic HMS architecture, demonstrate a HMS 

prototype against nominal and fault injection mission simulations. Type of 

tender C(2) - activities in open competition, where a significant 

participation of non-primes is requested. For additional information please 








C 03 

Q1 


Programme Ref.: TRP MXO-001 

Status: 

02.2MX.01 CRITICAL AEROTHERMODYNAMIC PHENOMENA AND TEST 

TECHNIQUES 

DIPC > 500 

N10 

ESTEC 

The present activity deals with improvements in the modelling of critical 

phenomena for design as well as with wind-tunnel and flight test techniques 

enhancements. 






CR 02 

Q3 

Spec. Prov.: DLR D, DASSAULT AVIATION F, ONERA F, CIRA I 


Status: 

DIPC > 500 



Page 99 


02.2MX.02 LOX-HYDROCARBON PROPELLANT STUDIES AND EXPERIMENTATION 

N10 

Very limited experience exists in Europe in the design and operation of 

LOX/hydrocarbon engines. An improvement of the state of the art in this field 

has to be achieved to acquire experience and know-how on the design and 

operation of this type of engines. This activity aims at conducting suitable 

LOX-Hydrocarbon propellant studies and experimental investigations, 

including: injection and combustion stability studies, assessment of 

generatively cooling efficiency, cocking effects, and investigation of soot 

deposits and their impact on reusability. This work will include the testing 

of injectors and a combustion chamber of appropriate scale, with some 

activities possibly done in international co-operation. 






CR 02 

Q3 

Spec. Prov.: ASTRIUM D, SNECMA F, FIAT-AVIO I 


Status: 

02.2MX.03 DEVELOPMENT OF A FLIGHT TEST BED FOR ATMOSPHERIC 

RE-ENTRY PHENOMENA 

DIPC > 500 

N10 

ESTEC 

The need for in flight aerothermodynamic research has been stressed at 

several occasions and its usefulness has been confirmed by the post-flight 

MIRKA and ARD activities. In-flight testing of critical aerothermodynamic 

phenomena is currently possible thanks to the availability of affordable 

launch vehicles. Flight data on critical aerothermodynamic phenomena are not 

only important for the verification and validation of physical modelling for 

CFD-use for design but also for the qualification of "wind-tunnel to flight 

extrapolation methodologies". 






CR 02 

Q3 

Spec. Prov.: ALENIA SPAZIO I, ASTRIUM D, EADS LV F 


Status: 

DIPC > 500 



Page 100 


02.1PU.01 PHASE C/D, MANUFACTURING, ASSEMBLY AND TESTING OF THE 

SECOND STAGE INTERMEDIATE FREQUENCY UNIT (IF-2) FOR 

THE HIFHI INSTRUMENT ON BOARD HERSCHEL SPACE 

OBSERVATORY 

N1 

ESTEC 

The HIFI instrument, on the Herschel Space Observatory of the European Space 

Agency, is one of the three instruments on Herschel and contains a high 

resolution heterodyne spectrometer for quasi-optical signals with frequencies 

between 480 and 2700 GHz, divided in 7 bands and for 2 polarisations. These 

signals are down converted using heterodyne mixing techniques to an 

intermediate frequency (IF) between 4.0 and 8.0 GHz. These IF signals are 

amplified in a first stage inside the mixer subassemblies of the instrument, 

and in a second stage inside the IF-2 unit of HIFI. The IF-2 unit contains 14 

input isolators, 14 low noise amplifiers, and 4 4x1 signal combiners. As 

such, the 14 input signals coming from 7 channels for 2 polarisations are 

amplified and combined into 4 output signals. The IF-2 unit will be mounted 

onto the focal plane unit (FPU) of HIFI and will operate at a nominal 

temperature of 10 K. The development work on the IF-2 unit has been done at 

the Microwave Electronics Laboratory of the ETH Zurich and will result in the 

delivery of a functional Development Model to the principal investigator. The 

output of the subject Phase C/D is to deliver a Qualification Model, a Flight 

Model and a Flight Spare Model. The selected contractor will be responsible 

for the manufacturing, assembly and testing of the IF-2 units for all models. 

SCIENTIFIC PROGRAMME - D/SCI 

PRODEX / SCI-R 

Responsible: MR OLTHOF 

Budget Ref.: 100110 - Prodex 1995 Onwards 

C 02 

Q2 

Spec. Prov.: LIMITED TO CH 


Status: 

DIPC > 500 



Page 101 


02.1PU.02 PHASE C/D, MANUFACTURING AND VERIFICATION OF THE MIXER 

SUB-ASSEMBLY AND DIPLEXER HOUSING THE HIFI INSTRUMENT 

ON BOARD HERSCHEL SPACE OBSERVATORY 

N1 

ESTEC 

02.1PU.05 

N25 

ESTEC 

The HIFI instrument, on the Herschel Space Observatory of the European Space 

Agency, is one of the three instruments on Herschel and it contains a high 

resolution heterodyne spectrometer for quasi-optical signals with frequencies 

between 480 and 1900 GHz, divided in 7 bands. The re-imaging of the sub 

mile-meter radiation from the telescope towards the 14 Mixer Sub-Assemblies 

(MSA), 2 per band, is done in a Common Optics Assembly (COA), which contains 

a set of common mirrors for all 7 bands, as well as a diplexer to split the 

two polarisations for each band. The output of the subject Phase C/D is the 

delivery of 14 MSA and 7 Diplexers housings for the flight HIFI instrument as 

well as the procurement of 7 MSA and 7 diplexers housings as Flight Spares. 

The MSA and the Diplexers will be integrated with the COA to form the Focal 

Plane unit of the HIFI instrument. The selected contractor shall be 

responsible for the manufacturing and verification of the MSA and Diplexer 

housings. 


PRODEX / SCI-R 



C 02 

Q2 

Spec. Prov.: LIMITED TO CH 


Status: 

COROT COVER 

The purpose of this procurement is to define all tasks, working policies, 

organisation and deliverables related to the procurement of the "COROT Cover 

System". The selected contractor will be responsible for the final design, 

manufacturing, assembly and verification of two physical models (QM and FM)of 

the COROT Cover System. The cover purpose is to prevent contamination of the 

internal cavity of the baffle and telescope during ground testing and launch. 

It also provides a protection for the detector chain against direct sun view 

during commissioning of the spacecraft in orbit. The cover restraint, release 

and opening mechanisms have been pre-designed and tested on a prototype. The 

working principle is based on techniques already used for earlier projects. 



MECHANICAL SYSTEMS DIVISION / TOS-MM 



C 02 

Q4 

Spec. Prov.: LIMITED TO B 



DAC > 500 

NO 200-500 



Page 102 


01.1QC.02 CRITICAL EVALUATION TECHNIQUES FOR MICROMACHINED 

DEVICES 

Many initiatives to develop micromachined components are pursued by ESA. The 

mechanical and electrical properties of the materials used is generally 

poorly known and poorly controlled, often leading to designs that do not work 

as expected in practice. The objective of this activity is the development of 

techniques for measurement and control of properties (Electrical, stress, 

expansion coefficients, etc.) of micromachining materials and for reliability 

testing of completed micromachined components. Type of tender C(2) - 




programmes". 


PRODUCT ASSURANCE AND SAFETY DEPARTMENT / TOS-Q 

COMPONENTS DIVISION / TOS-QC 

Responsible: MR KALLBERG 


C 02 

Q2 


Programme Ref.: TRP T-S-QCT-02-FZ4 

Status: 

01.1QC.07 INVESTIGATION ON USE OF BUMPED MMIC 

DAC 200-500 

ESTEC 

Bumped MMICs are currently being introduced in industry for microwave hybrid 

applications. This activity shall determine the current range of suppliers 

and users, the materials/processes used and identify potential test problems 

and performance limitations. This shall include the procurement, assembly and 

testing of samples for characterisation. 






C 02 

Q2 


Programme Ref.: TRP GAD 6.01 

Status: 

NO 50-100 



Page 103 


01.1QC.08 RELIABILITY ASSESSMENT OF EUROPEAN POWER MOSFETS PHASE 

1 AND 2 

European Space projects are heavily dependent on US suppliers for radiation 

tolerant/hard Power MOSFET devices, critical components in all spacecraft 

power systems. A basic radiation characterisation programme covering various 

commercial products from European manufacturers has been performed yielding 

some promising results. Further work is required and foreseen to be performed 

in the frame of this activity to establish the reliability data to determine 

their space application and possible radiation hardening potential. Type of 









C 02 

Q3 


Programme Ref.: TRP GAD 2.06.C 


01.1QC.09 EVALUATION OF FLIP-CHIP MOUNTING TECHNOLOGY AND 

ASSESSMENT OF RELIABILITY ENHANCEMENT BY THE USE OF 

UNDERFILL 

DIPC 100-200 

ESTEC 

Flip-chip technology although not new, has almost never been used for space 

applications. The aim of this activity is to investigate flip-chip technology 

for its possible utilisation in space. Various flip-chip assembly techniques 

in terms of chip and substrate types, bonding and underfill materials, are 

proposed to be manufactured and tested in order to assess their suitability 

for high reliability applications. It is also expected that the effectiveness 

of current nondestructive inspection techniques for the quality assessment of 

the flip-chip mounting, including underfill, will be verified and 

recommendations suggested. 






C 02 

Q3 


Programme Ref.: TRP GAD 3.08 

Status: CHANGED TO 01.3QC.13 

NO 100-200 



Page 104 


02.1QC.01 POWER AND THERMAL MANAGEMENT OF WIDE BANDGAP 

SEMICONDUCTORS 

N10 

To deal with the huge power density and to exploit the high temperature 

performances of Wide Bandgap devices, new structures and processes need to be 

developed for the thermal management on the die and in its environment. This 

is covered in a new research area called "Power and Thermal Management" in 

electronic component technology. This includes 3D thermal management, high 

temperature metallurgy in microelectronic chip processing, the introduction 

of very low thermal resistivity refractory structures directly or indirectly 

on the chip and necessarily new concepts of heat removal from the chip and 

housing structures. These actions will be initiated through a preliminary 

"brainstorming" phase followed by a full development of the most promising 

concepts. Microwave performance and industrial feasibility will be taken into 

account all along the programme and demonstrators required (e.g. 25W/mm heat 

removal capability in L-Band and 15W/mm @ 20 GHz). Type of tender C(1) - 









C 02 

Q4 


Programme Ref.: TRP QCT-003 


02.1QC.02 MICROWAVE FREQUENCY CAPABILITY OF WIDE BANDGAP 

SEMICONDUCTORS 

DIPC > 500 

N10 

ESTEC 

Operations up to 20 GHz has already been demonstrated overseas thanks to the 

continuous improvement of the GaN semiconductor material. No European 

activity has been initiated in the Ka-Band (30 GHz) frequency domain where 

VSAT and Satcom Multimedia System applications could benefit from the 

advantage of Wide Bandgap technology for direct satellite to home 

communication. Operation in V and W-Band are also theoretically possible but 

have never been attempted. It is therefore proposed to initiate a set of 

activities primarily to develop and demonstrate GaN components suitable for 

Ka-Band digital communication applications (objective >5W/die, 10 dB @ 30 

GHz) and later to assess the potential of this component technology toward 

the higher frequency domain (V-W-Bands). Ft of 160 GHz (Lg: 0.5 W/die @ 100 GHz should be considered. Type of tender C(1) - 









C 02 

Q4 




DIPC > 500 



Page 105 


02.1QC.03 DETECTORS BASED ON GAN SEMICONDUCTORS 

N10 

Single cell GaN solar blind UV detectors have already been demonstrated. No 

demonstration of 2 dimensional array and limited comparison with available 

technology has been carried out. It is therefore proposed to initiate a 

component demonstration activity to assess the potential and advantage of 

this technology for UV 2D detectors operating at ambient temperature. Type of 









C 02 

Q4 



Status: 

02.1QC.04 COMPONENTS FOR HIGH POWER CONDITIONING APPLICATIONS 

YAC 200-500 

N10 

ESTEC 

SiC is seen as an exceptional semiconductor for power conditioning systems. 

The main advantages are its excellent thermal conductivity and power 

handling. A large amount of DC/DC converters are on board each spacecraft and 

the use of SiC devices should allow higher switching frequency reducing 

losses, size and mass of the DC/DC converters. A preliminary investigation, 

restricted to Schottky diodes only, has already been initiated and shown the 

potential of this technology. This activity shall investigate the feasibility 

of PIN diodes and in particular the technology of P-doped materials and 

associated metallisation scheme, allowing the development of bipolar and 

hetero bipolar structures, barely addressed today within the development of 

wide bandgap semiconductor technology. Type of tender C(1) - activities in 









C 02 

Q4 



Status: 

YIPC 200-500 



Page 106 


02.1QC.05 WIDE BANDGAP COMPONENTS FOR X-BAND TT & C SSPA 

DEMONSTRATOR 

N10 

ESTEC 

The aim of the activity is to develop components for a Solid State Power 

Amplifier (SSPA). It is expected to get first devices by end of 2003 for 

application up to X-Band. On this basis, this activity will be dedicated to 

the development of a breadboard amplifier suitable for TT&C in X-Band with an 

output power of 15 to 30 Watts. The activity will also include a preliminary 

reliability and environmental testing of the components in order to assess 

the feasibility of a flight demonstrator. Type of tender C(1) - activities in 









C 02 

Q4 




DAC 200-500 



Page 107 


01.1QM.01 MATERIAL CHARACTERISATION FOR PLASMA INTERACTION 

ANALYSIS 

There is a need to refine the characterisation of material properties for 

spacecraft-plasma interaction prediction. Based on the results of EMA-022 

"Spacecraft Charging and Interaction Guidelines", which will identify the 

properties to be characterised, the European facilities will be reviewed and 

optimisation of test procedures will be defined. Moreover a series of test 

will be conducted on new materials and a database of these material 

properties will be created. The activity can be divided in 4 main 

sub-activities: (1) analysis of requirements and review of facilities, (2) 

definition and optimisation of test procedures, (3) characterisation of a few 

materials, (4) creation of data base. Type of tender C(1) - activities in 




ESTEC 



MATERIALS AND PROCESSES DIVISION / TOS-QM 

Responsible: MR DUNN 


C 02 

Q2 


Programme Ref.: TRP T-M-QMC-13-02 


DAC 200-500 



Page 108 


00.1QQ.02 QUALITY ASSURANCE FOR AUTOMATIC CODE GENERATION 

The purpose of this activity is to identify methods and techniques adequate 

to ensure the quality of the code generated by automatic code generation 

tools. For this purpose different types of tools in current use or 

prospective in space projects shall be identified (tools to generate complete 

applications, analysis and design tools, etc.). The requirements on the 

software development lifecycle (verification phases in particular) imposed by 

each type of tool shall be defined. On the basis of the outputs of the above 

activities requirements, methods and techniques to ensure the quality of the 

produced code shall be defined. These shall include at least: qualification 

of tools and automatic verification of generated code (automatic test case 

generation in particular). The results of this study shall be applied to the 

tool or tools selected in action item reference 00.1EM.01 (EME-011). 



QUALITY, DEPENDABILITY AND SAFETY DIVISION / TOS-QQ 

Responsible: Mr CIASCHI 


C 02 

Q2 


Programme Ref.: TRP T-M-QQS-14-4 


00.1QQ.03 PRODUCT ASSURANCE & SAFETY AND QUALITY MANAGEMENT 

SUPPORT 

DAC 200-500 

ESTEC 

Product Assurance (PA) and Safety support to projects are provided by staff 

from the PA and Safety Department (TOS-Q), in the form of either integrated 

or functional support. Experience has shown that temporary unexpected 

problems occur leading to peaks of support workload which cannot be covered 

by available ESA PA staff. In addition, projects for the development of 

Quality Management Systems and their certification to ISO 9001 have been 

initiated after the certification of ESOC to ISO 9001 in the Directorate of 

Application Programmes (Earth Observation Applications Department in ESRIN) 

and in the Directorate of Administration (Information Services Department in 

ESRIN). Similar activities in other areas can be expected to arise in the 

future, probably at a growing rate. Based on this, a frame contract is needed 

for a prompt and flexible deployment of temporary external resources in the 

Product Assurance & Safety and Quality Management fields. The tasks to be 

covered by the Contractor are the following: - Temporary provision of PA and 

Safety support to respond to specific and temporary project needs; - 

Temporary assistance with the design, development and implementation in 

several ESA departments of quality management systems, typically in 

accordance with the international quality standard ISO 9001. 



QUALITY, DEPENDABILITY AND SAFETY DIVISION / TOS-QQ 

Responsible: Mr CIASCHI 

Budget Ref.: 100932 - Technical Support 

C 02 

Q2 




DIPC > 500 



Page 109 


02.1SA.01 TECHNICAL ASSISTANCE IN SUPPORT OF GAIA SCIENCE 

OPERATIONS 

N19 

ESTEC 

GAIA is an approved cornerstone mission in the Agency’s science programme, 

due for launch around 2010. GAIA builds upon the observational techniques 

pioneered and proven by ESA’s Hipparcos mission. It will create an 

extraordinarily precise three-dimensional map of about one billion stars 

throughout our Galaxy and beyond. In the process, by combining this 

positional data with radial velocity data acquired by the satellite, it will 

map the stellar motions, which encode the origin and subsequent evolution of 

the Galaxy. Through comprehensive photometric classification, again using 

data acquired by the satellite, GAIA will provide the detailed physical 

properties of each star observed, characterising their luminosity, 

temperature, gravity, and elemental composition. The technology development 

programme for GAIA is now underway, and the external scientific structure, 

comprising some 200 scientists in 20 scientific working groups from some 60 

scientific institutes within Europe, has also been established. Development 

of the data analysis prototype, which will handle the massive data set from 

the satellite, is also under development. The present proposition is meant to 

support the execution of the scientific operations tasks, which are to be 

carried out by the Research and Scientific Support Department at ESTEC. 


SPACE SCIENCE DEPARTMENT / SCI-S 

ASTROPHYSICS DIVISION / SCI-SA 

Responsible: MR CLAVEL 

Budget Ref.: 100175 - Gaia Scientific Operations 

C 02 

Q4 




DAC > 500 



Page 110 


02.1SD.01 DATA SYSTEMS SOFTWARE ENGINEER FOR XMM NEWTON 

OBSERVATORY 

N12 

ESTEC 

02.1SD.02 

N12 

ESTEC 

02.2SD.03 

N25 

ESTEC 



SCIENCE OPERATIONS & DATA SYSTEMS / SCI-SD 

Responsible: MR KESSLER 

Budget Ref.: 

C 02 

Q4 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+IRL+A+N+FIN 



XMM NEWTON S0C SOFTWARE INTEGRATION ENGINEER 





Budget Ref.: 

C 02 

Q4 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+IRL+A+N+FIN 



TECHNICAL ASSISTANCE IN THE UNIX COMPUTER SYSTEM 





Budget Ref.: 100255 - Integral Scientific Operations; 100242 

CR 02 

Q4 

- XMM Scientific Operations; 100292 - Herschel 

Science Operations; 100029 - Space Science 

Spec. Prov.: TERMA A/S (NL); AEM SPACE SYSTEM BV (NL); AURORA 

TECHNOLOGY BV (NL); SERCO FACILITIES MANAGEMENT 

BV (NL); VEGA GROUP PLC (GB) 



NO 200-500 

NO 200-500 

NO 50-100 



Page 111 


97.1WA.02 AI TECHNOLOGIES IN SUPPORT TO ON-BOARD CREW TRAINING 

The proposed will focus on how a tool based on AI technologies, namely Expert 

Systems, could best meet in orbit crew training requirements specifically in 

the conditions of long in-orbit stay. The study is finalised to the 

development of a prototype ES, able to perform advanced, dynamically, 

configurable on-board training sessions, tailored on each crew member. Real 

training scenarios will be addressed and matched on actual Manned Space 

Programme requirements. The following aspects will be specifically addressed: 

man machine interface; capacity of tuning, training session with the mission 

profile as well as the astronaut personal characteristics; architectural 

solutions for its use in a manned space module, according to specific 

constraints of the orbital environment; evaluation of available technologies 

for their possible integration in the set of tools. Candidate to support crew 

member during their orbit stay time. 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/H70.6-WA201 

Status: CHANGED TO 02.3EM.06 

DAC 200-500 



Page 112 


99.1WM.09 INTERNET AND INTEROPERABLE TECHNOLOGIES FOR ON-BOARD 

S/W 

The project shall examine technologies such as Java and Corba which have been 

developed for use on internet/intranet applications but have characteristics 

which could be of use in the future for On-Board software. These technologies 

are increasing rapidly and it is necessary for the Agency to appreciate the 

capabilities of these technologies. 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP 98/WME02 

Status: 

NO 50-100 



Page 113 


99.1WS.01 EUROPEAN ENHANCED FORMATION FLYING 

The activity concerns the design, development, manufacturing, and testing of 

a unit, called European Enhanced Formation Flying EEFF). Two or more of these 

units allow autonomously reaching and maintaining a very high stable 

formation flying of more than two craft, without external intervention and in 

complex navigation environments. The proposed activity includes the 

development and testing of guidance and navigation algorithms, control laws 

and autonomous orbit control. Two EEFF units shall be delivered for testing 

the formation flying system. This system will give the possibility to 

distribute a payload among several craft reducing risks, increasing 

flexibility, and guarantying availability through redundancy. As a 

consequence there will be a reduction on production cost for flight hardware 

and software by reuse of components. This activity will maintain also a 

high-tech profile of European companies in formation flying for craft 

constellation technology. 

ESTEC 






C 02 

Q2 

Spec. Prov.: IRL 

Programme Ref.: GSTP-3 G00/B31.9A-WS223 


DIPC > 500 



Page 114 


00.1XA.02 OPTICAL NARROW-BAND BACKGROUND REJECTION FILTER 

A key-unit for the achievement of the radiometric performance of ATLID is the 

background rejection filter. Quasi-monolithic filters, based on molecular 

adhesion techniques or treated with ion-assisted coatings, can provide very 

narrow transmission bandwidths. Futhermore these technologies allow to 

increase the filter robustness and to better stabilise the center wavelength 

against the thermal drift of the satellite environment. The aim of the 

proposal is to design, manufacture and test such a filter and to perform an 

extensive functional and environmental testing campaign. 

ESTEC 




Responsible: MR LUTZ 


C 02 

Q2 

Spec. Prov.: F+IRL 

Programme Ref.: GSTP-3 G00/A03.XA-209 


NO 200-500 



Page 115 


96.1XE.05 ANTENNAS WITH ACTIVE COMPENSATION 

Development of future antenna systems in Ku-band and above to converse/reduce 

the satellite on-board power resource to give higher performance and possibly 

lower overall costs. Initial studies have shown great advantages to the link 

performance of both shaped and multibeam systems when active compensation for 

fading is implemented. The study shall include a more systematic evaluation 

of the fade associated with the frontal systems and shall be followed by 

detailed design breadboarding and testing of the necessary antenna system. 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/B50.2-XE201 

Status: 

DIPC 200-500 



Page 116 


97.1XR.29 RECONFIGURABLE OUTPUT SECTIONS 

Future telecommunication satellites (FSS/BSS) and multi-media missions at 

Ka-band will provide considerably higher than current and existing designs, 

requiring the use of multiple transmit beams. The need for providing flexible 

re apportionment of traffic between beams as well as capability of 

reconfiguring beams will be essential to achieve high overall efficiency. The 

Butler matrix concept, demonstrated already at Ku-band, shall be investigated 

for Ka-band applications ie with higher number of beams and heavy channel 

coding. This can be applicable for implementation in optional programmes eg 

ASTE. 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP 97/XRP01 


NO 100-200 



Page 117 


98.1YM.02 LOW FRICTION SOLAR ARRAY HINGE 

The deployment of spring-actuated solar arrays has to be performed with a 

substantial motorisation margin for high reliability, altogether with a low 

mechanical energy to minimise the end of deployment reducing as far as 

possible the friction variability of their resistive components (bushing, 

cams, spring effects) with respect to environment. 

ESTEC 






C 02 

Q2 

Spec. Prov.: B+E 

Programme Ref.: GSTP-3 G00/B34.9A-YM225 

Status: 

DAC 200-500 



Page 118 


98.1YP.02 STANDARD MODEL TESTING IN PLASMA FACILITIES 

Materials able to withstand high temperatures are continuously being 

developed and improved. An important investment has been made in Europe to 

improve the testing of such materials, through the development of new 

facilities (VKI plasmatron, CIRA’s SCIROCCO, Aerospatiale’s SIMOUN, DLR’s 

L3K,...).To increase the return on this investment, it is proposed to improve 

the present material testing techniques, by improving the knowledge of the 

facilities, instrumentations, procedures and methodologies. 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP 97/YPA03 


NO 100-200 



Page 119 


01.111.01 DEPLOYMENT OF A UNIVERSAL CABLING INFRASTRUCTURE AT 

ESOC 

This activity concerns the modernisation of the cabling systems at ESOC. The 

present computer cabling standard is the Universal Cabling System (UCS) 

called Cat 5 or Cat 6. Some of the ESOC Buildings are still equipped with the 

IBM type 1 data cabling system limiting the amount of information to be sent. 

Old cabling system shall be replaced in favour of the modern standard to stay 

in line with ESA standard and user requiements. The execution will be spread 

over a maximum of 5 years 

ESOC DIRECTORATE OF ADMINISTRATION - D/ADM 

ESA SITE MANAGEMENT SERVICES / ADM-G 

ESOC SITE MANAGEMENT SERVICES / ADM-GC 

Responsible: Mr OPPERMANN 

Budget Ref.: 100926 - Site Services 

C 02 

Q2 


Programme Ref.: ESOC-I-01-020 

Status: 

02.111.01 CLEANING SERVICES IN ESOC FROM 01-05-2002 

DAC > 500 

N3 

ESOC DIRECTORATE OF ADMINISTRATION - D/ADM 





C 02 

Q2 

Spec. Prov.: LOCAL TENDER D 

Programme Ref.: ESOC-M-02-121 


02.111.02 GARDENING SERVICES IN ESOC FROM 2002 ONWARDS 

DAC > 500 

N3 

ESOC 

DIRECTORATE OF ADMINISTRATION - D/ADM 





C 02 

Q2 

Spec. Prov.: LOCAL TENDER D 

Programme Ref.: ESOC-M-02-130 

Status: 

DAC 200-500 



Page 120 


00.112.09 DSP PROCESSOR FOR ANTENNA ARRAYING 

For support of Deep Space missions very large antenna apertures are needed. 

By arraying and processing the same signal received by several antennas, a 

reliable demodulation can be carried out. The objective of this activity is 

to validate the concept and build and test a breadboard and test it on two 

antennas. Based on the Rosetta mission requirements, a number of Digital 

Signal Processing algorithms shall be investigated and simulated. In 

parallel, a programmable hardware/DSP design shall be investigated for the 

proper interfacing to the ESTRACK standard receiving system (IFMS). 

ESOC TECHNICAL & OPERATIONAL SUPPORT - D/TOS 

GROUND SYSTEMS ENGINEERING DEPT / TOS-G 

STATION SYSTEMS DIV / TOS-GS 

Responsible: MR JENSEN 


C 02 

Q2 


Programme Ref.: TRP GSS-037 

Status: 

00.112.16 IMPLEMENTATION OF A CCSDS DECOMPRESSION LIBRARY FOR 

LOSSY COMPRESSION 

NO 100-200 

ESOC 

Data compression has been suggested for many space science exploration 

mission applications to either increase the science return or to reduce the 

requirement for on-board memory, station contact time, and data archival 

volume. The technical activity that forms the object of this Study is the 

design and implementation of a (ANSI C) CCSDS Lossy Decompression Library 

platform and application independent. The following objectives are envisaged: 

1. Definition of a clear set of requirements. 2. Architectural design of the 

Library. 3. Implementation of the Library. 4. Validation of the library and 

demonstration of integrity in host system(s). 






C 02 

Q2 

Spec. Prov.: D+I 

Programme Ref.: GSTP-3 G00/E59.GSD-048 

Status: 

DAC 100-200 



Page 121 


00.112.19 REAL-TIME HARDWARE EMULATION OF ERC-32 PROCESSOR 

An "off the shelf" hardware emulator of the ERC-32 processor has been 

developed in the frame of a TOS-EMS study contract. It is based upon a CHESS 

Engineering SHAM4 system. This emulator is being used mainly in Software 

Verification Facilities (SVF) for which there is no requirement to operate in 

hard real-time (simulated real-time is the term used to describe the 

behaviour of the emulator in the frame of SVFs). ESOC simulators have to 

operate in hard real-time, in particular for what concerns the execution of 

the flight software. The feasibility of using SHAM4 based systems within such 

simulators is not obvious and needs to be investigated. The objective of the 

proposed study is to analyse and, if applicable, to demonstrate the 

feasibility of using a SHAM4 system, together with SIMSAT-NT (Windows-NT 

based simulation infrastructure) to produce a real-time simulator for a 

complex mission. 

ESOC 



Responsible: MR J.F.KAUFELER 


C 02 

Q2 

Spec. Prov.: B+DK 

Programme Ref.: GSTP-3 G00/E62.GMS-050 


00.112.20 PC-BASED DISTRIBUTED SIMSAT-NT SIMULATION 

DIPC 200-500 

The version of SIMSAT currently being reengineered for Windows-NT systems 

(DEC Alpha and PC) will support decentralisation only as far as the 

man-machine interface and the ground station equipment models are concerned 

(they can run in a different machine from the main simulation). The objective 

of the proposed study is to analyse and, if applicable, to demonstrate the 

feasibility of modifying the architecture of SIMSAT-NT in such a way that it 

will enable the distributed execution of spacecraft models over several PCs. 

A further application of this distribution would be for missions involving 

several spacecraft which could be developed and run independently from each 

other (e.g. Cluster-type or Orbiter/lander-type configuration). A 

prerequisite for such a distributed simulation would be that all elements can 

be commanded from a single MMI application. 

ESOC 





C 02 

Q2 

Spec. Prov.: B+NL 

Programme Ref.: GSTP-3 G00/E62.GMS-009 


DAC 200-500 



Page 122 


00.112.21 IMPLEMENTATION OF A CCSDS FILE DELIVERY PROTOCOL 

LIBRARY 

The reliable transmission of bulk data between spacecraft and the ground 

segment is an increasingly common requirement. In order to reduce future 

mission costs and to increase opportunities for space/ground segment 

interoperability, the Recommendation of a CCSDS File Delivery Protocol (CFDP) 

is being approved by the Consultative Committee for Space Data Systems. The 

technical activity that forms the object of this Study is the design and 

implementation of a (ANSI C) CCSDS File Delivery Protocol Library the 

platform and application independent. The following objectives are envisaged: 

1. Definition of a clear set of requirements 2. Architectural design of the 

Library 3. Implementation of the Library 4. Validation of the Library and 

demonstration of integrity in host system(s). 






C 02 

Q2 

Spec. Prov.: I 

Programme Ref.: GSTP-3 G00/E59.GSD-046 

Status: 

01.112.05 SPACE-BASED OPTICAL OBSERVATION OF SPACE DEBRIS 

NO 100-200 

Currently about 10,000 objects larger than 10-30 cm in Low-Earth Orbit (LEO) 

and 1 meter in the geostationary ring are regularly tracked by the space 

surveillance networks of the US and Russia. This is the catalogued population 

with 94% debris objects and 6% operational spacecraft. In addition, a 

population of about 100,000 to 200,000 objects larger than 1 cm is in orbit, 

where only statistical information is available on their orbits. While 

primarily ground-based radars and optical telescopes are used for tracking 

space objects, some sensors are on orbiting platforms, such as the US 

Midcourse Space Experiment (MSX) satellite, which is in a near-polar orbit at 

900 km altitude. With ground-based detection and tracking in routine 

operations, the minimum size of detectable space objects is typically 10-30 

cm in Low Earth Orbit (LEO) and about 1 meter in the geostationary ring. With 

space based optical observations (active or passive) much smaller objects in 

the cm to mm size region can be detected and tracked.The purpose of this 

study is to analyse the feasibility for small-size debris detection and 

tracking with space-based optical sensors. Technical solutions based on 

active and passive sensors shall be analysed and compared for LEO and the 

geostatioanry ring. For the most promising concepts a system optimization 

shall be carried out in terms of performance, mass, power, data processing 

and other relevant parameters. The optical sensor should permit observations 

of catalogued objects and statistical volume searches of the local space. 

ESOC 




Budget Ref.: 100860 - Space Debris activities 

C 02 

Q4 




DIPC > 500 



Page 123 


02.112.03 MONITORING AND CONTROL MODULE ACQUISITION NODE 

N3 

A new monitoring and control (M&C) module is required. The system shall 

convert the data from/to the Central Station Monitoring and Control System 

to/from the various equipment in the station. The system will be deployed to 

the ESA ground stations. 






C 02 

Q4 



Status: 

02.112.04 TELEMETRY AND TELECOMMAND DEVELOPMENT 

NO 200-500 

N3 

The future Telemetry and Telecommand systems shall respond to requirements 

defined to support forthcoming ESA missions. The systems, after validation, 

will be deployed to the ESA ground stations. 




Responsible: MR PECCIA 


C 02 

Q4 



Status: 

02.112.05 CCSDS WHITE BOOK FOR TRACKING AND RANGING 

YIPC > 500 

N3 

ESOC 

In collaboration with the Agency the Contractor shall prepare the 

recommendations related to tracking and ranging services. Those 

recommendation will be included in the suite of CCSDS (Consultative Committee 

for Space Data Systems) recommendations for ground segment services. 





Budget Ref.: 100975 - Corporate and Admin Costs - D/TOS 

C 02 

Q2 


Programme Ref.: 01GSD06 (D/TOS STUDY PLAN) 

Status: 

NO 50-100 



Page 124 


02.112.06 MAINTENANCE & OPERATION OF THE TOS-G ENGINEERING 

FACILITIES 

N8 

The Ground Segment Engineering Department is responsible for the procurement 

of facilities required by the Agency for the control and operation of 

satellites in orbit and the acquisition of data from the satellite payload 

elements. These facilities comprise the ground stations, the operations 

control centres and the communications systems required to transport data 

between these two elements. Consequently, the Department’s responsibilities 

include the study and analysis of operational requirements, the choice of 

appropriate ground segment configurations and specification, procurement, 

installation and setting to work of the required systems and equipment. The 

Department also provides technical support for the maintenance of existing 

operational facilities. This support imposes the identification and 

rectification of major design deficiencies and the design and implementation 

of major modifications. In order to meet its responsibilities, the Department 

requires the support of a contractor to Maintain & Operate the following 

facilities: - a pool of standard test equipment - an engineering test station 

- a ground system integration area - a mechanical & electrical workshop - an 

equipment ready store - digital & RL Laboratories and provide the following 

engineering tasks: design and production of special-to-type equipment as 

required for ground station integration and post-design and 

post-installation, modification and rectification of operational systems. 

The contractor is also required to provide support services, which are 

related to the above i.e. technical administration, drawing support, 

documentation and library services, operational and systems computer support. 





Budget Ref.: 100953 - Basic Maint. & Managt Inv.Plan; 100953 

C 02 

Q3 

- Basic Maint. & Managt Inv.Plan 



Status: 

02.112.07 KIRUNA BACKEND UPGRADE 

DIPC > 500 

N9 

ESOC 

The Kiruna upgrade is mainly an integration task which embraces the design, 

installation and testing of a fully redundant backend chain. The signals are 

in the downlink received at intermediate frequency, demodulated and decoded. 

The uplink is treated in an equivalent manner. The integration shall be 

performed with either COTS items or with a blend of COTS and Customer 

Furnished Items. 





Budget Ref.: 100952 - Investment; 100774 - Earth Explorer 

C 02 

Q3 

Core Mission 2; 100773 - Earth Explorer Core 

Mission 1 



Status: 

YIPC > 500 



Page 125 


02.112.08 DEBRIS RISK ASSESSMENT AND MITIGATION ANALYSIS TOOL 

N22 

ESOC 

In order to assist ESA and national programs in performing orbital debris 

assessments in compliance with the "European Space Debris Safety and 

Mitigation Standard" a standardized software tool will be needed. The 

"European Space Debris Safety and Mitigation Standard", developed by ESA and 

National Space Agencies in the framework of the Network of Centers - 

Coordination Group Space Debris, is currently in its final review process. 

Later, it will be harmonized with global debris mitigation guidelines under 

development by the Inter-Agency Space Debris Coordination Committee (IADC). 

The European "Debris Risk Assessment and Mitigation Analysis" tool (DRAMA) 

shall cover all major risk and mitigation aspects, including debris and 

meteoroid flux, impact damage analysis for orbiting spacecraft, avoidance 

manoeuvres, de-orbiting (direct or to reduced lifetime orbits); prediction of 

orbital lifetimes (also on highly eccentric orbits); analysis of the 

atmospheric re-entry of an object. The analytical aspects of atmospheric 

re-entry, with possible spacecraft demise and/or fragmentation and debris 

dispersion on ground, including the analysis of related risks on ground, will 

be analysed in a parallel activity of ESA and CNES in the framework of the 

Network of Centers - Coordination Group Space Debris. The software shall be 

provided on a single CD ROM and shall run on most of today’s desktop 

computers and operating systems. 



MISSION ANALYSIS OFFICE / TOS-GA 


Budget Ref.: 100860 - Space Debris activities 

C 02 

Q4 




DAC 100-200 



Page 126 


02.117.01 PROCUREMENT OF AN ESA DEEP SPACE ANTENNA AT CEBREROS / 

VILLAFRANCA, SPAIN 

N3 

ESOC 

The European Space Agency operates and maintains a network of ground 

stations, which is currently being extended to include a 35m Deep Space 

Ground Station at New Norcia (Western Australia). This station will initially 

provide prime support to Rosetta and Mars Express. Several other missions in 

the 2005/2010 time frame require tracking time which cannot be provided by 

the current ESA ground station network alone. The Executive has determined 

that it is necessary to have a second deep space ground station as part of 

its infrastructure to maintain the support capability to its present and 

future missions. To complement the coverage provided by the New Norcia 

station and considering the radio frequency and meteorological constraints 

together with the need for cost efficient operations and maintenance it is 

planned to install the second deep space antenna at Cebreros/Villafranca 

(Spain). 


MISSION OPERATIONS DEPT / TOS-O 

Responsible: MR FRANK 

Budget Ref.: 100952 - Investment; 100171 - Bepi Colombo 

C 02 

Q4 

Development 




DIPC > 500 



Page 127 


02.117.04 FUTURE GROUND SEGMENT COMPUTER PLATFORMS 

The current ESA Ground segment IT infrastructure is predominantly based on 

VAX/VMS (old generation) and Sun/Solaris (latest generation). Other low cost 

platforms offer the potential to meet the technical requirements of the 

Ground Segment, and reduce the life-cycle IT operations costs. An example 

would be Linux on Intel hardware. The activity shall investigate these 

options considering the Ground Segment technical requirements and IT 

operations across the full mission lifecycle, which may extend over many 

years. The objectives of the activity, based on standard industry practices, 

are: to identify hardware, operating system and software configurations 

capable of meeting the Ground Segment operational requirements, e.g. 

availability, performance, security, operability and maintainability. In 

addition the total cost of operations for these configurations across a 

typical mission life cycle have to be estimated and the result of the 

trade-off shall be presented. All phases of the mission must be considered. 

initial planning, design, procurement, integration, test, maintenance, 

operations and phase-out. The identification of a low cost IT platform will 

lead to a reduction in overall cost of operations, e.g. in the area of 

procurement and running costs. The results of this activity will also be of 

interest to SMEs, which are currently developing Ground Segment systems 

together with the Agency. 

ESOC 


MISSION OPERATIONS DEPT / TOS-O 

Responsible: MR FRANK 


C 02 

Q3 

Spec. Prov.: 

Programme Ref.: GSTP-3 E61-ESO-002 

Status: 

DIPC 50-100 



Page 128 


01.120.02 GENERAL SERVICES AT ESTEC (PREVIOUS TITLE : 

COMMUNICATION SERVICES AT ESTEC) 

Provision of general services under a new contract. These services consist of 

: switchboard, reception, helpdesk, audio visual support and site coordinator 

ESTEC DIRECTORATE OF ADMINISTRATION - D/ADM 


ESTEC SITE MANAGEMENT SERVICES / ADM-GT 

Responsible: MR CANNOCK 


C 02 

Q3 


Programme Ref.: ESTEC-M-01-040 

Status: ON HOLD 1-4319 

01.120.05 CONSTRUCTION OF NEW LABORATORIES BUILDING 

DIPC > 500 

Construction of the next phase of the asbestos removal programme at ESTEC, 

i.e. the construction of a large building aimed at housing the laboratories 

and staff presently located in buildings Bb and Eb that are earmarked for 

demolition 






C 02 

Q2 


Programme Ref.: ESTEC-I-01-090 

Status: 

01.120.06 BANKING SERVICES 

DAC > 500 

This activity covers the provision of banking services on site for a new 

period of 5 years as from 2002 





Budget Ref.: 

C 02 

Q2 


Programme Ref.: ESTEC-G-01-010 

Status: 

02.120.02 DEMOLITION OF BUILDING EF/EG ON ESTEC SITE 

DAC 

N21 

ESTEC 






C 02 

Q4 

Spec. Prov.: LOCAL TENDER LIMITED TO NL 



DAC > 500 



Page 129 


02.120.03 ACCOMODATION OF THE TRAINING CENTER IN BUILDING YB 

ESCAPE 

N21 

ESTEC 






C 02 

Q4 

Spec. Prov.: LOCAL TENDER LIMITED TO NL 



DAC > 500 



Page 130 


01.123.04 MECHANICAL ENGINEERING DEPARTMENT TECHNICAL SUPPORT 

For several years the Mechanical Engineering Department (TOS-M) has 

complemented the support provided by the Department by a contractor to 

address manpower constraints and support fluctuations. The approach has been 

very effective and flexible in covering various support requests, and 

consequently it is intended to apply the same approach in the future. The 

activities to be performed cover specialised support in several technical 

fields e.g. structures, mechanisms, thermal, aerothermodynamics, and 

encompass the establishment and definition of requirements, preliminary 

identification of configuration concepts, and review of technical findings 

and critical evaluations. In addition, assessments are performed in case of 

failure and of critical effects on mission success where such activities need 

to be performed by competent, independent assessors. The contract would be a 

frame contract allowing flexibility to adjust to ESA requirements. 

ESTEC 



Responsible: MR STAVRINIDIS 

Budget Ref.: 100932 - Technical Support 

C 02 

Q2 



Status: 

01.123.09 VALIDATION OF MULTIPHASE FLOW MODELS 

DIPC > 500 

ESTEC 

Fluids expanding into vacuum can vaporise, condense and freeze. Also in fluid 

loops, phase change appears in microgravity conditions, and alters the flow 

characteristics (pressure losses, heat fluxes). The numerical analysis of 

such processes needs a proper validation, in order to increase the capability 

of analysis of such parameters as size of droplets produced by a passivation, 

etc. The objective of this activity is to prepare experimental databases by 

conducting tests with advanced measurement techniques, and to validate the 

industry codes and improve the numerical and physical models. Target fluids 

are liquids for vaporization/freezing studies, as well as gases for 

condensation aspects. The study will focus on two areas: sprays, and 

multiphase flow through pipes. Type of tender C(1) - activities in open 









C 02 

Q4 


Programme Ref.: TRP MPA-824 


DAC 200-500 



Page 131 


01.123.18 DEVELOPMENT OF A PROPELLANT FLOW CONTROL VALVE FOR 

1-20 N THRUSTERS 

Non-European (US) propellant Flow Control Valves (FCV) are generally used on 

European Reaction Control Thrusters (RCT) for spacecraft, mainly for reasons 

of cost and market acceptability. Export restrictions on US components for 

part of the potential spacecraft (and thruster) market severely affect the 

competitiveness of European thrusters and propulsion systems. The following 

tasks are foresen: 1. Market survey and analysis, and definition of 

requirement specification for a series redundant propellant FCV; 2. 

Establishment of basic design and Development and Test Plan; 3. Development 

and Design Verification testing of the FCV(s). 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/B43.MPC-858 


02.123.01 GRAPHITE NANO-FIBRE STORAGE 

NO 

ESTEC 

The aim of the activity is to investigate the underlying technology and 

develop a graphite nano fibre storage device which could outperform all 

present gaseous propellant (hydrogen) storage methods in terms of storage 

device mass efficiency and safety. There shall be a review and analysis of 

available information on nano fibre storage of gaseous hydrogen, and 

identification of open technology issues. Experimental investigation of open 

technological issues, and proof of concept demonstrations should be 

undertaken. 






C 02 

Q4 


Programme Ref.: TRP MPC-850 

Status: 

DAC 200-500 



Page 132 


02.123.02 AEROTHERMODYNAMICS OF AEROCPATURE AND HIGH SPEED EARTH 

ENTRY 

N12 

ESTEC 

Aerocapture and high speed entry are two essential components of future 

planetary missions, especially when sample return missions will be 

considered. The technologies have been developed for atmospheric entries from 

Earth orbit, but they require to be adapted to the new problems and processes 

occurring when super orbital velocities are encountered. In fact, when 

super-orbital entries or aerocapture manoeuvres are considered, new processes 

occur. In the plasma flowing around the spacecraft, ionisation and radiation 

become significant. The heat fluxes and pressures exerting on the vehicle 

increase dramatically. The thermal protection system design has to be 

changed, and ablative solutions are often needed, with consequences on the 

flow field (introduction of additional chemical species, vehicle shape change 

etc.). In addition, mass constraints lead to favouring passive capsules, thus 

avoiding the use of additional decelerators (e.g. parachutes). In this 

situation, the stability of the capsule in particular in transonic regime, 

must be guaranteed. The objective of the study is to establish the models 

for the assessment of the aerothermal and aerodynamic environment of superorbital 

entries, and to prepare the tools for the design of heat shields for 

aerocapture and high speed entry. The activity needs to include experiments, 

modelling and numerical analysis. The objective is to provide aero-chemical 

databases and validation data in a first step, validated models and analysis 

methods in a second. 






C 02 

Q3 



Status: 

DAC 200-500 



Page 133 


02.123.03 PLASMA RADIATION DATABASE 

N12 

ESTEC 

Radiative heat fluxes represent a significant contribution to wall heat flux 

and are not sufficiently precisely evaluated with tools and databases 

presently available in Europe. The prediction of plasma emission and 

absorption is important for Earth atmospheric entries at high velocities 

(typical of Sample Return missions), for high velocity entries into Mars and 

Venus atmospheres (typically above 9km/s) and for entries in atmospheres 

where dissociation produces strong radiators (e.g. Titan). Radiation plays 

also a major role in the thermal environment of solid rocket engines. A good 

knowledge of the radiative contribution to heat flux is already necessary in 

phase A and assessment studies, because of its large influence on the mass 

budget of the vehicle. ESA has initiated, under the Technology Research 

Programme (TRP) an initial development of a code and an experimental database 

for the determination of radiative heat flux: PARADE. This code is limited so 

far to some atoms, but should be extended to molecules and other species, and 

should be validated in order to become fully useful for the design of thermal 

protection systems. The objective of the study is to further develop and 

validate (by appropriate validation test when applicable) a code and to 

create an experimental database for thermal radiation of plasma (emission and 

absorption). Such a code should extend the present PARADE possibilities to 

include molecular species, and atomic species resulting from ablation of heat 

shields. 






C 02 

Q3 



Status: 

DAC 200-500 



Page 134 


02.123.05 ASSESSMENT OF ELECTRIC PROPULSION SYSTEMS FOR 

EXPLORATION MISSIONS : COMPARISON BETWEEN SOLAR 

ELECTRIC AND NUCLEAR ELECTRIC PROPULSION SYSTEMS 

N12 

ESTEC 

In order to accomplish missions requiring high delta-V such as travelling to 

other planets with or without humans, it is necessary to use propulsion 

systems capable to provide high specific impulses and sufficient thrust 

capability to bring the spacecraft to the target planet in a reasonable short 

time to avoid accumulating dangerous radiation dosage for the astronauts. 

Electric propulsion systems provide high specific impulses but the thrust 

level is very low. Only the availability of high power sources will allow 

electric propulsion engines to achieve high thrust levels. In this respect 

nuclear reactors such as the Russian TOPAZ have already been flown in space 

and the technology issues are reasonably understood. Nuclear reactors coupled 

with electric propulsion systems will allow systems capable to provide high 

specific impulses at reasonable high thrust. On the other hand the current 

solar generators used to feed electric propulsion systems are currently been 

used in commercial applications and the technology issues in LEO and GEO 

orbits are well understood. These commercial applications are a good base to 

develop higher power solar generators required to feed high thrust electric 

propulsion engines. A clear trade off between solar electric and nuclear 

electric systems for interplanetary applications with and without humans is 

needed to prepare the required roadmap of the propulsion technology for the 

AURORA exploration programme. This study should consider system and 

technology aspects of nuclear electric and solar electric systems and show 

their critical areas, the possible ways to solve them and to produce a clear 

trade-off capable of showing the advantages and drawbacks of both systems for 

interplanetary missions with and without humans. The final recommendations 

should be focused on creating a roadmap required for each technology in order 

to have these systems ready for the AURORA exploration programme. 






C 02 

Q4 




DAC 200-500 



Page 135 


02.123.06 ASSESSMENT OF CHEMICAL PROPULSION SYSTEMS FOR 

INTERPLANETARY MISSIONS 

N12 

ESTEC 

Interplanetary missions to solar system planets will require Delta-Vs of 

different magnitude, but usually rather high. Different propulsion systems 

may be used depending on several factors such as payload to mass fraction, 

mission time, etc. Chemical propulsion systems provide high thrust levels 

with relatively low specific impulse. In case of high delta-V missions, the 

use of chemical propulsion systems will impose long fly-bys in order to bring 

a specific payload mass to a target planet. When the delta-V is moderate the 

use of these systems bring benefits, which allow accomplishing the missions 

within a reasonable mission time. This study should consider system and 

technology aspects of possible new chemical propulsion systems for 

interplanetary missions with and without humans, identify critical areas and 

ways to improve the current chemical systems. The final recommendations 

should be focused on creating a roadmap required for each technology in order 

to have these systems ready for the AURORA exploration programme. 






C 02 

Q3 



Status: 

YAC 100-200 



Page 136 


02.223.01 ELECTRIC BIRD: SYSTEM AND MISSION IMPLICATIONS OF A 

FULL ELECTRIC PROPULSION SPACECRAFT 

The objective of the proposed study is to identify the critical issues and 

major impacts on the design of a spacecraft (size, mass, lay-out) and its 

space mission deriving by the replacement of conventional chemical propulsion 

thrusters or hybrid chemical/electric configurations with a full-electric 

propulsion spacecraft. The categories of missions to be investigated will be 

proposed by the Agency in the commercial and scientific areas. By taking into 

account status and projections for the next five/ten years also in the other 

major spacecraft technology areas, the study shall address in particular the 

following areas: * new design opportunities offered by a full EP system for 

the other major S/C subsystems (structural, thermal, power, telecommunication 

with ground); * overall spacecraft lay-out; * interfaces with the launcher 

(in "solo" and dual-passenger configuration); * mission scenario and 

operational strategies (including autonomy considerations); * ground segment: 

contacts during low-thrust transfer periods. Overall mission cost 

consideration shall also be included in the study. The output of the study 

will be used as a reference for the definition of technological activities to 

be initiated in the direction of new generations of full electric propulsion 

spacecraft. 

ESTEC 






C 02 

Q2 

Spec. Prov.: ALCATEL SPACE (F); ASTRIUM SAS (F) 

Programme Ref.: GS 01/N78; 02/N78 


DAC 200-500 



Page 137 


02.126.02 RENEWAL OF THE LARGE SPACE SIMULATOR PROGRAMMABLE 

LOGIC CONTROLLERS 

N5 

ESA’s Large Space Simulator was built in 1986 using the state of the art 

components at this time. For the process control, Programmable Logic 

Controllers (PLC), analogue sensors and hard-wired synoptic and control panel 

were used. Four independent PLC’s are used to control the following 

subsystems: *) Shroud Nitrogen Supply Equipment (SNSE); *) Sun Simulator 

(SUSI); *) Motion Simulator (MS); *) High Vacuum Pumping (HVP). Each PLC unit 

is a single point failure, which would result inevitably in a test abort. The 

refurbishment will cover the replacement of the sensors, the PLC’s proper, 

the man-machine interface and the related software. To avoid an unacceptable 

LSS down time period if the four subsystems were treated at the same time, it 

is proposed to phase the project. The refurbishment will be performed in four 

phases, one subsystem each year. The Shroud Nitrogen Supply Equipment shall 

be the first subsystem to be refurbished. 



TESTING SUPPORT DIV / TOS-MT 

Responsible: 


C 02 

Q3 



Status: 

02.126.04 CREATE DATA TRANSFER LINK BETWEEN ESTEC TEST CENTRE 

AND CUSTOMERS 

DIPC > 500 

N9 

ESTEC 

ESA test centre intends to establish a system enabling to transfer data 

(operational data and environmental test data from a specimen under test in 

the Large Space Simulator) in a highly cedured environment between the test 

centre and a remote location at the customer’s premises using public network 

(eg internet). 




Responsible: 


C 02 

Q3 



Status: 

NO 50-100 



Page 138 


02.126.06 ELECTROMAGNETIC COMPATIBILITY TEST FACILITY 

INSTALLATION 

N22 

The existing Electromagnetic Compatibility (EMC) chamber of the ESTEC test 

centre is too small to perform tests at system level especially in the range 

of Ariane 5 single passengers. The ESTEC Test Centre is the unique place in 

Europe, which is geared to verify very large spacecraft. To complete the 

range of its large test facilities, ESA decided to install a Large EMC 

chamber. A room perfectly suitable for the installation of a new large EMC 

chamber exists in a building recently constructed. This test facility will 

allow verifying spacecraft with optimum test facility performances and 

spacecraft configuration. 




Responsible: MR STAVRINIDIS 


C 02 

Q4 




02.226.01 RENEWAL OF THE MECHANICAL DATA HANDLING 

DIPC > 500 

N5 

ESTEC 

All the mechanical test facilities of ESA test Centre, i.e. electrodynamic 

shakers, Large European Acoustic Facility and the hydraulic shaker HYDRA, are 

using a common data acquisition system. This system provides to the 

engineering team the information required to perform safe test runs and to 

correlate properly the mathematical model after the test. The present data 

handling system was designed and developed internally in 1988. It is able to 

handle data from 252 accelerometers in parallel during vibration and acoustic 

tests. This procurement will cover the replacement of the hardware and the 

purchase of the software required by the data reduction. The new system will 

be able to handle 400 channels as a start but dispositions for growth to 1000 

channels will be required. 




Responsible: 


CR 02 

Q3 

Spec. Prov.: LMS B, DATAPHYSICS F, MTS F, M&P D, SPECTRAL 

DYNAMICS D 



YIPC > 500 



Page 139 


01.127.01 APPLICATION OF HIGHER ORDER DERIVATIVES METHODS TO 

STOCHASTIC STRUCTURAL ANALYSIS 

The proposed activities consist in performing a feasibility study by setting 

up a team of specialists in the respective stochastic structural analysis and 

Higher Order Derivatives disciplines, which will define a joint 

implementation of both methods and produce a demonstration prototype. The 

stages are: - definition of the requirements for the combined methods; - 

definition of the approach to combine both methods; - establishment of a 

demonstration prototype tool architecture; - set up of the demonstration 

prototype tool; - evaluation of the demonstration prototype; - conclusions 

and recommendations for future activities. Following successful completion of 

this feasibility study, further activities would be considered within TRP and 

GSTP programs for the detailed definition of the technology and it 

pre-industrial implementation as (in) engineering application(s). 



THERMAL CONTROL AND LIFE SUPPORT DIVISION / TOS-MC 

Responsible: MR KLEIN 


C 02 

Q4 




01.127.02 AIR BREATHING PROPULSION REVISITED 

DAC 50-100 

ESTEC 






C 02 

Q2 



Status: 

DIPC 200-500 



Page 140 


01.127.04 LARGE SCALE SPACE THERMAL ANALYSIS USING OPEN SOURCE 

SOFTWARE 

The objective of this study is to define and elaborate innovative ways of 

doing thermal analysis by making use of the open source software approach. 

Four aspects will be studied in close relation to each other: 1) 02.127.05 - 

Survey and assess the applicability of the OSS methodology and its components 

/ applications for the creation of a space thermal analysis environment; 2) 

Elaborate the possibilities to use high-performance Linux clusters and OSS 

for parallellisation of code to run large-scale thermal analyses; 3) 

02.127.02 - Study and refine the use of stochastic methods to run thermal 

analysis campaigns; 4) Study and refine the impact and potential benefits of 

using GRID computing for thermal analysis. Each of these aspects will be 

managed in a separate work package. 






C 02 

Q2 



Status: 

01.127.10 AIR BREATHING PROPULSION HEAT EXCHANGERS 

DIPC > 500 

ESTEC 

In advanced air-breathing propulsion systems for high performance launchers, 

air collection/air liquefaction cycles have been studied. In all of them, as 

the vehicle crosses the atmosphere, the air is cooled down to a liquid state 

and separated in gaseous nitrogen and liquid oxygen or directly used as 

oxidiser. A key component of these engines is the heat exchanger to extract 

the required power from the high-energy incoming air. This component, based 

mainly on the conventional shell-and-tube configuration, is very heavy and 

cumbersome and typically represents the larger fraction of the total weight 

of the engine. The objective of this activity is to study the use of an 

advanced configuration (for instance compact fin-plate, printed circuit heat 

exchanger) for a heat exchanger for air breathing application and to build a 

demonstrator for testing. Output of the activity will be the design, 

manufacturing and preliminary testing of a breadboard heat exchanger. The 

activity is divided in the following tasks: Investigation on advanced heat 

exchanger concepts; Design of a demonstrator; Manufacturing of the 

demonstrator. 






C 02 

Q2 

Spec. Prov.: B+E 

Programme Ref.: GSTP-3 G00/C52.MCT-988 

Status: 

DAC 200-500 



Page 141 


01.127.13 THERMAL CONCEPT DESIGN TOOL 

A thermal-concept tool is in development, which will provide a first version 

of this much-needed capability. The need for such tool has been highlighted 

by industry for the last couple of years during the yearly Thermal and 

Environmental Control & Life Support (ECLS) Software Workshops. The objective 

of this activity is to provide a rapid and quick design tool to support 

conceptual thermal design studies. The activity will be based upon results of 

a current TRP activity, and inputs from industrial users after use. Type of 









C 02 

Q2 


Programme Ref.: TRP MCV-882 


01.127.15 INSULATION FOR HOT STRUCTURES 

NO 100-200 

ESTEC 

The use of hot structure with materials able to withstand high surface heat 

fluxes requires the availability of lightweight, high temperature insulation 

to be put between the hot structure and the inside of the vehicle. Therefore, 

this activity aims at developing an advanced high temperature insulation 

system for hot structures. The insulation will be used in applications 

involving atmospheric pressure. The system should be multi-component, 

including different kinds of ceramic fibres or foams and based on a gradient 

approach in which different layers are used according to their temperature 

resistance and density for optimisation purpose. The output of the activity 

will be the design, manufacturing and high temperature testing at sample 

level of the new insulation. Type of tender C(4) - activities subject to SME 

subcontracting clause. For additional information please go to EMITS news 


programmes". 






C 02 

Q4 


Programme Ref.: TRP MCT-688 


DAC 200-500 



Page 142 


01.127.16 MINI AND MICRO HEAT PIPES 

For terrestrial applications the use of mini and micro heat pipes has shown 

to improve the thermal design of electronic components. Such heat pipes could 

also be beneficial for the thermal design of spacecraft components. The 

objective of this activity is to develop and fully performance test, mini & 

micro heat pipes for future use on spacecraft. Type of tender C(2) - 




programmes". 






C 02 

Q2 



Status: 

01.127.20 ESA DESIGN RESOURCE CENTRE 

DAC 200-500 

ESTEC 

The objective of this activity is to first identify relevant existing 

resources and databases within ESA and then provide this information on a 

single web-site. It shall also include the definition of a system parameter 

data model in ISO Express format and the provision of data in that format. 

This will allow direct access to the design data independent of the tools 

being used for the various disciplines involved in the mission and spacecraft 

design process. The single platform will allow suppliers to provide equipment 

and component data to any user. 






C 02 

Q4 


Programme Ref.: TRP MMS-733 

Status: EX ITEM 00.129.10 ISSUED 1-4254 

DAC 200-500 



Page 143 


01.127.26 NON-LINEAR DYNAMIC EFFECTS AND THEIR CONSEQUENCES ON 

SPACECRAFT VIBRATION QUALIFICATION 

Prestressed assemblies are usually the rule for spacecrafts equipment and 

structures not only to meet stability requirements but also because such 

assemblies behave in a predictable manner during high level since vibration 

runs. Such design rules ensure generally that linear behaviour will be found 

during vibration tests. However because of insufficient preload or poor 

construction non linear behaviour is sometimes encountered. The design and 

test of a truss with weak presstress and even controlled gaps is therefore 

proposed in order to investigate the testing problems which are bound to 

arise and the shock levels induced by the loose connections. The objective is 

a reduced requirements on tolerances/preload for S/C structures and to 

improve handling of vibration test anomalies. 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/H69.MM-I-146 


01.127.28 SHOCK ENERGY CHARACTERISATION 

DIPC > 500 

ESTEC 

Ariane 5 high shock requirements are today a big concern for spacecraft 

developpers. Although the high frequency content is reasonably well known, 

the low frequency one - 0 to 200 Hz - has not yet been precisely 

characterised. This lower part of the spectrum is quite important for 

structures, especially sensitive equipments such as telescopes. Dedicated 

tests and analyses must then be performed in order to gain better insight 

into this problem. Use of accelerometers mounted on mechanical filters could 

provide unambiguous determination of the SRS at low frequency. The objective 

is to improve requirements w.r.t shock levels. 






C 02 

Q2 

Spec. Prov.: F 

Programme Ref.: GSTP-3 G00/C55.MM-I-141 


DIPC > 500 



Page 144 


01.127.35 HIGH PRECISION FINITE ELEMENTS 

The Finite Elements Method (FEM) has become a synonym for Structural Analysis 

over the years. Nevertheless, the accuracy of FEM-results continues to be 

unsatisfactory in many cases, such as in the medium and high frequency range. 

The error is related to the fact that finite elements only approximate the 

partial differential equations (PDEs) describing the structure, where the 

quality of the approximation depends on the discretisation. A traditional 

finite element is given in the form Z = K - w2M, where K and M are (constant) 

stiffness and mass-matrices. A high precision finite element (HPFE), in 

contrast, is given in the form Z = Z(w2), where the elements of Z are 

transcendental functions (typically cyclic and hyperbolic sines and cosines) 

of the frequency w and/or other system parameters. The HPFEM could open 

interesting new avenues in application to spacecraft design and verification, 

and therefore the investigation of its capabilities is deemed fully relevant. 






C 02 

Q2 



Status: 

02.127.01 SMART THERMAL PROTECTION SYSTEM (TPS) 

NO < 50 

N13 

ESTEC 

Smart materials are an increasingly wide field of research. Ideally they are 

materials able to "feel" a certain thermo-mechanical environment and to 

change their basic properties to "react" or adapt to the environment. The aim 

of this activity is to study the applicability of the smart material 

principle to TPSs, investigating the modifications required for existing 

concepts and proposing new classes of materials. It should assess and 

quantify any advantages smart materials offer. Tasks include an investigation 

of suitable materials, sample preparation/procurement and basic testing of 

the smart properties. Parallel contracts may be placed. 






C 02 

Q4 

Spec. Prov.: 


Status: 

DAC 200-500 



Page 145 


02.127.04 CRYOGENIC TANK INSULATION 

Reusable launchers will rely on high performance liquid hydrogen/liquid 

oxygen engines. This implies the need of large tanks, especially for LH2, and 

of lightweight, efficient, reusable insulation systems. The foam materials 

used as insulation in the expendable launchers are not reusable and generally 

are not able to withstand an atmospheric re-entry. For this reason, during 

the ESA FESTIP programme, commercially available advanced foam materials were 

preliminary investigated. However, only a limited set of materials was 

investigated and the activity was limited to basic characterisation only. The 

objective of this study is to characterise a set of insulation materials in 

liquid hydrogen conditions. This includes a test campaign with thermal, 

mechanical and chemical and functional property characterisation and test of 

samples of the material in bonded condition. The output of the activity is 

the availability of a fully characterised cryogenic insulation for propellant 

tank application. The availability of the insulation material is crucial to 

the development of a critical component for a reusable launcher. 






C 02 

Q3 




02.127.05 APPLICABILITY OF THE OSS METHODOLOGY FOR SPACE THERMAL 

ENGINEERING 

DIPC > 500 

N11 

ESTEC 

Traditionally, software tools have been developed using a closed-source 

model. In this development model, the software developer produces a piece of 

software which is aimed to solve a number of problems in a certain domain. In 

contrast, Open Source Software (OSS) uses another development model. In this 

model, the software source is disclosed to all and is made available to the 

user community. Users can modify the software to suit its own needs and can 

make contributions to the software for use by others. The current activity 

aims to test the applicability of the OSS development model on real software, 

in the thermal engineering domain, and to verify under what conditions the 

OSS model will be useful for the complete software cycle, from design and 

development to the support and maintenance. To this purpose, a small but 

useful thermal analysis tool will be developed, based on available Open 

Source software, and made available to the user community as OSS. 

Furthermore, after release and during a limited period, the product will be 

supported under this contract. 






C 02 

Q3 



Status: EX ITEM 01.127.04 ISSUED 1-4217 

DIPC 100-200 



Page 146 


02.127.06 PHASES MANAGEMENT FOR ADVANCED LIFE SUPPORT PROCESSES 

N12 

ESTEC 

ESA has initiated in the last 15 years several activities in Advanced Life 

Support. These activities have been mainly focus on the ground demonstration 

of the concerned processes. Although the processes will have to be optimised, 

they are now rather well characterised and the next step to be investigated 

is the management of the inputs/outputs phases (liquid, solid, gas) to/from 

the processes. To foresee the closure of a life support loop the involvement 

of several interconnected processes (biological and physical-chemical) is 

unavoidable. Generally, liquid, solid and gas flows are the interfaces 

between these processes. The management of these flows induce generic 

problems (separation, extraction, transfer, mixing, adjunction, 

quantification, equilibrium control,etc), which will have to be handled. Due 

to the well known space constraints (e.g. reduced gravity, energy 

limitation), terrestrial technologies cannot be easily used and new concepts 

will have to be studied and developed. The objective of the proposed activity 

is the development and demonstration of the liquid, solid, gas management 

technology needed to establish, maintain and control, processes of Advanced 

Life Support with absolute minimum need for crew time. The work is focused on 

the ground feasibility demonstration of key technologies for phases 

management. Within this first phase it is proposed, to limit the 

investigations to the gas separation issues (N2, CO2, O2, H2, etc.). The 

technologies which allows to separate gases will be reviewed and trade-off. A 

concept will be selected and a demonstration breadboard will be developed for 

evaluation. 






C 02 

Q4 




DAC 200-500 



Page 147 


02.127.07 ULTRA-LIGHT STRUCTURES 

N21 

ESTEC 

The space community has clearly expressed an interest in lightweight 

inflatable structures, as a very feasible candidate for deployment and 

structural support of large appendages such as solar arrays, sun-shields and 

reflectors, needed for the next generation scientific and commercial 

spacecraft. Previous inflatable structures technology programmes of the 

European Space Agency have demonstrated the potential of complex inflatable 

structures (such as antennas and sunshields), and this combined with the 

above defined need, justifies actions foreseen to be taken in this area. The 

new interest for inflatable structures is fully explained by the perspectives 

they offer: with a lower mass and stowed volume, they may prevent the use of 

larger expensive launchers. Furthermore, they may offer new capabilities 

(large reflectors, large solar arrays, solar sails), which will open a new 

era in the space exploration. One can indeed imagine small satellites with 

large communication antennas, and increased on-board power due to large solar 

arrays made possible by inflatable structures. In order to further mature the 

inflatable structures towards a spacecraft application, a number of 

significant technological problems need to be solved. The final demonstration 

that such technologies are mastered and ready for a flight programme 

implementation is especially difficult. Indeed, for most of them, a 

validation on ground is not sufficient, or simply impossible. Therefore, 

steps to demonstrate feasibility of concept have to follow the logical 

approach of analysis, ground testing and finally a flight test demonstrator. 

It is the intention that this activity to: *) proof maturity of the relevant 

technology developments; *) select a flight demonstrator concept, considering 

not only technical requirements but also launch constraints; *) complete the 

detailed design of the flight demonstrator; *) manufacture and ground test 

qualify the flight demonstrator (combined analysis and testing). A successful 

completion of this program will thus pave the way for a future European 

inflatable structure flight demonstration mission. Flight test would be 

proposed as part of the GSTP. Type of tender C(2) - activities in open 









C 02 

Q4 


Programme Ref.: TRP MCS-001 

Status: 

DIPC > 500 



Page 148 


03.127.01 ELECTRO ACTIVE POLYMER ACTUATORS 

N21 

ESTEC 

The objectives of the proposed Innovative TRP study is to demonstrate the 

feasibility of radically new sensors and actuators embedded into lightweight 

structures for vibration control. Candidate materials such as fibre 

composites, fibre optics, piezoelectric materials, memory alloys, electro / 

magnetorheological fluids, thermocouples, strain gauges, biomimetic 

materials, Carbon nanotubes and electroactive polymer materials, are 

available or under development, but aspects related to space structure 

applications need to be developed further. The most promising candidates are 

electroactive polymer materials (Electroactivated Polymer Actuators), and 

emphasises shall be placed on possible application of such materials. The 

foreseen study should be divided into three parts. A first part of the study 

shall perform a trade-off for potential active/intelligent materials, with 

priority towards (however not limited to) potential use of EAP in space 

applications. Based on this, there shall be a definition and selection of: - 

a large scale application example (eg large inflatable or deployable 

structure, possible examples may be provided by the agency as a result of 

previous activities); - a number of candidate materials that will be further 

investigated toward the selected application; - a scaled laboratory 

demonstration of the selected concept. The second part of the study shall 

address investigations specific for the selected material(s) as well as 

manufacturing and construction of the demonstrator(s). Combined sensor and 

actuator technologies, to be integrated into the envisaged structural 

concept, shall be investigated in terms of environment, stroke, power and 

size. The aimed activity shall not only extensively address the material 

possibilities from a functional characterisation point of view, but shall 

also consider the actual structural implementation constraints, and sensing, 

dynamics, control, performances etc. Challenges posed by the use of EAP 

materials shall be addressed. A detailed characterisation and experimentation 

of selected EAP and other materials, shall be performed, and the material 

characteristics shall be evaluated in the light of structural implementation 

requirements (size, durability, power etc). Effort shall be devoted toward 

establishing methods for predicting the performances of EAPs, adequately 

addressing the multi disciplinary interaction of their chemistry - physical 

and mechanical nature. Recommendation toward improvements of EAP materials 

and design methodologies shall be made. The third and final part of the study 

shall consist of a detailed test evaluation of the demonstrator manufactured, 

followed by an evaluation/ analysis of the corresponding accuracy achievable 

in flight for the selected large scale application example. Type of tender 




programmes". 






C 03 

Q1 


Programme Ref.: TRP MCS-002 

Status: 

DIPC > 500 



Page 149 


00.129.02 IRSI INTEGRATED OPTICS 

The IRSI detector spacecraft has a large optical bench, which could be 

reduced in size and mass and its reliability improved by deployment of 

integrated optics. Integrated optics has a wide application area, in that it 

allows high speed optical processing on monolithic devices. Examples of 

applications area would be telecommunications and high speed computing. Some 

research work has been performed in the area but only few commercial 

applications have as yet used integrated optics. The following optical 

functions are candidates for the integrated optics module: beam-splitters, 

wave-front filters, amplitude matching units and beam combiners. Sub 

activities envisaged include: Review current state-of-the-art; Selection of 

technology for the IRSI integrated optics module; design, including selection 

of optical functions, of the integrated optics module; Performance test and 

evaluation. 






C 02 

Q2 


Programme Ref.: TRP SCI-12 

Status: 

00.129.05 JOURNAL BEARINGS FOR TURBOPUMPS 

DIPC > 500 

ESTEC 

The objective here is to investigate the suitability of promising materials, 

e.g. Ceramic Matrix Composites (CMC’s), and configurations for hydrostatic or 

hydrodynamic journal bearings in a reference application, i.e. for a 

turbopump in a cryogenic main propulsion system. Tasks include material 

investigation, design and manufacturing of radial/axial test bearings and 

bearings tests in liquid oxygen or hydrogen at available facilities. 






C 02 

Q2 


Programme Ref.: TRP MMM-956 

Status: 

DAC 200-500 



Page 150 


00.129.10 ESA DESIGN RESOURCE CENTRE 

The objective of this activity is to first identify relevant existing 

resources and databases within ESA and then provide this information on a 

single web-site. It shall also include the definition of a system parameter 

data model in ISO Express format and the provision of data in that format. 

This will allow direct access to the design data independent of the tools 

being used for the various disciplines involved in the mission and spacecraft 

design process. The single platform will allow suppliers to provide equipment 

and component data to any user. 






C 02 

Q2 


Programme Ref.: TRP MMS-733 

Status: 

00.129.15 PIEZO VALVES: ELECTRO-FLUIDIC DEVICES BASED ON PIEZO 

ACTUATORS 

DAC 200-500 

ESTEC 

The objective of this activity is to develop electro-valves based on existing 

amplified piezo actuators or linear piezo motors (or possibly on rotating 

piezo motors). Works will involve mechanics, but also driving electronics and 

control. A new validated concept of electrovalve that can be adapted to 

various applications is expected. A prototype valve and electronics will be 

manufactured and tested. 

****************************************************************** 

****************************************************************** 


















C 02 

Q2 



Status: 

DAC 200-500 



Page 151 


00.129.24 IN-ORBIT FORCE AND ACCELERATION MEASUREMENT 

In-Orbit measurement of accelerations and forces during launch by JPL 

identified that flight loads on instruments are often less (about 20% to 50%) 

than predicted, and that ground tests very often imply much higher forces on 

instruments than the actual spacecraft launch. The objective is to prepare a 

standard equipment for the measurement of instrument interface accelerations 

and forces during launch and spacecraft commissioning. The following tasks 

have been identified: -1) Development of sensor packages with wireless links 

to a data terminal on the spacecraft; Develop sensors or an interface to 

sensors, which provide a wireless link to a data-handling unit. This 

interface could be an electronic box, which is directly linked, by wires, to 

force transducers below an adjacent box. Main tasks are: review of 

requirements; design and manufacturing of wireless on board data transmission 

system; manufacturing and verification (as far stand alone possible) of this 

device. -2 Development of data handling for data transmission during launch; 

Develop a data-handling unit, which can be easily integrated on a spacecraft, 

with only minimum impact on the spacecraft, and which can receive 

acceleration of force measurement data from sensors on the s/c via wireless 

link; and which can transmit these data to ground. Main tasks are: review of 

requirements; design and manufacturing of the on-board data-handling device; 

manufacturing and verification (as far stand alone possible) of this device. 

-3) In-orbit experiment preparation, on-ground verification of the set-up to 

achieve flight readiness; Prepare a experiment set-up for the measurement of 

instrument interface accelerations and forces during launch and spacecraft 

commissioning by using the devices which have been developed within this 

mini-project. Verify the set up to degree that it would be ready for 

spacecraft integration. Main Tasks are: definition of requirement; definition 

of test set-up; simulation of in orbit data acquisition and transmission. 

ESTEC 






C 02 

Q2 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/H70.MMS-706 

Status: 

DIPC > 500 



Page 152 


00.129.25 ACTUATOR FOR SPACE APPLICATIONS 

Design, development and laboratory tests of the engineering model (EM) of an 

innovative actuator concept, referred to as "harmonic actuator", 

preliminarily implenented at prototype level in the framework of a 

feasibility study supported by ASI technology development program. The 

harmonic actuator features improved performances in comparision with the 

traditional motor and reduction gear assembly. Its key property is its high 

mechanical cut-off frequency in motion transmission, such that it well 

approximates the dynamic behaviours of a direct drive with better efficientcy 

in terms of torque-to-dissipated power ratio. Following the theorotical and 

experimental investigations carried out in the course of the feasibilty 

study, the present activity shall include: Identification of the optimum 

electromechanical and driver controller configuration, with implementation of 

breadboards of the most promising actuator configurations and manufacturing 

and test of the EM. The harmonic actuator can find application in several 

demanding applications in space, including for instance: High accuracy 

pointing systems of antennas, Implementation of high accuracy, lightweight 

joints of robotic arms. The properties of the harmonic actuator make it 

applicable to high-performance sevosystems for terrestrial use. 

ESTEC 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/B34.MM-I-269 


DIPC > 500 



Page 153 


01.129.03 DEXTROUS ROBOT SYSTEM 

This activity shall develop a scalable medium-size lightweight dextrous robot 

arm for external space manipulation applications to the level of a 

demonstrator with completely flight qualifiable design. This shall be 

suitable for being complemented with more dedicated sub-system developments 

under GSTP or a similar programme, and for customisation and full 

qualification testing by user programmes. Innovative approaches and 

technologies shall be exploited to drastically minimise mass and power 

consumption while providing adequate force capability and repeatability. A 

target is to achieve a flight model design of an arm with full joints 

instrumentation and harness, with a 1 g payload capacity of 10 kg, within a 

total mass of 20 kg. Interface compatibility with existing other building 

blocks of space robot arm systems (e.g. on-board controller and avionics) 

shall be observed. The activity shall include the following phases: Phase 1 

(200 kEuros): System-level requirements analysis and definition, kinematic / 

structural / thermal / dynamic / control analyses, system architectural 

design and specification of requirements for sub-systems (joints, limbs 

structure, end effector, latching, ground support equipment).Phase 2 (500 

kEuros): Evaluation and tradeoff of radically different design concepts for 

low-power compact space robot joints according to the requirements 

established before. Detailed design, development, manufacturing and test of 

one joint prototype. Phase 3 (1300 kEuros): Upon possible design iterations 

based on the unit test results from Phase 2, development and manufacturing of 

a total of 7 similar joints. Integration in a dextrous robot arm system 

testbed, validation by system-level testing and demonstration. Type of tender 




programmes". 

ESTEC 






C 02 

Q2 


Programme Ref.: TRP MMA-622 

Status: 

DIPC > 500 



Page 154 


01.129.20 ADVANCED LIDAR CONCEPTS 

This study activity will review advanced Light Detection & Range Finding 

(LIDAR) concepts like synthetic aperture LIDAR’s, Differential Absorption 

LIDAR (DIAL), distributed transmitter/receiver flight formations, and 

telescope array LIDAR’s, etc. It will also assess the performance advantage 

over conventional concepts, review the current technology status and identify 

possible technology solutions needed in order to take advantage of the new 

LIDAR concepts. 






C 02 

Q2 


Programme Ref.: TRP MMO-624 

Status: 

01.129.27 MULTIFUNCTIONAL MICRO/NANO SYSTEM 

NO 100-200 

ESTEC 

The objective of this activity is to investigate the feasibility of a 

multifunctional microsystem configuration composed of structural elements, 

thermal control elements through forced cooling system, power/harness 

elements including electric power regeneration from heat sources rather than 

radiators for cooling, and data/communications functions combined in a single 

component. Activities proposed include the establishment of performance 

requirements and design constraints, identification of concepts for 

multifunctional micro-systems, detailed design of micro-system and 

manufacture of critical components using micro/nano technology approaches, 

hardware tests and performance evaluation. Type of tender C(1) - activities 









C 02 

Q4 




DAC 200-500 



Page 155 


01.129.31 TMA TELESCOPE WITH LARGE FIELD OF VIEW 

Within a study of Earth Watch superspectral missions, the need for wide field 

of view (larger than +/-12.5 degree) Three-Mirror-Anastigmatic telescope 

(TMA) was identified as key requirement for superspectral imager with a large 

swath. Up to now only TMA’s with smaller field of view have been 

manufactured. The proposed activity shows a significant potential for Earth 

Watch superspectral missions, but in addition will find applications in many 

other missions/ programmes requiring telescopes with a large field of view. A 

breadboard of a (TMA) shall be designed, manufactured and tested. The 

challenge will be the extreme wide field of view at an aperture of about 

200mm, the balancing of the asphericities of the three mirrors and the 

internal baffling. The mass of the telescope shall be minimized. 






C 02 

Q3 

Spec. Prov.: B+F 

Programme Ref.: GSTP-3 G00/A03.MMO-010 


01.129.32 TETHER SYSTEM EXPERIMENT DEMONSTRATION MISSION 

DIPC > 500 

ESTEC 

In this project a fast and low cost demonstration mission for a tethered 

re-entry on Foton-M will be designed, manufactured, integrated and tested. 

This mission is step 1 towards the implementation of a European 

tether-assisted sample-return service on the International Space Station and 

will focus on the insertion of a small sub-satellite in a re-entry trajectory 

with the aid of a tether. Baseline will be the concept developed in phase A/B 

of this project, which will be adapted for the ESA’s Foton-M flight 

opportunity to use 40 kg of spare payload mass. The main activities in this 

project are the development of a flight model of the Tether Deployer System 

and the Sub-satellite. Also part of the activity is the system integration 

and testing. In the next step the operation of the complete system under the 

constraints of an ISS sample-return application will be tested, including a 

re-entry and recovery of a full-scale sample return capsule. The activity is 

built around the following parts: 1) tether deployer system; 2) 

sub-satellite; 3) system integration and testing and 4) post flight analysis. 






C 02 

Q3 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/I71.MMM-964 

Status: 

DIPC > 500 



Page 156 


01.129.34 INTELLIGENT CAMERA FOR MICROGRAVITY DIAGNOSTICS: 

SCIENTIFIC REQUIREMENTS AND CAMERA SYSTEM CONCEPT 

N10 

ESTEC 

C-MOS/SMART Cameras have the potential to improve significantly the 

performance of optical diagnostic tools. They allow for random access to the 

sensor elements of the array, which leads to functions like choice of the 

field of view already on the camera chip, adaptable spatial resolution and 

adaptable time resolution. The last will lead to longer recording times for 

high speed imaging. As this camera type can be used for all diagnostics, the 

above mentioned functions are not limited to visual observation only. The 

minproject consists of the definition of requirements, market analysis, 

camera selection/ modification/ development, application and performance 

verification of performance via breadboarding and connection to existing 

optical demonstrators. Scientific requirements and camera system concept - 

This activity will identify scientific requirements, produce specification 

and design concept for the camera. Type of tender C(1) - activities in open 

competition limited to non-primes. Type of tender C(4) - activities subject 

to SME subcontracting clause. For additional information please go to EMITS 

news "Industrial Policy measures for non-primes, SMEs and R&D entities in ESA 

programmes". 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/A07.MMG-891A 

Status: INTENDED 

DIPC < 50 



Page 157 



APPLICATION AND VERIFICATION CONCERNING PHOTOGRAMMETRY 

N10 

ESTEC 











optical demonstrators. Application and verification concerning photogrammetry 

- The objective is the quantitative comparison of the performances of the 

photogrammetric diagnostic tool equipped with a CCD against the SMART camera. 

Type of tender C(1) - activities in open competition limited to non-primes. 

Type of tender C(4) - activities subject to SME subcontracting clause. For 








C 02 

Q2 


Programme Ref.: GSTP-3 G00/A07.MMG-891B 

Status: 

DIPC 100-200 



Page 158 



APPLICATION AND VERIFICATION CONCERNING HIGH-SPEED 

IMAGING 

N10 











optical demonstrators. Application and verification concerning high-speed 

imaging - The objective is the quantitative assessment of the high-speed 

measurement performance of an intelligent camera. This technique will make 

high-speed-imaging available to all diagnostics; this technique is 

significantly cheaper than dedicated high-speed-cameras. Type of tender C(1) 

- activities in open competition limited to non-primes. Type of tender C(4) - 

activities subject to SME subcontracting clause. For additional information 

please go to EMITS news "Industrial Policy measures for non-primes, SMEs and 

R&D entities in ESA programmes". 






C 02 

Q2 


Programme Ref.: GSTP-3 G00/A07.MMG-891D 

Status: 

02.129.01 REQUIREMENTS ON DETECTION DEVICES FOR SATELLITE PCS 

DIPC < 50 

ESTEC 

A patent was filed in begin of 1999 by the Agency, specifying specific 

embodiments for remote sensing instruments. PCS has never been applied to 

atmospheric measurements to detect particle sizes and directed air currents. 

Therefore, the aim of the proposed activity is to perform a feasibility study 

of the performance capability of PCS for atmospheric measurements. 






C 02 

Q2 


Programme Ref.: TRP MMG-907 

Status: 

NO 100-200 



Page 159 


02.129.02 HYBRID MECHANICAL-ELECTRONIC POINTING SYSTEM 

The objective is to demonstrate a hybrid pointing system for accurate 

pointing of large antennas with limited scanning capabilities over large 

angular areas. This activity will focus on the definition, design and 

breadboarding of a pointing system (mechanics, electronics and antenna 

emulator) using a combination of low-speed mechanical pointing and 

small-range electronic beam pointing to achieve high accuracy (


Page 160 


02.129.04 DYNAMIC SEALS FOR TURBOPUMPS 

The objective of this activity is to study and test innovative materials and 

designs for turbopump dynamic seals compatible with the requirements of 

future launchers. Specific attention shall be given to low consumption of 

helium typically used as buffer gas, and to an enhanced seal robustness and 

lifetime for reusable systems. Tasks include seal material investigation, 

design and manufacturing of prototype seals and seal tests in liquid oxygen 

or hydrogen at available facilities. Type of tender C(1) - activities in open 









C 02 

Q4 



Status: 

02.129.05 REGIONAL MARS ROVER FOR SCOUTING AND SAMPLE 

COLLECTION, PART 1 - MARS ROVER CHASSIS 

DAC 200-500 

N12 

ESTEC 

The rovers envisaged here are so-called mini-rovers, with a system mass in 

the order of 100 kg, a roving range in the order of tens of km and a 

relatively high degree of autonomy. This is the type of rover needed e.g. for 

deploying a multi-user exobiology payload package with a mass of tens of kg. 

The Russian Marsokhods have been optimised for operating on a particular type 

of terrain, but have limitations in terms of payload capability. For other 

types of landing site other approaches may be more appropriate. The activity 

shall include the selection, analysis, breadboarding and comparative testing 

of a number of designs for the locomotion subsystems (i.e. rover chassis) for 

an unmanned medium-sized Mars rover. This concerns mobility for deploying 

instruments and collecting samples (possibly with drilling/ coring) in a 

local or regional vicinity of a landing site (or base) as well as robotic 

scouting and exploration at larger ranges. The designs shall include wheeled 

as well as tracked options and shall identify the most appropriate type of 

chassis for a few different types of potential landing sites (e.g. hilly 

terrain with soft soil, flat terrain with small rocks, rough terrain), taking 

into account representative payload capabilities and total travel distances. 

The establishment of a development plan for further work is part of the 

activity. This activity is the generic (mission-independent) part of the 

activity "Regional Mars Rover for Scouting and Sample Collection" identified 

in the "Regional Mars Mini Rover" roadmap presented during the 2001 Robotics 

Harmonization Exercise. 






C 02 

Q3 



Status: 

DAC 200-500 



Page 161 


02.129.06 SMART PANORAMIC OPTICAL SENSOR HEAD 

N18 

By designing a sensor head with a "smart retina", it is possible to employ a 

simpler, lightweight panoramic lens, and then to correct the inevitable 

distortions and image degradations by means of processing the detector 

array’s image data. The aims are to design, build a breadboard demonstration 

smart panoramic optical head and to validate the principle for a range of 

sensor applications. Type of tender C(2) - activities in open competition, 









C 02 

Q4 




02.129.09 ULTRA LIGHTWEIGHT TELESCOPES 

DIPC 200-500 

N18 

ESTEC 

Future low-cost missions will benefit from mass savings and procurement cost 

savings achievable by ultra lightweight optical telescopes manufactured by 

advanced technologies.For RF antennas, technologies to produce very 

lightweight large antenna structures exist, such as CFRP and electroforming. 

In the optical spectral regime, however, - due to the much shorter wavelength 

- the requirements on shape and surface accuracy of the reflectors to achieve 

diffraction-limited performance are much more stringent.The objective of this 

activity is to develop a cost-effective process, which allows producing ultra 

lightweight telescopes of diffraction-limited performance in a wide 

field-of-view for the visible and near-infrared spectral range. Such 

telescopes will find applications in Earth observation missions (photometric, 

LIDAR, e.g. WALES), planetary missions, and laser communication. The activity 

will comprise the design, manufacturing and testing of such a telescope. 






C 02 

Q4 



Status: 

DIPC > 500 



Page 162 


02.129.10 LASER COOLED ATOM SENSOR FOR ULTRA-HIGH-ACCURACY 

GRAVITATIONAL ACCELERATION AND ROTATION MEASUREMENTS 

N24 

ESTEC 

Laser-cooling of atoms and atom-trapping is leading the way to new 

applications in Science. Very recently this concept has been 

proposed/investigated for the development of ultra-high accuracy 

gravitational acceleration and rotation sensor. This concept relies on 

coherent light pulses to stimulate transitions between (two) different states 

of atoms being laser-cooled and trapped in an optical cavity. It can be shown 

that due to quantum mechanical effects, the superposition of two or more 

spatially separated atomic states can lead to the measurement of 

gravitational accelerations or rotation of the reference frame with the 

utmost accuracy. This study will assess this emerging concept for the 

development of Gravitational Acceleration or Rotation Sensors for Space and 

Planetary (Earth) Science. The output of this study will be the definition of 

a technology roadmap, supported by key experimental verification and 

breadboarding. 






C 02 

Q4 


Programme Ref.: TRP MME-003 

Status: 

NO 100-200 



Page 163 


03.129.01 ROBOTIC ASSISTANCE TO HUMAN OPERATIONS 

N21 

ESTEC 

Human exploration scenarios have been studied extensively during the past 

several years. Autonomous monitoring and control and robotic systems can be 

applied to any exploration phase and to major systems such as transportation, 

habitation, or planetary surface systems. Round-trip communications lags can 

be as long as 40 minutes for Mars exploration missions. Mission simulations 

and analyses have shown that the only feasible missions for small crew sizes 

include adjustable autonomous monitoring and control, and adjustable 

autonomous robotic systems. Otherwise, crew time demands for operations and 

maintenance overwhelm the available crew time and mission risk, leaving the 

mission infeasible. The objective is to develop novel automation and robotics 

technologies with appropriate levels of autonomy and interaction 

("interactive autonomy") to increase the efficiency of human operations, yet 

with a maintained crew health and performance. Intelligent tools and robotic 

devices (robotic assistants) shall prepare, enable, support, amplify, and 

protect the human functions of perception, cognition, planning, locomotion, 

and actuation. Within the framework of this activity an actual case shall be 

demonstrated. The case shall be selected in order to achieve a measurable and 

sensible decrease of crew time (e.g. 30%) when robotic assistance is used. 

Type of tender C(2) - activities in open competition, where a significant 









C 03 

Q1 



Status: 

DIPC > 500 



Page 164 


03.129.02 SATELLITE SERVICING BUILDING BLOCKS 

N21 

ESTEC 

Proposals to construct satellites that could be re-fuelled or re-furbished in 

space have been put forward by several space actors in the past. However 

these proposals were quickly dismissed on the fear that the provisions needed 

on a serviceable satellite made it more complex, heavier and expensive, than 

a disposable one. Besides, in the past, servicing could not bring sensible 

advantages as life of satellites was mainly limited by the lifetime of 

components (eg gyros, high-power electronics) than by consumables (fuel). 

Advances in technology, trends in size and weight of commercial satellites as 

well as the increased bus standardisation (due to the reduction of satellite 

manufacturers) have changed past considerations. A satellite-servicing 

infrastructure together with its satellite engineering standards, and the 

increased flexibility of satellites built accordingly, would improve the 

competitiveness of European industry. For example satellites built for 

refueling could be made sensibly lighter thus decreasing launch costs. 

Furthermore lighter satellites would allow higher utilisation of launchers 

increasing the number of payloads per launch. To be noted: the DARPA is 

currently investigating a satellite refuelling system (Orbital Express/ASTRO) 

for which it has already awarded study contracts for $6M. The goal of this 

activity is to produce technology to support co-operative servicing of 

satellites in GEO. The Agency has already investigated the needed 

technologies of Rendez-vous, docking and berthing through previous TRP/GSTP 

activities, this activity shall therefore focus only on the robotics aspects. 

Within this frame, objectives of this study will be first to analyse the 

objectives/tasks for servicing (re-fuelling, re-furbishing), then to produce 

architecture and identify interfaces, and finally to design, prototype and 

test servicing hardware. Type of tender C(2) - activities in open 









C 03 

Q1 



Status: 

DIPC > 500 



Page 165 


02.136.01 IMPLEMENTATION OF TECHNOLOGY TRANSFER PROGRAMME 

N10 

ESTEC 

The ESA Technology Transfer Programme is aimed at stimulating space to 

non-space technology transfers and Spin-Offs creation. Core elements of the 

ESA TTP should comprise the following tasks: *) Technology Push: Europe-wide 

extraction and marketing of potentially transferable space technologies; *) 

Market Pull: Determination of market demands in non-space industries and 

search for "Space Solutions"; *) Networking: Association of EC schemes for 

transnational technology transfer and "Valorisation" of EC-developed 

technologies (IRC,JEV,5th FP,LIFT, ); *) Additional Sources of Funding: 

Identification of European, National and regional initiatives which would 

benefit to ESA-TTN activities. 

INDUSTRIAL MATTERS & TECHNOLOGY PROGRAMMES - D/IMT 

TECHNOLOGY PROGRAMMES DEPARTMENT / IMT-T 

TECHNOLOGY TRANSFER, PROMOTION & ASSESSMENT OFFICE / 

IMT-TP 

Responsible: MR BRISSON 

Budget Ref.: 100922 - Transfer of Technology; 100612 - 

C 02 

Q4 

Technology Transfer Programme; 100612 - 

Technology Transfer Programme; 100612 - 

Technology Transfer Programme 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+IRL+GB+A+N+FIN+POR+CDN 



DIPC > 500 



Page 166 


01.241.01 VINCI ENGINE NOZZLE-EXTENSION DEPLOYMENT SYSTEM 

The present invitation to tender is related to the nozzle-extension 

deployment system of the Vinci engine for the Ariane 5 cryogenic upper stage 

(ESC-B). It encompasses the following tasks: - System development and 

qualification, - Preparation of the following recurring production phase in 

terms of process industrialisation, - A commitment on recurrent production 

costs. The selected system architecture comprises an electrical engine 

coupled with 3 shafts transmitting the motion torque to 3 screw jacks; the 

deployment system includes a specific device allowing the engine nozzle to be 

locked once deployed. The nozzle deployment system is to be controlled 

through the existing electrical system. The selected contractor will be 

supplier of SNECMA. The ITT and contract management is under the 

responsability of CNES/DLA in Evry. Technical manager to be contacted: Jean 

Marc Ruault (CNES/DLA/SDA/ESC/M) Tel: 0033160877461 E-mail: 

Jean-marc.ruault@cnes.fr 

ESAHQ 

DIRECTORATE OF LAUNCHERS - D/LAU 

ARIANE 5 DEVELOPMENT DIVISION / LAU-D 

Responsible: MR DURAND 

Budget Ref.: 100392 - Ariane 5 Plus Step 2/ CNES 

CR 01 

Q1 

Spec. Prov.: SABCA (B); MICROTECNICA SPA (I); DUTCH SPACE BV 

(NL); CASA (E); SENER SA (E); KONGSBERG DEFENCE 

& AEROSPACE (N) 


Status: INITIATED 

02.241.01 STAGE SUPPLY VALVES 

NO 

N14 


Development and qualification of the ESC-B stage supply valves. These valves 

control the supply of liquid oxygen and liquid hydrogen to the Vinci engine 

turbopumps The selected contractor will be supplier to SNECMA Moteurs. The 

ITT and contract management is under the responsability of CNES/DLA in Evry. 

Technical manager to be contacted: Jean Marc Bahu (CNES/DLA/SDA/ESC/E) Tel: 

0033160877196 E-mail: jean-marc.bahu@cnes.fr 





CR 02 

Q3 

Spec. Prov.: TECHSPACE AERO (B); ASTRIUM GMBH (D) 


Status: 

NO 



Page 167 


02.241.02 ESC-B FUNCTIONAL PROPULSION ASSEMBLY (EPF) EQUIPMENT 

ITEMS: HELIUM PRESSURISATION UNIT 

N14 


The contractor will develop and qualify the ESC-B EPF helium pressurisation 

unit. The EPF includes the attitude and roll control system (SCAR), the O2 

and H2 pressurisation/outgassing units and the helium pressurisation unit. 

This hardware consists mainly of line valves, pressure reducers, relief 

valves, purge connectors, flap valves and associated lines. The selected 

contractor will be supplier to SNECMA Moteurs. The ITT and contract 

management is under the responsability of CNES/DLA in Evry. Technical manager 

to be contacted: Jean Marc Bahu (CNES/DLA/SDA/ESC/E) Tel: 0033160877196 

E-mail: jean-marc.bahu@cnes.fr 





CR 02 

Q3 

Spec. Prov.: TECHSPACE AERO (B); MICROTECNICA SPA (I); SENER 

INGENIERIA Y SISTEMAS SA (E); VOLVO AERO 

CORPORATION (S) 


Status: 


ITEMS: PRESSURISATION/OUTGASSING UNIT AND 

ATTITUDE/ROLL CONTROL SYSTEM (SCAR) SOLENOID VALVES 

NO 

N14 

The contractor will develop and qualify the ESC-B EPF 

pressurisation/outgassing unit and SCAR solenoid valves. The EPF includes the 

attitude and roll control system (SCAR), the O2 and H2 

pressurisation/outgassing units and the helium pressurisation unit. This 

hardware consists mainly of line valves, pressure reducers, relief valves, 

purge connectors, flap valves and associated lines. The selected contractor 

will be supplier to SNECMA Moteurs. The ITT and contract management is under 

the responsability of CNES/DLA in Evry. Technical manager to be contacted: 

Jean Marc Bahu (CNES/DLA/SDA/ESC/E) Tel: 0033160877196 E-mail: 

jean-marc.bahu@cnes.fr 




CR 02 

Q3 





Status: 

NO 



Page 168 



ITEMS: ATTITUDE AND ROLL CONTROL SYSTEM (SCAR) UNIT 

N14 


The contractor will develop and qualify the ESC-B EPF attitude and roll 

control system unit. The EPF includes the attitude and roll control system 

(SCAR), the O2 and H2 pressurisation/outgassing units and the helium 

pressurisation unit. This hardware consists mainly of line valves, pressure 

reducers, relief valves, purge connectors, flap valves and associated lines. 

The selected contractor will be supplier to SNECMA Moteurs. The ITT and 

contract management is under the responsability of CNES/DLA in Evry. 

Technical manager to be contacted: Jean Marc Bahu (CNES/DLA/SDA/ESC/E) Tel: 

0033160877196 E-mail: jean-marc.bahu@cnes.fr 





CR 02 

Q3 





Status: 

02.241.05 ELECTRIC GROUND SUPPORT EQUIPMENT 

NO 

N14 


The contractor will develop and qualify the ESC-B checkout and test stand. 

The selected contractor will be supplier to Astrium GbmH The ITT and contract 


to be contacted: Jean Marc Bahu (CNES/DLA/SDA/ESC/E) Tel: 0033160877196 

E-mail: jean-marc.bahu@cnes.fr 





CR 02 

Q4 

Spec. Prov.: 


Status: 

NO 



Page 169 


02.241.06 ENGINE CONTAINER 

N14 


Development and qualification of container for protecting engine during 

transport between the production and integration sites The selected 

contractor will be supplier to SNECMA The ITT and contract management is 

under the responsability of CNES/DLA in Evry. Technical manager to be 

contacted: Jean Marc Ruault (CNES/DLA/SDA/ESC/M) Tel: 0033160877461 E-mail: 

jean-marc.ruault@cnes.fr 





CR 02 

Q3 

Spec. Prov.: REVELLI METALLIK SPA (I); GENIUS KLINKENBERG BV 

(NL); SENER INGENIERIA Y SISTEMAS SA (E); 

AUSTRIAN AEROSPACE GES.MBH (A) 


Status: 

02.241.07 THERMAL SHIELD 

NO 

N14 


The contractor will develop and qualify the Vinci engine thermal shielding. 

Its purpose is to block off heat radiated by the divergent from the upper 

part of the engine. The selected contractor will be supplier to SNECMA The 

ITT and contract management is under the responsability of CNES/DLA in Evry. 

Technical manager to be contacted: Jean Marc Ruault (CNES/DLA/SDA/ESC/M) Tel: 

0033160877461 E-mail: jean-marc.ruault@cnes.fr 





CR 02 

Q3 

Spec. Prov.: SABCA (B); DUTCH SPACE BV (NL); CASA (E); 

IBERESPACIO (E); MAGNA STEYR FAHRZEUGTECHNIK AG 

& CO KG (A) 


Status: 

02.241.08 DYNAMIC TESTING OF ENGINE 

NO 

N14 


The contractor will carry out dynamic testing of Vinci engine The selected 

contractor will be supplier to SNECMA The ITT and contract management is 

under the responsability of CNES/DLA in Evry. Technical manager to be 

contacted: Jean Marc Ruault (CNES/DLA/SDA/ESC/M) Tel: 0033160877461 E-mail: 

jean-marc.ruault@cnes.fr 





CR 02 

Q3 

Spec. Prov.: INTESPACE (F); IABG (D); CASA (E); INTA (E); 

CONTRAVES SPACE AG (CH) 


Status: 

NO 



Page 170 


02.241.09 VINCI FLIGHT CONTROL SERVO-ACTUATORS 

N14 


The contractor will develop and qualify the Vinci engine servo-actuators. 

These control the Vinci engine’s thrust orientation by acting on the engine 

which has an articulated interface with the thrustframe via a gimballed 

joint. The servo-actuators form part of the servo-command system. The 

selected contractor will be supplier to ASTRIUM GmbH The ITT and contract 


to be contacted: Thierry Stillace (CNES/DLA/SDA/SEL) Tel: 0033160877436 

E-mail: thierry.stillace@cnes.fr 





CR 02 

Q3 

Spec. Prov.: SABCA (B); MICROTECNICA SPA (I); SENER 

INGENIERIA Y SISTEMAS SA (E) 


Status: 

NO 



Page 171 


00.243.02 FLTP - TECHNOLOGY DEVTS IN CERAMIC STRUCTURAL 

COMPONENTS 



NEW LAUNCHER CONCEPTS & TECHNOLOGY OFFICE 


Budget Ref.: 100351 - FLTP 

CR 00 

Q2 

Spec. Prov.: SNECMA , AEROSPATIALE MATRA LANCEURS F 



DIPC > 500 



Page 172 


00.153.07 COST EFFECTIVE, MODULAR ACTIVE ARRAY ANTENNAS 

The future S-UMTS satellite require complex steerable multi-small-spot-beam 

antennas, each antenna producing about 100 beams, rather than the 20 beams of 

the first generation PCS systems. Active array antennas are strategically 

important for this application. This activity is planned to meet the demand 

for such systems to enable European industry to offer second generation 

"turn-key" systems in this area, and to lead the space segment activity. The 

objective is to design and qualify multiple beam array antennas suitable for 

the S-UMTS user link and producing 60 to 100 beams. The activity will 

investigate active arrays built with multi-layer and modular techniques. It 

will concentrate on mass production and rapid testing and be concluded with a 

full EQM demonstration of an active array antenna. The first phase covers 

architectural trade-off and preliminary design, the second phase detailed 

design and qualification of the antenna sub-system. The technology developed 

should be suitable, in principle, for both phased arrays (applicable to LEO 

and MEO missions) as well as feed arrays (applicable to MEO and GEO 

missions). All scenarios shall be addressed during Phase 1. The EQM to be 

built in Phase 2 could be targeted to a specific mission scenario to be 

selected at the of Phase 1. In order to maintain competition in this critical 

technology the Agency envisages to place parallel contracts for the first 

phase for a maximum of 500 KEUR. For the follow-on phase, a detailed proposal 

shall be submitted and the best offer will be selected. 

ESTEC 






C 02 

Q2 



Status: 

DIPC > 500 



Page 173 


01.153.02 DEMONSTRATOR FOR REAL-TIME HIGH-SPEED SATELLITE 

DIGITAL TRANSMISSION TECHNIQUES 

The objective of this activity is the development of a (quasi)-real-time 

demonstrator for study and optimisation of advanced transmission techniques 

(such as coding, modems) for digital data transmission (broadcasting/ 

multi-casting/point-to-point) over satellite links. The system will emulate 

the end-to-end link including satellite non-linearity, filtering, 

satellite-to-Earth propagation, co-channel and adjacent channel interference, 

thermal noise and receiver phase noise. Additionally, the system shall also 

allow the interface to ground stations in order to evaluation performances in 

a real satellite environment, taking into account the various propagation 

conditions in different frequency bands (ranging from Ku up to Q/V) allowing 

the emulation and assessment of fading counter-measure. The demonstrator 

shall be easily programmable and configurable through a user-friendly man 

machine interface. 

****************************************************************** 

****************************************************************** 







C 02 

Q3 


Programme Ref.: ASTE FB1.12 


01.153.03 PROPAGATION BEACON PAYLOAD 

DIPC > 500 

ESTEC 

Future satellite communications will make use of millimetre wave frequencies. 

Planning and designing a satellite system in these new frequency bands will 

require accurate knowledge of the propagation conditions on the link which 

however can only be predicted with some degree of confidence, after 

experiments have been conducted. This activity therefore aims to prepare for 

such experiments with a propagation beacon payload. The objective of the 

activity is to investigate the feasibility of such a propagation beacon 

payload at millimetre frequencies, design a light-weight, low-power 

3-frequency mm-Wave beacon and build an elegant breadboard. 

****************************************************************** 

****************************************************************** 







C 02 

Q2 



Status: 

DIPC > 500 



Page 174 


01.153.04 PATCH ANTENNA FOR MOBILE RECEIVE ONLY TERMINALS 

The envisaged system is a car mounted mobile terminal, which is suitable to 

receive dedicated signals from standard Ku-band broadcast satellites. The 

antenna is a small flat patch antenna, which is electronically steerable and 

can track broadcasting satellites, even if they are at end of life and not 

fully stabilised anymore. The terminal design will need specific signal 

spreading, coding and interleaving equipment, suitable to mitigate the 

effects of a mobile Ku-band channel, which is characterised by frequent 

signal interruptions of various lengths. Such a system can potentially 

provide several attractive services like radio broadcasting and data casting 

with local caching of relevant information for the user. These services could 

be provided on a European wide scale at very low transmission cost, because 

end of life satellites can be used. A study undertaken under ARTES-1 will 

demonstrate the feasibility of such a system considering the service aspects, 

channel investigations and corresponding countermeasure equipment and 

ultimately a definition of critical items, which need to be developed. It is 

foreseen that the results of this study will become available at an early 

stage of the activity. It is anticipated that mobile satellite receive 

terminals will open a new market segment and will be able to further exploit 

Ku-band satellites, in particular those at end of life. A key element in the 

mobile terminal is a flat antenna, which can be electronically steered in 

order to track the satellite when the mobile terminal is in motion. 

Polarisation control, high aperture efficiency and a very low mechanical 

profile design are further challenging requirements. This kind of antenna is 

beyond state of the art and the development is considered risky. The activity 

will cover the design, implementation and testing of an antenna prototype. 

****************************************************************** 

****************************************************************** 


ESTEC 






C 02 

Q4 



Status: 

DIPC > 500 



Page 175 


01.153.05 MOBILE KU-BAND RECEIVE ONLY TERMINAL 

The envisaged system is a car mounted mobile terminal, which is suitable to 

receive dedicated signals from standard Ku-band broadcast satellites. The 

antenna is a small flat patch antenna, which is electronically steerable and 

can track broadcasting satellites, even if they are at end of life and not 

fully stabilised anymore. The terminal design will need specific signal 

spreading, coding and interleaving equipment, suitable to mitigate the 

effects of a mobile Ku-band channel, which is characterised by frequent 

signal interruptions of various lengths. Such a system can potentially 

provide several attractive services like radio broadcasting and data casting 

with local caching of relevant information for the user. These services could 

be provided on a European wide scale at very low transmission cost, because 

end of life satellites can be used. A study undertaken under ARTES-1 will 

demonstrate the feasibility of such a system considering the service aspects, 

channel investigations and corresponding countermeasure equipment and 

ultimately a definition of critical items, which need to be developed. It is 

foreseen that the results of this study will become available at an early 

stage of the activity. This mobile- terminal shall be able to support a 

number of voice and data services in the coverage area of Ku-band satellites. 

It shall make use of a flat antenna, which is electronically steerable and 

able to track inclined satellites, such as the one developed under activity 

FB 9.32. The receiver shall contain all the modules, necessary to mitigate 

the effects of a mobile Ku-band channel to a level, as required by the 

envisaged services. The spectrum of possible services supported by this 

terminal can be significantly enlarged by integration of functionality as 

provided by GPS and GSM modules. The development effort is complex and of 

high risk. The activity will cover the design, implementation and testing of 

a receiver prototype. 

****************************************************************** 

****************************************************************** 


ESTEC 






C 02 

Q4 



Status: 

DIPC > 500 



Page 176 


01.153.13 NOVEL RAILWAY CONTROL SYSTEM 

Railway operations in the different countries follow different standards, 

most of which have been developed during the last century. The introduction 

of high-speed train services call for a novel internationally agreed approach 

that relies on a combination of sensors and on integrated communication. 

Position determination by means of GNSS signals will play a major role. A 

number of GNSS developments have already been initiated in the railway 

sector, but all of them address specific applications. This activity concerns 

the proof-of-concept demonstration of a novel railway control system. It will 

complement already ongoing initiatives. The emphasis with this development 

will be on a demonstration programme through which the performances 

achievable with EGNOS and ultimately GALILEO will be critically assessed. The 

activity will be carried out in close cooperation with the European 

Commission. 

****************************************************************** 

****************************************************************** 







C 02 

Q2 


Programme Ref.: ASTE NS 10.2 

Status: 

01.153.16 MANOEUVRABLE ON-BOARD CAMERA 

DIPC > 500 

ESTEC 

The objective of this activity is the design of a camera system that could 

manoeuvre in some manner to provide pictures of critical features of the 

spacecraft in orbit. In the first phase the system shall be designed, in the 

second phase a proto-flight qualification model built. Equipment suppliers 

should involve satellite primes where appropriate. 

****************************************************************** 

****************************************************************** 







C 02 

Q2 



Status: 

DIPC > 500 



Page 177 


01.153.17 FLIGHT QUALIFICATION OF MOSAIC INFRA RED EARTH SENSOR 

Engineering models of solid state Infra Red Earth sensors have been 

developed, manufactured and tested by European companies. In previous 

activities a proof of concept has been achieved. To make such a sensor 

available as an off the shelf unit the following steps as part of the 

suggested activity will be required: • Qualification of infra red detector 

array; • Design update of engineering model and manufacturing of a flight 

model; • Qualification of the flight model. 

****************************************************************** 

****************************************************************** 







C 02 

Q2 



Status: 

01.153.18 FLIGHT QUALIFICATION OF LOW COST DIGITAL SUN SENSOR 

DIPC > 500 

ESTEC 

New designs of digital sun sensors based on the use of Active Pixel Sensors 

(APS) are currently under development. As next step in the deployment of this 

new generation of sun sensors a demonstration / first usage in flight will be 

necessary. The proposed activity shall prepare this by design update for a 

flight model, manufacturing and formal qualification of flight unit(s) for a 

first application. 






C 02 

Q4 




DIPC > 500 



Page 178 


01.153.20 GLOBAL ARCHIVE OF SATELLITE PROPAGATION DATA 

The objective of this activity is to: 1) Collect propagation data (raw data 

and statistics) from all possible sources (within and outside Europe) for any 

experiment less than 10 years back; 2) Check data for consistency and create 

meta-file (with all relevant formatting and conversion information); 3) Store 

all data on CD-ROM or DVD and create master index. 

****************************************************************** 

****************************************************************** 







C 02 

Q2 



Status: 

01.153.22 SELF-REGULATING HEATERS 

DAC 200-500 

ESTEC 

Materials exhibiting physical properties able to effectively "modulate" their 

own electrical impedance as a consequence of temperature changes are known. 

These are used in the form of deposited tracks or "inks" in a number of 

terrestrial applications where the accuracy in controlling the dissipation, 

the reproducibility of the application and the reliability are subjected to 

relatively low standard requirements (e.g.: heaters for car mirrors). The 

proposed activity is aimed at upgrading the technology in question and 

renders it available for space applications through specific development and 

generic qualification process. 

****************************************************************** 

****************************************************************** 







C 02 

Q2 



Status: 

DAC 200-500 



Page 179 


01.153.32 DIGITAL PAYLOAD ROUTING SWITCH DEMONSTRATOR 

Broadband communication applications are now a reality, which require payload 

switches capable of routing dynamically 2-way traffic. The traffic supports a 

wide range of interactive telecommunication services resulting in data rates 

exceeding 10 Gbps. Such systems require a large number of beams with a 

frequently changing traffic distribution. An efficient usage of the satellite 

resources require fast and flexible frequency demultiplexing and 

multiplexing, the implementation of which is only feasible in digital 

technology. The digital technology available is not well suited to run at the 

required speed, as the power consumption would be excessively high. A 

promising architecture to overcome the speed limitations is the poly-phase 

filter concept, based on a combination of analogue delay lines, sample/hold 

switches, low/medium speed analogue-to-digital and digital-to-analogue 

converters, and standard Fourier transform components. Hereby the 

decimation/integration is performed by the analogue components, reducing the 

speed requirement substantially, allowing the analogue-to-digital conversion 

at reduced speed, followed by the digital electronic block performing the 

Fourier transform processing. To avoid expensive and time-consuming hardware 

manufacturing a demonstrator shall be built using off-the-shelf components. 






C 02 

Q2 



Status: 

01.153.33 AUTONOMOUS REAL-TIME SPACECRAFT ORBIT CONTROL BY GNSS 

DIPC 200-500 

ESTEC 

GNSS signals, complemented by some pseudolites on Earth, will allow for 

autonomous orbit control of GEO (telecommunication) spacecraft. This activity 

concerns a laboratory demonstration of such system. After initial discussion 

of the concept with satellite operators, the technique has been found 

attractive from the operations and the financial point of view. However, it 

has also been found necessary to validate the technique through a laboratory 

demonstration. The activity will comprise the preliminary studies, test 

campaign definition, GNSS signal generator and GNSS receiver upgrades, and 

laboratory validation of the Real-Time Spacecraft Orbit Control concept. It 

will involve as much as possible representative hardware and software. The 

test set up will comprise a GNSS RF signal generator and a GNSS space 

receiver. The signal generator will generate a combination of navigation 

signals transmitted from GNSS satellite constellations and navigation signals 

transmitted from terrestrial pseudolites stations. 






C 02 

Q2 


Programme Ref.: ASTE NS 14.1 

Status: 

DIPC > 500 



Page 180 


01.153.36 INFORMATION MANAGEMENT AND COMMUNICATIONS SUPPORT FOR 

THE ARTES PROGRAMMES 

The smooth operations of the Website and Intranet applications requires 

continuous support Website. The proposed activity covers Website operations 

and maintenance, project support around the existing information tools and 

the required technical maintenance of the underlying database applications 

and network computers. This includes the following tasks: Contents: Website 

editing, support and copy-writing of articles of Telecom Newsletter, 

preparation of press release; communication support at exhibitions and 

conferences, graphical support as needed.; Applications: Building 

applications to support internal and external business processes, such as 

Call for Ideas (submission and evaluation), submission of project pages, 

datasheets, progress reports from industry and linking them with internal 

database systems, linking dynamic web pages with the ARTES Information 

Management System (AIMS) e.g. status of programme activities, open tenders 

etc; Administrative support: Operations of AIMS, including invoice 

processing, maintaining our industry contact database including direct 

marketing and follow-up to support the start-up initiative (see Newsletter). 

In addition existing procedures and work processes and associated information 

flow will be analysed in regular intervals in order to identify priorities 

and recommendations for the most efficient way to enhance the system as a 

whole and make best use of the information systems in place. 

ESTEC 





Budget Ref.: 100441 - ARTES 1 PSI 3; 100404 - ARTES 4 TEPP; 

C 02 

Q2 

100415 - ARTES 5 ASTE 3; 100413 - ARTES 3 Phase 

2 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+IRL+GB+A+N+FIN+POR+CDN+LUX+ 

GR 


Status: POSTPONED 

YAC > 500 



Page 181 


01.153.38 SOLAR ARRAY SIMULATOR FOR MULTIJUNCTION CELLS 

The power level of solar arrays has been increasing at a rapid pace. This 

trend will continue as the market for Telecommunications Satellites of very 

high power levels of at least 25 kilowatts continues to grow. The mature 

operator wants the largest possible satellite with a maximum number of 

transponders/operational channels. Current designs generally utilise larger 

and larger areas of panels to be covered with Silicon or Gallium Arsenide 

cells to produce power. Now, Multijunction Solar Cells are quickly becoming 

the industrial standard for the power supply of Telecommunications satellites 

due to their improved performance resulting of the utilisation of a wider 

part of the Solar spectrum. A Solar Simulator is required to check the panels 

at a high level of accuracy for acceptance and verification following system 

tests. This simulator now needs to accommodate the wider spectrum utilised to 

create the power from Multijunction cells. Not only must the test spectrum be 

wider, but it is considered necessary to be able to check the individual 

junction performance separately. The Solar Simulator can be available for 

future ESA programmes as well as being available under commercial 

arrangements for industrial use. The objectives of the work are to produce a 

test procedure, to design, develop and build a Solar Array Simulator system 

for Multijunction solar cells. 






C 02 

Q2 



Status: 

02.153.07 LOW-COST SOLID STATE KU-BAND RF EQUIPMENT USING NEXT 

GENERATION PACKAGING TECHNOLOGY 

DIPC 200-500 

ESTEC 

This activity is to design, manufacture and test the RF section of a channel 

amplifier and a LNA/down-converter for Ku-band using RF building blocks based 

on next generation packaging technologies. The RF building blocks will be 

designed, manufactured and tested before being integrated into the RF 

sections of the above mentioned equipment. The next generation packaging 

technology offers a significant reduction of recurrent cost for the 

manufacturing of such sections. 






C 02 

Q3 



Status: 

DIPC > 500 



Page 182 


02.153.09 HIGH-END TELEMEDICINE APPLICATIONS 

This activity will concentrate on the development, integration and validation 

in pre-operational conditions, involving real end users, of high-end 

telemedicine applications. The work will be organised in a structured 

water-fall approach, enabling a careful definition and selection of the 

functionalities and user requirements for the medical peripherals and for the 

satcom component in order to respond to the user needs in the most efficient 

and economical way. 






C 02 

Q3 



Status: 

02.153.10 TRANSPORTABLE THIN ROUTE EMERGENCY REPLACEMENT 

TELECOMMUNICATIONS SYSTEM 

DIPC > 500 

ESTEC 

The objective is to develop a transportable, user friendly, flexible and 

rugged telecommunications system for establishing basic telecommunications in 

case of emergencies or natural disasters, where other telecommunications 

means are not existing or disrupted e.g. in case of earthquakes. The system 

will be composed of a transportable (wireless) communications base station 

providing local communication capability combined with a satellite link to 

the public network. Installation/maintenance support will be included for a 

limited period. 






C 02 

Q4 



Status: 

DIPC > 500 



Page 183 


02.153.11 INNOVATIVE NETWORKING TECHNIQUES AND TECHNOLOGIES 

The activity aims at studying and simulating innovative networking techniques 

and technologies in the frame of next generation broadband satellite systems. 

These systems will offer packet-based communications, and a largely increased 

capacity (> 10 Gbps) compared to current systems. In particular, this 

activity shall focus on access and network related aspects (OSI layered 

model), targeting an efficient utilisation of the satellite resources and 

providing a seamless integration with terrestrial networks. 






C 02 

Q3 



Status: 

02.153.12 60GHZ TWTA FOR INTERSATELLITE LINKS 

DIPC > 500 

The objective of this activity is to develop a TWTA at 60 GHz for 

intersatellite links providing up to 50W output power, and bandwidth of 2.5 

GHz. The design of the high voltage and the RF structures will be optimised 

to allow for a reliable operation in space, still with reasonable efficiency. 

Due to the relative high power level at this high frequency (i.e. small 

size), thermal and mechanical aspects will be carefully investigated. 






C 02 

Q4 



Status: 

02.153.13 Q/V BAND RF EQUIPMENT FOR DEMONSTRATION PAYLOAD 

DIPC > 500 

ESTEC 

The activity is to develop RF equipment at Q/V-band for aeronautical-, 

intersatellite- and space-to-ground links wideband communication. Equipment 

such as input and channel waveguide filters at both 40 and 50 GHz, R-type and 

C-type waveguide switches at 40 and 50 GHz, and 40 GHz lineariser will be 

designed, manufactured and tested to Engineering Qualification Model (EQM) 

standard. The activity will be undertaken only in case a demonstration 

mission will be available. 






C 02 

Q4 



Status: 

DIPC > 500 



Page 184 


02.153.14 DEVELOPMENT OF A GENERIC RADIO RESOURCE MANAGER FOR 

SATELLITE NETWORKS 

This activity is to analyse the system architecture of the various European 

satellite network initiatives and to derive requirements for a radio resource 

management (RRM) system. The different complexity of the satellite networks 

will be reflected in the architecture such that a modular design of the RRM 

can be defined, such that single modules can be used for simple star 

networks, while for complex multiple beam meshed regenerative networks an 

assembly of several RRM modules would be needed. The development will be in 

two phases; the first phase will cover the analysis of the network 

architecture of satellite systems, which are presently in the definition 

phase leading to the definition of the RRM requirements. Based on the 

requirements RRM architecture will be defined and all modules will be 

specified. The second phase will cover the software development including 

verification in a simulated environment. 






C 02 

Q2 



Status: 

02.153.15 ADAPTIVE CODING AND MODULATION MODEM FOR BROADBAND 


DIPC > 500 

ESTEC 

The activity is to study, design, manufacture and test an elegant prototype 

modulator and demodulator unit exploiting adaptive coding and modulation to 

be used in future broadband networks operating at Ka-band and above. The 

modem will support data rates ranging from a few Mb/s to hundreds of Mb/s. 






C 02 

Q4 



Status: 

DIPC > 500 



Page 185 


02.153.16 USER TERMINAL MODULARITY AND TECHNOLOGY 

This activity is to study and define the indoor unit of user terminals for 

the next generations of satcoms and to develop a technology demonstrator. The 

main objective is to reduce the cost by means of maximizing the re-use of 

core components in different terminal and system configurations. 






C 02 

Q4 


Programme Ref.: ASTE GI9.10 


02.153.17 DEMONSTRATION OF THE USE OF SPACE TECHNOLOGIES IN 

EMERGENCY AND DISASTER RELIEF APPLICATIONS 

DIPC > 500 

The objective of the activity is the development and demonstration of 

combined/integrated space technologies such as telecommunications, navigation 

and earth observation, in emergency, large events or disaster relief 

applications. The applications may include forest fires, earthquakes, floods, 

exceptionally heavy winter conditions, hazardous materials related 

emergencies, large sport events such as the Olympic Games etc. 






C 02 

Q3 


Programme Ref.: ASTE SE 10.4 

Status: 

02.153.18 PHOTONIC BANDGAP ARRAYS 

DIPC > 500 

ESTEC 

This activity is to design, manufacture and test a photonic bandgap array 

(PBGA) antenna. Improvements in terms of bandwidth and scanning capability 

with respect to traditional phased array antenna technology will be 

quantified. 






C 02 

Q3 



Status: 

DIPC > 500 



Page 186 


02.153.19 NEXT GENERATION LARGE ANTENNA TECHNOLOGIES 

This activity is to study different solutions for a deployable large 

reflector (conventional unfurlable strut design, inflatable membrane 

reflector, deployable flat reflector, reflector shaping by controlled rib 

bending), selection of the most promising concept, and the design, 

manufacturing and test of a prototype unit composed of unfurlable/deployable 

reflector and feed horn assembly. Both, mechanical and electrical tests will 

be performed. 






C 02 

Q3 



Status: 

02.153.20 MINIATURISED LIGHTWEIGHT SYNTHESIZER 

DIPC > 500 

ESTEC 

This activity is to design, manufacture and test an engineering model of a 

miniaturised lightweight frequency synthesizer with low phase noise and phase 

locked to an external reference. The synthesizer is to be used in future 

communication satellite payloads, including systems using 8-PSK modulation 

and higher order modulation schemes. Advanced technologies (MMIC, ASIC, 

packaging and interconnections) will be used to give small, reproducible and 

highly reliable equipment, simultaneously facilitating assembly and tuning. 






C 02 

Q3 



Status: 

DIPC > 500 



Page 187 


02.153.21 HIGH PERFORMANCE ON-BOARD PROCESSING TECHNOLOGY 

This activity is to investigate the applicability of the transputer 

architecture in the field of high performance data processing. The 

investigations will be supplemented by breadboarding activities to verify 

some critical functions. Undoubtly the transputer concept is an extremely 

powerful reconfigurable processor technology built by using scalable arrays 

of arithmetic processing elements, with embedded memories and input/output 

interface ports. Data handling capacity of >10Gbps and data throughput of 

>6Gbyte/s are being considered feasible. In parallel the possible advantage 

of neural networks, eventually in combination with the transputer array 

architecture, will be investigated. 






C 02 

Q4 



Status: 

02.153.22 NEW STANDARD COMPLIANT TT&C TRANSPONDER 

DIPC > 500 

ESTEC 

The activity is to develop a spread spectrum Telemetry, Command and Ranging 

(TCR) transponder for Geostationary Communications Satellites based on a 

recently developed ETSI standard. The technology used will be spread spectrum 

suppressed carrier modulation, operating initially in Ku-Band but with 

scalable to future Ka-Band systems. In addition, the transponder will be dual 

mode in order to be compatible with existing ground networks when required in 

LEOP and emergency situations. 






C 02 

Q3 



Status: 

DIPC > 500 



Page 188 


02.153.23 DEVELOPMENT OF PAYLOAD EQUIPMENT WITH WIRELESS TT&C 

INTERFACE 

The objective of the activity is to identify and study promising wireless 

communication systems for the next generation on-board telemetry and 

telecommand system. Both RF and optical candidate systems should be studied, 

and one system should be selected, built and tested in a representative 

configuration to demonstrate its feasibility for on-board applications. 






C 02 

Q3 



Status: 

02.153.24 THIN FILM SOLAR CELLS 

DIPC > 500 

The objective is to develop the thin film solar array cell technologies for 

application in the construction of very large arrays. As satellites reach 

higher power levels, there is a need for significant cost reduction if 

possible in the procurement of solar arrays. Thin film technology promises to 

allow for significant cost savings as compared to the current designs. The 

cost reduction needs to be of the order of 50 per cent per watt allowing for 

a lower performance and larger array. This activity will be coordinated with 

TRP activities on the same subject. 






C 02 

Q3 



Status: 

02.153.25 THIN MULTI-JUNCTION SOLAR CELLS 

DIPC > 500 

ESTEC 

The objective is to develop the thin quad junction solar cells in order to 

reduce costs, mass and improve performance for the large solar arrays. 

Technology is ready to reduce the thickness of Germanium to 100 microns or 

less and apply the layers for a quad junction cell with efficiencies in 

excess of 30 per cent conversion. This activity will be coordinated with TRP 

activities on the same subject. 






C 02 

Q4 



Status: 

DIPC > 500 



Page 189 


02.153.26 SUPERCONDUCTIVE MATERIALS FOR ELECTRIC PROPULSION 

The activity is to assess, breadboard and test the suitability of 

superconductive materials for the electric coils in electric propulsion 

systems. 






C 02 

Q4 



Status: 

02.153.27 EUROPEAN FLOW CONTROL VALVE FOR APOGEE BOOST MOTOR 

DIPC 200-500 

This activity is to develop a flow control valve for a 400 N bipropellant 

thruster, which is primarily used as apogee boost motor for communication 

satellites. The work will consist of the design, manufacturing and 

verification/qualification of the valve/thruster assembly including 

environmental and hot firing testing. 






C 02 

Q4 



Status: 

02.153.28 ENVIRONMENTALLY FRIENDLY SMALL MONO-PROPELLANT SYSTEM 

DIPC > 500 

ESTEC 

The activity is to develop a monopropellant system with environmentally 

friendly propellants. The development will include design of thrusters 

suitable for the new propellant. Plume impingement and contamination will be 

addressed. This activity will be coordinated with TRP activities on the same 

subject. 






C 02 

Q4 



Status: 

DIPC > 500 



Page 190 


02.153.29 HIGH RESOLUTION ACTUATOR FOR ANTENNA POINTING 

The goals of the activity are to develop and qualify a European innovative 

high-resolution standard rotary actuator for space mechanisms. The actual 

resolution of space rotary actuator used for antenna pointing mechanisms is 

around 0.01 . The aims of this activity are to go to "un-powered" resolution 

less than 0.005 , decrease the full step resolution to less than 0.005 , 

increase life time to 15 years (at actuator and sensor level) and to achieve 

an FM price under US market level. 






C 02 

Q3 



Status: 

02.153.30 STRUCTURE TECHNOLOGY 

DIPC > 500 

The objective is to develop the technologies associated with the payload 

module of the Large Platform. The development will include design, 

manufacturing, test and qualification of a preferred concept to be identified 

early in the activity. 






C 02 

Q3 



Status: 

02.153.31 MECHANICAL PUMP FOR FLUID LOOPS 

DIPC > 500 

ESTEC 

The activity is to study the feasibility and subsequently to develop a 

mechanical pumping system with high reliability and suitable for large 

telecommunication platforms. Development of appropriate accelerated 

life-testing techniques will be performed to demonstrate the required 

reliability. The activity will be taking advantage of previous and ongoing 

TRP/GSTP activities in this field. 






C 02 

Q3 



Status: 

DIPC > 500 



Page 191 


02.153.32 NEW STANDARD COMPLIANT TT&C GROUND MODEM 

The activity is to design, manufacture and test a spread spectrum Telemetry, 

Command and Ranging (TCR) ground modem for geo-stationary communications 

satellites based on a recently developed ETSI standard. The technology used 

will be spread spectrum suppressed carrier modulation, operating initially in 

Ku-Band and upgradeable to future Ka-Band systems. The modem itself will 

operate at an IF frequency appropriate to the ground station installation. 






C 02 

Q4 



Status: 

02.153.33 S-DAB PROPAGATION MEASUREMENT CAMPAIGN 

DIPC > 500 

This activity is to develop and verify an RF propagation model at L- and 

S-band for satellite communications to mobiles in cities. The link outage 

duration and the frequency of outages will be modeled. The model will be 

verified by performing a measurement campaign in city areas with high rise 

buildings. An assessment will be made of the number of terrestrial repeaters 

needed to provide a flawless signal reception. 






C 02 

Q3 



Status: 

02.153.34 ADVANCED DEPLOYMENT MECHANISMS FOR SOLAR ARRAYS 

DAC 200-500 

ESTEC 

This activity is to design, manufacture and test an advanced deployment 

mechanism for solar arrays. The deployment mechanism will be designed such 

that it is adaptable to a range of performance requirements. 






C 02 

Q3 



Status: 

DIPC 200-500 



Page 192 


02.153.35 TUNEABLE EMITTANCE THERMAL COATING 

The activity is to study the applicability of the electrochromic and 

electrophoretic effects to spacecraft thermal control coatings and surfaces 

and to design, manufacture and test the performance (at breadboard level) of 

promising materials. 






C 02 

Q4 




02.153.36 MINI HEAT TRANSPORT SYSTEM DEPLOYABLE RADIATOR 

DAC 200-500 

This activity is to develop a novel type deployable radiator based on recent 

advances in miniaturization of two-phase technology, aiming at smaller heat 

loads and providing a high degree of flexibility. A critical assessment will 

be performed of all recently developed two-phase loop technologies, e.g. CPL 

and LHP miniaturization, novel evaporator designs, new materials for CPL/LHP 

design and adapt/optimize such designs - experimentally and analytically - 

for an implementation into a novel type of deployable radiator. Aspects like 

heat rejection to mass ratio, design flexibility, efficiency, reliability, 

cost shall be major design drivers. A prototype will be designed and tested 

under simulated orbital conditions. This activity will be based upon TRP 

results. 






C 02 

Q3 



Status: 

02.153.37 PASSIVE HEAT FLOW SWITCHING DEVICE 

DAC 200-500 

ESTEC 

The activity is to study, manufacture and test a breadboard of a 

light-weight, high performance heat-switching device aimed at controlling the 

temperature of high dissipating equipment by passive means. 






C 02 

Q3 




DAC 200-500 



Page 193 


02.153.38 PROGRAMMABLE ACTIVE NETWORKS FOR NEXT GENERATION 

MULTIMEDIA SERVICES PROVISION THROUGH SATELLITE 

TERRESTRIAL HETEROGENEOUS SYSTEMS 

N1 

ESTEC 

Next generation satellite systems are elements of integrated but still 

heterogeneous multi-service network infrastructure. Satellite-terrestrial 

systems integration is driven by the demand of content and service providers 

that want to reach an ever-increasing number of end users that access through 

different edge network segments. The service providers demand also 

flexibility to create, enable and tailor services to different network 

loading conditions supporting more and more sophisticated applications with 

guaranteed Quality of Service (QoS). The present activity aims at 

investigating the applicability of programmable active network based 

technology for the provision of advanced multimedia services through 

satellite-terrestrial heterogeneous systems. Programmable active networks 

represent a ’quantum leap’ in the evolution of networks supporting dynamic 

control and modification of the network behaviour using well defined packets 

structures that contain general-purpose code and uniform standardised 

execution platform at the network nodes and edges. Therefore, they expose 

resources, mechanisms, and policies for constructing or refining new services 

with guaranteed QoS and facilitate connection control and unified management 

in heterogeneous environments. The study objectives include * the definition 

and evaluation of an end-to-end integrated network architecture including 

multi-beam transparent and regenerative satellite segments for supporting the 

new protocols; * the identification of the necessary key technological 

developments to deploy and use such new protocols to be developed on top of 

the new QoS architecture based on IPv6 and DiffServ; * complete assessment of 

the feasibility and the potential of the advocated approach by conducting 

thorough testing of advanced multimedia applications. 




Responsible: MR CASAS 

Budget Ref.: 100441 - ARTES 1 PSI 3 

C 02 

Q2 


GR 


Status: 

DAC 200-500 



Page 194 


02.153.43 HIGH-TEMPERATURE HEAT PIPES FOR TELECOM SATELLITES 

N5 

With ever growing payload power the thermal control is becoming an important 

design driver for large communication satellites. Efficient heat transport is 

of paramount importance, especially from collectors of the high power 

traveling wave tubes and the payload’s output multiplexers towards the 

satellite’s thermal radiators. In this activity prototypes of a new type of 

high-temperature heat pipes will be developed. While currently available heat 

pipes are operated typically at temperatures around 80C, these new heat pipes 

will work at higher temperatures, hence allowing for more efficient 

radiation. High-temperature heat pipe technology exists in the U.S., but is 

not available in Europe. As this equipment is key for large communication 

satellites the Agency considers it strategically important to develop the 

technology in Europe as a matter of urgency. 





Budget Ref.: 100428 - ARTES 8 Large Platform Missions 

C 02 

Q3 

Spec. Prov.: F+D+NL+CH+N+LUX 


Status: POSTPONED 

02.153.45 THREE-AXIS FIBRE OPTIC GYRO (FOG) 

YAC 200-500 

N9 

ESTEC 

The purpose of this activity is to perform pre-development in order to 

qualify European Fiber Optics Gyros for Telecommunication satellites. The 

presently used gyros are DTG (Dynamically Tuned Gyros), HRG (Hemispherical 

Resonator Gyros) and RLG (Ring Laser Gyros). DTG (Sagem, Astrium/Condor) will 

be obsolescent around 2007. HRG (Litton) would demand a high development 

investment for a space product to be produced in Europe. No cost improvement 

perspective appears with RLG (Honeywell, L3COM). FOG technology appears the 

most credible and competitive European solution, to be developed in synergy 

with Earth Observation and Scientific applications. Specifications for 

Telecom FOG will be produced in the frame of the CNES @BUS phase A2 contract, 

depending on the selected AOCS architecture. Main requirements could be the 

following: * Cumulated on time: trade-off to be performed 1 year (TBC) or 15 

years; * Reliability: >0.99 for 1 year cumulated on time among 15 years 

(TBC); * Flicker noise


Page 195 


02.153.50 CHARACTERISATION OF MULTI-FLUID-LOOPS IN A LARGE 

DEPLOYABLE RADIATOR 

N9 

The purpose of this activity is to characterise the mono-evaporator 

mono-condenser loop heat pipe (LHP) behaviour when several LHPs (typically 4) 

are operating simultaneously under the configuration where: * the LHP 

evaporators heat loads are strongly uneven; * all the LHP condensers are 

mounted in close proximity to each other on a same radiator panel; * big and 

non homogeneous (in temperature) radiator panel. The breadbord configuration 

will be as close as possible to large platform deployable radiator (DR) 

concept. Critical issues to be investigated include: * interaction between 

the loops at radiator level, with one set working with the thermal interface 

at 50 deg C and other set at 35 deg C.; * effect of the environmental 

conditions such as solar flux with partial shadowing of the radiator, 

possible heating of the flexible lines etc. 




Responsible: MR MAUROSCHAT 


C 02 

Q3 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+IRL+GB+A+N+FIN+POR+CDN+LUX 

Programme Ref.: ARTES 8 PP17.5 


02.153.51 HIGH PERFORMANCE LOOP HEAT PIPES 

DIPC > 500 

N9 

ESTEC 

The purpose of this activity is to develop an enhanced European loop heat 

pipes (LHP) compatible with: * specific Large Platform satellite shelves’ 

heat-pipe networks; * large Large Platform deployable radiators (typically 

5-6 m2); * satellite and DPR ground test configuration without payload 

operational constraints. Main development points to be investigated will be: 

* evaporator enhanced performance (multiples flanges, higher heat transfer 

coefficient, lower pressure drop through the grooves, ...); * enhanced 

reservoir body & wick design compatible with the following constraints: long 

fluid transport lines, large condenser, reduced mass, ...; * enhanced 

capillary wick material (smaller pore size, lower conductivity, ...); * large 

condenser with lower pressure drop; * possible multiple freezing and thawing 

of the condenser; * multiple evaporator LHP concept; * hydraulic connections 

for assembling/ disassembling of LHP components to facilitate large 

deployable radiator manufacturing and integration. 






C 02 

Q3 


Programme Ref.: ARTES8PP17.6 


DIPC > 500 



Page 196 


02.153.54 ELECTRIC TRHUSTER DEPLOYMENT AND ORIENTATION MECHANISM 

FOR ORBIT RAISING AND STATION KEEPING 

N9 

The purpose of this activity is to perform the prototyping for deployment and 

orientation mechanism, including the supporting arm for electric thrusters. 

Main preliminary requirements are the following: * Arm Length between 0.8 and 

1.6 m * Between 2 & 3 axis of motion * 1 for deployment * 2 for thruster 

pointing * Possibility to use deployment axis for pointing to reduce total 

number of motion axis * Orbital life duration: 15 years. 






C 02 

Q3 


Programme Ref.: ARTES 8 PP 16.1 

Status: 

02.153.55 HIGH TEMPERATURE HEAT PIPES 

DAC 200-500 

N9 

ESTEC 

The purpose of this activity is to perform the pre-development in order to 

qualify later on a European High temperature Constant Conductance Heat Pipe. 

The present CCHP with ammonia as working fluid are able to work properly 

under 90 deg C. For controlling directly high temperature units above 100 deg 

C, CCHP able to work in this temperature range are necessary. Main 

requirements are the following: * Working temperature range: 0 deg C ; 150 

deg C * Non operating temperature as low as - 40 deg C * Heat transport 

capability: 100 Wm (objective up to 200 Wm) * CCHP orbital life duration: 15 

years * Background: Controlling high temperature units directly with high 

temperature CCHP will allow significant mass saving (around -20% of radiative 

surface is foreseen). Present trend is to increase the operational 

temperature of dissipative units and consequently the working temperature 

range of heat pipe networks. Presently with units qualified at +85 deg C, 

CCHP are working at their limit temperature range. Increasing the qualified 

temperature above 100 deg C induce the necessity to have qualified high 

temperature CCHP, able to work in the range 0 deg C; 150 deg C. The potential 

uses for this CCHP are for thermal control of TWT and OMUX. 






C 02 

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Page 197 


02.153.56 HIGH CAPACITY HEAT PIPES 

N9 

ESTEC 

The purpose of this activity is to develop and qualify a European High 

performance Constant Conductance Heat Pipe. The present CCHP currently used 

are limited to diameter 22 mm and an associated capacity of 300 Wm. For the 

new satellite, high performance heat pipes with a capacity above 500 Wm at 70 

deg C with limited mass increase are necessary. Main requirements are the 

following: * Working temperature range: -40 deg C; +80 deg C * Heat transport 

capability: from 500 Wm to 700 Wm * Mass: around 500 g/m * Flange/vapour heat 

transfer coefficient: > 3000 W/m2/K. As far as heatpipe testing is concerned, 

in addition to the classical heatpipe qualification program, the heatpipe 

reflux mode shall be characterized. 






C 02 

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DAC 200-500 



Page 198 


02.153.58 HIGH THROUGHPUT PROCESSOR FOR FUTURE BENT-PIPE 

BROADBAND NETWORKS 

N10 

ESTEC 

The present activity aims at the detailed architectural study for a high 

throughput processor for the Next Generation broadband networks. Example of 

reference satellite system can offer a capacity up to 50 Gbps, support a 

larger number of narrower Ka-band user beams (up to 200 beams) and require 

few high-throughput (Q-band) gateways in site diversity configuration to 

reduce terrestrial segment cost and deployment time. Bent-pipe architectures 

for on board processors -non regenerative -non-on-board switching, seem the 

most attractive ones for medium term developments as many operators are still 

reluctant to directly adopt a full regenerative on board processing solution. 

This activity will start with an overall concept assessment in the context of 

a bent-pipe Next Generation Broadband Satellite Access networks. The first 

step shall be to investigate and select the most suitable digital processing 

algorithms and architectures. Some more specific dimensioning inputs for the 

proposed processor shall be derived from parallel market and system 

assessment activities already in ARTES 1 plan. A thorough simulation analysis 

of competitive algorithms and architectures shall be conducted with the aim 

to assess the maximum performance achievable with the state of the art 

technology, identifying critical technological issues that can impair the 

feasibility or performance of the proposed processor architecture. These 

critical issues shall also be addressed in detail through specific 

investigations. The activity shall carefully analyse the technology maturity, 

since it is clearly the winning element to achieve a real breakthrough in 

next generation payloads. Finally, the processor finalized target 

performances shall constitute input for a possible follow-up prototyping 

activity. 



PROGRAMME DEVELOPMENT OFFICE / APP-TP 

Responsible: MR ELIA 


C 02 

Q4 


GR 



DIPC > 500 



Page 199 


02.153.59 ULTRA-FAST ON-BOARD PROCESSOR FOR MESHED PACKET 

NETWORKS 

N10 

ESTEC 

The present activity aims at investigating a new ultra fast processor concept 

that handles only packet headers and switch transparently (without 

regeneration) packet payloads. Such a processor provides: * Reduction of the 

on board complexity due to the drastic reduction of on board modems (only 

needed for the headers) with obvious benefits for mission efficiency and 

reliability; * Increase of the system throughput; * Flexibility for air 

interface selection (no processing is involved in packet payloads) and the 

coexistence of several protocols within the same satellite network (e.g. ATM, 

IP) and support of future protocol evolutions. Furthermore, the use of 

standardised packet headers (label switching concept) necessitates only basic 

packet switching functions to be implemented on-board whereas more complex 

functions are shifted towards the edges of the network on-ground (MPLS type 

of architecture). The proposed activity aims at a detailed architecture 

definition and design of such an ultra fast processor (targeting throughput 

in the order of 100 Gbps) for broadband meshed packet networks. Some more 

specific dimensioning inputs for the proposed processor shall be derived from 

parallel market and system assessment activities already in ARTES 1 plan. The 

study shall start with an overall concept assessment against suitable 

satellite meshed packet network scenarios and the definition of suitable 

processor architectures. Detailed network and system dimensioning shall be 

provided. Thereafter, the most suitable digital processing algorithms and 

architectures shall be investigated. The overall performance of the selected 

architectures for the processor shall be assessed through detailed simulation 

analysis. Critical technological issues that may impair the feasibility or 

performance of the proposed processor shall be addressed through specific 

investigations. The finalized processor target performances shall constitute 

inputs for a possible follow-up prototyping activity. 






C 02 

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GR 



DIPC > 500 



Page 200 


02.153.62 PROTOCOLS & SIGNALLING FOR ADAPTIVE FADE MEASUREMENT 

TECHNIQUES (FMT) IN DVB-RCS MULTI-BEAM SYSTEMS 

Multimedia multi-beam systems operating at high frequency bands (Ka and 

above) need to counteract atmosphere and propagation effects in order to 

avoid system over-sizing and consequently wasting of resources. The use of 

adaptive coding is envisaged as a powerful tool to optimise system 

performance under time variant conditions; its implementation requires the 

estimation of fading and interference level by the opposite side of the link 

in order to adapt the physical layer parameters. This activity aims at the 

study of adaptive coding techniques in tandem to power control for a 

multi-beam satellite system and in particular investigates the possibilities 

of the DVB-RCS air interface specification to support the necessary 

adaptability. Three system scenarios shall be investigated: - transparent 

system in a star configuration; - transparent system in a multistar 

configuration; - regenerative system. The expected output is the definition 

of modifications to the current DVB-RCS standard (frame, protocols and 

signalling) required to support adaptive coding. Furthermore system level 

advantages and transmitter/ receiver impacts shall be studied; capability to 

estimate and track typical fading variations shall be demonstrated by 

analysis and simulation. Inputs to standardisation shall be provided. 

ESTEC 






C 02 

Q2 


GR 

Programme Ref.: ARTES 1 A2.23 


NO 200-500 



Page 201 


02.153.64 LIGHT-WEIGHT DEPLOYABLE RADIATOR STRUCTURE 

N16 

ESTEC 

The purpose of this activity is to develop, design, test and qualify a light 

and cheap deployable radiator panel structure based on carbone fiber 

technology. This pre- development shall be split in two phases. Phase 1: 

Competitivity evaluation of carbon fibre design for DPR panel - Preliminary 

carbon fibre design for DPR able to meet mechanical and thermal performance 

requirements. Comparison with classical optimised aluminium design with 

respect to mass, complexity and risks; - Non- recurring and recurring costs 

evaluation for the carbon fibre design. Comparison with classical optimised 

aluminium design; - Trade off to be performed with the Primes between carbon 

fibre design and classical aluminium design. The main criteria will be: Cost 

(launch cost, recurring and non recurring manufacturing cost) and Risks. 

Phase 2: Carbon fibre design development: - Optimising heat transfer 

properties of radiator structure: Tailoring of heat paths in panel with ply 

positioning, lay- up, material choice, fibre orientation, fluid loop piping 

layout; - Integration of thermal hardware (4 heat transfer loops and OSR) 

into the structure (thermo elastic aspects); - Mass, Manufacturing and 

process cost optimisation; - Design, manufacturing and testing of lightweight 

and high accuracy CFRP fixation elements with new technologies, for 

mechanisms, hinges and hold down points; - Manufacturing test coupons for 

concept trade- offs; - Structure and Thermal test program; - Manufacturing 

one semi-size representative pane. The main requirements on the deployable 

radiator structure design are: - Double side radiator panel (5m2 size); - 

Mass < 3.5 Kg/ m2 (TBC) excluding hinges and hold-down points but including 

loop piping, and thermal HW (OSR); - Thermal efficiency >50 W/ m2K (TBC) 

between loop piping and mean radiator external surface temperatures. 



LARGE PLATFORM MISSION OFFICE / APP-TL 



C 02 

Q3 




DAC > 500 



Page 202 


02.153.65 TRIMMING MECHANISM USED IN COMBINATION WITH RF SENSING 

N16 

The purpose of this activity is to design and develop a light 2 axes trimming 

mechanism for antenna fine pointing. This mechanism shall be able to be 

operated in close loop with RF sensing. Phase 1 activity aims to trade 

different solutions, select one and issue a validation test plan; Phase 2 

activity is related to validation test on a bread board mecanism including 

confidence life test. Main technical requirements are the following: - Mass < 

1Kg; - Volume envelope < 0.5 dm3; - Angular step of 0.01degree in two 

directions; - Actuation frequency > 1Hz; - Life time operation in orbit 15 

years. 






C 02 

Q3 




02.153.68 FLEXIBLE WAVE GUIDES FOR DEPLOYABLE FEEDS ON LARGE 

PLATFORMS 

DAC > 500 

N12 

ESTEC 






C 02 

Q3 


Programme Ref.: ARTES-8 PP 4.1 


NO 100-200 



Page 203 


02.153.69 HIGH DEFINITION OF COMMUNICATION SERVICES FOR A 

SATELLITE BASED AIR/GROUND COMMUNICATION SYSTEM 

N12 

ESTEC 

The Aeronautical Mobile Communication Infrastructure used by the Air Traffic 

Services (ATS) is currently mainly based on systems operating inside the VHF 

band (118-137 MHz).Alternative mobile communication systems are currently 

under consideration for introduction in the Mobile Communication 

Infrastructure, thus complementing the current systems. Among the promising 

systems, the Satellite-based technologies are considered promising, due to 

their global nature as well as their adaptation to specific airspace (e.g. 

low density/oceanic airspace, upper airspace) and to specific services (e.g. 

ground-to-aircraft broadcast). Before undertaking system design phases, the 

high-level service requirements to be supported need first to be established, 

discussed and then agreed within the Civil Aviation community. Therefore, the 

work proposed for this study will aim at establishing the high-level service 

requirements for a satellite-based communication system supporting 

safety-of-life related communication known as Air Traffic Services (ATS) and 

(Airline Operational Communication (AOC) on a worldwide basis. 






C 02 

Q3 


GR 

Programme Ref.: ARTES 1 A 2.31 

Status: 

NO 200-500 



Page 204 


02.153.70 UNIFIED TERRESTRIAL AND SATELLITE NETWORK MANAGEMENT 

SYSTEMS 

N12 

ESTEC 

To address new market segments, satellites become an integrated element of 

full telecommunications multi-service and multi-standard platforms. To 

accelerate the adoption of satellite access networks within telecommunication 

global networks, network management interfaces between telecommunications and 

satellite operators would need to be simplified and standardised. Currently, 

network management issues are the cause of various objections raised against 

the introduction of a satellite platform in a global network (i.e. 

Public/private addresses issue, quality of service and billing issues, CPE 

installation and management issues). In order to support a smooth 

integration, it is necessary to define how the satellite platform could be 

"plugged-in" as access network from the perspective of the telecommunications 

operator as well as of the satellite operator.The current activity shall 

review the problems caused by the introduction of a satellite platform within 

a business network (Internet/Intranet/Extranet) from the network management 

point of view. It shall provide recommendations for telecommunications and 

satellite operators for establishing standard interfaces that would help 

support the integration of satellite access networks in global networks. 






C 02 

Q3 


GR 

Programme Ref.: ARTES-1 A 1.11 

Status: 

NO 200-500 



Page 205 


02.153.71 RADIO ACCESS RE-CONFIGURABILITY FOR MULTI-STANDARD 

TERMINALS 

N12 

ESTEC 

Next generation of networks convergence towards an IP-based core network 

whilst offering ubiquitous and seamless access between 2G, 3G, broadband and 

satellite and/or terrestrial broadcast access schemes. In this ’composite 

radio environment’ where several highly standardised legacy radio transport 

schemes exist, one inherent goal is to develop re-configurable terminals to 

enable interworking and delivering of diverse applications and services using 

the most appropriate radio access scheme(s).Terminals re-configurability is 

based upon the pervasive use of software re-definition to implement 

updating/patching of any transport/network element and all services and 

applications running on the same hardware platform. It also permits the 

phased introduction of enhanced features of new generation systems such from 

second to third to fourth generation.The present study activity aims to 

investigate the applicability of re-configurable and multi-standard terminals 

for example in the area of satellite interactive networks e.g. using DVB-RCS 

multi-profile terminals and/or other advanced satellite terminals, in the 

area of integrated terrestrial satellite networks e.g. DVB-RCS and cable 

terminals. 






C 02 

Q3 


GR 


Status: 

NO 200-500 



Page 206 


02.153.72 COOLED LOW NOISE AMPLIFIER IMPLEMENTATION ON LARGE 

PLATFORMS 

N14 

The objective of this study is to analyse the impacts on large platform 

configuration of the implementation of cooled LNA (from 273 K down to more 

than 220 K) and to derive the associated requirements for the platform 

thermal control.The activity will be carried out in two parts.The first part 

of the study is devoted to identify the short term and long term requirements 

for LNA operating temperatures including the on spot beam /one feed system 

configuration and the focal array fed reflector mono-polarisation and 

dual-polarisation one and then to derive the main inputs for the analysis 

including the environmental conditions induced by Solar array, deployable 

radiators, reflectors etc..In the second part the preliminary definition of 

the thermal control solutions and their implementation feasibility will be 

assessed and traded. Output of the activity will be: - LNA thermal control 

interface requirements including environmental conditions; - Preliminary 

design of the thermal bus from LNA to radiator ( fluid loops/heat pipes) and 

of the radiator; - Recommendation and technical requirements for the 

specific thermal control needed; - Synthesis of the impact on large platform 

configurations. 






C 02 

Q3 


Programme Ref.: ARTES-8 PP 17.7 


02.153.73 LARGE KU-BAND DUAL POLARISED MULTI-BEAM/-CONTOURED 

BEAM ANTENNA FOR FREQUENCY RE-USE 

NO 100-200 

N14 

ESTEC 

Most current Ku-band commercial satellites are using single contoured beam 

antennas derived from shaped reflector systems requiring one antenna per 

beam. To provide multiple contoured beam coverage with frequency re-use 

between closely spaced zones it is interesting to re-visit multi-feed 

contoured beam antennas feeding large aperture reflectors (in the five metre 

class). The activity will comprise the design, both electrical and 

thermo-mechanical, of the total antenna sub-system and a detailed design, 

manufacturing and testing of the feed system qualification model. Key issues 

are likely to be in the antenna architecture and in the total feed system 

accommodation as well as the beamforming network, power handling and thermal 

control. 






C 02 

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DIPC 200-500 



Page 207 


02.153.75 LOW COST INSTALLATION OF SATELLITE INTERACTIVE 

TERMINALS 

N18 

ESTEC 

The main driver for the take up of satellite interactive services is the 

development of low cost and consumer-friendly satellite-return system. Low 

costs solutions lead to the reduction of the services’ overall ’cost of 

ownership’ that takes into account both service investment costs and 

operational costs. Lowering the ’cost of ownership’ can be performed, mainly 

by lowering the following cost contributions: • Terminal cost; • Bandwidth 

per user cost; • Network operations costs including the terminals’ 

installation costs. The present activity aims at investigating in particular 

technical solutions for reducing substantially the installation costs of 

Satellite Interactive Terminals (SITs). Today SIT installation is performed 

by professional installers, as for VSATs, resulting prohibitively expensive 

either for consumers or prosumers. The study will investigate and analyse 

amongst others: commercial requirements for the low installation costs both 

for consumer and prosumer market segments, scenarios for manual and automatic 

antenna pointing processes, enhanced feed to support multi-output Out Door 

Units (ODU) and/or the presence of two receivers using the same ODU, and/or 

receivers in communal housing. 






C 02 

Q3 


GR 


Status: 

NO 200-500 



Page 208 


02.153.76 PREPARATION FOR IPV6 IN SATELLITE COMMUNICATIONS 

N18 

The introduction of IPv6 (Internet Protocol Version 6) is however foreseen in 

the upcoming five years and satellite communications will need to keep 

abreast with developments in the terrestrial and 3G worlds concerning this 

new protocol. In the satellite communications world only a minimal number of 

activities are undertaken that prepare for the transition from IPv4 to IPv6, 

currently no discussion is on-going on its merits and drawbacks, or 

recommendation present for activities for satellite specific prototyping. The 

aim of the proposed activity is to provide an overview and recommendations 

for the introduction of IPv6 in satellite communications in the broadest 

sense: the activity shall address the efforts and costs necessary for the 

transition, the interfaces with the terrestrial world, propose transition 

scenarios for access, mesh, broadcast and trunking scenarios, include IPv6 

satellite specific Mutlimedia Home Platform (MHP) developments in combination 

with home networking, discuss changes in the access layers such as DVB-S/RCS. 



COMMUNICATION SERVICES DIVISION / APP-TS 



C 02 

Q3 


GR 

Programme Ref.: ARTES-1 D 1.1 

Status: 

02.153.77 STANDARDISATION SUPPORT OF ENHANCED IETF IP 

ENCAPSULATION TECHNIQUES FOR DVB-S 

NO 200-500 

N18 

ESTEC 

The Multi Protocol Encapsulation (MPE) protocol provides a standard to 

transport Internet Protocol (IP) traffic over satellite links. Thanks to the 

rapid acceptance of this standard, equipment prices have been falling. 

Although in the short term MPE will be used there are some limitations 

related to lack of support of emerging protocols as well as efficiency. The 

current standards for IP over DVB encapsulation such as Multi Protocol 

Encapsulation (MPE) are not optimized for emerging protocols such as IPv6 

(Internet Protocol Version 6) and Multi Protocol Label Switching (MPLS). The 

aim of the proposed activity is a study of emerging alternative protocol for 

Multi-Protocol Encapsulation to support the further definition of the 

Internet-Drafts, support further work on signaling and address resolution 

issues, and demonstrate proof-of-concept implementations and their cross 

interoperability for DVB-S Gateways and receivers, in a similar fashion as 

ETSI Bake-off actions for SIP or IPv6. 



COMMUNICATION SERVICES DIVISION / APP-TS 



C 02 

Q3 


GR 

Programme Ref.: ARTES-1 D 1.2 

Status: 

NO 200-500 



Page 209 


02.153.78 TELECOMMUNICATIONS DEPARTMENT WEB SITE SUPPORT 

N21 

ESTEC 

In order to carry out the various tasks defined in its communication plan, 

ESA Telecom is requesting qualified support to manage its dedicated Web site. 

Experience has shown that such support is indispensable to an efficient 

management of the diverse activities. Whereas ESA’s promotional programmes 

aimed at the general public tend not to require an active response, ESA 

Telecom does require a direct response from its target group to foster their 

active participation in the ARTES programme. Hence the department has two 

distinct but complementary needs: a) communication with the general public, 

which is shared with other ESA departments, to promote the value of the 

department’s work and use highlights of broad interest to illustrate the 

scope of its programmes. This activity is co-ordinated and carried out with 

the Communications (PR) department at ESA headquarters. b) two-way 

information exchange with ESA Telecom’s specific industrial and business 

partners. Activities under this heading are carried out within the Telecom 

department as they form part of the day-to-day operation of the programmes. 

These activities are designed to pursue two main objectives: - to encourage 

companies to take part in ESA Telecom programmes which can be seen as 

’participant acquisition’; - to provide access to a set of tools (forms, 

templates, documentation) that facilitates the interaction between ESA and 

the User community, as well as the execution of the daily project work. The 

activity described in this Statement of Work consists of providing technical 

and operational support to the Telecom Web site, including the associated 

content development under the supervision of the ESA Telecom Communications 

Officer. The present activity is launched to provide such support for two 

years. 






C 02 

Q4 


GR 



NO 200-500 



Page 210 


02.153.79 DEVELOPMENT OF GE-BASED SUBSTRATES ENABLING 

HIGH-VOLTAGE INTEGRATED MULTIJUNCTION MODULES 

N24 

ESTEC 

With the increasing power demand for high power telecom spacecraft (doubling 

every five years), there is a need to develop technology that will allow for 

high voltage power systems. This will reduce the current and allow for less 

system wiring mass. The higher voltage will also allow for the deletion of 

specific power processing hardware required to produce these voltages from 

lower levels. For example, with a 300-volt array, there is the possibility of 

deleting the power processing required for the plasma thrusters. This 

development will result in considerable mass saving that can facilitate a 

shared launch or significant increases in payload. However, at present for 

these elevated voltage levels, there remains the longstanding problem of 

arcing on the solar arrays that can result in permanent damage and 

degradation. There is thus a need to develop a module that will obviate and 

preclude arcing and even allow operation in a plasma environment such as in 

the situation of electric propulsion with a failed neutraliser. There is also 

the need to develop a technology that can accommodate the current cell 

manufacturing processes and also allow for lay down on existing structural 

hardware to reduce the overall cost of implementation for this efficiency 

improvement. Significant elements of the required technology are now 

available to make modules where the GaAs on Ge layer is very thin, enabling 

the MOVCD (Metal Organic Chemical Vapour Deposition) processing of standard 

multi-junction cells to be placed under a cover glass carrier with minimal 

external exposed interconnection. These technology elements are the result of 

many earlier related developments some of which are currently beginning to 

produce specific results. Integrating and improving on these technology 

elements in this development will result in a very lightweight module that is 

also robust in high voltage configurations. The study will: bond a Ge carrier 

on a temporary carrier, allow significant thinning of the Ge carrier to 

approximately 20 microns, demonstrate application of a GaAs layer that allows 

for normal MOVCD reactor processing for the multi-junction cells resulting in 

high power conversion efficiency, demonstrate integrated interconnections in 

the module, have a cover glass carrier installed allowing the removal of the 

reusable temporary carrier, demonstrate feasibility of the high voltage 

module from 50 volts up to 400 volts under worst case plasma conditions. A 

similar development process was performed in the successful introduction of 

Ge substrates a few years ago that has resulted in the European supply of 90 

per cent of the world wide solar cell GaAs substrates at the present time. 

These substrates support the application of multi-junction technology by many 

suppliers for efficient power conversion. This new approach for improved next 

generation substrates should allow Europe to maintain its substrate supplier 

role for some time to come as well as allow for significant performance 

improvements to the telecom spacecraft. This will be followed by a phase not 

part of this activity where substrates would be available for solar cell 

manufacturers to demonstrate their own specific multi-junction modules that 

would then be implemented in very efficient solar array systems. 



TELECOMMUNICATION MISSIONS & SYSTEMS DIVISION / APP-TM 

Responsible: 


C 02 

Q4 



YIPC 



Page 211 

Status: 



Page 212 


01.154.02 INITIAL GALILEO SYSTEM TEST BED (GSTB) GROUND SEGMENT 

DEVELOPMENT (V1) 

In order to reduce programme risks during the GalileoSat Definition Phase, a 

GALILEO System Test Bed (GSTB) has been defined as an integral part of the 

GALILEO Development and Validation Phase. The GSTB is subdivided in two main 

development steps, Version 1 (V1) and Version 2 (V2). GSTB V1: As part of V1, 

measurements from existing systems (GPS, GLONASS) are collected to verify 

GALILEO concepts for Orbit Determination & Time Synchronisation (OD&TS) and 

Integrity. During GSTB V1 development, collaboration with the International 

GPS Service (IGS) community and UTC Time Community is envisaged. Furthermore, 

interfaces with the EGNOS System Test Bed (ESTB) are foreseen. GSTB V1 is a 

self-contained step and it is not dependent upon the implementation of GSTB 

V2. GSTB V2: GSTB V2 will consist of an experimental GALILEO payload to be 

launched in 2003, up-grade of GSTB V1 Ground Segment including GALILEO 

receivers, up-graded processing algorithms operating in a real-time 

environment. This procurement addresses the development of GSTB V1 Ground 

Segment, together with twelve months operations and experimentation support. 

The procurement of the GSTB V2, including an Experimental GALILEO Payload, 

will be addressed by separate procurement actions at a later date, once the 

GSTB Space Segment baseline will have been consolidated. The GSTB V1 ground 

segment hardware/software to be developed, manufactured and tested shall 

consist of: • Experimental Orbitography and Synchronisation Stations (E-OSS) 

and Integrity Monitoring Stations (E-IMS); • Experimental Precision Timing 

Station (E-PTS); • Experimental Orbitography and Synchronisation Processing 

Facility (E-OSPF); • Experimental Navigation Control Facility (E-NCF); • 

Experimental Integrity Processing Facility (E-IPF). ESA will ensure tight 

coordination of the GSTB V1 Ground Segment development and experimentation 

plan with the overall GALILEO Development and Validation Phase, in particular 

the GALILEO Phase B2 Contract which is the subject of a separate procurement 

proposal. 

ESTEC 


NAVIGATION DEPARTMENT / APP-N 

GNSS-2 OFFICE / APP-NS 

Responsible: MR BENEDICTO RUIZ 

Budget Ref.: 100451 - Galileosat Development & Validation 

C 02 

Q2 



Status: 

YIPC > 500 



Page 213 


01.154.04 GALILEO MISSION CONSOLIDATION SUPPORT 

This procurement action addresses several urgent tasks aimed at supporting 

the consolidation of the GALILEO Mission. Objective is to finalise the 

GALILEO mission & system requirements prior to the start of Phase C/D. Close 

co-ordination between the GALILEO Phase B2 contract and these Mission 

consolidation activities will be ensured. In particular the work to be 

carried out here shall result in an accurate specification of required 

GALILEO services and interoperability with respect to other positioning and 

timing systems such as GPS and GLONASS, as well as the interface between 

GALILEO and other external systems such as UMTS. It shall include the 

establishment of a number of specialised working groups dealing with issues 

like time-frequency interface, geodetic reference system 

aspects,interoperability, etc., and also consolidate the issues related to 

provision of a Search & Rescue Service and other value-added services (like 

communications) within GALILEO, and contribute to the consolidation of the 

local component requirements, including standardisation. Moreover, this 

activity shall provide support to definition of the GALILEO signal in space 

for the various services through the organisation of task forces gathering 

major experts in the field and user groups. It will liase closely with the 

signal work carried out under the GALILEO Phase B2 study contract and will 

take into account the results of the international discussions (EU, USA and 

the Russian Federation) on the different frequency plans. While not 

exhaustive, a summary description of tasks is provided. The scope of these 

tasks has been closely co-ordinated with the EC. In particular, the EC 

intends to launch complementary Mission-related activities in 2001, under its 

5th Framework Programme. Bidders will be invited to submit proposals either 

for individual tasks or for a combination of tasks. This may result in a 

number of separate contracts to be placed. 

ESTEC 





Budget Ref.: 

C 02 

Q2 



Status: 

DAC > 500 



Page 214 


01.154.08 GALILEO MISSION CONTROL SYSTEM ASSESSMENT 

The Galileo System is a MEO constellation of 30 satellites in 3 orbital 

planes. The consistent operation of the complete constellation is fundamental 

for the achievable overall navigation performance. A powerful and efficient 

Mission Control System, adapted to the requirements of routinely operating 

such a satellite constellation with limited operator intervention is 

required. There are various platforms for Mission Control Systems available 

on the market based on European technology. However, none of them has 

demonstrated their capability to handle a constellation mission like Galileo 

with more than 30 satellites. Also ESA, in co-operation with European 

Industry, has developed a Mission Control System, which is successfully used 

for single missions (SCOS-2000) but its use in a constellation mission 

environment would require further evolution. This situation is perceived as a 

significant technological risk for the Galileo Programme. Therefore, 

feasibility studies, possibly with integrated demonstrations, of at least two 

European mission control platforms to handle a constellation like Galileo are 

planned under this activity. This will allow assessment of the real risks and 

efforts for such system for subsequent programme phases and eventually the 

initiation of appropriate risk mitigation actions. The assessment of 

feasibility shall be based on an initial analysis of the requirements of a 

Galileo Mission Control System and the definition of a possible Design, 

Development and Validation Plan respecting a design to cost approach. The 

outputs of this activity will be: - Feasibility Study Reports for a Galileo 

Mission Control System based on European Technology; - Demonstrations of the 

capability of existing/modified mission control platforms to handle a 

satellite constellation like Galileo; - Requirement Specifications for a 

Galileo Mission Control System; - Design, Development and Validation Plans 

for a Galileo Mission Control System including Development Schedules; - 

Price/Costs Targets and Design to Cost Approach for a Galileo Mission Control 

System. In view of the nature of the activity (the pre-development of 

satellite equipment) this procurement is proposed to be limited to 

competitive bids from non-primes including SMEs. Parallel contracts are 

proposed in order to obtain different competitive solutions provided 

acceptable offers are received. 

ESTEC 





Budget Ref.: 

C 02 

Q2 



Status: 

DAC 200-500 



Page 215 


01.154.10 SECURED TT&C, INTEGRITY AND TWTTF GROUND STATION 

EQUIPMENT 

The Galileo System is considered a strategic asset for Europe and the 

space-to ground interfaces need to be protected against intentional and 

unintentional interference. For that reason in the GalileoSat Programme, 

there is already an on-going development of a dual-mode TT&C on-board 

subsystem, which will implement all required space-to ground interfaces for 

telemetry and telecommand, two-way ranging, integrity up-links and two-way 

time transfer of the on-board time. To match the on-going pre-developments of 

the on-board TT&C subsystem and to support the end-to end validation of the 

secured space-to ground interfaces the pre-development to prototype level of 

TT&C, Integrity and Two-way Time Transfer base-band equipment for the Galileo 

Ground Segment is required. Such equipment will allow to explore the use of 

the secured TT&C and Integrity transmission modes, the two-way ranging and 

the two-way on-board time transfer foreseen for the Galileo TT&C on-board 

subsystem using spread spectrum techniques. The following units/equipment 

shall be developed to prototype standard: • Down-link Spread-Spectrum 

Demodulator; • Up-link Spread-Spectrum Modulator; • Spread-Spectrum- based 

Ranging and Two-way Time Transfer Equipment. Type of tender C(1) - activities 




ESTEC 





Budget Ref.: 100453 - Galileosat Definition 3 

C 02 

Q3 




DIPC > 500 



Page 216 


02.154.01 GALILEO INTEGRITY RELATED PRE-DEVELOPMENTS 

N10 

The provision of integrity-related services in Galileo, specifically for 

safety-of life applications, require high continuity, availability, accuracy 

of data products delivered to the navigation users. The objective of this 

activity is to mitigate the technological, performance and programme cost 

risks for the implementation of the infrastructures in Galileo providing such 

integrity-related data products. Therefore, studies and sub-sequent 

pre-developments in critical areas need to be initiated early enough to 

assess and control the risks and to make suitable technologies available in 

Europe in due time for the implementation of the Galileo. Areas to be 

addressed are the pre-developments of safety critical functions in the 

Galileo Ground Segments, e.g.: Prototyping of integrity-related algorithms; 

Prototyping of integrity data validation and selection mechanisms; 

Prototyping of integrity check functions; Prototyping of data transfer 

mechanisms. These pre-development activities shall also demonstrate the 

suitability of the chosen approach and selected technologies for 

safety-critical SW Engineering and shall identify issues with regard to 

certification of such systems in critical application areas. Cost drivers and 

performance sensitivities shall be identified and need to be considered in 

the technical trade-offs. The activity shall address as much as possible 

generic building blocks and common risk areas of Galileo integrity 

infrastructure. Prototypes developed under this activity could also be 

considered to be used in the context of the Galileo System Test Bed (GSTB). 

Expected Outputs: a) prototypes of critical SW functions like: 

integrity-related algorithms; check functions; data selection and data 

validation mechanisms; data transfer mechanisms; b) demonstration of 

suitability of chosen SW Engineering Approach and identification of 

certification aspects; c) identification of cost drivers and performance 

sensitivities. 





Budget Ref.: 100453 - Galileosat Definition 3 

C 02 

Q1 



Status: 

02.254.01 GALILEO GSTB-V2 AND IOV PHASE LAUNCH SERVICES 

DAC > 500 

N5 

ESTEC 





Budget Ref.: 

CR 02 

Q2 

Spec. Prov.: 


Status: 

YIPC > 500 



Page 217 


01.155.01 PHASE A OF OCEAN EARTH WATCH 

Phase A activities for the Ocean Earth Watch mission base on altimetry and 

visible-infrared optical capabilities. The proposed activity will be a study 

at phase A level of the complete mission architecture. The scope, logic and 

milestones are as established in the industrial standard ECSS-M-30. The study 

will cover the complete mission architecture. It will start from mission 

observation and data requirements derived from user service requirements. The 

mission observation and data requirements will be translated into system 

requirements. It will include a first step of analysis of system requirements 

and derivation of lower level requirements and opening of performance 

allocation budgets. Options will be identified for each element of the 

architecture and defined to the level needed for trade-off and selection of 

baseline. Trade-off criteria will be established. The baseline of the 

technical concept will be established. Satisfaction of user requirements will 

be a key criterion for trade-off, but also development aspects and cost. The 

first step will end with the preliminary concept review (PCR) at which the 

technical baseline will be agreed. In the second step after the PCR, the 

technical baseline concept will be defined in detail to the level required to 

analyse feasibility and establish performance and cost. Feasibility will 

include not only technical feasibility but also programmatic feasibility, 

mainly development time and cost. End-to-end mission performance models will 

be established and used to estimate mission performance and to scrutinise 

requirements, in particular major cost offender requirements. The second step 

will end with the preliminary requirement review (PRR) at which mission and 

system concepts must be matched. Following the PRR, a final third step is 

envisaged. During the third step the technical concept will be consolidated 

and a programmatic dossier will be established. The dossier will include 

development plans, including plans beyond the first launch, management and PA 

assumptions, work breakdown structure and costs. The third step will end with 

open final presentation and the acceptance of all deliverables. Two parallel 

contracts are foreseen. 

ESTEC 





Budget Ref.: 100783 - EOPP Extension 2; 100783 - EOPP 

C 02 

Q4 

Extension 2 




DIPC > 500 



Page 218 


01.155.05 BASIC RESEARCH IN SUPPORT OF A FUTURE EARTH RADIATION 

MISSION 

Radiation is the only means by which the Earth can exchange energy with its 

environment, i.e. deep space. While short-wave radiation is received from the 

sun the Earth is emitting in the long-wavelength part of the spectrum. The 

balance between short-wave in-coming and long-wave outgoing radiation is 

usually referred to as the Earth’s Radiation Budget (ERB). The accuracy with 

which the short-wave component of the ERB can be derived is very sensitive to 

the viewing geometry. While the solar incidence angle is important in both 

the short-wave and in the long-wave parts of the electromagnetic spectrum, in 

the short-wave the viewing angle of the observation is also of very high 

importance. This viewing angle dependency, also called the BRDF 

(bi-directional reflection distribution function), is only known 

approximately for most surfaces. Thus, if high accuracy ERB components are to 

be derived, a more refined description is mandatory. Mid-layer clouds 

specially mixed-phase (with both ice and water) are very poorly understood. 

The Agency conducted an extensive airborne campaign and ground-based campaign 

to measure mid-layer clouds (CLARE’98). The preliminary results from the 

campaign have shown that in mid-layer clouds, ice and water coexist but in 

spatially separated regions. These preliminary results have a very important 

impact on the modelling of clouds in numerical models and on the radiative 

role of clouds. The proposed activity will evaluate the range of 

applicability of the observations of CLARE’98 by developing improved 

retrieval algorithms of cloud characteristics, by extending the data analysed 

up to now and by improving the cloud microphysical modelling. Reflecting the 

above mentioned needs in support of a future Earth radiation mission the 

following items are proposed for study: - Study and characterisation of 

mid-layer clouds; - Improvement of angular dependence models (ADMs). 

ESTEC 



EARTH SCIENCES DIVISION / EOP-FS 

Responsible: MR READINGS 


C 02 

Q2 



Status: EX ITEM 01.1JP.04 

DIPC 200-500 



Page 219 


01.155.06 PREPARATION OF A FUTURE LAND SURFACE PROCESSES MISSION 

This study is intended to the advance of knowledge of land surfaces by the 

further exploitation of various Earth Observation techniques. It will be 

split into five different activities: 1.The use of long wavelength SAR for 

land applications - See action item 01.155.15 2.The use of signals of 

opportunity in SAR interferometry to retrieve bio- and geophysical parameters 

- See action item 02.155.03 3.The retrieval of atmospheric variables and the 

removal of atmospheric effects from hyperspectral campaign data. Various 

atmospheric correction schemes, designed for use with data from hyperspectral 

imagers,will be investigated by retrieving atmospheric variables such as 

water vapour abundance and aerosol characterisation (type and loading) from 

spectral observations - See action item 02.155.10 4.The integration of 

surface process models and radiative transfer schemes for terrestrial process 

investigations. The aim is improve the parameterisation of processes 

occurring at the interface between the biosphere/geosphere and the 

atmosphere. It will involve the integration of terrestrial process models, 

with radiative transfer schemes optimised to quantify land surface processes, 

and the formulation of "up-scaling" schemes so that hyperspectral, 

bi-directional remote sensing data can be used in global models. 5.The use of 

solar-induced natural fluorescence for the analysis of vegetation state and 

condition - See action 02.155.02 

ESTEC 




Responsible: MR HERLAND 


C 02 

Q2 



Status: EX ITEM 01.1JP.05 PARTLY INITIATED - SEE SUMMARY 

DIPC > 500 



Page 220 


01.155.07 SYNERGETIC DATA EXPLOITATION IN VIEW OF FUTURE OCEANIC 

MISSIONS 

The proposed activity will take maximum benefit of future and present 

missions for high-latitude ocean modelling through a study of the synergetic 

exploitation of the various observational data. This study shall seek 

assimilation approaches and strategies for an optimal exploitation of the 

various oceanic missions for improved high-latitude ocean-circulation 

modelling. Suitable data assimilation methodologies will be established for 

use of; ice thickness, ice drift, and SSS data. Numerical simulations will be 

performed in order to demonstrate improvements in model performance and to 

better define future observational requirements for studies of high-latitude 

climate variability. Similarly, future altimeter data together with an 

improved geoid will offer the potential to accurately characterise the broad 

topography and dynamical adjustments of the large terrestrial ice sheets. The 

goal is to investigate the synergies of nadir and off-nadir microwave 

backscatter and emission data for the purpose of demonstrating a snow 

accumulation retrieval capability (to a given accuracy) which could be 

exploited on a future mission. The study will exploit SMOS, GOCE and CryoSat 

data in conjunction with ERS-2 and SSM/I data for the purpose of isolating 

the contributions of roughness, layering and snow characteristics upon 

altimetric topographic profiles and accumulation estimates. This will enable 

identification of deficits and short-comings of various microwave frequencies 

and polarisations, leading to the identification of requirements for a future 

mission. Reflecting the above mentioned needs in view of future oceanic 

missions the following items are proposed for study: - Synergetic Use of 

Remote Sensing Data in Snow Accumulation and Ice Sheet Topographic Change 

Estimates - See 02.155.01 and - Synergetic Use of Remote Sensing Data in High 

Latitude Coupled, Ocean-Atmosphere Models Simulations. 

ESTEC 






C 02 

Q2 



Status: EX ITEM 01.1JP.06 PARTLY INITIATED - SEE SUMMARY 

DIPC 200-500 



Page 221 


01.155.08 SCIENTIFIC ASSESSMENT OF SPACEBORNE HIGH TEMPERATURE 

EVENT OBSERVING MISSION CONCEPTS (PREPARATION OF 

FUTURE ENVIRONMENTAL MISSIONS) 

The procurement shall analyse potential mission concept meeting scientific 

observation requirements for high temperature event monitoring and 

investigate the potential of a millimetre-wave limb sounder instrument in 

providing the requisite observations required to meet the scientific 

objectives of a potential atmospheric chemistry processes mission. The 

environment is increasingly threatened by pollution of the environment. 

Concern over this has lead to the consideration of various space-borne Earth 

Observation tools to detect and monitor high temperature events such as 

volcanic eruptions. This study is intended to investigate potential mission 

concepts satisfying the scientific requirements for these observations. It 

will address various possible configurations for a space-borne ’hot spot’ 

observing mission. Mission scenarios will be established in line with 

scientific observation requirements and investigated for feasibility and 

appropriateness. The goal of the study will be to establish a scientific 

mission concept to enable: - the detailed analysis and characterisation of 

high temperature events, - the monitoring of such events, - assessment of 

their impact on the environment. The key objectives of a future Earth 

Explorer Atmospheric Chemistry mission - climate/chemistry interactions, 

stratospheric/tropospheric exchange and upper tropospheric chemistry - 

require measurements of several trace gases through the upper troposphere and 

lower stratosphere with high vertical resolution and good global coverage. 

Millimetre-wave limb sounders are insensitive to clouds and can nowadays be 

equipped with large bandwidth receivers, as necessary for tropospheric 

observations. The agency is therefore developing the MASTER instrument as a 

core instrument for this mission. The airborne instrument MARSCHALS, being 

built under the Agency’s contract, will be a precursor of MASTER. It shall 

demonstrate MASTER’s ability to sound at least ozone and water vapour in the 

upper troposphere. This study comprises the data collected through a campaign 

using MARSCHALS. The study will consist of development of calibration and 

retrieval algorithms, complete data analysis and model-supported 

intercomparison with correlative data. Reflecting the above mentioned needs 

in view of future environmental missions the following items are proposed for 

study: - The scientific concept for a space-borne high temperature event 

observing mission; - The scientific analysis of limb sounding observations of 

the upper troposphere. 

ESTEC 






C 02 

Q2 



Status: EX ITEM 01.1JP.07 INITIATED 1-4367 

DIPC > 500 



Page 222 


01.155.09 OPERATIONAL ATMOSPHERIC CHEMISTRY MONITORING MISSIONS 

The proposed study will analyse the monitoring requirements as derived in 

ongoing GSP activities and in the actions of the V Framework Programme of the 

European Commission. Services and products will be defined. The results of 

research expected to be achieved with ENVISAT and other missions will be 

analysed. The needs for sensors will be identified. Mission profiles will be 

established. The international context in research and also monitoring, e.g. 

NPOESS, GCOM A, will be analysed. Scenarios will be identified and traded. 

Earth Watch mission concepts will be established, including characterisation 

of actors, services, products, sensors and systems and definition of the 

deployment strategy. 

ESTEC DIRECTORATE OF EARTH OBSERVATION PROGRAMMES - D/EOP 





C 02 

Q4 



Status: EX ITEM 01.1JP.08 ISSUED 1-4273 

01.155.10 DEFINITION OF SCENARIOS AND ROADMAP FOR OPERATIONAL 

OCEANOGRAPHY 

DIPC 200-500 

ESTEC 

The proposed activity will analyse the actors and their roles in operational 

oceanography. It will continue with the analysis of the EO based services and 

the associated products. It will analyse the sensors for the suitability, 

uniqueness and availability. It will investigate the status of modelling and 

prediction capabilities following the new research missions. Considering the 

international context, in particular the NPOESS, and the European context, 

scenarios for operational implementation of oceanography missions will be 

identified and traded. Candidate scenarios: mission concepts, systems, 

services, and deployment strategies will be developed in detail. Earth Watch 

mission concepts will be established. 






C 02 

Q2 



Status: EX ITEM 01.1JP.09 

DIPC 200-500 



Page 223 


01.155.13 STUDY OF TECHNIQUES AND SENSORS FOR OBSERVATION OF 

EXTREME WEATHER EVENTS 

Extreme weather events such as hurricanes and typhoons cause loss of lives 

and large damages every year around the World. Accurate predictions of their 

devastating strength and courses are most often very difficult tasks for 

meteorological services due to lack of timely and quantitatively reliable 

observations. The state of the art, operational numerical weather prediction 

models generally provide poor predictions of such events as no accurate 

observations can be assimilated into the models. Manual interventions of 

experienced meteorologists are often required in order to correct model 

behaviours. All existing and planned satellite sensors fail to provide 

quantitative observations within hurricanes: atmospheric sounders in 

millimeterwave and infrared spectral regions are not able to deliver 

information from inside hurricanes due to strong signal attenuation; wind 

measurement capabilities of scatterometers and microwave radiometers 

generally saturate above wind speed of approximately 30 m/s. Satellite-based 

observations are particularly needed as hurricanes and typhoons are always 

born and grow over ocean where in-situ measurements are rare or almost 

non-existent. New remote sensing techniques and sensor concepts need to be 

developed in order to enable quantitative measurements within hurricanes. In 

this study, observation requirements will be established and sensor concepts 

for enabling such observations in microwave region will be developed (eg 

radiometers, scatterometers, altimeters). Technological limits associated 

with those sensors will be analysed and their designs will be established at 

a preliminary level. A development plan will be established and critical 

technology areas will be identified which would require long term 

developments. 





Budget Ref.: 100783 - EOPP Extension 2 

C 02 

Q2 



Status: 

01.155.17 ALTERNATIVE ARCHITECTURES FOR FUTURE OPERATIONAL LEO 

METEOROLOGICAL SYSTEMS 

DAC 200-500 

ESTEC 






C 02 

Q2 



Status: 

DIPC > 500 



Page 224 


01.155.23 REFLECTOR BASED MULTIPLE BEAM SAR ANTENNA 

A study has been carried out in the context of risk management in which a 

reflector antenna-based Synthetic Aperture Radar (SAR) concept was developed 

as a low cost solution for future missions. Depending on a specific 

instrument design and the frequency band of operation, generation of a number 

of shaped beams with well-defined characteristics is needed for the 

realisation of a reflector antenna-based SAR instrument. The antenna is, as a 

spatial filter with its performance, a major element for the overall SAR 

instrument performance and therefore it has been considered as important for 

detailed investigation. The technology of agile, multiple beam, 

deployable/unfurlable reflector antennas has been advanced mainly in the area 

of satellite telecommunications and it is the aim of this activity to exploit 

such developments in Earth observation. The activity considered here is to 

study, design and analyse a reflector-based SAR antenna with emphasis on its 

elements like the low loss cluster feed-network for multi-beam operation and 

the deployable/unfurlable reflector. Breadboarding activities are 

anticipated, mainly for the feed-network arrangement. The first phase of the 

activity concerns a revisit of the reflector based SAR system with the 

objective to consolidate detailed antenna requirements. This phase includes a 

detailed design, analysis and overall instrument performance analysis based 

on the proper antenna design and analysis of the focal plane array and its 

feed network. It is then followed by an overall performance analysis. 

Feasible solutions for the reflector and for the RF front-end should be 

analysed and recommendations shall be given in order to proceed with a second 

phase. The second phase includes a breadboarding activity, covering for 

instance the design, manufacturing and testing of a multi-beam feed array 

network, supported where applicable with the necessary verifications and 

modelling. The activity is concluded with an overall antenna performance 

analysis and requirement verification of the total antenna subsystem and with 

a performance analysis of the SAR instrument. 

ESTEC 





Budget Ref.: 100783 - EOPP Extension 2; 100061 - Techno 

C 02 

Q2 

Res/Core Activities 



Status: ON HOLD 

YIPC > 500 



Page 225 


01.155.25 DEFINITION OF A KA-BAND DOWN-LINK SYSTEM FOR EARTH 

OBSERVATION MISSIONS 

The capability of the existing X-band systems is at the limit for present 

missions and will be insufficient in future Earth observation missions. The 

current exploitation of the X-band is already at the limit of what is 

acceptable from two points of view, the technical one (e.g., trade-off 

between the use of higher order modulation schemes providing higher spectral 

efficiency and bit error rate) and the regulatory one (bandwidth occupation). 

The most convenient solution to these problems is to employ down-links at 

higher frequencies, in particular in the Ka-band where a very substantial 

allocation of 1.5 GHz exists for Earth observation missions. This is four 

times the available bandwidth at X-band and will satisfy the needs of all 

missions planned to be realised in the current decade. The proposed activity 

will consider all aspects of the utilisation of Ka-band down-link and 

include: - definition of system requirements, covering both space and ground 

segments, on the basis of on-going, planned and expected Earth observation 

mission developments; - analysis of requirements and achievable performance, 

accounting for e.g. impact of atmospheric and rain losses, technology 

state-of-the-art, etc. and for system constraints (e.g. redundancy, 

interfaces to payload data handling); - subsystem analysis and architectural 

design for modulator, transmitter, power conditioning and antenna; - detailed 

design of critical subsystems; - definition of enabling technologies; - 

definition of detailed development plan and cost estimation. The activity is 

expected to take maximum advantage of existing K- and Ka-band technologies 

and equipment for broadband satellite communications. Because of the high 

level of expertise available at several industries in Europe and of the 

anticipated high interest, two parallel studies will be carried out, so 

providing the possibility to select the most attractive design for 

continuation of the development in future activities. Type of tender C(2) - 




programmes". 

ESTEC 






C 02 

Q2 



Status: ON HOLD 

DAC > 500 



Page 226 


02.155.07 PERFORMANCE ESTIMATION OF FTS FOR WATER VAPOUR AND 

TEMPERATURE RETRIEVAL 






C 02 

Q4 




02.155.09 IMPROVEMENT OF ANGULAR DEPENDENCE MODELS 

NO 50-100 

ESTEC 






C 02 

Q4 




DIPC 100-200 



Page 227 


02.155.14 OBSERVATION TECHNIQUE AND SENSOR CONCEPT FOR POST-MSG 

MISSIONS 

N10 

ESTEC 

A work plan has been established by ESA and EUMETSAT. Concerning ESA 

activities, the plan emphasises the need to conduct studies on potential 

observation techniques and sensor concepts, covering: 1) Cloud/surface 

imaging (visible and infrared radiometers); 2) Aerosols observation 

(UV-VIS-SWIR); 3) Atmospheric sounders (interferometers / spectrometers); 4) 

Surface pressure and cloud top height by differential absorption (e.g. oxygen 

A-band spectrometer); 5) Lightning monitoring (fast imager); 6) All weather 

imaging and sounding (microwave imagers and sounders); 7) Atmospheric 

composition and chemistry monitoring (e.g. UV-VNIR spectrometers). The 

studies subject of this procurement proposal are part of the ESA contribution 

to the plan. The objective of the proposed activity is the analysis of the 

above mentioned techniques and the definition of the sensors. They will cover 

items 1 to 5. Items 6 and 7 are covered by separate actions. Contents: A 

user-driven, top-down approach will be followed. The mission objectives and 

requirements are being identified in scientific studies carried out by 

EUMETSAT with ESA support. The results of these studies will be the starting 

point. In the proposed activity the instruments and system requirements will 

be derived. Instrument concepts will be subsequently established encompassing 

configuration, functional, electrical, thermo-mechanical and data 

architecture, system, subsystems and assemblies. For each type of sensor 

analysis and design activities will be carried on candidate concepts. The 

required technologies will be identified and characterised in terms of 

functionality and overall performance. Instrument performance models will be 

established to assess the impact of instrument design features and of 

technology performance on the mission return. After trade-off, baseline 

concepts will be identified for each type of sensor. The baseline concepts 

will be subject to detailed analysis and design activities including detailed 

analysis and characterisation of the required technologies. The development 

approach will be established for the selected baseline, including detailed 

plan for the development of the enabling technologies. Cost estimates will be 

provided. Two parallel contracts will be placed. 





Budget Ref.: 100783 - EOPP Extension 2; 100772 - Earth Watch 

C 02 

Q4 

Definition 




DIPC 200-500 



Page 228 


02.155.15 PHASE A SYSTEM STUDIES FOR THE ACE+ CANDIDATE EARTH 

EXPLORER OPPORTUNITY MISSION 

N10 

ESTEC 

The ACE+ (Atmosphere and Climate Explorer) mission is devoted to the 

establishment of climatologies of temperature and humidity with high accuracy 

and vertical resolution for a variety of studies. This is achieved by 

sounding the atmosphere with occultation techniques between the satellites in 

low Earth orbit (LEO) and the GNSS satellites (LEO - GNSS occultation) and 

between satellites in different LEO orbits (LEO - LEO occultation). In the 

Lead Investigators’ (LI) proposal the space segment consists of four 

micro-satellites in two orbits of 90 degree inclination and separated 180 

degree in longitude. Two satellites are in one orbit at 850 km altitude and 

two are at 650 km altitude. Each satellite carries a GNSS receiver for 

atmospheric sounding and, depending on the orbit, the transmitter or receiver 

section of the instrument for exploitation of LEO - LEO occultation. The 

ground segment consists of a command and data acquisition element (CDAE), the 

mission operations and satellite control element (MSCE) and the processing 

and archiving element (PAE). In the LI’s proposal parts of these elements are 

implemented with national facilities. The Phase A system study will address 

all elements of the mission architecture, space segment and ground segment, 

platform and payload, operations and exploitation. Parallel contracts will be 

placed. 





Budget Ref.: 100631 - EO Preparatory Activities; 100631 - EO 

C 02 

Q4 

Preparatory Activities 




DIPC > 500 



Page 229 


02.155.16 PHASE A SYSTEM STUDIES FOR THE EGPM CANDIDATE EARTH 


N10 

ESTEC 

The EGPM (European contribution to the Global Precipitation Mission) mission 

is intended to improve the rainfall estimation accuracy and the detection of 

light rain and snowfall for a wide range of scientific studies and 

applications. It is conceived as the European contribution to the Global 

Precipitation Mission (GPM) promoted by NASA and NASDA that includes a mother 

spacecraft with a passive microwave radiometer and a two frequency (Ku- and 

Ka- band) rain radar, and several drone satellites with passive microwave 

radiometers. The European contribution proposed in EGPM meets the objectives 

of the GPM and the particular observation requirements of European / Canadian 

latitudes. This leads to a microwave radiometer with an additional high 

frequency channel as compared with the standard TMI-like assumed for GPM, and 

the possibility to include a Ka-band radar. The ground segment consists of a 

command and data acquisition element (CDAE), the mission operations and 

satellite control element (MSCE) and the processing and archiving element 

(PAE). A specific feature of this mission is the need for the ground segment 

to be considered in the context of the GPM and the particular requirements of 

near real time delivery (2 hours) for all data and for 15 minutes delivery 

time for data over Europe. The Phase A system study will address all elements 

of the mission architecture, space segment and ground segment, platform and 

payload, operations and exploitation. Two parallel contracts will be awarded. 





Budget Ref.: 100631 - EO Preparatory Activities; 100631 - EO 

C 02 

Q4 

Preparatory Activities 




DIPC > 500 



Page 230 


02.155.17 PHASE A SYSTEM STUDIES FOR THE SWARM CANDIDATE EARTH 


N10 

ESTEC 

The SWARM mission is intended to study the dynamics of the Earth’s magnetic 

field and its interactions with the Earth system. In the proposal of the Lead 

Investigator (LI), the space segment consists of four small satellites 

carrying on a boom a scalar magnetometer and, mounted on an optical bench, a 

vector magnetometer and a star sensor package. The payload also includes a 

GNSS receiver, an accelerometer and an electric field instrument, the latter 

composed of an ion drift meter, a retarding potential analyser and a Langmuir 

probe. Two satellites are in a 550 km altitude 86O inclination orbit while 

for the other pair the orbit parameters are 450 km altitude, 84.6O 

inclination. The LI’s proposal outlines the implementation of the ground 

segment elements, i.e. the command and data acquisition element (CDAE), the 

mission operations and satellite control element (MSCE) and the processing 

and archiving element (PAE), in national facilities developed for the CHAMP 

and OERSTED projects. The Phase A system study will address all elements of 

the mission architecture, space segment and ground segment, platform and 

payload, operations and exploitation. Parallel contracts will be awarded. 





Budget Ref.: 100631 - EO Preparatory Activities 

C 02 

Q4 




DIPC > 500 



Page 231 


02.155.18 PHASE A OF INSTRUMENT STUDIES FOR THE VISIBLE INFRARED 

IMAGER FOR METOP-3 

N10 

ESTEC 

This is a phase A study for the visible infrared imager for MetOp-3. The 

study will start with the thorough analysis of the requirements and the 

derivation of instrument concepts. This will be done in an incremental 

manner, starting from the core mission (optimum support to the IASI sounding 

mission and the operational meteorological mission) and including, at steps 

of added performance, other priorities. Trade-off analysis shall lead to the 

selection of a baseline concept based on performance, technical and 

programmatic criteria. End-to-end instrument performance models will be 

developed in support of the trade-off analyses. At a preliminary concept 

review (PCR) the baseline concept will be selected for further definition in 

the second part of the study. The second part will be devoted to the detailed 

analysis and design of the baseline concept. Development plans and cost 

estimates will be provided and a preliminary requirements review (PRR) will 

be held at which the compliance of the instrument with the mission and system 

requirements and with the programmatic constraints will be reviewed. Paralle 

contracts will be awarded. Type of tender C(2) - activities in open 









C 02 

Q3 



Status: 

DIPC > 500 



Page 232 


02.155.25 SYNERGETIC USE OF REMOTE SENSING DATA IN COUPLED 

OCEAN-ICE-ATMOSPHERE MODEL DATA ASSIMILATION 

N12 

ESTEC 

Sea ice remains poorly represented in state of the art coupled 

atmosphere-ocean general circulation models (AOGCMs). Insufficient 

parameterisations of sea-ice extent, concentration, drag, and thickness in 

these models do not allow ice volume and mass to behave in a manner 

consistent with natural time-space evolution of the bi-polar sea-ice cover. 

This limits the ability of AOGCMs to consistently and accurately reproduce 

observed natural variability in freshwater flux (in the form of ice) from 

high to low latitudes. This deficiency has a bearing on the sensitivity of 

modelled meridional overturning to high-latitude processes associated with 

sea-ice flux, and thus understates the vital connection between the polar and 

mid-latitude oceans. The present array of satellite remote sensing and 

in-situ bi-polar observations that are now routinely available are 

underutilised in the context of these coupled models. Only satellite passive 

microwave retrievals of ice concentration and extent receive widespread use. 

Others which shall be considered in the context of future ESA missions are, 

amongst others, radar altimetry and scatterometers. The primary reasons for 

this are perceived as the lack of application of rigorous assimilation 

schemes in coupled ice-ocean models, and the requirement for a demonstration 

of flexible, efficient assimilation modules, capable of assimilating a 

variety of different observations (satellite or in-situ) into AOGCMs. The 

objectives of this study are thus to: - address the deficiencies of current 

models by developing rigorous assimilation methods such that models can 

benefit from combinations of remotely sensed observations; - evaluate and 

test assimilation schemes using commonly available satellite observed 

quantities; - assess the benefits and improvements to model simulations; - 

assess the spatial validity of time-varying, simulated ice and ocean 

conditions with respect to reproducing typical large scale modes of 

variability such as the Arctic Oscillation, North Atlantic Oscillation, El 

Nino Southern Oscillation, or Antarctic Circumpolar Wave. 






C 02 

Q4 




DIPC 200-500 



Page 233 


02.155.27 GEOPHYSICAL DATA RETRIEVAL ALGORITHMS DEVELOPMENT FOR 

SWIFT ONBOARD GCOM-A1 

N20 

The objective of the study is to select, develop and test an end-to-end SWIFT 

Simulator and Retrieval System (SWIFT-SRS). The Contractor shall: *) review 

and eventually revise the SWIFT data products definitions (Level 0, Level 1b, 

Level 2); *) develop the SWIFT-SRS and all its elements; *) select the 

appropriate retrieval algorithms by comparative analysis of alternative 

approaches. The two primary objectives of the study are the development of 

the SWIFT-SRS and the selection of retrieval algorithms. The SWIFT-SRS shall 

contain the following elements: - the SWIFT Radiative Transfer Simulator 

(RTS); - the SWIFT Instrument Simulator (SIS); - the SWIFT Geophysical Data 

Product Retrieval System (GDR); - the SWIFT Data Visualisation Toolbox (DVT). 




Responsible: MR INGMANN 


C 02 

Q4 




02.155.28 STUDY OF HIGHLY STABLE FRONT END RECEIVER FOR ACE+ 

NO 200-500 

N24 

ESTEC 

In the framework of ESA Earth Explorer Core Missions a concept for exploiting 

inter-satellite radio links to derive water vapour and temperature 

information in the stratosphere and troposphere has been studied to pre-phase 

A level. The inter-satellite radio occultation concept is based on the 

observation of multiple signals at frequencies in the X and K bands in such a 

way to be able to collect two fundamental radiometric parameters for each 

transmitted signal, namely the amplitude and the carrier phase. From these 

data it is possible, under appropriate conditions, to retrieve profiles of 

humidity and temperature throughout the troposphere and the stratosphere. 

More specifically, this activity is aimed at the design, breadboarding and 

testing of the 22.6 GHz front-end of the receiver, which is defined as the 

analogue electronics from the input of the Low Noise Amplifier (LNA) to the 

output of the last stage preceding the analogue-to-digital conversion of the 

signal. 






C 02 

Q4 




NO 200-500 



Page 234 


02.156.02 DEVELOPMENT OF GOCE PAYLOAD DATA SEGMENT 

N24 

ESTEC 

The present Procurement Proposal is aimed at the development of the GOCE 

Payload Data Segment up to level 1.b. This development comprises: *) the 

procurement of the PDS Framework, which consists of the computing facilities, 

their operating system and the management of the various data interfaces; *) 

the development of the Instrument Processing Facilities ("IPFs"), which will 

process all the scientific data up to level 1.b.; *) the integration of the 

IPFs within the PDS framework; *) the development and procurement of the data 

storage and data distribution facilities (to be used during the active 

satellite lifetime). 


EO PROGRAMMES DEVELOPMENT DEPT / EOP-P 

GOCE PROJECT / EOP-PG 

Responsible: MR MUZI 

Budget Ref.: 100773 - Earth Explorer Core Mission 1 

C 02 

Q4 



Status: 

YIPC > 500 



Page 235 


01.160.12 GAIA SYSTEM LEVEL TECHNICAL ASSISTANCE AND DEFINITION 

STUDY 

The objective of the Definition Study is to make a detailed assessment of the 

mission scenario and of the different system elements, using a reference 

Model Payload studied during the GAIA Concept and Technology Study with the 

industry, with the technology approach validated by the GAIA Technology Plan 

activities. Then, based on the study results, the two selected contractors 

will support ESA in the preparation of the ITT for the selection of the Prime 

Contractor for the GAIA Project Phases B and C/D. The ITT content will 

combine the inputs from the two contracts, and although supported by 

industry, the actual ITT content will be confidential until the time of its 

release. The ITT will allow the selection of an industrial consortium through 

the competitive action between the two Definition Study Contractors. 

ESTEC SCIENTIFIC PROGRAMME - D/SCI 

SCIENTIFIC PROJECTS DEPARTMENT / SCI-P 

SCIENCE FUTURE PROJECTS & TECHNOLOGY OFFICE / SCI-PF 

Responsible: MR WHITCOMB 

Budget Ref.: 100129 - Mission Preparation - GAIA 

C 02 

Q2 



Status: 

01.160.22 OPTICAL COMPONENTS FOR INTERFEROMETRY 

YIPC > 500 

ESTEC 

The objective of this activity is to initiate the development of the generic 

critical technologies required by these interferometric missions. The 

developed critical components shall be integrated in system-relevant 

breadboards for validating the mission performances and for the 

identification of future technology development directions with the objective 

to confirm the feasibility of the missions and to reduce the development 

risks associated. Type of tender C(2) - activities in open competition, where 

a significant participation of non-primes is requested. For additional 








C 02 

Q2 



Status: EX ITEM 00.129.03 ISSUED WITH 01.160.64 

DIPC 200-500 



Page 236 


01.160.23 FIBER OPTICS WAVEFRONT FILTERING 

The DARWIN system requires wavefront errors of less than lambda/1000 at 5 

micron between pairs of telescopes in order to achieve the required nulling 

quality. Such high wavefront quality is difficult to achieve without 

wavefront filtering measures. The aim here is to establish a wavefront 

filtering system (WFS) of the DARWIN telescope system. The sub-activities 

envisaged are: Establishment of wavefront filtering concepts for the DARWIN 

system based on single-mode fibres, Investigation of additional 

functionality, which can be fulfilled by a fibre-optic system, Design and 

breadboarding of a broadband single-mode IR fibres system, Performance 

Validation of the fibre-optic filtering (and nulling) system. This activity 

makes use of infrared single mode fibres developed in related activity. Type 

of tender C(2) - activities in open competition, where a significant 









C 02 

Q2 




01.160.25 PROOF OF NULLING INTERFEROMETRY 

DIPC 200-500 

ESTEC 

The aim of this activity is to build a narrow-band infrared nulling 

interferometer. The interferometer is to be installed and used at ESO’s Very 

Large Telescope Interferometer (VLTI) in preparation for the DARWIN mission. 

It will allow the analysis of exo-zodical dust clouds around nearby stars, in 

the DARWIN list of candidate solar systems which could host earth-like life. 

The spectral band of the instrument has to be selected to optimise the return 

in terms of increased knowledge of the candidate solar systems. The VLTI will 

be optimised at a wavelength around 2 micrometer. It is therefore foreseen 

that the nulling interferometer will operate in this spectral range, possibly 

in addition also at 10 um. The activity shall prove nulling to a factor of 10 

4 to 10 

5 on celestial objects. In order to achieve this the contractor will have to 

control optical path length difference, amplitude, polarisation and wavefront 

errors very accurately. The contractor shall only use design concepts and 

technologies which can also be utilised in the DARWIN spectral range (4 - 18 

um). Type of tender C(2) - activities in open competition, where a 

significant participation of non-primes is requested.For additional 







Budget Ref.: 100461 - CTP - General 

C 02 

Q2 


Programme Ref.: ID-OP-07 

DIPC > 500 



Page 237 


01.160.40 COMPOUND SEMICONDUCTOR FOR HARD X-RAY AND GAMMA RAY 

ASTRONOMY 

N24 

ESTEC 

The aims of this activity are to develop a second-generation detector. It is 

proposed to consider the development of a new generation of Compound 

Semiconductor (CSS) detectors emphasising the harder X-ray/Gamma ray region 

so as to be well placed technically to respond to the requirements for future 

high energy astrophysics missions. Specifically it is proposed to investigate 

the use of TlBr and other compounds as base detector materials. The key tasks 

in this proposed activity are to develop the crystal growth techniques with a 

view to ensuring single crystals, epitaxial materials or low defect CSS 

samples, screen the material for suitability to fabricate science grade 

detectors, package acceptable materials as part of a program for monolithic 

detectors and carry out studies to develop the design of these basic 

detectors into large format arrays. The end result should be the fabrication 

of breadboard arrays as pre-cursors to large format devices. Type of tender 









C 01 

Q4 


Programme Ref.: TRP A 06 

Status: EX ITEM 01.1SA.03 TO BE RE-ISSUED 1-3907 

DIPC > 500 



Page 238 


01.160.43 OPTICAL PETAL MODEL 

The feasibility of the XEUS project is based on the ability to produce an 

X-ray mirror petal which is a segment of a full Wolter I mirror. This will 

require the development of a series of different models leading eventually to 

the production of a engineering model containing 6- 10 mirror plates each 

with an X-ray resolution of


Page 239 


01.160.45 OPTICAL / IR REJECTION FILTER TECHNOLOGY 

It is the purpose of this activity to design, breadboard and test inductive 

grid based filters which will specifically attenuate the levels of Near 

Infra-Red (NIR) & optical radiation expected in the XEUS Focal plane 

detectors to the appropriate level without effecting significantly the soft 

x-ray flux. Type of tender C(1) - activities in open competition limited to 








C 02 

Q2 


Programme Ref.: TRP X 04 

Status: EX ITEM 01.1SA.07 

01.160.46 LARGE SCALE LOW COST MANDRELS 

DAC 200-500 

ESTEC 

The XEUS Project will require hundreds of mandrels to produce the final 

mirror assembled in orbit at the International Space Station. With current 

polishing and general production techniques the mandrels required for XEUS 

will have a far too long production time and cost. Alternatives which respect 

the XEUS mandrel optical requirements as well as the electroforming Nickel 

technology required for the production of the Wolter I mirror plates need to 

be developed. Type of tender C(1) - activities in open competition limited to 







Budget Ref.: 100461 - CTP - General 

C 02 

Q2 


Programme Ref.: X 07 

Status: EX ITEM 01.1SA.08 

DIPC > 500 



Page 240 


01.160.49 MINIATURISED INERTIAL MEASUREMENT PACKAGE 

N19 

The objective of this activity is to develop and qualify a highly 

miniaturised accelerometer and gyroscope package suitable for future 

interplanetary missions and landers. Low mass/power gyroscopes and 

accelerometers are currently mass-produced for ground applications. Their 

development has been driven largely by the automotive industry. The 

capability to calibrate out sensitivity to thermal, radiation and 

acceleration (in the case of gyroscopes) disturbances must be proven, space 

hardy packaging and electronics surrounding the sensing element must also be 

designed and proven. The designed sensor will be manufactured and 

qualification tested under expected environmental conditions (tv, vibration, 

radiation sensitivity). Type of tender C(2) - activities in open competition, 








Budget Ref.: 100462 - CTP - BepiColombo 

C 02 

Q4 


Programme Ref.: BC-AO-04B 


01.160.56 MERCURY HORIZON SENSOR 

DIPC > 500 

ESTEC 

The objective of this activity is the design and development to prototype 

level of an horizon sensor for the Mercury Planetary Orbiter (MPO) and the 

Mercury Magnetospheric Orbiter (MMO) requirements. The technology requirement 

includes a thermal stability in the order of 0.01 K, an operating temperature 

up to 473 K (optical head), and an operating altitude from 300 to 12,000 km 

above Mercury surface. It should have application on both 3-axis and 

spin-stabilised platform (15 rpm). Required funding assumes a new 

development, rather than adaptation of current Earth sensor technology, 

because of the specific radiance environment of Mercury. Output: prototype 

and simulator with relevant software for calibration. Type of tender C(1) - 








Budget Ref.: 100125 - Mission Preparation - BepiColombo 

C 02 

Q2 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+IRL+GB+A+N+FIN+POR 

Programme Ref.: BC-AO-01 

Status: 

DIPC > 500 



Page 241 


01.160.57 MOLE-CARRIED SENSOR PACKAGE FOR MERCURY SUB-SURFACE 

MEASUREMENTS 

The aim of this activity is to design and develop an instrumented penetrating 

mole, that is suitable for Mercury sub-surface physical and chemical 

measurements. The activity shall include: - Review of the capabilities of 

currently existing mole design and assessment of its performance, including 

early testing of critical functions in the severe Mercury thermal 

environment; - Review of sensor package requirements and assessment of the 

availability of suitable sensors, including required adaptations. The 

measurements of interest include heat flow, density and electrical 

conductivity of regolith, volatiles in the regolith, and soil material 

composition by infrared spectrometry and close-up imaging; - Update of the 

mole design for the accommodation of the sensor package and the provision of 

the required instrument resources (particularly mass, volume, and power); - 

Building the upgraded mole with the integrated sensor package; - Functional 

performance and environmental testing of the instrumented mole. Type of 









C 02 

Q2 


Programme Ref.: TRP BC-AR-05 


01.160.64 OPTICAL DELAY LINES 

DAC 200-500 

ESTEC 

The DARWIN nulling interferometer requires an extremely accurate control of 

the optical path length differences between the various telescopes placed on 

free-flying satellites. A key element for optical path length difference 

control is an optical delay line. SMART-2 as precursor mission for DARWIN 

will demonstrate precision formation flying in combination with an optical 

delay line. The objective is to develop an elegant breadboard (representative 

in form/fit/function) to the optical delay line needed for DARWIN, supporting 

the SMART-2 FM procurement phase. The design of the optical delay line and 

the selection of materials have to take into account the space environment. 






C 02 

Q3 


Programme Ref.: TRP ID-OP-12 


DIPC 200-500 



Page 242 


01.160.67 GAIA DEFINITION AND IMPLEMENTATION 





Budget Ref.: 100129 - Mission Preparation - GAIA; 100175 - 

C 02 

Q1 

Gaia Scientific Operations 




02.160.03 MERCURY ORBITER SOLAR ARRAY 

YIPC > 500 

The objective of the proposed activity is the adaptation of high-temperature 

solar array to BepiColombo MPO and MMO requirements. Specific requirements 

include the substrate temperature up to 200o C, the cell temperature up to 

250o C and the operations under both 3-axis and spin stabilisation. Output: 

coupons of MPO and MMO solar arrays, tested in relevant environment. 





Budget Ref.: 100123 - Mission Preparation - Technology 

C 02 

Q2 


Programme Ref.: BC-EP-02 

Status: 

02.160.04 SOLAR ELECTRIC PROPULSION MODULE SOLAR ARRAY 

TECHNOLOGY 

DIPC > 500 

ESTEC 

The aim of this activity is the adaptation of solar array (materials 

selection, layout and power profile) to the BepiColombo Solar Electric 

Propulsion Module (SEPM). Specific requirements includes operation of solar 

array at high temperature, high intensity (0.3 AU from Sun), protection 

against direct sunlight incidence and adaptation of Solar Array Drive 

Mechanism (SADM): power range up to 20 kW per SADM, rotation angle –180 . 

Output: solar array wing panels and drive mechanism tested in relevant 

environment. 





Budget Ref.: 100123 - Mission Preparation - Technology 

C 02 

Q2 


Programme Ref.: BC-EP-03 

Status: 

DIPC > 500 



Page 243 


02.160.10 OPTIMUM COMPRESSION ALGORITHM 

The objective of the activity is to identify and validate lossless or quasi 

lossless compression algorithms to be applied on-board and in real time to 

reduce as much as possible the GAIA payload data rate to be transmitted to 

ground. An efficient on-board data compression, taking advantage of the 

advanced processing technologies, could allow not only the transmission of 

higher data rate, but will also make more viable the spacecraft design, 

alleviating critical design constraints on-board as well on the ground, with 

reduction of the overall cost. This activity should first identify, study and 

develop the most suitable algorithm, then implement the algorithm within the 

GAIA payload environment, with trade-off on hardware/software. Type of tender 









C 02 

Q2 


Programme Ref.: TRP G 16 

Status: 

02.160.11 MN FEEP FULL QUALIFICATION 

NO 100-200 

ESTEC 

GAIA reaction control system design assumes, among other things, a continuous 

thrust of mN FEEPs to control the satellite scanning law and attitude for a 

mission lifetime of 5 years, extendible to 6 years. This solution has been 

baselined to satisfy the strict requirements on satellite pointing accuracy, 

eg the rotation rate stability better than 0.001 "/s, over a period of 3 

hours (Hipparcos performance was 1.5"/s over 2 hours). At present, no mN 

FEEPs have been qualified and characterised for a continuous thrust of 6 

years, but only for much lower duration, e.g. 3 years. The objective is first 

to assess criticality of mN range FEEP based RCS requirements and constraints 

for GAIA, by establishing a FEEP RCS design and then build a demonstration 

model of the final product, including, at least, a sample of the most 

critical /sensitive items, and carry out a qualification and characterisation 

programme of the model according to GAIA needs. Type of tender C(1) - 








Budget Ref.: 100463 - CTP - GAIA 

C 02 

Q3 


Programme Ref.: CTP G 13 


DIPC > 500 



Page 244 


02.160.14 INCH-WORM MECHANISM 

To insure optical quality in-orbit, by recovering optical misalignments which 

may be induced by launch effects, the need for a 5 DOF, refocusing mechanism 

(two tilts and three translations) has been identified, based on inch-worm 

piezo-actuators, working at low temperature (150-200K). Requirements: 

amplitude misalignment –50 microm, with an accuracy of –1 microm. The 

inchworm piezo-actuators are being manufactured for twenty years for 

terrestrial applications. The supplier Burleigh (US) is carrying out a R&T 

program under NASA funding to develop and validate inch-worm actuators for 

Space operation, Cold environment, down to 30 K, providing holding force when 

un-powered. This makes these actuators attractive candidates for GAIA M2 

quasi-static correction mechanism, but the performance and feasibility of 

this mechanism relies only on one (American) supplier (Burleigh) and on the 

progress of the NASA R&T. To mitigate the associated risks and potential 

criticality, the activity proposed includes two stages: specification and 

design refinement of the actuator (phase 1) and demonstrator development and 

test (phase 2). Type of tender C(1) - activities in open competition limited 

to non-primes. For additional information please go to EMITS news "Industrial 







C 02 

Q2 


Programme Ref.: TRP G 23 

Status: 

02.160.16 INERTIAL SENSOR GROUND TESTING & NOISE MODEL FOR LISA 

DAC > 500 

ESTEC 





Budget Ref.: 100464 - CTP - LISA 

C 02 

Q3 


Programme Ref.: L 01/2 


DIPC 200-500 



Page 245 


02.160.18 PLANETARY MICROPROBES 

The objective of this activity is to develop a Micro-robotic Probe (1-5 kg) 

for the in-situ exploration of planetary atmospheres and surfaces. Aims are 

to assess the scientific measurements that are desirable to be performed to 

further our understanding of the physical and chemical properties of the 

surface of planets. The engineering requirements that result from the 

accommodation of suitable sensors and measurement strategies shall be 

assessed. A test model of a planetary micro-robot shall be developed and 

shall be subject to a comprehensive test programme in order to validate the 

concept. Type of tender C(1) - activities in open competition limited to 








C 02 

Q2 


Programme Ref.: TRP SCI-S30 

Status: 

02.160.19 PLANETARY AEROBOTS 

DIPC 200-500 

ESTEC 

Robotic balloons can be prime tools to enable the global exploration of solar 

system worlds with sufficient atmosphere. The objective is to perform a first 

study of application scenarios, requirements, design approaches and critical 

technologies for aerobots. Tasks include the identification of application 

scenarios, requirements, key technologies, design concepts, breadboarding of 

first critical functions, test and demonstration in a planetary robotics 

testbed. Type of tender C(1) - activities in open competition limited to 








C 02 

Q4 




NO 100-200 



Page 246 


02.160.26 ALTERNATIVE MIRROR COATINGS ON NICKEL MIRRORS 

N11 

ESTEC 

The objective of this activity is to develop an Electroformed mirror with 

non- Au-coating. In this study a small demonstration mandrel, which will not 

be of the X-ray quality required by XEUS, but will be adequate to examine the 

technological problems associated with the deposition and release of 

alternative X-ray reflective coatings from the mandrel through the 

electroformed nickel process. The main aim of the program will be to assess 

the range of materials and their distribution across the mirror plates, study 

the deposition techniques and sticking forces involved in coating a XEUS 

mandrel, assess the approach to release of the electroformed mirror from the 

mirror and also to assess the X-ray reflectivity properties of the 

electroformed mirror. Type of tender C(1) - activities in open competition 

limited to non-primes. For additional information please go to EMITS news 


programmes". 



SCIENCE PAYLOADS TECHNOLOGY DIVISION / SCI-ST 

Responsible: MR PEACOCK 


C 02 

Q4 


Programme Ref.: TRP X 08 


DAC 200-500 



Page 247 


03.160.01 RECONSTRUCTION OF NULLING INTERFEROMETER IMAGES 

N14 

ESTEC 

Nulling interferometry as planned to be used for DARWIN in the search for 

extra-solar planets will provide spectrally dispersed data (typically spread 

over 20 to 50 bins from 5 to 20 microns) and their time evolution over 

periods of hours. Each spectral bin provides a photometric single-pixel 

signal and its temporal evolution. The field of data post-processing for 

nulling interferometers has up to now not been adequately addressed. The 

available images have been constructed from data, generated by simulated 

nulling interferometers, by use of simple algorithms based on 

cross-correlation. Nulling interferometer designs are evaluated against their 

mean and maximum modulation efficiency. The mean modulation efficiency is a 

measure on how well the interferometer can detect planets while the maximum 

modulation efficiency reflects the interferometer’s capability of taking 

planet spectras, once the planet has been located. However, since the data 

reduction task involves complex modulation maps these figures may not give a 

correct indication of the actual performance of the nulling interferometer. 

In this activity different image processing algorithms, interferometer 

configurations and observational sequences shall be defined and traded-off 

against each other, on the basis of typical target system models. The 

processing algorithms shall address both the planet finding and planet 

characterisation tasks. An integral task of this activity is to determine the 

observational programme as required per target system, i.e. the 

interferometer configuration for each observation, observation duration, 

number of interferometer reconfigurations and revisits to the same target 

system. The benefit of constant movement of the apertures shall be evaluated. 





Budget Ref.: 100122 - Mission Preparation - Studies 

C 02 

Q4 


Programme Ref.: ID-IP-01 

Status: 

NO 200-500 



Page 248 


02.164.01 TECHNICAL ASSISTANCE FOR IMPLEMENTING THE HERSCHEL 

SCIENCE CENTRE 

N24 

ESTEC 

As part of the overall Herschel Ground Segment, the Herschel Science Centre 

is embedded into a network of nodes consisting of a Mission Operations 

Centres (MOC, responsible for up-linking all satellite commands and satellite 

safety), three Instrument Control Centres responsible for the definition of 

instrument modes of operation, for providing software to generate data 

products from the telemetry produced in these modes, and for maintaining 

instrument health as far as the scientific validity of such data is concerned 

and the NASA Herschel Science Centre. The "glue" in this distributed system 

is the Herschel Common Science System (HCSS) under development. The 

development approach for the Herschel Common Science System differs from 

earlier developments of Science Operation Centres (ISO, XMM-Newton, Integral) 

in a number of areas: *) a conscious decision has been made to develop the 

scientific part of the Herschel Ground Segment at ESTEC as a joint venture 

between ESA and the nationally funded control centres for the three Herschel 

instruments; *) the HCSS is a purely object-oriented, all Java-system; *) the 

HCSS is developed incrementally in close co-operation with its users and with 

frequent user releases (~ one every 4-6 months) to ensure that the system 

functionality and handling meets user requirements. The Agency requires 

technical assistance in developing the HCSS system to ensure a robust and 

coherent framework for an incremental design process. The areas for which 

this technical assistance is sought are in particular the HCSS system 

architecture and system engineering. These activities need to be deployed at 

ESTEC and require experienced software skills preferably with experience on 

similar missions in the past. It is considered that a minimum of two highly 

qualified software engineers is required to undertake these tasks. 





Budget Ref.: 100292 - Herschel Science Operations 

C 02 

Q4 



Status: 

YIPC > 500 



Page 249 


02.165.01 4HE CRYOSTAT FOR STRATOSPHERIC BALLLOON FLIGHTS 

N9 

ESTEC 

This procurement concerns the manufacturing of a liquid helium cryostat for 

stratospheric balloon flights. No space qualification requirements apply. 

Standard mechanical strength requirements apply (10 g vertical, 5 g lateral). 

The cryostat shall have a hold time longer than 48 hr and a dry mass not 

larger than 60 kg. The heat load generated by the internally installed 

experimental set-up will not exceed 10 mW. The cryostat will comprise a 

number of thermal shields and provide an experimental chamber with a clear 

diameter of 35 cm and a clear height of 40 cm. By exploiting the reduced 

atmospheric pressure (of order 3 mbar at h=40 km), the cryostat shall ensure 

an equilibrium temperature of 2.3K (cold plate / experimental chamber) once 

at cruising altitude. The cryostat shall be equipped with a number of 

(separately supplied) electrical connectors and a 50 mm diameter optical 

window, located on the bottom side. The cryostat shall include the provision 

for the heat sinking of the cryo-harness but the latter is not part of this 

procurement action. 



SCIENCE PAYLOADS TECHNOLOGY DIVISION / SCI-ST 

Responsible: MR PEACOCK 

Budget Ref.: 100029 - Space Science 

C 02 

Q2 




NO 50-100 



Page 250 


02.167.01 WEB PUBLISHING, EDITORIAL SUPPORT AND TECHNICAL 

ASSISTANCE TO THE ESA SCIENCE WEB SITE 

N23 

ESTEC 

The Science Programme Communications Service (SPCS), in collaboration with 

the Agency’s Public Relations Services, manages the internal and external 

communications of the Scientific Programme. SPCS has pioneered the first 

internet based information service in the Agency. To ensure the success of 

such "start-up", the type of activity required by SPCS was not IT development 

only, but rather content development with a clear emphasis on editorial 

capabilities. The content of the work has evolved and the present procurement 

is expected to provide only limited IT services ie a minimum interfacing with 

ESRIN in view of the migration and integration of the present Science web 

pages into the ESA Science portal. The editorial functions (ie ensuring 

quality of published material and writing material if so required) will 

remain but should cover not only the web, but the other editorial needs of 

the SPCS as well. The SPCS will still hold the ultimate responsibility to 

approve, or modify, any produced material. Finally, a function of monitoring 

an overall balance of the web textual and graphical content will be required, 

also including web refurbishment while being in line with the ESA web portal. 


SCIENCE PROGRAMME COORDINATION & PLANNING OFFICE / 

SCI-C 

SCIENCE PROGRAMME COMMUNICATIONS SERVICE / SCI-CC 

Responsible: MR CAVALLO 

Budget Ref.: 100282 - Science Programme Support 

C 02 

Q4 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+IRL+A+N+FIN+POR; ATOS 

ORIGIN ENGINEERING SERVICES BV (NL); EJR QUARTZ 

BV (NL); E-VISION (NL); SAPIENZA CONSULTING LTD 

(GB) 



DAC > 500 



Page 251 


01.171.03 COMMUNICATION SERVICES AT ESA HQ AS FROM 2002 

The activities to be covered comprise the operation of the reception, the 

switchboard, the mail and fax room, the reproduction equipment as well as 

internal transport within HQ. The activities will be for a period of 3 years 

with 2 possible extensions of 1 year 

ESAHQ DIRECTORATE OF ADMINISTRATION - D/ADM 


HQ SITE MANAGEMENT SERVICES / ADM-GH 

Responsible: MR LOLIVIER 


C 02 

Q2 


Programme Ref.: HQ-M-01-070 

Status: 

01.171.05 CONSTRUCTION OF A BUILDING EXTENSION AT ESA HQ 

DAC > 500 

Construction of a building extension above the "annex" of ESA HQ aimed at 

providing additional offices and meeting room facilities (700 to 900 sqm) 

ESAHQ DIRECTORATE OF ADMINISTRATION - D/ADM 





C 02 

Q2 


Programme Ref.: HQ-M-01-030 

Status: 

02.171.02 GENERAL SUPPORT CONTRACT : SWITCHBOARD, TRANSPORT, 

HELPDESK, FAX, REPRODUCTION, MAIL AS FROM 01-01-2003 

DAC > 500 

N12 







C 02 

Q3 

Spec. Prov.: LOCAL TENDER F 

Programme Ref.: HQ M-02-151 


DAC > 500 



Page 252 


01.174.01 NEWS ROOM EDITING SUPPORT 

Support of Web editorial activities identified as needed to support the ESA 

Web Portal regular operation for a period of three years. 

ESRIN 

DIRECTORATE OF STRATEGY AND TECHNICAL ASSESSMENT 


Responsible: MR KRATZENBERG-ANNIES 

Budget Ref.: 100973 - Corporate and Admin Costs - D/SER 

C 02 

Q2 



Status: 

02.174.02 TECHNICAL SUPPORT FOR THE ESA VIDEO ARCHIVE FOR THE 

PERIOD 2003-2005 

DAC > 500 

N10 


STRATEGY AND EXTERNAL RELATIONS - D/SER 

COMMUNICATION DEPT / SER-C 

Responsible: MR KRATZENBERG-ANNIES 

Budget Ref.: 100980 - Corporate Communication 

C 02 

Q4 




DAC 200-500 



Page 253 


02.179.03 CENTRE FOR SATELLITE PROPAGATION MEASUREMENTS 

N23 


Advanced Multimedia Communication and Navigation Satellite systems require a 

detailed characterization of the propagation channel. The experimental 

characterisation of the propagation channel, for both, along with theoretical 

models accuracy assessment is a key element in the design of innovative 

Navigation and Communication satellite systems. Purpose of this activity is 

to set-up a centre of excellence for satellite propagation measurements. This 

centre should design and build specialised receiver hardware, deploy and 

calibrate the equipment and carry out propagation measurement campaigns which 

make use of signals of opportunity from 20 to 85 GHz (such as the 42 GHz 

beacons on board of STENTOR). The bidder will also be invited to address 

L-Band measurement aspects relevant for GNSS design. The envisaged contract 

will cover the following work: * Development of innovative equipment for 

propagation measurement; * Deployment and operation of measurement equipment; 

* Data analysis 

INDUSTRIAL MATTERS & TECHNOLOGY PROGRAMMES - D/IMT 

INDUSTRIAL POLICY OFFICE / IMT-I 

Responsible: MR MOREL DE WESTGAVER 

Budget Ref.: 100079 - Portugal’s Industry Incentive Scheme 

C 02 

Q4 

Spec. Prov.: P 


Status: 

DAC 100-200 



Page 254 


01.185.02 DOCUMENT ARCHIVE SYSTEM 

ESA’s document archive system currently runs on a customised implementation 

of the NOVA content management system. There are two different versions of 

this system - one running internally to ESA’s firewall for use by ESA staff 

and one running outside the firewall which currently hosts the Industry and 

Launchers web sites. The current system is very slow, its physical 

limitations have been reached, and the product developer no longer supports 

it. The system hence must be replaced. ESA has identified File-Net as the 

proposed tool. The scope of this tender is to finalise ESA’s requirements; to 

validate File-Net through a prototype demonstration; to specify the 

architecture and detailed design; to acquire, parameterise and deliver the 

COTS document archive system; to convert and migrate existing data; and to 

train the users and system managers. 

ESRIN DIRECTORATE OF ADMINISTRATION - D/ADM 

INFORMATICS DEPARTMENT / ADM-I 

MANAGEMENT INFORMATION SYSTEMS DIVISION / ADM-IM 

Responsible: MR ALVISI 

Budget Ref.: 100930 - Common IT Infrastructure 

C 02 

Q2 




02.185.01 CENTRALISED ACQUISITION OF PERIODICALS 

NO 100-200 

N9 

ESTEC 

The Information Systems Department is responsible for the purchasing of 

periodicals/magazines published worldwide for all ESA establishments. The 

areas covered correspond to ESA activities and range from scientific & 

technical to administrative topics. The number of periodicals/magazines 

subscriptions purchased annually is about 1000. The purchasing and delivery 

service to ESA has been centralised and is to be assigned to an intermediary 

company. 


HEAD OF ESRIN / ADM-E 

Responsible: MR MARTIN-RICO 

Budget Ref.: 100972 - Corporate and Admin Costs - D/ADM 

C 02 

Q3 



Status: 

02.185.02 INFORMATION AND DOCUMENTATION SERVICING 

DAC > 500 

N10 

ESRIN 


HEAD OF ESRIN / ADM-E 


Budget Ref.: 100972 - Corporate and Admin Costs - D/ADM 

C 02 

Q4 



Status: 

DIPC > 500 



Page 255 


01.286.01 ESA WIDE PROCUREMENT OF PERSONAL COMPUTERS 

ESRIN 


INFORMATICS DEPARTMENT / ADM-I 


Budget Ref.: 100930 - Common IT Infrastructure 

CR 02 

Q2 

Spec. Prov.: COMPAQ, DELL, HEWLETT PACKARD, IBM, 

SIEMENS/FUJITSU 


Status: 

DAC > 500 



Page 256 


00.187.07 EO USER INFORMATION SYSTEMS APPLICATION CLIENT 

ESRIN DIRECTORATE OF EARTH OBSERVATION PROGRAMMES - D/EOP 


GROUND SEGMENT ENGINEERING DIVISION / EOP-AG 

Responsible: MR GUIGNARD 


C 02 

Q2 

Spec. Prov.: B+A 

Programme Ref.: GSTP-3 GOO/67.APP-U03 

Status: 

01.187.04 GROUND PROCESSOR WITH SCALABLE DSP ACCELERATORS 

DIPC > 500 






C 02 

Q2 

Spec. Prov.: 

Programme Ref.: GSTP-3 G00/F65.ETD-041 

Status: CHANGED TO 02.1ET.04 

01.187.05 MODELLING & SIMULATION TOOLS TO SUPPORT END TO END 

APPLICATIONS 

DIPC > 500 






C 02 

Q2 

Spec. Prov.: N 

Programme Ref.: GSTP-3 G00/F66.APP-S08 

Status: 

02.187.03 MULTI-MISSION MASTER CATALOGUE: ALOS DEVELOPMENT 

DIPC > 500 

N12 

ESRIN 

ALOS could be the first mission on a new master catalogue, hosted on a new 

platform. The existing Master Catalogue is based on a 11 years old 

development and cannot be further maintained at low cost. The design should 

be multi-mission compatible, such that all the other EO Missions (under ESRIN 

Control) can be moved to this new master catalogue at a later stage (not part 

of this development) 





Budget Ref.: 100766 - ALOS 

C 02 

Q3 




DAC 200-500 



Page 257 


02.187.04 INFEO IMPROVEMENTS FOR USAGE AS ALOS INTEROPERABILITY 

LAYER 

N12 

INFEO provides an interoperability layer above MUIS. It is an already 

existing system, developed by several companies having all the knowledge and 

the capacities to upgrade it. As soon as NASDA has finalized its 

interoperability requirements, this element will be implemented through the 

currently envisaged Open Competition 






C 02 

Q3 




02.187.05 ASSEMBLY, INTEGRATION AND TESTING (AIT) OF ALOS 

DAC 100-200 

N13 

ESRIN 

ESA is currently implementing a Ground Segment (called ADEN GS) for the 

reception, processing and distribution to users of ALOS data.The Advanced 

Land Observing Satellite (ALOS), built by NASDA is a Satellite succeeding the 

Japanese Earth Resources Satellite-1 (JERS-1) and the Advanced Earth 

Observing Satellite (ADEOS), which will utilise advanced land-observing 

technology. ALOS will be launched by an H-IIA launch vehicle in mid 2004. The 

implementation of the ADEN GS is performed through different contracts, 

mainly one contact for the development of the Acquisition and Processing 

Centres and separated contracts for the embedding of ALOS into the 

multi-mission user services (TUSC) at ESRIN, (including a Multi-Mission 

Master Catalogue). The Agency has decided to have the processes of the 

verification and acceptance of the Master Catalogue, and the integration of 

the TUSC with the ADEN GS performed by an independent organisation. 

Therefore, within this Contract, the Contractor will be responsible to 

execute these processes with a high degree of independence. The complete 

scope of this activity is the following: 1. Review of the Multi-Mission 

Master Catalogue Documentations 2. The creation of the Acceptance Test 

Specification and the execution of the Multi Mission Master Catalogue on-site 

acceptance 3. The ADEN GS and TUSC Integration and Validation process 






C 02 

Q3 




DAC 200-500 



Page 258 


02.187.06 SURVEY AND ASSESSMENT OF ADVANCED FEATURE EXTRACTION 

TECHNIQUES AND TOOLS FOR EO APPLICATIONS (SURF) 

N12 

The key objectives of the proposed activities are to obtain an up-to-date 

picture, with ranking per EO application area, of advanced techniques, 

algorithms and tools for feature identification / extraction and information 

mining from EO data (images in particular) with or without assisted learning 

and fusion with EO and non-EO data. In detail the activity shall: •Assess and 

rank per EO application area (e.g.: for relevancy, maturity, potentiality, 

feasibility, ) the current and emerging techniques, algorithms and tools 

(like fractals, wavelets, genetic algorithms, chaos theory, neural networks, 

etc.), applicable to feature identification / extraction and information 

mining from EO data (images in particular) •Analyse and assess the possible 

synergies and combinations of techniques• Identify, the most relevant 

techniques, algorithms and tools, of related constraints and requirements, as 

well as of possible architectures and exploitation scenarios 

•Analyse/demonstrate feasibility of the selected techniques, algorithms and 

tools. 






C 02 

Q4 


Programme Ref.: TRP PDE-KEO-002 


02.187.07 ESA MULTI-MISSION CATALOGUE TO OPENGIS WEB MAP SERVER 

BRIDGE (MUIS2WMS) 

DAC 200-500 

N21 

ESRIN 

The ESRIN Multi-Mission Catalogue (MUIS), contains thousands of browse 

products from ESA missions (ESR1/2, ENVISAT) and Third Party Missions 

(Landsat, NOAA AVHRR or TERRA/MODIS...). Within MUIS, the browse products are 

stored in native sensor projection and therefore cannot be easily merged with 

other satellite of GIS data. The purpose of this contract is to develop an 

OpenGIS Web Map Server (WMS) interface on top of the MUIS server so that 

users can obtain via a simple http request graphical representations of the 

browse products in a well-known geographic projection (Plate-Career in 

particular) and control the geographic region and time window of interest. 

Besides interfacing with the MUIS Catalogue, the main task of this contract 

consists in the geocoding of satellite images from various optical and radar 

sensors with performances compatible with web applications (i.e. a few 

seconds). 





Budget Ref.: 100065 - Earthnet; 100781 - Envisat Operations 

C 02 

Q4 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+A+N+FIN+POR+CDN 



NO 200-500 



Page 259 


02.189.01 MECHANICAL INFRASTRUCTURE OF THE GROUND SEGMENT OF THE 

VEGA SMALL LAUNCHER DEVT 

The different stages as well of the upper composite of the VEGA Launcher are 

assembled, in Kourou, on the VEGA Launch Site in the VEGA Integration 

Building called "BIV" which is composed by a Mobile Gantry, the Launch table 

and the umbilical mast. The Mobile Gantry covers the Launch zone while 

integrating the Launcher directly on the Launch fixed table. Doing this way, 

the Launcher is protected against meteorological condition as well as 

lightning risk during the whole integration campaign. Before entering into 

final countdown, the Gantry is transferred in a rear zone, using a lifting 

and a rolling system, allowing the lift-off. This concept was already the one 

used on ELA1 and is the usual concept for a low launch rate as it is 

specified for VEGA (average 4 launches per year). The present VEGA Ground 

Segment procurement concerns the Mobile Gantry and Launcher Interfaces.The 

breakdown of the activities to be performed by Industry consists of a 

detailed design, the manufacture, the transport from Europe to Kourou, the 

site installation of all relevant components as well as the corresponding 

test activities up to final acceptance by customer of: 1. The Mobile Gantry 

composed of a coverage, a frame structure, a lifting system, a rolling 

system, all necessary Launcher access including the upper composite and a 

quick building evacuation mean. 2. The BIV Launcher Interfaces composed of 

the Launch table, the mast, the stages Transfer and erection means and 

finally the Upper Composite integration means on the Launcher. 3. The 

adaptation of A5 booster segment trailer to transfer the P80 from its 

preparation zone to the BIV and the existing Launcher Upper Composite trailer 

used as well and adapted to VEGA needs. 

ESRIN 


VEGA PROGRAMME / LAU-V 

Responsible: MR BARBERA 

Budget Ref.: 100341 - Small Launcher Development 

C 02 

Q3 

Spec. Prov.: B+F+I+NL+E+S+CH 


Status: 

DIPC > 500 



Page 260 


02.189.02 CIVIL INFRASTRUCTURES OF THE GROUND SEGMENT OF THE 

VEGA SMALL LAUNCHER DEVT 

Following the conclusion of the Steering Board of the VEGA Launch Site 

Working Group, ELA1 was selected to be used for the VEGA Launches operated 

from CDL3 (Launch Centre of Ariane 5).Under the general heading of "Civil 

Infrastructures", the task addressed by this procurement will consist of the 

adaptation of the "Project Room used for the Flight 501", located in the 

reinforced building of CDL3, an installation of the VEGA Operational Control 

Command Computer and the relevant interfaces. Equipped Offices with energy, 

air conditioning, telecom means, etc, shall be provided for the VEGA 

Operational and maintenance teams. The existing ELA1 civil work will be 

refurbished and adapted for the VEGA Integration Building and the associated 

components. Access roads and general services shall be adapted as well as de 

jet deflectors. Air conditioning of all VEGA buildings is part of the present 

work. Finally, the different categories of energy powering the VEGA Ground 

Segment are part of the present work description. The present VEGA Ground 

Segment procurement comprises the Civil Infrastructures design, manufacture, 

transport, site installation of components and the associated test activities 

up to final acceptance by customer. The activity shall start from the 

Preliminary design issued from the Ground Segment Preliminary Design Review 

and it is relevant to the following components: • ELA1 Civil work • Access 

road and various service systems • ELA1 jet deflector adaptations • Launch 

Control Centre adaptation (CDL3) • Offices • Air conditioning • Energy This 

activity shall end by the associated tests activities on all necessary 

components 

ESRIN 





C 02 

Q3 



Status: 

DIPC > 500 



Page 261 


02.189.03 OPERATIONAL COMPUTING SYSTEM & OPERATIONAL SOFTWARE OF 

THE GROUND SEGMENT OF THE VEGA SMALL LAUNCHER DEVT 

The VEGA Ground Segment is to be operated manually and automatically through 

the Operational Control Command Computer to be located in the reinforced 

building of CDL3. An agreement with Arianespace was finalised at the steering 

Board of the VEGA Launch Site Working Group on this matter.Manual Operation 

is required for Industrial sub-system and component tests but automatic 

procedures are mandatory for operating the Launcher and all activities part 

of final chronology. The computer system will be used as well for integration 

test activity and final acceptance of P80 performed at BIV during Production 

phase. The present VEGA Ground Segment procurement comprises the Operational 

Computing System and Operational software, design, manufacture, transport, 

site installation and test activities up to final acceptance by customer. The 

activity shall start from the Preliminary design issued of the Preliminary 

Design Review. The first phase shall include the following components: 

• Operational Control Command Computer, necessary to operate Ground Segment 

and Launcher operations up to lift-off and after flight Ground Segment 

revalidation. • The Calculation Centre / Ground Software workstation, used to 

produce software and Operational Data Base as well as the applicative Data 

Base • Payload Control Command bench, necessary for final checks and 

acceptance of the Payload before transferring onto the Launcher as well as 

following the Payload status until lift-off. • Thrust Vector Control (TVC) 

Substitution Power Supply, which has to be supplied to operate nozzle of each 

Solid Propellant stage during launcher preparation (Synthesis Control) and 

specifically for final checks and acceptance of the first stage (P80), which 

is manufactured in French Guyane. • Launch Base and Payload Interfaces, 

necessary for the campaign coordination activities (Radio Frequency, Optical 

Fibre links, Universal and local Time Distribution, Launcher status, Launcher 

Base status, tracking system, telecommand system, real time telemetry 

acquisition system, ) The second phase shall consist of developing all 

operational software necessary to operate automatically the Ground Segment 

and the Launcher with respect to the corresponding Operation Specification 

Manual. Each software component will be individually tested after coding by 

Contractor. The Contractor shall support the integrated validations onto the 

control bench. In this context, the software update is expected while and 

after integrated tests in compliance with Operational Specification Manual 

evolution. Any corrective maintenance of software shall be foreseen. The 

Executive intends to allocate activities at Prime Contractor level by open 

competitive tender, subject to an acceptable offer. Certain equipments 

interfacing with ELA3 or CSG (Centre Spatial Guyanais) shall have to respect 

existing design and operations constrains.It is an objective of the Executive 

to ensure a technical coherence between the initial hardware development and 

the subsequent operational software by performing the overall activity under 

a common industrial responsibility.A first phase, starting mid 2002, is 

related to all activities except software development.Subcontractors 

experienced in designing an economical, efficient and proven architecture 

will be selected to support the Prime Contractor, who will be selected for 

the first Phase and who will continue his prime contractor-ship during Phase 

2 as well. The design shall interface the Bus 1553, the Ariane5 Telemetry 

system and the Thrust Vector Control system already defined.For the second 

phase, starting beginning of 2005, a sub-contractor, skilled and able to 

develop, validate and support integration tests and software updating all 

through the maiden flight campaign included, will be selected to further 

support the Prime Contractor. Appropriate provisions will be introduced, 



Page 262 

safeguarding the Agency’s rights and interests, especially regarding the 

delivery schedule, performance and costs with respect to their impact on the 

overall Program. 

ESRIN 





C 02 

Q2 



Status: 

02.189.04 FLUIDS PROCESS AND GENERAL MEANS OF THE GROUND SEGMENT 

OF THE VEGA SMALL LAUNCHER DEVT 

DIPC > 500 

The VEGA Flight Campaign request of supplying fluids (air, helium, nitrogen, 

oil, ) to perform all necessary launcher operation as well as toxic 

propellant (UDMH, N2O4) to feed the AVUM’s upper stage tanks.The associated 

instrumentation is required to deliver the needs with respect to temperature, 

pressure, and flow as specified in the Operational Specification Manual for 

Ground Segment and Launcher.The use of toxic fluids and gas implies specific 

treatment and leak detection system as well as security means (fire fighting 

equipment, ).The coordination and survey of the here above mentioned 

operations is done through operational, communication and survey means to be 

provided (telecommunication, access management, video, specific fast camera 

for lift-off, ). The present VEGA Ground Segment procurement comprises the 

Fluids Process and General means design, manufacture, transport, site 

installation and Industrial test activities up to final acceptance by 

customer. The activity will start from the Preliminary design issued from 

Preliminary Design Review of the project and apply to the following 

components: • Conventional Fluids • Toxic Propellant Process 

• Instrumentation • Propellant detection and treatment • Security means 

• Communication means • Operational means In order to implement the above 

activities, the Executive intends to place a contract with a Prime Contractor 

in competitive tender, subject to an acceptable offer. The Prime Contractor 

is expected to place sub-contracts for specific activities, in particular for 

equipments in interface with ELA3 or CSG (Centre Spatial Guyanais) that will 

have to respect existing design and operation constrains. An experienced 

company working in technically complex processes is required to provide the 

necessary skills.Appropriate provisions will be introduced, safeguarding the 

Agency’s rights and interests, especially regarding the delivery schedule, 

performance and costs with respect to their impact on the overall Program. 

ESRIN 





C 02 

Q4 



Status: 

DIPC > 500 



Page 263 


01.195.01 BIOMEDICAL ENGINEERING SUPPORT: DEVELOPMENT OF 

PRODUCTS AND IMPLEMENTATION OF CREW OPERATIONS 

SERVICES 

N18 

ESTEC 

In the frame of the International Space Station Utilisation Programmes, ESA, 

through the Crew Medical Support Office (CMSO) is participating in the 

implementation of multilateral medical operations services to the ISS 

crewmembers. In co-ordination with the International Partners, the CMSO has 

developed a medical support plan for the ESA Astronauts which addresses the 

main areas of clinical medicine, preventive medicine, behavioral health and 

performance and general astronaut support, emergency medical services and 

mission support. An operational infrastructure is also being developed by 

CMSO to support the implementation of services such as medical informatics, 

real-time mission support, crew and flight controller medical training, 

supplemental medical infrastructure. The objective of the proposed 

procurement is to obtain qualified support in very specialised areas of 

expertise to assist CMSO, under the responsibility and authority of CMSO, in 

implementing ESA’s medical support plan and provide the crew operations 

related services. 


EUROPEAN ASTRONAUTS CENTRE / MSM-A 

Responsible: MR MESSERSCHMID 

Budget Ref.: 100555 - ISS Astronauts 

C 02 

Q3 




DIPC > 500 



Page 264 


03.197.01 PARALLEL PHASE A2 STUDIES OF AN EXOBILOLOGY PAYLOAD 

AND ROVER FOR THE EXOMARS MISSION 

N24 


STRATEGY AND EXTERNAL RELATIONS - D/SER 

ADVANCED CONCEPTS & STUDIES OFFICE / SER-A 

Responsible: MR ONGARO 

Budget Ref.: 100580 - AURORA; 100162 - EMIR-2 Extension 

C 03 

Q1 

Spec. Prov.: B+DK+F+D+I+NL+E+S+CH+GB+A+N+FIN+P+CDN 

Programme Ref.: GS 03A10 

Status: 

YAC > 500

LIST OF INTENDED INVITATIONS TO TENDER 2002 - emits - ESA

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