document title / titre du document TRP W ORK PLAN ... - emits - ESA

document title / titre du document 

TRP WORK P LAN 2005 – 2007 

C OMPLETE L IST OF A CTIVITIES 

prepared by/préparé par 

TRP Management Office 

reference/réference 

TEC-SB/7935/dc 

issue/édition 1 

revision/révision 0 

date of issue/date d’édition 12/02/2009 

status/état 31/12/2008 

Document type/type de document Information Note 

Distribution/distribution 

a 

TEC-SB_7935_TRP2008-2010

s 

TRP WORKPLAN 2008-2010 

Complete Llist of Activities 

issue 1 revision 0 - 

3page ii of iii 

APPROVAL 

Title 

Titre 

TRP Work Plan 2005-2007 – Complete List of Activities 

issue 

issue 

revision 

revision 

author 

auteur 

TRP Management Office 

date 

date 

10/02/2009 

approved by 

approuvé par 

date 

date 

CHANGE LOG 

reason for change /raison du changement issue/issue revision/revision date/date 

CHANGE RECORD 

Issue: Revision: 

reason for change/raison du changement page(s)/page(s) paragraph(s)/paragraph(s)

s 


Complete Llist of Activities 

issue 1 revision 0 - 

3page iii of iii 

T A B L E O F C O N T E N T S 

1 INTRODUCTION 

2 COMPLETE LIST OF ACTIVITIES 

3 DESCRIPTION OF ACTIVITIES

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Complete List of Activities 

issue 1 revision 0 

page 1 of 5 

1 INTRODUCTION 

This information note presents the complete list of activities that constitute the TRP 2005-2007 

work plan cycle, their status and descriptions. 

The document is structured as follows: 

Chapter 1, Introduction 

Chapter 2 includes tables listing all activities divided by following Service Domains: 

1. Technologies related to Earth Observation 

2. Technologies related to Science 

3. Technologies related to Human Spaceflight Manned Exploration 

4. Technologies related to Space Transportation & Re-entry Technologies 

5. Technologies related to Telecommunication / Navigation 

6. Generic Technologies and Techniques 

and provides following information: 

IPC Approval: 

Status: 

Budget: 

. 

Status of approval of the corresponding procurement proposal. 

(YXXXX= Year of approval for workplan activities previously 

endorsed & corresponding procurement proposals approved, if 

applicable. 

Proposed: Not yet approved/submitted to AC/IPC 

Intended: Approved by IPC but not committed yet 

Contracted: Contract signed 

Closed: Contract closed, all deliverables received 

Deleted: Removed from work plan 

Deferred: Previously approved but postponed 

Budget planned for this activity. Total Contract Authorisation (CA) 

values, given in KEURO, at yearly economic conditions.

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page 2 of 5 

Procurement Policy: 

C 

= Open Competitive Tender; (Ref. Article 5.1 ESA Contract 

Regulations). 

C(1)* = Activities in open competition limited to the non-Large-System 

Integrators. 

Note: In these activities, LSIs are not allowed to submit prime 

proposals to ESA. LSIs can participate as subcontractors. In this 

case, the proposal must demonstrate that: 

- the tasks assigned to the LSI do not constitute the core 

activities of the proposed development; 

- The technical expertise provided by the LSI is essential to the 

activity; 

- the non-LSI in the team retains the key capabilities to develop 

and exploit the results of the technology activity; 

- the presence of the LSI in the proposal does not 

undetermined or limit the leading role of the non-LSI in the 

team. 

(Otherwise, the bid will not be considered for further evaluation). 

C(2)* = Activities in open competition, where a significant participation 

of non-Large-System Integrators is requested. 

Note: These activities are open to all potential bidders, LSIs and 

non-LSIs. However, LSIs that submit bids are requested to 

include in those bids a relevant participation of non-LSIs, in 

quality and quantity, in accordance with the ITT guidelines - in 

the form of a percentage range of expected participation of non- 

LSIs – on which the C(2) measure is applied. (Otherwise, the bid 

will not be considered for further evaluation). 

C(3)* = Activity restricted to SMEs & R&D organisations, preferably in 

cooperation. 

The measure is proposed when the technology activity relates to 

early phases of the technology development (TRL

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page 3 of 5 

(judged in terms of quantity indicated as guidelines of the ITT on 

which the C(4) measure is applied). Offers shall provide an 

analysis of the potential advantages of the proposed 

participation (e.g. long-term rospects for future work). If no such 

participation is offered, the bid shall contain evidence of the 

effort made to meet these requirements and the reasons for the 

lack of success. (Otherwise, the bid will not be considered for 

further evaluation). 

C(R) = Competition is restricted to a few companies, indicated in the 

"Remarks'' column; (Ref. Article 5.2 ESA Contract Regulations). 

DN/S = Direct Negotiation/Specialisation; the contract will be awarded 

by direct negotiation in implementation of a defined industrial 

policy or resulting from a sole supplier situation (Ref. Articles 

6.1.A,D,F ESA Contract Regulations). 

DN/C = Direct Negotiation/Continuation; the contract will be awarded in 

direct negotiation being the immediate continuation of a previous 

activity with the same contractor (Ref. Article 6.1.C ESA 

Contract Regulations) 

Country: 

Remarks: 

Prime contractor country 

Provides information on Prime contractor and sub-contractors in case the 

activity is contracted or gives other additional info. 

Chapter 3 provides the descriptions of the activities. The Technology Activity Template provide 

following information: 

Description: 

Deliverables: 

Current TRL: 

Target TRL: 

Describes the activity, providing the context information, the purpose of 

the activity and the main tasks. 

Provides short description of the tangible outcome e.g. breadboard, 

demonstrator, S/W, test data. A final report is standard for every 

activity. 

Describes the current NASA TRL level of the product that is going to be 

developed in this activity. 

The NASA TRL level expected for the product at the end of the activity. 

For equipments TRP usually concludes with TRL 3, GSTP at level 5/6. 

However in the case of components target TRL level in TRP could be 

higher. It is also understood that TRL levels do not apply to S/W and tools.

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page 4 of 5 

For these cases description of SW quality, i.e: architecture, beta version, 

prototype, or full operational, achieved at the end of the activity. 

Application Need/Date: 

Describes the required TRL level and date for the technology development 

of which the respective activity is part of on the base of the maturity 

required by the application. The general rule is that a requirement specifies 

the need date for a product. For equipments/payloads this is in general 

TRL 5/6, - the level generally required for Phase B of a project. The 

exceptions are components, where TRL 8 (flight readiness) should be 

achieved. For S/W and tools separate readiness levels are defined below 

Application/Mission: Describes the first possible mission/application/follow-on and the flight 

date. 

Technology Readiness Level, as stated by NASA, to be achieved at end of the activity for 

TRL1 - Basic principles observed and reported 

TRL2 - Technology concept and/or application formulated 

TRL3 - Analytical and experimental critical function and/or characteristic proof-of-concept 

TRL4 - Component and/or breadboard validation in laboratory environment 

TRL5 - Component and/or breadboard validation in relevant environment 

TRL6 - System/subsystem model or prototype demonstration in a relevant environment (ground 

or space) 

TRL7 - System prototype demonstration in a space environment 

TRL8 - Actual system completed and "flight qualified" through test and demonstration (ground 

or space) 

TRL9 - Actual system "flight proven" through successful mission operations 

Readiness Levels for S/W and tools 

Algorithm Single algorithms are implemented and tested to allow their characterisation 

and feasibility demonstration. 

Prototype A subset of the overall functionality is implemented to allow e.g. the 

demonstration of performance. 

Beta Version Implementation of all the software (software tool) functionality is complete. 

Verification & Validation process is partially completed (or completed for 

only a subset of the functionality). 

S/W Release Verification and Validation process is complete for the intended scope. The 

software (software tool) can be used in an operational context.

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page 5 of 5 

TECHNOLOGY R&D 

Research & feasibility 

demonstration 

CAT. A 

predevelopment 

prequalification 

Innovative/Prospective 

Technology 

T.R.L. 1-2 

TRP 

Support to Programmes & 

Generic Technologies 

T.R.L. 3 T.R.L. 4 and/or T.R.L. 5 

CAT. B 

Support to Industry’s 

Competitiveness 

(Short Term) 

T.R.L. 4 and/or T.R.L. 5 

CAT. C 

ESA Technology Landscape (NASA TRL's) 

Contract Duration: 

Dossier 0 Reference: 

SW clause applicability: 

Duration of the activity (e.g. 24 month) 

Identifies the related Dossier 0 (ESTER) Requirement 

Special approval is required for activities labelled: 

either “Operational Software” or “Open Source Code”, 

for which the Clauses/sub-clauses 42.8 and 42.9 (“Operational 

Software”) and 42.10 and 42.11 (“Open Source Code”) of the 

General Clauses and Conditions for ESA Contracts (ESA/C/290, 

rev.6), respectively, are applicable. 

Consistency with Harmonisation Roadmap and Conclusions: 

Consistency with any related Harmonisation Roadmap or Dossier or 

Conclusion report, if applicable.

f 

Chapter 2 

TRP Work Plan 2005-2007 



12/Feb/09




12/Feb/09 

1.- Earth Observation 

1.1 - Data exploitation 

IPC 

Appr. 

TRP Ref. Title Budget (K€) PP C'try Remarks 

SW Clause 

applicability 

Status as of Contract 

2004 2005 2006 2007 2008 31/12/2008 

Y2004 T101-07GD Image Information Mining 1200 

C(1) / 

C(4) 

I 

ACS, U. Trento + SARMAP (CH) + 

CNES (F) + DLR (D) 

- Contracted 20433 

Y2004 T101-08GD Mission Planning for Constellations and Multi-use 400 C F EADS-Astrium - Contracted 19480 

Y2004 T101-09GD EO data archives: Improved access and presentation 400 C(4) - Intended 

Total 1.1 - Data exploitation 400 1,200 400 

Page 1 of 97




12/Feb/09 


1.2 - Microwave Instruments 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T102-01EE Multi-frequency feeds for Earth Observation applications 300 C F EADS-Astrium, IEEA - Contracted 20158 

Y2006 

T102-03EE 

Rigorous numeric techniques applied to microwave interaction with natural targets: 

volume scattering 

150 C F Cert/Onera, Noveltis 

Open Source 

Code 

Contracted 20449 

Y2004 T102-04EE KU Band SAR Snow Measurements for Snow Applications 150 C(1) A 

ENVEO + VEXCEL (GB) + U. 

Helsinki (Fin) + Noveltis (F) 


Y2004 T102-04EE KU Band SAR Snow Measurements for Snow Applications 135 C(1) N NORUT - Contracted 18595 

Y2006 T102-05ET Microwave Photonics Millimetre-wave Generation 250 C F 

TRT + Un. Duisburg (D) + Thales 

Sys (F) 


Y2004 T102-07ET P-Band Ice Sounding Radar Demonstrator Development 300 C(2) TU Denmark - Contracted 19307 

Y2006 T102-10ET GaN Highly Efficient HPA for X- and Ku-band SAR and Altimeter Applications 450 C I 

Thales Alenia Space + 

UMS(D)+Thales Alenia 

Space(F)+Thales 

Detexis(F)+Un.Bologna(I) 


Y2006 

/ 

Y2007 

T102-11ET GaN Self Protected LNA for X- and ku-band Radar Applications 350 C UK Budget increased // Qinetiq - Contracted 21794 

Page 2 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T102-12EE Innovative Low-loss FSS structures 450 17 C(1) UK RAL, Astrium, U. Belfast - Contracted 19854 

Y2006 T102-14ET LNAs for mm-waves 350 C Fin 

DA Design + FHG (D) + Millilab 

(Fin) 


Y2006 T102-16ET HBV multipliers for high power and high frequency 350 C S 

Wasa Millimeteer, Un. 

Chalmers+Astrium (D) 


Y2006 T102-17ET Integrated Schottky structures 400 C D ACST+RPG(D) - Contracted 21628 

Y2006 T102-18ET New Investigations of RF breakdown in microwave transmission lines 250 C(1) E 

Aurora Safety & Testing, Un. Polit. 

Cartagena, RYMSA + EPFL (CH) 

Open Source 

Code 


Y2006 T102-22ET Active calibration for radiometers 200 C F Astrium, LAAS - Contracted 21313 

Y2006 T102-23EE P-band SAR wave interaction and information retrieval 200 C(3) F 

Un. P. Sabatier, Cert/Onera + DLR 

(D) + Un. Wageningen (NL) + Un. 

Chalmers (S) 


Y2005 T102-28ET Development Schottky MMICs for high frequencies 475 C(1) IRL 

Farran Technology, Tydal + UMS 

(F) 


Page 3 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2005 T102-28ET Development Schottky MMICs for high frequencies 430 8 C(1) UK 

RAL, Un. Bath + Observatoire de 

Paris, EADS-Astrium (F) 


Y2004 T102-29ET Active Receive-Only Digital Front-End for Radar and SAR - Phase 1 & 2 700 60 DN/S D EADS-ASTRIUM + Subco - Contracted 19468 

Y2004 T102-30EE Next Generation L/S band SSPA Demonstrator for Radar 350 C(2) F 

Alcatel + Un. Limonge, Amcad 

Engineering, UMS 


Y2006 T102-32EE Understanding directionality in surface scattering by imaging radar 150 C(1) CH 

Gamma Rem Sensing + CNR (I) + 

Un. Munchen (D) 


Y2006 T102-41ET Altimetric Measurements of 2D Ocean Surface Currents 150 C E 

Starlab 

Barcelona+Ifremer(F)+Astrium(UK) 


Y2006 T102-43ET Integrated Receiver and ADC for Active Array SAR 400 C Fin 

VTT + DA-Design (Fin) + TU 

Helsinki (Fin) 


Y2006 T102-44ET Research into GPS Sea-Ice and Dry Snow Reflectometry 300 C(3) E 

IEEC + GFZ (D) + IFAC (I) + AD 

Telecom (E) 


Y2006 T102-45ET Advanced SAR-Instrument based on Digital Beamforming 150 C D Astrium, DLR+TU Denmark (DK) - Contracted 21079 

Page 4 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T104-17EE 

Bio- & geo-physical retrieval algorithm definition for active remote sensing of land 

surfaces at P- and L-band 

200 C(3) D 

DLR+Onera (F)+SARVision 

(NL)+AEL Consultants 

(UK)+Un.Wales 


Total 1.2 - Microwave Instruments 285 1,350 2,255 858 2,927 

Page 5 of 97




12/Feb/09 


1.2.1 - Microwave Equipment & Antennas (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2001 ETM-157 HBV devices 200 DN/S F U. Lille - Contracted 18164 

Y2002 ETP-111 Novel Simulation Interferometric radar altimeter 150 C(1) 

CLS, Alcatel, Boots Technologies 

+ Starlab Barcelona (E) 


Y2000 ETP-137 PARIS: additional work 50 C UK 

Astrium - C under prime for 

ETP-137A 


Y2000 ETP-137.A PARIS Technology Concept Definition/Integration - Phase 2 242 400 DN/C UK Astrium - Contracted 16110 

Y2000 ETP-137.B PARIS multi-beam array 300 C UK 


ETP-137A 


Y2000 ETP-137.C Beam Forming Networks for PARIS Concept 500 C UK 


ETP-137A 


Y2000 ETP-137.D PARIS Receiver and Signal Processor 500 C UK 


ETP-137A 


Y2002 ETP-153 New Radiometer concepts: Active Cold Load for Radiometer Calibration 300 C(2) Fin Ylinen +TUD (DK) - Contracted 18907 

Page 6 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 ETP-163.C L-Band Radiometry / Advanced Filter and Correlator integration and validation 590 120 DN/C E CASA, UPCA + U. Hel. (Fin) - Contracted 15138 

Y2002 ETP-190 Modular Signal Generation and Detection for Future SAR Instruments 300 C(2) UK 

Com Dev Europe + SEA (UK). 

Only 100kE committed, owing to 

contract closure. 


Total 1.2.1 - Microwave Equipment & Antennas (Source: TRP 

2000-2003) 

1,482 2,000 170 

Page 7 of 97




12/Feb/09 


1.3 - Optical Instruments 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T103-01FP High efficient Laser Pump Source for LIDAR Applications 600 C(1) I CESI, GA, Scimex - Contracted 18949 

Y2004 T103-02FP Pulsed laser source in NIR for LIDAR applications 300 C(1) F Onera, LMD + NEO (N) + CSIC (E) - Contracted 19813 

Y2004 

T103-03M 

M 

NIR Detector for LIDAR Applications 400 C(1) UK 

SSTL, U. Heriott-Watt, U. 

Sheffield, Hovemere 


Y2006 

/ 

Y2007 

T103-10GD Back-illuminated thinned CMOS imager focal plane 500 C(2) 

Increased budget, 500kE TRP + 

300kE EO 

- Intended 

Y2006 

T103-11EE 

Enhanced Quantum Well Infrared Photodetector (QWIP) Array Detector: Definition 

and optimisation 

750 C(1) F 

Alcatel Thales III 

Vlab+IMEC(B)+Astrium(F) 


Y2004 

T103-13M 

M 

L3CCD/EMCCD Technology for LIDAR Applications 300 DN/S UK 

EEV, 500kE to be funded by 

EOEP; see ESA/IPC(2004)1, 

add.23 


Y2004 T103-16FP Ultra-compact medium-resolution spectrometer for land application 570 DN/C I 

GA, ENEA + E2V (UK) + Ecole 

Nat. Sup. Phys. (F) 


Y2006 

T103-24M 

M 

Next Generation panchromatic detectors 800 C(2) - Intended 

Page 8 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T103-25M 

M 

Reliable space-compatible pump laser diodes 800 C F Nuvonyx + Osram - Contracted 20529 

Y2006 

T103-25M 

M 

Reliable space-compatible pump laser diodes 770 C UK Intense - Contracted 20642 

Y2006 

T103-26M 

M 

Laser interferometry high-precision tracking for LEO 400 C I 

Alenia Spazio + Ist. Metr. 

Colonnetti 


Y2006 

T103-27M 

M 

Large format APS detectors with on-chip intelligence for lightning imaging 600 C(2) F 

Astrium + Inst Sup Aeronautique et 

Espace (F)+SSTL(UK) 


Y2006 

T103-28M 

M 

High Energy Fiber-based Laser and Receiver development in the 2 micron region for 

atmospheric CO2 and other greenhouse gases measurements 

600 C(1) UK 

Qinetic+Crystal Fibre 

(DK)+NPL(UK) 


Y2006 

T104-13M 

M 

Instrument technology for fluorescence 300 C UK 

ABSL Space Products + 

Astrium(F)+Lidar 

Technologies(UK) 


Y2006 T104-15EE Vegetation Fluorescense Retrieval Algorithm 200 C D 

FLEX Mission. GFZ Postdam + 

Un.Polit.Vanlencia (E) + NLR (NL) 


Y2006 

T104-16M 

M 

Non-linear Laser Crystal Development for Frequency Conversion 400 C(1) D DLR + IHB (D) - Contracted 21747 

Page 9 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T104-18EE 

Aerosol modeling and synergetic aerosol correction algorithms for passive optical/IR 

sensors 

200 C(3) NL 

Argoss+Un.Bremen (D)+Finnish 

Meteorological Institute (FIN) 


Y2006 T104-20QC SWIR Laser Diodes 200 C E Tecnologica - Contracted 21957 

Total 1.3 - Optical Instruments 900 2,470 1,170 4,150 

Page 10 of 97




12/Feb/09 


1.4 - Platforms/ Other Instruments 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T104-02EE Very large space antenna aperture - architecture trade off 300 C F Alcatel + Kayser Threde (D) - Contracted 20392 

Y2004 T104-02EE Very large space antenna aperture - architecture trade off 300 C UK 

Astrium, Vexcel, U. Cambridge, 

BAE 


T104-07MC Array Antenna Based on Inflatable Technology 

C 

350kE. Postponed after 

T104-02EE. 

- Deferred 

Y2005 

T104-11FP 

Autonomous High Data Rate Secured Downlink System - Breadboard (Old title: High 

Data Rate Downlink Data Processor Chain – Breadboard) 

400 C - Intended 

Total 1.4 - Platforms/ Other Instruments 600 400 

Page 11 of 97




12/Feb/09 


1.4.1 - Lidar (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 EEO-003 Solid State Phase Conjungation 600 C F 

Thales. Combined with 

T-M-QCA-08-04 

- Closed 18284 

Y2001 

T-M-QCA-0 

8-04 

Radiation testing and evaluation for Core Laser Technologies (CHOCOLATE) 200 C(1) F 

Thales Research & Technology + 

CEN(B), Univ. Liege (B). 

Combined with EEO-003 


Total 1.4.1 - Lidar (Source: TRP 2000-2003) 800 

Page 12 of 97




12/Feb/09 


1.4.2 - Instruments and Sensor Breakthrough (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 EEA-044 Geo Atmospheric Sounder Ph.1 500 C(2) D EADS + Tikra(DK) + RAL(UK) - Closed 17924 

Y2002 EEA-044 Geo Atmospheric Sounder Ph.1 500 C(2) S Omnisys, Saab - Closed 17923 

Y2002 EEA-044 Geo Atmospheric Sounder Ph.2A 1400 DN/C S Omisys, Saab - Contracted 19449 

Y2002 EEA-044 Geo Atmospheric Sounder Ph.2B 1100 DN/C S Omisys, Saab - Contracted 19449 

Total 1.4.2 - Instruments and Sensor Breakthrough (Source: TRP 

2000-2003) 

1,000 1,400 1,100 

Page 13 of 97




12/Feb/09 


1.4.3 - Earth Observation P/L (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 MME-003 

Laser-cooled Atom Sensor for Ultra-High-Accuracy Gravitational Acceleration and 

Rotation Measurements 

147 C(1) D U. Hannover - Contracted 18330 

Y2002 MMO-624 Advanced LIDAR concepts 200 C I C. Gavazzi, INFR, INOA - Contracted 18944 

Total 1.4.3 - Earth Observation P/L (Source: TRP 2000-2003) 347 

Page 14 of 97




12/Feb/09 


1.4.4 - Payload Data Exploitation (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

PDE-KEO- 

001 

Knowledge Centred Earth Observation - Phase 1 700 C I 

ACT + DLR (D) +CNES (F) + GDT 

(E) 


Y2003 

PDE-KEO- 

001 

Knowledge Centred Earth Observation - Phase 2 600 DN/C I 

ACT + DLR (D) +CNES (F) + GDT 

(E) 


Y2002 

PDE-User- 

05.B 

Multiple Image Registration - MIR 150 DN/S N Norwegian Comp. (follow-on) - Contracted 18341 

Total 1.4.4 - Payload Data Exploitation (Source: TRP 2000-2003) 850 600 

Page 15 of 97




12/Feb/09 

2.- Science / Robotic Exploration Preparation 

2.1 - Missions in Development Phase: BEPI-COLOMBO 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T201-02M 

M 

Development of microlasers for laser altimetry on future planetary orbiters 650 C(1) D Zeiss Optronik - Contracted 19351 

Y2004 

/ 

Y2007 

T201-03SC Breadboard & Demonstrator of a Micro-pore Optics 550 74 

C(1) + 

DN/C 

F 

Photonis + Un. Leicester (UK) + 

Cosine Research (NL) 


Y2004 T201-04SC Scintillator sensor development 600 DN/S NL 

Consortium led by Cosine 

Research (NL) + 500K€ CTP 


Y2004 T201-06SC Active Pixel Sensor Focal Plane Assembly for NIR 547 C(1) F Sofradir - Contracted 19606 

Y2004 

/ 

Y2007 

T201-06SC Active Pixel Sensor Focal Plane Assembly for NIR - Additional work 150 DN/C F 

Sofradir. Equally cofunded TRP + 

CTP (SCI). 


Total 2.1 - Missions in Development Phase: BEPI-COLOMBO 2,347 74 150 

Page 16 of 97




12/Feb/09 


2.2 - Missions in Pre-Assessment Phase: Darwin 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 MMO-630 High Precision Optical Metrology 700 DN/C F 

Astrium (F) +Astrium (D) + TNO 

(NL) 

- Contracted 

T203-02ES Formation Flying Control and Avionics 

Postponed, awaiting System Study 

results. 500 K€ 

- Deferred 

Y2005 

T203-06M 

M 

Passive optical components for interferometry 1,500 C(2) - Intended 

Y2004 

T203-08MC Solid cryogen cryostat 



- Deferred 

Y2006 T203-09SC Wavefront tilt sensor 500 C(2) - Intended 

Y2005 

T203-11M 

M 

Integrated optics 1000 C F 

Thales Alenia Space + INIST (F) + 

LVC (F) + In. Charles Gerhard (F) 

+ Inst. Nationale Polytechnique 

Grenoble (F) 


Y2004 T203-13SC Pressure Regulator for Cold Gas Micropropulsion C 



- Deferred 

T203-16M 

M 

Development of compact absolute distance metrology system C(2) 500kE. Postponed - Deferred 

Page 17 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

T203-17M 

M 

Fibre coupled acousto-optical modulator C(1) 500kE. Postponed - Deferred 

T203-18MP Formation Flying electric propulsion system 1,400 C Postponed awaiting system study. - Deferred 

Y2006 

T203-19M 

M 

FIR linear Detector Array 2,000 C(1) Phased Activity - Intended 

Y2006 

T203-20M 

M 

Single mode waveguide 1000 C D+NL 

Change in PP. Astrium + Fibre 

Photonics (UK) 


Y2006 

T203-20M 

M 

Single mode waveguide 1000 C NL 

Change in PP. TNO+LVC(F)+Un. 

Southampton(UK) 


Total 2.2 - Missions in Pre-Assessment Phase: Darwin 3,700 5,400 

Page 18 of 97




12/Feb/09 


2.2.1 - Darwin (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 EEO-048 BiB detector 350 35 C B IMEC + Alcatel (F) - Contracted 18599 

Y2001 MMO-632 Fiber optical wavefront filtering 500 36 C(2) N 

Kongsberg + Alcatel, Onera (F) + 

Sintef (N) 


Y2001 MMO-632 Fiber optical wavefront filtering ph.1 100 C(2) CH 

Contrvaves + Astrium, U. Stuttgard 

(D) + U. Wien (A) + TNO (NL) 


Y2001 MMO-632 Fiber optical wavefront filtering Ph.2 400 C(2) CH 

Contrvaves + Astrium, U. Stuttgard 

(D) + U. Wien (A) + TNO (NL) 


Y2003/ 

Y2006 

MMO-634 High Stability Optical Benches for Darwin 1,000 C Increased budget - Intended 

MMS-987 Darwin Solar Array/Solar Shade C 

Deferred, awaiting System Study 


- Deferred 

Total 2.2.1 - Darwin (Source: TRP 2000-2003) 950 400 36 35 1,000 

Page 19 of 97




12/Feb/09 


2.3 - Missions in Pre-Assessment Phase: XEUS 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T204-03M 

M 

High performance X-ray optics 1199 C(2) NL 

Cosine Research + SRON (NL) + 

Max Planck Institut (D) + Danish 

National Space Center (DK) + 

Kayser-Threde (D) + Micronit (NL) 


Y2006 

T204-04M 

M 

Micropore baffle 400 C(2) - Intended 

Y2006 T204-06SC Low bandgap superconducting sensor 600 C(1) - Intended 

Y2006 

T204-07M 

M 

TES Spectrometer 700 C(1) - Intended 

Y2006 T204-08MC 50mK Continuous Cooling System 400 40 C F CEA - Contracted 21227 

Y2006 T204-08MC 50mK Continuous Cooling System 440 C UK Astrium - Contracted 

Total 2.3 - Missions in Pre-Assessment Phase: XEUS 1,599 2,180 

Page 20 of 97




12/Feb/09 


2.3.1 - XEUS (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


Y2002/ 

Y2006 

2004 2005 2006 2007 2008 31/12/2008 

Readdressing and splitting of the 

original activity. SRON+Physikalish 

SCI-X10.a Superconducting Read Out for Microcalorimeters 300 C(1) NL Tech 


Bundesan(D)+VTT(FIN)+INAF(I),T 

hales 

Y2002/ 

Y2006 

SCI-X10.b Superconducting Read Out for Superconducting tunnel junctions 500 C(1) 

Readdressing and splitting of the 

original activity 

- Intended 

Y2007 SCI-X11 Large Format Detector Read-Out - Additional work 400 DN/C I Thales Alenia Space - Contracted 17189 

Y2001 SCI-X4 Optical rejection filter 300 C(1) FIN Metorex - Contracted 18122 

Y2002 SCI-X8 Multilayer coatings for high energy 251 C(1) I MediaLario - Contracted 18023 

Total 2.3.1 - XEUS (Source: TRP 2000-2003) 551 700 500 

Page 21 of 97




12/Feb/09 


2.4 - Long Term Mission / Technology Reference Missions: Gamma Ray Imager 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2005 T206-01SC Gamma Ray Optics Development 400 C I 

Thales Alenia Space + Un. Paul 

Sabatier (F) + IKZ (D) + Inst. Laue 

Langvin (F) 


Total 2.4 - Long Term Mission / Technology Reference Missions: 

Gamma Ray Imager 

400 


2.5 - Long Term Mission / Technology Reference Missions: Venus Entry Probe 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T210-01M 

M 

A thin balloon envelope for harsh environments C(1) Deferred (not in Cosmic Vision) - Deferred 

Total 2.5 - Long Term Mission / Technology Reference Missions: 

Venus Entry Probe 

Page 22 of 97




12/Feb/09 


2.6 - Other Technologies / Missions 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T214-05SC High Resolution, Low Mass, Pore Optics 850 C(1) D 

Kayser-Threde + Cosine Research 

(NL) 


Y2004 T214-05SC High Resolution, Low Mass, Pore Optics: additional work 173 DN/C D 


(NL) 


Y2006 T214-05SC High Resolution, Low Mass, Pore Optics: additional work 197 DN/C D 


(NL) 


Total 2.6 - Other Technologies / Missions 850 173 197 

Page 23 of 97




12/Feb/09 


2.7 - GAIA (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 SCI-G16 Optimum Compression Algorithm 200 C E 

GTD Sistemas de Informacion, 

IEEC 

Open Source 

Code 


Total 2.7 - GAIA (Source: TRP 2000-2003) 200 

Page 24 of 97




12/Feb/09 


2.8 - Cosmic Vision 2025 (Solar Orbiter, WFI, ..) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T202-01M 

M 

Solar Blind sensor 600 C SOLO/SPO missions - Intended 

T215-01M 

M 

NIR large format sensor array 1500 C 

WFI mission. Deferred. Moved to 

TRP 2008-2010. 

- Deferred 

Y2006 T215-02MC Solar sails Materials 400 C(1) L SPO/IHP missions - Contracted 

Y2006 

T215-03M 

M 

Low bandgap EUV sensor 500 C(1) - Intended 

Y2006 

T215-04M 

M 

Planetary surface Dating Instrument (Luminescence dating) 600 C(2) DK 

NEO mission // TU Denmark + 

Cosine (NL) + TU Denmark (DK) 


Y2006 T215-05EE Jupiter Radiation Environment and Effect Tools 400 C UK 

Jupiter mission // Qinetiq + Onera 

(F) + DH Consultancy (B) 

Operational 

SW 


Y2006 T215-06EP High radiation tolerant Low Intensity Low Temperature GaAs solar cells 500 50 C D 

Jupiter mission. Azurspace, 

FHG+CESI (I) 


Y2006 

T215-07M 

M 

Demonstration of the deployment of a highly integrated low power ice penetrating 

radar antenna 

600 C(2) Jupiter mission - Intended 

Page 25 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T215-08EE Wideband Spectrometer 250 C D MPAE - Contracted 21142 

Y2006 T215-08EE Wideband Spectrometer 250 C UK 

Astrium+Astrium(F)+RAL(UK),Un. 

Dundee 


Y2000 

/ 

Y2006 

T215-09MC H2 Sorption Cooler 600 DN/C NL Un. Twente - Contracted 21348 

Total 2.8 - Cosmic Vision 2025 (Solar Orbiter, WFI, ..) 2,900 3,350 

Page 26 of 97




12/Feb/09 

3.- Human Spaceflight Manned Exploration 

3.1 - Advanced habitats 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T301-03MC Design Verification & manufacturing aspects relevant for inflatable Modules 800 C(2) I 

ALS + Aero Sekur + LTA 

Technologie (D) + Samtech (B) + 

Sener (E) + Austrian Aerospace 

(A) 


Y2004 T301-10MC Polymerisation of Composite Structures in Free Space 300 C(2) F 

EADS-ST + Un. Reims, 

EADS-Astrium + ARCS (A) + M. 

Bernasconi Cons. (CH) 


Total 3.1 - Advanced habitats 1,100 

Page 27 of 97




12/Feb/09 


3.2 - Automation and advanced robotic technologies 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T302-02M 

M 

Compact Automatic Tool Exchange Device 400 C(1) I GA, Tecnomare - Contracted 18774 

Y2004 

T302-08M 

M 

Vision Based Manipulation of non-co-operative objects 300 45 C(1) B 

Trasys, U. Leuven + GA (I) + IRIA 

(F) 


Total 3.2 - Automation and advanced robotic technologies 400 300 45 

Page 28 of 97




12/Feb/09 


3.2.1 - Automation & Robotics (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 MMA-622 Dextrous Robot System - Phase 1&2 700 C(2) CH 

Contraves, HTS, CSEM + Dutch 

Space (NL) 


Y2002 MMA-622 Dextrous Robot System - Phase 1&2 700 C(2) I GA, Tecnomare + Sener (E) - Contracted 18184 

Y2002 MMA-622 Dextrous Robot System - Phase 3 1300 500 C(R) GA, Tecnomare + Sener (E) - Contracted 18184 

Total 3.2.1 - Automation & Robotics (Source: TRP 2000-2003) 1,400 1,300 500 

Page 29 of 97




12/Feb/09 


3.3 - Closed loop life support technologies 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T303-02MC Bioregenerative Life Support Basic Development 250 250 250 DN/C F UPB, Melissa Partners - Contracted 38608 

Y2004 T303-11MC Air Sampling System for Microbial Contaminants Identification 250 C F 

Biomerieux + Statice Etudes et 

Developpement 


Total 3.3 - Closed loop life support technologies 250 250 500 

Page 30 of 97




12/Feb/09 


1.3.1 - Optical/Electro-Optical Technologies (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y1998 97/XAO08 Quantum Well Photodector 150 DN/S S ACREO - Contracted 18264 

Y2002 MMO-635 Assessment of Phasing Capabilities of Fibre Optic Devices 250 35 DN/S A TU Wien - Contracted 37028 

Total 1.3.1 - Optical/Electro-Optical Technologies (Source: TRP 

2000-2003) 

400 35 

Page 31 of 97




12/Feb/09 


3.4 - Crew Health and Performance 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T304-01M 

M 

Integrated Countermeasures for microgravity effects 340 C(2) D 

Novotec + Un. Hospital Freiburg 

(D) + Astrium (D) 


Y2004 

T304-01M 

M 

Integrated Countermeasures for microgravity effects 340 C(2) F 

Medes IMPS + Verhaert (B) + DLR 

(D) + Medessat (F) + Un. Antwerp 

(B) 


Total 3.4 - Crew Health and Performance 680 


3.5 - Free-Flyers (Rendezvous and Docking, In-Orbit Assembly and Servicing) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T306-03M 

M 

Selfcalibrating 3-D optical metrology 200 DN/C UK EM Technology - Contracted 18584 

Total 3.5 - Free-Flyers (Rendezvous and Docking, In-Orbit Assembly 

and Servicing) 

200 

Page 32 of 97




12/Feb/09 


3.6 - Instrumentation for Life Science 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T307-05M 

M 

Immuno-Biochemical Analyser 500 DN/C D 

EADS-Astrium + Diacdem 

Chip-Technologies + NTE (E) 


Y2004 

T307-09M 

M 

Virtual reality stimulator 300 C(1) NL 

Space Application Services + Un. 

Paris Descartes (F) + Un. Brussels 

(B) 


Y2004 

T307-15M 

M 

Life Support Technology for MISS 600 C(2) I Alenia Spazio - Contracted 19133 

Total 3.6 - Instrumentation for Life Science 1,100 300 

Page 33 of 97




12/Feb/09 


3.7 - Instrumentation for Physical Science 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T308-03M 

M 

Oxygen sensing/control 500 DN/C D EADS-ST and Sub ITT - Contracted 19963 

Y2004 

T308-06M 

M 

Enhanced Mini Lda 360 DN/C D 

ZARM-Technik, PTB 

Braunschweig, Laser Zentrum 

Hannover, BT 


Total 3.7 - Instrumentation for Physical Science 360 500 


3.8 - Payload Data Handling 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T310-02ES COTS based space borne computer 1 300 C F 

Thales Alenia Space + Thales 

Alenia Space (I) + Austrian 

Aerospace (A) 

- Contracted 

Total 3.8 - Payload Data Handling 300 

Page 34 of 97




12/Feb/09 


3.9 - Intelligent Space Systems Operation (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 EME-018 SDE and Space Palmtop Applications 200 C D Astrium + Skytek (Irl) - Contracted 18694 

Y2002 EME-018 SDE and Space Palmtop Applications 200 C DK Terma + Siemens (A) - Contracted 18695 

Y2006 EME-019 On-Board Model Checking 200 C I 

Thales Alenia Space + Fond. 

Bruno Kessler (I) + Thales Alenia 

Space (F) 

Operational 

SW 

Intended 20580 

Y2002 ESD-023 Mission Execution Crew Assistant 500 C(1) NL TNO Human Factor 

Open Source 

Code 


Y2002 ETD-037 High Performance Resilient Computer For Autonomous Robotics 750 C(2) I 

ALS, GA + Syderal (CH) + FHG 

(D) 


Y2002 MMA-624 Satellite Servicing Building Blocks 750 75 C(2) F EADS-Astrium - Contracted 19505 

Total 3.9 - Intelligent Space Systems Operation (Source: TRP 

2000-2003) 

1,150 1,250 75 200 

Page 35 of 97




12/Feb/09 


3.10 - Aurora 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2005 03/E15 Experimental and theoretical study of Mars dust effects 250 C D HPS - Contracted 19632 

Y2005 03/W15 Solar cell development for Mars exploration missions 400 C D 

RWE, FHG + Galileo Avionica, 

CESI (I) 


Y2005 03/W25 Solar cell electrical characterization facility for Mars exploration missions 200 DN/S INTA - Intended 

Y2005/ 

Y2006 

03/W35 Martian dust simulation facility for solar cells 400 C DK Change in PP. Un.Aarhus - Contracted 21285 

Y2005 04/G15 Precision landing GNC test facility 1000 C I 

CGS, Un. Padova, Un. D'Annunzio 

+ EADS-Astrium (F) + 

OHB-Systems (D) + Scisys (UK) + 

GMV (E) 

Operational 

SW 


Y2005 

04/G25 + 

T306-01ES 

Autonomous Rendez-vous GNC test facility + Integrated Multi-Range Rendezvous 

Control System 

1000 C E 

GMV, Sener + Skysoft (P) + 

Alcatel (F) + Alenia (I) 

Operational 

SW 


Y2005 

04/G25 + 

T306-01ES 



580 C F EADS-Astrium 

Operational 

SW 


Y2005 04/K15 Mars climate database and physical models 350 DN/C F 

LMD/CNRS + U. Oxford (UK) +IAA 

(E) 


Page 36 of 97




12/Feb/09 


3.10 - Aurora 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 04/K15 Mars climate database and physical models 18 DN/C F LMD/CNRS 

Operational 

SW 


Y2005 04/K25 Martian radiation environment models 400 C UK - Contracted 19770 

Y2005 04/K35 Cleaning / sterilisation technologies 213 C DK Lytzen - Contracted 21367 

Y2005 04/T45 Passive variable thermal conductance device for Mars rover applications 300 C F 

EADS-Astrium + EADS-Astrium 

(UK) + Euro Heat Pipes (B) 


Y2005 T213-01SC Water sensor for Mars Exploration 600 C UK 

Open University +NEO, Novsys (N) 

+ Stella Polaris (P) 


Y2004 

T213-03M 

M 

Sampling drill tools for rocky and granular soils 150 C - Intended 

Y2005 

T213-04M 

M 

Ultrasonic Tools for Planetary Surface Exploration 300 49 C(1) UK Magna Parva - Contracted 20314 

Y2004 

T213-06M 

M 

Imaging Lidar technology 900 C(4) D Jena-Optronik - Contracted 19635 

Page 37 of 97




12/Feb/09 


3.10 - Aurora 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T213-06M 

M 

Imaging Lidar technology 900 C(4) UK ABSL, Hovemere + Sensl (IRL) - Contracted 19603 

Y2004 

T213-07M 

M 

Down hole hammering Mechanism 250 C(1) I GA + TU Helsinki (N) - Contracted 19294 

Y2005 

T213-08M 

M 

Biochemical analyser 150 C(1) D ESE, Diacdem Chip-Technologies - Contracted 20389 

Total 3.10 - Aurora 1,750 5,648 400 612 

Page 38 of 97




12/Feb/09 

4.- Space Transportation / Re-entry Technologies 

4.1 - Materials and Structures / Advanced Hot Structures and Thermal Protection Systems 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T401-02MC Damage Tolerance of Cryogenic Pressure Vessels 200 C D 

MT Aerospace, DLR, Un.Stuttgart 

+ Inegi (P) 


Total 4.1 - Materials and Structures / Advanced Hot Structures and 

Thermal Protection Systems 

200 


4.1.1 - Structures & Thermal Protection (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/MCS-00 

1 

Full Scale structure Qualification Methodologies 1500 104 DN/S I ALS, CIRA + MAN (D) - Contracted 16751 

Y2002 MCT-998 Smart Thermal Protection System 400 C E INASMET +ALTA(I) + EADS(F) - Contracted 17799 

Total 4.1.1 - Structures & Thermal Protection (Source: TRP 

2000-2003) 

400 1,500 104 

Page 39 of 97




12/Feb/09 


4.2 - Materials and Structures / Advanced Materials 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T403-02Q 

M 

High temperature complex parts based on intermetallic components 200 C E 

Inasmet (E) + Qinetiq (UK) + 

Snecma (F) 


Y2004 T403-03MC Multiphysic Modeling of Near-surface Phenomena 200 40 C I Un. Roma - Contracted 19168 

Y2004 

T403-03MC 

.B 

Multidisciplinary Modeling of Fluid Structure Interaction 205 40 DN/S IRL ESIL, Special Measure IRL. - Contracted 19631 

Y2004 T403-09MC Increase of Bolted Joint performance for CFRP 500 C D 

DLR, HPS, Kayser-Threde + 

Contraves (CH), INEGI (P) + 

CASA (E) 


Y2005 T403-14MC Cryogenic Composite Tanks and Lines 400 DN/C A 

Magna Steyr, Special Measure 

Austria. (+150kE GSTP) 


Total 4.2 - Materials and Structures / Advanced Materials 605 500 400 80 

Page 40 of 97




12/Feb/09 


4.3 - Materials and Structures / Advanced Structures 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T405-01MC Non-destructive inspection methods for re-usable CFRP structures 250 C - Intended 

Total 4.3 - Materials and Structures / Advanced Structures 250 

Page 41 of 97




12/Feb/09 


4.4 - Propulsion / Advanced Liquid Propulsion 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 MPC-846 Acquisition and Evaluation of Cryo-Solid Propulsion: Additional Testing 140 DN/C D 

Aerospace Institute - LO, ADIRIM 

& PARTNERS 


Y2004 T402-05MP Scaling of Thermal Cavitation Effects on Cavitation-Induced Instabilities 350 40 C(1) I 

Alta + Inst. Nat. Pol. Grenoble (F) 

+ Un. Pisa (I) 


Y2004 

T402-10MP 

Unsteady subscale force measurements within a launch vehicle base buffeting 

environment 

450 C(1) D 

DLR, 

Astrium+Astrium(F)+Onera(F)+NL 

R(NL) 


Total 4.4 - Propulsion / Advanced Liquid Propulsion 940 40 

Page 42 of 97




12/Feb/09 


4.5 - Propulsion / Advanced Propulsion Concepts for In-Space Operations 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T404-02MP Technical Assessment for High Power Magneto Plasma Dynamics (MPD) Systems 300 C I 

Alta + Un.Stuttgart (D) + Snecma 

(F) 


Y2004 T404-03MP Advanced Electric Propulsion for a Service Module for VEGA 350 C I Elv + others - Contracted 20072 

Total 4.5 - Propulsion / Advanced Propulsion Concepts for In-Space 

Operations 

350 300 


4.6 - Propulsion / Air-breathing Propulsion 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T407-01MP Design of Flight Test Configuration for High-speed Airbreathing Propulsion 650 C D 

DLR, EADS-ST + Imperial College, 

Fluid Gravity, CGC Technology, 

Gas Dynamics (GB) + SSC (S) 


Total 4.6 - Propulsion / Air-breathing Propulsion 650 

Page 43 of 97




12/Feb/09 


4.7 - Propulsion / Solid Propulsion 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T402-08MP Cryogenic RCS thruster technology C 

385kE, postponed to mid 2007, 

awaiting system study. 

- Deferred 

Y2006 T411-01MP Hybrid propulsion evaluation for liquid booster application 250 C F SNPE + Avio(I) - Contracted 20676 

Y2004 T413-01MP Experimental demonstration of opto-pyro systems for launcher applications 400 45 C(1) CH Contraves - Contracted 20363 

Y2004 T413-01MP Experimental demonstration of opto-pyro systems for launcher applications 400 278 C(1) N KDA + EADS-ST (F) - Contracted 19800 

Total 4.7 - Propulsion / Solid Propulsion 800 250 323 

Page 44 of 97




12/Feb/09 


4.7.1 - Propulsion Technologies (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2000 MMM-956 Journal bearings for turbopumps 400 C F 

Snecma + Un. Liege (B) + Aea 

Technology (UK) + Energie 

Technologie, MAN (D) + Avio (I) 


Total 4.7.1 - Propulsion Technologies (Source: TRP 2000-2003) 400 

Page 45 of 97




12/Feb/09 


4.8 - Aerothermodynamics (ATD) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T406-04MP CFD validation in CO2 environment 350 C D 

DLR + Onera (F) +VKI (B) + FG 

(UK) 


Y2004 T406-04MP CFD validation in CO2 environment 350 C UK 

Fluid Gravity + U. Stuttgart (D) 

+EADS, U. Provence (F) 


Y2004 

T406-09MP 

Development and qualification of in Flight Test Measurement (FTM) techniques: 

Electron Beam Fluorescence fo Aerothermodynamic Applications 

200 C F Onera - Contracted 20454 

Y2004 

T406-09MP 


Nose & Payloads 

1025 C D 

DLR, U. Stuttgart + CIRA + 

Hyperschall Technologie 

Goettinger 


Y2004 

T406-09MP 


Nose & Payloads 

930 C I 

CIRA, Alta + DLR, Hyperschall 

Technologie Goettinger (D), Onera 

(F), VKI (B) 


Y2004 T406-12MP Preparation of an electrodynamic-heatshield flight experiment 200 50 C D EADS-ST, DLR - Contracted 19337 

Y2007 T406-13MP Advanced Methods for Hypersonic plasma - flow control 350 C - Intended 

Total 4.8 - Aerothermodynamics (ATD) 550 2,505 400 

Page 46 of 97




12/Feb/09 


4.8.1 - Aerothermodynamics (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/MPA-00 

1 

In-Flight Aerothermodynamic Measurements 480 DN/S I 

CIRA + DLR(D) + ONERA(F) + 

subs 

- Closed 18125 

Y2003 

/ 

Y2007 

94/8.2.1.4, 

03/MPA-00 

2 

Plasma Radiation Database 105 105 DN/S UK Fuid Gravity - Contracted 11148 

Total 4.8.1 - Aerothermodynamics (Source: TRP 2000-2003) 480 105 105 

Page 47 of 97




12/Feb/09 


4.9 - Avionics and GNC 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T408-01MX 

Modern Guidance Schemes for the Terminal Area Energy Management (TAEM) 

Flight Phase of Reusable Space Transportation Systems 

100 C p Spinworks + Astos Solutions(D) 

Open Source 

Code 


Y2004 T408-06ES Robust Multi-mission Navigator 650 C(2) F 

Astrium, Astrium (D) + AAS (A) + 

Deimos (E/P) +SciSys (UK) 

Open Source 

Code 


Total 4.9 - Avionics and GNC 650 100 


4.10 - Health Management System (HMS) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T410-01MC Health Monitoring system for TPS and Hot Structures 200 C D 

ASTRIUM + Univ. Stuttgart (D) + 

Dutch Space (NL) 


Total 4.10 - Health Management System (HMS) 200 

Page 48 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 MXO-001 Health Management System for Re-usable Space Transportation 700 C(2) D 

Total 4.11 - Intelligent Space Systems Operation (Source: TRP 

2000-2003) 

700 

EADS-ST, DFKI + Alenia, U. 

Roma, Cira (I) + Deimos (E/P) + 

Sctd (NL) + Snecma (F) +U. 

Aalborg (DK) 


5.- Telecommunication / Navigation 

5.1 - Conventional Fixed Telecommunication Service 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

ETM-101 

Surface Treatment and Coatings for the Reduction of Multipactor and Passive 

Intermodulation Phase 2 

200 DN/S D Tesat + UAM (E) - Contracted 17025 

Y2004 T503-03ET RF breakdown in Multicarrier systems 400 C(2) E 

Aurora Safety & Testing, Un. Polit. 

Valencia, Un. Valencia + EPFL 

(CH) + TESAT Spacecom (D) 

Operational 

SW 


Total 5.1 - Conventional Fixed Telecommunication Service 600 

Page 49 of 97




12/Feb/09 


5.2 - Engineering and Verification Tools & Techniques 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T506-01EE European Antenna Modelling Component Library - Telecommunications 450 50 330 250 DN/S DK Ticra + Satimo (I) - Contracted 18802 

Y2004 T506-02MC Modelling of Porous Shells 400 C(4) D 

HPS, Invent, TU Munich + Saab, 

Royal Inst. Technology (S) + Inegi 

(P) 


Total 5.2 - Engineering and Verification Tools & Techniques 450 450 330 250 

Page 50 of 97




12/Feb/09 


5.3 - High capacity multi-beam systems 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T501-02EE Active multi-beam antenna concept using advanced very high order multilayer BFN 250 C(2) I 

Activity reduced in scope - Space 

Engineering, MECSA 


Y2006 

T501-04EE 

Development of high order propagation models for multimedia Satellite 

Communication Systems 

300 C Revised description. 

Operational 

SW 

Intended 

Y2004 T501-06ET High Frequency SIGE MMICS for Converter 500 C D 

Kayser-Threde, IMST, IHP + Saab 

Ericsson (S) 


Y2004 T501-07ET High Reliability MEMS Redundancy Switch 750 C(2) F 

CEA + Thales Alenia Space (F) + 

CNRS (F) + Un Athens (GR) 


Y2004 T501-07ET High Reliability MEMS Redundancy Switch 750 C(2) I 

Fond. Bruno Kessler + Un. Munich 

(D) + CMR IMM (I), Space 

engineering, Thales, Un. Bologna, 

Un. Padova, Un. Perugia 


Y2006 

T501-08EE 

Innovative architectures for reducing the number of controls of multiple beam 

telecommunication antennas 

350 C I 

Space Engineering + Aristotle Univ 

(GR) + CNIT (I) 


Y2004 T501-10ET High throughput highly re-configurable bent-pipe processor for access networks 1500 C(2) F 

Alcatel + Alenia Spazio, Space 

Engineering (I) 


Y2004 T501-10ET High throughput highly re-configurable bent-pipe processor for access networks 500 C(2) UK EADS-Astrium - Contracted 19942 

Page 51 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T501-11EE New concepts for dual-gridded reflectors (study) 400 30 C D 

HPS, Invent, TU Munchen + ASD 

(I) + ASC (DK) 


Y2004 T501-11EE New concepts for dual-gridded reflectors (study) 400 C S Saab Ericson - Contracted 19678 

Y2004 

T501-12ET 

Study of Enhanced digital transmission techniques for Broadband Satellite Digital 

Transmissions 

400 C(2) B Newtec CY - Contracted 19370 

Y2006 T501-14ET Broadband low-power ADC design & prototyping 990 C F 

See ESA/IPC(2006)88. E2V 

Technol., Thales+Astrium (UK 


Y2006 T501-15ET Broadband low-power DAC design & prototyping 900 177 C D 

Total 5.3 - High capacity multi-beam systems 900 2,800 2,650 1,847 

See ESA/IPC(2006)88. Kayser 

Threde, Advico Microelectronics, 

IHP+ Maser 

Engineering(NL)+SAAB Ericsson 

Space(S) 


Page 52 of 97




12/Feb/09 


5.4 - Mobile Communications 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T502-06EE Simulation of the satellite to indoor propagation channel at L and S bands 200 C E - Contracted 19778 

Total 5.4 - Mobile Communications 200 

Page 53 of 97




12/Feb/09 


5.5 - Navigation & Positioning 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T504-02EM Energetic Electron Environment Models for MEO 250 C(1) F Onera + QinetiQ (UK) + SSTL (UK) Operational 

SW 


Y2004 

T504-05GN 

Satellite and station clock modelling for GNSS, link between physical models and 

estimation / prediction processes 

250 C(1) - Intended 

Y2006 T504-08ET Next Generation Compact Atomic Clocks 400 C(1) - Intended 

Y2006 T504-10ET Development of Innovative Atomic Clock for Satellite 500 C(1) - Intended 

Y2006 T504-11ET Signal Processing Techniques and Demonstrator for Indoor GNSS Positioning 600 C(2) D 

IFEN + Sepa (I) + Un Munich (D) + 

Audens Act Consulting (D) + 

Telespazio (I) 


Y2006 T504-11ET Signal Processing Techniques and Demonstrator for Indoor GNSS Positioning 600 C(2) E 

GMV + Skysoft (P) + Un Barcelona 

(E) + Nemerix (CH) + Un Leeds 

(UK) + Thales Alenia Space (F) 


Y2006 T504-14ET Evolutionary Navigation Systems 300 C D 

Astrium+Joann.Research 

Centre(A)+JAST(CH) 


Y2006 

T504-16M 

M 

Development of key Optical Clock technologies 400 C(1) - Intended 

Total 5.5 - Navigation & Positioning 1,200 2,100 

Page 54 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 


5.6 - Satellite / Platform Technologies 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T505-04ES Low Cost Coarse Earth Sensor Development 300 C(1) I Galileo Avionica - Contracted 19555 

Y2006 T505-14EP Fuel cells for Telecom systems 150 C D Astrium+Astrium(F)+QinetiQ(UK) - Contracted 21370 

Y2006 T505-14EP Fuel cells for Telecom systems 150 C F Thales+Prototech(N) - Contracted 21349 

Total 5.6 - Satellite / Platform Technologies 300 300 

Page 55 of 97




12/Feb/09 


5.6.1 - Antenna Technologies (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 EEA-013 Q/V Band Antenna S/S 250 C I Space Eng. - Contracted 18094 

Y2002 EEA-013 Q/V Band Antenna S/S: additional work 49 C I Space Eng. - Contracted 18094 

Y2002 MMM-946 Hybrid mechanical-electronic pointing system 450 C E Sener - Contracted 18186 

Total 5.6.1 - Antenna Technologies (Source: TRP 2000-2003) 700 49 

Page 56 of 97




12/Feb/09 


5.6.2 - On-Board Equipment Technologies (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/ETM-00 

1 

SAW Filter Development (original activity: SAW resonator technology for L and 

S-band space applications) 

300 DN/S N AME - Contracted 13635 

Y2003 

03/ETM-00 

1 

SAW Filter Development (original activity: SAW resonator technology for L and 

S-band space applications) 

200 350 DN/S N 

AME (Special measures for 

Norway) >> continued in TRP 

2008-2010 


Y1998 

/ 2003 

97/XRF02 Tool for high speed end to end system simulation 330 C(2) F 

Astrium + DGRO (D) + Critical S/W 

(P) 


Y2000 EEP-009 Characterization and modeling of Propagagation effect Q/V Band 250 C UK RAL + U. Louvain (B) - Contracted 17841 

Y2001 ETM-080 Cold Cathode TWT 500 C(1) F Thales - Contracted 19388 

Total 5.6.2 - On-Board Equipment Technologies (Source: TRP 

2000-2003) 

880 500 200 350 

Page 57 of 97




12/Feb/09 


5.7.2 - Telecommunication P/L (Source: TRP 2000-2003) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 EEO-010 Technology for optical payloads 350 C(1) E Sener - Contracted 18610 

Total 5.7.2 - Telecommunication P/L (Source: TRP 2000-2003) 350 

Page 58 of 97




12/Feb/09 

6.- Generic Technologies and Techniques 

6.1 - On-board Data Systems 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/EDP-00 

1 

SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A) 450 40 DN/S D Astrium + ATMEL - Contracted 18329 

Y2006 

03/EDP-00 

1 

SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A): enhancement 80 DN/C D Astrium + ATMEL - Contracted 18329 

Y2002 

03/ESD-00 

1 

Rf Wireless Intra-Spacecraft Communications - Phase 1 550 C UK 

SEA+Astrium(F)+Aerospace 

Wireless(NL)+SSC(S)+4Links(UK) 


Y2002 

03/ESD-00 

1 

Rf Wireless Intra-Spacecraft Communications - Phase 2 950 C UK 

SEA+Astrium(F)+Aerospace 

Wireless(NL)+SSC(S)+4Links(UK) 


Y2002 

03/ESD-00 

2 

Optical Wireless-Intra-Spacecraft Communications - Phase 1 500 C E Inta - Contracted 19545 

Y2002 

03/ESD-00 

2 

Optical Wireless-Intra-Spacecraft Communications - Phase 2 1000 C E Inta - Contracted 19545 

Y1998 97/WSP01 Fast Transform DSP Coproc Ph. 2 & 3 600 DN/C D Astrium - Closed 15314 

Y2003 ESD-006 Design & verification of validation techniques for On-Board Microprocessors 500 DN/S S Gaisler Research - Contracted 18533 

Page 59 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 ESD-016 Safeguard Data Recorder 500 C D 

EADS ST + Un. Braunschweig + 

EADS-Astrium (F) 


Y2001 ESD-034 Optical Wireless Data Transmission 500 

C(1) / 

C(4) 

CH 

Contraves, CSEM +UPM, ERZIA 

(CH) 


Y2000 

/ 

Y2006 

ESM-006 High Speed Link Interconnect Network – Additional work 200 DN/C D 

Astrium + Austrian Aerospace (A) 

+ Un. Dundee (UK) 


Y2001 ETD-025 Compact Data Processing Unit 200 C(2) CH Syderal, EPFL - Contracted 18792 

Y2001 

/ 

Y2006 

/ 

Y2007 

ETD-028 Integrated Payload Data Processing System System 250 40 60 C(2) I Aurelia Microelettronica - Contracted 18780 

Y2002 ETD-036 Next Generation Mass Memory Architecture 200 C - Intended 

Y2002 ETD-038 Space wire Controller Remote User 500 77 23 17 10 C(2) S Saab - Contracted 18585 

Y2002 ETD-039 TOPNET: Pilot Operation Implementation - Topnet Deployment 166 C(2) F 

Astrium + Astrium (D) + Astrium 

(UK) + Sodern (F) + Galileo 

Avionica (I) 


Page 60 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 ETD-039 TOPNET: Pilot Operation Implementation - Topnet Deployment 166 C(2) F 

Thales Alenia Space + Thales 

Alenia Space (I) 


Y2002 ETD-039 TOPNET: Pilot Operation Implementation - Topnet Deployment 166 C(2) UK 

4Links Limited + SAAB Space (S) 

+ Science and Technology (UK) 


Y2006 T603-05ET FPGA Based Generic Module and Dynamic Reconfigurator 500 C - Intended 

Y2004/ 

Y2006 

T603-08ES Next Generation Multi-purpose Microprocessors 800 C - Intended 

Y2005 T603-09ES Validation and further development Spacecraft-Controller-on-a-Chip (SCOC) 250 30 DN/C F Astrium Velizy - Contracted 20167 

Y2006 T603-20ET Development of a Mass Memory Module with Embedded File System Support 600 C(2) Awaiting for ETD-036 results - Intended 

Y2006 T603-22ES Synthesizable VHDL IP cores 250 C CH Syderal - Contracted 22043 

Y2006 

T603-27ED 

Evaluation of Radiation Effects on Deep Sub-micron CMOS Technologies (Original 

title:SEE Identification, Modelling & Severity assessment) 


Page 61 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T608-26ES 

Radiation Hardened by Design ASIC library qualification, procurement and 

maintenance 

400 DN/S B IMEC - Contracted 

Y2004 T609-08ET Massively Parallel Processor Breadboarding 400 C(2) NL Recore Systems+Un.Twente(NL) - Contracted 21986 

Y2006 T609-25ED SpaceWire Network Bandwidth Performance Simulation Tool 200 C 

Operational 

SW 

Intended 

Y2006 T609-26ED OCP-IP building blocks for Space-SoC 150 C F 

Astrium + Gaisler Research (S) + 

Magillem (F) 


Y2006 T609-27ED Standardisation of spacecraft onboard communication services 200 C UK Scisys + Astrium (F) 

Operational 

SW 


Total 6.1 - On-board Data Systems 2,900 617 1,993 1,405 4,910 

Page 62 of 97




12/Feb/09 


6.2 - Space System Software 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 EME-012 Component Oriented Development Techniques 250 C F 

Alcatel + U. Padova (I) + P&P 

Software (CH) + GMV (E) 

Operational 

SW 


Y2006 EME-012 Component Oriented Development Techniques 250 C F Astrium + Intecs (I) 

Operational 

SW 


Y2001 EME-014 Compact Computer Core S/W 500 C(2) F Astrium + Scisys (UK) - Contracted 18787 

Y2006 EME-017 Tools For The Production Of O/B Sw Running On New Generation Computers 200 C P 

Edisoft + Syderal (CH) + Aonix 

(UK) + EADS-Astrium (F) 

Open Source 

Code 


Y2001 

EME-100 

(EME-011, 

T-M-QQS-1 

Effective Use of autocoded Comp. 650 C(2) F 

4-4) 

EADS LV + SciSys(UK) + 

Synspace (CH)+ Gerlich (D) 


Y2006 

T603-28QQ 

Validation of Safety and Dependability Critical Software Componenets with Model 

Based Requirements 

200 C p Skysoft+GMV(E) - Contracted 21404 

Y2006 

T603-29S 

W 

System and Software Functional Requirements Techniques 250 C I 

INTECS + Thales (F) + Sapienza 

Un.Rome (I) + Thales (I) 


Y2004 T607-01EM Automation of the life cycle: automatic test generation 272 C(1) P 

Operational 

SW 


Page 63 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T607-05EM Verification and Validation: Testing Object Orientation 250 C(3) P Critical Software 

Open Source 

Code 


Y2006 T607-08EM Standardisation and Building Blocks: Standardisation watch and verification 300 C 

Operational 

SW 

Intended 

Total 6.2 - Space System Software 1,150 1,022 200 750 

Page 64 of 97




12/Feb/09 


6.3 - S/C Power 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 EPB-001.C Development of Regenerative H2/O2 fuelcell 150 DN/S N Prototech - Contracted 18312 

Y2003 EPG-025 Solar Cells Testing Spasolab 244 270 220 220 DN/S E Multi-year contract. - Contracted 18444 

Y2003 ESB-008.A Adaptation of terrestrial fuel cells for space applications 50 DN/S D Ballard - Contracted 18534 

Y2002 ESG-007 Thin Film Solar Cells Ph. 3 600 DN/C NL Dutch Space + HMI (D) - Contracted 17644 

Y2001 ESG-009 Reverse Bias Protection of GaAs Solar Cells 150 C D Astrium, RWE - Contracted 18199 

Y2001 ESG-010 Development Of Interconnection Techniques For Thin Film Solar Cells 200 C NL Dutch Space + HMI (D) - Contracted 20391 

Y2001 ESG-017 Flexible Blanket Technology 100 C F Alcatel - Contracted 18037 

Y2001 ESP-003 Solar Array Sizing tool for Phase A/B studies 100 C B IAL - Closed 17947 

Page 65 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

T505-05EP Thin Film cell and module development 600 C - Deferred 

Y2006 T505-11EP Advanced research and pre-development of new materials for space solar cells 200 C(1) - Intended 

Y2005 T604-02EP Advanced Lithium Batteries Evaluation 300 C(1) F CEA - Contracted 20044 

Y2006 T604-03EP Development of Next Generation GaAs Based Multi-Junction Solar Cells - 2 1100 DN/C D 

RWE, FHG + CESI (I) + UMICORE 

(B) + Frauenhoffer (D) 

- Contracted 

Y2004 T604-05EP Development of Next Generation GaAs Based Multi-Junction Solar Cells - 1 2,000 DN/C D 

RWE, FHG + CESI (I) + UMICORE 

(B) 


Y2006 T604-06EP Nanotechnology for Space Solar Cells 200 C - Intended 

Y2006 

T604-07EP 

Efficient Low Cost Power Conversion for Standard and Advanced Fast Digital 

Electronics 

600 C S Saab Space - Contracted 20680 

Y2006 T604-08EP Integrated Current Limiter 350 C(R) 

C(R) restricted to DK, N, FIN, A, 

IRL. 

- Intended 

Page 66 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T604-10EP Study of new Power Systems architectures for LEO missions 400 C - Intended 

Total 6.3 - S/C Power 3,394 270 520 2,720 1,150 

Page 67 of 97




12/Feb/09 


6.4 - S/C Environment & Effects 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/EMA-00 

1 

Muon Telescope 200 DN/S D U. Greifswald, HTS - Contracted 18835 

Y2002 EMA-022 Spacecraft Charging & Plasma Interaction Guidelines 100 C UK Qinetic - Contracted 18061 

Y2004 T602-01EM Solar Energetic Particle Environment modelling 400 C(1) B 

Belgian Inst Space Aeronomy, Un. 

Leeuwen+Un.Polit.Cataluna(E)+Un - Contracted 20162 

. Southampton(EK), Qinetiq 

Y2004 T602-02EM Radiation Effects on Advanced Technologies: Models and Software Ph.1 250 C(1) UK 

Qinetiq + Rhea System, Belgian 

Institute Space Aeronomy (B) + 

Un. Bern (CH) 


Y2004 T602-02EM Radiation Effects on Advanced Technologies: Models and Software Ph.2 350 DN/C UK 

Qinetiq + Etamax (D) + TRAD (F) + 

Un. Genova (I), SPaceIT (CH) 


Y2006 T602-03EM Development of a predictive discharge numerical model on solar panels 200 C F Onera+Artenum(F)+Astrium(F) 

Operational 

SW 


Y2007 T602-04EM Rapid prototyping toolkit for space environment engineering tools 250 C D 

Resubmitted after positive 

Harmonisation check // Etamax 

Space 

Open Source 

Code 


Y2004 

T602-05MC 

Harmonisation of Thermal and Space Environment Analysis Software and Interfaces 

- Exchange of Thermal Models via STEP-TAS 

300 C 

prime + subs Alstom (UK) / 

Astrium-SAS (F) / Alcatel (F) + 

RAL (UK) / Astrium (D) 

Open Source 

Code 


Page 68 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T602-06EM Space Weather Warning for Space Systems 300 C 

Open Source 

Code 

Intended 

T602-08EE Time-dependent Engineering Models of GEO and LEO Radiation Belts 340 DN/S F 

Onera + BIRA (B) + QinetiQ (UK). 

// Deferred 

Operational 

SW 

Deferred 

Y2006 T602-09EE Investigation and analysis of very high energy accelerators for radiation simulation 300 C D 

FHG+SpaceIT(CH)+Gesellschaft 

fur 

Schwerionforschung(D)+Maprad(I) 


Y2006 T607-11EE Rapid Reverse Monte Carlo and Ion Physics for Dose and SEE 200 C UK 

Phase1// Qinetiq + TRAD (F) + 

Spaceit (CH) 

Open Source 

Code 


Y2004 T609-14QC General Spacecraft Environment Monitor 350 DN/S CH Contraves - Contracted 18619 

Total 6.4 - S/C Environment & Effects 650 250 650 740 1,250 

Page 69 of 97




12/Feb/09 


6.5 - Space System Control 

IPC 

Appr. 


SW Clause 

applicability 


Y2002 

/ 

Y2005 

/ 

Y2007 

2004 2005 2006 2007 2008 31/12/2008 

MME-002 Integrated-Optics Laser gyro Technology (IOLG) Ph.2B 147 65 DN/C I Macchine Intelligenti - Contracted 16782 

Y2006 

T603-01M 

M 

Novel Optical Gyro Concept 500 C F 

Atmel + CNRS (F) + Un 

Montpellier (F) + Thales Avionics 

(F) 


Y2004/ 

Y2005 T603-03ES Robust LPV Gain Scheduling Techniques for Space Applications 300 C E Deimos + Un. Leicester (UK) + TU 

Delft (NL) 

Open Source 

Code 


Y2004/ 

Y2005 T603-03ES Robust LPV Gain Scheduling Techniques for Space Applications 300 C F EADS-Astrium, CNRS, Onera Open Source 

Code 


Y2006 T603-04ES Robust Model Predictive Control (MPC) for Space Constrained Systems 400 C 

Operational 

SW 

Intended 

Y2004 T603-10ES MEMS Rate Sensor 930 1000 C(1) UK SEA, BAe Systems, Selex - Contracted 18800 

Y2006 T603-11ES Attitude Determination Tailored to Multiple Heads Star Tracker 150 C F 

Alcatel (F) + Alcatel Alenia Space 

(I) 

Operational 

SW 


Y2004 T603-12ES Autonomous On-Board Momentum Management C Deferred (low priority, 300kE) - Deferred 

Page 70 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T603-13ES Modern Control Techniques Applied to Satellite FDIR 350 C F Astrium 

Open Source 

Code 


T603-30EC Sensor on a Chip Feasibility study and Avionics Evolution 650 180 C I 

Galileo Avionica + BAE (UK) + 

Cypress Semicond. Corp (B) + 

Alcatel Alenia Space (F) 


Y2006 T603-36EC Future technology studies for APS Star Trackers 500 89 C D 

Jena Optotronic + Cypress 

Semiconductor Corporation (D) + 

Gaisler Research(D) + Zaimler 

Technik(D) + Frauenhofer(D) 


Y2006 T603-36EC Future technology studies for APS Star Trackers 500 C DK Terma + TNO(NL) - Contracted 20966 

Y2006 T603-38EC Enhanced CCD Star Tracker 400 DN/S DK Terma. Special Measure DK. - Contracted 20209 

Y2006 T603-41EC System study to define European accelerometer development 200 C F 

Thales,Memscap,Thales 

Avionics+Thales(I)+SEA(UK) 


Total 6.5 - Space System Control 1,077 2,800 1,765 1,019 

Page 71 of 97




12/Feb/09 


6.6 - RF Payload System 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 ETP-029 O/B SAR Calibration 200 C F Alcatel - Contracted 18439 

Y2002 ETT-059 Neural networks for radionavigation 400 C(3) F M3S, TESA + GMV, UPCA (E) - Contracted 18824 

Y2004 T603-14ET Frequency Flexible Synthesizer Breadboard suitable for O/B TTC 200 C I Alenia - Closed 18769 

Y2004 T603-14ET Frequency Flexible Synthesizer Breadboard suitable for O/B TTC: additional work 39 C I Alenia - Contracted 18769 

Y2004 T603-29ET Telecommand & Telemetry System Security 300 C F EADS-Astrium - Contracted 19130 

Y2006 T603-31QC Linearity Assessement of GaN Technology 500 C(1) D 

Tesat, FBI + Qinetiq (UK) + TU 

Denmark (DK) 


Y2006 

T603-32ET 

Power/Efficiency flexibility of spaceborne SSPA using Doherty scheme associated to 

a linearizer 

550 C F 

Thales Alenia Space + Un. Basque 

Country (E) + Un. Limoges (F) + 

Amcad Engineering (F) + United 

Monolithic Semiconductors (F) 


Y2006 T603-33ET Solid State Isolators based on GaN technology 400 C NL TNO + FBH(D) - Contracted 21854 

Page 72 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T603-33ET Solid State Isolators based on GaN technology 400 C UK Qinetiq+ComDev Europe (UK) - Contracted 21904 

Y2006 T603-37ET Future Multipurpose TT&C Systems & Techniques 300 C I Space Engineering - Contracted 21174 

Y2006 T603-39ET Design and Synthesis of a New Class of Receiver Filters 150 C E 

Un.Polit.Catalunya + Mier 

Comunicaciones (E) 


Y2006 

/ 

Y2008 

T603-40ET 

Evaluation and validation of electromagnetic software, test facilities and test 

standards in Europe to predict and test RF breakdown and passive intermodulation 

(PIM) 

530 DN/S Budget increased / PP change - Intended 

Total 6.6 - RF Payload System 400 739 500 850 1,480 

Page 73 of 97




12/Feb/09 


6.7 - Electromagnetics Technology 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/EEA-00 

1 

Quasi Optical Modelling 250 DN/S DK Ticra - Contracted 18123 

Y2003 

03/EEE-00 

1 

Development of low frequency probes 150 DN/S DK TU Denmark - Contracted 18222 

Y2003 

03/EEE-00 

2 

Instrumentation for injecting current shaped waveforms 398 DN/S CH Montena - Contracted 18788 

Y2001 EEE-006 Novel Techniques For General Antenna Characterisation In The Time Domain 300 C - Intended 

Y2001 EEE-008 Spacecraft EMI control in the presence of composite materials 300 C(1) D 

HPS, Kayser Threde (D) + Mira, 

NPL (UK) 


Y2003 

ETM-192 / 

T-M-QCT-0 

6-FZ3 

Design of photonic crystals front-end (Photonic crystals: Material selection and 

fabrication) 

250 DN/C E U.P. Navarra + Sub in Competition - Contracted 15632 

Y2004 T603-27EE Secured link for TT&C antennas design phase 297 C(2) UK BAE Systems - Contracted 19674 

Y2004 T603-28EE RCS Quiet Zone Characterization at Millimetre Wavelengths 100 DN/S NL March Microwave Systems - Contracted 19230 

Page 74 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 T605-01EE Advanced System Level Conducted Emission Analysis and Simulation for EMC 250 C I 

Carlo Gavazzi 

Space+Terma(DK)+Polit. Milano(I) 

Operational 

SW 


Y2006 T605-13EE Advanced System Level Radiated Noise Analysis and Simulation for EMC 250 C I 

Carlo Gavazzi Space+EM 

Software(D)+Polit.Milano(I) 

Operational 

SW 


Y2006 T607-10EE European Antenna Modelling Component Library - Step 2 250 DN/C DK 

Ticra + IDS (I), SATIMO (F), and 

others 

Operational 

SW 


Total 6.7 - Electromagnetics Technology 798 650 297 500 550 

Page 75 of 97




12/Feb/09 


6.8 - System Design & Verification 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 EMM-004 Virtual spacecraft design (Ph.1&2) 2000 C(R) D 

EADS-Astrium, EADS-ST + ALS (I) 

+ EADS-Astrium (F) 


Y2006 

T504-15SR 

Technology reference and proof of concept for a space based Automated 

Identification System for maritime security 

500 100 DN/S N 

Norvegian Defence Research 

Establishment + subs 


Y2004 T605-05AC Grid-based distributed concurrent design (GDCD) 500 C(2) I 

Datamat + DNV, EPG (N) + Alcatel 

(F) + Alenia (I) 


Y2004 T605-06MT Virtual AIV Techniques for Virtual Integration of a Satellite in the Test Facilities 250 C(2) DK Terma - Contracted 18775 

Y2004 T605-15EM Space System Reference Model 200 C D Astrium (D,F) + Prostep (D) - Contracted 20396 

Y2006 T607-06EM System-Software Co-Engineering: Performance and Verification 500 C D 

Rhein-Westfal 

Tech.Hochschule+Thales(F)+Fond 

. Bruno Kessler (I) 


Y2006 T607-09SR Concepts for future spacecraft architecture and development approaches 800 C F Thales+Thales(I)+SSTL(UK) - Contracted 21214 

Y2006 

T607-12S 

W 

System of Systems analysis and design environment 500 C UK Vega+Thales(I) - Contracted 21254 

Page 76 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T607-13S 

W 

Monitoring and Control Data Modelling 300 C I 

Space Software Italia + PNA 

Group(NL) 

Operational 

SW 


Y2006 

T607-14S 

W 

Building Block Approach for EGSE 250 DN/C DK 

Rovsing + Dutch Space (NL) + 

Critical SW (P) + SciSys (UK) 

Operational 

SW 


Total 6.8 - System Design & Verification 250 2,500 500 2,000 650 

Page 77 of 97




12/Feb/09 


6.9 - Mission Control & Operations (GS Data Sys) 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 GI-001 XML Framework 600 C(1) DK Terma + Siemens (A) - Contracted 18074 

Y2003 GSS-041 InP X-Band Cryo LNAs 200 DN/S E Fundae. Gen. - Contracted 17955 

Y2006 T603-34GI TC Authentication 300 C A Siemens 

Operational 

SW 


Y2006 T603-34GI TC Authentication 300 C F Thales IS, Telindus 

Operational 

SW 


Y2006 T603-35GI Security communications for SLE services 250 C F Cap Gemini 

Operational 

SW 


Y2004 

T605-07GI 

Feasibility of Automated Regression Testing for Space Systems Operational 

Software 

400 C A 

Siemens + Critical Software (PT) + 

Terma (DK) 


Y2004 T605-09GI N-Tier architectures applied to Ground Operations Systems 200 C D Terma - Contracted 20807 

Y2004 

T605-17GI 

European Technology Harmonisation on Ground Systems Software - First Set of 

Standard Interfaces 

500 C PT 

Critical Software + Dutch Space 

(NL) + Vega (D) + SciSys (UK) + 

GMV (E) 


Total 6.9 - Mission Control & Operations (GS Data Sys) 800 900 1,050 

Page 78 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 


6.10 - Flight Dynamics & Navigation 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T606-08GF 

Analysis of a Standardised Approach to the Emulation of the Highly Autonomous 

Avionics Systems of Interplanetary S/ C 

120 C D EDS - Contracted 19614 

Total 6.10 - Flight Dynamics & Navigation 120 

Page 79 of 97




12/Feb/09 


6.11 - Mission Analysis & Space Debris 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T605-08GA Astro-toolbox: a toolbox for preliminary mission analysis 100 C E GMV + Un. Glasgow (UK) - Contracted 19617 

Total 6.11 - Mission Analysis & Space Debris 100 

Page 80 of 97




12/Feb/09 


6.12 - Ground Station System & Networking 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T606-01GS Two-layer servo concept with movable BWG mirrors 250 C(1) I ADS International - Contracted 19515 

Y2004 T606-02GS Multipurpose Highly Stable System for Ground Station Characterisation 500 C E Indra Espacio - Contracted 19516 

Y2006 T606-06GS Experimental InP Ka band cryocooled LNAs 250 DN/C E 

Fundacion General de la 

Universidad + ETHZ (CH) 


Y2006 T606-06GS Experimental InP Ka band cryocooled LNAs 250 DN/C S Un. Chalmers - Contracted 20744 

Y2006 

T606-12GS 

Study and Breadboarding of a Sapphire Oscillator for Ultra-High Short-Term Station 

stability 

500 C F 

CNRS + Timetech (D) + National 

Physical Laboratory (UK) 


Total 6.12 - Ground Station System & Networking 750 500 500 

Page 81 of 97




12/Feb/09 


6.15 - Mechanisms & Tribology 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/MMM-0 

01 

Self Contained Deployment Mechanism 850 DN/S N Kongsberg - Contracted 18770 

Y2007 

03/MMM-0 

01 

Self Contained Deployment Mechanism 200 DN/C N Kongsberg - Contracted 18770 

Y2003 

03/MMM-0 

02 

Integrated SADM+HDRM 650 DN/S N Kongsberg - Closed 18622 

Y2003 

03/MNT-00 

1 

Mirco Nano Satellite Technologies 500 DN/S S U. Uppsala - Contracted 18600 

Y2004 

T601-21M 

M 

APSEE: Arc Phenomena in Space Environment & Equipment 400 DN/S CH Meccanex + ONERA (F) - Contracted 18700 

Y2006 

T601-36M 

M 

Unlimited resetable, no-shock Hold-Down and Release Mechanism (HDRM) 350 C(1) A Austrian Aerospace - Contracted 21291 

Y2005 

T601-47MX 

AEA Technology (ESR 

/ MMM-960 Tribology Application Programme 200 200 200 200 DN/S UK Technology). Multi-year frame 

contract: 2007 

Operational 

SW 

Closed 

Y2006 

T608-31M 

M 

Fully Variable Bearing Active Preload System 450 DN/C UK ESR Technology - Contracted 20511 

Page 82 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T608-32M 

M 

Angular position sensor based on MEMS technology 300 C(1) CH Ruag - Contracted 20404 

Total 6.15 - Mechanisms & Tribology 2,600 200 950 750 

Page 83 of 97




12/Feb/09 


6.16 - Optics & Opto-Electronics 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002/ 

Y2005 

MMO-670 

Materials for Ultra-Stable Lightweight Optical Benches and Mirrors (old title: Ultra 

lightweight Telescopes) 

600 88 C F 

Alcatel Alenia Space, Seso + ECM 

(D) 


Y2006 

T507-06M 

M 

Entangled photon source for Quantum Communications 250 C - Intended 

Y2004 

T609-05M 

M 

Instrument concepts using dynamic diffraction gratings (ICDDG) 200 C F Alcatel, LAS - Contracted 20519 

Y2004 

T609-05M 

M 

Instrument concepts using dynamic diffraction gratings (ICDDG) 200 C FIN VTT - Contracted 20532 

Y2006 

T609-16M 

M 

Advanced Side-pumping Technique for Double Clad Fiber Lasers 400 C(1) - Intended 

Y2006 

T609-17M 

M 

Programmable optoelectronic adaptive lens 250 C NL Cosine + Un. Durham (UK) - Contracted 21473 

Y2006 

T609-23M 

M 

Programmable micro-diffraction gratings 400 C(2) CH CSEM,INMI,LAS+Thales(F) - Contracted 21212 

T609-24M 

M 

Micro-optical beam delivery device for optical terminals for formation-flying cluster 

constellations 

C 250kE. Postponed. - Deferred 

Total 6.16 - Optics & Opto-Electronics 800 600 988 

Page 84 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 


6.17 - Aerothermodynamics 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 

T601-25MP 

Development of advanced models and acceleration of Monte Carlo methods for 

simulation of rarefied gas dynamics 

200 C I Alta + HPCC (D) - Contracted 20169 

Y2007 T601-28MP Feasibility Demonstration of a European Space Propulsion Simulation Tool 398 DN/C E 

Empresarios Agrupados + 

EADS-ST (D), EADS-ST (F), 

Cenaero (B) 

Operational 

SW 

Intended 21490 

Y2006 T601-48MP Validation of aerothermo chemistry models for reentry applications 650 650 C 

UK + 

B 

(D) +Astrium(F),CEA DAM CESTA, 

CNRS, ISA, Lab 

EM2C+CNR-IMM(I)+IST(P) /// 

(21234) Von Karman Inst. + EPFL 

(CH) + DLR (D) + HPS (D) + Lab 

Operational 

SW 

Contracted 

Y2006 

T601-49MP 

Hypersonic facility instrumentation enhancements for improved flight extrapolation 

and scaling 

500 C F 

Onera Dsac + DLR (F) + Von 

Karman Institute (B) 


Total 6.17 - Aerothermodynamics 200 1,150 1,048 

Page 85 of 97




12/Feb/09 


6.18 - Propulsion 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y1998 98/YPE01 SMART- 1 EPS Flight Equipment 126 DN/C F Snecma - Contracted 13516 

Y2002 GAD 3.10 Investigation Into MEMS - MEOMS Packaging 100 C - Intended 

Y2000 MPC-842 Green Propellants Phase 2 238 DN/C D EADS - Contracted 17929 

Y2000 MPC-842 Green Propellants Phase 2 238 DN/C F SNECMA - Contracted 17789 

Y2002 MPC-850 Hydrogen Storage Technologies 250 C N Prototech - Contracted 17925 

Y2001 MPE-878 New Grid System for Ion Engines (additional activities) 150 DN/C UK Qinetic, CCN - Contracted 16614 

Y2004 T505-02MP Development of a High Thrust Density cusped Plasma Thruster 600 DN/S D 

Thales. See 

ESA/IPC(2005)3,add.3 


Y2004 T505-09MP Hall-effect Thruster with Multi-Sectional Conductive Walls 360 DN/S F SNECMA + Alta - Contracted 20332 

Page 86 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T601-02MP Development of advanced EP Thruster characterisation diagnostics 250 50 C I 

Aerospazio + Astrium, U. Giessen, 

U. Leipzig (D) 


Y2004 T601-02MP Development of advanced EP Thruster characterisation diagnostics 250 C I Alta - Contracted 20486 

Y2004 T601-17MP Development of a Circular Slit Field Emission Thruster 400 C I Alta +Alcatel, Snecma (F) - Contracted 20445 

Y2005 T601-31MP Advanced Technologies Demonstrator for Very High-Power Hall-Effect Thrusters 600 DN/S F SNECMA + Alta - Contracted 20332 

Y2006 

/ 

Y2007 

T601-42MP Development of a fuel/oxidiser compatible diaphragm 500 DN/S UK MT Aerospace + subs - Intended 

Y2004 T608-25QC Reliability of MEMS based pressure sensors 250 DN/C N Presens - Contracted 18804 

Y2004 T608-27QC Methodology for complex Micro-Propulsion Systems Space Validation 120 C S Nanospace - Contracted 20720 

Y2004 T609-22MP Innovative Gas Storage in Satellites 300 DN/S N 

Prototech + IFE (Special measures 

for Norway) 


Total 6.18 - Propulsion 776 300 2,935 120 650 

Page 87 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Page 88 of 97




12/Feb/09 


6.19 - Structures & Pyrotechnics 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2002 MCS-001 Ultra light Structures - Phase 1 500 C(2) F 

EADS-LV + Zodiac, Ecole N.S. 

Lille, Ideamech, EADS-Astrium + 

MC Bernasconi (CH) + KDA (N) + 

IABG (D) 


Y2002 MCS-001 Ultra light Structures - Phase 2&3 1497 190 DN/C F EADS-LV (Team from Ph.1) - Contracted 18738 

Y2002 MCS-002 Electro Active Polymer Actuator 1,410 C I 

Kayser Italia,U. Roma,U. Pisa + 

DLR,HPS(D) +Risoe(DK) 


Y2006 T505-06MC Active Structures for Large Solar Array Panels 250 C D 

Astrium (D)+IABG(D)+TU 

Munich(D) 


Y2004 

T601-05MC 

Derivation of satellite equipment design and test specifications from random 

vibration environments 

200 C D 

Astrium (D,F,UK) + Alcatel (F) + 

Alenia (I) 


Y2004 T601-09MC Establishment of satellite mechanical shock design and verification guidelines 150 C F Alcatel, Astrium + Alenia (I) - Contracted 20503 

Y2004 T601-11MC Assessment and Improvement of Dynamic Test Data 250 C F 

Astrium, Intespace + Un. Kassel 

(D) 


Y2004 T601-14MC Random Vibration Environment derivation by Vibro-acoustic simulation 200 C D HPS + IABG(D) + ESI Group(D) - Contracted 20731 

Page 89 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2004 T601-14MC Random Vibration Environment derivation by Vibro-acoustic simulation 200 C E 

EADS Casa Espacio + Un. Pol. 

Madrid (E) 


Y2006 T601-46MC Vibro-Acoustic Analysis & Test methods for Large Deployable Structures 450 C NL 

Dutch Space + Un. Polit. 

Madrid(E)+01DB 

Metravib(F)+Thales Alenia 

Space(I) 


Y2006 

T601-50MC 

Advancement in Thermo-Elastic Distortion Verification Methods for spacecraft 

structures 

300 C 

Phase 1. (Ph2. in 2009, see TRP 

2008-2010) 

- Intended 

Y2004 T605-11MC Non-Contact Measurements of Membranes 200 C(3) B Un. Liegi + TU Munich (D) - Contracted 20042 

Y2004 

T605-12MC 

Improvement of force limited vibration testing methods for equipment/instrument unit 

mechanical verification 

250 C(2) I 

Thales Alenia Space + Un. 

Leicester (UK) + Mecano (F) + 

IABG (D) 


Y2006 

T605-20MC 

Advancement of Mechanical Verification Methods for non-linear spacecraft 

structures 

300 C F 

Astrium+LMS(B)+Interspace(F)+As 

trium(UK) 


Total 6.19 - Structures & Pyrotechnics 1,910 1,497 990 650 1,300 

Page 90 of 97




12/Feb/09 


6.20 - Thermal 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 MCT-694 MST Compressor for JT cooler 400 DN/S UK RAL - Contracted 18248 

Y2002/ 

Y2006 

MCT-698 Mini And Micro Heat Pipes 200 C B 

Revised description. Euro Heat 

Pipes + Astrium (D) 


Y2003 MCT-700 Regenerator Technology for 10-100K Stirling and Pulse Tube Coolers 600 DN/S UK RAL + CEA Grenoble (F) - Contracted 18771 

Y2003 MCT-701 Maxi compressor for low temperature cooler 500 DN/S UK Astrium,RAL - Contracted 19218 

Y2001 MCV-882 Thermal Concept Design Tool 200 C(1) I Blue Eng 

Open Source 

Code 


Y2004 T601-04MC Thermal model correlation using genetic algorithms C Deferred, low priority. - Deferred 

Y2004 T601-24MC Novel, Composite Wicks (for two-phase loops) 350 C - Intended 

Y2006 T601-39MC Cryogenic Harness for Detector Arrays 350 C - Intended 

Total 6.20 - Thermal 1,200 500 900 

Page 91 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Page 92 of 97




12/Feb/09 


6.22 - Components 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

03/QCT-00 

1 

Evaluation Thermistors 125 DN/S IRL Beatherm - Contracted 17827 

Y2001 GAD 1.01 

Process Development And Concept Validation Of Metamorphic High Electron 

Mobility Transistor Ph.2 

Deferred (low priority, 200kE) - Deferred 

Y2001 

GAD 2.06 

A 

Design And Evaluation Initiative For Rad Tolerant Components 600 DN/S F STM - Intended 

Y2001 

GAD 2.06 

C 

Reliability Assessment Of European Power Mosfets Phase 1 And 2 C(1) Deferred (low priority, 500kE) - Deferred 

Y2001 

GAD 

2.06.D 

Study Of RF Compression & Overdrive on Components 200 C - Intended 

Y2003 GAD 3.04 Testing of Chip Scale Package (CSP) 100 DN/S F Astrium - Contracted 14936 

Y2003 GAD 4.02 HDI demonstration Module with CSP / ECR32 MCM Validation 150 DN/S F Astrium - Contracted 14936 

Y2003 QCA-004 Utilisation of the Proton Irradiation Facility (PIF) for Components Studies 550 DN/C CH PSI - Contracted 18465 

Page 93 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 QCA-005 Utilisation of the Radiation Effects Facility (RADEXF) for Components Studies 330 110 110 DN/S Fin U. Jyvaskyla // Multi-year contaract - Contracted 18197 

Y2002 QCT-006 Component for high power conditioning applications (SiC, GaN, ) 500 C(1) E CRISA - Contracted 18755 

Y2004 T608-01QC Radiation Test methodology for Optocouplers Devices for Space Applications 150 DN/S F EADS-Astrium - Contracted 19623 

Y2004 

T608-05Q 

M 

Carbon Nanotube based composite Material 300 C(1) D 

HPS, Futurecarbon, NMW, EADS 

(D) 


Y2007 

T608-05Q 

M 

Carbon Nanotube based composite Material: additional testing 100 80 DN/C D 

HPS, Futurecarbon, NMW, EADS 

(D) 


Y2004 

/ 

Y2007 

T608-24QC WALES: Wafer Level Encapsulation for micro-Systems 550 DN/S CH 

Y2004 T608-28QC MEMSRAD: MEMS sensitivity to space RADiation 300 C F 

Change of PP; budget increased. 

CSEM + LETI (F) + FGH (D) + 

IMEC (B) 

Astrium (F, D, UK), EADS-Astrium, 

Infoduc + Lusospace (P) + 

Angstrom Aerospace Corp. (S) + 

Alcatel Alenia Space (F) + EADS 

(D) 

- Intended 


Y2006 T608-29QC Radiation testing of candidate microelectronic components for space applications 600 C - Intended 

Page 94 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2006 

T608-34Q 

M 

Performance benchmarking of European GaN epitaxial wafer suppliers 250 C D FBH, Tesat, UMS - Contracted 20328 

Y2006 T608-36QC SRAM based FPGA for space applications 300 C - Intended 

Y2006 

T608-37QC 

Study of long term parametric drifts of EEE components for inclusion in component 

detail specifications and worst case analysis 


Y2006 T608-38QC Survey of available micro and nanotechnology 200 C UK 

NPL + Inst. Nanotechnology (UK) 

+ Esys (UK) 


Y2006 T608-39MC Nanotube re-inforced structural materials for spacecraft applications 250 C - Intended 

Y2006 T608-42ET Deep-Sub-Micron ASIC technology assessment and High-Speed-Serial-Links design 1200 C(R) F 

C(R) with Atmel (F) and STM (I/F). 

See ESA/IPC(2006)88. ST 

Microelectronics, 

Thales+ISD(GR)+Astrium(UK) 

- Contracted 

Y2006 T608-43QC GaN Reliability Enhancement and Technology Transfer Initiative (GREAT2) 1,800 C D 

See ESA/IPC(2006)89. TESAT 

Spacecom + IMEC (B) + Ferdinand 

Braun Inst. (D) + FHG (D) + UMS 


(D) 

Y2001 

T-M-QCT-0 

2-MT 

MTSL Lab 150 150 DN/C IRL NMRC - Contracted 10582 

Page 95 of 97




12/Feb/09 



IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

T-S-QCA-0 

2-08 

Utilisation of the Heavy-ion Irradiation Facility (HIF) for Components Studies 373 150 DN/S B Un. Louvain // Multi-year contract - Contracted 12471 

Y2003 

T-S-QCT-0 

2-FZ4 

Micro-Optical Electromechanical Systems (MOEMS) Delta Space Qualification 

Methodology (Critical evaluation techniques for micromachined devices) 

300 C(2) F Alcatel - Contracted 18669 

Total 6.22 - Components 2,428 710 800 1,540 4,750 

Page 96 of 97




12/Feb/09 


6.23 - Materials & Processes 

IPC 

Appr. 


SW Clause 

applicability 


2004 2005 2006 2007 2008 31/12/2008 

Y2003 

(03/)EEA-0 

02 

Metamaterials for Space 250 DN/S CH EPFL - Contracted 18545 

Y2006 

T608-04Q 

M 

Assessment of the reliability of High Density Integrated Boards (HDIs) for future 

space use 


Y2006 

T608-12Q 

M 

Study of the impact of the power meshed plane on electromagnetic behaviour of 

electronic boards (PCBs). 


Y2006 

T608-15Q 

M 

Test and validation of contamination models through ground experiments modeling 200 DN/S F Onera - Intended 

Y2006 

T608-30Q 

M 

Joining technology to bond Carbon to Carbon in stable sandwich structures 250 DN/S F Alcatel + Snecma - Contracted 20479 

Y2006 

T608-33Q 

M 

Radiation stable optical adhesives 300 C D ZARM Technik + FHG (D) - Contracted 20784 

Total 6.23 - Materials & Processes 250 250 300 610 

Page 97 of 97

f 

Chapter 3 


Description of Activities 


12/Feb/09




12/Feb/09 


1.1 - Data exploitation 

TRP Reference: 

Title: 

T101-07GD 

Image Information Mining 

This activity shall identify and implement demonstrators of Image Information Mining methods, in particular for change 

detection, applicable to medium resolution SAR or optical sensors, addressing all aspects from preparation of data in the 

archives up to semantic classification of images and of extracted information or accompanying text. Tasks include: 

Requirements, trade-offs of potential new concepts, feasibility assessment, demonstrators and evaluation, system 

architecture. 

Deliverables: 

Software demonstrator and documentation. 

Current TRL: Target TRL: Prototype Application Need/Date: SW operational by 2009 

Application/Mission: EO image archieves Contract Duration: 24 months 

SW Clause : - Dossier0 Ref.: T-572, T-7699 

Consistency with Harmonisation 

Roadmap and Conclusions: 

TRP Reference: T101-08GD 

Title: 

Mission Planning for Constellations and Multi-use 

Implementation of demonstrators to identify the critical issues and demonstrate the feasibility of possible solutions for quasi 

conflict-free planning of payload acquisitions for missions based on satellite constellations and serving different user 

communities (e.g.: civil, military, institutional, research, etc.). The demonstrators, solutions, and scenarios will take into 

consideration the experience made by ESA in parallel planning ERS-1, ERS-2, and Envisat for different user communities with 

various priorities, and in implementing and testing a multi-mission conflict reduction planning tool. The project shall also take 

into account the need of the forthcoming constellations of EO satellites. 

Deliverables: 

Software and test scenarios. 


Application/Mission: GMES Contract Duration: 18 months 

SW Clause : - Dossier0 Ref.: T-536 



Page 1 of 227




12/Feb/09 


Title: 

T101-09GD 

EO data archives: Improved access and presentation 

The objective of this activity is to identify, implement and test new methods for easing user access to archived data via 

advanced technologies permitting multi-mission, integrated search, browsing and direct access to data or information (also 

extracted in real time), best supporting (also as indicated by system suggestions) user applications, maintaining an high level 

of system security. The system should make simple for the user to obtain only the necessary information at the highest 

possible level, with the minimum of additional effort, and in formats compatible (and as transparent as possible) with his 

application or process. 

Deliverables: 

Study analysis report, System Design Documents, Demonstration system. 


Application/Mission: EO data archieves Contract Duration: 18 months 




Page 2 of 227




12/Feb/09 



Title: 

T102-01EE 

Multi-frequency feeds for Earth Observation applications 

This activity should study feed concepts that can operate in several frequency bands, with wide-band, dual polarisation 

capability, and compact volumes, for usage in remote sensing instruments such as radiometers, radars and altimeters. It 

should be mentioned that depending on frequencies separation and bandwidth involved very different feed concepts have to 

be considered. This justify the need to consider several design. 

Deliverables: 

Feed concepts for multi-frequency operation capability. 

Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2008 

Application/Mission: Post EPS radiometer Contract Duration: 14 months 




TRP Reference: T102-03EE 

Rigorous numeric techniques applied to microwave interaction with natural targets: 

Title: 

volume scattering 

The main objective of this activity is to review the validity of microwave interaction models with natural targets that induce 

volume interaction. This aims at assessing their limitations in terms of range of input parameters, quantifying their accuracy 

and - whenever possible - providing insight on possible improvements. Based on theoretical considerations, the first objective 

shall be the assessment of the validity range of the simplified approaches. The second objective is to implement a numerical 

test facility, which would give the possibility of validating asymptotic approaches. The third objective is - at least for the 

application cases described above, and based on the test facility - to derive the validity range and the limitations of the current 

approximate models. The fourth objective is to propose possible improvements to the asymptotic solutions or to propose 

alternative solutions to obtain results closer to reality. 

Deliverables: 

Data package including the demonstration software of the asymptotic approaches used in the study as well as a downsized 

version of the numeric "test facility". 

Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: SW operational by 2009 

EO and Planetology microwave 

Application/Mission: Contract Duration: 24 months 

Instruments 

SW Clause : Open Source Code Dossier0 Ref.: T-7769 



Page 3 of 227




12/Feb/09 


Title: 

T102-04EE 

KU Band SAR Snow Measurements for Snow Applications 

Deliverables: 

Current TRL: Target TRL: Application Need/Date: 

Application/Mission: 


SW Clause : - Dossier0 Ref.: 



TRP Reference: T102-05ET 

Title: 

Microwave Photonics Millimetre-wave Generation 

The trend in terrestrial communications has been to faster and faster data rates, now well into the tens of Gigabits per second 

range. This has led to the development of very high speed components primarily dedicated to digital communications. 

However, those components could also be used in the analogue domain (i.e. GHz instead of Gb/s).The aim of this activity is to 

evaluate the feasibility of broadly tunable high frequency generation (tens of GHz) based on microwave photonics 

implementation. This is of interest for millimetre and sub-millimetre-wave LO generation and distribution. 

Deliverables: 

Microwave photonics high frequency generation demonstrator 

Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012 

Application/Mission: mm/sub-mm missions (e.g. PREMIER) Contract Duration: 18 months 




Passive Millimetre and Submillimetre wave Instruments (no RM) 


Title: 

T102-07ET 

P-Band Ice Sounding Radar Demonstrator Development 

The objective of the activity is to perform a feasibility study on ice-sounding radars in order to:- Trade-off system parameters- 

Select the most suitable transmit pulse characteristics and waveform.- Examine nadir and off-nadir surface ambiguity 

suppression techniques.- Make a performance analysis over simulated representative target (best knowledge of Antarctic 

ice-sheet and bedrock).The study will conclude with the development of a hardware demonstrator in the form of a P-band 

ice-sounding instrument developed using COTS equipment which eventually might be suitable for mounting on-board an 

aircraft for a possible future campaign to verify the findings of the study and to pave the way for a space borne ice-sounding 

mission. 

Deliverables: 

A P-band ice-sounding instrument developed using COTS equipment suitable for mounting on-board an aircraft. 


Application/Mission: P-band Ice Sounding Radar Contract Duration: 24 months 




Page 4 of 227




12/Feb/09 


Title: 

T102-10ET 

GaN Highly Efficient HPA for X- and Ku-band SAR and Altimeter Applications 

Semiconductor components based on GaN material have already demonstrated unparalleled performances on laboratory 

level compared to classical GaAs based materials. The prospects are impressively good. The material properties are ideal for 

radar applications. Power levels can be achieved, which were in former times the domain of vacuum devices like travelling 

wave tubes. 

Within the framework of this activity an HPA device shall be designed, manufactured and tested for demonstration of high 

power handling capability at X and Ku-band. 

Deliverables: 

Technology demonstrator with the usual documentation 


Application/Mission: future SAR and altimeter missions Contract Duration: 24 months 




Critical RF Payload Technologies 


Title: 

GaN Self Protected LNA for X- and ku-band Radar Applications 

Semiconductor Components based on GaN material have already demonstrated unparalleled performances on laboratory 

level compared to classical GaAs based materials. The prospects are impressively good. The material properties are ideal for 

radar applications. GaN is very often only proposed for high power applications, although the material has excellent noise 

properties very close to GaAs based materials. The high breakdown voltage is of great importance because this allows save 

operation in the vicinity of high power levels, typical for all Radar applications. Limiter always needed in conjunction with GaAs 

devices will become unnecessary or only very simple device. Noise figure is going to improve. Furthermore if considered for 

integration in T/R Modules The power device and the LNA can be integrated on the same chip. Two chip or even single chip 

T/R modules become feasible with corresponding cost advantages. 

Deliverables: 

Tested demonstrator LNAs with and without on chip limiter in X and Ku band. Design and Test Documentation. 

Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 by 2010 

Application/Mission: future SAR and altimeter missions Contract Duration: 18 months 




Critical RF Payload Technologies 


Title: 

Innovative Low-loss FSS structures 

The objective of this activity is to develop an accurate computer model to design multi-layer mesh filters. The simulation tool 

will account for the effects of non-perfect element shapes, metal conductivity and slot thickness. Investigate potentially 

suitable novel materials and micromachining techniques and create controllable and repeatable fabrication routes with suitable 

structural properties. Investigate potentially suitable techniques to make all-metal FSS structures and create controllable and 

repeatable fabrication routes with suitable structural properties. This should be followed by preliminary fabrication trials and 

process optimization. Measurements will be performed to quantify the efficiency improvement and increased out of band 

rejection. If applicable, existing prediction tools will be updated to explain discrepancies with theory and experiment. 

Deliverables: 

FSS hardware, prediction tools, full performance report. 


Application/Mission: mmWave sounders, imagers Contract Duration: 24 months 




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Title: 

T102-14ET 

LNAs for mm-waves 

Objective of this activity is the development of low-noise amplifiers (LNAs) with improved noise performance for 183/220 GHz 

for application in future atmospheric sounders. Recent developments in Indium Phosphide (InP) and metamorphic (MHEMT) 

technologies have made LNAs possible for the frequencies above 100 GHz. First demonstrations, however, did not have 

sufficiently good noise performance. In addition to reducing the gate length close to 50 nm, optimisation of the fabrication 

process and device structure and geometry are needed for improvement. This activity aims to take benefit of the on-going 

developments of low-noise MMIC processes towards higher frequencies, and develop an LNA with improved noise 

performance. 

Deliverables: 

LNA Breadboard 


Application/Mission: Post-EPS, MTG Contract Duration: 24 months 





Title: 

HBV multipliers for high power and high frequency 

HBV multipliers are developed aiming at achieving high power capability at mm/sub-mm waves with high efficiency. One 

important advantage of Heterostructure Barrier Varactors (HBVs) over Schottky varactors is the possibility of tailoring the 

device to a desired power level by epitaxially cascading an appropriate number of barriers. This capability has never been 

explored in detail. An on-going TRP activity aims at achieving the understanding of the power limiting mechanisms, and to 

perform the initial development of HBV devices for very high power level. In the proposed activity, the objective is to reach an 

output power capability around 1 W at 100 GHz by further development of the multi-barrier devices, and establishing a 

suitable mounting technique. A demonstrator employing one or more of these devices will be designed, manufactured and 

tested. 

Deliverables: 

HBV Multipliers demonstration model 


all heterodyne instruments at 


mm/sub-mm, Post-EPS, MTG 

Contract Duration: 24 months 

SW Clause : - Dossier0 Ref.: T-326, T-7712, T, 424 



Passive Millimetre and Submillimetre Wave Instruments 

Page 6 of 227




12/Feb/09 


Title: 

T102-17ET 

Integrated Schottky structures 

Schottky diodes are generic components that are used in practically all millimetre and sub-millimetre wave receivers. They are 

especially critical to future Earth observation instruments. At the highest frequencies Schottky circuits (mixers, frequency 

multipliers) have to be realised as integrated structures and tailored to the specific application, in routes that allow the 

integration of sub-micron Schottky diodes with matching and coupling circuitry on a suitable substrate (e.g. membrane or 

transferred substrate). The most promising technology approach will be used to realise waveguide demonstrators for 

frequencies above 300GHz. 

Deliverables: 

Mixer and multiplier demonstrators in waveguide package 


Post-EPS, MTG, Sentinels 45, CIWSIR, 


Premier, GOMAS 



Passive Millimetre and Submillimetre Wave Instruments 



Title: 

T102-18ET 

New Investigations of RF breakdown in microwave transmission lines 

Micro-strip and bar-line are two types of transmission lines, which are nowadays used in many space components because of 

their low loss and reduced weight. However, these transmission lines, located between the RF output amplifier and the 

transmitting antenna are prone to suffer from RF breakdown due to the high RF power levels generated by the transistors in 

the Solid State Amplifier (SSPA). Breakdown in these components implies, in most of the cases, the lost of the RF chain and, 

in some cases, even the lost of the mission. Many of the existing and future space programs (Envisat, Terrasar, Galileo, 

Metop, ATV, etc.) include high power SSPA in their payloads. The output section of these amplifiers and several of the 

components, which drive the RF signal towards the antenna are made of micro-strip and bar-line technology. The RF 

performance of these payloads is limited by the power handling of the components using this technology. A modular software 

tool compatible with existing general electromagnetic software shall be produced to simulate and prevent the multipactor and 

corona breakdown in these two transmission lines would imply a significant step not only in the investigations of these two 

unwanted phenomenon, but also would have a a great impact in the design and testing process of all high power components 

based on this technology. 

Deliverables: 

Software simulation tool for micro-strip and bar-lines; a number of representative samples on both technologies; final report on 

all theoretical and testing investigations 


Application/Mission: Telecom, EO Contract Duration: 18 months 




Page 7 of 227




12/Feb/09 


Title: 

T102-22ET 

Active calibration for radiometers 

The principle of the use of the active cold load (ACL) for radiometer calibration has already been preliminarily demonstrated at 

X-band (10.7 GHz ) by a bredboard (Contract 18907). This proposed activity is aimed to further enhance and demonstrate the 

ACL concept towards higher frequencis and potential applications especially in Earth Observation. Important possibilties are 

foreseen in passive EO systems at frequencies between 18 to 37 GHz where significant mass, power, and cost reduction 

could be achieved by substituting the currently used mechanically switched quasi-optical calibration systems by the use of 

electrically switched solid-state calibration ACLs. 

On the other hand, the use of an ACL could be advantagious when integrated into a quasi-optical cold calibration target which 

would give more freedom in the mechanical design and calibration routines by avoiding the need for frequent sky calibration. 

The activity first aims at investigating suitable technologies that are adequate to ACLs at frequencies from 18 to 37 GHz 

(MMIC vs. disctere, M/InP-HEMT, HBT...). Secondly, the ACLs are designed and breadboarded to demonstrate the capability 

of the ACLs to be used as replacements of mechanical calibration systems in the future. Both coaxial and quasi-optical ACLs 

will be implemented to demonstrate the benefits of the concept for different types of radiometer front-ends. 

Deliverables: 

Cold load demonstrator 


Application/Mission: GEOsounder, Post-EPS Contract Duration: 24 months 




Not directly linked to harmonised technology. 


Title: 

P-band SAR wave interaction and information retrieval 

P-band SAR has been considered a potential tool for measuring forest biomass since the 1980s. Its proponents claim to offer 

a larger dynamic range than possible with shorter wavelengths. Qualitatively that seems correct, but limited quantitative 

assessments and immature physical understanding do not help us quantify its scientific value. The study develops 

physically-based wave interaction and retrieval models appropriate to P-band and to high biomass forests. The observational 

and theoretical basis for P-band will be reviewed. A scattering model is to be developed in order to evaluate the sensitivity of 

polarimetric P-band signals to forest, soil and environment variables. A sensitivity analysis will be conducted, using the 

forward model to identify key drivers for backscatter. The potential accuracy of a universal retrieval algorithm is to be 

assessed through the review and the modelling. 

Deliverables: 

Identification of scientific observational drivers and tresholds. Physical model appropriate to P-band. Identification of key 

scattering components and their relationship to biomass. Assessment of retrieval algorithms and their use in potential mission. 


Future P-band SAR missions. One of 

Application/Mission: the Earth Explorer candidate missions is Contract Duration: 12 months 

covering this type of measurements 




Page 8 of 227




12/Feb/09 


Title: 

T102-28ET 

Development Schottky MMICs for high frequencies 

Schottky diodes are generic components that are used in practically all millimetre and sub-millimetre wave receivers. They are 

especially critical to future Earth observation instruments. Since the availability of Schottky technology for frequencies above 

100 GHz is very limited (single U.S. supplier), it is important to develop a European source. 

United Monolithic Semiconductors (UMS) is a European GaAs foundry that has a dedicated Schottky MMIC process 

commercially available for applications below 100 GHz. Preliminary studies have indicated that it is possible to introduce 

modifications that will improve the performance at higher frequencies, without changing the core fabrication process. 

The aim of this activity is to investigate theoretically and experimentally such modifications, develop the device design and the 

necessary processing steps, and demonstrate the improved performance at 200/300 GHz. 

The activity will include a theoretical study for diode optimisation using device and EM simulators, design of the discrete 

devices and MMIC Demonstrators, fabrication run(s) using the BES process of UMS, process experiments for different 

modifications in the fabrication, and the design, construction and characterisation of the Demonstrators. The Demonstrators 

will consist of discrete devices and fully functioning MMICs (mixer/multiplier) for 200/300 GHz. At least one MMIC will be 

mounted and characterised in a waveguide housing. 

Deliverables: 

Characterised Demonstrators (discrete devices and MMICs). Definition of processing modifications. 


Application/Mission: EO, Sience Contract Duration: 24 months 





Title: Active Receive-Only Digital Front-End for Radar and SAR - Phase 1 & 2 

Traditional SAR design has a well-known limitation between resolution and swath width, which have to be traded-off. A way 

out of this limitation is in the introduction of a bi-static approach with separated transmit and receive antenna, mounted on the 

same platform. This leads to the novel high-resolution wide swath approach for SAR, which makes use of innovative digital 

beam forming during receive and solves in this way the well known restriction. 

- Within phase 1 of the proposed activity a SAR system design based on this new concept shall be carried out. The key 

system performance parameters have to be determined by simulation and evaluated in comparison to traditional approaches. 

Critical components and subunits needed for a front-end demonstrator have to be identified and specified. 

- In phase 2 of the activity the critical components and subunits have to be breadboarded and feasibility shall be 

demonstrated. The scan while receive function, the key feature, has to be demonstrated. 

Deliverables: 

Fully tested Digital Rx-only Tile Demonstrator. Documentation. 


Application/Mission: SAR Contract Duration: 24 months 




Page 9 of 227




12/Feb/09 


Title: 

T102-30EE 

Next Generation L/S band SSPA Demonstrator for Radar 

The objective of the activity is the design, manufacturing and test of SSPAs (Solid State Power Amplifier) at L and S-band 

using advanced European microwave power technology. Newly available GaAs HBT and wide bandgap technologies under 

development now ( SiC, GaN) are good candidates for the development of very high power(i.e. over 50 watt) and thermally 

robust SSPAs that will represent a breakthrough on power capabilities at L and S band.Special attention shall be given to the 

packaging problems associated with the high power levels involved.These SSPAs shall demonstrate high power capabilities 

and good thermal properties. Possible applications are on next generation SAR antennas, active array antennas operating at 

L and S band. 

Deliverables: 

Fully tested elegant breadboard of very high power (over 50 watt) L and S band SSPA. 

Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2009 

Application/Mission: L- band Radar Contract Duration: 24 months 





Title: 

Understanding directionality in surface scattering by imaging radar 

The work will provide a more comprehensive extension of current approaches to electromagnetic modelling of radar-soil 

interactions, making use of explicit directional descriptions of soil roughness power spectra. The use of such power spectra, 

or reasonable parameterisations of them, within scattering models is intended to replace the trivial omni-directional 

descriptions now widely used, and allow for clarity in identifying the key interaction physics. This clarity of physical interaction 

is at the heart of this work and a key output will be the identification of the most important (directional) spectral ranges of soil 

roughness that determine backscatter and the role of other scales up to and beyond the resolution scale of the radar 

instrument. Benefit will be taken from currently running GSP activity on numerical validation of surface scattering models. 

Experimental demonstration, either from historical ERS-1/-2 or Envisat datasets plus relevant observations of soil roughness 

will be required to support the theoretical aspects of this work. Such datasets exist within a number of European groups. 

Deliverables: 

Demonstration software incorporating explicit directional effects for microwave soil scattering. Recommendations for 

strategies to avoid or mitigate retrieval errors associated with unforeseen directional artefacts in future satellite SAR data. 


Imaging radar missions (e.g. Sentinel-1, 


Envisat/ASAR) 





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12/Feb/09 


Title: 

T102-41ET 

Altimetric Measurements of 2D Ocean Surface Currents 

Understanding of ocean circulation and currents is of special importance to oceanographers and climatologists. Conventional 

altimeters provide highly accurate measurements at the sub-satellite point, but this coverage is insufficient for faster changing 

currents, eddies and, in particular, coastal areas, which also suffer from land contamination in the signal. Along track SAR 

interferometry (ATI) is one way in which surface currents can be derived and dedicated systems to do this have been 

proposed in the past. ATI though only provides one ocean surface current vector - orthogonal to the direction of flight. This 

approach is extended in ESA patent 511, which describes a technique for deriving 2D ocean surface currents using two 

antennas producing four squinted beams each. While the basics for the technique are outlined in the patent, a further system 

study should be performed in order to optimise all the system parameters, perform modelling and determine performance 

parameters for frequencies from X- to Ka-band as well as the potential of formation flying two satellites in order to realise the 

desired along and accross track baselines. 

Deliverables: 

Basic system design (or designs) of the instrument for measurement of 2D Ocean Surface Currents. 


Application/Mission: Future ocean missions Contract Duration: 12 months 






Title: 

Integrated Receiver and ADC for Active Array SAR 

Next generation spaceborne SAR will utilise digital beam forming techniques to improve performance and flexibility. For this 

application early down conversion and medium number of bit digitalisation on subarray level would be needed. Power 

consumption is crucial while high bandwidth is needed. New semiconductor technologies based on SiGe have the potential to 

integrate digital and analogue functions on the same chip with low power consumption. 

Within the activity an integrated receiver and medium number of bits A/D converter shall be designed manufactured and 

tested in order to prove the concept for next generation of SAR instruments. 

Deliverables: 

Technology demonstrator and documentation 


Application/Mission: Future SAR missions Contract Duration: 24 months 





Page 11 of 227




12/Feb/09 


Title: 

T102-44ET 

Research into GPS Sea-Ice and Dry Snow Reflectometry 

Sea-Ice applications: 

Reflected GPS signals obtained over sea-ice during airborne campaigns and via the UK-DMC satellite suggest that phase 

coherency can be maintained for some time allowing accurate altimetry to be performed. UK-DMC data however, suffers from 

poor datation and relatively low SNR whereas airborne data is limited, expensive to acquire and provides only a snapshot of 

ice conditions. In order to investigate fully the potential for GNSS Reflectometry to derive sea-ice parameters including 

freeboard a longer term alternative needs to be found. This could be in the form of mounting up and down looking GPS 

antennas at a suitable location overlooking sea-ice e.g. Zeppelin Mountain on Svalbard, and then collecting and analysing 

data over a protracted period, say 6 months. The resultant dataset would be invaluable in determining the ability of GNSS-R 

techniques to retrieve sea-ice parameters. 

Dry-snow applications: 

Dome Concordia in Antarctica is currently being investigated for its suitability as a calibration site for SMOS. The extremely 

dry snow with minimal precipitation each year, make it very attractive for this purpose. To test this a radiometer has been 

mounted on a tower at Dome C. Research into GPS Reflectometry over land has shown that provided the moisture content 

does not change then the forward scattering of GPS signals correlates extremely well over the same ground-track on different 

days. Since L-band penetrates many metres into dry snow, by mounting a down-looking GPS on the same tower at Dome C, 

a dataset could be built up over time showing L-band forward scattering as a function of incidence angle at this location. This 

would be of great interest to scientists and add insight into the radiometer retrieved signal. In addition, if both L1 and L2 

reflections could be captured then high accuracy TEC maps could be generated for the area. 

Deliverables: 

Long-term GPS-R dataset collected from a fixed position over sea-ice. Data analysis for altimetric purposes and ice 

properties. 

Dataset of L-band forward scattering as a function of incidence angle over the SMOS calibration site Dome C, Antarctica. High 

resolution TEC maps for the sky above Dome C. 


Future altimeter/ice mission, SMOS / 


SMOS ops 



N/A 


Page 12 of 227




12/Feb/09 


Title: 

T102-45ET 

Advanced SAR-Instrument based on Digital Beamforming 

Next generation high performance SAR systems will benefit from digital beamforming techniques to overcome limitations 

related with tolerance and temperature stability problems inherent with classical analogue implementations. Digital 

implementation of beamforming opens the door to new modes of operation such as scanning on receive, adaptive pattern 

nulling and multibeam capability. Major parts of this kind of radar electronics can be reused in other radar bands because it is 

inherently frequency independent. 

First ESA internal investigations have shown feasibility of such SAR front-ends in terms of processing speed and power 

consumption. 

New advanced analogue and digital semiconductor technologies (GaN, SiGe, deep sub-micron) meanwhile available or under 

development for ground based commercial telecom and military systems are beneficial for implementing such kind of system. 

The compatibility of these technologies with the environmental conditions in LEO applications has to be investigated. 

Digital implementation of beamforming would open the door to further optimisation of instrument architecture, making it 

possible to simplify the remaining analogue part of the system in terms of development and integration. 

The main objective of the study will be to elaborate the performance improvements and/or cost reductions expected from 

utilisation of digital beamforming and advanced technologies for next generation instruments, staggered in mid- and long-term 

time scale. 

The following work has to be performed in order to meet the objective: 

- Definition of key performance figures and functional requirements for next generation SAR systems for different applications. 

- Survey on advanced technologies available and under development suitable for SAR systems based on digital beamforming. 

- Instrument architecture trade-off and optimisation for taking maximum benefit from the identified digital implementation 

possibilities. 

- Establishment of a conceptual design together with estimate of power, mass and thermal figures, and assessment of 

performance. 

- Definition of technology roadmaps identifying development needs of critical parts for implementation of advanced 

instruments. 

- Outline of a Breadboard for the proof of critical elements as potential next step. 

Deliverables: 

- Technical note on technologies for advanced SAR 

- Technical note on advanced architectures 

- Technical note on implementation roadmaps 

Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5/6 by 2013 

Application/Mission: Advanced SAR Systems Contract Duration: 12 months 




N/A 

Page 13 of 227




12/Feb/09 


T104-17EE 

Bio- & geo-physical retrieval algorithm definition for active remote sensing of land 

Title: 

surfaces at P- and L-band 

This project aims to define, demonstrate and assess algorithms for the retrieval of a set of bio- and geo-physical parameters 

from observations that include a strong contribution from L-band SAR. 

A set of bio- and geo-physical parameters will be selected, based on perceived scientific or operational need and on expected 

feasibility. These are expected to include (but not be limited to) forest and other vegetation biomass, soil moisture, snow 

water equivalent. Targets for operational effectiveness of retrieval algorithms shall be identified at the outset. 

The work will take advantage of previous research on the refinement of wave interaction models and descriptions of the 

natural surfaces and vegetation appropriate to these wavelengths. New and independent developments of interaction models 

are not expected. Here, state-of-the-art descriptions and interaction models are to be used to construct, refine and predict the 

robustness of quantitative retrieval algorithms. 

The project will require validation experiments to be analysed. These are expected to be based on P- and L-band airborne 

and, where possible, satellite datasets plus complementary remote sensing and other data or knowledge. In particular, data 

from recent ESA led airborne campaigns and from Japan’s ALOS satellite (PALSAR instrument) should be a significant input 

to the study. 

Although not the focus of work at this stage of maturity, initial consideration of assimilation into land surface process models 

would be encouraged as a theme setting the scene for future study activities. 

Deliverables: 

Prototype algorithm 

Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: SW operational by 2009 

Application/Mission: Biomass mission / Habitat Contract Duration: 18 months 





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12/Feb/09 



Title: 

ETM-157 

HBV devices 

Deliverables: 








Title: 

ETP-111 

Novel Simulation Interferometric radar altimeter 

Deliverables: 







TRP Reference: ETP-137 

Title: 

PARIS: additional work 

This activity aims at the development of the receivers and the signal processor (complex correlator unit) which would provide 

the power versus delay waveforms that carry the information on the geophysical parameters (ocean height, ocean wind, 

significant wave height and TEC). This activity will comprise the breadboarding and testing of the breadboard, according to the 

requirements defined during the concept definition study. 

Deliverables: 

Breadboard (+testing). 


Application/Mission: GNSS-R Contract Duration: 14 months 




Page 15 of 227




12/Feb/09 


ETP-137.A 

Title: PARIS Technology Concept Definition/Integration - Phase 2 

The study was divided into two phases. In Phase I the scientific requirements for mesoscale ocean altimetry have been 

reviewed and the concept of the PARIS altimeter instrument has been defined, including the requirements for the related 

building blocks. During the current Phase II these building blocks will be integrated into the PARIS airborne sensor 

demonstrator, including testing of the demonstrator. 

Deliverables: 

Technical note. Sensor demonstrator (+testing). 






TRP Reference: ETP-137.B 

Title: 

PARIS multi-beam array 

Navigation signals are weak and therefore a multi-beam antenna followed by a beam-former is needed. Navigation signals are 

narrow in bandwidth which means averaging and/or phase processing is needed to get altimetry accuracy below 10 cm. The 

main objectives of this activity are the design, breadboarding and testing of a multiple-beam array according to the 

requirements defined during the concept definition study. The most promising solution shall be identified , following an initial 

trade-off among different antenna solutions based on PARIS operational scenarios, the selection and preliminary design of a 

couple of promising candidate. 

Deliverables: 

Technical Note. Breadboard. 






TRP Reference: ETP-137.C 

Title: 

Beam Forming Networks for PARIS Concept 

Navigation signals are weak and therefore a multi-beam antenna followed by a beam-former is needed. Navigation signals are 

narrow in bandwidth which means averaging and/or phase processing is needed to get altimetry accuracy below 10 cm. This 

activity addresses the need for the development of a PARIS Beamforming Network for a receive only phased array. In order to 

obtain a compact, lightweight Beamforming Network, advanced technologies like multilayer Radiofrequency (RF) substrates 

and Monolithic Microwave Integrated Circuits (MMICs) shall be used. This activity will comprise the breadboarding and testing 

of the breadboard, according to the requirements defined during the concept definition study. 

Deliverables: 







Page 16 of 227




12/Feb/09 


Title: 

ETP-137.D 

PARIS Receiver and Signal Processor 

This activity aims at the development of the receivers and the signal processor (complex correlator unit) which would provide 

the power versus delay waveforms that carry the information on the geophysical parameters (ocean height, ocean wind, 

significant wave height and TEC). This activity will comprise the breadboarding and testing of the breadboard, according to the 

requirements defined during the concept definition study. 

Deliverables: 








Title: 

ETP-153 

New Radiometer concepts: Active Cold Load for Radiometer Calibration 

During the course of this study the concept for an instrument and a demonstrator will be defined and critical 

technologies/building blocks identified. 

Deliverables: 

Breadboard. 


Application/Mission: Post EPS/METOP Contract Duration: 24 months 





Title: 

SMOS 

ETP-163.C 

L-Band Radiometry / Advanced Filter and Correlator integration and validation 

Deliverables: 


Current TRL: TRL3 Target TRL: TRL3/4 Application Need/Date: TRL6 by 2006 



SW Clause : - Dossier0 Ref.: D47 



Page 17 of 227




12/Feb/09 


Title: 

ETP-190 

Modular Signal Generation and Detection for Future SAR Instruments 

Deliverables: 




SW Clause : - Dossier0 Ref.: D48 



Page 18 of 227




12/Feb/09 



Title: 

T103-01FP 

High efficient Laser Pump Source for LIDAR Applications 

Improving the efficiency of the laser pump source could benefit a space lidar system by either decreasing the power demand 

at spacecraft level or extending the performance and measuring capabilities of the space lidar. First generation of laser pump 

sources developed for ATLID or wind space lidars are deemed to be improved by new crystals and new pumping geometries 

which have been developed in European laboratories in the past years. This activity is focused on pulsed laser systems and is 

targeting a performance of 10% electro-optical efficiency. 

Deliverables: 

Breadboard of the laser 


Application/Mission: future Earth Explorer Contract Duration: 24 months 




TRP Reference: T103-02FP 

Title: 

Pulsed laser source in NIR for LIDAR applications 

The activity proposed is supporting potential new lidar missions aiming at sounding atmospheric constituents as CO2, O3, 

CH4, H2O.Pulsed laser source in NIR have been studied in the past for space lidars in the wavelength ranges of 2micron and 

10micron, other spectral domain in the NIR could be of interest, 1.4micron to 4micron (to be defined in link with GSP 

study).This activity aim at supporting the definition of these new lidar missions by providing a first assessment of available 

technologies and the suitability for high energy pulsed laser sources and space lidars. 

Deliverables: 

Technology review report. Design and performance assessment report. Test report. Laboratory demo. 


Application/Mission: future Earth Explorer Contract Duration: 24 months 




TRP Reference: T103-03MM 

Title: 

NIR Detector for LIDAR Applications 

The activity proposed is supporting potential new lidar missions aiming at sounding atmospheric constituents such as CO2, 

O3, CH4, H2O. 

The optical detector is an important sub-system in the lidar instrument concept. In general It has to provide features such as 

high quantum efficiency, photon counting capability and high dynamic range. 

Current studies of detectors for lidar are rather focussed from UV to visible spectral range and assessment/background on 

high performance detector in the 1.4-4micron spectral range for lidar applications is missing. This study should aim at 

supporting the definition of these new lidar missions by providing a first assessment of available technologies. 

Deliverables: 

Technology review report. Design and performance assessment report. Test report 

Current TRL: - Target TRL: TRL1 Application Need/Date: TRL5 by 2010 

Application/Mission: Lidar for Earth Exploration Contract Duration: 24 months 




Page 19 of 227




12/Feb/09 


Title: 

T103-10GD 

Back-illuminated thinned CMOS imager focal plane 

The suitability of Active Pixel Sensors (APS) with the on-chip capabilities of the CMOS technology for numerous detector / 

sensor application is presently uncontested. Furthermore, since charge is not being clocked, their susceptibility to 

proton-induced lattice damage is negligible (ionizing damage must be - and can be - mastered). The main drawback of 

monolithic APS is their electro-optic / radiometric performance disadvantage wrt modern, back-illuminated CCD's (a.o. 

uniformity, noise, QE): In particular, hyper-spectral imagers for Earth Observations (EO), which would otherwise strongly 

benefit from the system-on-a-chip capability of APS's, need the performance levels of the latter. The present activity aims at 

developing the back-illuminated (BI), thinned solution, offering a cost advantage over the hybrid-Silicon approach (as well as 

monoliticity) together with the same electro-optical performances as BI CCDs it is intended to eventually replace. Main 

challenges are the back-surface accumulation (as in the BI CCDs; mastered well here) and the optical inter-pixel isolation. 

Deliverables: 

Fully characterized performance demonstrator model of modest dimensions 

Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2009-2010 

Application/Mission: MTG Contract Duration: 24 months 




Optical Remote Passive Instruments - Detectors 


T103-11EE 

Enhanced Quantum Well Infrared Photodetector (QWIP) Array Detector: Definition and 

Title: 

optimisation 

Future thermal-infrared Earth-observation instruments are expected to need spectral channels near 15 microns for accurate 

temperature measurements. At this wavelength, long HgCdTe arrays often used 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 offer 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 which can be expected to 

extend further into the thermal-infrared range, and at a lower cost due to the growing maturity of QWIP technology. In the 

context of the EO programmes, it is necessary to pursue the development of a detector in the long IR wavelength range, 

typically around 15 microns, to meet the requirements of planned instruments, such as the IR Sounder for post-MSG. It is 

clear that these requirements have much in common with the development possibilities of the Quantum Well Infrared 

Photoconductor trial detector activity. Following the initial feasibility demonstration anticipated under that present contract, it is 

proposed to progress to a mission-representative array, in terms of pixel size, element number, uniformity, operating 

temperature and other parameters, to provide the basis for an EO instrument. Particular emphasis will be placed on 

characterising and optimising the relationship between dark current, operating temperature and cut-off wavelength. 

Deliverables: 

QWIP detector arrays demonstration model, operating in the 15 (TBC) micron band, with approximately with operating 

temperatures higher than 55K, with corresponding readout electronics and mission-relevant performance parameters 

Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2008-2009 

Application/Mission: Future IR missions Contract Duration: 24 months 




Page 20 of 227




12/Feb/09 


Title: 

T103-13MM 

L3CCD/EMCCD Technology for LIDAR Applications 

The L3CCD (Low Light Level)/Electron Multiplying technology is a rather new technology developed by E2V (UK) combining 

the CCD capability with the photon counting capability. The detector has been primarily developed for night vision applications 

but could have very interesting applications in space lidar remote sensing where very low backscatter signals have to be 

detected and photon counting capability is required for the acquisition chain. Such a detector would provide very high quantum 

efficiency, as other silicon CCDs associated with quasi-null detection noise. This would improve the Signal to Noise Ratio and 

the lidar capabilities, when compared to Accumulation CCDs as proposed for AEOLUS mission. It would furthermore provide 

shot-to-shot capability.If the suitability of such a detector, and in particular the amplification process, for lidar application is not 

demonstrated, it is then proposed to assess such a devices for generic lidar applications.The concept of such detectors is 

suitable for any UV-Visible and NIR lidar. The proposed tasks are : derive detector design requirements for lidar applications; 

breadboard and manufacture of CCDs based on EMCCD/L3CCD technology; define, develop and breadboard a set-up for 

operating the detector including proximity electronics Integration and Tests; performance consolidation and suitability of the 

detector for lidar applications. 

Deliverables: 

Detector design report Detector breadboard Electronics and set-up to operate the detector Reports on results of assessment 

and suitability to lidar applications. 


Application/Mission: Future LIDAR missions Contract Duration: 24 months 




TRP Reference: T103-16FP 

Title: 

Ultra-compact medium-resolution spectrometer for land application 

The objective of this activity is to develop a linear variable filter elegant spectrometer breadboard. This activity will make use 

of the linear variable filter technology developed in a previous TRP contract. The novelty of the concept is to glue a linearly 

variable filter glass directly onto the detector array, thus achieving a very compact spectrometer instrument for hyperspectral 

medium resolution applications. The linear variable filter coated on a cover glass will be packaged and aligned to a detector 

array, which has been already space qualified. The overall assembly of filter and detector will be optically and environmentally 

tested. 

Deliverables: 

Elegant breadboard of a linear variable filter spectrometer in which the filter is directly applied to the detector. The breadboard 

will be optically, electronically and environmentally tested. 


Application/Mission: GMES, Post-EPS Contract Duration: 24 months 




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Title: 

T103-24MM 

Next Generation panchromatic detectors 

Hyper-spectral imagers for EO covers both the visible and the infra-red (with varying long-wavelength cut-off)spectral region. 

MCT is the "workhorse" in the IR with adjustable cut-off wavelength, Silicon detectors (CCDs) cover the visible band. While 

these established detector technologies used for each wavelength region have very good performance, it requires the costly 

development /qualification of two (or more!) detectors and associated front-end electronics as well as a complex 

accommodation in the instrument's focal plane. 

MCT as a material has a very good response in the VIS, it is the substrate in these hybridized, "back-illuminated" detectors 

which is opaque at short wavelengths. The substrate removal (backside thinning) of this rather unforgiving material (in 

contrast to Silicon) is recently considered very prosing by the relevant industry. The development of such a "panchromatic" 

detector will allow the use of a single detector covering the entire spectral range of interest with the corresponding tremendous 

advantages (substantial simplification and savings in power, mass and size) including elimination of cross-calibration and 

co-registration problems for (Hyper-) spectral imagers as the primary instruments in EO. 

The activity shall consist in the development of a technology / performance demonstrator of modest dimensions, focussing on 

the optimization/mastery of the metallurgy and post-processing of the detector material and it's electro-optical performance. 

Deliverables: 

Detector array Demonstration Model 


Application/Mission: FLEX / Sentinel 5 Contract Duration: 24 months 






Title: 

T103-25MM 

Reliable space-compatible pump laser diodes 

This activity will focus on the development of improved wafer technology for high-power laser diode (array and/or stacks) as 

pump for solid-state lasers. Aspects of space environmental compatibility, lifetime and reliability are the key technology to be 

addressed. 

Deliverables: 

Improved high-power laser diode wafers samples, testing and characterization. 

Current TRL: TRL2-3 Target TRL: TRL3-4 Application Need/Date: TRL5 by 2008-2009 

Application/Mission: Forthcoming Lidar missions Contract Duration: 18 months 




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Title: 

T103-26MM 

Laser interferometry high-precision tracking for LEO 

The GSP study “Laser Doppler Interferometry Mission for Earth Gravity”, has identified a number of technological criticalities 

for LEO laser interferometry high precision tracking. The laser beam steering mechanism needs to be further investigated. In 

particular, repeatability of the beam pointing calls for a testing activity to ensure reliable results. Another issue is the final 

implementation of the laser interferometer: a heterodyne interferometer with amplitude modulation scheme has been proposed 

to mitigate photo-detector noise issues and proof-of-concept tests have been performed that confirm feasibility. Additional 

tests with state-of-the-art components and, possibly longer baselines, are needed to demonstrate the required performances. 

Deliverables: 

Test-bed demonstrator of critical technologies. 


Application/Mission: Future EO solid Earth Missions Contract Duration: 24 months 





Title: 

T103-27MM 

Large format APS detectors with on-chip intelligence for lightning imaging 

The Lightning Imaging Mission is intended for continuous mapping of lightning discharges during both day and night, into a 

geostationary orbit. Detection on a geostationary earth disk basis, real time observation of the total lightning flash activity 

represents valuable improvements for all operational applications. From geostationary orbit, the sensor will be capable of 

detecting all forms of lightning with a high spatial resolution and detection efficiency. Since this data will be distributed in real 

time, it will be an invaluable tool to aid weather forecasters in detecting severe storms in time to give advance warning to the 

public. The lightning imagery mission will also support applications in atmospheric chemistry, as lightning plays a significant 

role in generating nitrous oxides. The natural nitrous oxide budget is a matter of great uncertainty at this time, and long-term 

observations of one of its sources will prove valuable as the subject develops. 

The selected observation technique is based on the detection of the strongest lightning emission feature within the cloud top 

optical spectra produced by the neutral oxygen line at 777.4 nm. 

Deliverables: 

Sensor demonstration model 


Application/Mission: MTG Enhancement Contract Duration: 18 months 

SW Clause : - Dossier0 Ref.: T-325bis 




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T103-28MM 

High Energy Fiber-based Laser and Receiver development in the 2 micron region for 

Title: 

atmospheric CO2 and other greenhouse gases measurements 

In the context of the third cycle of Earth Explorer Core Missions the Agency is currently investigating the technical feasibility of 

an active optical sensing mission to measure the concentration of atmospheric carbon dioxide (CO2). A spaceborne 

Differential Absorption Lidar operating at the near-infrared absorption band of CO2 around 2.05 micron constitutes one of the 

candidate measurement concepts. Regarding the required system performance it appears that the use of pulsed laser 

sources with an average power on the several Watts level offers advantages over modulated continuous-wave (CW) laser 

based concepts. In the parameter regime of modest laser pulse energy (mJ level) and kHz pulse repetition rates an all-fibre 

laser concept is a promising candidate. Given its intrinsically high optical efficiency, system compactness and alignment 

insensitivity a fibre laser offers significant assets for spaceborne implementation. On the other hand the targeted fibre laser 

system will have to tackle major technological challenges that come with the combination of cutting-edge pulse energies out of 

a fibre and highly demanding spectral requirements in particular on centre wavelength stability and spectral purity. This activity 

will address the development of a laser diode pumped all-fibre laser source at 2.05 micron for spaceborne CO2 

measurements. 

Deliverables: 

Technology demonstrators of Tx/Rx key elements. 


Application/Mission: A-Scope Mission Contract Duration: 18 months 




Lidar Critical Solid-state Components 


Title: 

Instrument technology for fluorescence 

This activity will address the development of critical technologies for the measurement of fluorescence from low Earth orbit 

satellites (fluorosensors). The FLEX mission aims to produce global scale maps of vegetation photosynthetic activity 

contributing to biosphere and global carbon cycle studies. The mission is based on a three-instrument system for measuring 

plant fluorescence, multi-angle hyperspectral reflectance and canopy temperature. Early instrument pre-development shall be 

dedicated to the demonstration of the feasibility to measure the weak fluorescence signals over heterogeneous natural 

vegetation and to achieve high spectral resolution and spectral stability across a large field-of-view. 

Deliverables: 

Breadboard of critical instrument core unit demonstrating the achievable sensitivity of the fluorosensor. 



FLEX (Fluorescence Explorer) mission 

(selected for assessment studies for third 

cycle Earth Explorer Core Mission) 


18 months 





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Title: 

T104-15EE 

Vegetation Fluorescense Retrieval Algorithm 

Vegetation fluorescence can be used as an early indicator for the vegetation health, status and vitality. Observation of 

vegetation fluorescence from space would advance knowledge of the biosphere dynamics, one of the major issues in Earth 

Science. 

The vegetation fluorescence signal is composed by the far-red and red chlorophyll fluorescence and the blue-green 

fluorescence which are associated to different processes. The measurement of the photosynthetic activity of vegetation 

requires very accurate atmospheric corrections in order to isolate the fluorescence signal. 

The aim of this study is to define an atmospheric correction algorithm accurate enough in order to be used for the 

determination of the vegetation fluorescence signal from passive optical data. The study shall include a review of the main 

strategies used by the scientific community to perform atmospheric corrections. 

Deliverables: 

Tested algorithm 

Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: SW operational by 2009 

Application/Mission: FLEX Mission Contract Duration: 18 months 






Title: 

Non-linear Laser Crystal Development for Frequency Conversion 

The activity aims at developing solid-state nonlinear materials optimized for space applications as far as optical quality, 

conversion efficiency, laser induced damage threshold, radiation tolerance and vacuum operation are concerned. In particular: 

1) development and characterization of nonlinear materials from various European manufacturers with respect to their space 

suitability (e.g. radiation hardness, thermo-mechanical properties, laser-induced damage threshold in vacuum); 2) modeling 

and experimental investigation of degradation and failure mechanisms of solid-state nonlinear materials (including vacuum 

operation, contamination effects, colour-center formation, solarization, UV degradation). 

Deliverables: 

Technical note. Crystals samples, fully tested and characterised in a rappresentative environment. 


All Lidar missions, e.g. Earth Care, 


A-Scope 



Lidar Critical Solid-state Components 


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T104-18EE 

Aerosol modeling and synergetic aerosol correction algorithms for passive optical/IR 

Title: 

sensors 

The aim of this study is to enhance the wave interaction modeling of aerosols for passive optical remote sensing instruments. 

A brief review of existing aerosol models and aerosol atmospheric corrections shall be performed. Assessment of the 

empirical content and of the domain of validity of these models and algorithms shall be carried out. This study shall focus on a 

sound theoretical description of the aerosol effects on the top of atmosphere observed surface reflectances. Separated and 

concomitant multi-spectral / multi-angular / polarized approaches shall be studied to retrieve aerosol optical properties and to 

correct surface reflectances for their effects. Synergetic approaches are strongly encouraged to solve the uncertainties 

inherent to single instrument measurements and to test the general applicability of the aerosol correction algorithms output by 

the study. 

This activity would be beneficial for all passive optical imaging sensors (e.g. the candidate Earth Explorer missions A-SCOPE 

and FLEX, or the GMES Sentinel-2 mission) and should also include occultation measurement techniques. 

Deliverables: 

Tested prototype algorithm 


Application/Mission: A-Scope, FLEX, GMES Sentinel-2 Contract Duration: 18 months 





TRP Reference: T104-20QC 

Title: 

SWIR Laser Diodes 

Since a number of years Distributed-FeedBack (DFB) semiconductor laser diodes capable to be tuned to any frequency in the 

Short Wave InfraRed (SWIR) domain, with wavelenghts up to ~2.8 micron, are available. They have been used on-ground in 

telecommunications and can be regarded as the optical equivalent of the voltage control oscillators (VCO) in electronics: the 

emitted wavelength depends only on well-controlled parameters in a robust and reproducible way. Fast tuning is possible by 

e.g. current control and large mode-hop-free tuning ranges are achievable. Applications of these laser diodes in space 

include remote sensing by active limb sounding. Very good frequency and intensity stability performance is required for this 

and other applications, at output powers in the order of tens of mW in continuous wave (CW) operation. There is no 

experience with such diodes in space and the capability to maintain the ground-proven performance in the space environment 

is being questioned. This activity will select and fully analyse the most promising SWIR laser diodes with respect to the 

relevant optical, electrical, mechanical, reliability parameters, deriving specific conclusions for the envisaged applications. 

Deliverables: 

Technical note 


Active (optical) limb sounding missions, 

Application/Mission: e.g. ACCURATE; optical communication Contract Duration: 

missions 




12 months 

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1.4 - Platforms/ Other Instruments 


Title: 

T104-02EE 

Very large space antenna aperture - architecture trade off 

Earth observation and telecommunication antennas operating at low frequencies require large aperture in order to provide the 

required directivity. This activity will investigate innovative ways to generate very large aperture in space. Beside Reflect 

Arrays (RA) and Direct Radiating Arrays (DRA), innovative concept such as smart skins and lenses including only very 

compact switches and phase shifters (amplifiers being located on the spacecraft) can allow for drastic cost reduction in 

generating large aperture. Such innovative concepts are one order of magnitude less sensitive to surface errors thanks to 

phase compensation at elementary radiator level. An investigation of not continuous aperture like sparse array possibly 

coupled with Digital Beam Forming techniques and surface generated by formation flying satellite shall also be studied in the 

frame of this activity. 

Deliverables: 

Architecture trade-off report. Design report. No breadboarding (done in next activity). 


Application/Mission: P-band Radar Contract Duration: 12 months 




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12/Feb/09 


T104-11FP 

Autonomous High Data Rate Secured Downlink System - Breadboard (Old title: High 

Title: 

Data Rate Downlink Data Processor Chain – Breadboard) 

Security for Earth Observation (EO) systems including the space borne assets is one of the urgently to be addressed topics. 

In addition guarantee the safety of the space assets the integrity and originality of the data from observation by space borne 

platforms up to delivery to users on ground needs to be implemented. This classically includes security in uplinks and 

downlinks and after reception on ground. 

A study on link protection for EO systems (recently conducted by ESA, Contract No. 17176/03/NL/GS) showed, that currently 

no agreed security concept for the space/ground links exist. The existing ESA Packet Telecommand Decoder standard 

foresees only a very weak authentication scheme. Secure communication shall incorporate as minimum means for 

self-authentication, key agreement, message authentication and en-/decryption of telemetry data. Typically the high rate 

downlink is secured by encryption and message authentication. The encryption and authentication keys for the downlink are 

classically generated on ground and sent to the space platform via a command uplink, which needs then be highly secured. 

This is a feasible approach but requires the design of both a secured high rate downlink and a highly secured low rate up- and 

downlink. Also it requires a bi-directional communication link for the key exchange and authentication. Some ground stations 

are not providing real-time full duplex communication. 

A secured downlink system should be as far as feasible decoupled from the requirements of the command/control links, taking 

into account, that evaluation, standardization, development and implementation of a secured command and control link will 

take some years time from the current view. 

There are algorithms existing that provide secure key exchange and authentication by using a unidirectional link, only. Elliptic 

Curve (EC) based cryptography today is regarded as high secure implementation of the standard techniques. An EC based 

unidirectional scheme could provide the necessary level of security for a unidirectional link. 

The keys for encryption and authentication could in principle be generated on-board. This requires a cryptographically reliable 

key generator to be implemented space compliant. 

By combining both EC based unidirectional key exchange/authentication and on-board key generation an autonomous 

secured downlink system can be designed, which is decoupled from the security requirements of the command uplink. This 

could allow a straightforward “Sensor to User” end-to-end security concept. 

The currently used downlink systems provide some 100 Mbit/s data rate. The applied algorithms and protocols shall therefore 

be suitable for high rate implementation. 

The study objective is to identify alternative and optimised solutions for future applications in EO downlink systems and shall 

comprise following elements: 

• Analysis of Security requirements for downlink systems including the on ground part; 

• Design of a high rate secured downlink system with selection of appropriate algorithms and protocols; 

• Breadboard (BB) implementation of core technology to demonstrate feasibility of high rate application as well as space 

compliance. 

Deliverables: 

System Requirements Document, Breadboard of core elements + test report and test results evaluation. 


Application/Mission: EO, other programmes Contract Duration: 18 months 




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1.4.1 - Lidar (Source: TRP 2000-2003) 


Title: 

EEO-003 

Solid State Phase Conjungation 

Deliverables: 








Title: 

T-M-QCA-08-04 

Radiation testing and evaluation for Core Laser Technologies (CHOCOLATE) 

Deliverables: 







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12/Feb/09 

1.4.2 - Instruments and Sensor Breakthrough (Source: TRP 2000-2003) 


Title: 

EEA-044 

Geo Atmospheric Sounder Ph.1 

Deliverables: 









Title: 

Geo Atmospheric Sounder Ph.2A 

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 the 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 has been conducted in 2 phases, with the first phase comprising of definition of a concept, trade-offs and 

preliminary design. In order to promote innovation, 2 parallel contracts for phase 1 have been placed, to be followed by a 

selection by the Agency of the most promising instrument concept for demonstration in phase 2. Phase 2 will include detailed 

design, critical breadboarding, and manufacturing integration and test. 

Deliverables: 



Application/Mission: Earth Observation from GEO Contract Duration: 36 months 






Title: 

Geo Atmospheric Sounder Ph.2B 

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12/Feb/09 

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 the 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 has been conducted in 2 phases, with the first phase comprising of definition of a concept, trade-offs and 

preliminary design. In order to promote innovation, 2 parallel contracts for phase 1 have been placed, to be followed by a 

selection by the Agency of the most promising instrument concept for demonstration in phase 2. Phase 2 will include detailed 

design, critical breadboarding, and manufacturing integration and test. 

Deliverables: 



Application/Mission: Earth Observation from GEO Contract Duration: 36 months 





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1.4.3 - Earth Observation P/L (Source: TRP 2000-2003) 


MME-003 

Laser-cooled Atom Sensor for Ultra-High-Accuracy Gravitational Acceleration and 

Title: 

Rotation Measurements 

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. 

Deliverables: 

Definition of a technology roadmap, supported by key experimental verification and breadboarding. 


Application/Mission: HYPER Contract Duration: 18 months 

SW Clause : - Dossier0 Ref.: - 



TRP Reference: MMO-624 

Title: 

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. 

Deliverables: 

Technical note. 


Application/Mission: Future LIDAR Missions e.g. DIAL Contract Duration: 12 months 




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12/Feb/09 

1.4.4 - Payload Data Exploitation (Source: TRP 2000-2003) 

TRP Reference: PDE-KEO-001 

Title: Knowledge Centred Earth Observation - Phase 1 

Deliverables: 








Title: Knowledge Centred Earth Observation - Phase 2 

Today, a big discrepancy exists between the current EO data offers (data sets or images) and the real user need 

(information). The manual process mainly performed by experts to mine information from images is currently too complex and 

expensive to be applied systematically or even on just an adequate number of acquired scenes. This hinders the access to 

the petabytes of available or new data, penalises large projects of human relevancy like those related to environment 

monitoring, and might even leave totally undetected important events. 

The situation might become worse in future, since, in order to cope with requirements for monitoring events as well as global 

and local changes, more missions and also constellations are being deployed, with broader sensor variety (e.g.: gas detection, 

hyper-spectral), increasing data rates (higher resolution, number of channels) and increasing complexity (e.g. data formats). 

Therefore, the user desire for value-added information (focused, concise, reliable, timely, understandable, compliant with user 

processes) will likely remain unsatisfied, despite the availability of potential answers in the EO data, unless a breakthrough is 

introduced. Emerging technologies, which could support / ease experts’ tasks also by applying their knowledge to large data 

sets, could provide this breakthrough. These technologies should perform automatic information mining and classification, 

through the support of “intelligent” learning systems capable to discover, store and use the knowledge necessary to retrieve 

and fuse data and information from EO and non-EO fields, to model user semantic and domain of interest, and to mask the 

inherent complexity of the entire mechanism. 

The aim of the KEO research activities is to foster the enlargement of EO data utilisation, and in particular of the large 

archives of multi-mission and multi-temporal images. This should be obtained through a better support to research, 

value-adding industry, service providers and EO user communities (like those involved in scientific investigations, in risk and 

disaster management, or in the Global Monitoring for Environment and Security programme), by permitting in sequential 

steps: 

• Identification of the relevant data by its content (and not simply on the basis of spatio-temporal queries) 

• Direct access to the information contained in the data (as opposite to access to the images). 

This aim can be pursued identifying technological opportunities for the following main objectives: 

• Information mining and classification based on algorithms or knowledge for bulk EO data processing at large archive centres 

or at small companies (which manage limited but specialised data sets); in particular data relevant to classification attributes 

(also for enhanced catalogue searches) and / or information (avoiding the need to access the images), through: 

- Interactive Information mining based on acquired knowledge 

- Bulk classification based on acquired knowledge 

- Bulk classification based on feature extraction algorithms 

• Intelligent human interfaces, characterised by: 

- Learning capability for knowledge transfer (from experts) or its dynamic acquisition during user sessions 

- Capability to understand / talk user semantic 

- Capability to support complex multidiscipline queries 

- Advanced features (including graphical / multi-modal / multi-media interactions, self-adaptation to user interest, 

recommending, etc.) 

• Knowledge Discovery / Management 

• Advanced Support Techniques (e.g.: for data / information fusion, information management, time series handling, etc.). 

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Deliverables: 

Demonstrated methods and evaluated S/W architecture 


Application/Mission: Image Information Mining Contract Duration: Ph. 2 12 months 





Title: 

PDE-User-05.B 

Multiple Image Registration - MIR 

Deliverables: 







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12/Feb/09 

1.3.1 - Optical/Electro-Optical Technologies (Source: TRP 2000-2003) 


Title: 

97/XAO08 

Quantum Well Photodector 

Deliverables: 







TRP Reference: MMO-635 

Title: 

Assessment of Phasing Capabilities of Fibre Optic Devices 

Optical phased arrays are today a well accepted technology for future space exploration interferometric missions, present 

attractive performance, mass and complexity advantages for laser communication systems, LIDAR systems and can play a 

major role for advanced applications like power relays. The aim here is to review the main requirements of telescope array 

systems (interferometry, LIDAR, power relay) and identify the main critical components and parameters for each application 

and assess possible solutions. There shall be a selection of an application for the evaluation of the capability of a fiber-based 

telescope array, e.g. for stellar interferometry. There is also the need for an evaluation of the performance of the system for 

the selected application and issue recommendations for solutions allowing to achieve the required performance. 

Deliverables: 








Title: 

Assessment of Phasing Capabilities of Fibre Optic Devices 

Deliverables: 







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12/Feb/09 


2.1 - Missions in Development Phase: BEPI-COLOMBO 


Title: 

T201-02MM 

Development of microlasers for laser altimetry on future planetary orbiters 

The realisation of a diode pumped microlaser for planetary altimetry requires the development of a monolithic solid-state 

device providing efficient coherent pulsed emission with high repetition rates and modest pulse energies. The active material 

that provides these characteristics can be achieved by Nyodymium (Nd) or Yterbium (Yb) doped host materials, which 

provide very good conversion efficiencies to fundamental wavelengths in the 1 micron region. The Yb doped systems have 

better energy storage capability and thus may be a better option for the pulsed microlaser. The high repetition rates can be 

provided by a q-switch, which, in the monolithic case, would be a passive and not an active device. The passive unit is a 

saturable absorber and avoids the need for a high voltage source, as would be required for an electro-optic q-switch in a 

discrete resonator. This has many obvious advantages for space operations. The laser dimension can be a small as 1mm3 or 

less for Continuous Wave operations. For pulsed operation the need to be below surface and bulk damage thresholds will 

dictate the eventual size of the laser due to laser fluence levels being dependent on beam diameter. Such a system does not 

presently exist in Europe and is deemed to be a requirement for Europe to provide a viable alternative to the conventional low 

repetition rate high energy systems which are currently available. 

Deliverables: 

Demonstrator of a micro-laser transmitter. 


Application/Mission: Bepi-Colombo, JEP/NEO Contract Duration: 24 months 




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Title: 

T201-03SC 

Breadboard & Demonstrator of a Micro-pore Optics 

The activity shall focus on building a large size breadboard of a x-ray optic. Considerations shall be given about the coating of 

the walls for optimum reflection. Techniques for quality control of the alignment of the pores and of the coating shall be 

defined. 

More in detail, it shall be developed a demonstration of an x-ray optic, formed from pairs of micro channel plates mounted into 

Wolter I tandem pairs, integrated into a structure that maintains them in their correct positions. 

A previous ESA contract (C15668) developed the manufacturing capability to draw square fibres and stack them into a radial 

configuration, suitable for making MCP plates that were then slumped and used as constituents of a Wolter I optic. This 

contract follows on that work to demonstrate a mounted arrangement for the tandems into a complete optic, for which x-ray 

measurements shall demonstrate the current capability. 

Following a thorough revision of the technology development activities needed to the mission preparation, some weakness 

points have been highlighted and appropriate measures have been undertaken to reduce the development risks. 

So at present, the activity encompasses the following main steps: 

- Phase 1: review of requirements and design of the optic and the structure. To cope with programmatic and technical needs, 

as well as to minimise risks, a first CCN has been implemented for a parallel concept structure design. 

- Phase 2: Manufacture of MCP plates and breadboard structure. Through the above mentioned CCN, the original Phase 2 

has been modified to include a CDR (critical design review) to select the most appropriate solution from the parallel detailed 

structure designs available at the end of Phase 2a. Following CDR it was decided to pursue no further technical development 

of the MCP plates or structure. The remaining funds will be used to procure MCP tandem plates from the prime, Photonis, at 

the current state of the art, using the material that has already been purchased under this activity. These will be used by the 

BepiColombo MIXS instrument team in the development of their micro-pore optic breadboard. 

Deliverables: 

Micro pore optic tandem plates. 


Application/Mission: Bepi-Colombo Contract Duration: 26 months 




TRP Reference: T201-04SC 

Title: 

Scintillator sensor development 

The activity addresses the development of new high-density high-light output scintillators for gamma-ray spectroscopy. 

Specific materials include the lanthium halides (LaBr:Ce and LaCl:Ce) and Lutenium based compounds (e.g., LuAP, LuYAP, 

LuYSO). These compounds are at present in a very early stage of development and production needs to be scaled to 

industrial volumes. An important part of the activity is a representative set of tests, aimed to establishing the viability and 

suitability for the planetary environment. 

Deliverables: 

Several representative crystals and one breadboard detection system. 


Application/Mission: Bepi-Colombo Contract Duration: 18 months 




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Title: 

T201-06SC 

Active Pixel Sensor Focal Plane Assembly for NIR 

The main objective of this activity is to develop, fabricate and validate an APS sensor to cover the wavelength range 

0.4-2.2um, possibly extending the wavelength range to 2.5um to be used as sensor onboard the BepiColombo mission. 

Previous development activity was mainly driven by European military needs and more recently, earth observation 

programmes. In the framework of the earth observation programme, a 256x1000pixel focal plane array has been developed 

and flown (SWIR hyperspectral application); however the sensor is targetted to the SWIR range. A cut-off at 0.8um is due to 

the CdTe substrate on which the HgCdTe (MCT) detector is grown. In order to fullfill the science requirements of 

BepiColombo and indeed potential future scientific satellites, there is the need to further develop the technology in the 

following areas: 

1) reduction of the thermal current; 2) extension of the wavelength range down to 400nm; 3) radiation hardening/verification. 

A compact focal plane assembly shall be attempted for mapping spectroscopy in the visible and NIR (Near InfraRed) 

wavelengths. Possible technologies to be explored are back-thinned MercuryCadmiumTelluride (MCT) or 

IndiumGalliumArsenide (InGaAs). The detector should be part of a breadboard for the imager/spectograph VIHI onboard 

BepiColombo. This activity will benefit from a experience gained in a similar activity, concluded with D/EOP, where a 250-1000 

MCT detector was developed. A further development and optimization is needed in order to accomodate the wavelength 

range from 0.4 to 2.2 microns. 

Deliverables: 

Compact focal plane breadboard. 


Application/Mission: Bepi Colombo Contract Duration: 24 months 





Title: 

Active Pixel Sensor Focal Plane Assembly for NIR - Additional work 

The main objective of the original activity has been to develop, fabricate and validate an APS sensor to cover the wavelength 

range 0.4-2.2um, possibly extending the wavelength range to 2.5um to be used as sensor onboard the BepiColombo mission. 

Previous development activity was mainly driven by European military needs and more recently, earth observation 

programmes. In the framework of the earth observation programme, a 256x1000pixel focal plane array was developed and 

flown (SWIR hyperspectral application); however the sensor is targetted to the SWIR range. A cut-off at 0.8um is due to the 

CdTe substrate on which the HgCdTe (MCT) detector is grown. In order to fullfill the science requirements of BepiColombo 

and indeed potential future scientific satellites, there has been the need to further develop the technology in the following 

areas: 1) reduction of the thermal current; 2) extension of the wavelength range down to 400nm; 3) radiation 

hardening/verification. 

A compact focal plane assembly has been attempted for mapping spectroscopy in the visible and NIR (Near InfraRed) 

wavelengths. Possible technologies being explored are back-thinned MercuryCadmiumTelluride (MCT) or 

IndiumGalliumArsenide (InGaAs). The development is in a first instance intended for the imager/spectograph VIHI onboard 

BepiColombo, but could serve future missions requiring hyperspectral capability from visible to NIR wavelength range. This 

activity benefits from the experience gained in a similar activity, concluded with D/EOP, where a 250-1000 MCT detector was 

developed. Further development and optimization has been needed in order to accomodate the wavelength range from 0.4 to 

2.2 microns. 

In order to cover the additional development required when carefully reviewing the Bepi Colombo missions needs, a CCN will 

be placed. 

It will allow to cope with with a number of technology issues. In fact, the manufacturing and testing of a hyperspectral detector 

(0.4 to 2.2 um) for the Bepi Colombo/VIHI instrument appears to be extremely challenging at many levels. Due to the limited 

budget, the detector concept proposed by SOFRADIR is heavily relying on heritage of a previous D/EOP contract. This 

heritage is particularly obvious for the CMOS readout circuitry, which will be entirely used as such. 

This major design parameter has led to the need of total ionizing dose tests to prove the capability of the readout to withstand 

the harsh environment of Bepi Colombo. Within the original contract, it was possible to accommodate only one TID test, using 

an existing device of the EOP. However it is clear that this unique test will only respond very partially to the radiation 

tolerance, a second test would definitely give more credit to the campaign. The outcome of the test will determine whether the 

BepiColombo/VIHI team will use this detector or if they need to rely on a US backup (Rockwell or Raytheon). It is worth noting 

that the results of this radiation campaign may also be of particular interest for EOP and its future developments. Last but not 

least, a better knowledge of the TID behavior of the device will considerably improve our understanding of the proton tests, 

aiming at studying the potential displacements damage effects occurring in the thinned Mercury Cadmium Telluride substrate. 

The tests which will be carried out by SOFRADIR will cover the main electro-optical characteristics of the final device. Due to 

timescale and technical limitations of SOFRADIR’s test bench, some specific tests will not be achievable within this contract 

(e.g. spot scanning for visible MTF…). Therefore, it is of prime interest to have the possibility to carry out additional tests on 

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the deliverable at ESTEC (where more adequate equipments exist). The present CCN will cover the needed upgrading of the 

deliverable by adding some peripheral units, including cooler and control electronics, to enable the above mentioned post 

delivery tests. 

Deliverables: 

Compact focal plane breadboard. 


Application/Mission: Bepi Colombo Contract Duration: 12 months 





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Title: 

MMO-630 

High Precision Optical Metrology 

The objective of this activity is to improve the reliability of the optical metrology sensors as developed to breadboard level for 

precise formation flying of the DARWIN satellites. The aim is to reach the maturity status of "elegant breadboard" 

representative in form, fit and function for some presently critical parts (e.g. interferometric head, heterodyne modulation 

sub-system and fibre coupling system). An emphasis shall be put on the measurement stability in vacuum and under 

reasonable thermal variations as well as vibrational constraints and over representative distances. The activity's detailed 

definition shall be made with an aim of using and testing this type of metrology on PROBA-3 and other space missions. The 

output of this activity will also help to better define follow on activities currently foreseen in the TRP, addressing miniaturisation 

of the current concepts and new measurement techniques. 

Deliverables: 

Elegant Breadboard 


Application/Mission: Darwin, Proba III Contract Duration: 12 months 




Roadmap: N/A 


Title: 

Passive optical components for interferometry 

The first objective of this activity is to design, manufacture and test passive optical components for interferometry. This 

includes the development of achromatic beam splitters, dichroic filters, compensation and polarization plates, wide band 

antireflection coatings, etc. The second objective is to establish manufacturing techniques and technologies to achieve a 

constantly high optical quality of the above-mentioned components, such that differences between the interferometer arms are 

minimized. The functionality and performance of the components shall be demonstrated by means of a breadboard that shall 

be subjected to a verification test campaign in an environment compatible with DARWIN mission (e.g. Cryogenic 

Interferometry Facility).The broadband infrared beam (6-18 micron) has to be split in a specific ratio and accurately over the 

full wavelength range. Current technology for beam-splitters does not allow such accurate beam splitting over wide spectral 

ranges. Furthermore a number of dichroic plates, polarization beam splitters, compensator plates, antireflection coatings (e.g. 

multilayer dielectric stacks or sub-nm gratings, etc. on bulk and optical waveguides), reflective mirrors (with special metallic 

and associated protected coatings) are also used in the interferometer. The selected contractor will investigate and define 

techniques to guarantee and control minute differential effects between the arms of the interferometer during the 

manufacturing process, and will propose techniques capable of measuring such very small differences (e.g. differential 

spectral response, differential polarization effects, differential chromatic dispersion, etc). 

Deliverables: 

Breadboards of the passive components for interferometry, and modelization software. 


Application/Mission: Darwin Contract Duration: 24 months 




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Title: 

T203-09SC 

Wavefront tilt sensor 

In this activity the wavefront tilt sensor shall be designed, breadboarded and tested. The testing shall be performed in a 

representative environment. Optimum wavelengths and operating points shall be specified. 

In the DARWIN mission a telescope pointing error will cause a tilt of the interferometer’s input beam, which translates into an 

amplitude error after wavefront filtering. The interferometer’s nulling performance is proportional to the square of the wavefront 

tilt angle, and already small tilt values will cause unacceptable amplitude differences. The baseline system design foresees 

high accuracy star trackers mounted in the focal plane of each telescope spacecraft with a large CCD detector. An alternative 

design is to sense the wavefront tilt as received in the central beam combiner spacecraft. The wavefront sensor is to be 

mounted in the cryogenic payload module of the telescopes or the beam-combiner spacecraft. This shall be done coherently 

and complementary with the Fringe Sensor developments. 

Deliverables: 

Detailed resource specification of the sensor; breadboard; preliminary characterization of the performance; recommendations 

about integration and beam routing. 








Title: 

Integrated optics 

This activity deals with the design and manufacturing of optical components and functional devices in integrated-optics 

technology. In comparison to a realisation of the same functionality by bulk optics, an integrated optics device provides large 

benefits by its low mass and its low sensitivity to temperature and other environmental factors. Whereas integrated-optics for 

telecommunications (operating at 1.5 micron) is a well-mastered technology, the spectral range of DARWIN is not yet 

explored or mastered. The challenge is to find materials which are transparent in this spectral range, but allow also defining 

two-dimensional waveguiding effects using reliable manufacturing processes. Therefore a number of different materials and 

technologies (e.g. integrated optics by photo inscription, Index guided photonic crystals) will have to be investigated 

experimentally, and the most promising combination will be selected for the manufacturing of sample devices. 

Deliverables: 

Integrated-optics components to be used in an interferometer breadboard. 






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Title: 

T203-19MM 

FIR linear Detector Array 

The purpose of this activity is to develop a novel detector technology to realize the linear focal plane array (FPA) for the 

DARWIN mission spectrometer. The linear array must cover the wavelength band going at least from 6 to 18 µm with 

state-of-the-art sensitivity and take into account the mission thermal budget. The wavelength band and sensitivity 

requirements are essentially constrained by extra-solar planet contrast considerations. In addition, system design issues 

favour higher operating temperatures than those offered by existing detector technologies. Phased contract. 

Deliverables: 

Technology demonstrator 







Title: 

Single mode waveguide 

The wavefront quality of the interfering beams has to be improved in order to achieve the required nulling performance. This 

improvement can best be performed by filtering by means of propagating the wave in a single mode waveguide. 

Pre-developments of IR single mode fibres have been successfully completed, resulting in the identification of promising 

technologies such as SilverHalide, Calcogenide and Tellurium based waveguides. In this activity the manufacturing process 

shall be refined and the detailed properties of the waveguides determined. 

Deliverables: 

Process assessment, technology demonstrator. 






The proposed activity is not directly related to a harmonised subject. 

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2.2.1 - Darwin (Source: TRP 2000-2003) 


Title: 

EEO-048 

BiB detector 

Deliverables: 







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Title: 

MMO-632 

Fiber optical 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. 

Deliverables: 

Breadboard 


Application/Mission: Darwin 






Title: 

Fiber optical wavefront filtering ph.1 







Deliverables: 

Breadboard 


Application/Mission: Darwin 






Title: 

Fiber optical wavefront filtering Ph.2 







Deliverables: 

Breadboard 






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Title: 

MMO-634 

High Stability Optical Benches for Darwin 

The functionality and the performance of future science interferometric missions like DARWIN are based on the availability of 

ultra-high stability optical benches capable of maintaining dimensional stability of picometers over periods of hours without 

active control. This activity aims to assess the optical system technologies and materials suitable for achieving these stability 

and design, develop and test a representative scaled optical bench under cryogenic conditions demonstrating picometer 

stability over periods of up to 3 hours. 

Deliverables: 

Demonstrator 







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2.3 - Missions in Pre-Assessment Phase: XEUS 


Title: 

T204-03MM 

High performance X-ray optics 

HPO optics will require further development with a view to improving the spatial resolution and overall mass. In addition a 

range of reflective coatings need to be developed ranging from Au to Ir together with layered synthetic microstructures for 

hard X-ray reflectivity. Building on the ongoing HPO Activity, the angular resolution shall be improved while optimising the 

required mass resources. In addition the high performance of the optics shall be extended to the edges of the optics modules. 

Deliverables: 

Assessment of the coating process and samples testing. 


Application/Mission: XEUS Contract Duration: 18 months 




Not directly linked to Harmonised Technology. 


Title: 

Micropore baffle 

On either side of the XEUS mirror elements a baffle system is required to provide X-ray and visible stray light baffling, and 

provide thermal and contamination control. A hierarchical micropore baffling system is required. Standard sheet metal 

baffles, for example in aluminium, could be significantly improved upon with use of pore optic technology, for instance in glass 

or silicon. Test samples need to be manufactured with relevant shape and dimensions to demonstrate the higher efficiency 

established with such systems. This activity complements T204-03MM. 

Deliverables: 

Breadboard. 

Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5>2011 






TRP Reference: T204-06SC 

Title: 

Low bandgap superconducting sensor 

Small arrays of DROID devices have been demonstrated, but to meet XEUS energy resolution requirements, fabrication on 

narrower band gap material should be demonstrated. Methods to massively increase the array size to match field of view 

requirements are required. 

Deliverables: 

Process assessment and samples manufacturing. 







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Title: 

T204-07MM 

TES Spectrometer 

Small arrays of Transition Edge Sensor devices have been demonstrated to work at high X-ray energies, but do not meet 

XEUS energy resolution requirements. These detectors form a baseline for the next generation X-ray observatories 

instrumentation. For the XEUS energy range, fabrication of devices with lower heat capacity is necessary to meet the 

required performance. At the same time massively increasing the array size to match field of view requirements is required, 

which needs development of lead-out technology and multiplexing. The low energy performance needs to be developed & 

optimised for resolution and efficiency. 

Deliverables: 

Technical notes. Breadboarding. 






TRP Reference: T204-08MC 

Title: 

50mK Continuous Cooling System 

Future Scientific Mission as e.g. Xeus require temperatures for the detection chain between 50mK-100mK. For such 

applications, the need to develop in advance a vibration-free cooling system with a long lifetime which covers the cooling in 

the temperature range 4.5K down to 50mK was identified. 

The objective of this activity is to design a 50 mK cooling system, compatible with current mechanical coolers providing a 

pre-cooling temperature of 4.5K (4.5K- JT cooler qualified for Planck Mission). 

Different technologies can be used for building a system that reach 50mK, as e.g. Adiabatic Demagnetisation Refrigerators, 

dilution cooler or hybrid systems using He-sorption cooler for pre-cooling at 300mK. Current European technologies such as 

ADR or He-sorption are single shot devices and therefore only allow a limited observation time or are open-loop systems 

(dilution) with a limited lifetime. To comply with the need for the required observation times, large bulky systems would be 

required with a long recycling time in combination with a JT pre-cooler. A continuous system therefore allows building smaller 

systems and sizing the pre-cooling chain to the average power dissipation, rather than to the peak power dissipation required 

by a single-shot system. 

The concept of a cooling system will be selected during the proposal evaluation and within the initial phase of the activity a 

conceptual design will be established based on resource budget (mass, volume, electrical power etc). In the second phase the 

most promising concept(s) shall be designed, manufactured and tested on breadboard level. To reduce as much as possible 

the interface problems between different types of coolers and refrigerator systems, efforts shall be put in designing a self 

standing, compact cryogenic system. 

The requirements of the cooler will be derived from the XEUS payload architecture study. 

Deliverables: 

Breadboard Cooler and associated technical documentation 


XEUS mission (launch >2015), FIRI 

Application/Mission: Contract Duration: 

mission (launch >2025) 



Cryogenics 


30 months 

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2.3.1 - XEUS (Source: TRP 2000-2003) 


Title: 

SCI-X10.a 

Superconducting Read Out for Microcalorimeters 

In the frame of the development of cryogenic instruments with large array sizes, as required to meet the science requirements, 

it is proposed to develop a low noise readout electronics, specifically tailored to x-ray microcalorimeter arrays. In this 

development program a low noise readout electronics based on a high bandwidth Super-Conducting Quantum Interference 

Device (SQUID) will be studied, in conjunction with a suitable multiplexing scheme. The main issues to be addressed include 

the design of the amplifier system, power requirements, noise performance and the thermal requirements of the amplifier 

readout. These issues will be studied theoretically and then validated against breadboard designs and models. 

Deliverables: 

Technical Note (design of the amplifier system with multiplexing scheme, power requirements, noise performance and the 

thermal requirements of the amplifier readout). Breadboard (+testing). 







TRP Reference: SCI-X10.b 

Title: 

Superconducting Read Out for Superconducting tunnel junctions 

In the frame of the development of cryogenic instruments with large array sizes, as required to meet the science requirements, 

it is proposed to develop a low noise readout electronics for superconducting tunnel juncions. The electronics shall be based 

on high bandwidth Super-Conducting Quantum Interference Devices (SQUID) in conjunction with a suitable multiplexing 

scheme. The main issues to be addressed include the design of the amplifier system, power requirements, noise 

performance, reduction of channels through multiplexing and the thermal requirements of the amplifier readout. These issues 

will be studied theoretically and then validated against breadboard designs and models. 

Deliverables: 

Technical Note (design of the amplifier system including multiplexing topology, power requirements, noise performance and 

the thermal requirements of the amplifier readout). Breadboard (+testing). 







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Title: 

SCI-X11 

Large Format Detector Read-Out - Additional work 

Within the original contract a basic development for a read-out for future high resolution imaging spectrometers is undertaken. 

The study will focus on the electronics required to readout future high resolution imaging spectrometers. It will result in a 

complete instrument capable of delivering packaged data containing spectral and imaging outputs from detector arrays of up 

to 10,000 pixels. The key issues to be addressed are the design of the full readout chain, power requirements, noise 

performance, thermal requirements, and the rate and speed limitations. 

More in detail, a read-out electronics for large array detectors shall be designed, fabricated and tested. The design shall be 

scalable, radiation tolerant and highly integrated. In order to reduce the required interface circuitry to an absolute minimum, 

the ASIC shall include: 

1) ultra-low noise preamplifiers for each individual detector pixel, to achieve detector statistical noise limits 

2) programmable filter stages for each pixel 

3) event detection circuitry, with internally programmable threshold settings 

4) analog-to-digital converters 

5) event prioritization circuitry 

6) digital glue logic. 

In addition to the basic development summarised above, it is now proposed to place a CCN to cover additional testing and 

validation issues. During the development of the ASIC, it was realized that the circuit could not be sufficiently tested without 

any detector connected to it. Therefore, in order to validate the full functionality, it is required to bump-bond a 2-D detector 

array to the ASIC and test this assembly under X-ray radiation. In addition, and for the specific need for BepiColombo, the 

ASIC needs to be validated under gamma and proton irradiation. These radiation tests will also help to understand the basic 

limitations of the particular foundry and CMOS process, which is used not only for this development but also by several other 

institutes / companies intending to design ASIC for BepiColombo and Solar Orbiter. 

Deliverables: 

Set of ASIC wafers and ASIC + Detector assemblies as well as the full design databases. 


Application/Mission: XEUS / Bepi Colombo Contract Duration: 12 months 




N/A 


Title: 

SCI-X4 

Optical rejection filter 

Deliverables: 







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Title: 

SCI-X8 

Multilayer coatings for high energy 

Deliverables: 







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2.4 - Long Term Mission / Technology Reference Missions: Gamma Ray Imager 


Title: 

T206-01SC 

Gamma Ray Optics Development 

This activity aims at developing a combination of technologies that achieves true gamma ray focusing. This will allow improved 

localization and signal: noise for gamma ray observatories, and would be usable as a concentrator for gamma ray 

spectrometers. The aim is to develop imaging optics for the Gamma-ray energy range in the region of 100keV to ~2MeV. 

Using a Laue crystal diffraction lens, it is possible to focus gamma rays with quite high efficiency over rather narrow energy 

bands. The field of view, energy band and efficiency are all parameters that must be traded off in a practical design. The use 

of mosaic crystals, with slight misalignment between the microblocks within a large crystal, allows some tuning of these 

important parameters. The activity will develop improved crystal growing techniques to allow control of these parameters. 

Materials such as Ge, Cu and pyrolitic graphite, among others, will be investigated, and growth techniques will be correlated 

with measurements of the diffraction efficiency. For an optimized crystal choice, a system study will be performed to determine 

the parameters for a tunable system that allows (for a fixed focal length) to establish the angular control requirements to adapt 

the crystals to focusing individual emission line energies of astrophysical interest (e.g. annhilation energy, or nucleo-synthesis 

products within supernovae remnants). 

Deliverables: 

Mirror samples with graded density multi-layers, and Laue crystal arrays demonstrator. 


Application/Mission: Gamma Ray Imager (>2015) Contract Duration: 18 months 




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2.6 - Other Technologies / Missions 


Title: 

T214-05SC 

High Resolution, Low Mass, Pore Optics 

Introduction of novel lightweight materials will be used in the design of high resolution deployable low mass optics. The activity 

is to develop a preliminary breadboard phase for future astrophysics missions. The aim of the technology development is to 

maintain the high throughput and resolution via. a high reflectivity over a wide range of wavelengths, with a flexible design 

geometry dependent on wavelength. 

Deliverables: 

Low mass optics breadboard. 

Current TRL: TRL2-3 Target TRL: TRL3/4 Application Need/Date: TRL5 by 2010 







Title: 

High Resolution, Low Mass, Pore Optics: additional work 



maintain the high throughput and resolution via. a high reflectivity over a wide range of wavelengths, with a flexible design 


Deliverables: 









Title: 

High Resolution, Low Mass, Pore Optics: additional work 



maintain the high throughput and resolution via a high reflectivity over a wide range of wavelengths, with a flexible design 


The present extension to the original contract (rider to contr. number 18981) is due to the purchase of a additional silicon 

wafer to create an X-Ray Optical Unit (XOU), using a pair of CeSiC brackets that have already been manufactured under the 

original contract. The additional activity includes the assembly, alignment and X-ray test of XOU in petal structure, also 

manufactured under the original contract. 

Deliverables: 








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2.7 - GAIA (Source: TRP 2000-2003) 


Title: 

SCI-G16 

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 payload data rate for scientific missions 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 taking into account current and future missions (e.g. GAIA, Wide Field Imager), then implement this 

algorithm in software as a library element for applications based on ESA's space microprocessors. 

Deliverables: 

Optimised algorithm. 


Application/Mission: GAIA Contract Duration: 12 months 




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Title: 

T202-01MM 

Solar Blind sensor 

Detectors based on a Wide-Bandgap Semiconductor (WBG) as most likely candidate for the development of Solar Blind 

imaging sensors. These materials provide the following advantages over narrower-gap semiconductors: visible blindness, 

radiation hardness, VUV and EUV improved response etc. Alternative back-up solutions include MCP converters with APS 

readout. 

Deliverables: 

Breadboard. Technical data package. 


Application/Mission: Mission: SolO/SPO Contract Duration: 24 months 





Title: 

Solar sails Materials 

This activity will concentrate on the development of the appropriate Sail material. Approaches to the fabrication of such sail 

material with Al/Cr coating, 2 µm thick film, loading 8 g m-2 need to be studied. Sail degradation resulting from the material 

thermal & radiation effects need to be considered via sample tests. In addition the material needs to be compliant with the 

sail deployment system & final jettison of a large ~150 x 150 m2 sail. 

Deliverables: 

Samples. Technical data package. 

Current TRL: - Target TRL: TRL2-3 Application Need/Date: TRL5 by 2012 

Application/Mission: SPO/IHP Contract Duration: 24 months 





Title: 

Low bandgap EUV sensor 

UV/EUV and soft X-ray sensors based on low bandgap compound semiconductors are an ideal development to improve 

performance (efficiency and resolution) beyond sensors based on silicon. This development will concentrate on the material 

science of high quality films couple to the fabrication of the basic diode and small arrays. 

Deliverables: 



Application/Mission: SPO Contract Duration: 24 months 




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Title: 

T215-04MM 

Planetary surface Dating Instrument (Luminescence dating) 

The age of a planetary surface is a very important information in order to understand surface modulations and overall 

geodynamic processes of a planetary body. So far no approach has been made to adapt a specific technique for this 

purpose. Optically Stimulated Luminescence Dating is used on Earth commonly to measure sediments up to an age of one 

million years. This technique makes use of the interaction between ionizing radiation and solid matter. Free charges are stored 

in lattice defects and accumulated over time. Under defined conditions the electrons fall back on lower energetic levels and 

release light, the luminescence signal. The intensity of the signal is relative to the age of a buried grain. This method can be 

adapted to investigations on Mars, as such data from the Martian surface are elementary for understanding of the evolution of 

the planet. The same can be applied to other and Near Earth Objects (NEO). 

Deliverables: 



Application/Mission: NEO missions Contract Duration: 24 months 






Title: 

Jupiter Radiation Environment and Effect Tools 

The severe Jupiter radiation environment will be modelled. As a starting point the JPL and Salammbo code results will be 

used. The complete Jupiter spatial and energy range will be treated, and dynamic as well as long-term averages will be 

modelled. The results will be useable for engineering. The development will include the appropriate improvements to tools for 

shielding, internal charging (DICTAT), electronic radiation effects and solar array degradation as appropriate for the Jovian 

environment. Effects models for spacecraft nuclear elements will be included. 

Deliverables: 

Requirements analysis, models of environment and effects implemented in an engineering toolkit. 


Application/Mission: Jupiter missions Contract Duration: 24 months (Ph1&2) 

SW Clause : Operational SW Dossier0 Ref.: T-9 



Space Radiation Environment Models and In-Orbit Monitors (UPDATE) 

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Title: 

T215-06EP 

High radiation tolerant Low Intensity Low Temperature GaAs solar cells 

For Jupiter missions high efficiency / high radiation tolerant Low Intensity Low Temperature (LILT) solar cells, capable to 

survive the extreme Jovian radiation environment, are required. As the current technology status is not proven to be adequate 

to withstand the environment it is proposed, in a first step, to upgrade the existing and relevant photovoltaic/assembly facilities 

to allow for an appropriate characterization and verification of solar cells/assemblies w.r.t. the essential Jovian environment 

parameters. The definition of the facility performances and accuracies required shall be based on a study with a strong focus 

on the minimization of the solar array design margins to be applied when designing and verifying the technologies for missions 

to Jupiter's vicinity. 

In parallel to the facility related tasks of this activity a high radiation tolerant multi junction LILT solar cell structure shall be 

designed, the expected solar cell production performance predicted and compared with the performance and cost (recurring 

and non-recurring) of the existing 3G cell from RWE. 

It is planned to use the results from this activity to decide if a Jupiter mission specific solar cell or other solar array related 

developments are required to enable potential European Jovian missions. 

Deliverables: 

Technology assessment (of existing and potential of Jupiter specific solar cell performance). 

Upgraded facilities to allow for tests in Jovian representative environment. 


Application/Mission: Jupiter missions Contract Duration: 18 months 

SW Clause : - Dossier0 Ref.: N/A 





Demonstration of the deployment of a highly integrated low power ice penetrating radar 

Title: 

antenna 

The main objective of this activity is to design and demonstrate by test the deployment and stability of the Yagi antenna for a 

low power ice penetrating radar suitable for the investigation of the icy shell of Europa, one of Jupiter's moons. This moon has 

been recognised as one of the key interests for planetary exploration by the international scientific community and is the goal 

of the Jovian Minisat Explorer Technology Reference Study performed by the Agency. The contractor shall perform the 

antenna Radio Frequency (RF), mechanical and thermal design/analyses and manufacture/test a Demonstration Model 

representative of the intended flight design in terms of materials and the following functions: Hold down, release, deployment, 

latching and pointing. The activity shall fully demonstrate the feasibility and the mechanical functionalities of the developed 

model. The antenna design is expected to be based on a highly integrated bars and hinge mechanisms (possibly elastic 

collapsible hinges) assembly due to the very stringent mass and stowed volume requirements. Main critical issues lie in the 

antenna layout, the deployment kinematics, dynamics and simulations, the testability of the mechanical functions and, the 

selection of the most suitable materials with respect to ageing and sensitivity to radiations to be encountered in the Jovian 

environment in order to guarantee both the deployment and the RF performances of the antenna. 

Deliverables: 

Deployable antenna demonstration model 


Application/Mission: Jupiter missions Contract Duration: 24 months 





T-196, T-732, T-373, T-409, 

T-753 

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Title: 

T215-08EE 

Wideband Spectrometer 

This activity is devoted to the design and practical implementation of wide-band spectrometer system. The activity will start 

with a trade-off between several state-of the art technology options. After a preliminary design the activity will be followed by 

breadboarding at critical component level after which a re-design will be performed with a full-scale breadboard. Special 

emphasis will be given to low mass and low power consumption. 

An initial CDF study in very close co-operation with the science directorate has clearly demonstrated the need for this activity 

where the mass of the instrument was driving the entire design. With direct relevance to Dossier 0 Science requirements, this 

proposal was elaborated and justified within the Harmonisation dossier on Millimetre and Submillimetre waves together with 

experts from user directorates who have approved and supported it as relevant and important for their future programmes. 

Deliverables: 

Spectrometer demonstrator 


EO and Science missions (e.g. Jupiter, 


Venus,..) 



Passive Millimetre and Submillimetre wave Instruments 



Title: 

T215-09MC 

H2 Sorption Cooler 

In the frame of a previous TRP activity a He4 Sorption cooler was successfully developed. The temperature range covered by 

the cooler is 14.5K down to 4.5K. Pre-cooling at 14.5K–15K is required by the He4 Sorption cooler in order to work properly. 

Using same technology as developed until now, changing the running gas to hydrogen, the new breadboard might be able to 

cool down from 50K to 14.5K. It is the objective of this activity to demonstrate that this is feasible. 

Tasks include: 

- re-design 

- breadboarding 

- extensive testing. 

Deliverables: 

Technical note, breadboard, test report. 


Science missions such as DARWIN, 


XEUS (not before 2018). 




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3.1 - Advanced habitats 


Title: 

T301-03MC 

Design Verification & manufacturing aspects relevant for inflatable Modules 

The present activity is proposed in the frame of the development of larger pressurised volumes for habitation (less mature 

than Al modules), required by future manned space missions, longer and more demanding on the crew that LEO missions. 

This activity should investigate design, verification and manufacturing aspects relevant for inflatable modules, e.g. analysis 

and test technologies, specific design aspects such as the interface between hard and soft parts of the structure w.r.t. air 

tightness, strength, etc. (e.g. docking system or window to inflatable shell) and deployment systems. Preliminary tasks are:- 

Identification of possible materials to be used for inflatable modules- Identification of possible material configurations - 

Investigate design, verification and manufacturing aspects- Investigate analysis and test technologies for flexible materials- 

Specifically look at juncture between hard and soft materials- Evaluation of the findings. 

Deliverables: 

Technical datapackage, subscale breadboard of inflatable module. 


Manned missions, exploration (next step 

Application/Mission: should be an in-flight inflatable Contract Duration: 18 months 

demonstrator) 





Title: 

Polymerisation of Composite Structures in Free Space 

The capability of polymerisation in free-space conditions makes possible the in-orbit deployment of large structures with a long 

lifetime. Objective of the proposed activity is the development of the curing process of composite structures in free-space 

conditions. In particular: a reference curing process concept shall be developed (thermal, UV, etc); some environmental 

testing shall be performed; curing models shall be studied and breadboarded. 

Deliverables: 

Process description report. Curing process breadboard. 


Application/Mission: all inflatable (rigidizable) strucutres Contract Duration: 18 months 




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12/Feb/09 

3.2 - Automation and advanced robotic technologies 


Title: 

T302-02MM 

Compact Automatic Tool Exchange Device 

Deliverables: 


Application/Mission: exploration missions Contract Duration: 24 months 





Title: 

Vision Based Manipulation of non-co-operative objects 

Non-cooperative objects, in conventional robotics terms, are those which do not provide help to robotics means to ease their 

manipulation. In the case of robotics vision, this definition applies to objects not equipped with optical markers. This activity 

shall develop a concept of the software/hardware to allow a robot system equipped with a stereo camera sensor to 

operate-on/manipulate human-made non cooperative objects. This shall allow real time visual serving control of robot motion 

directly into the sensor frame. The activity shall also develop concepts for robust techniques to overcome the problems 

created by the extreme lighting conditions typical of orbital applications. 

Deliverables: 

Breadboard including Vision based manipulation software and hardware, Calibration and test equipment for the software. 






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3.2.1 - Automation & Robotics (Source: TRP 2000-2003) 


MMA-622 

Title: Dextrous Robot System - Phase 1&2 

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: 

1. Phase 1 (200 kEuros): System-level requirements analysis and definition, kinematics / structural / thermal / dynamic / 

control analyses, system architectural design and specification of requirements for sub-systems (joints, limbs structure, end 

effector, latching, ground support equipment). 

2. Phase 2 (500 kEuros): Evaluation and trade-off 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 

demonstrator. 

3. 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, demonstration by system-level 

testing. 

Deliverables: 

Technical Note. System design and Requirements definition. Joint demonstrator (design, manufacturing and testing). 7 joints 

development, manufacturing, integration and testing in a dedicated test-bed. 







Title: Dextrous Robot System - Phase 3 

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: 

1. Phase 1 (200 kEuros): System-level requirements analysis and definition, kinematics / structural / thermal / dynamic / 

control analyses, system architectural design and specification of requirements for sub-systems (joints, limbs structure, end 

effector, latching, ground support equipment). 

2. Phase 2 (500 kEuros): Evaluation and trade-off 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 

demonstrator. 

3. 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, demonstration by system-level 

testing. 

Deliverables: 

Technical Note. System design and Requirements definition. Joint demonstrator (design, manufacturing and testing). 7 joints 

development, manufacturing, integration and testing in a dedicated test-bed. 


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12/Feb/09 

3.3 - Closed loop life support technologies 


Title: 

T303-02MC 

Bioregenerative Life Support Basic Development 

MELISSA has as ultimate objective the development and on-ground demonstration of the basic technology needed to 

establish, maintain and control, with absolute minimum need for resupply, closed manned environments (e.g. Lunar Base, 

Mars Outpost, Mars transit vehicles).The work is focused on the ground feasibility demonstration of a closed loop of 

compartments, each specialised for a specific processing task. Thus waste products from the "crew" compartment are 

progressively processed as they move around the loop, finally arriving back at the beginning in the form of regenerated food, 

water and oxygen. Although the ultimate goal is space, there is considerable scope for terrestrial spin-off en route, which has 

already been realised in the form of 2 patents. Generally speaking, individual partners specialise in particular areas, e.g. one 

particular compartment, system control algorithms, etc. The results of the past research have demonstrated the theoretical 

validity of the concept, as well as the feasibility of each independent compartment. The main objectives of this new phase will 

be a pilot scale demonstration, and performance assesment, with 3 coupled compartments. 

Deliverables: 

Technical notes. Breadboarding. 


Application/Mission: manned mission, exploration Contract Duration: 36 months 





Title: 

T303-11MC 

Air Sampling System for Microbial Contaminants Identification 

Development of an air sampling system concept for microbial contaminants identification. The proposed activity will exploit the 

experience of terrestrial and space industry, respectively in terms of concentration of microbes from large air volume, DNA 

extraction and amplification, and of reduced gravity constraints on liquid handling, hardware miniaturisation, to develop an 

instrument for continuous sampling of air on board manned spacecraft. Within this study it is proposed to review and trade-off 

the potential concepts of air sampling system compatible with future amplification of the genetic information of the microbial 

contaminants, to select the most promising concept, to built a breadboard unit, to test and evaluate this development. This 

work will be harmonised with the requirements and developments of MIDASS Project (Microorganisms Detection in the Air 

Space Systems). 

Deliverables: 

Deliverables will include design reports, drawings, test data and developed hardware (breadboard). 


Application/Mission: manned mission, exploration Contract Duration: 18 months 




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12/Feb/09 

3.4 - Crew Health and Performance 


Title: 

T304-01MM 

Integrated Countermeasures for microgravity effects 

Prolonged microgravity leads to impairment of many Physiology Systems (PS), amongst them bones, muscles and the 

neuro-sensory system. Countermeasures to counteract the lack of gravity stimulation are delivered mainly via physical 

exercise (treadmill, ergometer) or use of special suits such as the Penguin (in MIR), but results are just moderate. To prepare 

for interplanetary missions - and for long-duration ISS stays, additional musculo-skeletal and neuro-sensory countermeasures 

need be developed. The aim of this activity is to develop and test technology concepts for integrated countermeasure systems 

for each above-mentioned PS, study the compatibilities of the countermeasure technologies (bone, muscle, neurosensory), 

define complementarities, assess the design drivers and define a good ergonomics of the system. A biofeedback technology 

will also be studied where the vibration frequency, amplitude and direction will be tuned to optimise the musculo-tendinous 

responses (EMG, reflexes). The technologies will be characterized and, when possible, evaluated on humans. 

Deliverables: 

Technology application, evaluation report, specifications for adaptation to ISS. 

Current TRL: TRL2 Target TRL: TRL2-3 Application Need/Date: TRL5 > 2012 

Application/Mission: Manned Exploration Contract Duration: 18 months 




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12/Feb/09 

3.5 - Free-Flyers (Rendezvous and Docking, In-Orbit Assembly and Servicing) 


Title: 

T306-03MM 

Selfcalibrating 3-D optical metrology 

3-D imaging system has been developed that uses an interferometric technique to obtain range and profile information. The 

system is self-calibrating, once knowledge of the camera and projector are known, and can handle discontinuities. An 

improvement to the current system is proposed that would allow it to operate without a piezo stepper, allowing a significant 

mass saving. The objective of this work is to breadboard and test the new design. This follows from a concept studied under 

fast-track SME TRP initiative. Deliverables: Design, build and test of a self-calibrating, 3-D vision system breadboard. Analysis 

of system limitations as regards spatial and temporal resolution, field of view etc. 

Deliverables: 







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12/Feb/09 

3.6 - Instrumentation for Life Science 


Title: 

T307-05MM 

Immuno-Biochemical Analyser 

In-situ ISS Bio-chemical analysis has been recognized a high priority since many years. Results would then become available 

in real time, drawbacks of cryo-preservation would be avoided (download weight, biochemical degradation). Previous attempts 

to adapt ground clinical analyzers for space use didn't turn out positive results. Hence in the previous TRP, it was decided to 

explore a technology concept for a ISS-compatible biochemical analyser. Out of this activity, two major technologies have 

been confirmed or adapted:- a new microtiter plate (37.5 mm x 20mm 96 reaction wells) with capillary distribution 

(microgravity compatible) to be used for bio-chemical measurements,- a Two-Photon excitation (TPX) reader, combined with 

optical pressure pumping, has been validated on above microtiter plate, making it suitable for immuno-chemistry 

measurements. The aim of this activity is to develop the set of enabling technologies for a ISS-compatible biochemical 

analyser in a mid-term future to measure the classes of biochemicals required by ISS physiology research or astronaut 

medical follow-up. 

Deliverables: 

Full technology concept of a ISS-compatible biochemical analyzer, test adaptation procedures, evaluation results. 

Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: TRL5 > 2010 

Application/Mission: ISS/Aurora Medical Contract Duration: 24 months 





Title: 

Virtual reality stimulator 

Cognitive neurophysiology is identified as one of the research themes of interest for the ISS. Besides electroencephalography 

and electromyography, it requires neurosensory stimulators, amongst them the visual/aural ones. Up to know, because 

computer power was limited, virtual reality generators for neurophysiology were custom-designed, closed systems, used only 

for one experiment. Moreover, it was not possible to make easy and simple modification of the protocols as scientists usually 

need it, this instead required major software and hardware redesigns. Making use of the enhanced capabilities of computers 

and virtual reality devices, the proposed activity aims at studying the enabling technologies for the realization of a 

multi-purpose, flexible Virtual-Reality generator for cognitive-neurophysiology, that could be used over several ISS increments 

by a the wide community of users. 

Deliverables: 

Documentation, enabling technologies and software for multipurpose virtual reality generator, and evaluation report. 

Current TRL: TRL1 Target TRL: TRL2 Application Need/Date: TRL5>2010 

Application/Mission: ISS/manned exploration Contract Duration: 18 months 




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12/Feb/09 


Title: 

T307-15MM 

Life Support Technology for MISS 

The aim of the activity is to develop a life support system for small animals with good scientific performance and low logistic 

load. Typical technologies to be considered include compensation systems for O2 consumption and removal of produced CO2 

including recycling methods. Furthermore odour control and interaction with the water supply and the waste collection have to 

be taken into account. An initial concept phase will be followed by the breadboarding and functional/biological testing of the 

complete selected concept. 

Deliverables: 

Fully functional and verified breadboard of a life support system for small animals. 


Application/Mission: Photon Contract Duration: 24 months 




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12/Feb/09 

3.7 - Instrumentation for Physical Science 


Title: 

T308-03MM 

Oxygen sensing/control 

Any device operating at elevated temperatures has a strong demand for measuring partial Oxygen pressures as the content of 

this radical deteriorates every material in long term, and oxygen outgassing from compounds needs to be immediately 

detected to prevent facility damage. Within this activity a development of a sensor technique to measure oxygen partial 

pressure in the Electro-Magnetic Levitator processing atmosphere via electrolytic cells with high vacuum compatibility is 

proposed. Based on this sensor a control can be set-up that will be completed within this activity in terms of feasibility, too. In 

addition the activity will also focus on methods to reduce residual oxygen concentrations. 

Deliverables: 

Tested sensor breadboard, oxygen reduction and control loop breadboard 


Application/Mission: ISS MSL/EML Contract Duration: 24 months 





Title: 

Enhanced Mini Lda 

This activity aims at enhancing the features of a 1D-Mini-LDA System currently under development under ESTEC Contract 

No. 16554/02/NL/CP.The optical components of the 1D-Optical Measurement Head are already prepared for an upgrade to a 

2D-Optical Measurement Head. In addition to the upgrade of the measurement head the expected FSL/EC breadboard is 

planned to be used together with the head after having been extended on h/w and s/w level to allow for real simultaneous 

measurements of two velocity components and their directions. After design, manufacture, integration and calibration, the 

2D-Mini-LDA System shall be applied to representative experiments to verify its scientific measurement performance. 

Deliverables: 

One 2D Optical Measurement Head, representative for the FSL micro-gravity experiments, integrated into an 

updated/calibrated BB system for scientific measurement performance verification. Final Reoprt (+ measurements 

experimental verification). 


Application/Mission: ISS FluidLab Contract Duration: 18 months 




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12/Feb/09 

3.8 - Payload Data Handling 


T310-02ES 

Title: COTS based space borne computer 1 

The use of COTS components for the design of on-board computers is not new but has always been considered in a 

case-by-case basis when appropriate. Convergence between several industrial domains: aircraft, automotive and space have 

demonstrated that COTS-based solutions used in these domains can be applied also to space. Evolution of the system design 

techniques is also rendering possible the use of robustness by design techniques better than intrinsic robustness by radiation 

hardening. It is then proposed to study COTS based solution for on-board computers in the domain of high reliability oriented 

systems and safety & availability oriented systems. The objective of this activity is to propose solutions towards space borne 

COTS based computers and to assess their efficiency and usability for real space missions. At the software level there are 

considerations about the reintegration of a failed unit. It is difficult point since modern powerful processors contain on-chip 

caches. Reloading of these caches is not possible, and thus the software in the triple units has to be aware that a 

resynchronisation is taking place and thus needs to flush the data and instruction caches of the non-failed units. Continuation 

of this activity is foreseen in GSTP. 

Deliverables: 

Breadboard 


Application/Mission: Robotics, Exploration Missions Contract Duration: 12 months 




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Title: 

EME-018 

SDE and Space Palmtop Applications 

Deliverables: 







TRP Reference: EME-019 

Title: 

On-Board Model Checking 

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. 

Deliverables: 

Architectural concept + building blocks. (Operational SW usable by the community) 

Current TRL: - Target TRL: S/W release Application Need/Date: SW operational >=2007 

Application/Mission: planetary exploration Contract Duration: 9 months 




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12/Feb/09 


Title: 

ESD-023 

Mission Execution Crew Assistant 

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 optimize the ground/crew task sharing in a 

long duration mission scenario. 

Deliverables: 

Crew assistance tool demonstrator. 

Current TRL: 

Target TRL: 

Application Need/Date: SW operational (preparation 

- 

Prototype 

of manned missions) >=2015 

Application/Mission: manned planetary exploration Contract Duration: 18 months 





Title: 

ETD-037 

High Performance Resilient Computer For Autonomous Robotics 

Deliverables: 







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12/Feb/09 


Title: 

MMA-624 

Satellite Servicing Building Blocks 

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 (e.g. 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 refuelling could be made 

sensibly lighter thus decreasing launch costs. Furthermore lighter satellites would allow higher utilization 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, manufacture and test a demonstrator of servicing hardware. 

Deliverables: 

Technical note (analysis of objectives/tasks for servicing, architecture, interfaces). Servicing hardware demonstrator (design, 

manufacture and test). 


Application/Mission: all spacecraft Contract Duration: 24 months 




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12/Feb/09 

3.10 - Aurora 

TRP Reference: 03/E15 

Title: 

Experimental and theoretical study of Mars dust effects 

In the frame of planetary exploration, a number of issues are related to presence of particles in the flow surrounding a probe 

during its atmospheric entry. Three major situations can be addressed: 

(1) For Mars and Earth entries in particular, the presence of dust or ice high altitude in the atmosphere. 

(2) The particles (carbon etc ) produced by the ablation of the heat shield and/or by potential re-condensation of gases in 

expansion regions. 

(3) The potential presence of organic material (spores, cells ) transported by the flow and contaminating unprotected payloads 

of the probe. 

This last point is particularly important in the case of sample return exobiology missions. 

The problems associated with the presence of the particles can be listed follows: 

(1) Mechanical/thermal abrasion of the heat shield 

(2) Increased convective fluxes linked to earlier flow transition turbulence 

(3) Inclusion of additional chemical species in the flow 

(4) Two phase flow 

(5) Emission of radiation by the dust particles 

(6) Electrostatic effects 

(7) Potential chemical contamination of payload 

(8) Potential biological contamination of payload 

It is proposed to perform an experimental and numerical study to assess the problems abovementioned for exobiology and 

Mars sample return missions of Aurora programme. The focus of the study will be on points 1, 2, 7 and 8: Assessment of the 

influence of dust and particles on the transition, the mechanical and thermal loads of the heat shield as a first task, 

assessment of contamination, and in particular of survival of biological samples in the hypersonic flow around a probe. 

For each of the two tasks, a review of the literature and in particular of the work performed in the frame of ISTC 1549 shall be 

performed, numerical approaches shall be selected, and facilities shall be identified for validation tests. A limited number of 

test cases shall be set-up and the numerical and experimental methodology selected shall be applied to the test cases. An 

effort shall be made to summarize the results and prepare engineering tools or correlations appropriate for design of future 

Aurora missions. 

Deliverables: 

Technical note (experimental/numerical study, assessment of problems for exobiology/Mars sample return missions). 






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12/Feb/09 

TRP Reference: 03/W15 

Title: 

Solar cell development for Mars exploration missions 

The program is devoted to the characterisation and pre-development of the solar cells to be used for operating in "Low 

Intensity Low Temperature" (LILT) conditions. The possible range of environments which could be experienced at Mars is very 

wide and dependent upon, in particular, the planetary coordinates, season, surface location and dust conditions, which 

together dictate the solar spectrum, intensity and diffuse/direct content. This study will characterise solar cell performance 

over a range of environmental conditions. However, in order to allow appropriate preparation for Exomars, particular emphasis 

will be given to solar cell characterisation over the specific range of conditions, which are expected to be relevant to this 

mission. In addition, investigation of the development of solar cells for Mars initiated in the framework of the Aurora General 

Study Programme (which focussed upon two possible mission scenarios) will be continued in order to further define the 

trade-off's associated with the requirements of different possible Mars missions. This is expected to include manufacture and 

testing of one or more new solar cell designs in order to further improve our understanding of the possible performance benefit 

under an appropriate range of Mars conditions.. 

Deliverables: 

The following functional devices will be delivered: 

* 200 solar cell assemblies 

* Technology Data Package 


Application/Mission: Exomars Contract Duration: 18 months 




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12/Feb/09 


Title: 

Solar cell electrical characterization facility for Mars exploration missions 

The differences between the Mars environment and the orbital environment in which the solar cells are most commonly used 

require dedicated facilities to test both the solar cell and the photovoltaic assembly Coupons. 

The critical differences between the two environments having strong impacts in the solar cell and photovoltaic assembly 

testing are: 

- Solar intensity and spectrum modified by dust 

- Low temperature operation 

- Dust deposition on the solar array surface 

The Mars surface is characterized by low temperature, low solar intensity and by a solar spectrum which is strongly affected 

by the atmosphere. The sunlight reaching Mars is strongly scattered by the dust particles hanging in the air; for this reason the 

diffused component is larger than the direct light. The direct part of the spectrum, incident on the Mars surface is more intense 

in the blue region whereas the diffuse part is more red due to the blue light absorption. Being the opacity of the atmosphere 

defined as the optical depth, the total spectrum is redder when the optical depth increases. It can be roughly assumed that the 

solar cells will work on Mars at an average temperature between -80oC and +20oC with a solar constant between 0.2 and 0.4. 

These conditions are however changing over the course of one day and depend on the seasons and atmospheric 

phenomena. 

The atmospheric dust does not remain suspended in the atmosphere, but deposits out of the atmosphere onto any horizontal 

surfaces with a dust coverage rate of 0.3 % power loss per day. This is potentially the major lifetime limiting factor for a solar 

power system on any Mars mission longer than 100 days. 

For these reasons it is very important to upgrade and to modify the existing test facilities dedicated to the characterization and 

the qualification of the photovoltaic components, in order to be prepared for the future Aurora missions on the surface of Mars. 

To achieve the above described objectives, a first activity is proposed. The consideration / simulation of Martian dust 

deposition effects on the solar array surface will be addressed in another new Aurora technology activity entitled Martian Dust 

Simulation Facility for Solar Cells . The main technical objective is the realisation of a solar cell electrical characterization 

facility adequate to the specific Mars environment requirements by modifying and upgrading the already existing INTA facilities 

at SPASOLAB. 

These facilities will be adapted to the electrical characterization of both Silicon and Gallium Arsenide based solar cells. 

The following development steps are proposed as follows: 

- Modification/Upgrading of the optical system of Spasolab multi-zone solar simulator, dedicated to the multi-junction GaAs 

solar cells, by means of the realisation of a dedicated filter able to meet the requirements of the Mars surface illumination 

spectrum 

- Modification/Upgrading of the optical system of Spasolab single source solar simulator, dedicated to the Silicon solar cells, 

by means of the realisation of a dedicated filter able to meet the requirements of the Mars surface illumination spectrum 

- Modification/Upgrading of the Cryostat dedicated to the electrical characterization of the solar cells at low temperatures, in 

order to be suitable for the existing larger solar cells. 

Deliverables: 

Assessment/realisation of a solar cell electrical characterization facility (by modifying/upgrading the optical system of Spasolab 

). 

Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL4 in 2008 

Application/Mission: Mars Exploration Contract Duration: 18 months 




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12/Feb/09 


Title: 

Martian dust simulation facility for solar cells 

The differences between the Mars environment and the orbital environment in which the solar cells are most commonly used 

require dedicated facilities to test both the solar cell and the photovoltaic assembly Coupons. 

The critical differences between the two environments having strong impacts in the solar cell and photovoltaic assembly 

testing are: 

- Solar intensity and spectrum modified by dust 

- Low temperature operation 

- Dust deposition on the solar array surface 

The Martian dust does not remain suspended in the atmosphere, but deposits out of the atmosphere onto any horizontal 

surfaces with a dust coverage rate of 0.3 % power loss per day. This is potentially the major lifetime limiting factor for a solar 

power system on any Mars mission longer than 100 sols. 

For this particular reason it is very important to upgrade and to modify existing test facilities that could allow the 

characterization and the qualification of the photovoltaic components under representative Martian dust conditions so as to 

timely match the needs of future Aurora missions on the surface of Mars. 

To achieve the above mentioned technical objective, the following activity is proposed: 

- Development of a Martian dust simulating facility for solar cells and coupons by modifying an already existing Wind Tunnel 

facility. 

This activity will be mainly devoted to the realization of an environmental test chamber aimed at blowing representative Mars 

dust over the samples in order to perform specified dust adhesion experiments. 

The activity will be based on a Mars Dust and Environment Specification to be provided by ESA. Special emphasis will be 

more particularly placed on the definition of the detailed composition of representative Martian dust particulates and of the 

environmental conditions to be reproduced under testing. This test specification will be elaborated in the currently running 

Aurora technology activity, titled Solar Array design and technology development for Mars exploration missions. 

Deliverables: 

Development of Martian dust simulating facility for solar cells/coupons by modifying an already existing Wind Tunnel facility 

(Mars dust particulate/environment study and consequent realization of an environmental test chamber). 

Current TRL: TRL1 Target TRL: TRL4-5 Application Need/Date: TRL5 in 2009 

Application/Mission: Mars Exploration Contract Duration: 18 months 




Solar Generators & Solar Cells 

TRP Reference: 04/G15 

Title: 

Precision landing GNC test facility 

To mitigate technical, schedule and cost associated with enabling GNC technologies of future planetary missions requiring 

safe precision landing, they have to be tested as much as possible on ground in a precision landing GNC test facility. The 

main objective of the activity is to develop a precision landing GNC test facility that will emulate real lander dynamics and test 

safe precision landing navigation, guidance and control technologies to the performance level required by future planetary 

landing vehicles. Starting from the outputs of the on-going activity on "Verification Strategy for Smart Lander", the activity will 

involve: (1) analysis and trade-offs of precision landing GNC test facility configurations, inc. test facility requirements definition; 

(2) mechanical and electrical detailed design of the selected baseline test facility configuration; (3) manufacturing, assembly, 

acceptance tests and test campaign definition, and (4) integration of smart lander technologies from on-going TRP activities 

and test campaign results analysis. 

Deliverables: 

Precision Landing GNC Test Facility; Documentations (technical data package, summary report and abstract), including 

precision landing test facility configuration trade-offs/analysis, detailed design, test results, GNC SW demonstrator, test 

plan/results. 

Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: TR5 in 2008 

Application/Mission: ExoMars, MSR Contract Duration: 24 months 




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12/Feb/09 


04/G25 + T306-01ES 


Title: 


Building upon the heritage from ATV, the European reference rendezvous with manned targets in LEO, and ongoing 

technological developments applicable to rendezvous systems, the main objective of the study is to design and develop the 

2nd generation of space autonomous rendezvous GNC systems applicable to a wide set of potential missions (rendezvous 

with cooperative, non cooperative and natural objects). Special emphasis is given on a vision-based solution for the 

rendezvous navigation system from target acquistion to terminal approach. Two image processing algorithms, namely 

Features Extraction and Object Recognition & Matching, will be developed, prototyped and tested. These algorithms will be 

implemented on the NPAL camera breaborad that has been developed vision-based soft landing applications. In order to 

support image processing validation in the overall navigation chain, PANGU will be extended in order to generate 

representative space scene. Guidance Expert and robust control techniques, that take into account the specificity of 

performing rendezvous in elliptical orbit, will be developed and tested via Monte Carlo simulations. Finally, the preliminary 

design of the Autonomous Mission Management (AMM) will rely on a multi-layer architecture based on a decision level 

(planner) in charge of the onboard operation management, an execution level in charge of the time line detailed definition and 

execution, and an independant safety protection level in charge of the collision avoidance. The planner will make use of the 

guidance expert system in charge of re-computing adequate trajectories that fulfil the current system constraints. The AMM 

design will be validated via computer simulations using an upgraded functional engineering simulator. 

Deliverables: 

SW/HW, test facility + documentation. Documentation (technical data package, summary report, abstract), including 

autonomous rendezvous & capture GNC test facility configuration trade-offs/analysis, detailed design, GNC SW demonstrator, 

test plan/results. 

Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: 

Application/Mission: exploration missions e.g. MSR Contract Duration: 24 months 






Title: 


The activity combines two sub-activities: 

1. Autonomous Rendez-vous GNC test facility (04/G25): redez-vous/docking and capture operations are of primary 

importance for sample return missions as well as in-orbit servicing and inspection. On the other hand, to mitigate technical, 

schedule and cost associated with enabling GNC technologies of future planetary missions requiring rendezvous and sample 

capture, they have to be tested as much as possible on ground. The overall study objective is to take a major step towards a 

European capability for autonomous orbital rendezvous and docking. Starting from recent study results on lidar/vision-based 

GNC systems and heritage from ATV GNC development, the activity concerns (i) the adaptation or enhancement of existing 

mission and simulation tools, real-time avionics and dynamics test benches for the validation of a high integrity autonomous 

multi-range rendezvous & docking control system (HARVD); (ii) the rapid prototyping of the autonomous mission and vehicle 

management (AMM) software and fault detection, diagnosis and recovery (FDIR) software and the integration of the on-board 

HARVD S/W demonstrator; (iii) the testing of its real-time performance and autonomous operations and transition capabilities 

(terminal rendezvous phase) with hardware-in-the-loop (HIL) in a laboratory environment. 

2. Integrated Multi-Range Rendezvous Control System (T306-01ES): The main objective of the study is to define, develop and 

breaboard a generic multi-mission rendezvous GNC system applicable to a whole set of potential missions (rendezvous with 

cooperative, non cooperative and natural objects). The generic GNC architecture (sensors, actuators, algorithms, avionics) 

will be defined for two mission scenarios: in-orbit servicing (Earth environment) and sample return (Mars environment). The 

autonomous navigation system will make use of recent technology breakthroughs in vision and imagin lidar. Absolute and 

relative attitude and position measurements, from RF sensor and optical camera or lidar sensor, will seamlessly be integrated 

using an iterated, extended Kalman filter. Robust guidance and control algorithms will be developed for rendezvous in circular 

and elliptical orbits . For maneuver planning, it is foreseen to use a Lambert planner at long range with genetic algorithm 

optimization of start and transfer times. A Simplex planner with path constraints will be used at close range. Finally, a 

breadboard of the on-board software of the integrated multi-range rendezvous control system, inc. mission management and 

FDIR functions, will be developed and real-time performance tests with electrically stimulated relative navigation sensors and 

simulated actuator units on the ESA generic avionics testbed. 

Deliverables: 

SW/HW, test facility + documentation. Documentation (technical data package, summary report, abstract), including 

autonomous rendezvous & capture GNC test facility configuration trade-offs/analysis, detailed design, GNC SW demonstrator, 

test plan/results. 


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12/Feb/09 

Application/Mission: exploration missions e.g. MSR Contract Duration: 24 months 




TRP Reference: 04/K15 

Title: 

Mars climate database and physical models 

In order to compute accurately the incoming solar flux on inclined solar panels, a Monte-Carlo radiative transfer code for the 

martian atmosphere has been developed by LMD. Additional work is now needed to complete the Mars Climate Database and 

Physical Model development. In particular, the following main tasks are foreseen: validation of the Monte-Carlo radiative 

transfer tool for Mars, with a reference radiative transfer tool; implementation of a graphical interface for the Monte-Carlo 

code; extension of the capability of the Monte-Carlo code with a feature to compute the incident solar flux for a generically 

oriented flat panel on the Mars surface. 

Deliverables: 

Technical note (incl. the illumination spectrum in four particular conditions); validation report; updated Monte-Carlo Mars Sun 

Radiation environment tool, incl. Source Files / User's Manual / test files. 

Current TRL: 

Target TRL: Operational Application Need/Date: 

N/A 

tool / 

SW operational by 2008 

method 

Application/Mission: Aurora, Exomars, HMM Contract Duration: 2 months 





Title: 

Mars climate database and physical models 

Update the European resources for Mars mission development related to environmental and dust characterisation. Reduce 

the uncertainties in the parameterization of physical processes. 

In order to prepare the future of Mars Exploration in Europe, and in particular improve our knowledge of the Martian 

environment at a level suitable for the Aurora program, the unique European Martian Circulation Model and Climate Database 

(developed by ESA with later support from CNES) must be improved by: 

- Inclusion of data from Mars Global Surveyor, Mars Express, and Mars Odyssey 

in the European Mars Climate Database (EMCD) 

- Dedicated study of the Mars atmosphere dust storms 

- High latitude processes on Mars (CO2 and H2O ice microphysics) 

- Inclusion of heating rate by phototelectrons in simulation of the 

thermosphere (120 - 300 km) 

- High resolution simulations of the lower atmosphere 

- Upgrades of the EMCD access software. 

Deliverables: 

Improved general circulation model of the Martian atmosphere, allowing mesoscale simulations; Assessment of Martian 

environment during dust storms; Improved Martian climate database based on assimilated data of current Mars missions. 

Current TRL: 


N/A 

tool / 


method 

Application/Mission: Aurora, Exomars, HMM Contract Duration: 24 months 




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12/Feb/09 


Title: 

Martian radiation environment models 

The aim of this activity is to produce dynamic models of the radiation environment on and around Mars. 

Due to the rarity of its atmosphere, the surface of Mars is exposed to large fraction of the incoming cosmic ray heavy ions, 

solar X-rays and ultraviolet radiation and, during solar active periods, to large fluxes of energetic solar charged particles. 

Adding to these, there is a contribution from secondary particles generated by nuclear reactions either in the atmosphere or 

on the Martian surface, neutrons being of particular concern. 

The following features will be addressed: 

- In-orbit radiation environment around Mars; 

- Atmospheric attenuation of incoming radiation 

(utilising the existing dynamic models of the Martian atmosphere); 

- Surface contours and altitude variations; 

- Effects of dust storms to radiation propagation; 

- Particle absorption and backscattering from the surface, taking into account the 

latest results on the water content and the elemental composition of the local soil; 

- Local pockets of magnetic fields in the southern hemisphere of the planet, 

and their potential radiation shielding effect. 

The study shall utilize the new data from Rosetta SREM instrument. The models shall enable input of galactic cosmic ray and 

solar event particle spectra as chosen by the user. The particle transport software shall utilise the open-source Geant4 toolkit 

and be implemented in an easy-to-use WWW-based engineering environment. Interface to the existing Mars environment 

data base 

(http://www-mars.lmd.jussieu.fr/mars/live_access.html) 

could be considered. 

Deliverables: 

New WWW-based, easy-to-use engineering models and software for Martian radiation environment prediction. 

Current TRL: 

Target TRL: 

Application Need/Date: SW operational (updated 

TRL1 

TRL3 

model) >2007 

Application/Mission: Aurora missions phase B from 2007. Contract Duration: 18 months 




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12/Feb/09 


Title: 

Cleaning / sterilisation technologies 

Future Mars exploration missions will call for the implementation of planetary protection policy and regulations. The ExoMars 

of the Aurora programme will seek evidence of life through in situ investigations on the surface of Mars. A mission designed to 

return the first Martian samples is also being studied. 

One of the great challenges is to develop or find the adequate technologies that will make compliance with planetary 

protection policy routine and affordable. Planetary protection is directed to: 

- the control of microbial contamination associated with robotic space vehicles intended to land; 

- the control of contamination of the Earth by extraterrestrial solar system material collected and returned by such missions. 

A state-of-the-art survey will be first performed so as take stock of past relevant Russian and European experience gained in 

the Mars 96 mission and Beagle 2 project regarding the compliance with planetary protection requirements. The aim of the 

study is then to focus on technologies / techniques requiring additional development effort for possible implementation into the 

future Mars exploration missions of Aurora programme. Special attention will be more particularly paid to cleaning / cleaning 

validation of surfaces of S/C-payload elements to be sent to Mars or to be used in laboratories for specific testing. 

The goal is to remove all types of contaminants like microorganisms, cells, and organic molecules to levels beyond the 

sensitivity of the scientific instrument used for the detection of traces of life. 

The activity will address cleaning procedures, equipment necessary to achieve the required cleanliness, instrumentation to 

verify the cleanliness level achieved and handling and packaging procedures to maintain the required cleanliness level. 

The purity of the surfaces may be achieved by using flashes of UV light at 7eV, ozone, detergent followed by a second 

cleaning and inspection. The hardware should be designed to allow cleaning of all critical items to be in contact with soil and 

detection tools and allow integration of this material in a protective envelope before flight. Sterilization techniques will also be 

investigated for suits, laboratory cabinets, tools and containers. 

Deliverables: 

Preocess assessment note (cleaning procedures, necessary equipment necessary, verification instrumentation, 

handling/packaging procedures to maintain the required cleanliness level). 






TRP Reference: 04/T45 

Title: 

Passive variable thermal conductance device for Mars rover applications 

The primary task of the Thermal Control Subsystem is to guarantee that all satellite components can operate in a benign 

thermal environment. In general, in order to maintain the units within allowable temperature limits regardless of varying 

external conditions and unit operating mode, the radiator is sized for hot case operation and sufficient heater power has to be 

allocated in the other cases. However, power is a limited resource for a spacecraft and needs to be properly allocated among 

the subsystems. In the USA R&D in the field of thermal control has focused on developing novel techniques to effectively keep 

the temperature of electronics within the required limits while reducing spacecraft power requirements. A paraffin-actuated 

heat switch as part of the thermal-control system for the battery on board a Mars rover has been developed and qualified. A 

heat switch is a variable thermal conductance device, which is mounted between a dissipating component and a cold sink. 

The temperature of electronics is passively controlled by the variation in conductance of the switch: the higher the power 

dissipation, the higher the thermal conductance. This allows the removal of excess heat from dissipating units when 

necessary, while the reduction in conductance prevents the electronics to get too cold. 

The goal of this activity is to develop a lightweight heat switch device for passively controlling the temperature of dissipating 

units. 

Deliverables: 

High performance thermal switch at breadboard level (design, manufacturing and testing). 


Application/Mission: Exomars rover Contract Duration: 18 months 




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12/Feb/09 


Title: 

T213-01SC 

Water sensor for Mars Exploration 

This study is intended to develop a method, which can easily analyse water films on grains. Such a technique must be 

incorporated into an instrument requiring low resources (mass, power, volume) and placed on the surface of Mars. Since 

many sites on the Martian surface need to be visited, the instrument must be incorporated into a mobile surface rover having a 

soil penetration capability. A possible technique, which may satisfy the requirements, is infrared spectroscopy in combination 

with attenuated total reflection (ATR). In combination with a spectrometer the ATR method delivers an absorption spectrum of 

the substance close to the boundary between the grain and the thin film. In the case of water films on Martian soil grains a 

Fourier infrared spectrometer would appear appropriate. It would be sensitive not only to the water film but also detect other 

adsorbates on the grains surface. There are other techniques and physical principles which could serve to reach the scientific 

goals. Eventually the ideal technique or combination of techniques has to be identified. Measurement principles and 

instrument design issues of ATR-IR spectroscopy are addressed under a current ESA contract.Resources are crucial for this 

instrument and must be minimised and in particular the weight and corresponding small outer dimensions are the key drivers 

for the assessment of an advanced design of an ATR. Initially the instrument must be able to be incorporated into a transport 

vehicle. The baseline is the ESA Nanokhod rover having a sub-surface penetration capability, i.e. a drill with a sample return 

to the surface for ATR analysis from the Rover payload cab. In a second scenario the sensor should also be integrated into a 

surface penetrating device (the ESA mole now under development). The design should serve a wide range of exploration 

strategies for the Martian surface. 

Deliverables: 

Breadboard model. 


Application/Mission: ExoMars Contract Duration: 18 months 





Title: 

Sampling drill tools for rocky and granular soils 

This activity will develop and demonstrate three alternative tool designs (ca. 20 mm in diameter) to be mounted on a drill, to 

collect soil samples (sand or rock) at a desired drilling depth, the Mars surface being considered as reference. Operation of 

the soil sampling tools is based on opening and closing the sample chamber in the tool at the desired depth. Operation of a 

rock sampling tool is based on a wedge-type core cutter ring or a conical core catcher. A combined rock and granular soil 

sampling tool will be able to sample both sandy and rocky soil with negligible losses. Tool actuation force will be traded-off: it 

may be generated either by electric actuators (motor, solenoid, shape memory alloy), or it may passively take advantage of 

drill rotation or reversal of the drill rotation. 

Deliverables: 

Drill Tool 






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12/Feb/09 


Title: 

T213-04MM 

Ultrasonic Tools for Planetary Surface Exploration 

The suitability of ultrasonic tools, e.g. for coring and drilling to limited depth (or generally sample acquisition and 

transportation) shall be studied and demonstrated with adequate hardware. A small initial feasibility study has been carried out 

by Leicester University in the frame of the AURORA programme, and has encouraged the use of ultrasonic tools for miniature 

sampling devices. Compared with classical mechanical corers and drills, ultrasonic equipment is very robust and simple as it 

does not require a high number of moving parts or a sophisticated drive mechanism. Several actuator types and mechanical 

amplifiers shall be studied. A major constraint is expected with the typical electric power limitations of planetary landing 

missions. Furthermore, the interaction of ultrasound with rock and softer materials is largely unknown. 

Deliverables: 

Demonstrator Model(s), including the ultrasonic transducer and drive electronics. 

Current TRL: TRL2 Target TRL: TRL3/4 Application Need/Date: TRL5 in 2008 






Title: 

Imaging Lidar technology 

Nowadays Imaging Lidars can perform measurements up to few kilometres at typical distance resolutions of a few centimetres 

at a rate of a few kHz. Imaging Lidars can support a number of space applications on orbiter modules, landers and planetary 

rovers like surface mapping, hazard avoidance and safe landing, navigation, multiple spacecraft operations (rendez-vous and 

docking), target properties recognition. However, since most of these systems rely on complex scanning mechanisms, they 

are bulky and often too heavy for future solar system exploration missions. The recent emergence of novel and advanced 

technologies like new 2-dimensional detector arrays (APD or CMOS arrays) and optical micro components (like MEMS and 

MOEMS) will bring a new trend in the development of compact, high resolution and multi-task sensor Imaging Lidars. This 

activity shall study the use of these novel technologies, assess the impact on the Lidar performances and develop an Imaging 

Lidar proof-of-concept breadboard that validates these technologies, making the Imaging Lidar a feasible instrument for space 

applications in the frame of AURORA. 

Deliverables: 

Imaging Lidar breadboard. 


Application/Mission: Aurora (ExoMars) Contract Duration: 24 months 





Title: 

Down hole hammering Mechanism 

The objective is to develop a high-energy (0.5-2 J/impact) hammering system, that can be placed inside the drill string (20-40 

mm in diameter). Power generation can utilize an electric motor, but shape memory alloys and piezo-elements (operating in 

an inch-worm manner) can be considered as an option. An optional passive mechanism to take impact power directly from the 

drill rotation (without any additional power sources and power feed-through) can also be considered. Impact frequency will be 

limited by the power of the actuator; however, impact energy must be kept at a level high enough to provide the desired effect. 

Deliverables: 

Breadboard of a drill- hammering device. 

Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 in 2008 





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12/Feb/09 


Title: 

T213-08MM 

Biochemical analyser 

Bio-chemical analysis is taking an increasing importance not only for the Space Station but also for interplanetary missions, 

first for search for life and later for supporting manned missions. If a system can be made available for the ISS in a relatively 

short term, it will use commercial, wet reagents with stability span of a couple years maximum, hence not compatible with 

long-duration interplanetary missions without re-supply capabilities. To be interplanetary-mission compatible, both technology 

and consumables (i.e. the reagents) must be adapted to reduced volumes and be compatible with preservation constraints 

and reduced operational capabilities (the first systems will be fully automated). No system is known that may be compatible 

with interplanetary mission requirements. 

Deliverables: 

Feasibility assessment. 

Current TRL: - Target TRL: TRL2 Application Need/Date: TRL5 > 2012 

Application/Mission: MSR Contract Duration: 18 months 




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12/Feb/09 


4.1 - Materials and Structures / Advanced Hot Structures and Thermal Protection Sy 


Title: 

T401-02MC 

Damage Tolerance of Cryogenic Pressure Vessels 

Cryogenic pressure vessels are one of the key applications for reusable space launcher design. The use of friction stir welded 

aluminium lithium for such structures is expected to improve their efficiency in terms of saved mass and design solutions. The 

objective of the proposed activity is to study and characterise the friction stir welded Aluminium Lithium from damage 

tolerance point of view in cryogenic pressure vessel applications. 

Deliverables: 

Al-Li friction stir welding characterisation report; Al-Li friction stir welding defects NDI detection method report; Al-Li friction stir 

welding damage tolerance assessment. Test specimens. 

Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 >2008-2010 

Application/Mission: launchers Contract Duration: 18 months 




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12/Feb/09 

4.1.1 - Structures & Thermal Protection (Source: TRP 2000-2003) 


Title: 

03/MCS-001 

Full Scale structure Qualification Methodologies 

The proposed activity focuses on the development of qualification techniques for hot structures and thermal protection 

systems by use of plasma facilities. 

The project aims at advancing the European Technology readiness level in such critical hot structural components, maturing 

the European know-how in aerodynamic control surfaces design, manufacturing and testing methodologies, for any future 

space transportation system application. This will be achieved by performing the design, development, manufacturing and 

qualification in the Scirocco facility of metallic and CMC (Ceramic Matrix Composite) components. 

Two significant test cases have been identified in order to provide actual results: 

• aerodynamic control surfaces, to test simple CMC structures 

• a hybrid structure winglet, to test the ceramic/metallic coupling. 

More in detail, the following main tasks will be carried out: 

1. Design manufacturing and testing of aerodynamic control surfaces of re-entry vehicles, consisting of design, fabrication and 

testing within Scirocco of ceramic flaps. For practical reasons an existing flight component has been selected as reference 

design for the flaps, the EXPERT flight test bed flaps. Indeed, the proposed activity would benefit of such an exceptional near 

term opportunity to validate the entire design-to-fly methodologies, and to perform a full verification loop with in-flight 

qualification. 

2. Demonstration of a ceramic/metallic hybrid structure, consisting of fabrication and testing of a winglet as suitable for a lifting 

re-entry demonstrator. 

The main technological issues will be relevant to the coupling of different hot structural materials and components, with 

different thermo-mechanical properties, subject to severe thermo-mechanical environments, such as those for winglets of 

reusable space transportation concepts. 

As reference component the scaled X-38 winglet upper fin has been selected, to mature the technology for any future lifting 

re-entry demonstrator development. 

Deliverables: 

Qualification breadboard of aerodynamic control surfaces of re-entry vehicles, i.e. ceramic flaps (design, manufacturing and 

testing within Scirocco). Breadboard of a winglet as suitable for a lifting re-entry demonstrator. 

Current TRL: 

TRL1-2 Target TRL: Application Need/Date: TRL8 (in-flight demo on 

TRL3-4 

EXPERT) by 2007 

Application/Mission: EXPERT, future re-entry vehicles Contract Duration: 18 months 





Title: 

MCT-998 

Smart Thermal Protection System 

Deliverables: 







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12/Feb/09 

4.2 - Materials and Structures / Advanced Materials 


Title: 

T403-02QM 

High temperature complex parts based on intermetallic components 

The proposal intends to develop injection of parts made of gamma TiAl for propulsion thrusters parts with complex geometry. 

It comprises the following:- Critical review of requirements for propulsion parts suitable for TiAl materials will be performed.- 

Design of an of elegant breadboard (EBB).- Improvement of manufacturing process of intermetallic powder by a 

Self-propagating High-temperature Synthesis (SHS). 

Deliverables: 

Technical notes. Design of breadboard-Test samples and reports-Breadboard. 

Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5 by 2010-2012 

highly loaded, high temperature parts in 

Application/Mission: propulsion systems. ESA next generation Contract Duration: 18 months 

concepts. 





Title: 

Multiphysic Modeling of Near-surface Phenomena 

In the last decade many advancements have been achieved in the theoretical modeling of hypersonic flows, but still 

phenomena exist that need to have deeper understanding for the improvement of TPS design with reduced safety margins. In 

the design of Thermal Protection Systems (TPS) a crucial issue is the correct evaluation of the heat fluxes. To this end, it is 

proposed to describe by accurate modeling the complex flow/structure interactions, and namely phenomena of catalysis, 

oxidation and ablation. In particular: near surface phenomena will be identified and modelled, including fluid/structure 

interactions (catalysis, oxidation, ablation); a test case will be selected and simulated and a recommendation will be 

formulated on the basis of the results analysis. 

Deliverables: 

Technical note (+ near surface phenomena identification/model description). Model (fluid/structure interactions: catalysis, 

oxidation, ablation). Test case selection/simulation. Results analysis + conclusion/recommendation. 

Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: TRL5 >2010 

Exploration missions, FLPP, Planetary 


entry missions 




Page 85 of 227




12/Feb/09 


Title: 

T403-03MC.B 

Multidisciplinary Modeling of Fluid Structure Interaction 

In the last decade Europe has invested significant effort in the development and qualification of various hot structures and 

thermal protection systems (TPS) as well as on the theoretical modeling of hypersonic flows; although major critical issues 

have been addressed and several investigations have been successfully carried out, further attention is required to improve 

the understanding of the physical phenomena occurring at the interfaces between the aerodynamic flow field and the TPS 

outer surface, to enhance the prediction of the thermo-mechanical environment, and, thereafter, to reduce the design margins. 

To this end it is proposed to characterize the thermo-chemical fluid-surface interactions occurring in the proximity of the outer 

surface (and on the surface itself) by physical and numerical modeling and to study and apply a suitable fluid/structure 

coupled approach, so that the analysis capability of the flight thermo-mechanical environment is enhanced. 

A set of test cases will be selected and simulated and a recommendation will be formulated on the basis of the results 

analysis. 

Deliverables: 

Technical note (+ survey on critical fluid-surface interaction phenomena and fluid-Structure thermal coupling, Modeling report). 

Models. Computational modules. Test cases selection/simulation. Results analysis + conclusion/recommendation. 

Current TRL: TRL1-2 Target TRL: TRL3 Application Need/Date: SW operational >2010 

Design SW for TPS for Space 

Application/Mission: Transportation applications, entry Contract Duration: 18 months 

missions 





Title: 

Increase of Bolted Joint performance for CFRP 

Joining of structural CFRP-parts with bolts and rivets is a common approach for manufacturing and repairing in the space and 

aeronautical industry. However this joining method does not reflect an appropriate joining technology in terms of fiber 

reinforced plastics (FRP). The main principle in joining with bolts and rivets is the fact that forces are transferred not by 

tension and pressure force but by shear and bearing stress. Fiber reinforced plastics with common matrix systems usually 

reach good values for tension and pressure but not for bearing stresses and are therefore not suitable for a bolted joining. 

Current studies on metal-composite laminates for aircraft composite joints show that these offer better mechanical and fatigue 

performance over conventional composite bolted joints. An alternative way to increase the bearing stress would be by 

introducing local softened carbon fiber laminates. Therefore the development and evaluation of composite laminate bolted 

joint concepts for highly loaded launcher and RLV space applications is urgently needed. The proposed activity aims at 

studying and evaluating possible concepts of composite laminate bolted joint, for highly loaded space applications, including 

removable and replaceable joints. 

Deliverables: 

Design and verification guidelines for highly loaded composite structural joints. Reference design catalogue. Reference tests 

data collection. Test specimens. 

Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: TRL5 > 2008 

Application/Mission: spacecraft and launcher structures Contract Duration: 18 months 




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12/Feb/09 


Title: 

T403-14MC 

Cryogenic Composite Tanks and Lines 

During FESTIP 1 and 2, a feasibility study was carried out to assess the possibility of replacing all-metal cryogenic fluid 

transfer lines for launchers, with composite lines with low mass and good thermal insulation properties. This feasibility study 

took as reference the Ariane 5 feed line dimension: inside diameter of 185mm, with the length limited to 1m. Different 

techniques to design and manufacture such items using composite materials concluded that there are two different ways, both 

using filament winding technique for composite components: Single wall piping -composite piping with a metallic barrier/liner to 

reduce the gas diffusion at cryogenic temperature; Double walled, vacuum insulated cryogenic composite line, which further 

reduces the heat leaks through the system. The goal of this activity is to further develop the technology for designing and 

manufacturing light-weight cryogenic tanks and lines based on composite technology. Substantial mass reduction for 

cryo-tanks and lines is expected while at the same time the parasitic heat leaks will be reduced thereby increasing the lifetime 

of cryogenic storage (stand-time).The following tasks are envisaged:- adapt/develop processes, procedures (e.g. machining 

steps, welding) to produce small diameter lines including fittings and connections as well as cryo-tanks- design and 

manufacture a cryo-tank with some appropriate cryo-lines- perform a complete thermal and mechanical test programme with 

the built H/W to derive e.g. stand-time, parasitic heat leak, leakage. 

Deliverables: 

Processes and procedures to produce light-weight cryo-tanks, lines and systems based on composite technology. H/W: fully 

tested (thermal and mechanical) cryo-tank and lines. 


Space Missions (Science, Aurora, etc.) 

requiring cryogenic liquid storage 

(>=2009); Launcher, for launcher mass 


reduction by reducing the mass of the 


propellant tank and of the fluid feed lines 

(>=2010) 

SW Clause : - Dossier0 Ref.: T-8138, T-605, T-703 



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12/Feb/09 

4.3 - Materials and Structures / Advanced Structures 


Title: 

T405-01MC 

Non-destructive inspection methods for re-usable CFRP structures 

Secure NDI methods for CFRP structures are mandatory to guarantee re-use of reusable launcher structures like CFRP 

LH2-tanks or to identify maintenance or repair needs. Baseline technology and widely used is ultrasonic inspection (US), but it 

has some limitations (exact damage detection and location, damage detection in complex and large structures, mobility of 

inspection system, accuracy of information). Other inspection technologies meanwhile reached respective maturity and are 

interesting alternatives. It is proposed to perfom non-destructive inspection of structures for RLV, in particular: identification 

typical re-usable launcher structures for inspection, Technology Review of Existing Methods, NDI Methods Evaluation 

Program (Damage Sample Test Program), Damage Classification for Re-Usable CFRP Structures, CFRP structure test 

program (e.g. tank structure), Recommendations and Synthesis. 

Deliverables: 

Technical notes: survey of typical re-usable launcher structures for inspection and existing methods, NDI Methods Evaluation 

Program, Re-Usable CFRP structures damages classification and test program, test specimens. 


RLV and ELV structures, composite 

Application/Mission: tanks / spacecraft tanks; FLPP Contract Duration: 18 months 

demonstration vehicle 




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12/Feb/09 

4.4 - Propulsion / Advanced Liquid Propulsion 


Title: 

MPC-846 

Acquisition and Evaluation of Cryo-Solid Propulsion: Additional Testing 

Conventional solid rocket propellants have specific impulses that are low compared to cryogenic liquids. Cryogenic Solid 

Propellants (CSP), defined as frozen propellants that normally are liquids or gases, compare very favourably with conventional 

ones. The objective of this activity is to establish a firm evaluation of CSP in terms of applicability, performance, operability 

and cost. It is also necessary to establish the theoretical and experimental foundations of CSP-grain design, production, 

integration, handling, ignition, combustion etc and rapidly provide the knowledge base of a prototype demonstrator version of 

a CSP-motor. Experimental work carried out as part of this activity shall include investigations of strand burner and tests with 

sub-scale motors. This CCN will continue the experimental work. 

Deliverables: 

Test data 


Application/Mission: Future launchers Contract Duration: 18 months 





Title: 

T402-05MP 

Scaling of Thermal Cavitation Effects on Cavitation-Induced Instabilities 

Thermal cavitation effects, due to evaporation or condensation phenomena at the cavity interface, have long been known to 

deeply affect the steady performance of cavitating turbopumps. The main objective of the activity consists in investigating 

whether and to what extent established scaling laws developed for steady thermal cavitation effects are also applicable for 

correlating dynamic cavitation phenomena, cavitation-induced instabilities, unsteady fluid forces and moments acting on 

turbopump inducers. Thermal cavitation effects must be investigated by adjusting the liquid temperature as necessary for 

adequately scaling the pump prototype operating at design conditions (flow coefficient and cavitation number) with the given 

propellant. Instabilities must be characterized by both high-speed video movies and flow instrumentation (pressure and flow 

transducers), so to measure the instantaneous unsteady fluid forces acting on the rotors. Finally, some of the unsteady 

cavitation phenomena observed during the test campaign should be simulated and analysed with a 3D unsteady cavitation 

code, taking into account the thermal effects. 

Deliverables: 

Database and test data for validation of SW tools. 

Current TRL: N/A Target TRL: N/A Application Need/Date: TRL5 by 2007 

Application/Mission: ArianeV and evolutions. Contract Duration: 18 months 




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12/Feb/09 


T402-10MP 

Unsteady subscale force measurements within a launch vehicle base buffeting 

Title: 

environment 

Prediction of the unsteady forces on a full-scale, main stage, nozzle is normally obtained via wind tunnel testing. In such wind 

tunnel testing however, problems arise when the forces on the nozzle need to be evaluated. In the past this has been 

achieved using heavy instrumentation of the nozzle, to allow integration of unsteady pressure measurements and, thus, the 

derivation of the forces. This technique has, to date, been proven to be unreliable and the results are sometimes questionable, 

due to the drastic modification of the model of the nozzle required to accommodate the instrumentation. Based of the above, 

the proposed TRP activity is defined as follows: 1. In a first step, available literature should be examined and an evaluation of 

the potential for the separate techniques should be given.2. Secondly, a technical specification for a system, allowing the 

direct measurement of the unsteady forces on a scale nozzle in a representative environment, should be defined. 3. Finally, 

the performance of the new system should be: evaluated in testing; compared against the pressure integration techniques 

already developed; scaled for comparison against available flight data. 

Deliverables: 

Tech. Spec of Measurement methodology of unsteady forces on subsc. nozzle (representative of launch vehicle base flow 

environment). Final report (subsc. test results, comparison with avail. flight data, applicat. w.r.t. assoc. flow structure 

interations). 


Application/Mission: all launchers, future launchers Contract Duration: 24 months 




Page 90 of 227




12/Feb/09 

4.5 - Propulsion / Advanced Propulsion Concepts for In-Space Operations 


Title: 

T404-02MP 

Technical Assessment for High Power Magneto Plasma Dynamics (MPD) Systems 

The proposed activity has the following main objectives: 1. Mission analysis, to investigate MPD mission possibilities and 

subsequent MPD system requirements. 2. Preliminary consideration of a MPD in the 110-300kW range, and critical areas 

identification (self applied and externally applied magnetic field solutions shall be studied and a trade-off shall be performed); 

lifetime issues and possible improvement/solution shall be considered. The physical phenomena shall be analysed and 

possible design analytical and mathematical models shall be used to evaluate impacts on the MPD system. A comparison 

between self applied and applied magnetic field should be done.3. MPD roadmap: research and development activities plan to 

achieve the maturity of the technology shall be done, together with the required time schedule evaluation. The Aurora 

programme shall be taken into consideration as main driver. 

Deliverables: 

1. Mission analysis report. 2. 110-300kW MPD preliminary design report.3. MPD roadmap report.4. Final report 

Current TRL: TRL2 Target TRL: TRL2-3 Application Need/Date: TRL5 >2015 

Future high power platforms (exploration, 


etc.) 



Electric Propulsion 


18 months 

TRP Reference: T404-03MP 

Title: 

Advanced Electric Propulsion for a Service Module for VEGA 

This activity includes the detailed assessment and preliminary design of a service module using electric propulsion (EP) to be 

applied for LEO-MEO/LEO-GEO transfer orbits in order to increase payload capability of the Vega launcher. The service 

module shall be equipped with independent AOCS, telecommunications system, autonomous navigation system (to reduce 

cost of the ground segment). A set of orbital maneuvers (station keeping, GEO transfers and corrections on LEO) shall be 

guaranteed. EP technologies to be assessed for the module are related to both classical EP (i.e. gridded ion engines, 

Hall-effect thrusters and other types of EP. After a trade-off on performance, configuration and mission capability, the module 

shall be designed and a development plan shall be prepared. The detailed activities include: feasibility study of EP (applied to 

Vega), I/F’s requirements w.r.t the launcher, module configuration study, key technologies evaluation, mission analysis, 

development & cost plans for B, C, D phases. 

Deliverables: 

Technical reports. Design file. 


Application/Mission: Vega evolution. Contract Duration: 14 months 




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12/Feb/09 

4.6 - Propulsion / Air-breathing Propulsion 


Title: 

T407-01MP 

Design of Flight Test Configuration for High-speed Airbreathing Propulsion 

Deliverables: 







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12/Feb/09 

4.7 - Propulsion / Solid Propulsion 


Title: 

T411-01MP 

Hybrid propulsion evaluation for liquid booster application 

Whilst Hybrid Engine Technology has been around for many years, it has made significant improvements in recent years and 

now is a realistic option for low cost Expendable Launch Vehicle (ELV) boosters. The main objectives of this study are: - to 

perform a survey of the state-of-the-art to identify possible propellant combinations, their applications for a ELV booster 

application and a system trade-off; - to compare hybrid propulsion with current baseline solid boosters and to identify future 

technological investigation/research programmes; - a detailed review of Hybrid Rocket Engines should be performed to 

evaluate the state-of-the-art and potential applications. This would include a literature and market survey, and system trade-off 

studies toassess the potential advantages of using Hybrid Rocket Engines. The work should include the following: - Hybrid 

propulsion literature review of state-of-the-art (+ identification of possible propellants combinations, particularly to non-toxic 

combinations), assesment of potential applications, for future space / launcher, and def. of requirements related to the 

proposed booster; - mathematical models for the design and sizing of Hybrid Rocket Engines and a preliminary design of an 

Hybrid Rocket Engine system for each application based on two different technology level options (med/advanced propulsion 

assumptions); - analysis of a vehicle mission and and performance for the above two options and comparison to baseline 

data; - summary of the performance budget and identification of any technological critical item. 

Deliverables: 

Technical datapackage + matematical models. 


Application/Mission: future launchers Contract Duration: 12 months 





Title: 

T413-01MP 

Experimental demonstration of opto-pyro systems for launcher applications 

Opto-pyro designates a technique whereby laser pulses distributed via optical fibres are used for initiation of explosives. This 

technique offers several advantages compared to the classical pyro system, which is based on electrical initiators and 

explosive cords. Previous preliminary studies of the introduction of this technology for the separation systems of Ariane 5 

have been carried out. In the present activity, the definition and investigation of other possible applications of the opto-pyro 

technology will be performed. In particular, such applications as stage separation for Ariane 5 and future RLVs, SRM ignition, 

ignition of RCS in RLVs, as well as possible use in satellite platforms, will be considered. In addition, investigations of an 

opto-pyrotechnic chain addressing key technologies and issues (optical source and fibres, signal distribution, sequencing and 

delays...) will be conducted. An optimisation of the optical architecture will be performed. An experimental demonstration of 

the concept will be carried out through the testing of an opto-pyro platform, to verify the general design concept of the 

opto-pyrotechnic sub-system. 

Deliverables: 

Technical note. Experimental demonstration. 


Application/Mission: future launchers Contract Duration: 18 months 




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12/Feb/09 

4.7.1 - Propulsion Technologies (Source: TRP 2000-2003) 


Title: 

MMM-956 

Journal bearings for turbopumps 

Deliverables: 







Page 94 of 227




12/Feb/09 

4.8 - Aerothermodynamics (ATD) 


Title: 

T406-04MP 

CFD validation in CO2 environment 

The proposed study is related to the ground-to-flight methodology for planetary entry missions in atmosphere mainly 

composed of carbon dioxide and some other minor components. In frame of the CNES PREMIER program, related to Mars 

exploration facilities have been used to generate cold and hot CO2 flows. The Long shot facility (at VKI) features cold CO2 

and rather high Reynolds flows while the F4 facility (at ONERA) features high enthalpy and moderate Reynolds flows. Both 

facilities should be more carefully characterised in terms of actual flow conditions ahead of the models (as required when 

using advanced measurement techniques). This characterisation should be made in a close loop manner with numerical 

simulation of nozzle flow and the thermo-chemical models should rely on validation carried within other TRP work on "high 

speed kinetics". The extrapolation methodology will be first based on simplified approaches to compare the ground 

condition(s) to the real flight conditions. Codes based on computing the flow on the stagnation line will be used to investigate 

the main non-dimensional relevant parameters. Then the extrapolation methodology will rely on the 3D solvers using the same 

models. 

Deliverables: 

Experimental campaign reports. Mid-term report. Final report proposing the ground-to-flight proposed methodology. 

Current TRL: 

Target TRL: 

Application Need/Date: TRL5-6 (facility validated) by 

TRL1 

TRL2-3 

2007-2008 





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Title: 

Electron Beam Fluorescence fo Aerothermodynamic Applications 

Development and improvement of techniques for in-flight measurement of critical aerothermal properties and specific flow 

variables, both on-board and off-board hypersonic vehicles are key elements required for the future demonstrator vehicles. 

Smaller and more accurate sensors, as well as advanced non intrusive measurement techniques are to be developed. The 

development concerns detailed numerical sensitivity analysis as well as demonstration models assembly activities leading to 

integrated subsystem testing in relevant plasma facilities. The objective of this activity is to improve intrusive and develop the 

concept non intrusive diagnostic techniques for in flight ATD research. New developments promise an extension of these 

techniques to higher densities, better spectral resolution and higher sampling rates (to be, in the future, qualified in 

combination with well established temperature and pressure measurements techniques). The activity includes: 1. Emission 

spectroscopic improvements for ground based facility and flight testing - Emission spectroscopic data for CFD verification. 2. 

Improvements of pyrometry and infrared thermography methods for ground based facility and flight testing. 3. Improved and 

extending pressure range for EBF (Electron Beam Fluorescence). 4. Flow visualisation on N2 and/or NO(gamma) (CCD 

Camera) using EBF. 5. N2 density via visible light or X ray (photomultiplier /Xray scintillator). 6. N2 vibrational and rotational 

temperatures using EBF (spectrometer). 7. EBF for NO density (spectrometer/photomultiplier). 8. Prospective IR integration 

experiments in plasma conditions. 9. Comparison of the measured data with CFD calculation of the flow field. 

Deliverables: 

Technical note (incl. Test/Measurements results). Breadboarding. 

Current TRL: 

Target TRL: 

Application Need/Date: TRL8 (in-flight 

TRL2 

TRL4-5 

demonstration) by 2008 

EXPERT (2008), Exploration, Future 


Launchers 





Development and qualification of in Flight Test Measurement (FTM) techniques: Nose & 

Title: 

Payloads 

Development and improvement of techniques for in-flight measurement of critical aerothermal properties and specific flow 

variables, both on-board and off-board hypersonic vehicles are key elements required for the future demonstrator vehicles. 

Smaller and more accurate sensors, as well as advanced non intrusive measurement techniques are to be developed. The 

development concerns detailed numerical sensitivity analysis as well as demonstration models assembly activities leading to 

integrated subsystem testing in relevant plasma facilities. The objective of this activity is to improve intrusive and develop the 

concept non intrusive diagnostic techniques for in flight ATD research. New developments promise an extension of these 

techniques to higher densities, better spectral resolution and higher sampling rates (to be, in the future, qualified in 

combination with well established temperature and pressure measurements techniques). The activity includes: 1. Emission 

spectroscopic improvements for ground based facility and flight testing - Emission spectroscopic data for CFD verification. 2. 

Improvements of pyrometry and infrared thermography methods for ground based facility and flight testing. 3. Improved and 

extending pressure range for EBF (Electron Beam Fluorescence). 4. Flow visualisation on N2 and/or NO(gamma) (CCD 

Camera) using EBF. 5. N2 density via visible light or X ray (photomultiplier /Xray scintillator). 6. N2 vibrational and rotational 

temperatures using EBF (spectrometer). 7. EBF for NO density (spectrometer/photomultiplier). 8. Prospective IR integration 

experiments in plasma conditions. 9. Comparison of the measured data with CFD calculation of the flow field. 

Deliverables: 

Technical note (incl. Test/Measurements results). Breadboarding. 

Current TRL: 

Target TRL: 

Application Need/Date: TRL8 (in-flight 

TRL2 

TRL4-5 

demonstration) by 2008 

EXPERT (2008), Exploration, Future 


Launchers 




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12/Feb/09 


Title: 

T406-12MP 

Preparation of an electrodynamic-heatshield flight experiment 

It is the objective of the present work to prepare a flight demonstration experiment by looking into the available magnet 

technology with regard to technical performance and cost consideration and by performing preliminary on-ground tests. The 

boundary conditions imposed by a reentry capsule and its launch vehicle shall be taken into account. The focus of this work 

will deal with the coil section (nose of the capsule), which must contain the superconducting coil and its magnetic screen. 

Deliverables: 

Experimental demonstration/modeling. 


Application/Mission: re-entry vehicles Contract Duration: 18 months 





Title: 

Advanced Methods for Hypersonic plasma - flow control 

The objective of the present proposal is to advance new techniques to control the flow within the hypersonic shock layer of 

space transportation systems entering planets or re-entering earth at hypersonic speeds. A promising very innovative concept 

is the one of controlling the flow pattern through electro-magnetic forces acting on the ionized component of the flow impacting 

the vehicle. 

This electro – magnetic interaction of the flow could potentially: 

• Reduce locally the heat flux via shock standoff increase. 

• Increase wave drag thereby also reduce heat load due to reduction of ballistic coefficient. 

• Be used to control the flow for stability and trimming resulting in simplification or elimination of RCS. 

• Manipulate black out periods and therefore optimize communication links. 

The purpose is to build up further on recent advances made in the HEAT and L2K facilities and to take advantage of the 

ongoing associated activities within the CIRA CAST and DLR programmes. 

The following activities are proposed : 

• Small scale experiments in HEAT and L2K thereby augmenting their expertise in this field including numerical rebuilding. 

• Developments of associated intrusive and non intrusive diagnostic measurement for later use in SCIROCCO. 

• Preparatory activities for SCIROCCO testing compatible with CAST. 

• Study on potential system impact for possible future application and in flight demonstration. 

Deliverables: 

Technical note 


Exploration and Science Planetary Entry 


and Earth Reentry missions 



Roadmap: “Aerothermodynamics Tools”, 2007; Conclusions: 1st semester 2007 


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12/Feb/09 

4.8.1 - Aerothermodynamics (Source: TRP 2000-2003) 


Title: 

03/MPA-001 

In-Flight Aerothermodynamic Measurements 

Deliverables: 







TRP Reference: 94/8.2.1.4, 03/MPA-002 

Title: 

Plasma Radiation Database 

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 

and diatomic molecules, but should be extended to triatomic molecules such as CO2, major component of Mars atmosphere. 

PARADE new additions 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 triatomic molecular species. 

Deliverables: 

Database model / notes. 

Current TRL: Algorith Target TRL: 

m 

Prototype 

Application Need/Date: TRL5 by 2009-2010 

ExoMars, Mars Sample return, or for 

Application/Mission: missions to Venus (EVE), NEO missions Contract Duration: 12 months 

(Marco Polo) 




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12/Feb/09 

4.9 - Avionics and GNC 


T408-01MX 

Modern Guidance Schemes for the Terminal Area Energy Management (TAEM) Flight 

Title: 

Phase of Reusable Space Transportation Systems 

To develop and validate novel guidance approaches and algorithms for the TAEM flight regime, which is critical for the 

development of future European reusable space transportation systems, and which will be needed for preceding experimental 

vehicles. During the TAEM phase, the guidance system aligns the vehicle with the runway, while controlling altitude and 

velocity. The proposed activity shall improve the knowledge of the TAEM phase by analysing typical spacecraft configurations 

and requirements for this phase, shall research novel guidance approaches for TAEM, which would enhance the degree of 

autonomy and reusability, and which would reduce the operations costs, and shall include the testing and verification of 

algorithms on a validated software platform. 

Deliverables: 

GNC algorithms for the Terminal Area flight phase, verified on a validated software platform; Technical Report and Technical 

Notes, summarizing the analytical trades and documenting the key features and advantages of the selected guidance 

approach. 

Current TRL: 

Target TRL: Beta Application Need/Date: 

TRL1 

version 

FLPP demonstrators, Exploration 


missions 




TRP Reference: T408-06ES 

Title: 

Robust Multi-mission Navigator 

Hybridized navigation concept, using GPS-like signals to complement IMU information as well as air data sensor, laser 

altimeter/ranger and optical sensor data, is a promising solution for compensating drift errors and uncertainties of the 

gravitational field. A hybridized navigation solution is being studied in the frame of the on-going TRP study on "Aeroassist 

Technology for Planetary Exploration", nevertheless, some specific problems need to be investigated in details. In the light of 

the above considerations, the aim of the proposed activity is to develop a European multi-mission hybrid navigator breadboard 

that will be tailored for upcoming Earth entry vehicle demonstrator(s). The expected benefit is a highly integrated robust hybrid 

navigator breadboard with multi-mission capabilities ready for use in future space transportation and re-entry programmes. 

The hybrid navigator will exclusively be based on European technologies due to strict export control licenses on US 

components. The study shall include the functional performance evaluation of three cases: launcher, aeroentry/reusable 

space transportation, multi-mission hybrid navigator. 

Deliverables: 

Nav. Breadboard. Hybridised nav. flight SW demo. Data package / summary report / abstract, incl. nav. sensor spec, 

hybridised nav. sys. prel. design, functional perform. evaluation (mentioned 3 cases); spec/baseline architecture; design; test 

results. 


FLPP demonstrators, Launchers, 


Exploration missions 




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12/Feb/09 

4.10 - Health Management System (HMS) 


Title: 

T410-01MC 

Health Monitoring system for TPS and Hot Structures 

Monitoring and evaluation of structural performance will play a key role in reducing the overall operational cost associated with 

maintenance and refurbishment of reusable space transportation systems. Future launch vehicles will have to increase 

operational efficiency whilst maintaining or improving reliability. The objective of the proposed activity includes:- analyse and 

define system requirements in the TPS and Hot Structures Health Monitoring field (resulting in preliminary specifications of a 

Health Monitoring System suited to TPS and Hot Structures requirements).- Starting from the requirements on TPS and Hot 

Structures components a technological study on the HM techniques for both in-flight and on-ground inspection will be 

performed. Particularly the technology should include investigation of the loosening of joints connecting the panels with the 

structure and impact damages on the panels as well as temperature and strain monitoring and leak detection. 

Deliverables: 

System Requirements Document for TPS and Hot Structures Health Monitoring; Identification of associated system and 

components Specifications. Technology development plan. 

Current TRL: TRL0-1 Target TRL: TRL1 Application Need/Date: TRL5 by 2010-2012 

re-entry vehicle, RLV's, FLPP 


demonstrator 




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Title: 

MXO-001 

Health Management System for Re-usable Space Transportation 

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 

demonstrate processes for HMS design and optimisation, develop models and analysis means for a generic HMS 

architecture, demonstrate a HMS model against nominal and fault injection mission simulations. 

Deliverables: 

Notes. Models/analyses for a generic HMS architecture. HMS demonstration model. 

Current TRL: TRL1 Target TRL: Prototype Application Need/Date: 

Application/Mission: FLPP, Exploration missions Contract Duration: 24 months 




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12/Feb/09 


5.1 - Conventional Fixed Telecommunication Service 


ETM-101 

Surface Treatment and Coatings for the Reduction of Multipactor and Passive 

Title: 

Intermodulation Phase 2 

Objective of this activity is the evaluation of practical and stable coatings with extremely low secondary electron emission for 

reduction of multipactor effect in RF components in space. The concept is based on the secondary emission suppression of 

rough surfaces or special morphologies. Inert or noble metal porous coatings will be used to achieve: optimum values, control, 

reproducibility, homogeneity, and stability in air for the secondary emission and electrical conductivity. The activity will verify 

the good results achieved in the previous TRP activity on Surface Treatment and Coating for the Reduction Multipactor 

Degradation in RF components (Ref: ETM-101 in 2000-2003 Plan), which has yielded several patents and 9 publications. 

Deliverables: 

Test Report on 10 further samples 


Application/Mission: Telecom, Navigation Contract Duration: 12 months 





Title: 

RF breakdown in Multicarrier systems 

Multipactor is a RF breakdown phenomena occurring in space RF components. The consequences of this breakdown can be 

catastrophic for the mission of the satellite. In those payloads using multicarrier operation, the levels of risk of RF breakdown 

increases exponentially. The aim of this activity is to asses these rules and ensure that any theoretical analysis based on 

these rules can be considered valid, thus avoiding expensive test campaigns. A modular software tool compatible with existing 

electromagnetic softwrae shall be produced to evaluate and predict RF breakdown in multicarrier operation taking these 

theories into consideration. These two "rules" are described bellow: The "fringed effect" is related to the geometrical shape of 

the internal edges in the RF device. It is believed that this shape (sharp or smoothly curved) has a significant influence in the 

Multipactor behaviour of the component. However no investigations in this area have ever been completed. In multicarrier 

operation testing at such high levels is not always possible. Previous works indicated that, as long as the duration of the 

multicarrier peak and the mode order of the gap are such that no more than twenty gap-crossing can occur during the 

multicarrier peak, then multipactor-generated noise should remain well below thermal noise. This rule is know as the "Twenty 

Gap-Crossing" rule and its theoretical confirmation plus test verification would imply a significant step in the understanding 

and mitigation of this destructive phenomena. It would also reduce the amount of components needed for testing. 

Deliverables: 

Final report + detailed theoretical doc. Samples (possibly waveguide filters; design to reflect the theories investigated and 

tested). Test reports. Modular SW tool. 






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5.2 - Engineering and Verification Tools & Techniques 


Title: 

T506-01EE 

European Antenna Modelling Component Library - Telecommunications 

The library shall be based on existing tools, while being able to easily incorporate the implementation of any new algorithms 

developed to satisfy emerging antenna engineering needs. The present activity will focus on the development of components 

specific to Telecommunication missions. In particular it will be articulated in two components: a structural component to 

ensure the background activity to pursuit the common objective of bringing forward antenna modelling technology and tools 

and a thematic component, dedicated to specific needs.-The structural component will focus on: the Earth 

Observation-specific aspects,electromagnetic modelling data domain standardisation, geometrical CAD tuned to 

electromagnetic modelling needs for telecommunication specific antenna configurations.-The thematic components will focus 

on: refinement of reflector antenna analysis tools , multi-frequency multi-coverage synthesis, improvement of antenna 

interaction models.The present activity will be carried out as part of the global development of the "European Antenna 

Modelling Component Library" foreseen by the above Dossier. 

Deliverables: 

Software component library with relevant documentation. Validation hardware (satellite and antenna mock-ups) 








Title: 

Modelling of Porous Shells 

Porous materials, such as triaxial woven fabrics, are being employed in antenna technology due to the significant mass 

reduction and acoustic load relaxation. The drawback being the RF transparency, limiting the application of current ultralight 

technologies to the Ku frequency band. Therefore, a reduction of hole size is needed and consequently the acoustic load case 

comes back to the scene. The objectives of this activity are:1.Vibroacoustic modelling of porous materials and triaxial fabrics, 

comprising material characterisation and a procedure for implementation into Finite/Boundary-Element vibroacoustic 

simulation.2.Thermo-elastic modelling of porous/triaxial shell. Material characterisation and implementation into Finite Element 

simulation. 

Deliverables: 

Identification of relevant parameters (analysis + existing data). Thermo-elastic/acoustic/RF characterisation (coupons + 

samples). Finite Element and Boundary Element modelling procedure. Correlation with sample tests. 

Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5 >=2009-2010 

Application/Mission: all spacecraft with reflectors) Contract Duration: 18 months 




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Title: 

T501-02EE 

Active multi-beam antenna concept using advanced very high order multilayer BFN 

The objective of this activity is the design, manufacturing and test of critical components for a very high order Analog Beam 

Forming Network (BFN) for future Ka band broadband multimedia telecommunication missions. A promising approach may 

consist in implementing an active lens able to generate a very high number of adjacent beams (>50). This system includes a 

fine antenna pointing electronic correction for surface shape/deployment inaccuracy compensation. This innovative concept is 

foreseen to provide improvement toward in-orbit performance tuning, implementation feasibility, manufacturing accuracy 

relaxation, high reliability due to graceful degradation performance, low sensitivity to multipaction and PIM, and excellent 

power to beam flexibility. Such antenna architecture with high order BFNs represent a challenge and this activity will prove the 

capabilities of technology for their implementation. Advanced multilayer technologies and advanced design concepts and 

technologies are expected to be used leading to a compact and cost effective solution. 

Deliverables: 

Detailed design and critical breadboard. 


Application/Mission: Multibeam Telecom Contract Duration: 12 months 





Development of high order propagation models for multimedia Satellite Communication 

Title: 

Systems 

The proposed activity is aimed to the development of models of high order statistics of radiowave propagation parameters 

relevant for Satellite Communication Systems operating at frequencies from 20 to 50 GHz. Existing models are mainly 

focused on the description of first order statistics of propagation parameters (like the atmospheric attenuation cumulative 

distribution function), but, because the design of advanced SatCom systems relies on Propagation Impairment Mitigation 

Techniques (PIMT) and on its integration with network control, additional information on higher order or conditioned statistics 

(e.g. fade duration, fade slope, seasonal and diurnal effects, instantaneous and long-term frequency scaling, spectral 

propertied and spatial and time correlation, etc. ) are needed. As well issues related to exploitation of Ka Band for EO and 

Science missions data downlink require new models. 

This new activity shall start by a critical review of existing models based on current and expected system requirements (like 

the QoS - Quality of Service - issues or PIMT design) along with the existing dataset collected during propagation 

experiments. The main core of the activity shall be constituted by: 

• Collection of data from past propagation measurements. 

• A new experimental propagation campaign, based on existing satellite beacons. 

• A data analysis and model development activity. 

• A validation and testing activity for the assessment of the accuracy of new models. 

Deliverables: 

Propagation models / SW 


Application/Mission: Satellite Telecommunication systems Contract Duration: 24 months 





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Title: 

T501-06ET 

High Frequency SIGE MMICS for Converter 

The objective of the activity is the design, manufacturing and test of high frequency SiGe MMICs to be used in the next LO 

generation and up and downconverter units both for on board and user terminal applications. SiGe permits the implementation 

of very low cost mixed analogue/digital circuits that can significantly reduce manufacturing costs of LO generation modules, 

frequency synthesizers and up and downconverter units. Low phase noise is another characteristics of SiGe HBT technology. 

On the user terminal area, there is a strong push towards extremely low recurrent costs. Frequency synthesizer has been 

identified as one of the cost drivers and SiGe technology has potential for significant cost reduction 

Deliverables: 

High Frequency SiGe HBT MMICs to be used as building blocks on future LO generation and frequency converter units both 

for on board and user terminal applications. 


Application/Mission: Telecom Contract Duration: 22 months 





Title: 

High Reliability MEMS Redundancy Switch 

Micro Electro-Mechanical Systems (MEMS) technology has been quite successful in the demonstration of low loss, high 

frequency switches with the emphasis on a high number of ON/OFF cycles. However, very little is know about the reliability 

(failure and degradation mechanisms, ..) of such switches, specially when it comes to few cycles with may years between ON 

and OFF actuations, as for redundancy switches on board satellites. The aim of this activity is to design and realise a high 

frequency (up to a least Ka-band) low power redundancy switch, based on MEMS technology, with proven reliability i.e. 

including investigation and analysis of failure/degradation mechanisms. 

Deliverables: 

Demonstrator of MEMS redundancy switch. Identification and analysis of failure/degradation mechanisms. 


Application/Mission: Telecom, EO, Science, Navigation Contract Duration: 24 months 





Innovative architectures for reducing the number of controls of multiple beam 

Title: 

telecommunication antennas 

This study shall perform innovative design and radiation performances analysis (mainly Gain and maximum sidelobes/grating 

lobes levels) of different Array configurations including uniform and non-uniform elements spacing, overlapped subarrays and 

other techniques to identify achievable performances toward number of active controls. Based on these analyses, detailed 

design and definition shall be performed leading to BFN (Beam Forming 

Network) architecture, mass and technological constraints identification as well as performance achievable for the selected 

implementation.This study will cover all architectural trade-offs, the concept selection and a detailed design. Breadboarding 

activities will allow demonstrating the feasibility and performances of this innovative concept. 

Deliverables: 

Performances analysis of different arrays configurations. 






Array Antennas 

Page 105 of 227




12/Feb/09 


Title: 

T501-10ET 

High throughput highly re-configurable bent-pipe processor for access networks 

The proposed activity aims at the design, implementation and validation of the Proof of Concept (PoC) of a high throughput 

highly re-configurable and scalable digital processor for future bent-pipe satellite broadband access networks that meets these 

new challenging requirements in terms of flexibility and processed bandwidth (expected to be up to 50 GHz). The prototype 

shall demonstrate all the key functionalities of the processor (e.g. high bandwidth signal processing algorithms, channel to 

beam allocation flexibility, wideband digital beam forming, etc.) and assess in detail the use of cutting-edge digital 

technologies (e.g. 0.13 micro-m, new low power consumption ADC/DAC) needed for achieving efficient processing of the 

large bandwidths involved within the next generation of communication systems. For budgetary reasons the PoC will make 

extensive use of FPGA technology. The prototype shall be implemented at a laboratory breadboard level and is expected to 

work at reduced scale in terms of processed bandwidth per beam and be scaled-down in terms implemented links. The PoC 

shall allow a thoroughly validation of the proposed architecture, signal processing algorithms and achievement of the 

performance requirements. Power and mass estimate for the final target technology shall be however performed. A real-time 

air interface simulator shall be developed for both up and downlink in order to provide the processor with the required IF and 

control signals. The simulator shall cover functions such as interference and propagation effects, satellite delays, network 

synchronization mechanisms, payload impairments, packet demodulation, background signalling loading of the switch 

controller, etc. 

Deliverables: 

Processor Detailed Design Report PoC of a scaled-down version of the High Throughput Transparent Processor. 







Title: 

New concepts for dual-gridded reflectors (study) 

Dual-gridded reflector antennas allow the combination of two apertures in almost the same room that would be occupied by 

only one normal reflector. This is achieved by using polarisation sensitive grids printed on the reflector surfaces. This concept 

is extremely important due to the accommodation constraints of the platforms and lead to very high polarisation purity. 

Ku-band dual-gridded reflectors are widely used today on commercial satellites. This activity deals with the study of possible 

technological implementations of dual-gridded reflectors for telecommunications applications in Ka-band. New concept and 

materials are mandatory due to high transmission losses of the front shell (approximately 0.8 dB) when Ku-band technology is 

considered for Ka-band. It is proposed to follow this preliminary design activity by an ARTES-funded demonstration phase. 

Deliverables: 

Design of dual-gridded reflector antenna at Ka-band. RF and mechanical samples to be used as proof of concept. 






Page 106 of 227




12/Feb/09 


T501-12ET 

Study of Enhanced digital transmission techniques for Broadband Satellite Digital 

Title: 

Transmissions 

Advanced digital techniques can be envisaged making use of dynamic signal pre-distortion at the modulator side combined 

with adaptive non-linear equalizer at the receiver in order to compensate both the amplitude and the ISI (Inter-Symbol 

Interference) distortions caused by the channel non-linearity. If digital pre-compensation and equalization techniques are 

used, the optimum operating point in terms of Baud rate may be shifted towards greater value of Bs/Bf while output back-off 

reduced. This is particularly true if higher order modulations (such as 8PSK, 16/32-APSK) currently proposed by DVB-S2 are 

adopted. Efficiency gains in the order of 2 dB in terms of power efficiency and 20-30% in spectral efficiency are expected with 

affordable implementation complexity. A further step is represented modulation schemes with constant envelope like M-ary 

CPM (Continuous Phase Modulation) signals and re-assessment of their suitability to broadband satellite communications. In 

particular, their energy and spectral efficiency on linear channel shall be investigated and compared to more classical linear 

band-limited M-QAM modulations. Performance shall also be investigated for typical non-linear satellite channels to show the 

performance gain of these signals. New coding schemes employing CPM signals shall also be studied. Carrier and timing 

synchronization techniques that are able to work at the very low operative SNR of typical satellite transmissions in presence of 

powerful coding schemes, shall be studied and optimised. Overall coded modulation performance over typical satellite 

nonlinear channels shall be finally estimated through an accurate end-to-end simulator. Finally implementation complexity 

issues for the demodulator and decoder shall be analysed and CPM complexity shall be compared with current state-of the art 

M-QAM demodulator/decoders. This is a key issue as in the past adoption of CPM schemes was often discarded for 

high-speed applications because of the lack of maturity of digital signal processing technologies. The activity shall include: 1. 

technical report trading off different equalization techniques for the specific application showing the proposed innovative 

techniques as well as their performance results assessed through analysis and computer simulations; 2. the description and 

the performance of the selected coded modulation scheme over the linear and non-linear channel; 3. the gain w.r.t the more 

classical modulations shall also be assessed; 4. the description and the performance of the carrier and symbol timing 

synchronizers suitable for the selected modulation scheme for both the forward and the return channel; 4. an in-depth 

assessment of the equalizer complexity and feasibility study for the selected application scenarios; 5. a software package in 

MATLAB or C/C++ implementing the overall system simulation including the channel distortion elements (IMUX/OMUX and 

power amplifiers) and modulators and demodulators with the proposed innovative techniques. 

Deliverables: 

Technical report. Selected modulation scheme description/performance/feasibility study; SW (MATLAB or C/C++). 






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12/Feb/09 


Title: 

T501-14ET 

Broadband low-power ADC design & prototyping 

The present activty is in line with the DSM (Deep Submicron Microelectronics) initiative strategy paper (ESA/IPC(2006)88). 

The main object of this study is the development of a 10 bits broadband (500 MHz / ~1.500 Msps) Analog-to-Digital Converter 

(ADC) with low power consumption (~1W) for on-board digital processing applications. 

This activity shall encompass the following tasks: 

- Process selection: 1. Radiation effects and mitigation techniques, 2. Reliability, 3. Lifetime. 

- Architecture trade offs. 

- Design. 

- Layout. 

- Simulations post layout. 

- Prototype/s manufacturing. 

- Electrical testing and performances measurement. 

- Limited environmental tests (temperature / radiations). 

This activity will be continued in the NewPro program (doc. ref. ESA/IPC(2006)75, activity ref. NP10-01ED). 

Deliverables: 

Electrically characterised prototypes and preliminary environmental tests results. The prototype shall be as representative as 

possible of a flight model, including the manufacturing of the die but also the package (ceramic hermetic package). 

Furthermore, the manufacturer shall propose a business model definition for the qualified product. 

Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5/6 >2011 

TLC: on-board processing, SCI: science 

& remote sensing instruments, EO: 


instruments, TLM&control, high-speed 


rate data downlink. 




ESA/IPC(2006)88 


Title: 

Broadband low-power DAC design & prototyping 


The main object of this study is the development of a 12 bits broadband (500 MHz / ~1.500 Msps) Digital-to-Analog Converter 

(DAC) with low power consumption (~.6W) for on-board digital processing applications. 

This activity shall encompass the following tasks: 

- Process selection: 1. Radiation effects and mitigation techniques, 2. Reliability, 3. Lifetime. 

- Architecture trade offs. 

- Design. 

- Layout. 

- Simulations post layout. 

- Prototype/s manufacturing. 

- Electrical testing and performances measurement. 

- Limited environmental tests (temperature / radiations).. 

This activity will be continued in the NewPro program (doc. ref. ESA/IPC(2006)75, activity ref. NP10-02ED). 

Deliverables: 

Electrically characterised prototypes and preliminary environmental tests results. The prototype shall be as representative as 

possible of a flight model, including the manufacturing of the die but also the package (ceramic hermetic package). 

Furthermore, the manufacturer shall propose a business model definition for the qualified product. 

Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5/6 after2011 











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12/Feb/09 

5.4 - Mobile Communications 


Title: 

T502-06EE 

Simulation of the satellite to indoor propagation channel at L and S bands 

The main objective of this activity is the characterisation through simulation of the propagation effects in the satellite to indoor 

channel at L and S frequency bands. This activity involves several tasks: Task 1: develop a precise 3-D characterisation of 

different types of buildings such as warehouses, office buildings, shops and shopping malls, factories, apartment blocks and 

single family dwellings taking into account the electrical properties of the different construction materials and elements. Task 

2: carry out simulations with a validated deterministic electromagnetic propagation model in all the previously generated 

buildings for different geometrical configurations (satellite elevation and azimuth and receiver position inside the building). 

Task 3: analyse the results of the simulations and develop a statistical propagation model for the satellite to indoor channel. 

Deliverables: 

The expected deliverable is a statistical propagation model for the satellite to indoor propagation channel at L and S bands. 

(SW IPR to ESA for operational activities (TBC)) 


Mobile Satellite Telecommunication 


systems 




Page 109 of 227




12/Feb/09 



Title: 

T504-02EM 

Energetic Electron Environment Models for MEO 

New models will be constructed to take into account the temporal, spatial and spectral variations in electron fluxes at altitudes 

and inclinations relevant for Galileo. The NASA AE-8 model that is traditionally used for the electron flux predictions in the 

radiation belt environment is static, based on data collected in the 1960s and 70s, and hence badly outdated. New models 

taking into account the dynamic nature of the outer electron belt are therefore needed. The aim of this activity is to produce 

such models utilising data from the ESA Standard Radiation Environment Monitor (SREM) instruments flying on Integral, 

PROBA-1 and the GSTB-V2. Electron measurements from other radiation monitors, including DoubleStar shall also be 

included, where applicable, utilising past ESA-sponsored data base developments, together with other observations and 

theoretical considerations. The models shall be WWW-based, and readily available for implementation in the SPENVIS 

system. Interfacing to Geant4-based software for radiation and charging effects analyses shall also be considered. 

Deliverables: 

WWW-based electron environment models for MEO orbits. These shall take into account the temporal, spatial and spectral 

variations in electron fluxes at altitudes and inclinations relevant for Galileo. 


Application/Mission: Navigation/Telecom Contract Duration: 24 months 




TRP Reference: T504-05GN 

Satellite and station clock modelling for GNSS, link between physical models and 

Title: 

estimation / prediction processes 

The data transmitted by navigation satellites (GPS, Glonass, Galileo) include so-called pseudo-range measurements, which 

arise from a multiplication of the signal travel time and the velocity of light. The travel time is computed as the difference 

between time stamps at signal transmission by the spacecraft and signal reception by the (ground or low-earth orbiting) 

receiver. These time stamps are generated by two independently running clocks. For all applications of the data, whether 

real-time navigation or post-processed geodetic use, the relative offsets between these clocks, or both offsets to a common 

reference time, need to be known with a high precision. The clock offset estimation process is based on an epoch-by-epoch 

estimation of all clock offsets, not taking into account the physical behaviour of clocks. The clear advantage of this approach is 

that the process is insensitive to the erratic behaviour of some clocks, and indeed this method can be used successfully in the 

presence of the deliberate degradation of GPS signals known as Selective Availability. The disadvantage is that some 

valuable information is not used in the estimation process, namely that there are some highly stable clocks in the system, with 

known statistical properties. The proposed study should investigate which models of clock behaviour are available and how 

they can be implemented in the orbit and clock estimation systems currently used and under development at TOS-GN. The 

algorithms to be implemented should allow the user to select clock modelling as an option, and also allow a combination of the 

traditional epoch-by-epoch estimation process with the use of clock models. 

Deliverables: 

Model and documentation. 


Application/Mission: GNSS Contract Duration: 18 months 




Page 110 of 227




12/Feb/09 


Title: 

T504-08ET 

Next Generation Compact Atomic Clocks 

The current Galileo navigation payload is based on two different clock technologies, Rubidium (RAFS) and H-maser (PHM). 

While the PHM provides medium to long-term fractional frequency stability at least 5 times better than the RAFS (in the 1E-14 

level), this is achieved at the expenses of mass and volume (factor 6 and 12 higher respectively). Atomic clocks based on 

vapour-cell technology (like RAFS) are intrinsically more 

compact and easier to realize (i.e. lower cost) than their atomic beam counterparts (like PHM). In addition, their lifetime is not 

primarily limited by the supply of atoms. A number of new innovative clock schemes are being proposed, showing the 

capabilities to improve the stability of vapour-cell based clocks to the level of the current H-maser, with relatively minor 

modifications of the existing unit. The objective of this activity is to 

define, design, validate and test a new scheme for atomic clocks based on vapour-cell technology, providing a factor of two 

improvement with respect to current technology, fractional frequency stability below the 1E-14 level in a mass-volume 

envelope comparable to present RAFS, and compatible with the Galileo space environment. In a first Phase, the various 

schemes shall be reviewed and analysed, leading to the selection of the most appropriate one. In a second Phase, the 

selected scheme shall be implemented and validated at BB level. 

Deliverables: 

1 vapour-cell atomic clock breadboard. 







Title: 

Development of Innovative Atomic Clock for Satellite 

High performance on-board atomic clocks are the core of a satellite navigation system such as Galileo. Each Galileo satellite 

will embark two different type of clocks: Rubidium (RAFS) and Passive Hydrogen Maser. While the performance of those 

clocks are fully meeting the today system requirements, next generation Galileo satellites would benefit of the use of higher 

performance clocks (in terms of fractional frequency stability), still compact (low power and mass) and able to operate in the 

Galileo space environment. A number of T&F laboratories are currently proposing a variety of new innovative clock concepts 

(e.g. cold atoms, CPT-maser, CPT-dark-line,), with the potentiality of improving significantly the stability performance, still in 

a reasonable mass-volume-power envelope. The objective of this activity is to identify and demonstrate (at demonstrator level) 

an innovative clock technology achieving at least a factor 2 improvement in fractional frequency stability with respect to the 

today demonstrated performances, still with mass-volume-power consumption budgets compatible with the Galileo payload 

accommodation, and able to operate in the Galileo space environment. In a first Phase, various innovative clock concepts 

shall be reviewed and analysed, in order to select the most promising one. In a second Phase, a demonstration model of the 

selected concept shall be assembled and tested, and a development plan (including the development and qualification of 

critical technologies) shall be proposed. 

Deliverables: 

Clock demonstration model. 


Application/Mission: GNSS second generation Contract Duration: 24 months 



Freq. & Time Generation - Space 


Page 111 of 227




12/Feb/09 


Title: 

T504-11ET 

Signal Processing Techniques and Demonstrator for Indoor GNSS Positioning 

GNSS-based location based services represent one of the main applications of GNSS however the users of those services 

are located in severely handicapped environments for the reception of the GNSS signals (outdoor urban canyons and in-door 

environments). 

The objective of this activity is to develop a number of enabling technologies suitable for operation in those environments. The 

techniques include: 

• New signal processing techniques that allow to drastically reduce the acquisition threshold (down to 15dB-Hz – normal 

outdoor value is 45dB-Hz) at a feasible implementation complexity and able to cope with strong multipath 

• Techniques for the detection of the EGNOS message down to a value of C/No around 25dB-Hz. EGNOS corrections will 

definitively improve the accuracy of indoor position computation. The reception of the EGNOS signal can be improved 

compared to other GNSS satellites since both the transmitter (GEO satellite) and the receiver (the speed of the receiver 

indoors is very reduced) are static. 

• Efficient ways of transmitting the assisting information to the mobile 

• Integration of measurement taken from GNSS and cellular systems 

• Techniques for the exploitation of the Galileo pilot signals with longer codes. This characteristic of the Galileo will alleviate 

the costly time transfer of the GNSS time from the base station to the mobile, at the same time that it can improve the 

accuracy by an order of magnitude 

The techniques shall be implemented and demonstrated in a receiver prototype based on FPGAs and DSPs on the basis of a 

core module containing a number of GALILEO, EGNOS and GPS channels. The core module channels will be designed 

according to the HS-GNSS principle and receive via wireless LAN the information provided by the A-GNSS server to be 

developed within the activity. 

Deliverables: 

New techniques for indoor positioning using GPS and Galileo, Indoor GNSS receiver demonstrator, Assisted-GNSS server. 


Application/Mission: Hybrid Navigation Systems Contract Duration: 20 months 





Title: 

Evolutionary Navigation Systems 

Nowadays, there are navigation applications that could not be foreseen when GPS was developed in the 70’s. The 

improvement of semiconductor technology, communication systems, positioning techniques, etc. are continuously giving rise 

to new areas where satellite navigation systems can be applied with new and always more stringent requirements. The 

objective of this activity is to study the future (beyond Galileo) needs that users will demand from navigation systems and to 

identify the critical technologies and techniques that have to be developed. A complete exploration of user needs and 

associated technologies will be done, and special attention will be devoted to: 

• Requirements of multi-modal applications 

• Integrity and certification requirements 

• Local augmentations 

• Improvement of signal reception in indoor or dense urban environments, and adaptation of the navigation message. 

• Resilience to multipath propagation and non-intentional interference 

• Ability to selectively improve the performance in “hot spots”. 

• Use of new signal bands (e.g. C-band) 

• Interoperability with satellite and terrestrial communication systems. 

• High-accuracy application requiring three or more frequency ambiguity resolution and carrier-phase based extended range 

positioning techniques. 

Deliverables: 

Analysis of user requirement for future navigation systems. Documentation containing a preliminary evaluation of 

architectures, technology and techniques that need to be developed in order to satisfy those needs. 


Application/Mission: Galileo evolution program Contract Duration: 15 months 




Page 112 of 227




12/Feb/09 


Title: 

T504-16MM 

Development of key Optical Clock technologies 

The development of a full optical clock has important bearing on Space Science, Navigation, Earth Science, Secure 

Communications, etc. Optical clocks in space are considered essential tools for the exploration the limits of contemporary 

phyics (e.g. general relativity). They would allow, for example, the direct observation of Gravitational waves, direct 

measurement of fundamental physics constants, redefinition of the second, etc; or provide highly accurate long-term (days or 

more) time referencing as needed for precise positioning and navigation (future Galileo satellites). Despite the various 

world-wide effort going into optical clocks for ground applications, no yet any serious effort has been initiated into the 

definition and development of a space-compatible optical clock. The activity here proposed will address the critical technology 

of the basic components of an optical clock (clock laser, atom/ion/molecule cooling unit, laser trapping unit, detection and 

measurement unit) with the aim of identifying a design suitable for space. Environmental aspects, as well as critical design 

and qualification issues will be addressed. The output of this actvity will be a breadbord of critical parts of an optical clock 

capable to prove the feasibility of optical clock in space. 

Deliverables: 

Breadboard 


Space Science, Navigation, Earth 


Science, Secure Communications, etc. 



Freq. & Time Generation - Space 


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5.6 - Satellite / Platform Technologies 


Title: 

T505-04ES 

Low Cost Coarse Earth Sensor Development 

The objective of this activity is the design of a low cost (




12/Feb/09 

5.6.1 - Antenna Technologies (Source: TRP 2000-2003) 


Title: 

EEA-013 

Q/V Band Antenna S/S 

Deliverables: 








Title: 

Q/V Band Antenna S/S: additional work 

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. 

Deliverables: 








Title: 

MMM-946 

Hybrid mechanical-electronic pointing system 

Deliverables: 







Page 115 of 227




12/Feb/09 

5.6.2 - On-Board Equipment Technologies (Source: TRP 2000-2003) 


03/ETM-001 

SAW Filter Development (original activity: SAW resonator technology for L and S-band 

Title: 

space applications) 

Surface Accoustic Wave (SAW) quartz resonators are often used in Voltage Controlled Oscillator (VCO) with demanding 

phase noise requirements. However, the use of SAW resonator based VCOs (SAWR-VCO) has so far mainly been limited to 

frequencies below 1 GHz for very high Q applications. The use of SAW resonators at higher frequencies and on other 

materials has been demonstrated in the MATOPS program for the use in low-loss impedance element filters (IEF). For both 

SAW-IEF and SAWR-VCO the main goal in design of the resonators is to achieve high resonator Q-values. 

The proposed activity aims at investigating and improving SAW resonator technology for use in VCOs in the 1-2.5 GHz range. 

There are several space applications of low-phase noise VCOs in navigation and communication systems operating in this 

frequency range. The results will also be applicable for narrowband low-loss filters and SAW notch filters. 

In particular, the study will focus on: 

• Analysis of material and design limitations of high-frequency, high-Q quartz resonators; other materials, such as Langasite 

(with lower intrinsic material loss), or other low-loss wave modes (STW). 

• Evaluation of high-Q resonators design aspects. 

• Breadboarding (design and development) of a SAW resonator, including manufacturing and testing of critical components 

and technologies; evaluation of specific manufacturing processes issues. 

• Evaluation of possible applications of a SAW resonator in VCO. 

This activity is proposed as a special measure to Norway. 

Deliverables: 








Title: 

SAW Filter Development (original activity: SAW resonator technology for L and S-band 

space applications) 

Deliverables: 







Page 116 of 227




12/Feb/09 


Title: 

97/XRF02 

Tool for high speed end to end system simulation 

Deliverables: 








Title: 

EEP-009 

Characterization and modeling of Propagagation effect Q/V Band 

Deliverables: 







TRP Reference: ETM-080 

Title: 

Cold Cathode TWT 

The aim of this activity is to develop a Breadboard of a cold cathode Travelling 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. 

Deliverables: 

Preliminary design, breadboard of the gun assembly and the design and breadboard of a cold cathode TWT. 

Current TRL: TRL2 Target TRL: TRL2-3 Application Need/Date: TRL6 >=2009-2011 

Application/Mission: Telecom payloads Contract Duration: 24 months 




Page 117 of 227




12/Feb/09 

5.7.2 - Telecommunication P/L (Source: TRP 2000-2003) 


Title: 

EEO-010 

Technology 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 is 

complementary to TRP activity 94/2.1.6.5. 

Deliverables: 

Breadboard 

Current TRL: Target TRL: TRL2 Application Need/Date: TRL5 >2008 

Application/Mission: Optical Beam Forming Networks Contract Duration: 18 months 




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12/Feb/09 




Title: 

03/EDP-001 

SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A) 

The first generation of high speed digital links controllers is based on the IEEE1355 standard which was the starting point to 

the definition of SpaceWire networks. They are used in very large number of ESA missions. However, the SMCS332 and 

SMCS116 devices are not fully compliant with the SpaceWire specification (e.g. they do not support time codes) and are 

implementing an initialisation state machine that leads to major operational constraints. Furthermore, they suffer from several 

design anomalies, discovered by first Users but today well characterised (e.g. w.r.t to interfaces in some sub-modes). 

Considering the situation, it required to upgrade the SMCS332 and SMCS116 to full SpaceWire compliance. This will allow as 

well to correct the identified anomalies and to secure the availability of such devices by producing them on a more recent 

silicon process (e.g. migrating from MG1RT to MG2RT). An extensive validation campaign is included in the proposed activity. 

Deliverables: 

Breadboard 


All missions (first possible application 


might be Cryosat 2) 




36 months 


Title: 

SMCS 332+SMCS116 upgrade to Spacewire (ECSS-E50-12A): enhancement 

The first generation of high speed digital links controllers is based on the IEEE1355 standard which was the starting point to 

the definition of SpaceWire networks. They are used in very large number of ESA missions. However, the SMCS332 and 

SMCS116 devices are not fully compliant with the SpaceWire specification (e.g. they do not support time codes) and are 

implementing an initialisation state machine that leads to major operational constraints. Furthermore, they suffer from several 

design anomalies, discovered by first Users but today well characterised (e.g. w.r.t to interfaces in some sub-modes). 

Considering the situation, it required to upgrade the SMCS332 and SMCS116 to full SpaceWire compliance. This will allow as 

well to correct the identified anomalies and to secure the availability of such devices by producing them on a more recent 

silicon process (e.g. migrating from MG1RT to MG2RT). An extensive validation campaign is included in the proposed activity. 

Deliverables: 

Breadboard 


Application/Mission: All missions Contract Duration: 36 months 




Conclusions: ESA/IPC(2003)32 

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12/Feb/09 


03/ESD-001 

Title: Rf Wireless Intra-Spacecraft Communications - Phase 1 

RF wireless techniques are being considered for on board short-range communications in view of the potential mass and 

power reduction and for the added benefit of increasing functionality and flexibility in S/C design, construction and testing. 

From recent years, RF wireless systems have known a great development in industrial, offices and home applications and 

offer a wide spectrum of mature products. The availability of high performance consumer-markets components make today 

RF an attractive approach for low mass on board-space communications for applications providing that EMC/EMI issues are 

adequately addressed at system level and shall be thoroughly investigated. This investigation will consider the space 

environmental aspects, in particular radiation, the spacecraft internal environment (in particular EMC/EMI) as well as the 

functional and operational aspects as a part of the on board data handling system (control and monitoring telecommand 

distribution/telemetry acquisition functions). 

The proposed activity deals with the use of optical wireless techniques for on board communications, and in particular will 

cover the following technology areas: 

• Functional and performance specifications for on board RF wireless communications for control, monitoring, command 

distribution and telemetry acquisition as part of the Spacecraft avionics for a set of typical mission scenarios (platform type, 

mission profile, orbit) and in line with relevant CCSDS standards 

• Identification of the most suitable system configuration and architecture for selected applications/scenarios 

• Identification and selection of commercial/industrial RF wireless communications systems (protocols, components) 

• Performance/reliability assessment of technology, components and devices 

• Assessment of Qualification for components and devices 

• Evaluation and characterization of electronics equipment/component and their interfaces 

• Selection of a Test application case from the preliminary set of applications scenarios to be used as System demonstrator 

• Definition of a Flight Test Demonstration based on the above 

• Preliminary design of the RF wireless communication system 

• Critical component and subassembly design and developments including mixed digital-analog Asics 

• Development of Software tools for system analysis optimisation and computer aided design (link budget…) 

• Development of communication protocol and interface layers for selected configurations, operation and test environment 

software 

• Integration and Test of the Elegant bread-board of a complete RF wireless systems for the selected applications 

• Consolidated technology road map and proposal for a flight demonstration based on the demonstration system. 

Deliverables: 

Technical datapackage. Elegant BB. 

Current TRL: TRL2 Target TRL: TRL3 Ph1. Application Need/Date: TRL5 by 2009 







Title: Rf Wireless Intra-Spacecraft Communications - Phase 2 

See Ph1. Description 

Deliverables: 


Current TRL: 

Target TRL: 

TRL3 

TRL3-4 

PH2 

Application Need/Date: TRL5 by 2009 






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12/Feb/09 


03/ESD-002 

Title: Optical Wireless-Intra-Spacecraft Communications - Phase 1 

Optical wireless techniques are being considered for on board short-range communications in view of the potential mass and 

power reduction, EMI immunity, and for the added benefit of increasing functionality and flexibility in S/C design, construction 

and testing. Recent advances in optical Micro and Nano Technology, the availability of high performance consumer-markets 

Opto-electronic components make today optical unguided links a feasible valuable approach for low mass, low power, high 

data-rate on-board space communications. Furthermore, the increasing bandwidth’s requirements for Earth Observation and 

Telecom payloads, the possibility to handle multi-user configurations, and strict S/C EMI immunity and cross-talk 

requirements, make optical wireless a very valuable solution to be thoroughly investigated. 

This investigation will consider the space environmental aspects, in particular radiation (electronics, electro-optics and optics 

components), the spacecraft internal environment (topology, materials reflectance and absorption) as well as the functional 

and operational aspects as a part of the on board data handling system (control and monitoring, telecommand 




• Functional and performance specifications for on board optical wireless communications for control, monitoring, command 




• Identification and selection of commercial/industrial optical wireless communications systems (protocols, components) 



• Evaluation and characterization of Opto-electronic equipment/component and their interfaces 



• Preliminary design of the optical wireless communication system 

• Critical component and subassembly design and developments such as fast IR repeater 



software 

• Integration and Test of the Elegant bread-board of complete optical wireless systems for the selected applications 


Deliverables: 


Current TRL: TRL2 Target TRL: TRL3 Ph1 Application Need/Date: TRL5 by 2009 







Title: Optical Wireless-Intra-Spacecraft Communications - Phase 2 

Optical wireless techniques are being considered for on board short-range communications in view of the potential mass and 

power reduction, EMI immunity, and for the added benefit of increasing functionality and flexibility in S/C design, construction 

and testing. Recent advances in optical Micro and Nano Technology, the availability of high performance consumer-markets 

Opto-electronic components make today optical unguided links a feasible valuable approach for low mass, low power, high 

data-rate on-board space communications. Furthermore, the increasing bandwidth’s requirements for Earth Observation and 

Telecom payloads, the possibility to handle multi-user configurations, and strict S/C EMI immunity and cross-talk 

requirements, make optical wireless a very valuable solution to be thoroughly investigated. 

This investigation will consider the space environmental aspects, in particular radiation (electronics, electro-optics and optics 

components), the spacecraft internal environment (topology, materials reflectance and absorption) as well as the functional 

and operational aspects as a part of the on board data handling system (control and monitoring, telecommand 




• Functional and performance specifications for on board optical wireless communications for control, monitoring, command 


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• Identification and selection of commercial/industrial optical wireless communications systems (protocols, components) 



• Evaluation and characterization of Opto-electronic equipment/component and their interfaces 



• Preliminary design of the optical wireless communication system 

• Critical component and subassembly design and developments such as fast IR repeater 



software 

• Integration and Test of the Elegant bread-board of complete optical wireless systems for the selected applications 


Deliverables: 


Current TRL: 

Target TRL: TRL3-4 Application Need/Date: 

TRL3 

TRL5 by 2009 

(PH2) 






TRP Reference: 97/WSP01 

Title: Fast Transform DSP Coproc Ph. 2 & 3 

Floating point data representation is not a requirement for some applications and a performance increase about one order of 

magnitude w.r.t the ADSP21020 can be achieved by using a fixed-point co-processor. This is particularly true for small block 

size FFts, FIR filters and transforms in general. A configurable device with multiple parallel ALUs shall be developed in the 

frame of this activity. The ASIC will be very suitable as a stand alone computing unit for low level processing or as an 

accelerator when coupled to the ADSP21020. 

Deliverables: 

Technical data package. Breadboard. 

Current TRL: TRL2-3 Target TRL: TRL5/6 Application Need/Date: TRL5/6 by 2008 

Application/Mission: RF instruments e.g. SAR, altimeters Contract Duration: 24 months 




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Title: 

ESD-006 

Design & verification of validation techniques for On-Board Microprocessors 

Deliverables: 








Title: 

ESD-016 

Safeguard Data Recorder 

Deliverables: 








Title: 

ESD-034 

Optical Wireless Data Transmission 

Deliverables: 







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Title: 

ESM-006 

High Speed Link Interconnect Network – Additional work 

The SpaceWire Router ASIC under development in this activity is based on the RMAP protocol, an extension of the 

ECSS-E50-12A standard. Owing to some protocol changes adopted by the international working group on RMAP, as well as 

to some functional problems in the current version of the SpaceWire Router design, not covered by the original requirements, 

some additional work is necessary. This activity will improve the component and will provide an interoperable, reliable and 

standard compliant ASIC. The activity shall include the following main tasks: 

- Router VHDL technical changes: 1. bit serial implementation of the reversed CRC, LSB first; 2. include a data CRC with 

value 0 when data field is empty; 3. correction of the link speed to the minimum authorized value in case a wrong command 

sequence would try to set it below; 4. allow the router to respond to 0 source address RMAP commands; 5. modification of 

one of the timeout conditions at the input ports; 5. modify accordingly the Validation SW. 

- VHDL test bed and test vectors modification accordingly to the router changes. 

- Verification of the new RTL model of the router. 

- Synthesis of a new RTL model for FPGA and ASIC technology. 

- Verification of new ASIC netlist. 

- Making of a new CIDL. 

- Reprogramming of the 5 router FPGAs. 

- New router FPGA validation exercise on single and double router test bed (shorter and simpler FPGA validation exercise, 

compared to the previous ones, where we only seek to validate that the changes to the netlist provide the expected functional 

changes). 

- Extension of the original WPs reserved for the basic router ASIC Validation to a full ASIC validation, as described in separate 

document. 

Deliverables: 

- Updated FPGA routers. 

- Updated FPGA router Data sheet. 

- Updated validation SW and related documents. 

- Report on the new FPGA router validation. 

- Extended ASIC router validation report. 


Application/Mission: All spacecraft data handling systems Contract Duration: 12 months 

SW Clause : - Dossier0 Ref.: T-901 (2004 D0) 




Title: 

ETD-025 

Compact Data Processing Unit 

Deliverables: 







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Title: 

ETD-028 

Integrated Payload Data Processing System System 

The objective of the 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. 

After the completion of the original tasks, CCN2 has been placed for the updating of the RMAP already implemented in IPPM 

to the latest draft (draft E) of the SpW standard. 

In addition, in order to ovecome some technical functional limitation envisaged during the final test phase, CCN4 has been 

placed, having the following scope: 

* Replacement of faulty SpaceWire router with FPGA version of the SpW router 10x ASIC. 

* Modify memory interface between Leon2 processor and memory devices to achieve maximum operational speed 100MHz. 

The main tasks involved are: PCB rework, VHDL code refinement, PCB manufacturing, assembly and integration, FPGA 

fitting and post layout simulations, Test and validation Session. 

Deliverables: 

Demonstration model. 







TRP Reference: ETD-036 

Title: 

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 the further 

increasing data rate requirements from future payloads, nor with the dramatic technology evolution of the commercial DRAM 

technology. The commercial SDRAM used in today’s SSMM are soon expected to be obsolete. The PC marked already 

moved to newer and faster DRAM standards like DDR-SDRAM and DDR2-SDRAM. These new devices are expected to put 

some architectural constraints at memory bank level. This comprises amongst others new requirements on the readout 

circuits and possible new radiation introduced error modes in the read out and the more complex on chip addressing logic. 

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 new 

DRAM standards and the emerging very high data rate payload requirements shall be developed. 

Deliverables: 

Breadboard. 

Current TRL: TRL2 Target TRL: TRL3-4 Application Need/Date: TRL5/6 by 2007 

Application/Mission: EO, SCI missions Contract Duration: 18 months 




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Title: 

ETD-038 

Space wire Controller Remote User 

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. The devices will also be made available to the 

participants of ETD-039. 

Deliverables: 

SpaceWire specific Controller and Remote-User-Interface demonstrator. 


Application/Mission: Spacewire Networks Contract Duration: 24 months 




TRP Reference: ETD-039 

Title: 

TOPNET: Pilot Operation Implementation - Topnet Deployment 

The objective of this activity is to demonstrate the benefits of the TOPNET approach through early integration of actual 

hardware. For this purpose equipment supplier will be invited through an AO to participate by making their (existing) 

equipments available for the demonstration. Development of new equipments is not foreseen as part of the demonstration. 

Contract value will range between 50-150 KEeuro. The activity will utilise the tools developed under ETD-037.A and the 

controller developed under ETD-038. 

Deliverables: 

Pilot Demonstration 


Application/Mission: all S/C, SCI, EO, in line testing Contract Duration: 24 months 





Title: 

FPGA Based Generic Module and Dynamic Reconfigurator 

In the framework of the on-board payload data processing reference system, the computing power is de-centralised and 

distributed in well-defined processing modules where the applications rely on. One of the major benefits of this architecture is 

to allow the independent technological evolution of the modules without affecting the architecture itself: objective of this 

activity is therefore to provide the system with new processing models that can be, on one side, painless inserted into the 

exiting architecture and, on the other side, not specifically designed for a particular need. In this way, words like equipment 

re-use or non-recurrent costs saving become realistic; but which hardware components can we use for such a development 

The most profitable solution is to develop this processing module using an FPGA based design: this approach gives some 

flexibility during the definition and early validation phase as well as smooth porting of the demonstration to its flight version 

(using space qualified FPGAs). 

Deliverables: 

HW demonstrator, validated into the payload data processing reference system. 


Application/Mission: Exploration missions Contract Duration: 24 months 




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Title: 

T603-08ES 

Next Generation Multi-purpose Microprocessors 

The prototypes of the AT697 of ATMEL (LEON2–FT) are already available for evaluation and advanced design of flight 

computer boards and the flight parts of the AT697 will be soon commercialised. The AT697 microprocessor is based on the 

LEON2 model and it offers a significant increase of performance (100 MIPS, million of instructions per second) with respect to 

the previous generation of the ERC32 microprocessor (25 MIPS for the TSC695). This new AT697 microprocessor will satisfy 

the newly and evenly increasing requests of performance for the new space missions. The development time of high 

performance microprocessors for space use (with Single Event Effects tolerance) is at least 5 years and consequently it must 

be largely anticipated. In a present contract the Agency is already preparing the next generation of general purpose of 

microprocessor with the target to offer an increase of performance in a ratio of 10 with respect to the last generation of the 

AT697 together with a higher flexibility of usage that is based on a multiple core approach that will be an enabler for a new 

class of system architectures and capabilities. The objective of that present activity is to adapt and to configure the new 

available commercial LEON3 model for its use in a high performance processor architecture suitable to space use and to 

validate that new architecture on FPGA (Field Programmable Gate Array). The previous experience with the development of 

the AT697 has shown that the implementation of a complex processor model using advanced silicon technology is not trivial 

and need also some anticipation work. The purpose of the proposed activity is to continue the present activity based on the 

LEON3 model with the objective to establish the appropriate design implementation methodology and select the appropriate 

design implementation tools, to make the necessary fine tunings of the architecture and the detailed design of the model that 

are required by the design implementation, and to produce a silicon demonstrator using an advanced commercial silicon 

technology as close as possible of the target space technology for the final implementation and that will exhibit the full 

performance and that will be as much as possible representative of the functionality of the future space version of the next 

generation general purpose microprocessor. Microprocessor devices and evaluation boards will be made available to the 

European space community that can be used for familiarisation, evaluation, and consolidation of the specification of the next 

generation general purpose microprocessor product. 

Deliverables: 

Documentation and breadboard. 

Current TRL: TRL1 Target TRL: TRL4 Application Need/Date: TRL5 by2012 

Application/Mission: all missions Contract Duration: 24 months 



OBCDS - Microprocessors and Microelectronics 



Title: 

Validation and further development Spacecraft-Controller-on-a-Chip (SCOC) 

In the SCOC1 contract (13345/99/NL/FM), a prototype design (called SCOC1 from now on) and an evaluation board (BLADE) 

for the SCOC device has been developed by/with EADS-Astrium Vélizy. The final objective of the SCOC programme is to 

produce an ASIC, available as off-the-shelf component to European Industry, which will simplify the architecture of future 

OBDH systems. The device functionality shall be comprehensive such as to satisfy a large variety of system requirements, yet 

be scalable such as to be able to work in systems not using all of the features at reduced power consumption. With the 

experience and lessons learned from SCOC1, the Definition and Architectural Design (updated/modernised Specification, 

verified RTL code) for an ASIC implementation (called SCOC2) shall be performed in the present contract. Manufacturing, 

industrialisation and software development being subject to follow-up activities, this contract ends with an enhanced feasibility 

study (selection of, and synthesis into potential target technologies). The activity also includes the development of new IP s 

(e.g. AMBA bus monitors) or updating of existing IP s as appropriate. New IP s are also deliverable as separate IP's. The goal 

is to have at the end of this contract a verified RTL design, which is ready to be mapped into an ASIC. 

Deliverables: 

Updated SCOC-FPGA design database and development board; specification for SCOC-ASIC; demonstration report and 

SW/driver library; new or updated IP. 


Application/Mission: all S/C Contract Duration: 18 months 




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Title: 

T603-20ET 

Development of a Mass Memory Module with Embedded File System Support 

The Payload Processing System architecture is able to host a set of well defined modules (Processing, Storage, I/O) 

interconnected through a network. As far as storage modules are concerned, a first demonstrator of the concept was 

developed and manufactured (High Capacity Memory Buffer). Based on standard interfaces, the module was designed in 

order to be very close in terms of functionality to a "solid state" disk providing basically to the User a sea of data blocks 

(random block mode) rather than emulating a tape recorder (LIFO/FIFO modes).Building on this, it appears clearly that the set 

of data blocks can be organised in a more flexible manner by embedding block allocation tables in the mass memory module 

itself. Of course and ultimately, the link between a "file" as seen by the payload data system controller and block allocation 

tables shall be established by a well defined split of functions between the supervisor and the high capacity buffer. This 

activity will focus on the development of a mass memory module embedding file system support following the concept outlined 

above. 

Deliverables: 

Two mass memory modules electrical/elegant breadboards 





Payload Data Processing 



Title: 

Synthesizable VHDL IP cores 

The objective is to develop Intellectual Property (IP) VHDL cores that meet the demands of future spacecraft architectures. If 

the VHDL cores can also be used in the commercial domain, the advantage of free distribution and user community feed back 

should be exploited. The actual cores to be developed need to be investigated at start of the activity. The activity shall be 

coordinated and maintain compatibility/compliance with standards established by previous developments (LEON/AMBA) and 

other new activities. Apart from completely new designs, the adaptation/improvement of existing IP's (or previous ASIC 

designs) shall be considered. The suggested VHDL IP cores to be developed are a Floating Point Unit for digital signal 

processing; improvement of inter-chip and inter-board interfaces (e.g. PCI, PCIX); ethernet controller; high speed 

telemetry/telecommand for CCSDS Advanced Orbiting Systems and Proximity Links; image Compression cores; Star Tracker 

Interface and Gyroscope Interface ESA shall retain ownership and full IP rights as to be able to use the delivered new IP 

cores for internal and external ESA or non-ESA projects, at ESA discretion. Special attention shall be given to the high quality 

of the User's Manual documents to be produced for each IP Core, to guaranty maximum autonomy of the IP Core customers, 

and minimise the level of technical support requested to ESA. 

Deliverables: 

Synthesizable VHDL IP cores with User's Manual, and testbench documentation. 






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T603-27ED 

Evaluation of Radiation Effects on Deep Sub-micron CMOS Technologies (Original 

Title: 

title:SEE Identification, Modelling & Severity assessment) 

Based on an extensive review of already published information, this activity will establish in a first instance specific 

vulnerabilities of deep submicron silicon technologies (target 90 nm CMOS). This first assessment will be based on modelling 

and simulating potential impacts of radiation effects on digital circuits, allowing to determine their severity (taking into account 

very low supply voltages and high operating frequencies). Then workaround techniques will be proposed and assessed in 

terms of feasibility taking into account all possible mitigation techniques at all levels. Finally a set of test structures shall be 

designed, demonstrating the models and the effectiveness of the proposed mitigation techniques on Silicon. 

Deliverables: 

Models (to derive impact on digital circuits and suitable mitigation techniques). Severity assessment of forecasted effects 

(SET FIT quantification for given design/rad environment). Test structures design. 







Title: 

T608-26ES 

Radiation Hardened by Design ASIC library qualification, procurement and maintenance 

This activity will give continuity and consolidate the results of two previous activities in which a 

Radiation-Hardened-by-design (layout design) Standard Cell library based on a commercial CMOS .18 micron library (from 

Virtual Silicon Technologies) and ASIC manufacturing process (UMC) has been developed, tested, and pre-qualified by 

means of two test-vehicles ASICs and a large DSP (>1Mgates) ASIC . 

This new proposed activity seeks to consolidate this library as a reliable and inexpensive new alternative to the very few 

library/foundry choices that exist in Europe to fabricate Rad Hard ASICs. 

Deliverables: 

Fully characterised and tested RHBD library. 






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Title: 

T609-08ET 

Massively Parallel Processor Breadboarding 

The demand for digital signal processing from on-board applications in earth observation, science and communication is 

continuously growing while the only available radiation hard DSP processor TSC21020F is today old technology and will 

disappear latest by 2007. It is not clear if there will be a follow on for this DSP as 32-bit DSP manufacturers are not numerous 

and are in general not interested in licensing their technology for a niche sector like space. The performance need of the 

applications lead today to a lot of ASIC developments for every new application in order to cope with the requirements. On the 

other hand FPGAs, which provide flexibility are not able to deliver the needed performance. The objective of this activity is to 

demonstrate, that new flexible processor architectures are capable to fill the gap between ASICs and FPGAs with respect to 

required flexibility, performance and budgets. These new flexible architectures are based on multiple DSP cores which can be 

internally rearranged (in parallel or in pipeline) by software command according to the algorithm requirements. The processor, 

once being available as customisable IP core (Intellectual Property), shall provide a high performance complement to FPGA 

technology for space applications as it can be tailored in a most efficient way and it shall be possible to transfer it at a later 

stage to radiation hardened technologies. 

Deliverables: 

BB incl. a commercial grade ASIC with new flexible multi DSP processor architecture demonstrating flexibility/performance. IP 

core of multi DSP architecture transferable to other ASIC processes. Programming tools (for appl. implement on the 

processor). 


Application/Mission: missions with high data rates e.g EO, Sci Contract Duration: 18 months 




TRP Reference: T609-25ED 

Title: 

SpaceWire Network Bandwidth Performance Simulation Tool 

In a number of activities ESA has prepared the SpaceWire technology that allows to embark high speed data networks on 

board of future satellite systems. This new technology has become widely adopted not only by ESA missions but also by other 

agencies and industry. The design of the topology and routing tables of such a on-board network, which has to comply to the 

system requirements, is left today to the engineering judgement of the designer and can be only validated at a late stage 

during system testing. This task becomes more and more difficult when the complexity of the on-board networks increases. 

A simulation of such high speed on-board networks will allow to verify the performance requirements like latency and 

throughput and to verify the redundancy scheme. It will allow to optimise the routing tables and ensure that the designed 

network is non blocking. A simulation software for this task should configurable with the network topology, link, router, node 

characteristics and the network data load. The results of this simulation should provide a clear view on the network statistics 

and provide a validation of the chosen network topology already during the design phase 

Deliverables: 

Engineering software tool for modelling and performance assessment of High Speed On-board Networks. 


All payload data systems using high 


speed onboard networks 

SW Clause : Operational SW Dossier0 Ref.: 


Payload Data Processing 


12 months 

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Title: 

T609-26ED 

OCP-IP building blocks for Space-SoC 

"Open Cores Protocol" (OCP) is an emerging standard set of requirements and tools that are being successfully applied to 

facilitate IP Cores reuse, easier integration and compatibility between different on-chip bus systems (CAN, AMBA, SpaceWire, 

I2C, etc). The activity would be about designing OCP-IP modules for our existing ESA IP Cores, so future space-SoC can 

make use of ESA OCP compliant building blocks. 

Deliverables: 

OCP-IP modules architecture. 


All spacecraft data handling systems / 


Space-SoC 



On-Board Payolad Data Processing 


TRP Reference: T609-27ED 

Title: 

Standardisation of spacecraft onboard communication services 

Until recently, standardisation efforts within the realm of onboard spacecraft have concentrated on physical interfaces and 

associated protocols. Such activities have been handled by the Consultative Committee for Space data standardisation ( 

CCSDS) or the ECSS. Within these standardisation bodies emphasis is now being placed on the definition of communication 

services and protocols which allow independence from the underlying hardware and thus open up the possibility for software 

re-use across multiple missions. This has the potential to significantly reduce spacecraft development times and associated 

costs. As part of the ongoing work of the Spacecraft Onboard Interface Services (SOIS) group within the CCSDS, 

recommendations for a suite of communication services are well advanced and will be made available in draft form before the 

end of 2006. In order achieve final publication, the draft recommendations must be prototyped and verified in a representative 

spacecraft environment. This activity will cover there required prototyping, integration and test on an existing ESA test-bed 

infrastructure. Results will be incorporated by ESA into the final CCSDS recommendation which will subsequently be adopted 

by ESA for potential application to all spacecraft projects. The software should take the form of reference libraries which can 

be made available for use by ESA projects. 

Deliverables: 

Software implementing the CCSDS defined services and protocols 


Application/Mission: All spacecraft data handling systems Contract Duration: 12 months 





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Title: 

EME-012 

Component Oriented Development Techniques 

The objective of the activity is to put in practice for space flight software the various techniques used in the wider IT world in 

this domain: components, frameworks, model driven development and architecture, aspects features, etc. This includes the 

assessment of the state of the art, precision of the vocabulary used in the domain, impact on flight software where the 

hardware resources (memory / execution time) are limited, and development of a case study based on prototype generic 

architectures or building blocks. 

Deliverables: 

Component-based space architecture + its assessment in terms of performance and standardisation. (In view of using the 

prototype as ESA building block for future missions, operational SW is necessary). 

Current TRL: algorith Target TRL: 


prototype 


m 






Title: 

EME-014 

Compact Computer Core S/W 

Deliverables: 







TRP Reference: EME-017 

Title: 

Tools For The Production Of O/B Sw Running On New Generation Computers 

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. 

Deliverables: 

SW breadboard 

Current TRL: - Target TRL: S/W release Application Need/Date: SW operational >=2007 

Application/Mission: All missions within LEON Contract Duration: 8 months 




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TRP Reference: EME-100 (EME-011, T- 

Title: 

Effective Use of autocoded Comp. 

Deliverables: 







TRP Reference: T603-28QQ 

Validation of Safety and Dependability Critical Software Componenets with Model 

Title: 

Based Requirements 

The validation of safety and dependability critical software components starts with ensuring that the requirements have been 

confirmed as fully testable and that they are complete and consistent. One approach that promises to facilitate the 

requirements definition process to achieve those three objectives is the use of models that can be analysed and simulated. 

Suitable models would need to be able to cope with incomplete and vague requirements at the early stages of a project’s 

definition and support the evolution towards formal or semiformal requirements at the end of the requirements definition 

phase. The simulations and analysis that would be possible on requirements models would support the preparation of high 

quality validation test suites. 

Deliverables: 

Technical notes (incl.: requirements models/quality requirements, and associated metrics; analysis techniques and simulation 

techniques for the requirements models; proof-of-concept through application to a case study). 

Current TRL: - Target TRL: Algorithms Application Need/Date: SW operational by 2010 






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Title: 

T603-29SW 

System and Software Functional Requirements Techniques 

The activity will investigate how to integrate the two processes (system and software) through the use of complementary and 

integrable modelling technologies in phase A and B. The expected benefit is to arrive at the PDR with consolidated system 

functional requirements easily transferable to the software life cycle development. This will ensure a better continuity of the 

overall life cycle, from mission level modelling to software implementation through incremental model translation. The new 

method will complement the ASSERT results and both could be integrated in the long term in the CDF for final 

experimentation. The activity will include: (i) selection of a mission appropriate for mission level functional modelling and 

associated software requirements modelling. (ii) survey and selection of system and software modelling techniques (not 

limited to aerospace, but including also railway and automotive) (iii) implementation of the case study (iv) definition of the 

appropriate process and tools in reference with ECSS-E10Part1 and ECSS-E40Part1 (v) possible experimentation in the 

CDF. 

Deliverables: 

Suitable modelling methods, prototype environment, case study covering phase A and B. 

Current TRL: - Target TRL: Prototype Application Need/Date: SW operational >=2010 





On-Board SW 

TRP Reference: T607-01EM 

Title: 

Automation of the life cycle: automatic test generation 

The existence of more and more models of the system requirements allows to derive automatically sequences of test from the 

models. The issue is the selection of the tests which are appropriate for the test goal, and therefore the selection of the test 

goal itself. The selection criteria may be based on the test coverage, or on the activation of given internal states of the system, 

or selected use cases of the system that should be verified. The automatic tools will try to find all the test scenarios that oftwa 

the goal of the tests, either in a systematic way or through the use of statistic (statistical testing), or trying to achieve a 

coverage rate. The activity will select modelling languages on which automatic testing is possible, propose a test vector 

generator for given test goals, and give the process to use the tool. The activity will also investigate the statistical testing as a 

mean to target the test effort, precise its application to space oftware, and define how to use it in accordance with the 

software standards. 

Deliverables: 

Report (selection of appropriate modelling languages for automatic testing; testing criteria/statistics). Testing tool 

implementing the various testing policies. Report on adequacy of statistical testing with SW standards and a case study. 

Current TRL: 

Target TRL: Opeartional Application Need/Date: 

- 

tool / 

demontstrat 

SW operational >=2007 

ion 

Application/Mission: all space project Contract Duration: 12 months 




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Title: 

T607-05EM 

Verification and Validation: Testing Object Orientation 

Object oriented languages are entering more and more into the space on-board software domain. Since the shy beginnings of 

object-based design using the HOOD method, a long way has lead us to the more frequent use of UML, C++ and Java 

languages on-board. This introduces powerful design features which express a lot in a small pattern. However, the associated 

code is also complex, and sometimes the selection of the piece of code to execute is made at run-time. It becomes extremely 

difficult to exhaustively test the overall software behaviour, as there may be too many combination and undeterminism. The 

goal of the activity is to investigate these specific OO features whose use makes testing very hard. The activity will propose 

solutions to overcome the problem. The solution ranges from proposing a clever and appropriate test policy specific to the 

feature, up to banning the use of the feature in a coding standard. 

Deliverables: 

Documentation with guidelines on testing object oriented on-board software and contribution to coding standards. 

Current TRL: 


- 

tool / 


method 






Title: 

T607-08EM 

Standardisation and Building Blocks: Standardisation watch and verification 

The activity aims at guiding, supervising, controlling and verifying the standardisation of the building blocks. It is a long term 

activity all along the standardisation period. It includes the creation and animation of a standardisation watch group involving 

industry members who will be in charge of defining what needs to be standardised, how it is standardised. It takes care of the 

maintenance of the standard. It steers the open source implementation, it guarantees the availability of the reference 

architecture, it decides on the deployment, and is responsible for organising the maintenance of the building blocks. It also 

includes the verification of the standards during their definition in terms of completeness and consistency between each 

others. This will be done with some dedicated tasks to verify specific technical aspects such as consistency of interface, 

completeness of the behaviour definition, data models, etc. 

Deliverables: 

System Model of a generic avionic architecture and a decomposition in building blocks. 

Current TRL: 


- 

SW operational >=2009-2010 

version 




On-Board SW 


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12/Feb/09 



Title: 

EPB-001.C 

Development of Regenerative H2/O2 fuelcell 

Deliverables: 







TRP Reference: EPG-025 

Title: 

Solar Cells Testing Spasolab 

A five years contract (220kE/year) is proposed aiming at covering Spasolab 2003-2007 operational phase for supporting solar 

cell developments in the TRP. 

A list of Spasolab solar cell test laboratory capabilities is provided in the following: 

• Complete characterisation of space of Space Silicon and Gallium Arsenide solar cells (Type approval tests). 

• Development of test methods for the characterization of last generation photo-voltaic devices 

• Electrical characterization at panel and module level. 

• Electrical and environmental characterization at coupon level. 

• Calibration of reference solar cells (primary and secondary standards). 

• Research and development activities (e.g. elaboration of specifications for new devices). 

Deliverables: 

Tested samples. Technical note, test results. 

Current TRL: N/A Target TRL: N/A Application Need/Date: N/A 

Application/Mission: all space projects Contract Duration: 60 months 




Solar Generators 

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12/Feb/09 


Title: 

ESB-008.A 

Adaptation of terrestrial fuel cells for space applications 

Deliverables: 







TRP Reference: ESG-007 

Title: Thin Film Solar Cells Ph. 3 

Deliverables: 







TRP Reference: ESG-009 

Title: 

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. 

Deliverables: 

20 - 30 GaAs solar cells (demonstrators) with the newly developed protection technique and an evaluation report of old and 

new protection methods, including assessment at system level and costing. 







Page 137 of 227




12/Feb/09 


Title: 

ESG-010 

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. 

Deliverables: 

At least 1 development sample (mini module) for each solar cell type shall be produced. 


Application/Mission: Telecom, Science, EO Contract Duration: 18 months 





Title: 

ESG-017 

Flexible Blanket Technology 

Deliverables: 








Title: 

ESP-003 

Solar Array Sizing tool for Phase A/B studies 

Deliverables: 







Page 138 of 227




12/Feb/09 


Title: 

T505-11EP 

Advanced research and pre-development of new materials for space solar cells 

The aim of the project is to allow pre-development of new materials and concepts which will enable construction of solar cells 

with performance closer to theoretically possible values, such as multi-junction cells with an efficiency of >40%. This project 

will also aim to extend the alliance of the best European materials technology with European solar cell research groups and 

manufacturers. In this project, growth of new materials such as nitride based alloys will be researched in order to produce 

material quality required for state of the art photovoltaic devices, in particular to facilitate multi-junction devices. Further 

research, needed into novel processing techniques and device concepts required to exploit the new materials, is not included 

in this proposal and it is recommended as follow-on activity. 

Deliverables: 

20 demonstration solar cells (using other materials as well as/instead of GaAs based alloys). Report which assesses the likely 

developments and applications of new space solar cells for missions until 2015. 


Application/Mission: Missions >=2020 Contract Duration: 18 months 




TRP Reference: T604-02EP 

Title: 

Advanced Lithium Batteries Evaluation 

The objective of this activity is to evaluate new advanced rechargeable lithium batteries offering energy density over 250 

Wh/kg. Such batteries could lead to mass and volume savings of spacecrafts. 

Lithium cells (graphite/LiCoO2 couple) offer today energy density around 180 Wh/kg. This electrochemical system is reaching 

maturity, with a limitation at about 200Wh/kg; therefore, to obtain a significant gain in energy density, it is necessary to study 

new electrochemical couples. The development of high energy density lithium batteries is driven by the terrestrial market, and 

studies on new electrode materials and new electrolytes are numerous. 

Positive electrode materials with higher capacity, also with higher potential (up to 5 V, i.e LiCoPO4) are studied by many 

groups. Negative electrode materials are also developed to replace the current graphite anode (i.e FeSi or FeSn can offer an 

energy 10 times greater). Lithium, the lightest and most energetic metal but highly reactive, can also replace the graphite 

anode. The use of such new electrode materials requires new electrolytes (i.e polymers, ionic liquids, plastic crystals, …). 

Some promising electrochemical systems are under investigation in Europe and elsewhere. 

This activity will include: a survey of the new electrodes materials and new electrolytes, identification of new electrochemical 

couples that could lead to the highest energy density, preparation of cells with the new materials, testing of the new cells. 

Deliverables: 

Report on the survey, various trade-off analysis following this survey, a technology dossier of the selected electrochemical 

systems, breadboard of the electrodes and cells, tests and tests report. 


Application/Mission: Applicability to all missions (>2010) Contract Duration: 18 months 




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12/Feb/09 


T604-03EP 

Title: Development of Next Generation GaAs Based Multi-Junction Solar Cells - 2 

The development of next generation multi-junction solar cells will facilitate higher power satellites and will enable new 

applications, mainly for telecommunications purposes. It will also contribute to an independent European supply of 

state-of-the-art multi-junction solar cells to ESA and European prime contractors at open market conditions. This activity has 

the following main objectives: 

1. Development of improved triple junction cells (>30% efficiency) and 4 / 5 junction solar cells, with target >32% efficiency at 

beginning of life (>41mW/cm2) and 90% remaining factor at end of life. 

2. Development of cheaper, lighter multi-junction cells on alternative substrates. Pre-qualification devices. 

Deliverables: 

30 samples of triple junction cells (efficiency >30%) and 80 samples of 4 or 5 junction space solar cells with a beginning of life 

efficiency greater than that of the best triple junction cells (target >32%), ready for qualification; target end of life performance 

of 90% of initial value; 100 samples of multi-junction space solar cells grown on alternative substrates (pre-qualification 

samples); data package detailing overall progress towards cost reduction and performance improvement of multi-junction 

cells. 

Current TRL: TRL2 Target TRL: TRL2/3 Application Need/Date: TRL5 by 2009-2010 

Application/Mission: Applicability to all missions Contract Duration: 24 months 





TRP Reference: T604-05EP 

Title: Development of Next Generation GaAs Based Multi-Junction Solar Cells - 1 

Deliverables: 







Page 140 of 227




12/Feb/09 


Title: 

T604-06EP 

Nanotechnology for Space Solar Cells 

Nanotechnology could permit a new degree of freedom for solar cell design (as already for other electronic components such 

as lasers) due to the possibility to engineer quantum opto-electronic properties that are otherwise fixed for a given material. 

This project will develop ideas for new structures which use the structural design of a solar cell to tailor the absorption 

properties in an advantageous way, as already underway in Europe mainly for terrestrial applications and elsewhere in NASA 

funded projects for space].This study will consist of two phases: the first one will study of the feasibility of at least one design 

for incorporation of nanotechnology in solar cells for space applications, especially in relation to the technology to be 

developed. This is intended to involve collaboration between universities / research centers to introduce nanotechnology 

concepts and eg. a space cell manufacturer or other partner to contribute relevant experience of space requirements. The 

second phase will consist in the manufacturing and testing of demonstration devices to evaluate potential for space. 

Deliverables: 

Report on feasibility/potential benefit of nanotechnology for space photovoltaics. Demonstration model: 25 cells incorporating 

nanotechnology (such as quantum wells or dots, Bragg reflector layers etc.). 







Page 141 of 227




12/Feb/09 


T604-07EP 

Efficient Low Cost Power Conversion for Standard and Advanced Fast Digital 

Title: 

Electronics 

In Europe, and in spite of the many development efforts performed so far, it is not possible to procure efficient, low cost 

converters as Off-The-Shelf (OTS) items readily available on the market and suitable for space missions. 

European users are therefore more and more considering the use of OTS converters from US, where market conditions exist 

to enable specialised companies to live on their converter products. 

The large commercial or military market-base of such companies allows them to propose OTS converters for space at 

competitive prices, when intermediate quality levels are offered (for example, class H hybrids according to MIL-PRF-38534 

specification). 

The present activity is aimed at establishing the initial steps towards the development and qualification of a European set of 

efficient, low cost, readily available OTS converters for standard and advanced digital electronics. 

The set of converters shall cover all the required output voltage ranges for digital equipments (very low voltages for advanced 

technologies – 2.5V and even 1.8V - and usual 3.3V and 5V for standard technologies). 

A couple of power levels (5W, 15W) shall envelope the typical applications required for payload users on board of the 

spacecraft, and the input voltage levels will be specified to cope with the regulated or unregulated bus standards around 28V 

or 50V. 

The initial development steps (to be covered under TRP) are the following: 

• definition and implementation of an COTS (Commercial Off The Shelf) EEE components policy for the specific application; 

• converter design, manufacturing and test (at prototype level); 

• basic verification on key performances in environmental conditions ( radiation verification, above all). 

The next essential steps to ensure that the final product will be effectively available on the market is manufacturing of 

representative QMs, and their qualification by an adequate and thorough test campaign (to be pursued later via a GSTP or 

other funding). 

Note that this second phase is essential for the success of the initiative. 

Important remark: The target markets for these converters are s/c payloads and not essential platform units (like PCU, PDU, 

CDMU, RTU, TX, RX). 

For essential platform units the proposed approach is deemed still too advanced, and the use of specific converter designs, to 

be developed on a case by case basis with space-grade EEE parts is still the preferred option. 

Note that European key players do recognise the power supply and conditioning of their essential platform units as a strategic 

asset for ensuring overall reliability, and therefore they have specific in-house converter development capabilities. 

Deliverables: 

• Definition and implementation of an OTS EEE components policy (using COTS) for the specific converter application; 

• Set of converter demonstrators showing the suitability of the selected design to cover the range of application. 






Page 142 of 227




12/Feb/09 


Title: 

T604-08EP 

Integrated Current Limiter 

Solid state switch devices for bus protection purposes are strongly established in ESA missions. However, they are always 

implemented in discrete version. Cost and size may sensibly benefit of a integration of this function. 

A typical discrete current limiter usually requires typically 6 cm x 6 cm. An integrated solution may be probably implemented 

in 3 cm x 2 cm. Thus, current limiters size would be dramatically reduced. S/C Power Distribution function may be reduced 

from the 10 double Eurocard modules required for instance in Herschel and Planck satellites to only 2. 

This integration of a recurrent discrete design would also offer cost reduction because the decrease in number of modules 

proportionally reduces recurring MAIT costs. Furthermore, the reduction of number of parts reduces the procurement effort 

and overall components price, thus, decreasing furtherly the cost. 

Last but not least, re-utillisation of a product repetitively used with success in different missions shall also reduce the 

development risks of the Power Distribution function within the spacecraft. 

With all this in mind, the objective of this activity should be the development of demonstration samples of a Standard 

Integrated Latching Current Limiter having a low recurrent price. 

Deliverables: 

Technical Notes, Demonstration samples 


All ESA missions, very specially those 

Application/Mission: where miniaturisation is key due to mass Contract Duration: 18 months 

budget constraints. 




Power Management and Distr. Units / Power Management 


Title: 

T604-10EP 

Study of new Power Systems architectures for LEO missions 

The availability of new, promising, re-usable and efficient power system architectures are deemed to be very importat to bring 

mass/performances/cost improvements for LEO missions. In particular, the optimisation of energy more than power efficiency 

is a key factor to have light, performant and cost effective power systems for LEO missions. 

The study will concentrate on the revision of new power conversion tecnologies (S3R, S4R, step down MPPT, step up MPPT, 

etc) to identify the most suitable power system per class of applications in LEO (fixed/pulsed load; regular, dask/dawn or 

specific orbit, etc). 

The most promisting concept(s) will be further designed in detail with the explicit aim to get a modular/re-usable system per 

class of LEO missions. 

A scaled demonstrator will be manufactured and tested to illustrate the concept(s). 

Deliverables: 

Technical Note, Demonstrator 


Application/Mission: LEO missions (not before 2015) Contract Duration: 24 months 




Power Management and Distr. Units / Power Management 

Page 143 of 227




12/Feb/09 



Title: 

03/EMA-001 

Muon Telescope 

Deliverables: 








Title: 

EMA-022 

Spacecraft Charging & Plasma Interaction Guidelines 

Deliverables: 







Page 144 of 227




12/Feb/09 


Title: 

T602-01EM 

Solar Energetic Particle Environment modelling 

Solar protons with energies of the order of 1 to 100 MeV are generated sporadically at the solar corona, and in the solar wind 

by moving interplanetary shocks. They constitute an increasingly critical hazard for the design of interplanetary missions via 

their impact on optical components, solar arrays, electronics and humans, and are a significant hazard to Earth-orbiting 

missions. This activity will create new engineering models to address future needs, in particular: - ingest new data and to take 

into account recent advances in understanding the generation mechanism; enable automatic model update and establish 

community consensus; - rather than producing only mission-integrated fluence for a given confidence level (for dose, solar 

array degradation), models will be designed to produce new types of user products, including peak flux statistics, durations of 

high flux periods, etc. (suitable for SEU rate and radiation background); - integrate databases of ion species and their fluxes 

into tools for SEU and background calculation so that past events and future scenarios can be simulated; - examine (limited) 

available data and improve physics-based shock-acceleration models to predict the expected event time profiles at non-Earth 

locations (near-Sun, Mercury, Venus, Mars,...) in order to get a realistic model of helio-radial variations to replace the (1/r^2) 

“rule of thumb” which leads to possibly over-severe environment specifications. 

Deliverables: 

Empirical model (solar proton fluence at 1AU) + update/maintaining method. Model extrapolationg + Fluxes model. Improved 

dose/SEU models (coupled with empirical). (SW IPR to ESA for operational activities (TBC)). 

Current TRL: - Target TRL: Prototype Application Need/Date: SW operational by 2008 

Application/Mission: Science, HME, EO, Telecom Contract Duration: 24 months 




Page 145 of 227




12/Feb/09 


Title: 

T602-02EM 

Radiation Effects on Advanced Technologies: Models and Software Ph.1 

This activity will evelop models in several critical areas, including:- Single Event Effects simulation and generic microdosimetry 

calculation capabilities for arbitrary materials and for modern complex (i.e. non-parallelepiped) device sensitive volumes. – 

Dramatically decrease simulation time for electron-bremsstrahlung total dose estimation in complex geometries by use of 

time-reversed Monte Carlo techniques;- New Non-Ionising Energy Loss and total dose simulation tools for future solar cells, 

glasses, CCDs, and materials;- Development of interfaces between CAD tools and Monte-Carlo tools- Extend the set of new 

Geant4 based models and engineering tools available to European space industry via the SPENVIS on-line system;- Develop 

new electromagnetic and hadronic physics models and other Geant4 kernel capabilities (e.g. geometry)Together, these new 

developments are aimed at enabling a clear increase in the use of Geant4 to a broad range of European space engineering 

applications. 

Deliverables: 

New, improved and easy-to-use radiation transport software, physics models, and auxiliary engineering tools and capabilities. 

(Open Cource Code / ESA IPR). 

Current TRL: - Target TRL: S/W release Application Need/Date: SW operational by 2008 






Title: 

Radiation Effects on Advanced Technologies: Models and Software Ph.2 

This activity will evelop models in several critical areas, including:- Single Event Effects simulation and generic microdosimetry 

calculation capabilities for arbitrary materials and for modern complex (i.e. non-parallelepiped) device sensitive volumes. – 

Dramatically decrease simulation time for electron-bremsstrahlung total dose estimation in complex geometries by use of 

time-reversed Monte Carlo techniques;- New Non-Ionising Energy Loss and total dose simulation tools for future solar cells, 

glasses, CCDs, and materials;- Development of interfaces between CAD tools and Monte-Carlo tools- Extend the set of new 

Geant4 based models and engineering tools available to European space industry via the SPENVIS on-line system;- Develop 

new electromagnetic and hadronic physics models and other Geant4 kernel capabilities (e.g. geometry)Together, these new 

developments are aimed at enabling a clear increase in the use of Geant4 to a broad range of European space engineering 

applications. 

Deliverables: 

New, improved and easy-to-use radiation transport software, physics models, and auxiliary engineering tools and capabilities. 






Page 146 of 227




12/Feb/09 


Title: 

T602-03EM 

Development of a predictive discharge numerical model on solar panels 

There have been a considerable effort from CNES to elaborate credible mechanisms to explain electrostatic discharges on 

solar array. A campaign of laboratory test is currently being performed under EMAGS-2 project lead by ESA (Photovoltaic 

Generator section). Following this testing sequence, this new activity will consist in the development of a predictive numerical 

model to simulate the effects from primary and secondary arcs on various designs solutions (network and cells). This model 

can be validated by the laboratory test results. A comparison in between laboratory conditions and real environment conditions 

could then be performed. It is foreseen to be carry out this comparison by using the so called SPIS, the TRP funded 

Spacecraft Plasma Interaction System. 

Deliverables: 

Proved numerical model. Comparison with test results. Simulation software. 


Application/Mission: EO, Telecom, Navigation Contract Duration: 24 months 





Title: 

T602-04EM 

Rapid prototyping toolkit for space environment engineering tools 

For space environmental analyses requiring the use of a spacecraft geometrical model ESA developed ESABASE as a 

general modelling and analysis environment, in the 1980's. Although the original ESABASE is aging and becoming difficult to 

maintain and use, the analysis capability is still very important both for ESA and the European space industry. As a means of 

investigating future options and problem areas, a small activity is currently developing a version of the important debris 

application of ESABASE using modern software tools and methods. The key objectives of work in this area are to work 

towards adoption of international standards for data representation and models, harmonisation with related tools and 

standards in other disciplines, and use of commercial tools and utilities. This activity will validate and apply similar methods to 

those established in the debris development to cover all the other environmental (atomic oxygen, radiation, solar UV, 

contamination) applications as well. It will move away from proprietary components and instead use available open source or 

COTs software. The result will be a replacement of ESABASE tools in various domains with open source desktop tools. 

Deliverables: 

A replacement of the ESABASE tools in the various domains with opens source desktop tools. 






Radiation Test Facilities and Engineering Tools (UPDATED) 

Page 147 of 227




12/Feb/09 


T602-05MC 

Harmonisation of Thermal and Space Environment Analysis Software and Interfaces - 

Title: 

Exchange of Thermal Models via STEP-TAS 

Following successful mapping and roadmap definition meetings with national delegations and industry on the topic of 

“Harmonisation of thermal and space environment analysis software and interfaces” in 2002, a Steering Board with very good 

cross-industry representation was established in May 2003. 

This Steering Board has unanimously adopted the ESA proposed harmonised policy for thermal and space environment 

analysis software and interfaces which provides a solid basis on which to develop further these engineering tools and 

interfaces. More specifically, the Steering Board re-emphasised the need expressed by National Delegations for robust data 

exchange for thermal models. 

Objectives of the activity are the transfer of the STEP data exchange protocol libraries to Space Thermal Software and its 

S/W implementation. Furthermore, the activity will include demonstrations, evaluation and preliminary validation involving end 

users and the developers of the Space Thermal S/W. The activity will be led by an independent consultant for the overall 

management co-ordination. 

Deliverables: 

Software 

Current TRL: 

Target TRL: 

Application Need/Date: SW operational (capability to 

exchange data / models 

S/W release 

among the different tools) 

>=2007 

Application/Mission: all ESA missions Contract Duration: 18 months 





Title: 

Space Weather Warning for Space Systems 

The activity will investigate the detailed requirements and technologies to be deployed in an eventual operational "space 

weather for spacecraft" system, then perform prototyping. This should include sensor technologies, data analysis 

infrastructure (including distributed data centre technologies) and data-model fusion. System elements will be prototyped and 

deployed. Innovative techniques for direct observation of the sun, the interplanetary medium, and near-earth conditions will be 

investigated. Coupling observations and data resources with physics-based models of the interplanetary medium, disturbance 

propagation, and models of the magnetosphere, to predict hazardous conditions will be developed. Conditions will include: 

energetic solar particle event (SPE) arrival, magnitude and time-evolution at Earth; SPE's at non-Earth locations (for 

interplanetary science missions and Aurora); geomagnetic storm enhancements of the electron radiation belt and; hot plasma 

environments. Distributed "virtual" data centre architectures will be developed. 

Deliverables: 

System design, demonstration software, future development proposals. 

Current TRL: TRL1 Target TRL: TRL3 Application Need/Date: Sw operational by 2008 





Page 148 of 227




12/Feb/09 


T602-09EE 

Title: Investigation and analysis of very high energy accelerators for radiation simulation 

Very high energy ion accelerators (E/n ~1GeV) available in Europe will be investigated in detail. Programmes for their 

characterization for use in space applications will be prepared and executed, and experiments performed to investigate 

energy-related phenomena. Facilities currently used by agencies and industry produce ions of relatively low energy, so that 

their ranges in typical components are limited. This is very unlike ions in space whose energies are so high that they can 

penetrate at least several cm of material. As a result there are many “range effects” where ions stopping in sensitive volumes 

deposit more than expected while others not reaching sensitive volumes do not contribute. Resulting effects calculations 

based on such data are incorrect and may explain discrepancies between in-orbit experience and pre-flight estimates. In 

addition, future manned programmes and increasing investigation of biological effects necessitates access to such machines. 

In addition to the detailed experimental investigation of these effects, detailed modelling of the processes will be undertaken, 

and comparisons made with results from “low energy” accelerators). The activity includes: 1. Analysis of existing and required 

facilities. 2. Experiments on effects in sub-100nm devices and simulation of beam interactions at sensitive node level. 3. 

Establishment and demonstration of new methods of analysis. 4. Development proposals. 

Deliverables: 

Technical notes. Test set-up's, simulation codes, results of the experimental activity. 






Radiation Test Facilities & Engineering Tools 


Title: 

Rapid Reverse Monte Carlo and Ion Physics for Dose and SEE 

Recent consultations with industry, the harmonisation process, project applications and results of R&D activities indicate the 

need for specific physical attributes in radiation effects simulations In particular, a “reverse” (adjoint) Monte Carlo simulation 

for rapid, highly accurate total dose calculations is lacking in Europe and has been identified as a key simulation improvement 

capable of dramatically reducing mass and design margins. Likewise the analyses of Single Event Effects (SEE) and 

Non-Ionising Energy Loss (NIEL) are becoming increasingly critical for a broad range of mission domains and have also been 

identified as priorities for simulation improvement. The underlying physics models utilised in present tools need to be updated 

and validated for engineering applications. 

This activity will focus on detailed radiation interaction physics modelling, including both theoretical and data-driven 

approaches, for incident particles, materials, and technologies typically encountered in a broad range of missions. The 

development shall include both prompt interactions (hadronic (~ion) and electromagnetic (e--) processing occurring at the 

site of the particle interaction) as well as effects at the semiconductor level (e.g. charge collection mechanisms). The 

resulting software shall be based on Object-Oriented technologies and implemented in the Geant4 particle transport toolkit, 

ensuring their availability to industrial tools. Validation of the models shall be carried out by rigorous comparisons to existing or 

specially generated experimental accelerator data, other Monte Carlo codes and/or analytical methods. 

Deliverables: 

New radiation interaction physics models, aimed specifically at shielding and component engineering applications and 

implemented in the Geant4 particle transport toolkit 


Application/Mission: Broad range of missions Contract Duration: 24 months (Ph1) 

SW Clause : Open Source Code Dossier0 Ref.: T-19; T-7765 



Page 149 of 227




12/Feb/09 


Title: 

T609-14QC 

General Spacecraft Environment Monitor 

Deliverables: 







Page 150 of 227




12/Feb/09 



Title: 

MME-002 

Integrated-Optics Laser gyro Technology (IOLG) Ph.2B 

Gyros are essential sensors for inertial guidance and control. A new, very interesting gyro configuration is the 

Integrated-Optics Laser Gyro (IOLG) as proposed by Politecnico di Bari and U.Glasgow. The IOLG offers many potential 

advantages by integrating all the components on a single GaAs substrate. It comprises of a multiple quantum-well (MQW) 

microring laser, a coupled output optical waveguide with push-pull electro-optic modulator, a Y junction and a wide band 

photodetector all fabricated on the one GaAs substrate. The objective of the following activity is assessing the feasibility 

through breadboarding of an IOLG and test. 

Deliverables: 

Breadboard 

Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: 







Title: 

Novel Optical Gyro Concept 

Initial TRP conceptual studies and breadboarding activities for an integrated-optical gyro (IOLG) sensor chip, integrating 

waveguides, SOA amplifiers, ring resonator, optical isolators, modulator, etc. with (external) laser diodes have shown the 

potential of novel opto-electronics techniques to provide novel gyro concepts of low/medium performance. Building upon this 

initial R&D study, the proposed activity intends to further the development effort towards novel gyro concepts for space 

applications. The following tasks are envisaged: critical evaluation of the IOLG concept/ initial results, trade-off among 

different novel concepts employing optical/photonic technology, e.g. : IOLG, Photonic crystals, quantum interferometry, etc. 

This work will be implemented in two phases, the first covering trade-offs among different novel concepts, followed by 

breadboarding of the most promising concept(s). The technology readiness level of this activity is TRL 3. 

Deliverables: 

BreadBoard 


Application/Mission: EO and Science Contract Duration: 24 months 




Page 151 of 227




12/Feb/09 


Title: 

T603-03ES 

Robust LPV Gain Scheduling Techniques for Space Applications 

Gain-scheduling is perhaps one of the most popular approaches to non-linear control design and has been widely and 

successfully applied in fields ranging from aerospace to process control. The traditional control design procedure consists of 

decomposing a non-linear time-varying problem into a number (operating conditions) of linear time invariant sub-problems. To 

verify that the closed-loop system behaves as expected and required between the operating conditions, extensive simulations 

and analysis are needed. A recent gain scheduling method, so-called Linear Parameter Varying (LPV) technique, address the 

issue of system parametrisation and directly offer an optimal solution. As the intermediate step of linearization and stationary 

control design is suppressed, the design verification effort is drastically reduced. The aim of the proposed activity is to 

evaluate, benchmark and demonstrate the benefits in validation effort of LPV gain scheduling techniques when applied to the 

design of robust controllers for uncertain time-varying systems. In addition, robust LPV-based controller design procedures 

and tool(s) that interface with industrial requirements will be developed. The expected benefits is a drastic reduction in control 

design verification effort for non-linear time-varying systems. 

Deliverables: 

Robust LPV gain-scheduled control design toolbox including benchmark models and documentation (technical data package, 

summary report and abstract). 

Current TRL: 


- 

version 




Roadmap: N/A 



Title: 

Robust Model Predictive Control (MPC) for Space Constrained Systems 

Model Predictive Control (MPC) is a widely used and well accepted controller design method in the process industry. The 

most appealing feature of this type of control is its ability to cope with constrained systems. Robust formulation of MPC 

problems which take into account model uncertainties are also available, and are subject of intensive current research. 

Furthermore, MPC can be combined with other control techniques such as H2/Hinfinity. Finally, the dramatically increasing 

available computer power give new interest in such computer intensive techniques as they can easily take into account 

actuator limitations, non-linearities or non-stationarity. The aim of the proposed activity is to evaluate, benchmark and 

demonstrate the benefits of robust Model Predictive Control on critical space mission scenarios, such as time-bounded 

manoeuvres, saturated control and terminal guidance that are difficult to address with classical techniques. In addition, 

real-time performance (CPU, memory, etc.) will be assessed, and robust MPC design procedures and tool(s) that interface 

with industrial requirements will be developed. 

Deliverables: 

Robust MPC control design toolbox including benchmark models and documentation (technical data package, summary 

report, and abstract). 

Current TRL: 


TRL1 

version 






Page 152 of 227




12/Feb/09 


Title: 

T603-10ES 

MEMS Rate Sensor 

The activity shall design and develop a 3 axis 'low accuracy' (5 deg/hr bias stability) MEMS based rate sensor suitable for use 

as a primary sensor on small sats, as an FDIR and acquisition sensor on EO and science missions and as a backup sensor 

for Telecoms applications. The unit shall have a target mass of less than 600g and a power consumption of less than 4 watts. 

A Demonstrator shall be breaboarded and tested to a level sufficient to demonstrate the packaging concept, performances, 

mass and power and to provide confidence in the environmental (vibration, TV and radiation) survivability. The activity may be 

continued in an optional program. Preliminary Specifications for the Flight System will be included in this tender. 

Deliverables: 

Breaboard and reports. 







Title: 

Attitude Determination Tailored to Multiple Heads Star Tracker 

Star tracker partial or total occultation or blinding by the Earth or the Sun can prevent stellar information from being available. 

The MHST is minded as a unit where a unique computer can manage data from different Optical Heads (OH), providing better 

attitude restitution through sensor fusion and managing occultation. It follows that the use of such a unit leads to a design of 

an innovative FDIR at unit and AOCS subsystem level and requires a greater interaction between AOCS designer and unit 

supplier to achieve an optimal AOCS design for a given mission. The proposed activity shall support initial development effort 

at unit and AOCS level prior practical implementation within future missions. Constraints will be identified and performance 

analysed and validated, including the case of a gyroless AOCS. 

Deliverables: 

Detailed documentation and SW model. (Open Source Code at system level / Operational SW at subsystem level) 

Current TRL: TRL1 Target TRL: Prototype Application Need/Date: SW operational >=2007 





Page 153 of 227




12/Feb/09 


Title: 

T603-13ES 

Modern Control Techniques Applied to Satellite FDIR 

Although the currently implemented algorithms are responding rather adequately to large class of the mission requirements, 

advanced new FDIR techniques recently introduced through modern control theory need to be further explored. From a cost 

perspective it is not manageable to have everywhere fault redundant hardware and complex and costly ground operation 

intervention. Therefore it is more efficient to study the analytic model based on-line fault monitoring techniques that use 

measured data fed into a detection filter responding with a threshold signal in the face system anomalies. 

The design of such FDI filters can be done using estimation and filtering techniques such as Kalman filters. In many cases 

residual generation becomes problematic in off-nominal conditions leading to a high occurrence of false alarms which can lead 

to unnecessary complex operational interventions. 

Therefore robust filtering techniques originating from the as H-infinity, mu-, LMI as well as LPV theories provide a well founded 

framework for the development of future FDIR systems to better respond to unforeseen situations. The development of FDI 

filters using these methods need to be investigated with the overall objective of enhancing the detection and isolation strategy 

in terms of robustness. 

Another important field that needs to be investigated is the interaction and cascading of multiple failure modes and models. 

The proposed activity shall further include the implementation of selected algorithms. The evaluation of the associated 

performances and robustness shall also be combined with trade-off analysis conducted within common and unambiguous 

testing scenario. Relevant test cases worth to be investigated are Lisa Pathfinder, Lisa and Gaia, agile and accuracy pointing 

satellites, Darwin formation flying facing thruster failures. Under that context, the definition of standardised benchmark 

developed typically under Matlab and Stateflow environment is also expected. 

Deliverables: 

Documentation and software. 






TRP Reference: T603-30EC 

Title: 

Sensor on a Chip Feasibility study and Avionics Evolution 

The technological feasibility of producing an entire sensor on a chip (i.e. optics, detector, processing and digital interface) shall 

be investigated using digital sun sensor, star tracker and navigation or descent and landing cameras as examples. The 

feasibility investigation shall cover the integration of imaging, processing and data interface functions on the same silicon chip, 

the production and performance of useable optics with MEMS technology (e.g. wafer stacking and bonding for 3-D integration 

of MEMS optical systems with the electrical functions) and the integration of such an assembly with power conditioning 

electronics within a hybrid. Key technologies will be demonstrated by production and test of a dedicated prototype (e.g. of an 

optical system). 

The system aspects surrounding the use in space of a sensor on a chip concept shall be investigated at both sensor unit and 

system level. These investigations shall cover the packaging of the 'sensor on chip', the thermal implications of such a 

concept for externally mounted sensors, power supply options, mounting and alignment problems and data interface methods 

and techniques. 

With the results of the technology investigations, unit level studies and system impact studies, a development plan shall be 

written for AOCS sensors on a chip covering sun sensor, star tracker and navigation camera and descent and landing camera 

applications, giving realistic target requirements and highlighting all critical areas of outstanding technology devlopment. 

Deliverables: 







Page 154 of 227




12/Feb/09 


Title: 

T603-36EC 

Future technology studies for APS Star Trackers 

The contractor shall investigate potential new star trackers technologies that may be of use in the future to further reduce the 

cost while improving the robustness (dynamic conditions, straylight/blinding, false stars and radiation) and functionalities 

(sensing of moon or earth/asteroid/planet position for example, direct entry to tracking). These shall include the mandatory 

consideration of LCMS APS detector by Cypress (Fillfactory) -designed specifically for this purpose-, baffle construction 

materials, plastic lenses, black coatings, alternative construction techniques, single chip electronics (all processing in the 

same ASIC/FPGA), and wireless communication. In addition, the contractor shall be expected to propose further new 

technologies themselves. Technical evaluations shall be performed on each technology considered and all promising 

technologies breadboarded for further, more detailed, evaluation and, where appropriate, development plans to bring the 

technology to the correct maturity level shall be drawn up. The emphasis shall be on production cost lowering from a 

continued reduction of the number of components, an easing of assembly, automated testing and cheaper construction 

techniques. 

Deliverables: 

Breadboards. 






Page 155 of 227




12/Feb/09 


Title: 

T603-38EC 

Enhanced CCD Star Tracker 

Since the introduction of the Autonomous Star Trackers in the 1990s, their popularity and use on space missions has steadily 

increased until today were these units are used on all classes of mission and are becoming the sensor of choice for almost all 

missions. 

The European space industry has been at the forefront of this technology development, indeed in 2000/2001 there were 

nearly 15 European companies developing or selling star trackers. This amount of competition was unsustainable and so, at a 

harmonisation meeting in 2001, it was decided to no longer support the development of CCD based star trackers and 

concentrate instead on targeted developments to produce the next generation of star trackers based on APS detectors, these 

having the potential to allow lighter, more compact and cheaper Star Trackers that simultaneously offered higher robustness. 

Industry was left to support itself for the CCD star trackers. This policy had the desired effect of reducing the number of 

European Star Tracker manufacturers dramatically while simultaneously forcing manufacturers to improve their units and 

reduce prices. Today there are 5 star tracker suppliers in Europe, each of whom have survived by being highly competitive on 

the world stage. With a manageable number of suppliers, a large proportion of each of these companies business now coming 

from outside Europe and there still being an expected overlap of 2 to 4 years between CCD based and APS based star 

tracker supply it is now time to resume providing support to maintain and improve the existing CCD based product lines. 

The Terma HE-5AS STR has been selected for Cryosat, Aeolus and the LPF missions. Following the loss of Cryosat at launch 

it is also expected to fly on Cryosat 2. Work performed now to secure the STR and improve its robustness, reliability and 

qualification status will therefore have a near term beneficial effect on several ESA missions. 

This policy was clearly expressed in ESA/IPC(2005)70 rev.1, calling for product improvements of CCD Star Tracker , mainly 

for recurring platforms. According to the outcomes of the 2005 Harmonisation Roadmap on AOCS Sensors and Actuators, the 

present activity aims at: ensuring the availability of the HE-5AS to ESA projects for at least the next 3 years; improving the 

robustness and ease of use of the HE-5AS within the scope of the existing electrical design limitations; improving the 

straylight and thermal design and the understanding of their interactions and dependencies on the s/c system and orbital 

environment. This will result in the following main three tasks: 1. Software improvements for Robustness and Reliability; 2. 

Component obsolescence and Europeanisation; 3. System level analysis and improvements. This measure is implemented in 

line with IPC(2005)30, rev. 1 (Formal review of the geographical distribution of contracts), calling for a DG's additional effort to 

improve the geographical return of certain countries, including Denmark. 

Deliverables: 

In-flight data analysis report; design improvements and trade off report; improved SW design report; SW Test 

plan/procedures/report 

Current TRL: 

TRL3-4 Target TRL: Application Need/Date: TRL8 (in-flight demo on 

TRL5-6 

Cryosat-2) by 2009 


T-25, T26, T-27, T-29, T-30, 


T-33, T-34, T-965 


Conclusions: ESA/IPC(2005)70 rev.1 


Page 156 of 227




12/Feb/09 


Title: 

T603-41EC 

System study to define European accelerometer development 

A number of space applications, such launchers, transfer vehicles, re-entry vehicles, landers, rovers, not only require angular 

rate, but also acceleration measurements. These applications require an Inertial Measurement Unit (IMU), combining gyro and 

accelerometers measurements, in order to provide these data to the spacecraft and rely today on US accelerometers. 

The development of a European accelerometer is highly desirable to guarantee non-dependence and better master IMU 

design and performance. A candidate for this accelerometer is MEMS technology, which now reached the level of maturity 

and reliability that makes it eligible for space applications. 

The proposed activity shall cover the first step before initiating such a development, which is to identify the accelerometer 

needs for space applications, both from a technical feasability and a market perspective. This technical feasability study shall 

be supported by simulations. 

The following tasks are expected: 

- Identification of accelerometer needs 

- Review of accelerometer market and trends 

- IMU performance study 

- Accelerometer preliminary specification, design and development plan 

The activity shall thus lead to select the performance grade of European accelerometer to be developed in priority, assess the 

feasibility with MEMS technology or another technology, and provide all inputs to make decision towards the development 

step. 

Deliverables: 

Accelerometer need for Space Applications, Review of accelerometer market and trends, IMU Performance Study and IMU 

algorithms, Simulation test plan and results, Accelerometer Technical Specification for Space Applications, Accelerometer 

Preliminary Design and Development Plan. 


Exploration (landers, re-entry vehicles, 


rovers,..) 



AOCS Sensors, AOCS Actuators 


Page 157 of 227




12/Feb/09 



Title: 

ETP-029 

O/B SAR Calibration 

Deliverables: 







TRP Reference: ETT-059 

Title: 

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. 

Deliverables: 

SW breadboard 


Application/Mission: Navigation systems Contract Duration: 18 months 




Page 158 of 227




12/Feb/09 


Title: 

T603-14ET 

Frequency Flexible Synthesizer Breadboard suitable for O/B TTC 

Deliverables: 








Title: 

Frequency Flexible Synthesizer Breadboard suitable for O/B TTC: additional work 

The overall objective of this activity is to analyse, design and breadboard a Frequency Flexible Synthesiser for space 

application. The S-band TT&C transponders for Near Earth applications represent the main target, but it can be suitable also 

for other applications for instance the X-band TT&C Transponders and the downlink Telemetry Transmitters.The Frequency 

Flexible Synthesiser shall allow programming the transponder for different RF channels. This can be applied on ground 

(before launch), but using a proper command in-flight as well. In-flight frequency agility becomes very useful in particular for 

spacecraft constellations, multiple launch solutions (to control in frequency diversity several spacecrafts during LEOP phase) 

and for secure link applications. This activity shall include the following main technical phases: architectural definition of the 

overall unit with particular emphasis on the frequency plan issues; design, breadboarding and testing of the frequency 

synthesiser; and design development plan (up to the flight model) including all the indications in terms of flight technologies, 

risk, schedule and costs. 

Deliverables: 







Page 159 of 227




12/Feb/09 


Title: 

T603-29ET 

Telecommand & Telemetry System Security 

This design study will include the following areas: 

1. Identification and evaluation of threats and vulnerabilities on current ESA Spacecraft Telecommand and Telemetry systems 

with an end-to-end perspective but with particular emphasis on the Space link and considering the particulars of various ESA 

missions, e.g. Science, Earth Observation, Manned Space flight, Navigation, Telecommunications. 

2. Exploration and definition of technical concepts for security measures at the relevant CCSDS protocol layers to guarantee 

adequate levels of availability, authentication, confidentiality, integrity and non-repudiation; particular emphasis shall be given 

to: physical and coding layers where current ESA/ECSS standards make no provision for Security and denial-of-service 

(jamming) attacks or traffic analysis are a possibility; application, packet, segment and transfer layers for the definition of 

authentication and encryption protocols where generic concepts have been documented by CCSDS but not standardised; 

particular implementations performed by ESA and other Agencies but either outdated or constrained by the particular mission 

and therefore, inadequate for future missions; Consideration of Operational aspects, e.g. key management; Consideration of 

Ground Networking aspects, e.g. outsourcing. 

3. Selection and detailed study for a case-study mission, e.g. Earth Observation. 

4. Derivation of security requirements for equipments and facilities on both Space and Ground Segments. 

Deliverables: 

Technical Notes 


Application/Mission: all programs Contract Duration: 15 months 





Title: 

Linearity Assessement of GaN Technology 

GaN offers the potential for realising state of art power performance. Previous ESA work programmes have shown that there 

is a requirement to investigate novel device structures to further enhance transistor performance. The aim of this activity is to 

optimise the GaN transistor structure (both physically and from a materials growth perspective) to achieve higher power 

performance through the introduction of device architectures known to enhance performance such as field plates, double 

hetero-junction channels, recess structures, graded channel doping and new vertical transistor structures. In particular, efforts 

will be undertaken to investigate the device and technology trade-off’s required to achieve simultaneous high linearity and high 

power added efficiency performance, along with undertaking an assessment of the introduction of the proposed techniques for 

improvement of device reliability and manufacturability. This work is an important requirement for future multi-carrier 

telecommunications transponders and if successful will allow world class device performance with increased power added 

efficiency and linear output power to be achieved compared with GaAs pHEMT technology. 

Deliverables: 

Technical notes, device samples, technology exploitation plan. 


Improved performance power transistors 

Application/Mission: for use in EO, Telecomms, Navigation Contract Duration: 24 months 

and Science payloads 




Page 160 of 227




12/Feb/09 


T603-32ET 

Power/Efficiency flexibility of spaceborne SSPA using Doherty scheme associated to a 

Title: 

linearizer 

The Doherty configuration is an advanced design concept of SSPA which can provide instantaneous flat efficiency for a wide 

range of input / power range. Very interesting results have been obtained for the base station market where extreme 

requirements for linearity/power and efficiency are rewarded. This activity is aiming at demonstrating the applicability of this 

concept to spaceborne applications by using the most advanced semiconductor technologies allowing to focus on very high 

constant efficiency. The linearity performance in a range of 3 to 6dB of output power flexibility will represent a key point, and 

linearization schemes will be addressed to assure sufficient performance. 

Deliverables: 

RF amplifiers demonstrators. Standard design documentation. Test reports. Associated linearization scheme. Standard design 

documentation. Test reports. 







Title: 

Solid State Isolators based on GaN technology 

This activity shall first concentrate on identifying ways to develop RF/microwave high power isolators based on solid state 

semiconductor GaN technology. In a second part, the demonstration of feasibility of isolators for space borne applications will 

be provided by designing and testing high power isolators aiming at shrinking both size/volume and mass of current ferrite 

based isolators used in SSPA equipments. 

Deliverables: 

Isolator breadboard. Design documentation. Test reports. 


Application/Mission: Telecom, EO, Navigation Contract Duration: 24 months 





Page 161 of 227




12/Feb/09 


Title: 

T603-37ET 

Future Multipurpose TT&C Systems & Techniques 

The objective of this activity is to investigate, analyse and propose new TT&C Communication Systems looking to the overall 

end-to-end perspective for a broad range of possible missions (e.g. from Near Earth to Deep Space). The target is to devise a 

flexible tool-kit of solutions for both the on-board and ground system which can be embedded in highly reconfigurable 

hardware platform to adapt to the different mission needs. This approach will avoid the use of expensive ad-hoc solutions to 

cope with the different missions and will be leveraging on the advances in signal processing techniques and technologies. 

Stemming from the requirements envisaged for future TT&C applications (and for the different application fields: Science, 

Earth Observation, Navigation and Telecommunication), this activity shall investigate a flexible yet robust solution for TT&C 

tackling aspects such as: spectrum congestion (interference, spectral efficiency, frequency reuse...), on-board power 

efficiency (nonlinearity countermeasures), link security, mission adaptability etc.... 

Deliverables: 

Analysis of curent/future application scenarios/req. Broad review of possible comm. link + ranging approaches. Identification 

of ref. scenarios, overall end-to-end perform. analysis + trade-off. Proposed solution benchmarking current approach. 







Title: 

Design and Synthesis of a New Class of Receiver Filters 

With the increasing complexity of satellite payloads there is increased demand of miniaturized high performance receiver 

filters. This includes waveguide and planar filters. Current synthesis techniques assume close to lossless (high Q) networks 

which forces the filter to be reflective. If this restriction is removed a new degree of freedom is achieved and very high 

performance filter transfer functions can be acomplised utilising very low Q resonators. Initial estimations show that the for 

same size significant improved flatness and selectivity can be achieved over state of the art predistorted topologies. 

Deliverables: 

Circuit design tool and breadboard demonstrators 







Page 162 of 227




12/Feb/09 


T603-40ET 

Evaluation and validation of electromagnetic software, test facilities and test standards 

Title: 

in Europe to predict and test RF breakdown and passive intermodulation (PIM) 

This activity shall start with a survey among the European Space Industry to identify the European needs in terms of 

prediction/simulation tools to avoid RF breakdown and PIM in space hardware. The next step of the activity is to propose a 

number of existing and available software packages best matching these requirements and recommend one of them as 

baseline in Europe for future software developments in the field. The selection shall be done comparing prediction data using 

the proposed packages with test results on a number of RF passive devices defined during the first phase of the study. 

To achieve this, the contractor shall also identify test facilities in Europe technically capable to perform high power RF tests 

(Power handling, Multipactor and Corona) and passive intermodulation (PIM) on space hardware. A number of waveguide test 

samples shall be produced and carried to the different test sites for the evaluation of their facilities and test procedures. This 

activity has been proposed in the frame of the “power RF measurements” document, presented by ESA during the 

Harmonization meetings in 2004. 

Deliverables: 

Golden test samples for each frequency band. Documentation. 






Microwave Power Breakdown Modelling and Characterisation 

Page 163 of 227




12/Feb/09 



Title: 

03/EEA-001 

Quasi Optical Modelling 

Deliverables: 








Title: 

03/EEE-001 

Development of low frequency probes 

Deliverables: 








Title: 

03/EEE-002 

Instrumentation for injecting current shaped waveforms 

Deliverables: 







Page 164 of 227




12/Feb/09 


Title: 

EEE-006 

Novel Techniques For General Antenna Characterisation In The Time Domain 

Beside frequency domain measurements allowing characterizing the device under test in its operational frequency domain, 

time domain measurements techniques are well known to provide additional information on the mismatches seen by a signal 

propagating in a guided circuit. The time domain performances dealing with large frequency bandwidth, this technique 

provides more qualitative measurements well suited for a diagnostic purpose. 

This activity deals with time domain measurement techniques to perform fast antenna radiation diagnostic. Time domain 

allows having in one acquisition a full signature of the antenna behavior which can be compared at different stages of 

environmental test sequence to identify potential hardware damage. This technique is particularly well suited as time gating 

allow rejecting parasitic reflections of the radiated signal and make possible measurements in reverberant situation (just 

before or after a Thermal vacuum test or a vibration test as compared to an ideal situation in an anechoic chamber). Reducing 

test time and making possible in-situ measurements is of particular relevance for all kind of antennas used for Earth 

Observation, telecommunication and science. The interest is reinforced when multiple beams are required. 

The activity will address theoretical aspects together with implementation constraints to end-up with a demonstration phase to 

be performed on an existing antenna. 

Deliverables: 

Technical note on time domain interest for radiative measurements. 

Test procedure 

Test report. 

Evaluation report on time domain for radiative measurements 


Application/Mission: All missions with complex antennas Contract Duration: 18 months 




TRP Reference: EEE-008 

Title: 

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. 

Deliverables: 

Technical note (characterisation of shielding performance and transfer impedance of target materials; development of 

measurement techniques). Analytical tools for EMC performance evaluation. 


Application/Mission: All missions with complex antennas Contract Duration: 18 months 




Page 165 of 227




12/Feb/09 


ETM-192 / T-M-QCT-06 

Design of photonic crystals front-end (Photonic crystals: Material selection and 

Title: 

fabrication) 

Photonic Band Gap technology is a breakthrough, mainly due to their ability to guide and control efficiently electromagnetic 

waves. As most fundamental components shall be soon available in PBG technology, a fully integrated receiver incorporating 

antenna, mixer, waveguides, LO injection and filtering in one unit could be developed in order to take full advantage of this 

technology. True integration of passive and active components can now begin to materialize using PBG technology leading 

towards the development of a complete system. 

In parallel, a PBG component in an ideal concept would be fully dynamic, reconfigurable and multifunctional and the 

association of PBG with other enabling technologies such as MST (Micro-Systems Technologies) and more specifically RF 

MEMS may allow completely novel EBG concepts and designs. Such a concept is clearly visionary, but the combination of RF 

MEMS with novel periodic structures such as PBG my allow prototyping (and probably patenting) innovative functional 

concepts to demonstrate adjustability of electromagnetic crystals. This would represent a fundamental change in the way 

systems are being designed today. 

Deliverables: 

Design documentation. 


Application/Mission: Imaging Instruments EO / SCI Contract Duration: 18 months 





Title: 

Secured link for TT&C antennas design phase 

This activity deals with the design of antennas for secure TT&C links using adaptive (including switching) antenna techniques. 

The activity shall consider identification of likely threat scenarios, trade-offs of adaptive antenna concepts, architectures and 

design, ground segment and other infrastructure impacts/requirements, interferer location techniques and adaptive antenna 

control including software and hardware requirements. The output of this activity shall be the design of the adaptive antenna 

system(s) together with analyses to investigate the antenna expected performance. Development plan for future hardware 

development. 

Deliverables: 

Adaptive antenna system(s) design and performances analysis. Future HW development plan. 


Application/Mission: EO, Telecom Contract Duration: 12 months 




Page 166 of 227




12/Feb/09 


Title: 

T603-28EE 

RCS Quiet Zone Characterization at Millimetre Wavelengths 

The technique has been used at ESTEC from some time and has been verified against the traditional and more cumbersome 

technique. What is not known is how far up in frequency the RCS technique is applicable with today's technology. While radar 

system are known to exist at up to 100 GHz, can the present "traditional" mode of RCS quiet zone determination be applied 

The question of the practical limit must be addressed in addition to the question of can a similar technique be used at higher 

millimetre wavelength frequencies. The application of innovative thinking is required here to be able to verify range 

performance where mechanism and mechanical tolerances are in the same order of magnitude as the electrical wavelength. 

It should be noted that in the near future the ESTEC CPTR will increase its range of operation to 100 GHz while the smaller 

CATR will operate up to 300 GHz, in line with present and planned Science and Earth Observation missions as well as 

potential use in QV band telecommunications. 

Deliverables: 

Technical note, including the way forward to characterizing antenna test facility quiet zone quality. 


Application/Mission: EO, Science Contract Duration: 12 months 





Title: 

Advanced System Level Conducted Emission Analysis and Simulation for EMC 

The scope of this activity is to generate a high fidelity system noise model, based on time domain equipment measurements in 

both differential and common mode. The exploitation of time domain measurements will improve the results of previous similar 

activities, reliant on frequency domain data, where the phase information was not accounted for by definition. The system 

complexity will be managed by breaking down of the relevant elements at the various degrees of detail available. The 

equivalent noise model shall encompass several features: treatment of shielded and unshielded Non Uniform Multi-conductor 

Transmission Lines; non-linear Components; statistical treatment of the system's uncertainties; and Signal Processing 

capabilities addressing noise, modulations and Power Spectral Density. The system noise model will be demonstrated against 

measurements on selected case studies and shall prove the ability to handle any relevant conducted emission and 

susceptibility. 

Deliverables: 

Technical note. System noise model. 







Page 167 of 227




12/Feb/09 


Title: 

T605-13EE 

Advanced System Level Radiated Noise Analysis and Simulation for EMC 

The objective of this activity is to create a numerical tool to simulate radiated electromagnetic field in low Q cavities and 

examine radiated susceptibility at unit/subsystem and system level by means of hybrid methods (full wave solvers and 

transmission line theory) in time and/or frequency domain. Emphasis shall be given to the representation of the 

electromagnetic field where the interference actually occurs, i.e. inside the spacecraft.The following features will be examined: 

the randomness of the system, i.e. random field from sources in a closed environment, will be treated with the stochastic 

treatment of Maxwell equations; characterisation of the field-to-wire-coupling onto a non-uniform multi-conductor transmission 

line. In order to account for the uncertainties of any complex system that lead to severe fluctuations of the electromagnetic 

coupling, a probabilistic approach shall be implemented. The system noise model will be validated against measurements on 

selected case studies. 

Deliverables: 

Technical report, test mock-up and demonstration SW macros 








Title: European Antenna Modelling Component Library - Step 2 

Following the successful activity on the European Antenna Modelling Library for Telecommunication applications, this activity 

will to continue along the path established by extending the Library to cover new requirements of by Earth Observation, 

Science and Telecommunication missions. Typical needs include: refinement of reflector antenna analysis tools (for very high 

frequency and quasi-optics instruments), innovative methods for array design (for SAR's), fast parametric modelling of small 

antennas (to improve speed and accuracy) and improvement of antenna interaction models (distributed antennas, out-of-band 

response), adaptation of modelling tools for the use as diagnostic means in AIT/AIV campaign. Furthermore, in order to reach 

these objective within the multi-tool environment of the Library the activity will also further consolidate the Electromagnetic 

Data Exchange standard. 

Further steps are foreseen to cover further requirements of the different type of missions not compatible with the current 

budget allocation and to further consolidate the most innovative developments. 

Electromagnetic modelling tools are a key factor in the timely and cost effective development of satellite antennas. The 

availability of well-established and validated tools has been proven to reduce costs and time to delivery by as much as 30%. 

Dedicated electromagnetic modelling tools are absolutely necessary for the successful development of European space 

antenna technology. Yet the expenditure in this area (about 5M over the past 10 years) has been small compared to the costs 

for breadboarding and mock-up testing of antennas on even a single satellite, and the potential for improvement has been 

exploited in a very limited way significantly reducing the benefit for European Space Industry. 

With direct relevance to Dossier 0 requirements, this proposal was elaborated and justified within the R&D dossier on Antenna 

Modelling and Tools Validation together with experts from user directorates who have approved and supported it as relevant 

and important for their future programmes. This action also fits the objectives of the reflector antenna harmonisation in the 

Telecom area. 

Deliverables: 

New antenna analysis modules for the European Antenna Modelling Library, using innovative techniques in advanced space 

antenna design software tools 

Current TRL: 

Target TRL: S/W Application Need/Date: SW modules operational by 

- 

modules 

2008-2009 

release 

All missions using antennas (reflector, 


arrays, TT&C and others) 



Telecommunication Antennas Reflectors 


Page 168 of 227




12/Feb/09 



Title: 

EMM-004 

Virtual spacecraft design (Ph.1&2) 

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. 

The approach is to develop a digital or “virtual” model of the spacecraft already in early phase B to support the specification 

and definition activities, and to evolve it to support design, AIT and operations phases. The programme of work shall 

concentrate on specific aspects of the development process, where experience shows substantial resources and risks are 

involved and where the virtual model technology can provide significant added value. Collaborative aspects shall be 

considered. An area of focus will be the AIT process, and its links to both the detailed design and the mission operation 

phases. 

These activities will be implemented in three steps: definition, implementation and demonstration. 

This innovative approach is required to increase the cost-effectiveness of the development process, because it helps 

optimising the design at system level, increasing the coherence between analysis, design, testing and operations, and 

contributes to the reduction of the number of design iteration loops, test models and testing. In particular, improvements are 

expected in the following areas: 

• Design trade-offs at system level 

• Analysis of system operability issues 

• Assessment of engineering margins 

• Coherence between analysis and testing 

• Preparation and execution of AIT 

• Transition from AIT to operations 

This is necessary to be able to cope with the ever-increasing complexity of space missions under tight resource and time 

constraints and to boost European industrial competitiveness in the global market. 

The innovative aspect consists in the way that the whole project is conceived, in a collaborative perspective, using digital 

models of the system as integral part of the design and verifications process, in full coherence with the use of hardware 

models, thereby optimising cost and schedule, as well in the way for the involved parties (ESA, prime and subcontractors) to 

interact with each other. 

The following steps are foreseen: 

• Definition of an advanced process based on Virtual design technology 

• Procure and deploy the necessary collaborative tools and applications covering design and AIT phases for multi-partners 

projects, with particular emphasis on: 

- Model/Simulation-Based design 

- Virtual Mock-Up 

- Virtual AIT 

• Demonstrate the benefits and added value of the results by applying the approach in real project(s). 

Deliverables: 

VSD process definition; functional simulator and digital mock-up and associated documentation, test procedures; lessons 

learnt and recommendations to projects. (Open source code to be delivered in agreement with GCC clause 42.4) 

Current TRL: 

- 

Target TRL: 

Project 

demonstrat 

ed in real 

project 


Application/Mission: All satellite projects Contract Duration: 24 months 




SW process operational 

>=2008 

Page 169 of 227




12/Feb/09 


T504-15SR 

Technology reference and proof of concept for a space based Automated Identification 

Title: 

System for maritime security 

The universal shipborne Automatic Identification System has been recently introduced by the IMO as a system for enhancing 

the safety of marine traffic at sea. Transmitters onboard the ships send signals which are received by other ships and 

onshore. The proposed activity is a technology reference and proof-of concept action aimed at analysing the feasibility of a 

space based system to collect the signals and thereby monitor ship traffic. 

The activity includes; 

• The analysis of the transmitted signal and its characteristics a range of orbit altitudes. 

• The analysis of the signal environment at satellite altitude for several conditions of ship traffic (number and relative location 

of transmitting ships). 

• The definition of satellite receiving systems and the establishment of performance models for quick trade-off a receiving 

system level and for insertion in the end-to-end performance simulator. 

• The definition of satellite concepts to accommodate the various receiving systems. 

• The set-up of an end-to-end simulation model including signal at transmission, propagation, reception at satellite level, 

considering relevant platform characteristics and orbit parameters. 

• The trade-off of options, orbit, satellite, receiving systems supported by simulations. 

• The selection of concepts and the allocation of performance requirements to the elements of the receiving chain. 

• The verification of the performance allocation by simulations with the end-to-end performance simulator. 

• The specification of the key technologies. 

• The outline of the plan leading to TRL-5 and further TRL-9. 

Deliverables: 

Report on Space-Based AIS implementation study 

Current TRL: TRL0 Target TRL: TRL3 Application Need/Date: TRL5 by end 2008 

Marine surveillance, EO (DCS), Security 

Application/Mission: demonstrators as ESA/C(2005)130, rev. Contract Duration: 

3 (signal intelligence). 




Roadmap: N/A 

12 months 

TRP Reference: T605-05AC 

Title: 

Grid-based distributed concurrent design (GDCD) 

The advantages of applying the Concurrent Engineering (CE) approach to the assessment and conceptual design of future 

space missions has been widely demonstrated during last years. The next step would be to remove the constraint of a 

centralized architecture (i.e. all specialists sitting physically in the same location). This activity proposes to develop a 

distributed model paradigm because the concept of Distributed Concurrent Design performed in a "Virtual Facility", i.e. design 

activities carried out concurrently but using geographically distributed resources, appears to be a natural evolution of the 

Design Centres concept. Grid technology will be the basis for the creation of such a "Virtual Facility", consisting of integrated, 

tool-oriented computing and communication systems to support scientific and engineering collaboration, removing barriers of 

geographic distance and time from research collaborations. This activity could start with the analysis of existing Grid-based 

collaborative and visualisation environments, like Access Grid or in SORS, and would continue with the design of a new 

distributed Concurrent Design Facility (CDF). As the last step a first prototype would be implemented. Two demonstrations will 

be carried out during this period, a first one to assess ESA internal capabilities and a second one to prove the concept (for 

technical reasons they might be organised without using GRID). 

Deliverables: 

Report on current Grid-based advanced collaboration environments; GDCD services specification, architecture and 

demonstration. 

Current TRL: N/A Target TRL: Prototype Application Need/Date: SW operational >=2008 

Application/Mission: all missions involving distributed teams Contract Duration: 18 months 




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Title: 

T605-06MT 

Virtual AIV Techniques for Virtual Integration of a Satellite in the Test Facilities 

Deliverables: 








Title: 

Space System Reference Model 

The engineering data is at the heart of the advanced system engineering concepts like simulation-based design (also called 

virtual spacecraft approach). In order to allow for this approach to be successfully implemented, the simulation must be 

embedded in de design process, in a way that the design baseline can be translated automatically in an executable 

simulation. The virtual model must reflect the content of the engineering database and must be kept in pace with the with a 

"changing" design baseline. System characteristics can be represented as simulation models as well as database items. 

Also, simulation models must be "generated" from a reference "system" representation together with requirements and system 

data. The purpose of the activity will be: review ongoing initiatives in ESA and industry; select appropriate technology for 

implementation of data model; define semantics and populate the data model for a typical spacecraft; and demonstrate that 

design baseline, simulation and engineering databases can be rendered consistent and generated from the same data model. 

Deliverables: 

S/C data model semantics definition/population; demo model of design baseline/automatic simulation generation and 

feedback to ECSS standards. 

Current TRL: - Target TRL: Prototype Application Need/Date: SW operational >=2009-2010 

Application/Mission: all space projects Contract Duration: 12 months 





Title: 

T607-06EM 

System-Software Co-Engineering: Performance and Verification 

This activity will focus on the verification of the system properties at system and software level. The activity aims at defining 

the verification techniques and their environment: schedulability analysis, network calculus, exhaustive verification of state 

machines, deadlock/livelock analysis, causality, performance, distributed workload, FMECA, SW-FMEA, etc. The use of 

existing commercial tools is encouraged, developing filters between the tools capturing the system description and the tool 

performing the verification. But specific development might be needed. 

Deliverables: 

Definition of the verification environment (lifecycle); identification of the commercial tools and needed developments; 

development of filters to the commercial tools; development of specific demonstration models and case study. 

Current TRL: 


- 

SW operational >=2009-2010 

version 




On-Board SW 


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Title: 

T607-09SR 

Concepts for future spacecraft architecture and development approaches 

The proposed activity will address the architecture of future spacecraft within the context of the overall mission architecture. 

This will be done for a set of strawman missions from various domains. The model requirements from the reference missions 

will be analysed and strawman mission architectures established. The focus would be on the spacecraft but considering the 

overall context. The experience with previous approaches, e.g. standardisation of full service modules (ERS-like), or mainly 

avionics (e.g. Flexbus) will be reviewed and lessons will be drawn. Experiences with standardisation / inter-operability in other 

domains will be analysed for applicability. 

The strawman mission will result in a series of strawman payloads which will provide context requirements for the spacecraft. 

The interfaces payload – platform will be addressed with the intention to establish the borders where appropriate to enhance 

efficiency. The availability of technology will be considered . 

Functional, operational and performance and other support analysis will be conducted to define the blocks of the spacecraft 

architecture. Reasonable flexibility and expandability goals will be established from each block and the overall. Special 

attention will be paid to the need to be at the same time efficient by the effect of scale procurement of equipments and the 

compatibility with multiple supplying sources. Recurrence versus innovation will be traded-off and the potential implications of 

obsolescence addressed. 

The needs of the end-to-end command and control chain, including ground and space segment will be considered. from 

commanding at mission level, e.g. obtain an observation, to actual implementation by the onboard and ground systems so as 

to standardise development, testing, operation, training. Observability, commandability will be addressed. 

Operational modes will be analysed and the impact on the architecture established. Availability goals will be discussed and the 

impact on the architecture derived. Quality levels will be also addressed. 

Levels of standardisation / commonality will be identified / discussed considering also the implementation context. 

The concepts will be considered with due regard to their implementation, i.e. considering the complete definition, 

development, verification and operation cycle. The process of handling requirements, system – software co-engineering, 

concurrent engineering, collaborative engineering, progressive verification, utilisation of end-to-end simulation, software 

simulators of increased fidelity, virtual spacecraft technologies will be addressed. The achievement of technology readiness 

levels, mainly in the area of payload shall be addressed for their impact on the development processes and features of the 

spacecraft architecture. 

This will be done with due attention to the ESA environment and constraints and implications on the implementation of 

projects. 

Candidate architecture concepts and DD&V and operation processes will be identified and traded-off for agreed criteria. The 

selected concepts will be then applied to the strawman missions. 

Deliverables: 

Technical Note (trade-off, architecture, critical technologies,..) 






Roadmap: N/A 

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Title: 

T607-12SW 

System of Systems analysis and design environment 

The boundaries of system design for space systems have changed significantly in the recent years. If it has been sufficient to 

provide single well defined products with a dedicated system in the past, the expectations of users shift towards services and 

support, with an entire functional chain required to provide these services. A system design needs to take into account various 

and partially divergent functions, to be implemented with space systems, processing and coordination functions on ground and 

service provision for the end user – who is not primarily interested in how a service is being established. 

This contextual approach requires integrating individual systems originally designed for specific purposes, in order to get an 

optimal synergy between these elements. Examples are Earth Observation systems (geographical context and surveillance 

functions), communication networks (with space and ground components) as well as navigation services (with their respective 

spatial and potential local increment components). In the extreme we find systems like Global Earth Observation System of 

Systems (GEOSS) and the future Human Security SoS. In order to be able to enable a global analysis and trade-off of 

parameters, it is required to enhance existing development methods and tools on (individual) system level to make them 

suitable to this system of systems. 

This activity shall define a methodology for the analysis and design of a system of systems. The required tools shall be 

prototyped and demonstrated for a multi-level system such as the combined GMES, Galileo and communication systems. 

The methodology needs to address hierarchical analysis approaches, based on proven and demonstrated methods from the 

classical system engineering domain. Languages such as UML/SysML and advanced approaches such as the “Virtual 

Spacecraft Design” need to be enhanced to be able to capture the increased complexity of such systems. A reference 

architecture for such a system shall be established. 

Supporting tools need to be prototyped. These tools need to support existing engineering and simulation paradigms as well as 

meta-modelling paradigms required for the methods identified above. The explicit support to performance modelling at the 

SoS level needs to be enabled with the proposed development, by providing elementary performance analysis blocks for the 

individual systems. 

Deliverables: 

Three main types of deliverables are expected form this activity: 

1) A well documented methodology for the analysis and design of a system of systems, addressing performance issues: 

Formal methods for system-level design and verification; Reference architecture. 

2) A support environment for this methodology, to establish relevant system and performance budgets and provide the 

elements for system-level trade-offs: System-level performance model building blocks; Architectural design tool for complex 

systems; ... . 

3) A demonstration prototype for an identified reference system. 


Application/Mission: Security, GMES, GEOSS Contract Duration: 18 months 

SW Clause : - Dossier0 Ref.: New rqmt 




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Title: 

T607-13SW 

Monitoring and Control Data Modelling 

Data base development is on the critical path of many projects; a tool to efficiently generate a validated mission-specific data 

model, compatible with the applicable standards will greatly contribute to reduce the development time and facilitate 

compatibility across project phases. To that purpose a data model for monitoring and control is needed. A user specification of 

an ontology (a data model that represents a domain and is used to reason about the objects in that domain and the relations 

between them) for the monitoring and control of space systems has been standardised in ECSS. The ECSS E-70-31 Standard 

specifies a set of "generic data" to be supported by any mission (any space system) and a set of "mission specific data" to be 

"tailored" for a given mission. The purpose of this activity is to study and develop tools able to formalise the specification of 

data required in the Spacecraft System Database in line with relevant ECSS standards. The end result will be an "Ontology 

modelling tool" based on the Object Role Modelling Methodology (potentially reusing the NORMA tool currently under 

production in academic establishments) able to: 

- support all modelling concepts and constraints (including tailoring rules) given in E-70-31 and E-70-32. 

- offer to mission users the capability to navigate through the tailoring rules (according to algorithms given in E-70-31), and 

tailor the ontology for their own missions (i.e. populating the tailoring variables). 

The tailoring being made, the ontology tool will automatically: 

- produce the mission specific ORM data model. 

- allow users to add mission specific data 

- validate the overall ORM schema and produce: the E/R and SQL data models for use in an RDBMS; the product data 

exchange interface specification (i.e. an XML schema for exchanging mission data, e.g. between different database systems). 

Deliverables: 

Data Model generation tool. 

Current TRL: 


- 


version 

Application/Mission: All future projects Contract Duration: 15 months 



GSSW (not specifically discussed at Harmonisation). 


TRP Reference: T607-14SW 

Title: 

Building Block Approach for EGSE 

In the context of the ground segment software harmonisation activity performed by Critical Software (P) the standardisation of 

a number of interfaces has been addressed. The end result is a set of ICD's derived through the application of a formal 

modelling process. One of these interfaces (specified by Dutch Space as sub-contractor to Critical) concerns the 

interconnection of EGSE elements and simulators (known as SIM--EGSE-Interface). In order to validate the interface 

specification it is proposed to develop a prototype of the EGSE-SIM interface in the context of the EGSE reference facility 

located at ESTEC. 

The target shall be to achieve a low cost scalable and configurable EGSE that can be applied on any mission and supporting 

reuse of simulation building blocks. 

Deliverables: 

A prototype EGSE system integrating existing Central Checkout System and a SCOE/Simulator, compliant with the 

established ICD. 


Application/Mission: All future projects Contract Duration: 12 months 




GSSW (not specifically discussed at Harmonisation). 

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Title: 

GI-001 

XML Framework 

Deliverables: 








Title: 

GSS-041 

InP X-Band Cryo LNAs 

Deliverables: 







TRP Reference: T603-34GI 

Title: 

TC Authentication 

The Authentication scheme proposed as optional in the ESA Packet Telecommand protocol is no more considered secure. 

Telecommand Authentication is deemed as the minimum Security barrier that ESA spacecraft missions should implement. 

This study covers the definition of an updated Authentication scheme for the Packet Telecommand protocol. 

Deliverables: 

Updated authentication scheme for the packet TC protocol. 

Current TRL: Target TRL: S/W release Application Need/Date: 







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Title: 

T603-35GI 

Security communications for SLE services 

Based on precedent System studies and the existing CCSDS Space Link Extension (SLE) transfer services and 

implementation by both ESA and NASA, this study aims at reviewing and upgrading the Security functions for missions where 

a high-level of Security might be requested. 

The Study will have to consider the available protocol and design the tools (e.g. protocols, encryption methodologies, etc.) 

needed to implement a high level of security that can be provided with ad hoc tailoring to a user mission. All the design 

choices shall be supported by Software breadboarding and simulation. The developed software shall be organized in form of 

Software Product (e.g. Library) for easy portability and integration in existing or proprietary software (sub)systems. 

Deliverables: 

Technical note, SW breadboard and simulation. 

Current TRL: Target TRL: S/W release Application Need/Date: 








Title: 

Feasibility of Automated Regression Testing for Space Systems Operational Software 

The operational S/W used within space systems is constantly increasing its complexity. Furthermore, due to standardisation 

and re-use of infrastructure systems, the expected lifetime of software components has also significantly increased. These 

trends have lead to a significant increase in the efforts required for system verification and validation, in particular to ensure 

integrity of previously validated functions (regression testing) when delivering a new version of the same software 

component/system. Currently, the vast majority of all testing activities, including regression testing, are performed based on a 

'manual' approach with the human in the loop. This is primarily due to the fact that, in order to automate testing activities, a 

large effort has to be invested upfront for the definition of appropriate test data, test tools/harnesses, test procedures and test 

outputs evaluation (pas/fail criteria). The proposed study should therefore demonstrate the feasibility and assess the benefits 

of adopting an automated approach for the execution of software systems regression testing. It will include the analysis of the 

specific features of space systems software components, with particular attention to the ground operations systems that are 

typically operated by humans via human-machine interfaces, and it will review the possible options offered by available 

technologies and commercial products for the preparation and automatic execution of systems regression testing. The 

selected approach shall be suitable for automated testing of all ground operations systems i.e. it shall not be bound to the 

specific implementation aspects of the individual systems. A demonstration test environment will be set-up covering the 

automatic execution of functional and non-functional tests of selected software components. This prototype shall demonstrate 

the re-usability of the automated test cases when validating a new version of the same software component. Finally, it will be 

assessed the required effort for the set-up of the individual test cases and evaluation of the potential benefits of the 

demonstrated approach. Special emphasis shall be given to the feasibility of identifying unambiguous pass/fail criteria for each 

test case, with particular reference to the non-functional tests. 

Deliverables: 

Technical documents (adoption of automated approach for execution of SW sys regression testing). Set-up of demonstration 

test environment + data/procedures. Final report (assessment of the potential benefits / relevant recommendations). 

Current TRL: - Target TRL: Prototype Application Need/Date: SW operational by 2008 





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Title: 

T605-09GI 

N-Tier architectures applied to Ground Operations Systems 

The current generation of Ground Operations Systems used at ESOC is based on client-server architecture, which is more 

generically referred to as a '2-Tier' architecture. In particular in the telemetry processing subsystem, the current 

implementation leads to severe requirements about the procurement and maintenance of all H/W workstations, including the 

large number of users workstations. The purpose of this study is therefore to investigate the possible benefits that can be 

achieved by adopting 'N-Tier' architectures to Mission Control Systems. In particular, the 3-Tier architecture should be looked 

at for the most critical subsystems i.e. the telemetry processing, the commanding and the On-Board Software Maintenance 

(OBSM). The 3-Tier architecture consists of a data server, implementing the management of the data; an application server, 

implementing most of the data processing functionality and a client, supporting the visualisation of the processed data to the 

end user. It attempts to overcome some of the limitations of the 2-Tier architecture by enabling a complete separation of the 

data presentation, the data processing and the data management using distinct entities. The different tiers interact via 

standard protocols such as CORBA, HTTP or standard database protocols. The middle-tier servers are typically coded in a 

highly portable, non-proprietary language such as C++ or Java. Middle-tier functionality servers may be multithreaded and can 

be accessed by multiple clients, not necessarily all under manual user control, thus enabling the automation of user actions. 

The analysis phase of the study shall identify the most suitable technology to be used for N-Tier implementations of Ground 

Operations Systems in general (e.g. code language of the application servers, data storage technology, interaction protocols). 

The design phase shall cover the architectural design of 'new generation' monitoring and control subsystems heavily involving 

data processing and visualisation (at least telemetry processing, commanding, OBSM and Station Monitoring and Control). 

The prototyping phase shall migrate an existing subsystem to the 3-Tier architecture and the assessment phase shall evaluate 

the benefits of the 3-Tier architecture at system level (including scalability, portability, flexibility, maintainability and 

performance) and provide recommendations for the future generations of Ground Operations System infrastructure S/W. 

Deliverables: 

Under review ------------------ Technical doc. (outputs of the analysis activities). Architectural design document (3-Tier 

architecture of the MCS most critical subsys). Model implementation of the 3-Tier architecture (selected MCS subsys). Final 

report. 

Current TRL: - Target TRL: TRL2 Application Need/Date: N/A 







European Technology Harmonisation on Ground Systems Software - First Set of 

Title: 

Standard Interfaces 

The European Technology Harmonisation on Ground Systems Software is supported through standardisation of functions and 

interfaces. It has been agreed to broaden the scope of this harmonisation (initially Mission Control and EGSE) to include the 

other ground system components (Flight Dynamics, simulators, Data archiving and mission planning);A three-phase approach 

has been adopted (medium term strategy) with: phase 1(System level): define, with the user community, a common system 

standard architecture and common requirement for identified modules to become ECSS standards; Phase 2: Define standard 

interfaces between modules (to become ECSS standards); Phase 3: Contracts to re-engineer, as needed, solutions compliant 

with requirements and standard interfaces, re-using as far as possible existing products. In this proposal, phase 2, it is 

proposed to produce the definition of the standard interfaces between the modules of the Ground Systems Reference 

architecture, which is key for the future work. Examples of standard interface definition are TM monitoring and Commanding, 

Operational Database, On-Board Software management function, Mission Planning System, although the final list of 

interfaces to be standardised and its priorities will be defined at the end of Phase 1 (March 2004). This proposal covers the 

first set of interfaces (i.e. 5). A second proposal will cover the remaining interfaces (See Proposal T605-18GI / 

TOS-GI-ETH-GSSW-002). 

Deliverables: 

A set of standard interface definition (to be detailed at the end of Phase 1) between the modules of the Ground Systems 

reference Architecture. 

Current TRL: Target TRL: TRL1-2 Application Need/Date: 






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6.10 - Flight Dynamics & Navigation 


T606-08GF 

Analysis of a Standardised Approach to the Emulation of the Highly Autonomous 

Title: 

Avionics Systems of Interplanetary S/ C 

The Avionics systems of the interplanetary S/C are highly autonomous and complex. In particular, they are designed to 

support uninterrupted operations for extended periods without ground support and they even guarantee the capability to 

autonomously point the antenna to the Earth and re-establish the link in case of any contingency . To achieve autonomy the 

ground station has to provide a large amount of commands and parameters to the Avionics system, which are normally time 

tagged and executed by an on-board command queue. Emulation tools play a key role in the generation of those command 

parameters. On one side they are used in the command generation chain, to actually produce the parameters to be up-linked 

to the S/C. On the other side they are used as verification tools to predict and test the effect of command parameters in the 

S/C. Also they are a valuable tool to create awareness of the Avionics systems in the operations teams. The purpose of the 

study is to explore and breadboard models for standardisation of FD emulation tools for interplanetary S/C to achieve a 

development framework which can easily be re-used for future missions. In particular it is envisaged to create standard 

modules for Spacecraft dynamics models, propulsion systems models, avionics units and S/W models and FDIR models. 

Deliverables: 

Breadboard of the models for standardisation and final report. 

Current TRL: Target TRL: Prototype Application Need/Date: SW operational >=2008 

Application/Mission: Deep Space Missions Contract Duration: 8 months 




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6.11 - Mission Analysis & Space Debris 

TRP Reference: T605-08GA 

Title: 

Astro-toolbox: a toolbox for preliminary mission analysis 

This study aims at the definition of the required tools for preliminary mission analysis and design. It will be necessary a 

trade-off between the level of accuracy for a preliminary assessment and the computing time required. The study will also 

include an implementation of the defined methodology and approaches into a modular software code and a verification of the 

Astro-toolbox on a number of selected test cases. The definition of the tools is necessary to identify all typical problems that a 

mission analyst commonly may encounter during a preliminary design (spiralling trajectories, multiple swing-bys, launch 

windows, orbit maintenance, HALO orbits,etc). The trade-off is necessary to define the most appropriate approaches and 

solution methods for the identified problems. The result obtained by each module must be reliable (within a certain tolerance) 

even in case of quick assessment. The maximum error (or the tolerance) allowed for a preliminary study must be defined in 

relation to the computational effort. Due to the nature of the toolbox, and the required modularity, it is recommended to use 

Matlab (or equivalent) as programming language and development environment. Interface with other systems (excel, STK,etc) 

must be provided in form of appropriate output and input data format. A graphical interface is also required to help in the 

design and visualisation of the results. 

Deliverables: 

Technical Report, Demonstration Software. 

Current TRL: 


- 

version 

Application/Mission: Mission analysis Contract Duration: 12 months 




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6.12 - Ground Station System & Networking 


Title: 

T606-01GS 

Two-layer servo concept with movable BWG mirrors 

In Deep Space operation at Ka-band, the pointing requirements are more demanding than for Near Earth missions. At 

present, the positioning of an antenna is carried out with a servo drive system for the elevation and azimuth axis. Due to the 

eigenfrequencies of the antenna structure, the involved masses and the limited torques at the output of the gearboxes 

provided by the main drive system, the compensation of pointing errors, position errors, is limited to slowly varying effects. For 

future deep space missions in Ka-band, due to the delay to the spacecraft, the earth rotation and the small beam-width of the 

antenna, a beam squint between transmission and reception is necessary. This will require a moveable mirror system to 

generate a movable beam offset between transmission and reception. A Beam WaveGuide (BWG) system for the RF signal 

path consists of several mirrors. Movable mirrors would allow to compensate the errors due to distinct faster varying effects, 

e.g. wind gusts. Such movable mirror would correct position errors detected by the encoders of main drives. The main drive 

itself cannot compensate the position error due to the above-mentioned reasons. Such system would be particularly 

interesting, because the pointing errors due to wind effects are the major source of position errors for the 35 m antenna. 

Taking into consideration the previous explanation, the purpose of this study is to design a servo system (including elevation 

and azimuth axis and a system of movable mirrors) and to identifying its critical areas, and also to develop a control system 

for the movable mirrors. Numerical simulations will be used to investigate the limits of the servo system regarding dynamic 

behaviour, position accuracy and response time. 

Deliverables: 

Study and design report with detailed dynamical analysis of the proposed design. Breadboard of a drive system for a movable 

mirror. 


Application/Mission: Deep Space Network Contract Duration: 18 months 




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TRP Reference: T606-02GS 

Title: 

Multipurpose Highly Stable System for Ground Station Characterisation 

There are two main needs for the proposed activity: 

precise time transfer among Deep Space Ground Stations; 

ability to measure the Allan deviation of large reflector antennas, such as the ones used to support Deep Space missions. 

Tracking requirements for future Deep Space missions demand accuracies that cannot be achieved with current tracking 

techniques. Planning ahead for future tracking methods that can meet these requirements, Delta Differential One-Way Range 

(DDOR) is included in the TT&C roadmap as a technique to be used in the future for more accurate tracking measurements. 

DDOR is a Very Large Baseline Interferometry (VLBI) technique that makes use of two or more distant Deep Space Stations 

in order to perform accurate spacecraft's angular position measurements. This technique requires very precise station 

synchronisation, which could be achieved by means of accurate time transfer. Additionally, radio science requirements of 

planetary missions call for extreme Allan deviation performances for Ground Stations. Deep Space missions time scales 

require the characterisation of the whole Ground Station and specifically of large mechanical structures in terms of electrical 

phase stability, which turns into tracking accuracy. At present there are no means to measure the contribution of the 

mechanical part of the antenna to the overall frequency stability of the ground station. In this context, the goal of this activity is 

to develop a system able to synchronize frequency standards from distant Deep Space antennas (like New Norcia and 

Cebreros) for DDOR measurements. This could be done by implementing a Ku-band link between the stations involved in the 

measurement. A small 3m (TBC) antenna transmitting/receiving in Ku-Band, together with a highly stable two-way time 

transfer processor and a highly stable link are required for this task. This system can also be used to characterise the stability 

of the antenna mechanics. An additional highly stable phase comparator module is needed for this application. 

Deliverables: 

Breadboarded system for evaluation, final report, and test reports. 

Current TRL: 

Target TRL: 

Application Need/Date: (Continuation in the 2008 

TRL2 

budget of ESA Investment 

Plan) TRL5 by 2012 

Bepi-Colombo; any mission using the 

Application/Mission: DSAs (e.g. Rosetta, MEX and VEX, Contract Duration: 18 months 

Herschel-planck, GAIA, SOLO, etc.) 




TRP Reference: T606-06GS 

Title: 

Experimental InP Ka band cryocooled LNAs 

This study shall provide technological advancement in manufacturing Ka-band cryo Low Noise Amplifiers (LNAs), as required 

for ESA missions. The study will be composed of two main tasks. The first task is the development and production of InP (or 

GaAs with high In content) devices (TRTs or MMICs) suitable for low noise cryogenic applications. The second task is the 

development and production of cryogenic LNAs suitable to work in ESA Deep Space antennae. More detailed, the work to be 

performed is to derive suitable specifications for transistor manufacturers and to breadboard o cryo Ka-band LNA with the 

developed devices (either MMICs or TRTs) so that it can be tested the RF performance at cryo and ambient temperature. 

Deliverables: 

Breadboard of the designed LNA and documentation and recommendations for the production of the serial units. 







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T606-12GS 

Study and Breadboarding of a Sapphire Oscillator for Ultra-High Short-Term Station 

Title: 

stability 

A clear trend in Ground Station engineering is the search for better Ground Station stability, since it results in better tracking 

accuracy. Generically, frequency stability is characterized with two quantities: Phase Noise (short term stability) and Allan 

Variance (long term stability). Among possible frequency stability improvements in Deep Space Ground Stations, sapphire 

oscillators are the most promising option because they permit phase locking to other sources. This allows simultaneous use of 

sapphires and MASERs in a single Ground Station frequency reference. By doing so, the good qualities of MASERs and 

sapphire oscillators are combined for optimum performance. However, there are currently no sapphire oscillators deployed in 

any ESA station. Before this becomes a reality, there is a need to understand design, integration and maintenance related 

aspects. The purpose of this activity is to design and breadboard a sapphire oscillator that improves Ground Station frequency 

stability performance up to 100 seconds. This activity will be divided in two phases (Phases I and II).Phase I activities shall 

present a general overview of sapphire oscillators; identify doping materials for external element compensation; compare 

cryocooled sapphire oscillators versus more inexpensive compensated sapphire oscillators at higher temperatures; analyse 

different phase locking techniques between a hydrogen maser and a sapphire oscillator; evaluate different down conversion 

schemes from the sapphire output frequency to the Ground Station frequency distribution outputs; describe relevant 

monitoring and control parameters for sapphire oscillator operation; detail any remaining issue that is relevant for sapphire 

oscillator's operation; address sensitivity of sapphire oscillators to electromagnetic fields; and trade-off all decision factors and 

present the most suitable solution for a combined maser and sapphire oscillator source in ESA Deep Space Ground Stations. 

During Phase II of the study, a sapphire oscillator shall be breadboarded, together with the necessary PLL circuitry to phase 

lock it to a MASER standard. The breadboard unit shall allow for basic M&C communications via TCP/IP. An acceptance test 

shall be performed on the breadboard unit, in order to validate the performance (phase noise, allan deviation, phase locking to 

maser, sensitivity to magnetic fields, other EMC effects and M&C). 

Deliverables: 

Intermediate report (end of phase I); breadboard; final report. 

Current TRL: Target TRL: TRL4 Application Need/Date: TRL5 by 2010 





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Title: 

03/MMM-001 

Self Contained Deployment Mechanism 

A SeCDeS (Self-Contained Deployment System),consisting of a motorized deployment system with a mechanism located in 

each of the panel hinge lines, is under development to reach a TRL4. The mechanism is simple, has low weight, and consists 

of a stepper motor connected to a gear box. All stepper motors are controlled from an electronic box located close to the root 

hinge of the spacecraft. The electronics are powered from a battery box also located close to the root hinge. The mechanism 

can easily be adapted to all types of mechanical hinges. This new system gives accurate panel synchronisation and the 

achieved SA cone angles are considerably reduced compared to existing systems. 

The subject CCN shall address two issues identified in the course of the BB development: 

1. A miniaturized position sensor must be developed to achieve the BB performance. Sensor fundamentals and mechanical 

robustness as well as signal integrity and analog filtering techniques will be addressed as main objectives. An EM sensor will 

be built and tested. 

2. A worst case environmental test of the double stage Harmonic drive gear box must be performed to ensure that the 

gearbox behaves as expected within the specified temperature range [Operational -130 degC to + 116 degC, Survival -180 

degC to +116 degC]. 

Deliverables: 

Miniaturized position sensor 


Application/Mission: Solar Arrays Contract Duration: 9 months 





Title: 

Self Contained Deployment Mechanism 

Deliverables: 







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Title: 

03/MMM-002 

Integrated SADM+HDRM 

Deliverables: 







TRP Reference: 03/MNT-001 

Title: 

Mirco Nano Satellite Technologies 

The subject CCN shall address two issues identified in the course of the BB development 

Deliverables: 








Title: 

APSEE: Arc Phenomena in Space Environment & Equipment 

A miniaturized position sensor must be developed to achieve the BB performance. Sensor fundamentals and mechanical 

robustness as well as signal integrity and analog filtering techniques will be addressed as main objectives. An EM sensor will 

be built and tested. 

Deliverables: 







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Title: 

T601-36MM 

Unlimited resetable, no-shock Hold-Down and Release Mechanism (HDRM) 

A worst case environmental test of the double stage Harmonic drive gear box must be performed to ensure that the gearbox 

behaves as expected within the specified temperature range [Operational -130 degC to + 116 degC, Survival -180 degC to 

+116 degC] 

Deliverables: 

HDRM breadboard model with associated datapackage documentation. 


Low mass appendages, where access is 

Application/Mission: critical (e.g. optical payload mechanisms, Contract Duration: 18 months 

small reflectors, covers) 




Hold-down and Separation Systems 

TRP Reference: T601-47MX / MMM-960 

Title: 

Tribology Application Programme 

Within the identified funding limitations, the R&D activities proposed will address in detail all subjects from tribological design, 

analysis, to development and lifetime test demonstration of advanced tribological components and lubrication solutions. Tool 

developments to facilitate the design and analysis of bearings and its components (cages) under specialised conditions as 

experienced on Earth Observation payloads are included. Furthermore, moving electrical contacts, sizing for stiction and 

dynamic friction, and tribological solutions for miniaturised mechanisms components and development of special tribological 

coatings to reduce payload and S/C cost for integration will be investigated. 

Deliverables: 

Tribological assessments, feasibility demonstrations of lubricants wrt. wear and lifetime performance, Software breadboard 

verifications of advanced lubricant solutions on key mechanisms components. 

Current TRL: - Target TRL: TRL3-4 Application Need/Date: N/A 

Application/Mission: all space missions Contract Duration: 60 months 






Title: 

Fully Variable Bearing Active Preload System 

The proposed activity aims at the development of a device that allows to actively control in-orbit the preload of ball bearings 

for applications requiring an extremely long life (e.g. Wheels, Pointing & Scanning mechanisms). The basic concept of 

bi-stable (one shot) operation, i.e. switching between high and low preload already proven in terms of concept, shall be 

extended to in-orbit full adjustment capability. Upon external command, it shall be possible to select a high preload and to vary 

a low preload setting within an appropriate range. Using a suitable target wheel as test bed, an engineering model of the 

preload adjustment device shall be designed, manufactured, integrated and tested in representative environment. 

Deliverables: 

Engineering Model (accompanied by Technical Data Package and further documentation). 

Current TRL: TRL3 Target TRL: TRL5-6 Application Need/Date: TRL5-6 in 2008 

Wheels, Pointing mechanisms, 


Scanning mechanisms 




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Title: 

T608-32MM 

Angular position sensor based on MEMS technology 

The purpose of this activity is to take benefit from existing MEMS devices already developed for ground application, and 

develop a MEMS angular position sensor suitable for space application. The targeted accuracy should be better than 0.1deg 

along 360 deg. 

Several non-contact technologies (Hall-effect, optical, micro-gyro, magnetic, ...) are potential candidates. First part of the 

activity should focus on possible design and the selection of the most appropriate technologies to achieve this MEMS position 

angular sensor with respect to space application needs and constraints. 

Second part of the project will be dedicated to the manufacturing and test of Engineering Model MEMS device to be validated 

in representative environment. 

Deliverables: 

Functional MEMS Angular sensor Engineering Models and associated datapackage documentation. 

Current TRL: TRL3 Target TRL: TRL5-6 Application Need/Date: TRL5-6 in 2008 

All mechanisms requiring angular 

position measurement (e.g. SADM, 


EPPM, Pointing & scanning 


mechanisms) 




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MMO-670 

Materials for Ultra-Stable Lightweight Optical Benches and Mirrors (old title: Ultra 

Title: 

lightweight Telescopes) 

Objective of the activity is the evaluation/development of material technologies for ultra-stable optical structures. The materials 

should be suitable for cryogenic applications (i.e. homogeneity, isotropy) and lightweight applications. In view of the 

development status reached for SIC100 (e.g. Herrschel), other materials shall be considered. During the course of this 

activity, a representative optical structure demonstrator (optical bench, mirror, telescope) shall be developed and extensively 

characterized. Alternative material or technologies (shell technologies) shall be considered. 

Deliverables: 

Material characterisation Data 


Applicability (>2010) to SCI/EO missions 


(e.g. Darwin, MTG) 





Title: 

Entangled photon source for Quantum Communications 

Absolute (=unbreakable) security is a mandatory requirement in many space applications (satellite remote control, GALILEO, 

etc). Quantum cryptography provides a scheme for the absolute secure distribution of cryptographic keys, guaranteeing such 

stringent level of secure communications. ESA has placed two parallel studies entitled "Quantum Communications in Space” 

in the General Studies Programme (GSP). These studies have identified novel concepts for space communication systems 

based on the principles of quantum physics, along with related demonstration experiments using available infrastructure (e.g. 

ESA’s Optical Ground Station). Such experiments require the development of a quantum communication optical terminal. 

The objective of this activity is to initiate the development of the key building blocks of such a quantum communication optical 

terminal by the development of an efficient entangled photon source module that potentially could be used in space. Such a 

source is mandatory to perform fundamental tests of quantum physics and to implement quantum communication protocols 

based on entanglement (e.g. quantum teleportation, quantum dense coding). An entangled photon source can also be used 

as a single photon source. 

A complete quantum communication optical terminal in space would provide the capability of distributing entangled photon 

pairs to 2 separated receiver terminals (e.g. 2 Optical Ground Stations) simultaneously. Such a capability would be of great 

importance for absolute secure key distribution between widely separated points on Earth using the principle of quantum 

cryptography based on entanglement. Current terrestrial optical fibre networks limit the maximum separation of users to about 

100 km. Later developments of a complete quantum communication optical terminal would require further items such as: 

• Single photon detection module 

• Faint laser source module 

• Optical components for photon manipulation 

• Dual telescope opto-mechanical head 

• Data acquisition and classical communication channel. 

Deliverables: 

Experimental proof-of-concept demonstration of entangled photon source. 

Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 >2010 

Security applications (satellite remote 


control, GALILEO, ..) 




18 months 

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Title: 

T609-05MM 

Instrument concepts using dynamic diffraction gratings (ICDDG) 

The ongoing commercial development and exploitation of MEMS technologies has led recently to the availability of a new 

device type called "programmable micro diffraction gratings" (PMDG). Such devices are a key "enabling technology" for many 

potential applications in telecommunications (e.g. add-drop mutiplexers), Earth observation and remote sensing (e.g. 

reconfigurable correlation spectroscopy of trace and toxic species) etc. The possibilities are endless. As with all MEMS type 

devices one of the big advantages of PMDGs is their small size and programmability. In addition on first inspection they 

appear to be very robust. With mass production the unit cost will certainly decrease and their use for the construction of small 

but powerful sensor systems on micro or nano sats is a very attractive option. In this activity it is proposed to procure a PMDG 

device(s) from the US and to investigate its performance under laboratory conditions. In addition once it has been 

characterized and understood from an operational point of view, it will then be built into a breadboard spectrometer for 

functional testing. The breadboard spectrometer design will be optimized to take full advantage of the performance and novel 

characteristics of this US PMDG device. 

Deliverables: 

Fully characterized PMDGS devices 


Application/Mission: Small EO missions, planetray research Contract Duration: 12 months 





Title: 

Advanced Side-pumping Technique for Double Clad Fiber Lasers 

Double-clad fibre lasers allow for very improved pumping (optical to optical) efficiencies as well as higher absolute powers by 

maximizing the pump - active region overlap and matching to both pump and output wavelength. This activity is aimed to 

investigate an advanced side-pumping technique by using small coupling grooves in the cladding allowing elegant redundancy 

implementation of the pump system and system miniaturization. 

Deliverables: 

Laboratory test setup demonstrating the achieved pumping efficiency and absolute power of the proposed advanced pumping 

scheme. 


Application/Mission: generic Lidar technologies Contract Duration: 24 months 





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Title: 

T609-17MM 

Programmable optoelectronic adaptive lens 

Production of a lightweight, single element lens, consisting of a liquid crystal or electrochromic plate, dynamically controllable, 

to produce the desired optical refracting properties. Useful in many instruments normally requiring heavy, multi-element lens 

systems, and capable of varying optical properties on command. This device would be particularly relevant for microsats and 

nanosats. This activity will study, analyse and then design and manufacture a liquid crystal or electrochromic plate, with a 

matrix of addressable pixels or rings, allowing the localised and programmable variation of refractive effect or the generation 

of Fresnel zones. In this way, any desired effective refractive behaviour profile can be generated, in a somewhat similar 

manner to a Fresnel lens. This would permit the emulation of various types of lens systems within a very lightweight and 

compact optical assembly. Variation in the optical properties of the lens would also be possible on a dynamic basis. The 

device could also serve as an adjustable attenuator for sources of differing brightness. Testing, characterisation and analysis 

would then follow, to allow a clear assessment of how to proceed for future development in this technology. 

Deliverables: 

Optoelectronic lens demonstrator. 

Current TRL: - Target TRL: TRL2 Application Need/Date: TRL5 >= 2010 

Application/Mission: all optical missions Contract Duration: 18 months 





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Title: 

T609-23MM 

Programmable micro-diffraction gratings 

Programmable micro-diffraction gratings (PMDG) are on-chip-manufactured optical devices using micro-electro-mechanical 

system (MEMS) technology. Optical MEMS (MOEMS) devices are based on movable micrometric optical components and 

therefore provide large benefits in terms of mass, speed, low power consumption, size and ruggedness. In addition they have 

the potential to be available at low cost, since complete systems can be produced using essentially standard technologies of 

the semiconductor industry. 

Basically, a PMDG device consists of a one-dimensional array of very thin and flat optical mirrors (100’s of micromirrors) 

whose vertical position can be electrically controlled (e.g. by electrostatic actuation). By adjusting all the relative mirror 

positions a grating can be generated for diffracting the incident light into a selected angle with any desired spectral response. 

For example, they can be adjusted to form a blazed grating or to match the absorption or emission spectrum of a molecule. A 

new type of extremely compact correlation spectrometers, very promising for Earth Observation and Science Exploration 

missions, can be built. Only one single photo detector is needed to build the spectrometer, which is a great advantage 

compared to fixed grating spectrometers requiring a detector - array. Since the mirrors can be moved in less than 0.1 ms, 

many different spectral responses can be generated in a short time period. Moreover, a PMDG device is reconfigurable (i.e. 

the optical transfer function is programmable), allowing the target species to be changed by remote control, which makes this 

device concept ideal for planetary exploration. 

PMDG can provide elegant solutions to a huge variety of spectroscopy applications (e.g. detection/identification of chemical 

species), hence enabling new Earth Observation and Science Exploration missions, e.g. for spectroscopy instruments 

on-board microsatellites, nanosatellites, micro-aerobots and micro-probes, envisaged for some of the Science & Planetary 

Exploration reference missions (TRM) like JEM (Jupiter Explorer Mission), IHP (Interstellar Heliopause Probe) and VEP 

(Venus Entry Probe). The development of this “enabling technology” will ensure a strategic leadership in competitiveness and 

independence to Europe. 

The objective of this activity is to design, develop and manufacture in Europe programmable micro-diffraction grating (PMDG) 

devices for spectroscopy applications and to deliver a proof-of-concept demonstrator of such a device, which shall be 

subjected to a functional performance verification test campaign for the on ground validation of the selected concept, with the 

goal of demonstrating the functional requirements (e.g. spectral resolution) and the expected improvements in terms of mass, 

size and power consumption. The Contractor shall also investigate environmental, reliability and packaging issues to support 

future space qualification stages. 

PMDG devices are presently commercially available in the USA as well as in Japan. The TRP activity “Instrument concepts 

using dynamic diffraction gratings, T609-05MM”, assesses experimentally the performance and capabilities of PMDG devices 

procured in USA and investigate novel instrument concepts based on PMDG device technology. The outcomes of this activity 

will be used for the proposed PMDG development activity. 

Deliverables: 

Technology data package; Executive summary report; Modelization tools (mathematical/numerical computer models); 

Samples and Proof-of-concept demonstrator of PMDG's for spettroscopy applications. 


Application/Mission: Small EO missions, planetray research Contract Duration: 24 months 





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6.17 - Aerothermodynamics 


Development of advanced models and acceleration of Monte Carlo methods for 

Title: 

simulation of rarefied gas dynamics 

The objective of this activity is to improve the DSMC tools for analysis and design of tree molecular and transitional fluid 

dynamic phenomena such as oftware plume contamination, plume interaction and heating, vehicle reentry and/or destruction 

ATD, satellite environment assessment, and Mems analysis (micro thrusters). The following taks will be done: - Development 

and implementation of advanced models for chemistry and relaxation (diatomic and polyatomic gases) that take into account 

the quantum nature of internal energy modes and vibration-dissocciation coupling. Verification and validation of developed 

models via comparisons with available experimental data- Creation of majorant frequency schemes based on master kinetic 

equation (MKE) for an implicit treatment of the collision processes.- Development hybrid approaches combining continuum 

and kinetic descriptions of the flow, kinetic schemes of gas dynamics should be used to facilitate the automatic domain 

decomposition and coupling of MC solution with continuum equations. A unified computer code should automatically switch 

between kinetic and continuum models to maximize computational efficiency and ensure numerical stability.- Creation of an 

object-oriented software (OOS) system using C++ language and based on RGDAS software. This OOS system should include 

above mentioned models and approaches and permit to compute 2D, axisymmetric and 3D plume flows and their interactions 

with the spacecraft; incorporates pre- and post-processing systems that enable the use by non-expert users; reduces the time 

to set-up + run complex simulations from months to days.The proposed activity is aimed at the development of a single 

European DSMC code for realistic 3d configurations, physically accurate, for simulation of rarefied flows ranging from 

suborbital to ground-test-facility conditions. The code could be developed as a modular, possibly object-oriented, program, in 

a open-source environment and with an open architecture which will allow maximum flexibility and modularity. 

Deliverables: 

European DSMC tool , open source , for simulation of rarefied and transitional flow phenomena. 

Current TRL: 

Target TRL: 

Application Need/Date: SW operational by 

TRL2 

S/W release 

2007-2008 

all satellites / re-entry vehicles (high 


altitude); Exploration, EO, EOPP 





Title: 

Feasibility Demonstration of a European Space Propulsion Simulation Tool 

The purpose is to demonstrate, as an extension of an already existing common environment, a mechanical engineering 

simulation tool for transient multi-disciplinary systems and cycles (e.g. spacecraft systems, chemical and electrical propulsion 

cycles, ground support equipment & operations, ground/qualification tests,...) to be used by European space industries, 

research institutes and universities. Due to the intrinsic complexity of this activity, the feasibility of the concept should first be 

demonstrated, allowing:The proof of concept to couple several mechanical disciplines (fluid flow, thermal, machinery, 

electrical, chemistry...) into one single engineering analysis tool.The proof of concept to reduced modelling of particular 

physical processes in space environments along with appropriate validation.The proof of concept to run in a temporally 

unsteady way a system and/or a cycle where the different demonstration models and discipline couplings are integrated. 

Deliverables: 


Current TRL: - Target TRL: Prototype Application Need/Date: SW Operational by 2010 

Application/Mission: Launcher and satellite propulsion Contract Duration: 18 months 




Roadmap: 2nd sem. 2004 - 1st sem. 2005 

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Title: 

T601-48MP 

Validation of aerothermo chemistry models for reentry applications 

Improvement of the measurement techniques associated with radiation spectral measurements in hypersonic shock tubes and 

plasmatrons. Performance of dedicated experiments using appropriate gases simulating planetary and earth reentry mission. 

Based on these validation experiments, improved physical models will be developed using ab initio modelling techniques 

consistent with the physics of flight. Here special support will be required from universities competent in the field. In a first 

phase emphasis will be put on post flight analysis of the Huygens mission. In a second phase , in addition to the shock layer 

radiation coupling activities, gas surface interaction experiments shall be performed for improved ablation, catalysis and 

oxidation modelling. Here experiments shall be performed in solar furnaces and at universities where specific expertise exists 

on gas surface recombination modelling as well as in plasmarons to obtain catalysis and oxidation data on a set of 

preselected materials used as TPS for planetary and earth exploration vehicles. 

Deliverables: 

Improved and demonstrated physical models for inclusion into aerothermodynamic and thermal protection system design tools 

for application in space vehicle design associated with planetary entry as well as high speed earth reentry missions. 

Current TRL: Target TRL: S/W release Application Need/Date: TRL5 >2011 

Application/Mission: re-entry applications, explorations Contract Duration: 24 months 





Hypersonic facility instrumentation enhancements for improved flight extrapolation and 

Title: 

scaling 

It is proposed to demonstrate the capabilities which hot hypersonic wind tunnels can offer to current and future programmes 

associated with re-entry. What industry is interested in most when performing design work is the influence of high-temperature 

effects not only on thermal and mechanical loads but, in particular, on forces and moments in order to have a sound data base 

for the choice of trajectory, material and so forth. The assured knowledge of such properties would also allow to further 

validate computational prediction methods and models. A suitable approach is to perform some kind of standard model 

testing, i.e. using – if possible – the same test model in all wind tunnels. Two models should be considered, one which allows 

to measure pressure and temperature (heat transfer), and one to determine forces and moments (giving priority to the latter). 

These data would permit cross checking for validation of prediction methods. After consultation with industry a suitable lifting 

body, such as the HALIS model (which duplicates exactly the lower surface of the US ORBITER), and the ballistic model 

EXPERT shall be selected. In order to better demonstrate and clarify the effect of high temperatures on e.g. forces one should 

consider carrying out experiments also in classical cold hypersonic wind tunnels using the same models. The activity shall 

include: well characterized ground based hypersonic facilities, improved nozzle calibrations thanks to the development of 

advanced instrumentation enabling full hypersonic free stream nozzle calibration; testing of the EXPERT and HAlIS 

configuration in these high enthalpy facilities will provide a unique opportunity to study real gas effects thereby consolidating 

the uncertainties associated with windtunnel to flight extrapolation and scaling. 

Deliverables: 

Facilities characterization. Improved nozzle calibrations. 


all re-entry missions; launcher, 


exploration, .. 




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Title: 

98/YPE01 

SMART- 1 EPS Flight Equipment 

The Electric Propulsion Subsystem (EPS) provides primary propulsion onboard of the ESA SMART-1 spacecraft, which is the 

first of the Small Missions for Advanced Research and Technology (SMART) in the ESA Horizon 2000 plan. The EPS is 

supposed to demonstrate the use of electric propulsion as a primary source and under variable input power conditions. 

The EPS is composed primarily of a Xenon storage tank, a pressure regulation unit, a flow control unit, a power processing 

and control unit, propellant pipework, electrical harnesses, and electric thruster(s). The thrusters that can either be gridded ion 

thruster(s) or a Hall plasma thruster(s), The thruster alignment mechanism is not included and is under the direct responsibility 

of the SMART-1 Prime Contractor. In addition to the delivery of the SMART-1 EPS hardware, the contract includes also the 

assembly, the integration, the verification, on the spacecraft, as well as the support to the Prime Contractor for the 

environmental testing and flight operation support. This procurement is to be placed in one single stage starting from the 

development phase up to the flight phase. The design definition study phase has been performed at ESA and has been used 

to prepare the EPS technical specifications, which are part of the Request For Proposal (RFP). The SMART-1 design is based 

largely on existing electric propulsion system, currently developed for North-South station keeping of Geostationary 

telecommunication satellites. The development required is therefore limited to the adaptation of an existing system to the 

SMART-1 needs as specified in the technical specification. 

The activity was initiated in the frame of a previous TRP workplan. The current activity will cover an additional work package. 

Deliverables: 

Demonstrator; Technical Report 







TRP Reference: GAD 3.10 

Title: 

Investigation Into MEMS - MEOMS Packaging 

Micro Electronic Mechanical Systems (MEMS), commonly called micro-machines, are micron-sized devices that can sense or 

manipulate the physical world. MEMS are actual mechanical systems that are created via a process called micro machining. 

Due to the growing demand of miniaturised components, manufacturers are being forced to come up with technological 

breakthroughs in order to satisfy this demand. MEMS are a combination of mechanical and electrical features in a very small 

package. 

MEMS are used in medicine, transportation, industrial and consumer products, and most commonly for accelerometers in 

automotive air bags. The rapid increase in demand for communications has promoted the development of optical switching 

applications where high-speed broadband networks, expanding service capabilities, are needed, thus leading to the Micro 

Optical Electronic Machines (MOEMs). These need both improved optical and electrical interfaces as well as more 

time-efficient ways to make fiber connections. This is driving the need for new packaging solutions. Protection is a key 

element in packaging MEMS and MOEMs because corrosion, moisture, and debris can prevent the devices from working. 

Each device must be hermetically sealed in order to prevent the devices from becoming contaminated. The proposed activity 

will investigate the MEMS – MEOMS Packaging technologies. 

Deliverables: 

Technology assessment. 

Current TRL: TRL2-3 Target TRL: TRL5-6 Application Need/Date: TRL5/6 by 2008 

Application/Mission: all missions Contract Duration: 24 month 




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MPC-842 

Title: Green Propellants Phase 2 

The present activity is the phase 2 of a wider study aiming at providing information / data to support a decision on future 

investments in the technology of non toxic propellants to support decisions on possible hardware development initiatives. 

During phase 1 a compilation and synthesis of knowledge related to the use of green propellants and identification of open 

technological issues requiring further investigations was undertaken. 

The complete study (Ph.1&2) includes the analysis of the potential application of non toxic propellants for spacecraft and 

upper stage propulsion and resulting technological needs; it addresses cost-effectiveness and quality issues and involves 

proof of concept experimental investigations. 

In order to maximize the effectiveness and broadness of the study, the Ph.1 of the project has been carried out in parallel with 

two different companies. Owing to the encouraging results of Ph.1 and in order to exploit to the outmost the potential of the 

two involved contractors, the Ph.2 will be carried out by both companies teamed up. 

Based on the conclusions of Ph.1 which lead to the selection of attractive propellant combinations, the Ph.2 focus will be on 

the improvement of the basic knowledge aspects, (e.g. performance, ignition, combustion characterisation, material 

compatibility, sooting) through experimental/test activities using European test benches (ONERA, DLR, TUM) as well as study 

activities (definition of engine concepts, updating of Ph.1 critical technologies in light of test results) of LOX and N2O 

combined with Propane, Propylene and MAPP. 

Deliverables: 

Technical Note. Proof of concept experimental investigations (lab. Level). 







Title: 

MPC-850 

Hydrogen Storage Technologies 

Deliverables: 







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Title: 

MPE-878 

New Grid System for Ion Engines (additional activities) 

Deliverables: 








Title: 

Development of a High Thrust Density cusped Plasma Thruster 

The Highly Efficient Multistage Plasma Thruster (HEMPT) has demonstrated an excellent confinement of the plasma within 

the ceramic channel walls by means of permanent periodic magnetic multi cusp field system that reduces essentially the 

ceramic wall losses and erosion. This activity shall investigate the potential of this technology for high power thrusters and will 

focus on the following tasks: Phase I: Interface Definition and Functional Optimization on Prototypes. The Contractor shall 

create a functional analytical and numerical model of the thruster. The Contractor shall define as simple as possible 

mechanical, electrical, and thermal interfaces for the thruster with self-contained heat evacuation capability. The Contractor 

shall confirm the design and functional potential for very substantial mass and cost reduction for thruster and associated 

subsystem units. The Contractor shall optimize the thruster design through definition and realization of performance test 

campaigns on an evolving series of demonstrators. Phase II: Characterization and Design demonstration on Models. The 

Contractor shall assess the widest operational range w.r.t. thrust and specific impulse. The Contractor shall demonstrate the 

functional analyses with test results. The contractor shall quantify the thruster operation reliability, the performance stability, 

and the lifetime capability. The Contractor shall define and perform an environmental test program on engineering models to 

verify their engineering design compatibility with overall launch and flight conditions. 

Deliverables: 

Technical note/Breadboarding/Test results for at least one HEMPT (capable to operate at thrusts higher than 300mN and 

lower than 1N). 


Exploration and science missions 

Application/Mission: (>2012) will be the main objectives for Contract Duration: 24 months 

this technology 




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Title: 

T505-09MP 

Hall-effect Thruster with Multi-Sectional Conductive Walls 

An interesting approach to enhance HET efficiency consists in an innovative discharge channel architecture based on 

segmented conducting walls. A variable channel width can contribute to decrease the ion losses at the walls and improve the 

ion flow focusing (reducing erosion and sputtering problems), while the use of conductive materials with low secondary 

electron emission yield (with respect to more traditional ceramic insulators) can lead to significant increases of thruster 

efficiency (up to 80%, especially for high discharge voltages). The Contractor shall design a high-power HET with a 

multi-segmented (at least three) conductive channel. In addition, the Contractor shall improve the control of the potential along 

the channel, either by changing the relative position of the conductive floating sections to the distribution of the magnetic field, 

or by imposing with external power supplies their electric potential. This can contribute to reduce the beam divergence and the 

near-wall potential drop, responsible for channel sputtering and erosion. The Contractor shall also incorporate a modular 

magnetic system to be able to optimise the magnetic configuration. The Contractor shall manufacture a prototype a perform a 

complete characterisation test campaign and determine the operational limits of the technology. The Contractor shall 

instrument the test facility to be able to quantify the decrease of erosion with respect to standard discharge channels. 

Deliverables: 

Functional Design Assessment and Justification Report. Design document for a high-power HET with multi-segmented 

conductive channel. Demonstrator Characterisation. 


High power telecommunication missions 

(>2012) and interplanetary missions for 


Exploration and science (>2012) will be 


the main objectives for this technology. 





Title: 

Development of advanced EP Thruster characterisation diagnostics 

The objectives of the proposed activity are to develop and test Telemicroscopy and Thermographic diagnostic systems 

capable of being used for both Hall-effect oftware and Gridded ion engine systems operating with variable Isp and 

propellants. In addition to the diagnostics analysis techniques/software tools are also required for the interpretation of test 

data. This activity will be accomplished in two phases: Phase 1: Design and development of diagnostics; telemicroscopy 

diagnostic design and demonstrator manufacture; thermographic diagnostic design and demonstrator manufacture; 

Development of data analysis techniques/SW. Phase 2: Experimental characterisation of HET and Gridded thrusters; 

Experimental characterisation of HET/GIE Software in number of European facilities; Analysis of results and comparison 

between facilities. 

Deliverables: 

Advanced diagnostic systems and tools ready to be used in European EP test facilities. 


Application/Mission: All missions using EP thrusters Contract Duration: 18 months 




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Title: 

T601-17MP 

Development of a Circular Slit Field Emission Thruster 

Slit emitter field-emission electric propulsion systems have significantly improved their performances in terms of controllability 

and reliability over the last few decades. The desired higher emission levels would require a 25cm total slit. This considerable 

length can be achieved either with a cluster of several short linear emitters, or developing a single circular emitter with a radius 

of about 4cm. The circular configuration would present several advantages. First of all, it would eliminate emission wing 

effects; these perturbations were observed since the earlier works on field-emission, and counteracting measures were taken 

introducing field suppressors or complex compensating negative electrode geometries. A co-axial configuration would 

certainly enhance thrust homogeneity and help localizing the thrust vector. Besides, the assembly would be more compact, 

and the localization of the various subcomponents (heater, reservoir and feeding lines) could be optimised. Finally, the 

neutralizer could be ideally placed on the center axis of the oftware , thus providing optimal neutralization of the ion beam and 

reduced divergence angles. The purpose of the proposed activity is: Assess the technological complexity involved in the 

manufacturing and machining process of a 1um wide, 25cm long circular slit emitter; Design a complete circular slit 5mN 

FEEP assembly (including neutralizer); Manufacture a breadboard model; Perform a complete characterization test campaign. 

Deliverables: 

Technology assessment report. Design report for a 5mN circular slit FEEP model. Thruster breadboard model. 

Characterization test reports. 

Current TRL: TRL1 Target TRL: TRL2-3 Application Need/Date: TRL5 >2009-2010 

Application/Mission: EO, Science, .. Contract Duration: 18 months 





Title: 

Advanced Technologies Demonstrator for Very High-Power Hall-Effect Thrusters 

Future Hall-effect SW (HET) generations are technology limited: magnetic circuit, permanent magnets, high temperature 

materials, erosion resistant discharge channel, etc...Current high-power HET developments could simultaneously benefit from 

these new technologies in terms of mass, volume, lifetime, and performance. This activity will consist on: Phase I: Preliminary 

design of a 25 kW Hall-effect oftware (HET) using available scaling rules based on constant plasma density inside the 

acceleration channel. Functional analyses and performance simulations will be done to generate the expected performance 

envelop in discharge voltage and xenon mass-flow-rate. Based on the results of preliminary mechanical and thermal analyses 

it will be identified the technological improvements that would be required to manufacture and test a realistic 25 kW HET 

demonstrator while minimising mass, volume, and ceramic channel erosion. Phase II: Trading-off the various potential 

technologies and associated manufacturing and assembling issues, solutions to the technological improvements identified in 

Phase I will be proposed. In order to be able to test these new technologies, it is proposed to integrate them a smaller-scale 

SW as a demonstrator (5 kW power level). The use of a smaller demonstrator solves the problem of available vacuum test 

facilities and allows to put forward the added value of these new technologies for current power-class HETs. A specific test 

campaign shall be defined and performed for each of the technologies to be demonstrated. 

Deliverables: 

Technical note (prel. design/performance report and mechanical/thermal analyses for 25 kW HET; critical technol./manuf. 

processes; updated design + critical technol. for 5 kW demonstrator; technology demo test plan/results). Demonstrator. 


High power telecommunication missions 

(>2012) and interplanetary missions for 


Exploration and science (>2012) will be 


the main objectives for this technology. 




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Title: 

T601-42MP 

Development of a fuel/oxidiser compatible diaphragm 

The Propellant Expulsion Device (PED) as an alternative to propellant management device (PMD) shows advantages form 

cost, reliability and general system complexity stand point. Currently such a device is not available in Europe. The interest of 

this new proposal is both in the need to provide European space industry with autonomy with respect to the international 

competition and in the compatibility of the proposed material with both Hydrazine and bi propellants which would provide a full 

H/W commonality between the two main storable propulsion technologies used in Europe.The proposed activity is focused in 

developing a material which is compatible with both hydrazine (N2H4) and its derivatives (MMH, UDMH) and the oxidiser 

(MON, NTO) and it is suitable for manufacturing of diaphragms and bladders for spacecraft. 

Deliverables: 

Demonstration of material formulation feasibility, demonstration of diaphragm manufacturing feasibility and development 

testing. 


All satellites prop. / GMES (e.g. Sentinel 


2,3,4) 



Vessels & High Press Tanks 



Title: 

T608-25QC 

Reliability of MEMS based pressure sensors 

Deliverables: 







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Title: 

T608-27QC 

Methodology for complex Micro-Propulsion Systems Space Validation 

The overall objective of this 12 months preparatory activity is prepare a formal validation/pre-qualification of these complex 

micro-systems via GSTP4 in 2005 by using a representative pre-Qualification Model (pre-QM). The idea is to build a 

consortium regrouping the suppliers of complex micro-systems, the final users and ESA to obtain consensus for approval of 

the approach to be taken for validation/pre-qualification. 

The results of these discussion will be reported in technical documents that will be distributed to other potential interested 

parties like other final users (EADS ST, Alenia, Surrey, ...) or NSAs (SNSB, ASA, ASI, CNES, DLR...) and a Round Table will 

be organised to obtain consensus for approval of the approach to be taken for validation of the complex micro-systems via 

GSTP4 in 2005 and 2006 (Proposals QCT.LM.GSTP05&06). 

Deliverables: 

Process documentation, critical analysis report, test structures description. Evaluation/reliability testing definition, results and 

analysis. Final report. Representative test structures, >1 sample of each critical component. 


Application/Mission: microsatellites Contract Duration: 12 months 





Title: 

Innovative Gas Storage in Satellites 

The overall objective of the proposed work is to develop and verify a Breadboard Demonstrator (BD) for a generic 

compression and storage system for space applications. The compressor is based on metal hydride (MH)technology with 

integrated thermal control system. The system is specifically targeted towards compression and storage for regenerative fuel 

cell systems, but adaptable to other space and terrestrial applications, both for hydrogen, oxygen and other gases where 

compression and storage are required. 

Deliverables: 

Compression & Storage System, Breadboard Demonstrator. 


Application/Mission: Application: all satellites Contract Duration: 18 months 




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MCS-001 

Title: Ultra light Structures - Phase 1 

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 prove 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. 

Deliverables: 

Technical datapackage. Demonstrator. 








Title: Ultra light Structures - Phase 2&3 

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: 

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- 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 prove 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. 

Deliverables: 

Technical datapackage. On-ground breadboard and demonstrator. 


all spacecrafts (next step should be flight 


demonstration) 





Title: 

MCS-002 

Electro Active Polymer Actuator 

Deliverables: 








Title: 

Active Structures for Large Solar Array Panels 

A major challenge in designing structures for large solar arrays is the requirement for high fundamental frequencies and the 

ability to withstand considerable launch loads. The highest stresses in the structure often occur due to resonances in the 

frequency range of the launch loads. Active structures (e.g. actuated by piezo ceramics) can dampen resonances by 

closed-loop control. The objective of this activity is to develop S/A panel structures with closed loop control of their dynamic 

behaviour. 

Deliverables: 

Concepts assessment, trade-off and selection. Detailed design of breadboard control system. Detailed design of breadboard 

model. Manufacturing and performance test of breadboard. Definition of plan for introduction into future projects. Development 

plan. 


solar array structures, other large and 


flexible structures. 






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12/Feb/09 


T601-05MC 

Derivation of satellite equipment design and test specifications from random vibration 

Title: 

environments 

Recent experiences from several ESA satellite projects show that the approach conforming to ECSS standard E-10-03A 

results to requirements frequently contradicting spacecraft hardware measurements. As a result, there is a request from space 

industry and equipment manufacturers that the current approach for the derivation of equipment design and test load 

specifications needs to be reviewed and possibly improved. This is the subject of the proposed activity. The objective is to 

derive an adequate approach for the specification of equipment quasi-static design loads and random vibration test inputs. At 

the same time it will update and improve the currently applied approach derived by Intespace in the 1980’s. This would include 

the establishment of a relevant database containing acoustic test results from various spacecraft projects. Also the new 

approach will be implemented in a user-friendly tool based on e.g. an Excel spreadsheet. Description of sub-activities and 

Planning:1. Review of satellite project documentation concerning acoustic test results. Test data collection and preparation for 

database supporting the spreadsheet application. 2.Implementation of a limited number of complementary panel tests with 

various configurations (e.g. size, mass loading). 3.Development of a rationale for the correlation of equipment unit quasi-static 

design and random vibration test loads. 4. Development of the spreadsheet lay-out (preferably Excel) with a flow chart and a 

self-explaining user guide. Implementation of the calculation process. 5.Rationale for the reliability of the specification with 

probability of the loads compared to the acoustic test data basis. 

Deliverables: 

User guide, design methodology description. 


Application/Mission: all spacecraft/payloads Contract Duration: 12 months 





Title: 

T601-09MC 

Establishment of satellite mechanical shock design and verification guidelines 

In the past several studies have been performed dealing with different aspects of the mechanical shock problems such as 

shock source investigation, shock absorption, shock testing, shock analysis, shock transmission. Although the state of the art 

for shock environment prediction and verification in spacecraft have not yet reached the maturity of other environmental 

disciplines, recent advances in prediction techniques environment verification and test execution bring a better understanding 

of this environment. The experience, gained over the past years, shall be documented as guidelines in order to make this 

expertise available for ESA community. Two guidelines are proposed: - Guideline for shock environment prediction “Establish 

the specification, from LV I/F to unit I/F, resulting in definition of the equipment specification”. –Guideline for the qualification of 

units and for the test execution” Equipment Design verification, including SDRA in support to design / qualification, including 

testing, including correlation and usage of test results for analytical assessments and qualification purpose “In order to get the 

guidelines the following tasks will be done: review of satellite project and study documentation concerning mechanical shock; 

write the handbook’s chapters with comprehensive presentation of available know-how (shock sources, shock transmission, 

equipment sensitivity, shock test facilities, shock specification, shock analysis); and write guidelines/rules and prepare a 

release process for the guidelines/rules (working groups/sessions under control/with ESA/companies experts). 

Deliverables: 

Guidelines / handbook. 

Current TRL: - Target TRL: TRL5 Application Need/Date: TRL5 >2008 

all spacecraft / equipment subject to 


shock tanks 




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Title: 

T601-11MC 

Assessment and Improvement of Dynamic Test Data 

Dynamic testing of spacecraft structures and components plays a crucial role in the qualification of the spacecraft as well as 

the validation of corresponding dynamic models. Recent studies (RTMVI, Real Time Modal Vibration Identification, EDIS, 

Enhancements of Dynamic Identification for Spacecraft) have provided new methods and tools allowing efficient use of test 

data to improve the model validation process by considering base reaction measurements, real-time modal characterization 

and the use of stochastic analysis to introduce inherent uncertainty or scatter in the models. These new methods allow a 

much greater understanding of the model validation process, yet for the moment have focused primarily on the model in terms 

of its capabilities and limitations in representing the physical structure – with little emphasis being placed on the 

representativity of the test data itself. The objective of this study is to assess and improve the quality and representativity of 

test data by introducing a set of testing procedures, methods and controls to be used during test preparation, execution and 

post-test analysis and control. Description of sub-activities: review of state of the art in spacecraft testing; development of 

improved pre-test methodology and procedures; development of improved post-test procedures and data validation methods; 

validation using available spacecraft (“piggyback” application); and final assessment. 

Deliverables: 

Documentation of procedures. 


Application/Mission: all spacecraft subject to vibration testing Contract Duration: 18 months 





Title: 

Random Vibration Environment derivation by Vibro-acoustic simulation 

F.E. & SEA numerical simulations methods have been employed to derive the Random Vibration Environment (g2/Hz & grms) 

at equipment I/F due to the launch acoustic load. Refined methods to derive also the I/F force (N2/Hz & Nrms) are requested 

by Projects in order to avoid both the System over-design and the equipment delta qualification. A parametric analysis, taking 

into account not only the mass but also location, panel configurations, boundary conditions and acoustic parameters, would 

provide higher confidence in typical random vibration specifications. The objective of this activity is the derivation of the 

Random Vibration Environment in terms of I/F acceleration and forces levels due to the Launch Acoustic Load; to provide 

analytical and numerical procedures based on FEA and SEA and design guidelines; the identification of driving parameters by 

analysis; and the definition of correlation procedures with test data. 

Deliverables: 

Documentation of procedures, mathematical models. 


Application/Mission: all spacecraft / equipment. Contract Duration: 18 months 




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Title: 

T601-46MC 

Vibro-Acoustic Analysis & Test methods for Large Deployable Structures 

Classical rigid solar array vibro-acoustic modelling, analysis and test correlation has been developed up to a certain maturity, 

however such methods are not directly transferable to thin film structures, closely packed radiators, SAR antennas etc. and 

hence the vibro-acoustic FEM/BEM analysis, testing and their correlation of large-area light-weight structures need further 

development. The objective of this activity is to define a Finite Element and Boundary Element modelling methodology and 

tuning for mechanical loads applied to thin, flexible deployable structures, studying deterministic and random techniques, 

taking into account fluid structure interactions, non-linear behaviour, effect of thin airgaps, effect of membrane stretching etc; 

and the development of instrumentation techniques for subsystem vibration and acoustic testing. It will also include the testing 

and correlation of a full size structural model, representative of vibro-acoustic parameters. Several tasks have been defined: 

state-of-the-art review on analysis and testing methods; implementation of modelling technique in FEM/BEM code; definition 

of analysis/test methodology; parametric breadboard design and test plan; and analysis, test and correlation of vibration and 

vibroacoustic loads. 

Deliverables: 



solar array structures, deployable 

Application/Mission: radiator structures, deployable flat Contract Duration: 18 months 

antenna structures etc. 





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12/Feb/09 


T601-50MC 

Advancement in Thermo-Elastic Distortion Verification Methods for spacecraft 

Title: 

structures 

The objectives of the proposed activity are the following: 

- Improvement of materials modeling, especially composites and other advanced materials. 

- Improvement of numerical simulation of materials, components and assemblies of structures by using existing FEM software 

tools, but including in the mathematical models the specific aspects of materials and components. This shall consider 

non-linear and stochastic analysis. 

- Application of new measurement and monitoring techniques, such as ESPI (Speckle interferometry), laser radar and optical 

fibre sensing (Bragg grating), thermography... 

The activity will consist of two phases: 

Phase 1 

- short review of current state of the art with regard to analysis, control and test methods; 

- Modeling of composite materials, components, joints and assemblies. Typical hypothesis, such as the linearity of thermal 

expansion, shall be investigated, as well as the effects of anisotropy and large temperature ranges; 

- Measurement of material properties on coupons, including expansion coefficients, stiffness, thermal conductivity and all 

relevant parameters identified previously; 

- Verification of simulation tools and methods on coupons and joints; 

- Establishment of measurement uncertainty requirements and stochastic character of simulation tools; 

- Establish guidelines for predicting thermo-elastic distortions. In addition to methodologies for improved modeling, these 

guidelines shall also consider making recommendations on the need to perform material and component level tests; 

Phase 2 

- Definition of a breadboard representative of the complexity of a scientific instrument. 

- Modeling and prediction. 

- Stochastic (and non-linear) analysis 

- Definition of test set-up and selection of measurement technique 

- Correlation 

Where necessary, updating of guidelines established in Phase-1, and extension of guidelines to include recommendations on 

performance of system level test verification methods. 

Deliverables: 

Design and verification guidelines; test coupons and breadboard; modeling procedures. 


Application/Mission: Engineering tools applicable to all S/C Contract Duration: 24 months 






Title: 

Non-Contact Measurements of Membranes 

Inflatable Space Structures very often include a stretched membrane. Static and dynamic measurements of such membranes 

during testing remain a challenge due to detrimental added mass and stiffness of the classical instrumentation. The objective 

is to develop a non-contact method for measuring static and dynamic shapes of membrane spacecraft structures. This implies 

the review and evaluation of available methods; the selection and development of an innovative method; the demonstration on 

a breadboard model. 

Deliverables: 




thin membrane structures, including 

inflatable structures (e.g. schields, 

booms, solar sail); EO/Sci missions. 


12 months 




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T605-12MC 

Improvement of force limited vibration testing methods for equipment/instrument unit 

Title: 

mechanical verification 

The mechanical vibration testing approaches (sine and random) currently applied to satellite equipment / instrument units are 

in general very conservative and might result to severe over-testing of the units compared to real flight environments. The 

reasons for this are the different interface conditions applicable to the system and the test configuration (when the unit is 

hard-mounted to the shaker table). Consequently these test approaches lead also to over-design of the units and therefore 

significant mass penalties. Force limited vibration testing has been intensively investigated in NASA since many years. The 

methods aim at establishing interface force estimates for the case when the unit is mounted on a flexible satellite support 

structure rather than the shaker and to limit the test input for the unit test to these force estimates. The experiences in force 

limited vibration testing are still very limited in Europe. Further investigations of this subject should increase the relevant 

knowledge base and should contribute to the establishment of an ESA mechanical testing handbook covering the specific 

aspects of force limited vibration testing. The objectives are to investigate the influence of the support structure mechanical 

impedance on the random vibration environment and the execution of unit random vibration test on electro-dynamic shakers; 

to identify relevant methods to more accurately derive the interface force limits (e.g. direct measurement at system level, 

semi-empirical, analytical) and to assess their respective accuracy; to develop simplified but nevertheless adequate models 

for the simulation of coupled system conditions; to verify the developed approaches by analytical and experimental means 

(representative of existing equipment structures) and to establish the relevant input for the ESA Mechanical Testing 

Handbook. 

Deliverables: 

Technical notes (incl. identification of methods to more accurately derive the interface force limits, models for the simulation of 

coupled system conditions, verification of the developed approaches by analytical and experimental means). 

Current TRL: 

Target TRL: 

Application Need/Date: TRL5 (operational method) 

TRL2 

TRL3 

by 2008 

Application/Mission: Engineering toolsapplicable to all S/C Contract Duration: 18 months 





Title: 

T605-20MC 

Advancement of Mechanical Verification Methods for non-linear spacecraft structures 

For the purpose of spacecraft structure design development and verification by analysis the structures are in general a-priori 

assumed to behave linear. Analytical predictions include static & dynamic analyses at satellite level but also launcher/satellite 

coupled dynamic loads analyses (CLA) to predict flight loads for specific satellite configurations. However, experience has 

shown that spacecraft structures can exhibit highly non-linear behaviour (e.g. due to backlash, joint gapping, rattling) and the 

consequences of their dynamic effects can significantly affect the design verification procedures, in particular: to properly 

evaluate flights loads with linearised models used in the CLA; the general performance of dynamic verification tests; to 

demonstrate adequate coverage of non-linear dynamic effects in satellite verification tests. As a result, the presence of such 

effects in spacecraft structures increases significantly the complexity of the mechanical verification process (analysis and 

testing).The main objectives of this activity are: to review satellite design and verification test documentation in order to 

identify relevant structure verification problems related to non-linear dynamic effects; to develop strategies for handling 

non-linear dynamic effects within linear CLA models and to adequately convert the related CLA predictions into dynamic 

verification test specifications; to analytically investigate the impact of spacecraft structure non-linearities on the verification 

test performance (including non-linear dynamic effects resulting from e.g. shaker); to verify the proposed approaches with a 

bread-board model (using available space hardware as far as possible); and to finally establish guidelines and 

recommendations for the identification of potential structural non-linearities, the assessment of their effects and how to treat 

them during the spacecraft structure design and development and the verification test phase. 

Deliverables: 



Application/Mission: Engineering tools applicable to all S/C Contract Duration: 20 months 





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Title: 

MCT-694 

MST Compressor for JT cooler 

Deliverables: 







TRP Reference: MCT-698 

Title: 

Mini And Micro Heat Pipes 

In order to reduce volume and mass, there is a clear tendency for S/C electronics to go to denser packing of high dissipating 

units, while at the same time the heat dissipation of such units increases. To avoid hot spots, to optimise the thermal design 

and to keep the junction temperatures of critical components within acceptable limits, the use of mini & micro heat pipes can 

greatly improve the thermal design. For terrestrial applications the use of mini and micro heat pipes has shown to strongly 

improve the thermal design of electronic components (e.g. laptops, amplifiers). Such mini and micro heat pipes are judged to 

also be very beneficial for the thermal design of spacecraft units (e.g. high dissipating electronic units) and mini/nano satellites 

where small high-efficient thermal devices will allow to improve and optimise the design. The objective of this activity is to 

develop mini/micro heat pipes for use onboard spacecraft, taking advantage of the terrestrial heritage to the maximum extent 

possible; to build heat pipe demonstrators and to submit them to a full performance test programme. 

Deliverables: 

Fully tested heat pipe demonstrators with associated technical documentation. 


High dissipating units on S/C (telecom, 

Application/Mission: EO, science); minisatellites; small telecm Contract Duration: 24 months 

platform. 




Heat Pipes & Two phase loops 

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Title: 

MCT-700 

Regenerator Technology for 10-100K Stirling and Pulse Tube Coolers 

Deliverables: 







TRP Reference: MCT-701 

Title: 

Maxi compressor for low temperature cooler 

Objective of the proposed activity is the development of a compressor compatible with the 10K cooler and various other 

coolers. 

A demonstration model of the 10K Cold-finger has already been developed by Astrium UK for the US Air Force, using up to 

now 4 existing compressors. However for space applications, one large single compressor is required. 

The proposed compressor will be based on the design for the Miniature Pulse Tube cooler compressor currently developed by 

Astrium/RAL. The activity will cover the design, manufacture and test of a breadboard model of a large cooler compressor. 

The build standard will be such as to support full performance evaluation and verify capability to survive launch and operate in 

either a Space Station or satellite environment. 

The possible utilization of this large compressor goes beyond the 10K Cooler, as an example it can also work as a basis for 

other systems, e.g. a Large Heat Lift Pulse Tube cooler. 

The proposed activity will be followed by a 400kE GSTP project, called “Development of a 10K Cooler EQM”, referred to as 

G00/B46.MCT-003, aiming at developing a 6-10K cooler, with a cooling power of 45 mW at 10K and a zero load temperature 

of 6K (goal 4K). This latter activity will be based on the previous developments of the proposed Maxi Compressor and the 

previous work on 10K coolers. Future Earth Observation and Scientific instruments (e.g. XEUS) will benefit from this project. 

Deliverables: 

Technical datapackage (design, manufacture and test). Breadboard model of a large cooler compressor. 


cooling of science and earth observation 

instruments as well as of future 


telecommunication payloads 


(Superconductor applications) 




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12/Feb/09 


Title: 

MCV-882 

Thermal Concept Design Tool 

Deliverables: 




SW Clause : Open Source Code Dossier0 Ref.: 




Title: 

Novel, Composite Wicks (for two-phase loops) 

The present generation of capillary wicks used in two-phase loops suffer from a number of limitations. It is therefore necessary 

to improve the wick design by looking into new methods to produce wick structures (e.g. based on the lost wax method), to 

develop methods to reach a graded porosity wick or to investigate methods to produce composite wicks consisting of e.g. an 

outer layer of fine pore size metallic wick with an inner core of plastic wick assuring a thermal decoupling. Based on such 

novel type wicks, current limitations of two-phase loops (limited pumping capabilities under 1-g, need for subcooling, etc.) can 

be solved. This activity will develop novel types of wick structure for the next generation two-phase loops, perform an 

extensive trade-off taking into account all possible wick materials and wick producing methods, supported by experimental 

activities, and test selected wick structures in a realistic two-phase loop. 

Deliverables: 

Established manufacturing method for novel wicks, tested wick structures, associated documentation. 

Current TRL: TRL1-2 Target TRL: TRL4-5 Application Need/Date: TRL5 >2009 

Application/Mission: Telecom, EO, Science Contract Duration: 24 months 





Title: 

Cryogenic Harness for Detector Arrays 

There is a major need to reduce the cryogenic cooling power needed by a detector array, leading to significant reductions in 

payload mass, power and complexity. This in turn leads to a corresponding reduction in the susceptibility of detector arrays to 

EMI and microphonics. Current cryogenic harnesses have a number of problems. The electrical requirements on future 

harnesses will be the same as for current ones. However, new harnesses will need to carry much larger numbers of signals, 

and have higher immunity to the presence of magnetic fields. In addition, there has been no significant attempt to model the 

harness architecture and accurately predict the coupled electromagnetic and thermal performance of the harness. This activity 

focus on the design, development and testing of a cryogenic harness using new materials and manufacturing techniques. It 

will also develop an electrical/thermal model to support the design. The final harness will also be tested with S-Cam 4 at 

ESTEC. 

Deliverables: 

Fully tested harness plus associated documentation, delivered for further testing with S-Cam 4 at ESTEC SCI. 

Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: TRL5




12/Feb/09 



Title: 

03/QCT-001 

Evaluation Thermistors 

Deliverables: 







TRP Reference: GAD 2.06 A 

Title: 

Design And Evaluation Initiative For Rad Tolerant Components 

ST Microelectronics has been for long the leading European manufacturer for space qualified radiation tolerant standard logic 

products. In order to make use of their far greater technological capabilities being among the top 10 semiconductor 

manufacturers world wide, this initiative shall support the evaluation of commercial technologies & processes in the ST 

foundry and the radiation hardening of a series of selected linear and digital components currently unavailable as space level 

product from European sources. 

Deliverables: 

Samples. Technical note, test results. 






TRP Reference: GAD 2.06.D 

Title: 

Study Of RF Compression & Overdrive on Components 

The objective of this activity will be to get a better understanding of the effect of RF overdrive and compression on microwave 

devices, identify derating recommendations and derive safe operating area for some European devices. To this end, a set of 

RF life testing will be carried out, associated with advanced electrical characterisation and in-situ monitoring. Modeling of the 

effect and degradation mechanism will be contemplated. 

Deliverables: 

Samples, test results, derating requirements, procurement specifications 






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Title: 

Testing of Chip Scale Package (CSP) 

Deliverables: 








Title: 

HDI demonstration Module with CSP / ECR32 MCM Validation 

Deliverables: 








Title: 

QCA-004 

Utilisation of the Proton Irradiation Facility (PIF) for Components Studies 

Deliverables: 






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12/Feb/09 


Title: 

QCA-005 

Utilisation of the Radiation Effects Facility (RADEXF) for Components Studies 

The Heavy Ion Irradiation Facility (JYFL) at the Department of Physics of the University of Jyväskylä, Finland, has been 

utilised by ESA for several extended radiation test campaigns in the last years. First to determine the principle capabilities 

and suitability of this facility to support irradiation tests on EEE components and then in a comparative programme to perform 

a correlation between several European and US accelerator facilities. These test campaigns have been increasingly 

successful and productive, confirming its high energy beam quality and usefulness for EEE component testing. Following the 

approach established for other ESA radiation test facilities (HIF (B) and PIF (CH)) it is proposed to utilise JYFL as a state of 

the art test facility providing urgently needed complementary test capabilities and additional test capacity to ESA and the 

European Space Industry. 

After a short (1 year) set-up phase JYFL shall provide under the proposed contract (five years contract, 110kE/year) at least 

480 hours of beam time per year specifically for the characterisation and testing of EEE components. This shall include the 

cost of 240 hours of priority beam time for ESA, associated support, maintenance and nominal test area upgrades. These 

240 hours will be primarily utilised by TRP activities related to component research and development. In addition it will 

reserve a minimum of 240 hours of extra beam time for ESA projects and European Space Industry users at preferential 

hourly rates (subject to separate purchase orders). 

Deliverables: 





N/A 


TRP Reference: QCT-006 

Title: Component for high power conditioning applications (SiC, GaN, ) 

Deliverables: 







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12/Feb/09 


Title: 

T608-01QC 

Radiation Test methodology for Optocouplers Devices for Space Applications 

Following the results of the "opto2000" study, several unresolved issues need to be further investigated: identification of the 

main degradation mechanism in the different parts of the optocoupler; identification of possible annealing effects in 

non-ionizing degradations; and comparison between protons and sequential neutrons/dose irradiations on the same devices. 

Deliverables: 

Documentation and reports. 






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12/Feb/09 


Title: 

T608-05QM 

Carbon Nanotube based composite Material 

Nanotubes have many potential applications, making use of either 1 individual nanotube (electronic device) or an important 

amount of nanotubes (thermal, electrical, mechanical applications). Taking into account that mastering the distribution of the 

nanotube will enable many of the potential applications and that distributing nanotubes is a pre-requisite for any other 

application, this study aims at developing means to: a) Distribute evenly small volume fraction of nanotubes into a matrix 

(random orientation). This would increase cristallinity of a resin, strengthen a metal or bridge micro-cracks in a ceramic. b) 

Align high volume fraction of nanotubes into a matrix. Very high specific mechanical properties, very high thermal 

conductivity... could be achieved with such materials. The matrix could possibly be organic, metallic or even ceramic. The 

adequate distribution of the nanotubes will be assessed by microstructural investigation, elastic constant measurement, depth 

sensing indentation, electrical conductivity, coefficient of thermal expansion or any other suitable indirect measurement 

method. 

Deliverables: 

Technical notes; Samples of evenly distributed nanotubes into a matrix; Sample of aligned nanotubes (into or out of a matrix). 


high demanding applications (structural, 


thermal, electrical) 





Title: 

Carbon Nanotube based composite Material: additional testing 

Nanotubes have many potential applications, making use of either 1 individual nanotube (electronic device) or an important 

amount of nanotubes (thermal, electrical, mechanical applications). Activity T608-05QM aims at developing means to: a) 

Distribute evenly small volume fraction of nanotubes into a matrix (random orientation). b) Align high volume fraction of 

nanotubes into a matrix. The original activity budget allowed only 2 materials to be investigated. However, the first phase of 

the contract has shown that this is insufficient, due to the large number of candidate materials. Therefore, a first CCN has 

been placed to perform evaluation and characterisation of a third material. In addition, a second CCN is proposed to work on 

the processing of SiC matrix reinforced with carbon nanotubes and address the possibility offered by the high electrical 

conductivity measured. 

Deliverables: 

Technical notes; Samples of evenly distributed nanotubes into a matrix; Sample of aligned nanotubes (into or out of a matrix); 

SiC matrix reinforced with carbon nanotubes. 


High demanding applications (structural, 


thermal, electrical) 




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Title: 

T608-24QC 

WALES: Wafer Level Encapsulation for micro-Systems 

WALES Wafer Level Encapsulation for micro-Systems will first address the possible lid materials to be used for 0-level 

packaging (or equivalent lid material when no formal lid is expected). Associated mounting/gluing/soldering techniques and 

interfacing materials (solder, polymers) will be reviewed and selected. This exercise will de done both for Non-RF 

micro-systems and for the specific case of RF MEMS for which packaging is known to have significant influence on the device 

performance. 

Last but not least, WALES will assess the need for associated getters to be processed or reported during wafer level 

encapsulation. The contractor will perform a survey to identify and justify the need for getter, the types of micro-system 

requiring such getter will be listed as well as the type of getter needed and solutions on how to procure/process and 

implement this getter into the 0-level encapsulation. Demonstration by minimum processing will be required. 

Deliverables: 

Documentation (0-level packaging concept, lid, assembly materials for RF/non-RF systems). >20 wafer-level packaged 

devices (10 RF, 10 Non-RF, 5 from each fabrication batch); >3 samples of a wafer-level packaged micro-system containing a 

getter. 







Title: 

MEMSRAD: MEMS sensitivity to space RADiation 

The work to be carried out during MEMSRAD will be split into 3 separate sub-tasks to be performed. The first responsibility 

will be to write the basic requirements for testing MEMS devices. Both MOTS (MEMS Off The Shelf) and micro-systems still in 

the open research shall be addressed. The purpose of this specification is to define the requirements for testing 

semiconductor based MEMS devices, including sensing elements and microelectronic circuits. The scope includes detailed 

discussion of the charged particle environment in space, the physics of radiation effects on MEMS devices and materials, 

including Total Ionising Dose (TID) effects, Single Event Effects (SEE) and displacement damage effects. The outcome of this 

work will result in a general radiation evaluation guideline. However, because the different requirements of each project give 

rise to very different guidelines, no attempt shall be made here to specify or quantify formal technical requirements in terms of 

radiation tolerance and associated pass/fail criteria. This document shall contain information regarding radiation effects 

prediction and general radiation test methods related to the MEMS. The document shall be submitted to industry, other NSAs, 

research centres for approval. A one-day Round Table shall be organised to discuss the document and obtain consensus for 

approval. ESA will then decide how this document shall be formalised (ESCC specification or ECSS Level 3). 

Deliverables: 

Draft Guidelines for MEMS radiation testing requirements, test campaigns plans/reports. Public./present. at radiation/MEMS 

workshop/conferences (RADECS, NSREC, ESA MNT Round table...). Prep./implem. of obtained results on ESCIES. Final 

Report. 

Current TRL: TRL2 Target TRL: TRL4 Application Need/Date: N/A 





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Title: 

T608-29QC 

Radiation testing of candidate microelectronic components for space applications 

Radiation Effects on semiconductor components are process and design dependent. New component types and 

representative test structures for new process technologies or incorporating novel design techniques are tested in ground 

facilities for their behaviour under the influence of radiation. 

Deliverables: 

Radiation test data on Single Event Effects, Total Ionising Dose and Displacement Damage Susceptibility of semiconductor 

components foreseen for space applications. Associated test methods and capabilities. 






TRP Reference: T608-34QM 

Title: 

Performance benchmarking of European GaN epitaxial wafer suppliers 

The objective of this activity is the assessment and benchmark comparison of the RF and reliability performance of GaN 

HEMTs manufactured using European epitaxial wafer sources. 

GaN is a strategic technology that has the potential to revolutionise next generation space based payloads. Applications 

include miniaturised high power electronic equipments (e.g. solid state power amplifiers, X-ray detectors, highly robust 

receiver front-ends, local oscillator sources for mm-wave/sub mm-wave radiometers) that are capable of operating at extreme 

temperatures or in harsh environments. The availability of high quality epitaxial wafer material is a prerequisite for producing 

high performance devices. ESA has previously funded epitaxial wafer development work through IMEC (Athena and Epi-GaN 

programmes). An independent assessment and benchmarking exercise is now needed to assess the performance of IMEC 

material against other European suppliers. This will allow ESA to prioritise future investments needed to establish a European 

supply chain for GaN component technology. 

It is hence proposed for this activity that GaN epitaxial wafers (fabricated on SiC substrates) will be procured from European 

suppliers and from a state of art US/Japanese source to allow comparison of wafer performance within Europe and the rest of 

the world. Device fabrication will be undertaken by a single company using a common process control monitor and transistor 

test mask for each wafer. DC measurements and RF measurements (small signal and large signal) will then be made to 

derive basic performance parameters. This will be followed by a preliminary reliability assessment, with the aim of identifying 

likely causes of failure mechanisms. Upon completion, this work will allow identification of the optimum wafer supply route 

within Europe and allow ESA to independently assess the performance of the epitaxy suppliers in Europe. The data gathered 

from this work will be used to launch a major reliability improvement and technology transfer initiative involving manufacturing 

industry. Therefore this proposed TRP activity will form the foundation route for establishing a space qualified GaN component 

supply chain by 2009-2010. The following tasks are foreseen: 

1.- Wafer procurement and test mask design; 2.- Device processing; 3.- DC and RF assessment; 4.- Preliminary reliability 

assessment; 5.- Analysis and benchmarking of results. 

Deliverables: 

Hardware samples, test results, technical notes comparing and contrasting the results obtained from European epitaxial wafer 

suppliers. Requirements specification for Wafer supplies to target. 

Current TRL: TRL2 Target TRL: TRL5 Application Need/Date: TRL5 =< 2009 

Supported through CTB microwave 

Application/Mission: Contract Duration: Contract duration 12 months 

component work 




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Title: 

T608-36QC 

SRAM based FPGA for space applications 

Contrary to antifuse type Field Programmable Gate Arrays (FPGA), SRAM based types offer the possibility of in-system 

reconfiguration. Radiation hardened FPGA types using SRAM based configuration programming are currently being 

introduced /developed for space applications by the European manufacturer Atmel. While the prospects of exploiting this 

additional flexibility potential for re-configurable payload systems are seriously being considered there is still very limited 

experience with the safe utilisation of these features. This activity shall determine (1) if current Product Assurance 

requirements and practices for on board SW reconfiguration are applicable and sufficient for FPGA configuration data or if 

modified/additional provisions are required and (2) which methods and requirements are applicable to establish conformance 

of specific and dynamic FPGA reconfigurations with fixed system constraints during the application development process. 

The effectiveness of the proposed method(s) and requirements shall be suitably demonstrated. 

Deliverables: 

Study report and draft requirements 

Current TRL: N/A Target TRL: N/A Application Need/Date: TRL8 by 2009-2010 







Study of long term parametric drifts of EEE components for inclusion in component 

Title: 

detail specifications and worst case analysis 

Worst case analysis is a typical requirement of the ESA projects and is based on the known drift of EEE components during 

the mission life. These drifts are important as they help establish the system performance parameters with in the given 

mission profile. However, the attempted to re-validate the current drift values cited in the ESA PPS 01 301 and include these 

in the Worst case analysis standard envisaged that the values listed are based on a series of assumptions and activation 

energies that may not be applicable today. Additionally, as an outcome of an ECSS working group on how to approach the 

calculation of the Worst Case limits, it emerged that, inspite of ESA listing some drift paremeters in their specifications, 

industry wished to use other figures and for some technologies(drift parameters are technology, process and in some cases 

even manufcaturing line dependent) there was no easily obtainable referenece data. With the present activity it is now 

proposed to launch a study that determines what data resides with space/aerospace/automotive/commercial procurement 

agent, user and manufacturer. This study will then take existsing available data and provide clear dirt formulae for use in an 

ECSS standard. In addition where data does not exist it will define the missing program of work. 

Deliverables: 

Technical note (incl. reviewed - consistent - data to submit to ECSS for approval and inclusion in the ESCC abd ECSS 

documents). Work plan for missing data retrieval. 

Current TRL: N/A Target TRL: N/A Application Need/Date: TRL9 by 2010 





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Title: 

T608-38QC 

Survey of available micro and nanotechnology 

Nanotechnology is an advanced technology that has received a lot of attention for its ability to make use of the unique 

properties of nanosized materials. Nanotechnology is capable of manipulating and controlling material structures at the nano 

level (a nanometer is equal to one millionth of a millimeter) and offering unprecedented functions and excellent material 

properties. Nanotechnology consists of the “top-down approach” and the “bottom-up approach.” In the former approach, the 

sophistication of fine processing technologies, such as semiconductor manufacturing, can lead to the processing of nanosized 

fine structures. In the bottom-up approach, self-organization properties inherent in materials can be utilized to assemble 

nanosized fine structures from the atomic or molecular levels. Nanotechnology, including nanostructured material metrology to 

accurately determine physical properties at the nanolevel, is considered a strategic technological area that goes beyond 

conventional technologies, potentially leading to a paradigm shift in new industrial technologies. 

Nanotechnology is regarded world-wide as one of the key technologies of the 21st century. Nanotechnological products and 

processes hold an enormous economic potential for the markets of the future. The production of ever smaller, faster and more 

efficient products with acceptable price-to-performance ratio has become for many industrial branches an increasingly 

important success factor in the international competition. The technological competence in nanotechnology will be a 

compelling condition to compete successfully with better procedures and products on high technology markets in the future. 

Due to its interdisciplinary cross-section character, nanotechnology will affect broad application fields within the ranges of 

chemistry/materials, medicine/life sciences, electonics/information technology, environmental and energy engineering, 

automotive manufacturing as well as optics/analytics and precision engineering in various ways. The convergence of different 

fields like microelectronics, chemistry, physics, and biology will permit to create the emerging nanoscale functions in coming 

years. 

The future European space missions should get benefit of this fantastic 21st century Nanotechnology revolution. In particular 

the future evolutions of the coupling of micro and nano world interdisciplinary applications pushes towards the possibility of 

development of “Smart Systems”. 

The CTB MNT Working Group has proposed to carry out a technology survey on Nanotechnology. The so established position 

paper will be a strategic document for the development of Nanotechnologies for space sector, including the technological and 

industrial perspective, the state of the art outside and inside the space sector, the impacted industrials sectors, the potential 

contribution of nanotechnologies, the axes of collaboration to favour development of nanotechnologies, i.e. technological key 

issues and competence centers well positioned in the field of interest, a “Nanotechnology Roadmap”. 

Major tasks will include: 1.Survey of Nano technologies on : Structural materials, Sensors, Nanoelectronics and Computing; 2. 

Identification of potential applications for space sector: transportation vehicles, space crafts, pay loads, probes, etc.; 3. 

Elaboration of preliminary requirements ; 4. Identification of potential manufacturers for Nano technologies; 5. Establishment 

of First “Nanotechnology Roadmap for European space applications”. 

The roadmap should in particularfocus on short/mid/long term issues. At short mid term (




12/Feb/09 


Title: 

T608-39MC 

Nanotube re-inforced structural materials for spacecraft applications 

With strength and stiffness properties several 100 times better than that of steel and conductivity better than copper, Carbon 

Nanotubes (CNT) have extraordinary intrinsic electrical and mechanical properties making them potentially attractive materials 

for use in lightweight spacecraft structures and subsystems. Research on the possibility of using such materials for improving 

the properties of known materials such as Carbon Fiber Reinforced Plastics (CFRP), has been performed, and the results 

indicate that some improvement is indeed possible. 

The objectives of the proposed activity are to identify and investigate possible improvement of spacecraft structural materials, 

near term as well as long term. For what concerns near term the work shall focus on the reinforcement of the CFRP resin 

material. Realistic improvements shall be defined based on literature data and specially manufactured test samples, and shall 

address improvements related to: 

- tensile, compressive and shear (ILS) strength; 

- stiffness; 

- structural damping; 

- failure mechanisms; 

- conductivity;. 

Relevant manufacturing methodologies shall be investigated and documented. 

For what concerns long term, (>2015) possible applications of CNT in spacecraft structures shall be evaluated. This shall 

include the identification of possible new materials, e.g. development of new CNT reinforced fibres and resins, and their 

possible application areas, including highly loaded spacecraft structures, lightweight flexible deployable and inflatable 

structures, membranes etc. 

In addition, the perspective of availability of CNT for European activities shall be considered taking into account the required 

European non-dependence target, and a related survey document shall be produced. 

Deliverables: 

Overview of CNTs and their application as reinforcing element in CFRP structures, test reports, test specimen. 

Current TRL: TRL1-2 Target TRL: TRL2-3 Application Need/Date: TRL5/6 >2010 

Application/Mission: All spacecraft missions Contract Duration: 18 months 





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12/Feb/09 


Title: 

T608-42ET 

Deep-Sub-Micron ASIC technology assessment and High-Speed-Serial-Links design 


The activity aims at assessing deep submicron (i.e. 90 nm or below) Application-Specific-Integrated-Circuits (ASIC) 

technology with higher density chips and lower power consumption for on-board processing applications. Together with the 

ASICs’ core processing capabilities it is mandatory to improve the efficiency of data transportation (between ASICs, boards 

and equipments) by mean of embedded High-Speed-Serial-Link (HSSL). The design of ~10Gbps HSSLs with the selected 

ASIC process is a contextual objective of this activity. 

The activity shall encompass feasibility study, assessment and trade-offs of the following key issues: 

- Processes trade offs and selection. 

- Radiation evaluation (complementary tests): 1. Heavy ions, heavy protons and total dose effects; 2. SEE and SET 

characterisation; 3. Displacement damage; 4. Radiations effects on high k dielectric. 

- Reliability: 1. Electro migration; 2. Life time. 

- Proposal for hardening techniques in order to cope with radiation and reliability issues: 1. Enhancement at process level; 2. 

Enhancement at layout and cells design level; 3. Identification of the library cells requiring a redesign; 4. Identification of the 

work involved in order to harden the selected cells or eventually design new ones (clock tree buffers …); 5. Assessment CAD 

tool flow to support rad-hard library (hardened clock-tree network, TMR, etc.). 

- High speed serial links: 1. Assessment of the selected process to offer embedded high speed serial links able to provide a 

10 Gbps data rate while minimising power consumption (300mW per transceiver) and area; 2. Performance and architecture 

trade offs; 3. Design of the transceiver IP and implementation of the hardening techniques studied previously; 4. Layout; 5. 

Simulation post layout. 

- Preliminary study to define packaging options. 

- Sustainability of the space business (manufacturing costs, process lifetime, etc.): 1. The manufacturer shall propose a 

business model for future development activities and identify NRE and RE costs; 2. The manufacturer shall propose a 

sustainable model related to space business and guaranty access and support to the technology at fair conditions. 

Deliverables: 

Radiation and reliability reports, design rule recommendations, preliminary design and simulation report on HSSL, roadmap 

for the packaging technology, business model definition. 

Current TRL: TRL2-3 Target TRL: TRL3-4 Application Need/Date: TRL5/6 >2011 











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12/Feb/09 


Title: 

T608-43QC 

GaN Reliability Enhancement and Technology Transfer Initiative (GREAT2) 

An overall strategy paper towards implementing a coherent plan for gallium nitride (GaN) component and technology 

development was presented at the 233rd meeting of the IPC (Ref: ESA/IPC(2006)89). Key to this strategy and the subject of 

this procurement plan is the establishment of an independent European supply chain for GaN microwave power components 

that European space industry can access. 

Gallium nitride is clearly an emerging, but yet immature technology within Europe. At present, there is no commercial GaN 

component supply chain in Europe to satisfy the needs of space industry. The proposed activity is therefore based on a 

step-wise approach, allowing verification and assessment of results. Fundamental is the decision to initially limit the early 

development of materials and device techniques towards microwave payload technology. A further overriding consideration for 

space application is the need to demonstrate and improve the reliability of GaN based devices. The activity will address dual 

objectives: 

• Improvement of GaN device reliability for space application 

• Establishment of an independent European component supply chain for discrete transistors and MMICs. 

This TRP activity is planned to last 2 years and will focus on the required initial characterisation, modelling and process 

developments. These tasks will be supported by a follow on program of work, to be implemented through NewPro (Ref: 

ESA/IPC(2007)75, Activity : NP10-11QC), that will address the establishment of the process demonstration, technology 

industrialisation and performance evaluation. 

The program of work will be broken down into several distinct tasks with phases and a defined target at the end of each 

phase. Continuation through GSTP/NewPro funding will depend upon these TRP targets being met. Table 1 in 

ESA/IPC(2007)75 indicates the program of work, including the planned GSTP/NewPro activities, in order to give a clearer 

overall work break down description. 

Task Breakdown Description for TRP funded work items 

1) Thermal characterisation of GaN devices. 

Accurate measurement of transistor channel temperature is required to derive reliability information and to determine the safe 

operating area for application in space. Infra-red or numerical simulation techniques are commonly used to derive channel 

temperature information and can give inaccurate results due to poor geometrical resolution or inaccurate model parameters. 

The objective of this task is to investigate the use of micro-Raman measurement techniques in order to obtain high accuracy 

channel temperature and electric field measurements for GaN power transistors. 

2) GaN HEMT theoretical modelling and optimisation for space application. 

The objective of this activity is to use Monte-Carlo simulation techniques (or other appropriate modelling tools) to analyse and 

optimise GaN HEMT device performance. After successful “calibration” and agreement with measured results, the intention is 

to use this technique as a predictive tool to guide future device processing and physical structure developments to optimise 

operating frequency, breakdown voltage, output power and reliability. 

3) GaN HEMT design and fabrication for improved reliability. 

At present the reliability of wide bandgap active devices from European sources is unacceptable to allow operation in space. 

This task will undertake iterative, and closely linked, development steps to improve material quality and device design/process 

optimisation along with direct assessment of the effect upon reliability. This approach will allow a feedback loop to be 

established where incremental improvements in reliability are fed back to growth/processing engineers helping to guide further 

process/material improvements as required. This program will demonstrate improved GaN device reliability such that 

acceptably low FIT rates for space based operation are reproducibly achieved. 

4) Space compatible MMIC process technology development. 

The objectives of this work item are to identify the techniques required to enhance the reliability, reproducibility and 

performance of microstrip based GaN MMICs. The improvements will occur through an optimisation of front-side and 

back-side MMIC processing. Failure accelerating conditions and accelerating mechanisms shall be investigated and the 

threshold limits for onset of failure modes identified and eliminated (or managed). This approach will allow identification of the 

optimum processes required to achieve good manufacturing reproducibility and allow the planned production transfer to 

manufacturing industry to occur more rapidly. 

5) Initial developments GaN epitaxy. 

The objective of this task is to develop and implement techniques to (i) assess the quality of substrates procured from external 

sources (prior to commencing GaN epitaxy) and to (ii) characterise “as-grown” epitaxial wafers such that the best wafers can 

be pre-selected prior to commencing device processing. Key objectives are to define the substrate procurement 

specifications, to define the substrate quality assurance metrics and the use of appropriate test methods to measure substrate 

quality. 

Deliverables: 

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12/Feb/09 

1) Device test results, Calibrated channel temperature measurement approach that can be used within GREAT2. 

2) Calibrated device simulations; Recommendations on optimum device structures to concentrate development efforts. 

3) Identification of key parameters effecting reliability; Demonstration of materials growth and processing steps required to 

eliminate failure mechanisms; Discrete power transistor samples. 

4) Establishment of baseline GaN MMIC foundry process; Preliminary PID documentation, Reliability measurement data on 

test characterisation vehicles (TCV’s). 

5) Establishment of substrate and epitaxy specification criteria required for production transfer, implementation of fast and 

non-destructive analysis techniques, technical notes. 

Current TRL: TRL3 Target TRL: TRL4 Application Need/Date: TRL5/6 >2009 

Telecoms, EO, Navigation and Science 


payloads requiring HPA’s 





TRP Reference: T-M-QCT-02-MT 

Title: 

MTSL Lab 

Microelectronics Support Laboratory Frame contract (CCN). 

Deliverables: 

Technical notes, 



SW Clause : - Dossier0 Ref.: N/A 




Title: 

T-S-QCA-02-08 

Utilisation of the Heavy-ion Irradiation Facility (HIF) for Components Studies 

The availability of the Heavy Ion Irradiation Facility has been demonstrated to be of paramount importance for ESA projects 

and the European Space industry as recently again proven by the urgent and successful SEE characterisation of 19 device 

types for the XMM project. ESA’s continuing support of HIF will remain an instrumental asset for the European Space effort. 

The objective of this activity is to maintain, upgrade and keep the HIF operational. To provide 240 hours of free beam time 

per year on a priority basis for the purpose of the ESA lead irradiation campaigns. Additionally, a minimum of 240 hours of 

beam time will be made available to ESA industrial contractors, research institutes and other interested users. All campaigns 

are supported by a qualified physicist and control room staff. A minimum of eight campaigns shall be scheduled per year 

covering four 100-hour periods and four 24-hour periods, more or less evenly spread throughout the year. 

Deliverables: 

Tested samples. Technical note, test results. 






N/A 

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Title: 

T-S-QCT-02-FZ4 

Micro-Optical Electromechanical Systems (MOEMS) Delta Space Qualification 

Methodology (Critical evaluation techniques for micromachined devices) 

Deliverables: 







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12/Feb/09 

6.23 - Materials & Processes 


Title: 

(03/)EEA-002 

Metamaterials for Space 

Deliverables: 








Assessment of the reliability of High Density Integrated Boards (HDIs) for future space 

Title: 

use 

The need for smaller, high performance electronic equipments (higher density, new components) requires new layout with 

finer circuit line, narrow track spacing and thinner copper tracks. Some components can't be today assembled using the 

current design. The HDI technology (50 to 150 mm) will allow using such components. This study will evaluate the feasibility of 

manufacturing reliable HDI boards. In order to do that, the requirements in terms of manufacturing facility to enable the 

fabrication of such boards will be defined and the second part of the activity will demonstrate the concept by performing 

testing on test coupons according to ECSS-Q-70-10. 

Deliverables: 

Feasibility and test reports; HDI boards and application for space use. 


Application/Mission: All projects Contract Duration: 18 months 




N/A 

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12/Feb/09 


T608-12QM 

Study of the impact of the power meshed plane on electromagnetic behaviour of 

Title: 

electronic boards (PCBs). 

To improve the adhesion between the successive layers, and thus the reliability of PCBs, a qualified manufacturer is willing to 

replace full planes by meshed planes in PCBs. These modifications will impact the electromagnetic behaviour of electronic 

equipment. The goal of the study is to evaluate, in large frequency band (up to 3 GHz), the impact of meshed plane on the 

radiated emission, the signal integrity and the crosstalk. The study will consist on a bibliographic research on the topic, an 

experimental study of comparative measurements between configuration with full plane and with meshed plane; and a 

theoretical study in order to modelise the effect of meshed plane on electrical characteristics. 

Deliverables: 

Reports and documentation. 


Application/Mission: All projects Contract Duration: 15 months 




N/A 


Title: 

T608-15QM 

Test and validation of contamination models through ground experiments modeling 

Contamination can have a major detrimental impact on space systems. Its assessment is performed through physical models 

of contaminant emission, transport and effects. At system level contamination can only be assessed through numerical 

modeling, due to the complexity of a whole spacecraft. Unfortunately, the models and numerical tools under use have not yet 

been physically validated. A first reason is the difficulty and cost of flight experiments. A second reason was the inability of the 

old contamination software (ESABASE/OUTGASSING) to model ground experiments. This second problem has now been 

solved by the new software COMOVA, developed in a QMC-EMA mini project which was completed in 2000 (this new code 

also incorporates improved deposition models). It is thus now both possible and necessary to validate this new code and its 

physical models through ground tests. The proposed action consists in:- gathering ground data involving outgassing, 

deposition, re-emission. They can be existing VBQC data (with reemission) or a new dedicated experiment involving more 

complex transport paths.- modelling these ground experiments with COMOVA and comparing data and simulation- improving 

the modelling, either simply by improving the extraction of the deposition and re-emission parameters from basic experiments, 

or if necessary by improved the physical models implemented in COMOVA. 

Deliverables: 

Proposal for ground testing of a complex structure in a large facility; model of the structure outgassing and contamination 

characteristics; test and critical comparison of model and experiment (and adaptation of model if needed). 


modelling contaminants for optical 


satellite, such as GAIA, JWST, AEOLUS 





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Title: 

T608-30QM 

Joining technology to bond Carbon to Carbon in stable sandwich structures 

Selection of a technology to bond Carbon to carbon for ultrastable structure - verification of the soundness of the technology 

at sample level. 

Deliverables: 

Trade off, Technical notes, Test plan, sample manufacturing, test report. 


very stabe structures / optical benches / 

Application/Mission: telescope supports; missions coming Contract Duration: 15 months 

after LISA 





Title: 

Radiation stable optical adhesives 

High-tec., high performance optical adhesive and gluing process for optical assemblies exposed to high intensity radiation 

(visible, IR, UV, X-ray, gamma-ray,...). Typical applications are transparent silicone adhesives in solar cell assemblies (SCA) 

to bond cover glasses onto solar cells. Recent developments in shifting the spectral cut-off of cover glasses to shorter 

wavelength (e.g. CMO) to gain power output of the SCAs, does accelerate the degradation of the adhesive. Moreover there is 

a trend to reduce the thickness of the cover-glass thus increasing penetration of radiation into the adhesive. Currently, only 

one US manufactured adhesive is exhibiting adequate long term stability. The applications are not limited to SCAs, and cover 

any payload that require gluing of optical components that are exposed to high intensity irradiation. 

Deliverables: 

Technical notes, Test plan, sample manufacturing, test report, test samples tested in relevant environment. 


future GEO spacecraft (high power 

output), long lifetime, mass saving 

thanks to thiner coverglasses); 


interplanetary missions (solar panels 


pointing sun >> high intensities); high 

power optical systems 




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