ESA unclassified - For official use ESA/IPC(2013)3,add.5 Att.: … ESAIPC(2013)3,ADD.5-1.pdf · 2014-06-10 · ESA unclassified - For official use ESA/IPC(2013)3,add.5 Att.: Annexes

ESA unclassified - For official use

ESA/IPC(2013)3,add.5 Att.: Annexes Paris, 29 October 2013 (English only)

EUROPEAN SPACE AGENCY

INDUSTRIAL POLICY COMMITTEE

BASIC TECHNOLOGY RESEARCH PROGRAMME

TRP WORK PLAN 2014

The IPC is invited to approve the TRP Work Plan 2014 by simple majority of the

Member States. AT+BE+CH+CZ+DE+DK+ES+FR+FI+GR+IT+IE+LU+NO+NL+PL+PT+RO+SE+UK

SUMMARY

This document is the TRP Work and Procurement Plan for 2014. REQUIRED ACTION

1.- Member States are invited to approve the attached TRP Work Plan 2014. 2.- The Industrial Policy Committee is invited to approve the procurement plan associated to the attached Work Plan (Activities in Annex I identified with the label IPC), based on the descriptions and justifications provided in Annex II.

eCPB-2013-1597

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BASIC TECHNOLOGY RESEARCH PROGRAMME

TRP WORK PLAN 2014

Table of Contents

- Scope - ANNEX I: Detailed TRP Plan 2014 - ANNEX II: Description of the Activities - ANNEX III: Justification for Non-Competitive Tender (if applicable)


SCOPE OF THE DOCUMENT

This document presents the Work Plan of the Basic Technology Research Programme (TRP) for 2014. The TRP Plan 2014 builds upon the Preliminary Selection of Activities document (ESA-IPC(2013)107) presented for information to the 282nd IPC. The plan attached in Annexes I and II has been established as part of the Agency’s end-to-end process for the management of technology development defined in ESA/IPC(2008)61, rev. 1, refined with the lessons learned in the previous exercise and under the supervision of the Directors’ Subcommittee for Technology. Additionally, the justification for direct negotiation is attached in Annex III. The present plan covers the services domains of Earth Observation, Human Spaceflight& Exploration, Space Transportation, Telecommunications, Navigation and Generic Technologies. SD2 and SD9 are presented in separate documents for Cosmic Vision and Mars Robotic Exploration programmes respectively. In application of Council decisions contained in ESA/C(2012)104, the executive undertakes to identify technological activities capable to support the integration of New Member States and of under-returned countries, in view of a structural effect. Some procurement policies could therefore be adapted, and reported to IPC. The IPC is invited to approve the proposed 2014 Work Plan update and the connected procurement actions.


Key to Tables The TRP Workplan for 2014 is presented along the following headings:

– Technologies related to Earth Observation – – Technologies related to Human Spaceflight and Exploration

– Technologies related to Space Transportation & Re-entry Technologies

– Technologies related to Telecommunication

– Technologies related Navigation

– Generic Technologies

Each activity is given a programmatic reference, which will remain unchanged until completion. Additional planning elements associated with each of the activities are: IPC Approval: Status of approval of the corresponding procurement

proposal

YXXXX = Year of approval for workplan activities previously endorsed & corresponding procurement proposals approved (if applicable)

IPC or AC = IPC or AC approval requested

Budget: Budget planned for this activity. Total Contract

Authorisation (CA) values, given in KEURO, at yearly economic conditions.

Procurement Policy:

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

C(1)* = Activities in open competition limited to the non-Large-System Integrators. 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<3) with strong expectations on innovation contents, or to technology spin-in, and when SMEs & R&D organisations have recognised expertise and capabilities in the technology domain. Note: (Otherwise, the bid will not be considered for further evaluation).

C(4)* = Activities in open competition, subject to the SME

subcontracting clause. Note: Bidders are required to do their utmost to include in their bid an adequate participation of SMEs as subcontractor(s) (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)

* See ESA/IPC(2005)87, rev4. Industry has been informed, through the EMITS "News", of the content of that document. In line with the principles of FINPOL reform, and taking into account the outcome of the Interim Review of the geographical distribution of contracts, the Executive will implement all procurement principles agreed upon, including georeturn requirements. In particular, some changes in procurement policies are possible in the frame of the measures necessary to structurally recover georeturn deficits, e.g. by use of the so-called Special Initiative. To this purpose, an extensive review of existing capacities/potentials in all Member States is being conducted.


Activity Template

Together with the activity description the following information is reported: Objectives: Provides short summary of the main goals of the activity. Description: Describes the activity, providing the context information, the

purpose of the activity and the main tasks. Deliverables: Provides short description of the tangible outcome e.g.

breadboard, demonstrator, S/W, test data. A final report is standard for every 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. For S/W and tools separate readiness levels are defined below

Current TRL: Describes the current TRL level of the product that is going to

be developed in this activity. Target TRL: The TRL level expected for the product at the end of the

activity. For equipments TRP usually concludes with TRL 3/4, GSTP at level 5/6. However in the case of components target TRL level in TRP could be higher.

Technology Readiness Level, to be achieved at end of the activity (TRL’s typically targeted by the TRP are shown in bold):

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

Technology Readiness Levels for S/W and tools (TRL’s typically targeted by the TRP are shown in bold):

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.

Duration (Months): Duration of the activity (e.g. 24 month) Reference to ESTER: Identifies the related ESTER Requirement SW clause: 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 respectively, are applicable.

TECHNOLOGY R&D

Innovative/ProspectiveTechnology

Support to Programmes &Generic Technologies

Support to Industry’sCompetitiveness(Short Term)

Research & feasibilitydemonstration predevelopment prequalification

CAT. A

CAT. B

CAT. C

T.R.L. 1-2

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

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

TRP

ESA/NASA Technology Landscape (TRL's)

ESA/IPC(2013)3,add.5

ANNEX I

TRP WORK PLAN

List of Activities

TRP WORK PLAN 2014-2015: Work and Procurement Plan 2014

ANNEX I: List of ActivitiesESA/IPC(2013)3,add.5

1 - Earth Observation

1 - 01 - Microwave Payloads

IPCAppr. TRP Ref. Activity Title Budget (K€) PP Cty

SoftwareClause

ApplicabilityRemarks

Pref. Clausefor Strat.Initiative /

Sp. Measures

2014 2015

T106-401ET Study on future microwave radiometers for atmospheric correction of radaraltimeters on coastal regions 200 C N/A

T106-406ET Ka-band InSAR Front-end Development for Airborne Campaign 350 C N/A

T106-409ET High-performance calibration switch for mm-waves 350 C(1) N/A

T107-407EE Dual polarisation 94 GHz antenna for spaceborne Doppler radar (old title:Dual polarization 94 GHz Antenna for ground based Doppler radar) 300 C(1) N/A Title and scope slightly changed

from preliminary selection.

T107-410EE Frequency Selective Surfaces with improved performance for compact QuasiOptical Networks 400 C(1) N/A

IPC T107-411EE Microstructural origin of electromagnetic signatures in microwaveremote sensing of snow 200 C(3) Open Source

Total 1 - 01 - Microwave Payloads 1800

Page 2 of 20



1 - 02 - Optical Payloads


SoftwareClause



Sp. Measures

2014 2015

IPC T116-405MM NIR immersed grating in transmission for high resolution spectroscopy 600 C(1) N/A

IPC T116-406MM "Smart slit" for next generation high resolution spectrometers 500 C(1) N/A

IPC T117-407MM Complete Large-area MCT SWIR Detector 800 DN/C UK N/ASelex ES (UK).TRP 400 kE and EO IPD 400 kEco-funded activity.

IPC T117-408MM High Performance Silicon Visible Hybrid CMOS Image sensordemonstrator 800 C(1) N/A TRP 400 kE and EO IPD 400 kE

co-funded activity.

IPC T117-411MM Fiber based optical frequency comb at 2 micron for LIDAR applications 500 C(1) N/A TRP 200 kE and EO IPD 300 kEco-funded activity.

Total 1 - 02 - Optical Payloads 3200

1 - 03 - Platforms / Others


SoftwareClause



Sp. Measures

2014 2015

T107-405EE Low-complexity data downlink antenna 300 DN/S IT N/A Università di Siena (IT) and TAS-I(IT)

T118-401MP Assessment of the key aerothermodynamic elements for the realization of aRAM-EP Concept 224 C N/A

T119-402MP Consolidation of mN-FEEP Thruster Performance (mN-FEEP 4) 300 DN/S AT N/A FOTEC (AT)

IPC T123-401QT Investigation and preliminary characterization of component buildingblocks needed to establish a European mm-wave GaN foundry process. 600 C(1) N/A

Total 1 - 03 - Platforms / Others 1424

Page 3 of 20



3 - Human Space Flight and Exploration Preparation

3 - 01 - Robotic Assistance


SoftwareClause



Sp. Measures2014 2015

T313-405MM Localisation of Objects in Space through rf Tags (LOST) 300 C(1) N/A

T313-407MM Adaptable Wheels for Exploration (AWE) 450 C(1) N/A

Total 3 - 01 - Robotic Assistance 750

3 - 02 - Life and Physical Sciences;


SoftwareClause



Sp. Measures

2014 2015

T314-409MM Depolarised DLS optical cell for the COLLOIDAL SOLIDS instrument 300 C(1) N/A

T314-411MM Exploitation of the FOAM-C cartridge capabilities and environment forrheological stimulation of foam samples and measurements 200 C N/A

T314-413MM Monitoring and countermeasures of spine length variations and associatedback pain 250 C(1) N/A

Total 3 - 02 - Life and Physical Sciences; 750

Page 4 of 20



3 - 03 - Human Spaceflight and Exploration Preparation


SoftwareClause



Sp. Measures

2014 2015

T304-402EE Testing of innovative materials for passive radiation shielding for Humanspaceflight 400 DN/S IT N/A Thales Alenia (IT) and GSI (DE)

T323-419MM Online ammonium analysis for water recycling systems 300 C(2) N/A

T324-420QT Breadboard development for in-orbit demonstration of additive layermanufacturing technologies 400 C(2) N/A

Total 3 - 03 - Human Spaceflight and Exploration Preparation 1100

3 - 04 - Lunar Lander Missions


SoftwareClause



Sp. Measures

2014 2015

T316-414MM Miniaturized Imaging LIDAR Systems for landing applications (Phase 2a) 300 DN/C CH N/A CSEM (CH)

T319-416MP Structural Tanking 300 C N/A

Total 3 - 04 - Lunar Lander Missions 600

Page 5 of 20



4 - Space Transportation & Re-entry Technologies

4 - 01 - Launchers Oriented Technologies


SoftwareClause




T419-410MP High Order Cavitation Surge Characterization in Space Inducers 300 C(1) N/A

T420-415MS Development of new interface concepts for launcher main tanks 400 C(2) N/A

T424-420QT Monitoring Laser Peening for Stress-Corrosion Cracking and FatigueResistance Enhancement of Launchers External Structures 450 C(2) N/A

Total 4 - 01 - Launchers Oriented Technologies 1150

4 - 02 - Human Space Flight Oriented Technologies


SoftwareClause




T419-409MP Experimental Investigation of a Direct-Drive Hall Effect Thruster (HET)System 250 C N/A

T424-418QT Low Cost Hybrid Material Solutions for Radiation and Impact ProtectionSystems for Human Spaceflight 300 C(3) N/A

Total 4 - 02 - Human Space Flight Oriented Technologies 550

Page 6 of 20



4 - 03 - Generic Space Transportation Technologies


SoftwareClause



Sp. Measures

2014 2015

IPC T401-401ED Development of a representative AFDX/Time-Triggered-Ethernet-basedavionics system for RASTA. 200 C Open Source

IPC T402-403SW New Generation Launcher and Space Transportation AdvancedAvionics Test Bed 850 C N/A

T418-407MP Multi-phase Flow Modelling 400 DN/S ES N/A Empresarios Agrupados (ES)

Total 4 - 03 - Generic Space Transportation Technologies 1450

Page 7 of 20



5 - Telecommunications

5 - Telecommunications Technologies


SoftwareClause




T506-404ET Antennas and Signal Processing Techniques for Interference Mitigation inNext Generation Ka band High Throughput Satellites 400 C(1) N/A

T506-406ET Non-regular Multibeam Coverage Payloads 250 C N/A

T507-408EE AMC/Metamaterial Antennas for Broadband Connectivity 425 C(1) N/A

IPC T507-409EE Multiple Beam Antennas based on Reflectarrays & Transmitarrays 500 C N/A

T517-412MM Micro-optoelectronic FGU 300 C(1) N/A

T519-417MP Low-Erosion Long-Life Hall Effect Thruster 350 C N/A

IPC T523-414QT Development and reliability assessment of SiGe based wideband LNAand wideband mixer for space 500 C(1) N/A

T524-416QT Friction Stir Welding of Titanium Silicon Carbide Composites for XenonTanks Applications 280 C N/A

Total 5 - Telecommunications Technologies 3005

Page 8 of 20



6 - Navigation

6 - Navigation Technologies


SoftwareClause




T604-401EE Data Exploitation of new Galileo Environmental Monitoring Units (EMUs) 200 C(3) OperationalSoftware

T606-404ET End to End Dissemination Tool 200 C N/A

T606-405ET Orbit /SRP modelling for long term prediction 200 C N/A

T606-406ET Enhanced methodology and tools for system performance evaluation 250 C(2) N/A

T606-407ET Interference detection/protection for Telemetry/Telecommand and missionlinks 200 C N/A

Total 6 - Navigation Technologies 1050

Page 9 of 20



7 - Generic Technologies

7 - 01 - On-board Data Systems


SoftwareClause




T701-402ED Prototyping of space protocol(s) for SPI 400 C N/A

Total 7 - 01 - On-board Data Systems 400

7 - 02 - Space System Software


SoftwareClause




IPC T702-402SW Verification of Computer-Controlled Systems 600 C N/A

Total 7 - 02 - Space System Software 600

7 - 03 - Spacecraft Power


SoftwareClause




IPC T703-401EP Next Generation Solar Cells with an End of Life Efficiency of 30% 2500 C(1) N/A

Total 7 - 03 - Spacecraft Power 2500

Page 10 of 20



7 - 04 - Spacecraft Environment & Effects


SoftwareClause



Sp. Measures

2014 2015

T704-401EE Radiation Belt Model Development and Validation 300 C(3) N/A

Total 7 - 04 - Spacecraft Environment & Effects 300

7 - 05 - Space System Control


SoftwareClause



Sp. Measures

2014 2015

IPC T705-401EC Navigation on a chip 600 C N/A

Total 7 - 05 - Space System Control 600

7 - 06 - RF Payload Systems


SoftwareClause



Sp. Measures

2014 2015

IPC T706-401ET Flexible and Autonomous TT&C transponders for multi missionapplications 500 C(2) N/A

Total 7 - 06 - RF Payload Systems 500

Page 11 of 20



7 - 07 - Electromagnetics Technology


SoftwareClause



Sp. Measures

2014 2015

IPC T707-402EE Open source cables models for EMI simulations 400 C(1) Open Source

Total 7 - 07 - Electromagnetics Technology 400

7 - 09 - Mission operation and Ground Data Systems


SoftwareClause



Sp. Measures

2014 2015

T709-401GI Model based operations design, planning and execution 400 C(1) OperationalSoftware

Total 7 - 09 - Mission operation and Ground Data Systems 400

7 - 10 - Flight Dynamics and GNSS


SoftwareClause



Sp. Measures

2014 2015

T710-401GN 3-D ionospheric Total Electron Content (TEC) modelling 250 C(1) N/A

Total 7 - 10 - Flight Dynamics and GNSS 250

Page 12 of 20



7 - 11 - Space Debris


SoftwareClause



Sp. Measures

2014 2015

T711-402GR System for facilitating collaborative coordinated observations 250 C(1) OperationalSoftware

Total 7 - 11 - Space Debris 250

7 - 12 - Ground Station Systems and Networks


SoftwareClause



Sp. Measures

2014 2015

IPC T712-401GS Ka-Band cryocooled feed 600 C(1) N/A

Total 7 - 12 - Ground Station Systems and Networks 600

7 - 13 - Automation, Telepresence & Robotics


SoftwareClause



Sp. Measures

2014 2015

IPC T713-401MMhArmonised System Study on Interfaces and Standardisation of fuelTransfer (ASSIST) 800 C N/A

Total 7 - 13 - Automation, Telepresence & Robotics 800

Page 13 of 20



7 - 15 - Mechanisms & Tribology


SoftwareClause



Sp. Measures

2014 2015

T715-401MS Development of advanced lubricants for space mechanisms based on IonicLiquids 300 C(1) N/A

Total 7 - 15 - Mechanisms & Tribology 300

7 - 16 - Optics


SoftwareClause



Sp. Measures

2014 2015

IPC T716-404MM Active Optics correction chain for large monolithic mirrors 1000 C N/A

Total 7 - 16 - Optics 1000

7 - 17 - Opto-Electronics


SoftwareClause



Sp. Measures

2014 2015

IPC T717-401MM Lattice-matched III-V detector arrays with 2.5um cut-off 500 C(1) N/A

Total 7 - 17 - Opto-Electronics 500

Page 14 of 20



7 - 18 - Aerothermodynamics


SoftwareClause



Sp. Measures

2014 2015

T718-401MP Prediction of acoustic loads on space structures 300 C(3) N/A

Total 7 - 18 - Aerothermodynamics 300

7 - 19 - Propulsion


SoftwareClause



Sp. Measures

2014 2015

T719-402MP Model and experimental validation of spacecraft-thruster interactions(erosion) for electric propulsion thrusters plumes 400 C(2) N/A

Total 7 - 19 - Propulsion 400

7 - 20 - Structures & Pyrotechnics


SoftwareClause



Sp. Measures

2014 2015

T720-401MS Advanced damage tolerance assessment methodology for compositestructures 300 C N/A

Total 7 - 20 - Structures & Pyrotechnics 300

Page 15 of 20



7 - 21 - Thermal


SoftwareClause



Sp. Measures

2014 2015

T721-401MT Mini Hybrid Capillary Pumped Loop 400 C(1) N/A

Total 7 - 21 - Thermal 400

7 - 24 - Materials & Processes


SoftwareClause



Sp. Measures

2014 2015

T724-402QT Assessment of materials and processes design margins for spacecraft andlaunchers 250 C N/A

Total 7 - 24 - Materials & Processes 250

7 - 25 - Quality, Dependability and Safety


SoftwareClause



Sp. Measures

2014 2015

T725-402QQ Reliability of Mechanical Systems and Parts 300 C(2) N/A

Total 7 - 25 - Quality, Dependability and Safety 300

Page 16 of 20



7 - 26 - Spacecraft Avionic System


SoftwareClause



Sp. Measures

2014 2015

IPC T701-403ED OBC Mass Memories (Solid State Mass Memory board/moduleintegrated in OBC) 1000 C(1) N/A

IPC T702-403SW File Management Services interface standardisation 500 C N/A

T708-403SW CCSDS MO Services, CCSDS SOIS, and SAVOIR for future spacecraft 400 C N/A

Total 7 - 26 - Spacecraft Avionic System 1900

7 - 27 - End to End System Design Processes


SoftwareClause



Sp. Measures

2014 2015

IPC T708-404SW Augmented Reality for AIT, AIV and Operations 500 C(1) N/A

T708-405SW New modeling methods for Simulation, Verification and Validation 400 C N/A

Total 7 - 27 - End to End System Design Processes 900

Page 17 of 20



7 - 28 - Electronic Components


SoftwareClause



Sp. Measures

2014 2015

IPC T723-402QE Utilisation of the Proton Irradiation Facility at PSI for ComponentRadiation Studies 120 120 DN/C CH N/A

Paul Scherrer Institute (CH).Frame contract: for information,the running contract covers2008-2013 (ESA/IPC(2007)3,add3 and ESA/IPC(2010)3, add.4)and it is now extended until 2015.

IPC T723-405QE Utilisation of the High Energy Heavy Ion Test Facility at JYFL forComponent Radiation Studies 120 120 DN/C FI N/A

Un. Jyväskylä (FI).Frame contract: for information,the running contract covers2008-2013 (ESA/IPC(2007)3,add3 and ESA/IPC(2010)3, add.4)and it is now extended until 2015.

IPC T723-406QE Utilisation of a Heavy and Light Ion Facility at UCL for ComponentRadiation Studies 180 180 DN/C BE N/A

Un. Louvain (BE).Frame contract: for information,the running contract covers2008-2013 (ESA/IPC(2007)3,add3 and ESA/IPC(2010)3, add.4)and it is now extended until 2015.

T723-408QE Radiation Testing of EEE parts in support of ESA R&D activities 350 C(1) N/A

T723-409QT Prototyping and Characterisation of Radiation Hardened SiC MOSStructures. 420 C(1) N/A

T723-410QT Investigation into applicable Inspection & Analysis Techniques for Flip ChipDevices 320 C(1) N/A

Total 7 - 28 - Electronic Components 1510 420

Page 18 of 20



7 - 32 - Cleanspace


SoftwareClause



Sp. Measures

2014 2015

T704-403EE Space debris from spacecraft degradation products 250 C N/A

T719-403MP Thrust Vector Control Systems for solid propellant de-orbit motors 350 C N/A

T719-405MP HAN-based monopropellant assessment 350 DN/S UK N/A European Space Propulsion (UK)

IPC T724-403QT Citric Acid as a Green Replacement for Steels Passivation 500 C(1) N/A

T713-402MM Elastic tether design and dynamic testing 300 C(1) N/A

Total 7 - 32 - Cleanspace 1750

7 - 33 - Space & Energy


SoftwareClause



Sp. Measures

2014 2015

T722-401MM Space and Energy, EnRum 400 C(1) N/A

Total 7 - 33 - Space & Energy 400

Page 19 of 20



7 - 35 - Technologies Enabling Breakthroughs in Science


SoftwareClause



Sp. Measures

2014 2015

IPC T716-403MM Trade-off for very large space telescope mirrors 900 C N/A

Total 7 - 35 - Technologies Enabling Breakthroughs in Science 900

7 - 36 - Collaborative Activities


SoftwareClause



Sp. Measures

2014 2015

T705-404EC Star Sensing based Safe Mode 300 C N/A

IPC T708-411QT Compact impedance matched connectors for SpaceWire LinksDevelopment and ESCC Evaluation 600 C(1) N/A

T710-403GN New Concepts for Non-Real Time On-Board Precise Orbit Determination 250 C N/A

IPC T719-406MP Development of a miniaturised Gridded Ion Engine subsystem forfuture space missions 1400 C N/A Co-funded activity: TRP 700 kE

and EUCLID project 700 kE.

T721-403MTFlat Loop Heat Pipe Evaporator based on Advanced ManufacturingTechnologies 350 C(1) N/A

Total 7 - 36 - Collaborative Activities 2900

Page 20 of 20


ANNEX II

TRP WORK PLAN

Descriptions of Activities

TRP WORK PLAN 2014-2015: Work and Procurement Plan 2014ANNEX II: Detailed Description of Activities ESA/IPC(2013)3,add.5

1 - Earth Observation

1 - 01 - Microwave Payloads

TRP Reference T107-407EE TD TD07

Title Dual polarisation 94 GHz antenna for spaceborne Doppler radar (old title:Dual polarization 94 GHz Antenna for ground based Doppler radar)

ObjectivesStudy of a dual-polarised spaceborne antenna concept for 94 GHz Doppler radar and breadboarding of criticalsub-assembly for proving the concept.DescriptionGlobal observation of three-dimensional vector wind-field in the atmosphere has been the priority No. 1 of theatmospheric dynamics community for a number of decades. Lidar technology from space can potentially deliversuch information either in cloud-free conditions or above clouds. For measuring wind profiles within or below clouds,a radar technology would be required. Such information is sought by the NWP and nowcasting communities forpredicting severe weather, and by the atmospheric physics community for developing models of turbulences andconvection.

An initial concept for a conically scanning Doppler wind radar was developed through a GSP study on "Techniquesand Sensors for Observation of Extreme Weather Events", (2006). A subsequent TRP study (Swath PrecipitationRadar Instrument) revisited the conically scanning concept and a preliminary design was elaborated. A further TRPstudy on the scattering model development and Doppler retrieval (Capability of Atmospheric Parameter Retrieval andModelling for Wide-Swath Spaceborne Atmospheric Radars) addressed a number of different radar configurationssuch as single line-of-sight, stereo and conically scanning observation geometries. It also confirmed the adequacy94 GHz radar frequency for the Doppler estimation.

In all of the concepts elaborated above, a so-called pulse-pair Doppler estimation technique was adopted whichmakes use of a pair of closely spaced pulses with orthogonal polarisations. Thus, one of the requirements for theantenna is to be able to emit a pair of closely spaced pulses in H and V polarisations, and to receive echoessimultaneously in both polarisations. A second requirement is a high peak power handling capability of better than 2kW. Finally a reflector of 2 - 3 m diameter is considered for achieving the required beamwidth for accurate Dopplerextraction.

The activity will consist of:- consolidating the main requirements of the EO instrument and the antenna performance requirements- establishing the state of the art survey for antenna at the selected frequency- performing trade off analysis and selecting one baseline and one backup antenna solutions for the antenna.- designing and analysing critical breadboarding to validate the design and analyses- proposing a roadmap and a development plan for the critical elements.

Depending on the type of antenna sub-assembly selected for breadboarding, the Agency may decide to re-use thehardware output for a ground-based experiment.DeliverablesPrototypeApplication/Need Date 2015/2016

Current TRL TRL 4 Target TRL TRL 6 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-7769Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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Title Frequency Selective Surfaces with improved performance for compactQuasi Optical Networks

ObjectivesTo design and manufacture Frequency Selective Surfaces (FSS) with improved performance even when located inthe near field of the feed system. This will enable compact quasi-optical feed networks with potentials for a largenumber of instruments and applications.DescriptionFrequency Selective Surfaces (FSS) are screens designed to reflect and transmit electromagnetic wavessimultaneoudsly at 2 distinct frequency bands or more. They have been largely used in satellite applications. Achallenging technological problem still remaining to date is related to need to put them closer to the feed system inorder to reduce their size. It is proposed here to design and manufacturing a new FSS with improved performancebased on a larger number of degrees of freedom obtained by fully exploiting the positions and the layouts of theelements constituting the FSS. Non regular FSS designs will permit to implement feed closer to the FSS structurewith benefits in terms of compactness and reduced overall size while improving the performance in terms of losses,isolation and cross polarization.The activity shall analyse, with respect to traditional FSS, the benefits of compensation of the edges (truncationeffects), compensation for the amplitude and phase tapering in the signal illuminating the FSS (which is not a perfectplane wave), optimization of performance with respect to the angle of arrival of the signal and operation in linear andcircular polarization.To achieve these objectives it shall be assessed, and when needed, developed the requested electromagnetic toolenabling accurate, effective in time, modelling of generic non periodic or quasi periodic screen (without exploiting theperiodicity boundary conditions).The activity shall be organized in 2 parts: in the first the capabilities to design and modelling FSS based on nonregular lattices/elements will be developed while in the second a breadboard will be realized in order to validate theobtained benefits shown by simulations.The activity is expected to increase the European expertise in design and manufacturing of FSS and in the modellingof non regular FSS and make FSS available and useful for a large number of space applications.DeliverablesBreadboardApplication/Need DateCurrent TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8626

Applicable THAG Roadmap Technologies for Passive Millimetre &Submillimetre Wave Instruments (2010) Consistency with THAG Roadmap No

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TRP Reference T106-409ET TD TD06Title High-performance calibration switch for mm-wavesObjectivesTo develop calibration switches for internally calibrated radiometers between 89 and 250 GHz.DescriptionAn important new aspect in the radiometry is the use of internal calibration concept that could benefit the future EOradiometers by more efficient calibration. In addition to the noise sources, one critical element in the calibration is theRF switch that has to be used for switching between the calibration loads and the antenna. Key parameters of theswitch are insertion loss, isolation, switching speed, repeatability, low excess noise, low self-heating, and stability.Throughout the RF spectrum and especially at the mm-wave range, meeting these requirements are evidently verychallenging. Although commercial switches are available in a numerous types and qualities especially at lowerfrequencies, no specific low-power designs exist for the needs of radiometry.

This activity aims at developing calibration switches at selected frequencies between 89 GHz to 250 GHz. First,different switch technologies (e.g. MEMS, liquid crystal, ferrite, HEMT, PIN diode, + any new) and theirperformances shall be assessed and traded off. Secondly, two most promising technologies shall be selected forprototyping. Integration issues shall be considered from an optimum layout point of view in a representative receiverfront end. Finally, switch prototypes shall be designed, manufactured, and tested in a representative environment.DeliverablesPrototypeApplication/Need Date Microwave and millimetre wave radiometers, imagers, sounders, Jason CS.

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8209, T-8220, T-8206, T-8229Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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TRP Reference T106-406ET TD TD06Title Ka-band InSAR Front-end Development for Airborne CampaignObjectivesDevelopment and verification of a compact airborne Ka-band multi-baseline interferometric front-endDescriptionThe Ka-band frequency (35 GHz) is becoming increasingly attractive for spaceborne remote sensing applications.Unlike other radar bands, the Ka-band enables the development of compact high resolution interferometricinstruments and embarking the payloads on a single platform. This creates unique new opportunities in Earthobservation science and civil security applications, for instance in monitoring the changing cryosphere, generatinghigh resolution maps of ocean currents and ship and vehicle detection.A major obstacle in the development of Ka-band mission concepts is the absence of suitable reference datasets dueto lack of airborne prototype instruments. The workshop "Ka-band Earth Observation Radar Mission" held inNovember 2012 at ESTEC explicitly recommended airborne campaigns to demonstrate applications, developimaging techniques e.g. multi-baseline interferometry and test new technology.

The objective of the activity will be the development of a compact Ka-band multi-baseline InSAR frontend includingcharacterisation of the front end performance through rigorous testing. The front-end shall be suitable for theintegration with an existing multi-channel radar electronics core as used on research airborne instruments orenvisaged on UAVs and drones. With this approach the activity will serve two needs:- the demonstration of Ka-band multi-baseline imaging techniques for ATI and XTI applications- the provision of a Ka-band front-end enabling the assembly and operation of a complete airborne prototype imagingpayload- the delivery of Ka-band radiometric data through a dedicated airborne campaign.Through dedicated measurements and data evaluation the activity will provide timely inputs regarding the design offuture Ka-band spaceborne systems, mission design trade-offs including technological ones, stimulate thedevelopment of new application areas and enable the prototyping of products.DeliverablesPrototypeApplication/Need Date Airborne Ka-band campaign/2015

Current TRL TRL 3 Target TRL TRL 6 Duration (Months) 15S/W Clause N/A Ref: to ESTER T-8888Applicable THAG Roadmap Critical RF Payload Technologies (2004) Consistency with THAG Roadmap No

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Title Microstructural origin of electromagnetic signatures in microwave remotesensing of snow

ObjectivesThe activity should result in microwave models with improved snowpack characterisation.DescriptionExperimental and theoretical methods required to understand the impact of snow on microwave remote sensing fromfirst principles are now available. The proposed project will combine these methods to unravel the role of snowmicrostructure in microwave signatures of the cryosphere. Microwave models generally consider snow as a stratified,multi-layer medium, based on the assumption that each layer can be treated as an isotropic, random material whichis sufficiently characterised by its volume fraction of scatterers (snow density) and a single structural length scale,commonly subsumed in the term "grain size" or "effective grain size".Deviations between model predictions, brightness temperature and backscatter coefficient in active or passivemicrowave radiation cannot be unambiguously explained due to multiple, concurrent sources of uncertainties: i)physical model limitations ii) limitations of snow characterisation iii) additional influences, e.g. due to soil propertieswhich cannot be avoided in field measurements. While iii) is tricky, available methods can be combined tounambiguously assess i) and ii).Recent work on snow microstructure has revealed that the assumption of snow as an isotropic random medium, ascommonly pursued in microwave applications, is generally wrong in almost all snow conditions. Snowmicrosctructure is anisotropic, with significant differences between horizontal and vertical correlation lengths.The proposed activity therefore will combine the state-of-the-art knowledge in forward EM modelling with realisticsnowpack characterisation.Introducing microstructural physical properties of the snowpack within these models will enable a sensitivity analysesof introducing miscroscale parameterisation of the medium. Available experimental data will assist these analyses.Available datasets include multi-year scatterometer data co-inciding with multi-channel radiometer data. Thesedatasets are enriched with in-situ snowpack characterisation measurements utilising different measurementtechniques.DeliverablesStudy ReportApplication/Need Date Ku- / Ka-band SAR, radar altimetry for cryosphere investigations, MW radiometry

Current TRL TRL 2 Target TRL Prototype Duration (Months) 24S/W Clause Open Source Ref: to ESTER T-8153, T-8756Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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TRP Reference T106-401ET TD TD06

Title Study on future microwave radiometers for atmospheric correction ofradar altimeters on coastal regions

ObjectivesThe objective of the study is to investigate novel microwave radiometer concepts for improving the atmosphericcorrection in coastal regions of future radar altimeters. The study shall trade-off various options such as the additionof high-frequency channels and the definition of new radiometer concepts.DescriptionMicrowave radiometers are widely employed in radar altimetry missions, since they are fundamental for correctingthe path delay of the radar signal due to the presence of liquid water in the atmosphere (wet troposphere delay).State-of-the-art radiometers employ two or three observation frequencies (18.7GHz, 23.8GHz and 36.5GHz) withtypical spatial resolution of ~ 20km.However, such radiometric measurements generally fail over land or near the coasts where the signal coming fromthe surrounding land surfaces contaminates the radiometer measurement and makes the humidity-retrieval methodnot suitable. This is mainly due to the limited spatial resolution of the radiometers.Future altimeters will employ along-track SAR techniques and will reach very high along track spatial resolution<1km and will have improved altimetry performance near the coast. Therefore future radiometers will also require animproved along-track spatial resolution in order to support the altimetry observations.New types of radiometers have to be defined to support this needs. Possible solution may be the inclusion of highfrequency channels (in order to improve spatial resolution) or identify new technology options which increasealong-track antenna aperture.The trade-off between the addition of high frequency channels (including the retrieval algorithms analysis) and theimprovement of spatial resolution for standard frequencies shall be part of the study.

The work is organised in 4 tasks as follows:Task 1: Requirements review and state-of-the-art survey, including retrieval algorithms atmospheric correction,Task 2: Trade-off of novel radiometer concepts and atmospheric correction algorithms,Task 3: Detailed definition of selected conceptTask 4: Technology roadmapDeliverablesStudy ReportApplication/Need Date Ocean Altimetry / 2020

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-383, T-7769, T-8880, T-8794Applicable THAG Roadmap Critical RF Payload Technologies (2004) Consistency with THAG Roadmap No

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1 - 02 - Optical Payloads

TRP Reference T117-407MM TD TD17Title Complete Large-area MCT SWIR DetectorObjectivesDesign, manufacture and characterisation of full 2K x 2K pixel, SWIR MCT hybrid array.DescriptionThe current Large-area SWIR Detector development, that is due to finish in early 2014, aims to demonstrate theprincipl of a 2K x 2K detector through design, manufacture and characterisation of a full-size ROIC hybridised to asmaller MCT PV layer. This follow-on activity aims to design and manufacture a full 2K x 2K pixel PV MCT layer andhybridise it to the large ROIC developed under the previous activity. Full detector characterisation will also beperformed.DeliverablesBreadboardApplication/Need DateCurrent TRL TRL 2 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8173

Applicable THAG Roadmap Optical Remote Passive Instruments -Detectors (2011) Consistency with THAG Roadmap Yes

TRP Reference T117-411MM TD TD17Title Fiber based optical frequency comb at 2 micron for LIDAR applicationsObjectivesThe objective of this activity is to develop an optical frequency comb centred at the 2 micron region with a wideflat-topped spectral coverage using fiber Supercontinuum-based techniques. This shall achieve good re-configurationflexibility and enabling an adaptation of the central wavelength to the specific application.DescriptionPrior investigations in spectral broadening of high-rep-rate temporal pulse trains from actively mode-locked lasers orelectro-optic frequency comb generator showed a high degree of flatness with broad bandwidth when specific pulseprofile pulses are launched into an HNLF, operating in the normal dispersion regime. The temporal profile emergingfrom such a supercontinuum based comb can be used as a seed to achieve an ultra-broad optical spectrum (>3.64-THz or 28-nm) with excellent flatness and a high-degree of coherence.Nonlinear broadening techniques based on fiber based optical frequency combs generally do not provide therequired flatness over the entire available bandwidth. Ultra-broadband flat-topped optical frequency comb within lowpower variation covering the entire band of interest is a desirable feature to achieve good re-configuration flexibilityand high coherence.The key enabling point is the development of a directly generated Gaussian comb-based high rep rate pulse train toseed a highly nonlinear fiber with normal dispersion profile.The combination of the temporal characteristics of the pulses with the nonlinear device achieves the desired smoothflat-topped comb spectral envelope.DeliverablesBreadboardApplication/Need DateCurrent TRL TRL 2 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8645, T-8646, T-8690Applicable THAG Roadmap TBD Consistency with THAG Roadmap TBD

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TRP Reference T117-408MM TD TD17

Title High Performance Silicon Visible Hybrid CMOS Image sensordemonstrator

ObjectivesTo demonstrate the potential of Hybrid technology for high performance Silicon visible CMOS imagers, as analternative to monolithic approach. For that the aim is :to design, manufacture, and test a Silicon hybrid visible CMOS detector.DescriptionOne of the difficulties on monlithic approaches for Visible Si CMOS Image sensors is the complexity of the stackingthat imposes contraints at pixel level both on the electronic part of the detector (space available to handle capacitorsand electronic circuitery) as well as on the optical part (large diminution of fill factor available for example in front sidedevices due to the electronic parts). An interesting alternative to monolithic approach is the hybrid approach, which issimilar to what is done by IR-detector manufacturers. The idea here would be to take advantage of the wellestablished hybridized technology and ROICs, to concentrate the effort for this activity on the optical performances.This first step would therefore be aimed at the detection layer development, with the use of an existing CMOS ROIC(CTIA for example). The selected company would focus maily on diode performances such as dark current / QE,MTF, and homogeneity aspects. This is a lower risk/ lower cost approach, since the developpement and high risklinked to the ROIC developmenent is avoided here.Note that an advantage of this hybrid philosophy is the potential compatibility with IR detectors ROIC, which meansthat in a second phase (ie in the frame of a futur TRP if this one is succefull) use of state-of-the art ROIC underdevelopment at the moment for Infra-Red application (LFA for example) could be envisaged.DeliverablesBreadboardApplication/Need DateCurrent TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7886

Applicable THAG Roadmap Optical Remote Passive Instruments -Detectors (2011) Consistency with THAG Roadmap Yes

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TRP Reference T116-405MM TD TD16Title NIR immersed grating in transmission for high resolution spectroscopyObjectivesA NIR immersed grating in transmission shall be designed, developed, manufactured and tested. The requirementswill be based on actual NIR spectrometer mission studies (Flex, CarbonSat). The objective of this activity is todevelop a generic grating technology for the production of the most compact spectrometers possible combined withthe lowest stray-light possible for any future VIS-NIR mission. Transmission immersed gratings (prism-grating-prism)have namely the advantage to produce clearly less stray-light as their reflective counterparts and are as well easierto design/implement at instrument level.DescriptionMost of todays VIS-NIR grating studies and developments are based on reflective immersed gratings or transmissiongratings. Reflective immersed gratings are based on a prism with a grating profile on the second surface. Immersionof a grating helps to reduce grating and instrument size by a volume reduction proportional to the third power of therefractive index n. Fused silica immersed gratings used in that spectral range lead therefore to a volume reduction ofa factor of 3, which is a significant improvement. Each mission has of course its own grating requirements in terms ofspectral resolution, spectral band, polarisation sensitivity, diffraction efficiency and stray-light. In details, this leads foreach mission to a different grating profile and groove density and for certain missions it turns out that immersion isnot even required due to relaxed volume requirements. However, all these grating profiles, whether immersed(reflection) or in typical transmission can (and mostly are today) be manufactured using the same basic method,namely using planar semiconductor manufacturing tools (e.g. e-beam, photolithography, dry or wet etching). Suchgrating profiles have always planar top surfaces which offer an ideal contacting area for the direct bonding to a prismto form a prism-grating-prism element. This leads to transmission immersed gratings which always have a volumeadvantage at instrument level as well as minimised stray-light compared to other designs. So far, this has not yetbeen done because an additional grating-to-prism bond process is required.

The technology step required to obtain these optimised generic gratings, which is addressed in the proposed activity,is the bonding of the grating profile to the prism with all associated processes. One of these associated processescan be for instance a groove filling with high refractive index material. Thermal vacuum and mechanical load testsshall be performed.

This proposed activity fits perfectly to the strategy in getting generic standardized manufacturing technologies inEurope delivering the smallest and best performing grating spectrometers from the VIS to the SWIR.DeliverablesBreadboardApplication/Need Date CarbonSat, Flex, future Sentinel 4&5 type missions


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TRP Reference T116-406MM TD TD16Title "Smart slit" for next generation high resolution spectrometersObjectivesThe significant improvements of mission-critical performances such as stray-light (de-clouding), co-registration,dynamic range for detection and detector noise by introducing a "smart" slit in an optical spectrometer shall beinvestigated and analysed.Compact instrument designs for future Earth observation missions, based on requirements of Flex, CarbonSat,Sentinel-5, shall be elaborated, modelled and analysed.A bread-board shall be designed and built for a proof-of-concept demonstration of the key functions of a smart slitusing a commercially available micro-mirror-array.DescriptionWith "smart slit" is meant the hardware function to actively block or transmit each image sample (pixel) entering thespectrometer slit. It can be realised with an optical MEMS device having a micro-mirror/shutter array (1 x 400micromirrors/shutters) placed at the slit. Each image sample in the slit can therefore be blocked or transmitted to thespectrometer. This new function enables a series of new possibilities for performance increase and potential newservices with a minimal mass/volume impact, such as:a) De-clouding (stray-light performance increase)b) Co-registration error detection for active correctionc) Scene brightness equalisation to increase dynamic range for detectiond) Anti-smearing (blocking light during charge transfer)e) Chopper for modulated detection (detection noise reduction)f) Object selectiong) PSF scattering measurement/calibration

Optional functions to be considered are: h) Variable slit width; and i) Programmable Hadamard slit.Since this new intelligence is introduced at the spectrometer slit, the mass and volume impact is minimised.

The activity will comprise a design and a breadboarding phase:

(1) Compact instrument designs for future Earth observation missions, based on requirements of Flex, CarbonSat,Sentinel-5, shall be elaborated, modelled and analysed (Detailed optical design; Tolerance analysis; Stray-light analysis; End-to-end performance model; Performance verification and calibration plan);(2) A bread-board shall be designed and built for a proof-of-concept demonstration of the key functions of a smart slitusing a commercially available micro-mirror-array.DeliverablesOther: Breadboard + instrument designsApplication/Need Date Most future Earth Observation optical spectrometer missions

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-8885, T-7861Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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1 - 03 - Platforms / Others

TRP Reference T118-401MP TD TD18

Title Assessment of the key aerothermodynamic elements for the realization ofa RAM-EP Concept

ObjectivesThe objective of the present activity is to assess the feasibility of the key elements for the RAM-Electric PropulsionSystem: the intake and gas feeding system capable to provide the required inlet flow to an Electric PropulsionSystem and the compact compressor to increase pressure to the minimum level for thruster functioning, since thestagnation pressure that could be derived from the atmosphere at 250 km of altitude is in the order of maximum 1Pascal and a typical inlet pressure for HET with a standard spacecraft propellant system is in the order of 1000 Pa.DescriptionThis idea behind the RAM-EP System concept is that the lifetime of the spacecraft would in theory not be limited bythe amount of fuel if the same atmospheric constituents producing the drag were collected by an appropriate inletand used as propellant by the propulsion system.In 2007, an ESA CDF Study highlighted that the RAM-EP concept could provide a promising innovative solution tovery low altitude (below 250 km) and/or long lifetime LEO missions (not over a defined altitude). Further resentstudies have successfully determined the feasibility of use atmospheric components (mainly Nitrogen and Oxygen)as propellant for Hall Effect and Gridded Ion thrusters, as well. Hence, here it is proposed as a kind of continuation ofthe above described proof of concepts, to assess the feasibility of the two key elements, from anaerothermodynamics point of view, of the Ram-EP Propulsion system: a molecular intake and a low-power molecularcompressor. Further the impact that these elements could have on the overall EP Thurster will be also evaluated.Extensive literature searches will be performed to identify and possibly cover the needs of the two tasks, includingthe selection of a set of mission requirements to be kept for the whole activity. Numerical simulation and generalmodeling will be performed mainly while some experimental activities will be needed.

For the realization of a molecular intake with 1m diameter, the following activities are foreseen:(a) Definition of the target mission requirements (orbit altitude, spacecraft dimensions, available budgets for thepropulsion system)(b) Literature review and trade-off of the possible concepts for a molecular intake (for instance, use of electrostaticdevices, material compatibility, effect of solar activity etc.)(c) Preliminary design and performance analysis of the most promising concept.

For the realization of a small-size low-power molecular compressor, the following activities are foreseen:(d) Literature review and trade-off of possible concepts to increase the stagnation pressure obtained by the intakeexit(e) Preliminary design and performance analysis of the most promising concept, considering two different systemlevels: breadboard for on-ground testing (hence with relaxed budgets in terms of weight, volume and needed power)and preliminary design of the spacecraft subsystem.

Finally the analysis of the EP system modifications for use with the RAM-EP system will include:(f) Design and realization of performance tests for existing candidate EP thruster(s) to determine theinterfaces/requirements towards the RAM-EP propellant feeding system.(g) Preliminary design for the RAM-EP breadboard test thruster.(h)Preliminary sub-system design for the complete RAM-EP propulsion systemDeliverablesStudy ReportApplication/Need DateCurrent TRL TRL 1 Target TRL TRL 3 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-8403Applicable THAG Roadmap Aerothermodynamic Tools (2012) Consistency with THAG Roadmap No

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TRP Reference T119-402MP TD TD19Title Consolidation of mN-FEEP Thruster Performance (mN-FEEP 4)ObjectivesThe proposed activity aims to achieve:- An improved understanding of pertinent emitter characteristics by increasing the number of manufactured andcharacterized units- optimization of the wetting process and the electrode configurationDescriptionNext Generation Gravity Missions will require microthrusters to compensate the drag of several spacecraft flying information. Porous mNFEEP thrusters are important candidates for this task.The sharp, porous tungsten crown emitter used in the mN-FEEP thruster is capable of producing thrust from theµN-range to the mN-range. Furthermore, the technology has undergone an additional level of refinement in that theporous matrix, which is crucial to the operation, has been varied in grain size and sintering techniques in order to findthe most suitable candidate. The crown emitter is first manufactured and then wetted with indium in a distinct wettingfacility. It is then installed in the thruster module and the initial start-up, the so called "priming"; is performed at highemitter currents. Once the emitter is fully operable, it can be operated continuously with lower currents. Thebehaviour of the emitter during priming and the resulting thruster performance highly depends on the quality of thewetting process. This is also reflected in the necessity of high start-up-voltages compared to the nominal operationvoltages.Two main activities have been identified as the most valuable for this investigation. They focus on different potentialsfor improvement of the thruster performance or the manufacturing process and aim to establish a large data basecorrelating the manufacturing process with thruster performance.1.Characterization of the start-up behaviour and optimization of the wetting procedure: Implement the capability tomonitor all individual emission sites of the crown emitter during the start-up phase. Manufacture a large sample ofsimilar crown emitter, using the optimized manufacturing process found in previous activities. Investigate the start-upbehaviour of a large number of crown emitters wetted with different wetting procedures and find a wetting procedurethat maximizes firing homogeneity and/or minimizes the voltages required for the start-up phase. Investigate therepeatability of the chosen wetting procedure by applying it to a large number of crown emitters and testing thereliability of the predicted start-up behaviour.2.Assessment of the mass efficiency of the thruster:Measure the mass efficiency of a large number of crowns atvarious operating points, where all crows should be manufactured and wetted with the same previously optimizedprocedures. The sample size should allow for a statistical analysis of the mass efficiency over the complete thrustrange of the thruster.3.Assessment of the thrust characteristics of the thruster: Measure the thrust characteristics of a large number ofcrowns at various operating points, where all crowns should be manufactured and wetted with the same previouslyoptimized procedures. The sample size should allow for a statistical analysis of thrust and ISP over the completeperformance map of the thruster. Analyze the results of this task together with the mass efficiency measurementsconducted in Task 2 with respect to the performance of the used electrode configuration and investigate the potentialfor optimization of this configuration.DeliverablesStudy ReportApplication/Need Date Next Generation Gravity Missions (NGGM)

Current TRL TRL 3 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-1013Applicable THAG Roadmap Electric Propulsion Technologies (2009) Consistency with THAG Roadmap Yes

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TRP Reference T123-401QT TD TD23

Title Investigation and preliminary characterization of component buildingblocks needed to establish a European mm-wave GaN foundry process.

ObjectivesTo investigate and optimize the components/processing steps needed to establish anindustrial process for fabrication of mm-wave GaN HEMTs and MMICs in Europe.DescriptionWide band gap semiconductors (WBS) such as GaN and SiC offer many advantages for realising advanced spacesystems with component development ongoing in areas such as microwave electronics and DC-DC powerconversion. The initial ESA component development strategy (see information note ESA/IPC(2006)89) has focusedon development of GaN microwave devices that can provide an order of magnitude improvement in RF output powerand allow 0.5-1dB improvement in system noise performance compared to using GaAs or Si. However, at present,the industrial GaN microwave foundry capability in Europe is limited in operation to 20GHz.

Several TRP activities have been initiated (or are planned) to investigate the circuit benefits of mm-wave GaNcircuits with encouraging results obtained. However, no work is ongoing in Europe to develop the elementaryprocess building blocks to enable transfer of techniques developed by the research institutes (e.g. IAF, ETH) tomanufacturing industry (e.g. UMS, OMMIC, Selex).

Work is now urgently required to begin implementation and optimisation of a production compatible foundry processto allow establishment of an industrial mm-wave GaN foundry. To reduce risk, the work shall focus on developing150nm gate length technology allowing circuit operation up to V-band (60GHz) as a first step. In a second step, thiswill then be followed by further technology scaling, down to 100nm gate length, in order to allow operation in W-band(100GHz). The overall approach is essential so that the processes developed can eventually be space qualified andfully exploited by European space industry.

The work will build upon previous TRP activities that have already successfully demonstrated feasibility of operationup to V and W-band, albeit at research institute level. However, the focus here shall be on the transfer of researchinstitute know-how to a production foundry line, checking the suitability of process building blocks/modules essentialfor establishment of an industrial scale mm-wave GaN production foundry process, optimizing process moduleswhere required and undertaking early space reliability validation on elementary test structures. This early validationand corrective action approach has already been successfully implemented as part of the ESA GREAT2 project,allowing the UMS GH50_10 process to be EPPL listed two years earlier than originally planned.

The proposed work is essential in order to ensure that a stable and repeatable European source of qualifiablemm-wave GaN components is available for future Earth Observation programs. In particular, care shall be taken toensure that appropriate production equipment (e.g. for stepper lithography, wafer handling, gate process module,passivation deposition) is used and that a trade-off between mm-wave device performance and achieving the desiredspace reliability is considered. To-this end, a preliminary assessment of the process suitability for operation in spaceshall be investigated by undertaking preliminary accelerated reliability tests on transistor test structures, performingH2 poisoning, high temperature storage and humidity tests. This type of assessment has, so far, not been performedin Europe for mm-wave GaN technology being developed at the research institutes. It is important to identify duringthe early stages of any technology transfer if the correct manufacturing techniques and materials are being used.

The successful completion of this work program will allow the foundations for an industrial mm-wave GaN foundryprocess to be established in Europe and matured/qualified through follow on GSTP/ECI funding. Benefits to spaceend-users will be an industrialized and qualifiable European process for stable manufacture of improved performance(x5 higher output power) SSPA's and robust LNA's in Ka, Q, V and eventually W-band. Examples of futureapplications include Ka-band high data rate (2Gbps) downlinks, Ka-band SAR T/R modules, ground segmentKa-band SSPA uplink (100W), V-band ISLs for near real time data relay networking, W-band SSPA for radiometersystems (currently only being developed at institute level through TRP funding), high power mm-wave LO sources.DeliverablesStudy Report

Application/Need DateSSPAs and Robust LNAs for mm-wave payloads in EO and Telecom applications, Ka-band SAR, Ka-band receive front-ends, high power LOsources for EO radiometer chains.

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7830, T-9057Applicable THAG Roadmap Critical RF Payload Technologies (2004) Consistency with THAG Roadmap No

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TRP Reference T107-405EE TD TD07Title Low-complexity data downlink antennaObjectivesTo develop at proof-of-concept level a data down-link antenna based on a modulated meta-surface configurationoperating in dual polarisation and offering beam scanning at Ka band with minimum complexity.DescriptionIt has been shown that a proper layout of sub-wavelength features on antenna surfaces is very effective in controllingthe antenna pattern with the antenna fed from a single or a few points. The activity focuses on the development ofspecific solutions for data down-link antennas with minimum complexity and as small a foot-print as possible offeringthe possibility for azimuth scanning and elevation scanning at Ka, in dual polarisation, based on the results obtainedfor an isoflux fixed-beam antenna for the same purpose at X band. The activity will consider both fully electronic andmixed (e.g. mechanical azimuth and electronic elevation) scanning configurations, resulting in a complete design anddemonstrator.DeliverablesBreadboardApplication/Need Date Future EO missions \ 2018

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-8333Applicable THAG Roadmap Array Antennas (2011) Consistency with THAG Roadmap Yes

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3 - Human Space Flight and Exploration Preparation

3 - 01 - Robotic Assistance

TRP Reference T313-407MM TD TD13Title Adaptable Wheels for Exploration (AWE)ObjectivesInvestigation on concepts and prototyping of wheels that can adapt their geometrical/mechanical characteristics tooptimally serve the conflicting requirements of compact launch accommodation, best performance in soft soil andsmall steering radii.DescriptionThe problem of marrying large-surface contact with unobtrusive wheels can be solved by recurring to adaptabledesigns. Adaptable designs may provide a solution as the conflicting requirements on wheels are fortunatelydissociated in operation. E.g. small wheels are needed when the rover is stowed (but not necessarily when it moves),small steering radii are needed in cluttered terrain (but not in soft terrain), large contact surface is needed in softterrain (where steering radii can be large).Therefore it is possible to envisage that wheels with the ability to switch among a discrete number of geometricconfigurations could provide optimal performance in a rather large range of operational situations.To date at ESA there has not been any R&D into adaptable wheels. Past R&D proposals were dismissed with theassumption that adaptability introduced unaffordable complexity. However there has never been any serious effort toquantify the "penalty" of complexity and also to analyse whether the penalty is commensurate to the benefits inperformance.A rover placed on the Moon pole, which has unpredictable soil characteristics, needs top performance to accomplishits challenging mission. It is quite possible that adaptable wheels may provide the level of performance that the roverrequire and at the same time increased probability of suceeding.

The activity shall:1. Perform a state of the art search into the previously published concepts of adaptable wheels and analyse themwith respect to potential of use in lunar pole scenario2. Define requirements for adaptable wheels in a lunar pole scenario with attention to the operational phase/physicalenvironment where the individual requirements are applicable. Define test scenarios.3. Perform a trade off of the concepts to select the one that best accommodate the requirements also inconsideration of the means used to actuate the adaptation4. Prototype a set of AWE wheels and a set of conventional rigid wheels fulfilling the same requirements5. Comparatively test the 2 wheel sets on a rover platform in the test scenarios previously defined.DeliverablesBreadboardApplication/Need Date LUNA-GRUNT/2018

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-9126Applicable THAG Roadmap Automation & Robotics (2012) Consistency with THAG Roadmap Yes

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TRP Reference T313-405MM TD TD13Title Localisation of Objects in Space through rf Tags (LOST)ObjectivesDevelop a prototype of a short-range RF-based localisation system for mobile robots and objects. The system shallallow localisation and motion capture, with centimetre precision, of robots/objects in a cubic volume of about 20m ofedge. The use of such system will not only allow continuous localisation of space objects in difficult lightingconditions (where computer based methods are unreliable), but also may have use in finding objects scattered (lost)in a volume in civil applications (e.g keyfinder).DescriptionLocalisation in mobile robot systems is an essential function to attain motion in space. While robot arms can rely onlocalisation of their tooltips by means of enteroreceptive sensors, for mobile robots, these sensors do not work wellenough. So localisation is realised by means of inertial measurement units and exteroreceptive sensors (as vision orlidars). These means of localisation, require demanding hardware, are computational intensive and also are subjectto drift. Mobile robots and in general anything moving around space infrastructure may benefit from small localisationdevices that attached to any part of a moving body can precisely report their position relative to an origin frame.The development shall target a system made of 1) a base unit, equipped with suitable antenna set, and 2) severalsmall (target euro-coin sized) RFID tags to be worn by the robot/object.The development shall follow the classical flow of: requirement collation; preliminary design and principle prototyping;design of fine prototype; MAIT.DeliverablesPrototypeApplication/Need Date Experiments on the ISS needing localisation/2015

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-9138Applicable THAG Roadmap Automation & Robotics (2012) Consistency with THAG Roadmap No

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3 - 02 - Life and Physical Sciences;

TRP Reference T314-409MM TD TD14Title Depolarised DLS optical cell for the COLLOIDAL SOLIDS instrumentObjectivesBreadboard of a depolarised optical cell to be used together with the COLLOIDAL SOLIDS instrument breadboard inphase A/B studies.DescriptionThe COLLOIDAL SOLIDS instrument (to enter phase A/B, former COLIS) is an advanced light scattering capabilitymainly designed to enable colloid physics studies in the framework of ELIPS. It is also identified as an instrument ofchoice for nucleation studies of macromolecules in solutions. This can be accomplished by dynamic light scattering(DLS) using a depolarised optical cell.

In this TRP project a breadboard version of the deploarised cell will be developed that would enable confocaldepolarised dynamic light scattering measurements in order to detect and characterise clustering/nucleation eventswithout the influence of gravity. This breadboard will be used together with the COLLOIDAL SOLIDS breadboard.DeliverablesBreadboardApplication/Need Date Phase A/B study of COLLOIDAL SOLIDS instrument. / 2014-2015



Title Exploitation of the FOAM-C cartridge capabilities and environment forrheological stimulation of foam samples and measurements

ObjectivesCartridges at breadboard stage integrating mechanical and electrical systems for liquid foam investigations in theFOAM-C instrument.DescriptionThe FOAM-C instrument design with its optical diagnostics offers flexibility to develop sub-experiments, by exchangeof cartridge in orbit, to investigate foams with high liquid fraction that are unstable on earth.

Beyond the FOAM coarsening experiments on samples with a high liquid fraction already planned, there is a demandfor applying a controlled mechanical load on the foam samples in order to relate the stimuli with the rate ofcoarsening. This must be implemented within defined boundary conditions and requirements, including in particularthe coarse electromagnetic field employed to generate the foam samples. Beyond the scientific interest, there is aclear relevance of this research to e.g. the food industry.

In this TRP project a new suitable cartridge demonstrator is developed for the investigation of foams using theFOAM-C instrument in µ-gravity. The results of this project will be used when entering the phase C/D of the FOAM-Cdevelopment.DeliverablesBreadboard

Application/Need Date Investigation of mechanically and electrically stimulated foams in the FOAM-Cinstrument after integration in phase C/D in 2016.


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Title Monitoring and countermeasures of spine length variations andassociated back pain

ObjectivesTo develop, demonstrate and validate breadboard technologies relevant to monitor, prevent and counteractastronaut's spine length variations and the associated back pain caused by the exposure to microgravity.DescriptionCountermeasures are required during prolonged space flights in order to counteract the deleterious effects ofmicrogravity on the human body. Among others, the occurrence of low back pain in microgravity is one of the mostcommon problems reported by more than 50% of the astronauts during or after their flight. Like most of the humanbody systems, the musculoskeletal system is influenced by the gravitational load. On Earth, the musculoskeletalsystem triggers muscular contractions to orient and stabilize the body in an upright position, which compensates thecompressive force associated to the gravitation vector. In the absence of gravity, the intervertebral distance willincrease by several centimetres. Although causes of low back pain in microgravity are yet not fully understood,experts tend to support a mechanical etiology. The reverse phenomenon (spine contraction) also happens uponastronauts' flight return on the ground.When perceived, the pain associated to spine length variations is not only an unpleasant physiological concern butcan also temporarily disturb astronauts' sleep and potentially alter their ability to perform their tasks with full mentalconcentration.Several countermeasures activities have been financially supported by the Agency; exercise-based andcardio-vascular countermeasures have been developed and are used routinely in the ISS, such as the treadmill, bikeergometer or LBNP (Lower Body Negative Pressure) to name a few. For interplanetary missions - and for verylong-duration ISS stays - additional countermeasures targeting especially musculo-skeletal and neuro-sensorysystems need to be developed. Yet, none of them has been focusing on low back pain. In addition, the utilisation oftechnologies for rehabilitation purposes is also of high interest. There is consequently a clear need to study, design,develop, demonstrate and validate techniques and tools able to monitor and counteract this phenomenon.

The proposed activity will be carried out according to a clear set of tasks:- Task 1: scientific background and State-of-the-Art review : in this task, the contractor shall review all relevantdocumentation to get sufficient scientific and technical background, organize a technical meeting with experts inrelevant fields and review the requirements.- Task 2: safety Analysis: in this task, the Contractor shall prepare all elements of a safety file (technical, regulatory)in view of the performance of a scientific assessment for the system to be developed.- Task 3: preliminary design: in this task, the contractor shall propose a preliminary concept, including identification ofcritical aspects, interfaces identification definition of a preliminary test plan.- Task4: detailed design: within this task, the contractor shall establish a detailed design of the system and updatethe test plan with test procedures (technical and scientific evaluation)- Task 5: Manufacture, Assembly, Integration and Technical test: in this task, the contractor shall manufacture andtest the system, prepare the user manual and update the safety file- Task 6: scientific assessment, conclusions and recommendations: in this final task, the contractor shall perform thescientific assessment as per scientific protocols and procedures, analyse the results, provide conclusions andrecommendations for further improvements and possible additional developments. Synergies with terrestrialapplications shall also be part of this review.DeliverablesBreadboardApplication/Need DateCurrent TRL TRL 2 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-9146Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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3 - 03 - Human Spaceflight and Exploration Preparation


Title Breadboard development for in-orbit demonstration of additive layermanufacturing technologies

ObjectivesThe objective of this activity is the design, development, and testing of a fully functioning breadboard model foradditive layer manufacturing (ALM) for potential in-flight demonstration aboard the ISS. This development shouldmake use of commercially available state of the art ALM technologies and modify them fit for purpose to functionunder the constraints of the ISS inhabited environment considering interface requirements, safety, and microgravity.

During a past GSP contract (4000102112) it was demonstrated that ALM provides significant added value for spacemissions for the manufacturing or repair of spare parts, consumables, tools, etc. Since ALM technology is designedto work on ground, many of these processes are g-sensitive. Whereas this would still enable them with littlemodification to be used under reduced gravity such as the moon, the µ-gravity environment aboard the ISS providesan additional challenge. It is intuitively the logical step to select those technologies that are not gravity sensitive.Indeed, NASA has performed successful parabolic flights with Fused Deposition Modelling (FDM) that extrudes amolten polymer filament from a nozzle and Electron Beam Free Form Fabrication (EBF3), a layer additive processusing a wire feedstock into an electron beam. Other technologies are available that provide much larger flexibility onthe design, e.g. powder sintering processes, whose application in a µ-gravity environment are less obvious but notnecessarily impossible.

The objective of this activity is therefore not to perform a trade-off on paper for technologies that are already fit forthe µ-gravity environment, but to allow modifications in the hardware design to make them fit for purpose. With thisdegree of flexibility the most versatile ALM process will be realised. The activity shall lead to the development of alaboratory breadboard which demonstrates functional performance as well as its performance under µ-gravityconditions, the latter may be tested by relative simple means such as reversing the direction of the gravity vector.Based on the performance a parabolic flight experiment, to verify performance under µ-gravity conditions, shall beproposed.DescriptionTask 1: Review of performance and technical constraints of state of the art ALM technologies and trade-off versusthe constraints to operate in the ISS inhabited environment. This shall consider interface requirements, powerconsumption, mass/volume, safety, and microgravity. Deficiencies and need of modifications shall be identified. Forexample, technologies that are not fit for purpose under microgravity environment may be modified to enableadequate performance.

Task 2: A design shall be proposed which specifically considers the operational constraints of the ISS inhabitedenvironment. This task includes a development and test plan for performance verification.

Task 3: Breadboard development including the modification of a commercial system, and complete assembly thatallows full functional testing. Possible improvements and modifications not considered from task 2 may beimplemented.

Task 4: Full functional and performance testing. This shall include as much as possible the demonstration of processperformance in µ-gravity environment.

Task 5: Conclusions, critical revision of all tasks, identification of improvements, and design concept and ROM costsfor a parabolic flight experimentDeliverablesBreadboardApplication/Need Date Q4 2015


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TRP Reference T323-419MM TD TD22Title Online ammonium analysis for water recycling systemsObjectivesPreliminary technical feasibility for space applications shall be demonstrated.DescriptionThe necessity to further reduce the needed logistics from Earth led to foresee developments and validations to closethe ECLSS water loop. For this reason, technology research activities focus on developing closed-loop waterrecovery system capable to recycle grey water , urine and any other waste water stream. Today , ESA technologiesfor recycling of grey waters ( based on membrane filtration technologies) have been demonstrated extensively. Theircapability to produce recycled water meeting ESA water quality standards has been proven at prototype level. Whenurine is considered as part of waste water stream to recycle, new technological challenges are faced, linked to thevery specific composition of urine (high salinity, complex and variable chemical composition, presence of urea and itsdegradation products, e.g. ammonium). Among the critical chemical components, ammonium is identified due to itsvery small size and its ability to cross membrane filtration, even at the level of reverse osmosis. The thresholdimposed by ESA water quality standards (ESA - PSS 03-402 Issue 1) is rather low, i.e. 0.5 mg NH4+ mg.l-1 andtherefore the need of a sensitive and reliable ammonium detection and quantification along recycling processes is ofthe utmost importance. There are a number of methods and devices available on ground for determining ammoniumions. Determination of such an analyte poses analytical problems related to the low selectivity of the methods andthe presence of many interfering factors (e.g. matrix effect, high salinity...). Promising analytical techniques areexisting, based on ion chromatography, flow injection analysis or sequential flow analysis with spectrophotometricdetermination. Such techniques shall be assessed with regards to their applicability to the considered watersmatrixes. Advantages like simultaneous detection of other N-species, e.g. nitrate, nitrite shall be identified.Criticalities for their potential adaptation to space shall be investigated.The proposed activity shall cover the major following work tasks:- Requirements definition, selection of study cases- Trade-off and selection of the best promising analytical methods for ammonium determination in the proposedcontext ( specific chemical composition, future adaptation to space)- Demonstration of their ability to meet detection and quantification requirements (threshold, accuracy, repeatability..)- Study of critical items regarding adaptation to space: identification, investigation and proposals to tackle them- Preliminary technical feasibility demonstration in the context of space applicationsDeliverablesStudy ReportApplication/Need Date Manned exploration


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Title Testing of innovative materials for passive radiation shielding for Humanspaceflight

ObjectivesDevelopment and testing of innovative materials for passive radiation shieldingDescriptionRecent studies have shown that the level of radiation exposure that astronauts would face in a mission to Mars is toohigh compared to the currently accepted risk limits. In order to mitigate the effects of the absorbed radiation, theoptimization of the shielding is of key importance. In a previous TRP study "Radiation shielding by ISRU and/orinnovative composites for EVA, vehicles and habitats", the characteristics of a number of innovative and ISRUmaterials were assessed for shielding of vehicles and habitats.

In this activity the most promising materials identified in the previous TRP shall be further tested and studied andincluded in the design of realistic vehicles and habitats.

In order to take into account the latest developments in the field, new materials (with high hydrogen content) fulfillingpre-screening criteria for their use in space application like safety, low cost, lightweight, strength etc) will be includedin the test campaign.

The use of life support equipment (e.g. water bags) and astronaut waste as shielding will also be considered.

This activity will be supported by detailed radiation simulation and irradiation campaigns at suitable facilities.DeliverablesStudy ReportApplication/Need DateCurrent TRL TRL 3 Target TRL TRL 5 Duration (Months) 30S/W Clause N/A Ref: to ESTER T-7637, T-19, T-9157

Applicable THAG Roadmap Radiation Environments & Monitoring,Effects Tools & Testing (2009) Consistency with THAG Roadmap Yes

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3 - 04 - Lunar Lander Missions

TRP Reference T316-414MM TD TD16Title Miniaturized Imaging LIDAR Systems for landing applications (Phase 2a)ObjectivesFollowing the completion and based on the achieved results of the "Miniaturized Imaging LIDAR Systems (MILS)-Phase 1", contract (Co#4000103730), the objective of this activity is to execute the follow-on phase of the MILSdevelopment, which is Phase 2a, targeting the landing application requirements (applicable for Moon and Mars).Starting from the defined preliminary sensor design, in this Phase 2a the detailed design (including manufacturingplans and test plans) of an elegant breadboard shall be established.The objective of the breadboard is to be representative of a flash (or hybrid flash/scanning) Imaging LIDAR systemand to demonstrate the clear advantages in terms of performance and miniaturization achievable with theimplementation of detector arrays instead of single pixel detector systems with a mechanical scanner.DescriptionImaging LIDARs (LIght Detection And Ranging), or in other words three-dimensional imagers, are considered a keyenabling technology for future exploration missions. One of the future applications of Imaging LIDAR sensors isduring the automatic descent and landing operations of a spacecraft (SC) on other planetary bodies (like Moon orMars). In fact an Imaging LIDAR is an enabling technology for the SC Hazard Detection and Avoidance (HDA)capability required for safe landing operations.Nowadays, Imaging LIDARs based on single pixel detector require complex and bulky scanning mechanisms inorder to reconstruct the landing site 3D image, with low spatial resolution (<400 x 400 points per frame in <6seconds) in order to be able to select a safe landing site within the possible SC trajectory envelope. These systemsare not able to achieve the desirable high landing area resolution (1000x1000 points in one frame), with fast framerate acquisition (frame rate >1Hz) and in a relative large observation field-of-view (>20 degrees). In addition thesesystems have a mass of more than 12 kg and have high power consumption (>60W).In the course of the "Miniaturized Imaging LIDAR Systems (MILS) -Phase 1" contract several novel technologies, inparticular detector arrays, have been identified and tested in a dedicated technology demonstrator breadboard.Detector arrays can be used in the development of a flash-type Imaging LIDAR system and with that pave the wayfor the miniaturization of the sensor while achieving the required optimal performance as needed for the landingapplication.The preliminary design of a MILS system for the landing application has been established in Phase 1. This activity(Phase 2a) shall design in detail an elegant breadboard that can be later tested in a representative landingenvironment. The objective of the proposed activity is to cover Phase 2a of the miniaturization development,comprising the detailed design of the Imaging LIDAR system for the landing application. As to the build standard thisbreadboard shall be an "elegant" breadboard, sufficiently compact and robust to be transportable and to survive apotential airborne demonstration. It is envisaged to integrate the breadboard in future ESA's GN&C test benches(under definition / development).

During this activity the following tasks shall be executed:- Detailed design of a MILS (Miniaturized Imaging LIDAR System) targeting the landing application requirements andperformances. The design shall take into account all the interfaces, analysis and definition of key design parameters(including thermal aspects, breadboard control, data handling and processing, and opto-mechanical considerations)required for future airborne demonstrations.- Establish detailed manufacturing plans for the MILS breadboard- Define a detailed test plan taking into consideration the expected requirements and system performances for aspacecraft landing scenario on Moon or Mars.

The expected main performances of the MILS elegant breadboard are:- Perform fast frame rate measurements (>1Hz) during spacecraft decent (assuming vertical and horizontal speedsup to 45 and 160 m/s respectively)- FOV > 20x20 degrees- no cooperative targets and relevant background illumination conditions- up to 3km maximum operational range- down to 2 cm range accuracy at short ranges- acquire the range information of the target inside the complete FOV with high resolution (goal of >512x512 pixels)- average power consumption < 50 W- total mass <7 kgDeliverablesDesign Dossier (incl. manufacturing plans and test)Application/Need Date Mars Sample Return, Lunar Lander, Lunar Polar Sample Return

Current TRL TRL 3 Target TRL TRL 4 Duration (Months) 10S/W Clause N/A Ref: to ESTER T-7860Applicable THAG Roadmap N/A Consistency with THAG Roadmap Yes

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TRP Reference T319-416MP TD TD19Title Structural TankingObjectivesThe objective of the activity is to systematically investigate, via a comprehensive and detailed design trade-off, themost effective implementation of structural tanking for a large lunar lander mission.DescriptionSpacecraft typically employ discrete tanks which support only the propellant mass and internal pressure loads andwhich are robust to the generated mechanical environment. For spacecraft this has always been sufficient but forlander missions, especially lunar landing with it associated large delta V requirements and significant gravity losses,the resulting propulsion system is very large and the structure necessary to support it is also significant (typically thiscan be over 60% of the spacecraft mass).Launch vehicles also achieve better mass fractions by employing structural tanking. Structural tanking is also seenon upper stage designs in both low and medium pressure configurations.Simplifying greatly, landing missions can be considered as the reverse of launcher missions. Improving the dry massto wet mass ratio would bring huge benefits and structural tanking has huge potential in this regard.

Therefore the activity is foreseen as a predominantly design and analysis based.Starting with a defined large lunar lander concept at mission level, different designs for the lander based arounddown-selected structural tanking concepts . Lander performance shall be evaluated based on and idealisedparameterised engines. The engines will provide requirements and constraints on the tanking design including butnot limited to internal tank pressure, expulsion rate, and propellant compatibility.

A materials selection and trade-off will be madeto the various applications. The trade-off criteria will be based oncommon structural considerations and materials consideration including but not limited to fracture control fatigue .

For the most promising down selected candidates the mechanical thermal and propulsion elements of the resultingconfiguration will be examined in detail considering but not necessarily limited to Optimum pressure levels andManagement of load introduction to pressure vessels.DeliverablesStudy ReportApplication/Need Date 2016 for input to studied

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-9168

Applicable THAG Roadmap Chemical Propulsion - Components(2012) Consistency with THAG Roadmap Yes

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4 - Space Transportation & Re-entry Technologies

4 - 01 - Launchers Oriented Technologies

TRP Reference T420-415MS TD TD20Title Development of new interface concepts for launcher main tanksObjectivesCurrent propellant tanks to structural intefaces have load limits. This activity will investigate new tank intefaceconcepts. The result aims to introduce mass and cost savings through development of these new concepts of themain tank interfaces.DescriptionAs main structural components rocket launchers include a main propellant tanks. These tanks are prevalentlycryogenic metallic pressurized structures with specific mechanical interface to inter-tank non-pressurized structures.The common design of this interface is based on Y-shaped rings. Those allow good transfer of the launcher loadswhile exposing manageable technological challenges. Nevertheless, the Y-ring solution has its limits both in terms ofloads (strength and buckling) as well as in material properties (manufacturing by roll forging).

Therefore, the purpose of the proposal is to study several designs of the interface and optimize the selected solutionin more detail. This should include both geometry of the interface as well as alternative new joining technologies.Although the selection of the studied materials will signficantly depend on the preferred geometrical solution,standard materials used for cryogenic tanks should be taken as a basis.

Beside tests at specimen level to demonstrate any new technology, there will be a breadboard demonstration.DeliverablesStudy Report, BreadboardApplication/Need Date All european Launchers. TRL 5 by 2018


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TRP Reference T419-410MP TD TD19Title High Order Cavitation Surge Characterization in Space InducersObjectivesThe proposed activity is intended to carry out an extensive experimental characterization based on innovativetechniques on the cavitation induced instabilities occurring in typical space rocket turbopumps, focusing in particularon the High Order Cavitation Surge Instability.

Having a deeper understanding on this form of instability represents an added value for space inducers designers, inparticular when the turbomachine re-design is requested for meeting more stringent mission requirements.DescriptionIn the axial inducers used for liquid propellant rocket turbopumps, typically working under cavitating conditions, it isusual to observe the development of flow instabilities, which can seriously degrade the performance of the machineor even cause its rapid failure.

Classically, these flow instabilities can be divided in three main categories: global oscillations, local oscillations andinstabilities caused by radial or rotordynamic forces.

The most dangerous and well recognized instabilities in cavitating pumps are due to global oscillations, i.e. vibrationswhich affect the pump and the entire propulsion system on a large scale (rotating stall, rotating cavitation, surge,auto-oscillation, unsteady blade cavitation). Some examples of local oscillations, on the other hand, are representedby the blade flutter and the blade excitation due to rotor-stator interaction or to vortex shedding or cavitationoscillations. Radial and rotordynamic forces, finally, are global forces perpendicular to the axis of rotation: the firstare caused by circumferential nonuniformities in the inlet flow, casing or volute; the second occur as a result of aneccentric movement of the axis of rotation.

Instabilities in cavities have been experimentally observed. The analysis identified the dimension of the cavity withrespect to the thickness of the blade passage as one of the driving parameter in the development of cavitationinduced flow instabilities. The occurrence of flow instabilities like rotating cavitation has been extensively reported inthe development of most high performance liquid propellant rocket fuel feed systems, including the Space ShuttleMain Engine the Ariane 5 engine and the LE-7 engine of the H-II and H-II-A Japanese rockets.

Recently, Japanese researchers have postulated that the resonance of higher-order surge instabilities with the firstbending mode of the inducer blades was responsible for the fatigue failure of the liquid hydrogen pump inducer of the8th launch of H-II rocket in November 1999.

The experiments shall be carried out in full-scale tests under fluid dynamic and inertial/thermal cavitation similarityconditions on an inducer suitable designed for representing today's high performance machine for liquid propellantrocket engine feed systems.

The inducer design shall take into account new experimental approaches for the detection of the specific High OrderCavitation Surge (HOCS) oscillation. Experimental configurations shall be identified to allow for the continuousmeasurement of the pressure oscillation within the channel, particularly suitable for the detection of the High OrderCavitation Surge. One test item, representative of the typical geometry and characteristics of inducers for liquidpropellant rocket engine feed systems, shall be suitably designed for allowing on-board measurements.

The axial pump shall be characterized under both inertially and thermally dominated cavitation conditions for thedetermination of the pumping and suction performance curves and the identification of the operational regimesleading to the occurrence of specific types of cavitation instabilities, with special reference to higher order surgemodes in the blade channels.DeliverablesStudy ReportApplication/Need Date Support to Future Launcher development.


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Title Monitoring Laser Peening for Stress-Corrosion Cracking and FatigueResistance Enhancement of Launchers External Structures

ObjectivesThe proposed activity has the primary objective of identifying and optimising the ideal Laser Shock Peening (LSP)process for improving Stress-Corrosion Cracking (SCC) and fatigue life performances of susceptible materialscommonly used for launchers external structures, by introducing quantified, controlled and repeatable compressiveresidual stresses. It can be used as a suitable method for enhancing, repairing or protecting from SCC failures anysensitive external structures exposed to coastal environment during integration and launch phases.DescriptionStress corrosion cracking (SCC) has been an issue in the space industry since the days of the Apollo programme.SCC is a failure phenomenon which occurs in engineering materials, typically metals but also ceramics andpolymers, by slow environmentally induced crack propagation. The crack propagation is the result of the combinedsynergetic interaction of mechanical stress and corrosion.

Many cases where structural failures of space hardware were caused by stress-corrosion cracking at launch sitescan be found in the literature, occurring both in American and European space programmes, and generatingsubstantial costs and delays. More recently, stress-corrosion cracking on the hydraulic power units has jeopardisedthe mission of the Space Shuttle Discovery in 2001. In March of 2006 the first Falcon 1 launch ended prematurelywhen the first stage engine shut down 34 seconds into flight due to a fire caused by a fuel leak due tostress-corrosion, likely caused by prolonged environmental exposure at Kwajalein. Atmospheric water condensation,exposure to coastal environment, typically at launch sites, and the presence of chemical substances such ascleaning fluids or accidentally released substances (e.g. hydrazine, cleaning solvents and hydraulic fluids) canpromote stress-corrosion cracking in launchers structures. Laser Shot Peening (LSP) is an emerging technique thathas been successfully used to introduce compressive residual stresses (therefore minimizing the risk of SCC) intometallic structures with a wide range of possible applications such as aircraft engines and structures, panel forming,nuclear power reactors, steel bridges and medical implants. For instance, the aeronautical industry is stronglyinterested in the possible application of the LSP method at different stages of the aircraft life, i. e. in production as acost and time effective solution to introduce compressive residual stresses in fatigue and stress-corrosion criticalareas, during maintenance as an on-site repair solution for unexpected fatigue and SCC issues arising at an earlystage or for ageing aircraft skin structures susceptible to different forms of in-service damages.

In launchers applications, LPS can be applied as highly repeatable process on aluminum, titanium, high strengthsteels as well as stainless steels.

Traditionally, the majority of the materials used in launcher structure manufacture are selected from known and wellproven aircraft applications. 2000/7000 series aluminum alloys, also used in SCC sensitive heat treatmentconditions, are commonly used for stages and inter-stages manufacturing, exposing the external structures to asignificant risk of SCC damage.

The proposed activity has the primary objective of identifying and optimising the ideal LPS process for improvingSCC and fatigue life performances of susceptible materials commonly used for launchers external structures, byintroducing quantified, controlled and repeatable compressive residual stresses. It can be used as a suitable methodfor enhancing, repair or protect from SCC failures sensitive external structures exposed to coastal environmentduring integration and launch phases.

In particular the activity is divided into the following phases:- Identify materials (SCC sensitive as well as highly resistant covering aluminum, titanium and steel alloys) useforlauncher structures as well as propulsion systems manufacturing.- Identify the most suitable LPS process and characterize the amount as well as depth of penetration and distributionof the compressive residual stresses induced.- Perfor a fatigue crack propagation and SCC characterisation test campaign on the selected alloys in both pristineand post-LPS conditions and correlate the results with the amount of residual stresses/Laser powersettings/microsture pre- and post-treatment, in order to optimise the process for the selected alloys.DeliverablesTest ReportApplication/Need Date All launchers. TRL 5 by 2017


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4 - 02 - Human Space Flight Oriented Technologies


Title Experimental Investigation of a Direct-Drive Hall Effect Thruster (HET)System

ObjectivesDesign, assemble and test a Direct Drive Hall Effect Thruster System.In the framework of this activity, the Direct Drive System has to be fully characterized, pointing out its advantages,detecting any potential issue and evaluating its performance (for different operating regimes of the thruster, i.e.different mass flow rates and thus different power levels for a fixed value of the applied voltage, and for differentconfigurations of the solar arrays).DescriptionThe idea for direct drive of Electric Propulsion systems has been around since at least 1970. The key motivation forthe development of direct drive is the desire to significantly reduce the dry mass of solar electric propulsionsubsystems by eliminating or simplify the heavy and expensive power conditioning electronics between the solararray and the electric thrusters.

After several studies performed both in US and Soviet Union between the years 1970-2000, in 2001 NASA started aprogram to develop a Direct Drive Hall Effect Thruster (D2HET) system. This program included understanding thebehaviour of high-voltage solar arrays in the plasma environment produced by the Hall-thruster based propulsionsubsystem, and direct-drive systems engineering. No direct-drive testing with an actual solar array was performedunder this development activity.The first direct-drive test was performed on a 1.3 kW Hall Effect thruster from the Keldysh Research Center,operated directly from a triple junction, linear concentrator solar array. The 8-to-1 stretched-lens concentrator solararray used in these tests was mounted outdoors and could produce up to 1.2 kW at 500 V under clear skyconditions. These tests successfully operated the T-100 thruster direct drive at up to 600 W and 550 V.

In 2011 NASA made the decision to implement a National Direct-Drive Testbed to address the technical issuesidentified in previous direct-drive investigations. The National Direct-Drive Testbed was designed to performdirect-drive tests at power levels an order of magnitude greater than previous tests (300-kW).In Europe the development of high voltage solar array (e.g. concentrator solar array) has been initiated. Theavailability of high voltage arrays could make possible the concept of direct drive for European Hall Effect thrusters.This could lead to a consistent saving of mass, complexity and cost of the electric propulsion subsystem. Explorationmissions that will have high power requirements are the best candidates to use this technology.DeliverablesStudy Report, Test ArticleApplication/Need Date Exploration Missions, TRL 5 by 2017

Current TRL TRL 3 Target TRL TRL 4 Duration (Months) 18S/W Clause N/A Ref: to ESTERApplicable THAG Roadmap Electric Propulsion Technologies (2009) Consistency with THAG Roadmap No

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Title Low Cost Hybrid Material Solutions for Radiation and Impact ProtectionSystems for Human Spaceflight

ObjectivesTo design, manufacture and test new low cost hybrid material systems which have excellent radiation and impactprotection for future human spaceflight applications.DescriptionFor human spaceflight and exploration, two of the most important requirements are protection against radiation andspace debris. Recent results from Curiosity's Radiation Assessment Detector (RAD) have revealed that for thetransit to Mars, exposure of humans, even while safely ensconced inside a protected spacecraft, is dangerously high.Therefore it is necessary to develop new material solutions whereby the crew would be protected from such effects.Another area of concern is that of space debris. Although the International Space Station can be manoeuvred toavoid collisions with space debris, it would be beneficial if new protective panels could be developed which couldreplace the existing panels and therefore offer better protection.

One material which is receiving widespread attention in the aerospace industry is GLARE, which consists of a fibermetal laminate composed of several very thin layers of metal (usually aluminium) interspersed with layers ofglass-fibre "pre-preg", bonded together with a an epoxy matrix. The uni-directional pre-preg layers are often alignedin different directions to suit the predicted stress conditions. The aerospace version of GLARE is already used in themanufacturing of the Airbus A380 upper fuselage.

In the proposed activity, two hybrid solutions will be evaluated which will target both radiation and impact protection.Modified forms of GLARE will be developed with alternative metallic materials compared to aluminium. These willinclude a lightweight version tailored towards impact protection for the ISS, and a more dense version tailoredtowards radiation protection. It is possible that the radiation version will contain a sandwich type construction withouter layers of Space GLARE, and a sandwich of aluminium foam, which could be filled with gel.

The activity will consist of the following:1)An initial investigation into the current state-of-the-art which will include novel metallic layers which could be usedfor Space GLARE. These will include lightweight materials such as Ti and Mg for space debris protection, and moredense materials such as Tungsten for radiation protection. The development of modular systems including thecombination of Space GLARE with aluminium foam, or aluminium foam impregnated with gel will also be explored.2)From the pre-selection phase, at least 3 sandwich combinations will be selected for further study. For the use ofradioactive shielding materials, special consideration will be given to properties such as attenuation effectiveness,strength, resistance to damage, thermal properties, and cost efficiency.DeliverablesStudy Report, Structural Test SamplesApplication/Need Date ISS Follow-on, Human Exploration Missions beyond Earth Orbit. TRL 5 by 2017

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8841Applicable THAG Roadmap Composite Materials (2005) Consistency with THAG Roadmap No

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4 - 03 - Generic Space Transportation Technologies

TRP Reference T401-401ED TD TD01

Title Development of a representative AFDX/Time-Triggered-Ethernet-basedavionics system for RASTA.

ObjectivesBased on ESTEC's RASTA reference avionic testbench, this activity will develop the Avionics Full DupleX (AFDX)and TTEthernet equipment necessary to evaluate avionic architectures, protocols and specifications derived fromlaunchers and space transportation use-cases (e.g. FLPP, Ariane6, MPCV).DescriptionThis activity shall provide the missing building blocks to the already existing testbench that will allow ESA/ESTEC toindependently evaluate, test and design TTEthernet and AFDX technologies that are currently being baselined inFLPP, AvioniqueX, Ariane6 and Multi-purpose crew MPCV.

It shall design and build the RASTA-compatible boards and components (typically communication boards andswitches) and make full use of RASTA's triplicated OBC architecture in a reference use-case implementation. Thesystem will be used to implement and validate communication parameters and architecture defined in severalprogrammes.DeliverablesEngineering ModelApplication/Need Date Future Launchers (Eg, Ariane6), MPCV. TRL 5 by 2017

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 12S/W Clause Open Source Ref: to ESTER T-8602, T-7803

Applicable THAG Roadmap Data Systems and On-Board Computers(2011) Consistency with THAG Roadmap Yes

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TRP Reference T418-407MP TD TD18Title Multi-phase Flow ModellingObjectivesThe activity aims to cover two main aspects to enhance the ESPSS (European Space Propulsion SystemSimulation)libraries in two aspects:

(1) Extension of the application field, by developing new components for the simulation of new advanced propulsionsystems, and for the coupled simulation of the propulsion system and vehicle dynamics.

(2) Improvement of the robustness and accuracy of the 1D fluid simulation, by implementing new discretizationmethods and updating the existing ones, and extending the physical formulation for the two-phase flow.DescriptionThe ESPSS is an ESA initiative which aim is to set up a common European platform for simulation of in-space andlaunch propulsion systems. Since today satellite manufacturers are evaluating the use of hybrid propulsion ascomplementary thrust units for orbital plane changes to the all-electrical ACS-engines, the development of newcapabilities for ESPSS for the detailed 1-D simulation of advanced space propulsion systems arises then as a logicalactivity, in which the following tasks should be tackled:

a) Extension of the fluid/solid properties databaseb) Development of analytical correlations for the 1D simulation of the heat and mass exchange between the grainand the fluid, as well as the grain regression.c) Simulation and analysis of validation cases.

Further, the ESPSS libraries allow the 1D simulation of complex systems under two phase and two-components, i.e.two phase flow conditions of a fluid coexisting with non-condensable gas. The formulation used so far in the librariesis based on the homogenous equilibrium hypothesis, where the liquid, vapour and non-condensable gas coexist atthe same temperature and pressure in each node. Recently, a new formulation has been proposed, where differenttemperatures for each phase of the fluid is considered. In the present activity it is proposed to extend this newformulation taking into account the different flow regimes (annular flow, bubble flow, slug flow, etc) in the formulationof the library, as well as the validation of the new formulation with test cases.DeliverablesSoftwareApplication/Need Date All propulsion systems. TRL 5 by 2016

Current TRL TRL 4 Target TRL TRL 5 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-8091Applicable THAG Roadmap Aerothermodynamic Tools (2012) Consistency with THAG Roadmap Yes

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TRP Reference T402-403SW TD TD02

Title New Generation Launcher and Space Transportation Advanced AvionicsTest Bed

ObjectivesThe Advanced Avionics Test Bed for Space Transportation Systems shall allow to create a reference implementationthat can be re-used in several projects across the SD4 mission domain spectrum. The test bed shall also allow toease the missionisation process of the avionics of space transportation. The test bed will be available to industry, butshall also allow ESA to win hands-on experience and in-house knowledge along the development cycle of anavionics system and in particular for the integration phases. It shall also provide for a common "language" formulti-company projects and a complete architecture for testing hardware / software implementations on someselected space pre-qualified hardware and avionics.

Based on the new requirements set by AvioniqueX, FLPP, MPCV-SM as well as other relevant missions (e.g.re-entry, IXV, etc), the test bed should be able to demonstrate and support fast prototyping and development oftechnologies in order to support the projects in various phases (analysis, validation etc).DescriptionArchitectured in a modular way, the test bed will be, in the long term, a complete avionics solution able to cope withmodern and demanding closed loop controlled applications, data handling and software for space transportationsystems. It will be able to merge elements from the three Avionics discipline (Data Systems, Guidance, Navigation &Control as well as Software Systems) into a single compact and harmonized product. The computer and datahandling will make use of referenced onboard computers (e.g. Avionique-X has been looking into multicore systems),while the GNC will focus on optimal guidance, estimation and navigation sensing suite, and closed loop control parts.The software discipline will offer predictable real-time infrastructure able to support fast auto-coding andmissionisation processes.

Departing from elements, techniques, and technologies in the three avionics areas (Data Handling, GNC, andSoftware), the advanced avionics test bed activity shall comprise the following tasks:

- Task1. Requirements definition of the test bed, with inputs from FLPP, AvioniqueX and MPCV-SMThis task will allow the definition and collection of the requirements as well as of the space transportation scenariosrequired to be addressed. The scenario requirement shall be translated into GNC requirements that in turn shall betranslated into real-time software and hardware requirements for the test bed. Orbital and trajectory guidancerequirements will be considered as well as navigation requirements (navigation suite and estimation processes), andclosed loop control requirements. A classification of the possible scenario requirements will be provided. A specialcare will be taken as to harmonize the requirements with the concerned entities (e.g. ESA FLPP, CNES, MPCVproject mngt, etc), to ensure a total compatibility in objectives.

- Task2. Definition and design of the test bed and utilization usecasesThis task shall be devoted to the architecture of the test bed, i.e. the different parts and modules composing theavionics test bed. for example, the activity shall select the navigation sensing suite, the estimation algorithms, theguidance profiles, the control algorithms, the computing hardware, the real-time software components, and therequired elements that would bound together the previous parts and components. This architecture shall be basedon the results of all previous studies as well as the components or building blocks available across variouslaboratories. The activity shall define the hardware level architectural definition, including sensors and on-boardcomputer modules design, as well as real-time software components. The make or reuse trade-off will be made, witha preference for reuse. The characterization of the test bed will be performed as well in this task.

- Task 3. Validation of the test bed and commissioningThis task shall comprise the validation of the test bed built using some Case Study (e.g. VEGA Launcher, Ariane6)and a set of test cases. The test cases and the definition of scenarios will be made based on the current availablemission opportunities and specially taking into account the specific programs targeted in SD4.

For information, here are some detailed technologies that could be part of the testbed:- For Data Handling: new multi-core technology, new high performance and scalable space busses (Time triggeredEthernet / AFDX) to answer the new and future data rate and determinism requirements identified in both AvioniqueXand FLPP, dedicated Launcher software services and hardware support, file-system based mass memory,dynamically reconfigurable FPGAs, supporting the comparison and selection of space and COTS/commercialmicroprocessors and other EEE parts, identify the missing technologies for the future missions.- For Software: functionality and performance of the new multi-core Real Time Operating system, architecture to mixreal time and not real time (or critical and not critical) functions with the time and space partition system (IMA,Integrated Modular Avionics), model driven approach and automatic code generation.- For GNC: optimal guidance laws for ascent and stages re-entry, navigation sensing suite with hybridized solutionsand estimations, and advanced robust control techniques for complex flight management functions.

Note: the activity is proposed as a joint effort of TD1 (data handling), TD2 (software) and TD5 (control). It should bein an "avionics" TD, should it exist, or as a cross sectorial activity. It is in line with the Harmonisation avionicsroadmap, activities A9 and O2.

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DeliverablesPrototypeApplication/Need Date All launchers, MPCV. TRL 5 by 2017

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-303, T-8074, T-8602, T-7662, T-7819, T-88Applicable THAG Roadmap Avionics Embedded Systems (2010) Consistency with THAG Roadmap Yes

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5 - Telecommunications

5 - Telecommunications Technologies

TRP Reference T507-408EE TD TD07Title AMC/Metamaterial Antennas for Broadband ConnectivityObjectivesThe aim is to design, implement and test a breadboard demonstrating the benefits of a metamaterial based phasedarray antenna in Ku and/or Ka-band.DescriptionRecently, the US company Kymeta (http://www.kymetacorp.com) announced a research contract with Inmarsat todevelop an innovative meta-material based antenna for the aeronautical Global Express market. The technologypromises low profile, fully electronic scanning at a fraction of the power required with conventional phased array(USB power as opposed to kW). In Europe, there has been little work within the Satellite Industry to explore themetamaterial technology for phased array applications in Ku- and/or Ka-band. This actvity will provide an opportunityfor European industry to explore the benefits of metamaterial in a satellite ground segment context.

The activity is foreseen to have two phases. A first phase to study the feasibility, and a second phase forbreadboarding and testing.A first phase will study a literature survey to determine the State-of-Art. This is followed bythe selection and characterization of AMC/metamaterials and a preliminary antenna design. Special attention shallbe given to the electronic steering capability at Ka/Ku bands. Using all lessons learned a detailed design shall beperformed, a prototype manufactured and fully characterized. Finally, conclusions will be drawn and proposals forfuture activities will be suggested.DeliverablesBreadboardApplication/Need Date TRL 5 by 2017


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Title Antennas and Signal Processing Techniques for Interference Mitigation inNext Generation Ka band High Throughput Satellites

ObjectivesThe objective of this project is to investigate interference mitigation at antenna level, using adaptive nulling, anddemonstrate the concept through a prototype. This would allow sharing the band currently allocated to fixed“terrestrial” services (i.e. microwave links) with uncoordinated satellite services.DescriptionFuture Broadband Satellite Systems target achieving system capacity approaching the terabit/s. The most efficientway for pursuing this achievement is to use all the available band in Ka for user links, moving the feeder links to Q/Vband. In the forward link, it could be possible to exploit the portion of the band traditionally used for the feederdownlinks, referred to as "Ka coordinated band" (17.7-19.7 GHz).

The main problem in this band is that satellite systems cannot claim protection against other terrestrial services,allocated to the same band. Terrestrial services (fixed wireless systems operating in the 18 GHz frequency band)are allowed to transmit a power of up to 10 W at the antenna input and 55 dBW of EIRP in this band. Thus, efficienttechniques to mitigate the deriving interference must be investigated. In particular, this project aims at investigatingAdaptive antennas architectures and signal processing techniques for mitigating interference from terrestrialsystems.

Two main categories of technologies are identified: - Sidelobe cancellation applied to aperture antennas - Adaptive beamforming based on 2D phased array

The first technology allows cancelling adaptively an interference signal received from a sidelobe of the apertureantenna thanks to an additional omnidirectional antenna allowing nulling in the digital domain or at IF a specific partof the beam pattern. This technique should in principle not require a significant change of the user terminal. Thistechnique has been investigated in the past. The scope in this context is to verify its effectiveness in this specificscenario. On the other hand, adaptive beam forming using phased arrays could be used to achieve betterperformance. This second category is a possible solution in a long term scenario, the main issue being the derivingcost.

The project shall include:- Review of regulatory environment in Ka shared band- Characterization of terrestrial interference in the Ka shared band- State of Art review of relevant sidelobe cancellation and adaptive beamforming techniques- Simulation of the promising techniques and technologies in a representative simulated environment- Assessment of cost impacts on the UT- Breadboarding of a proof of concept for the sidelobe cancelling reflector- Recommendations on the mitigation techniques to be implemented in future consumer terminalsDeliverablesTechnical Reports, Simulation Software, prototypeApplication/Need Date Future Broadband Satellite Systems, TRL 5 by 2016


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Title Development and reliability assessment of SiGe based wideband LNA andwideband mixer for space

ObjectivesThe objectives of this activity are to evaluate the capability, the level of integration and the reliability of EuropeanSiGe technology for the implementation of a wideband LNA and a wideband mixer (up- and down-converter) forspace. The applications from C- to K-band frequency targeted are the (i) generic post-processor (i.e up-converter) fordigital transparent processor based payload, (ii) generic pre-processor (i.e. LNA and down-converter) for the digitaltransparent processor, standard telecommunication payloads, (iii) TM/TC transponders and (iv) SAR instruments.DescriptionSiGe BiCMOS technology is competing with GaAs up to frequencies as high as 40GHz due to the dramaticreductions in device feature size. Indeed, SiGe HBT technology enables integration of RF/analogue and CMOSdigital logic functions into fully monolithic BiCMOS structures. It is an attractive alternative combining, at reducedcosts, the best attributes of MOSFET technology (low power consumption logic, large-scale integration) and bipolartechnology (low phase noise, threshold uniformity). Such a process is particularly interesting for realizing highlyintegrated multi-function chips (i.e. variable attenuator + variable phase shifter + gain blocks), frequency generation(PLLs, VCOs, prescalers) or High-speed A/D and D/A converters.

This activity aims to evaluate the capability, the level of integration and the reliability of European SiGe technologyfor the implementation of a wideband LNA and a wideband mixer (up- and down-converter) for space. The tasksinclude:- Task 1. Survey of the capability of European SiGe technology for integrated LNA and mixer operations up toK-Band, and definition of the targeted technical specifications for wideband LNA and wideband mixer which could beused as up- and down-converter.- Task 2. SiGe technology reliability data overview- Task 3. Design, manufacturing and electrical testing of single basic cells for the wideband LNA and wideband mixer(up and down converter) using SiGe process.- Task 4. Design of the wideband LNA and wideband mixer (up- and down-converter, from C- to K-Band) testcomponent- Task 5. Reliability test plan definition- Task 6. Manufacturing and electrical characterization of the wideband LNA and wideband mixer (up- anddown-converter)- Task 7. Reliability testing and results analysisDeliverablesPrototypeApplication/Need Date TRL 5 by 2018

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7830, T-9057, T-7908Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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Title Friction Stir Welding of Titanium Silicon Carbide Composites for XenonTanks Applications

ObjectivesThe objective of the proposed activity is to develop a suitable Friction Stir Welding process ideal for application onTitanium Silicon Carbide composites, which will be used for Xenon tanks applications, allowing manufacturing tanksthat are less than half the weight of the equivalent current monolithic design, while maximizing the weldingperformances and reducing the manufacturing steps and costs to a minimum.DescriptionOver 120 spacecraft presently use electric thruster systems. They are now being used to provide most of thepost-LEO propulsion demands on geosynchronous missions. The availability of practical, high-specific-impulseelectric thrusters with long life, and the development of electrical power-systems required to sustain them, hasresulted in extremely rapid growth in the applications of this technology. ESA has engaged in programmes (e.g.SGEO, AlphaBus) where Xenon electric propulsion sub-systems are used to perform all orbital maneuvers (onSGEO) and inclination and eccentricity control for North/South station keeping as well as unloading of reactionwheels (on AlphaBus). Xenon storage pressure vessels with unique characteristics are needed. These tank must behigh performance, light weight, and designed to withstand severe launch and operational loads and are normallymanufactured with EB welded and composites overwrapped Titanium shells.

Titanium Silicon Carbide (TiSiC) is a Titanium alloy reinforced with continuous Silicon Carbide fibers aimed athigh-end applications (e.g. aeronautical and petrochemical). The advantage of ceramic fiber composites is that theycan be stronger and stiffer than the equivalent carbon structures. Silicon carbide fibers used to reinforce TiSiC are 4times stronger and 5 times stiffer than carbon fibers offering the possibility of significant weight savings. Fiberreinforced Titanium Matrix Composites (TMC) meet or exceed the performance of high strength steel, are corrosionresistant and are 30% to 70% lighter than conventional metal parts, with excellent fatigue properties and providingcrack arrest capabilities thanks to fiber bridging.

A small scale Xenon tank demonstrator has been successfully manufactured and tested showing promising masssavings and performances, however it has highlighted difficulties related to welding aspects: traditional fusionwelding techniques have a detrimental impact on the fibers/metal interfaces. Solid state welding processes such asFriction Stir Welding (FSW) is considered to be the most significant development in metal joining in decades and isadopted worldwide in a wide range of applications including aerospace primary structures. It allows joining materialsin the solid phase without reaching the melting point therefore leading to excellent mechanical and fatigue crackpropagation properties (comparable with the base material characteristics). Since with the FSW process the jointtakes place in the solid phase, very little heat is developed resulting in a very small Heat Affected Zone (HAZ), withminimal distortion and minimal residual stress, making it the ideal welding process for fiber reinforced materials: thenon-reinforced area (need for performing the weld) with be reduced to minimum and its performances maximizedthanks to the use of FSW.The activity will be divided in 3 phases:- Phase 1: Identification of the most suitable TiSiC material composition and characterization of mechanical, fracturemechanics, corrosion and stress-corrosion cracking properties.- Phase 2: Development, characterization and validation of a FSW process and tooling system able to weld theidentified TiSiC reinforced material, starting from sheets up to formed shells.- Phase 3: Characterization of the mechanical, fracture mechanics, corrosion and stress-corrosion crackingproperties in the performed FSW TiSiC joints.DeliverablesStudy ReportApplication/Need Date TRL 5 by 2017


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TRP Reference T519-417MP TD TD19Title Low-Erosion Long-Life Hall Effect ThrusterObjectivesThe aim of the proposed activity is to develop a low-erosion HET with the following objectives:• modeling and understanding of the couplings between the ceramic discharge channel geometry, the magnetictopology, and the ceramic erosion patterns.• design of an upgraded channel geometry and magnetic circuit with substantially lower erosion rates.• Test of the new design during the low erosion rate phase with a sufficient duration to characterize the stability of theerosion rate and estimate the overall lifetime capability.DescriptionThe lifetime capability of Hall-effect thrusters (HET) has been demonstrated by test and qualified worldwide to reachthe 10000 hours milestone. This is covering with margins the need for north-south station-keeping with electricpropulsion even for the largest Telecom platforms. However, the use of electric propulsion is expanding also in thedomain of orbit topping and for orbit transfer from GTO to GEO. Many platform configurations are possible but one ofthe most attractive from the point of view of mass and cost considerations requires the use of the same thrusters fororbit-transfer and station-keeping thereby drastically increasing the lifetime and total impulse requirements of theelectric propulsion subsystem.The main ultimate limitation in terms of total impulse capability for Hall-effect thrusters is related to the mechanicalerosion by ion bombardment of the ceramic discharge channel. This is ultimately leading to exposure and erosion ofthe magnetic pole pieces, which in turn is leading to progressive thruster performance degradation and eventuallythruster failure. Therefore, a specific thruster design optimised to reach a steady state of very low erosion rate isneeded in order to remove ceramic erosion as the main parameter of Hall-effect thruster lifetime limitation.The tasks are :- Perform erosion simulations coupled to plasma thruster modeling in order to reproduce available lifetime test data.- Analyze and identify what are the critical plasma parameters that govern erosion rate in relation to channelgeometry and global or local magnetic topology.- Perform the design of the ceramic geometry and of the magnetic topology.- Update the design an existing Hall-effect thruster that has been well characterized in terms of lifetime capability andceramic channel erosion, keeping unchanged the ceramic material that is already optimized in terms of sputteringyield when used with xenon and at a given discharge voltage- Perform a short endurance test campaign with the updated thruster- Analyze the test results and perform a prediction of the expected total lifetime capability of the new Hall-effectthruster designDeliverablesStudy ReportApplication/Need Date Any telecommunication satellite using electric propulsion, TRL 5 by 2017


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TRP Reference T517-412MM TD TD17Title Micro-optoelectronic FGUObjectivesThe objective of this activity is to breadboard a Frequency Generation Unit for Telecommunication Payloads basedon micro-optoelectronic technologiesDescriptionA recently completed ARTES-1 study on next generation Telecom payloads based on photonic technologies (thatexamined the optimisation of various of microwave-photonic PL designs) suggested an advanced and complex FGUdesign implemented by discrete opto-electronic devices.

A path to reduce the mass and power of this FGU is to implement it by micro-optoelectronic/micro-photonictechnologies targeting miniaturisation of components and higher level of integration. This is the approach that theAgency has followed for the other 4 equipment that are under consideration for the Microwave-Photonic PL designsi.e, the Frequency Converter and the Optical Switch (1st generation) and the Photonic Beam Forming and PhotonicRF Filtering (2nd generation). The micro-photonic technologies to be considered include among othersmicro-mode-locked lasers and micro-optoelectronic oscillators for the generation of optical frequency comb for thereplacement of multiple discrete laser sources. In addition, innovative and optimum ways of integrating the"micro-Frequency Comb" generator with photonic demultiplexers, modulators and possibly with other devices suchas optical amplifiers and optical switches, if agility in LO distribution is required, shall be investigated.

The work will involve:- Task 1: Review of micro-optoelectronic/micro-photonic techniques for FGU, Trade-Off of conceptual designs,Selection of preferred conceptual design- Task 2: Breadboard detailed design- Task 3: Breadboard Manufacturing and Testing- Task 4: Test Results Analysis, Conclusions and RecommendationsDeliverablesBreadboardApplication/Need Date Telecom satellites, TRL 5 by 2017


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TRP Reference T507-409EE TD TD07Title Multiple Beam Antennas based on Reflectarrays & TransmitarraysObjectivesTo develop multibeam antennas based on passive reflectarrays and/or transmitarrays. The new antennas shall bedesigned to generate multiple spot contiguous beams for broadband applications or multiple shaped beams forbroadcasting.DescriptionReflectarrays and transmitarrays can be designed to steer the reflected and transmitted beam away from thespecular direction or to shape it according to preassigned requirements. Their properties can be tuned also withrespect to the frequency. Their increased number of degrees of freedom may be beneficial in the design ofmultibeam antennas. The main expected improvements are: 1) the reduced number of apertures with respect toarchitectures based on conventional reflectors; 2) the planarity of the panels with benefits in terms of accommodationand deployment; 3) minimized crosspolarized components. The main expected criticalities are: 1) discrimination infrequency: contiguous beams have to work at different frequencies really close one each other; 2) discrimination inangle: contiguous beams have point in different directions; 3) discrimination in polarization: contiguous beams haveto exhibit different polarizations (circular or linear).

The activity will be organized in 4 parts: 1) identification and preliminary design of reflectarray and transmittarrayantenna architectures suitable for the generation of multibeam coverages as defined in operational Telecommissions; 2) detail design of a promising configuration; 3) identification, design, manufacturing and testing of themost critical components needed to validate the antenna concept; 4) comparison in terms of RF performances butalso mass, cost and complexity between the multibeam antenna based on reflectarrays and/or transmittarrays and aconventional reference antenna. The activity is proposed by TEC-EEA in coordination with TEC-ETP and TEC-SBS.DeliverablesBreadboardApplication/Need Date Ku- and Ka-band multi spot beam antennas, TRL 5 by 2018

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7912Applicable THAG Roadmap Array Antennas (2011) Consistency with THAG Roadmap Yes

TRP Reference T506-406ET TD TD06Title Non-regular Multibeam Coverage PayloadsObjectivesThe aim of the present activity is to investigate novel Non-regular Multibeam Coverage Payloads architectures forfuture multibeam satellites with Non-Uniform Traffic request over the coverage and to develop dedicated designtools.DescriptionNon-regular Multibeam Coverage Payloads offer substantial advantages to maintain an affordable payloadcomplexity while offering substantial advantages in increasing the offered satellite capacity for non-uniformlydistributed traffic request (preliminary assessment showed a potential increase of 50% of the offered capacity). Thestudy shall investigate novel Non-regular Multibeam Coverage Payloads architectures for future multibeam satelliteswith Non-Uniform Traffic request over the coverage and to develop dedicated design tools. Expected outcomesinclude:- definition of optimal coverage strategies and development of dedicated tools (with a transfer of ESA know-how onrelevant coverage and frequency plan optimization techniques- identification and trade-off of payload/antenna architecture- preliminary design of a future Non-regular Multibeam Coverage Payload for Non-Uniform Traffic- main performances and budget- cost analysis- identification of technology gaps and technological roadmapDeliverablesStudy ReportApplication/Need Date Future multibeam satellites with Non-Uniform Traffic, TRL 5 by 2017

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-7916, T-7908, T-7925, T-7825, T-7909, T-79Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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6 - Navigation

6 - Navigation Technologies

TRP Reference T604-401EE TD TD04Title Data Exploitation of new Galileo Environmental Monitoring Units (EMUs)ObjectivesTo create the processing chain to generate physical parameters from the raw EMU data including calibration arisingfrom modelling and cross-calibration. This shall allow rapid access to the data for Galileo operations and build up adatabase for validation of specifications and modelling. Improve the statistics and functionality of the current MediumEarth Orbit (MEO) models. The modelling process shall allow easy updating of the model as new data accumulate.DescriptionThe radiation environment of the Galileo spacecraft is severe and still poorly characterised. Current models of theGalileo orbit are based on a dataset that is much shorter than a solar cycle. Following the termination of radiationmonitoring from Giove-A and -B spacecraft operations using the Merlin, Cedex and SREM instrument, Galileo orbitradiation environment monitoring will resume with the novel EMUs on 2 FOC spacecraft. These data will be exploitedto validate the environment specifications, reduce uncertainties, define margins, support satellite operations (e.g.anomaly investigations) and improve models for future design. A processing chain will be created to generatephysical parameters from the raw data. As part of this process, calibration including Monte Carlo radiation modellingof the instrument response will be performed and there will be cross-calibration with comparable radiation datasetswhere mapping between the different locations is possible. Further development of radiation models of the Galileoenvironment e.g. MEO-V2 model will be performed and validation of general trapped radiation models will beundertaken, in order to improve the reliability of future spacecraft in the Galileo orbit. Priority will be given initially todeveloping the data processing tools, then the modelling techniques, with the modelling itself occurring mostly oncesufficient data have accumulated. Complementary Giove data will also be included in the new models.DeliverablesData and Model AlgorithmsApplication/Need Date Galileo Systems Analysis available by 2016 (data) 2017 (models).

Current TRL Algorithm Target TRL Algorithm Duration (Months) 18S/W Clause Operational SoftwareRef: to ESTER T-10, T-8374

Applicable THAG Roadmap Radiation Environments & Monitoring,Effects Tools & Testing (2009) Consistency with THAG Roadmap Yes

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TRP Reference T606-404ET TD TD06Title End to End Dissemination ToolObjectivesThe objective of this activity is to develop an end-to-end data dissemination simulation tool to help in the detailedcharacterisation of the mechanisms for the control and mission data dissemination within a Galileo architectureincorporating inter-satellite links.DescriptionThe incorporation of inter-satellite-links to the Galileo architecture is under detailed assessment by the GNSSEvolution Program, given its visible potential to:- Enhance the overall constellation command-ability- Enhance the overall constellation monitoring-ability- Simplify the Ground Segment, reducing the number of remote ground stations- Enhance the navigation message accuracy- Enhance constellation autonomy

The incorporation of inter-satellite-links to Galileo imply an important evolution of its functional and physicalarchitecture. It enables an alternative and/or complementary mechanism for the control and mission datadissemination within the System; which detailed and complete characterization requires of sophisticated end-to-endsimulation tools.

The activity high level tasks are as follows:- Consolidation of the tool specification; namely functional, performance and external interfaces requirements (initialspecification prepared by ESA).- Definition of the tool physical architecture; namely main physical blocks, related internal interfaces, and corealgorithms.- Definition of the tool physical detailed design; namely software modules, detailed algorithms, detailed internal andexternal interfaces.- Development and verification of the tool.- Consolidation of the definition of the operational scenarios to be analysed (initial definition prepared by ESA).- Extensive analysis of the control and mission data dissemination (e.g. in terms of throughput, latency, PER, BER,etc.), under the above operational scenarios; which shall include at least: i) Nominal G2G FOC operational scenarios. ii) Nominal G2G IOC to G2G FOC operational scenarios iii) Preventive and corrective maintenance (at ground or/and space segment) iv) Contingencies (at ground or/and space segment)

The final result of the activity shall be a tool to assist in the design of INter Satellite links for the Next Generation ofGNSS.DeliverablesSoftware

Application/Need DateThis activity is a relevant input to the tasks on Galileo II architecture definition to beperformed within ESA. Prototype needed for the next EGEP phase 2015-16.

Current TRL Algorithm Target TRL Prototype Duration (Months) 12S/W Clause N/A Ref: to ESTER T-8817Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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TRP Reference T606-406ET TD TD06Title Enhanced methodology and tools for system performance evaluationObjectivesAlong with the definition of the future GNSS systems and missions, the objective of this activity is the definition of anew methodology for performance assessment at system level complementary to the typical macro-models currentlyused, in line with the evolution of the services and the new system capabilities. This methodology is supposed tosupport realistic assessment of more complex services delivered in challenging environment taking into account alsothe time and space dependency. The activity also includes the design, development and testing of a tool in line withthe proposed methodology.DescriptionThe performance of the future GNSS systems will be driven by more and more demanding applications asking forthe ultimate accuracy in the most challenging scenarios and under every condition. To reply to this need, servicesare becoming more and more sophisticated, system features more and more complex (time/space diversity,advanced coding etc.) and new methodology and tools for assessing the performance level are therefore needed,along with the on-going definition of the second generation of GALILEO satellites and an extension of the EGNOSV3 mission together with their enhanced capabilities.

In fact, system performance evaluation is often based on standard figures of merit (Weighted Least Mean Square(WLMS) accuracy, Dilution of precision (DOP), DOC, etc.) and on macro-models for the environment which considera number of assumptions and simplifications. Although valid for well-established performance indicators, thesesimplifications are normally not suitable for analysis of future services, applications. In particular, the description ofthe environment is generally over-simplified and does not adequately consider possible dependencies on the actualobstacles, user location, time, and most GNSS performance are assessed based on a snapshot analysis of systemrequirements, normally averaged, with very basic visibility profiles. On the other hand, different approaches such asa deterministic ray tracing for all the possible, time-variant, sources of multipath events, are too complex to allow foran assessment on a large scale.

An intermediate level of abstraction is therefore necessary, that would include the definition of new syntheticperformance indicators to capture for example the effectiveness and the speed of the transport of information to theuser, the robustness of the data delivery, the capability of a filtering solution etc. and the modelling of the realisticevolution in both space and time of a given scenario. Specifically, the environmental aspects might include thoserelevant to blockage/masking, multipath and signal propagation in both the ionosphere and the troposphere. Theassociated effects on the performance might be estimated at the filtered PVT level (position domain), average time tofirst fix, time to authenticated fix, average and peak time for key recovery, continuity of given service level, probabilityof cycle slips and/or loss-of-lock, comparison among different time space diversity schemes, etc.

Modelling the RF environment should consider, as a minimum, the effects of (1) fading and multipath, (2) RFinterferences and (3) signal propagation in both the ionosphere and the troposphere.

The objectives of this activity would be then to define the methodology, the performance indicators and thescenarios, implement them in a tool and analyse the performance of more complex services. The proposed approachwill include standard cases from which one could include more or less complexity to focus on a particular study,application, etc. Furthermore, the inclusion of visual tools and graphics as much as possible would help analysis andconsolidation of the results.

Tasks:- Definition of services/key performance indicators/models/methodology for system performance evaluation- Definition of scenarios for performance assessment- Requirement definition- Candidate architectures for potential tool implementation- Simulation tool design- Simulation tool implementation- Testing and validation of tool- Performance evaluation in the predefined scenariosDeliverablesSoftwareApplication/Need Date Next EGEP phase starting 2015-2016


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Title Interference detection/protection for Telemetry/Telecommand andmission links

ObjectivesThe objective of this activity is the investigation on potential techniques for thedetection/characterization/classification/localization/potential mitigation of interference to be embedded or added tothe telecommands or mission receivers and protect space assets against interference sources.DescriptionProtection of space assets is becoming more and more important now that vital services and applications aredepending on space infrastructure. This is particularly true in the domain of navigation where an increased number ofapplications like safety of life aeronautical services, critical bank transaction are relying on the services provided bythe GNSS systems as the primary if not the sole source of the time and position solution.

Designing robust telecommanding and Mission receivers is therefore one of the mandatory requirements for thedesign of future systems. The support also for the investigation on the nature of the threat, the characterization andeven its localization/mitigation are also becoming features of interest to ease the investigation and theimplementation of a solution/countermeasure, that would allow the overall infrastructure to be more robust. Thisactivity is focusing on this additional capability.

Key characteristics of the identified solution would be the minimum modification to the currenttelecommanding/Mission receiver/antenna configuration, the maximum flexibility towards the characterization andclassification of the type of interference, as well as its range of power level, and good accuracy in the localization.

This activity shall look broadly to the type of interference and techniques to allow its detection, characterization,classification and localization starting from simple power profile to more complex Doppler or Phase tracking, onboard quasi real time against offline post processing, shall also define the scenarios and the mission profiles (GEO,MEO, IGSO). The set of most suitable techniques shall be traded off taking into account performance and complexityaspects. Finally the selected interference detection and protection techniques shall be implemented in a simulatorrepresentative of defined realistic scenarios and performance analysis run.

Tasks:- Definition of scenarios/ mission profiles- Definition of interference type/characteristics- Detection/characterization/classification/localization techniques /assumptions on the equipment- Analysis of the performance/tools and simulationsDeliverablesStudy ReportApplication/Need Date Next EGEP phase starting 2015-2016


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TRP Reference T606-405ET TD TD06Title Orbit /SRP modelling for long term predictionObjectivesThe activity aims to analyse and support the long term extension of Galileo ephemerids for mass marketapplications, by providing a more accurate model of SRP over these longer periods. The final output shall be a SRPmodel tailored to improving GNSS satellite orbit determination and in turn improving user positional accuracy.DescriptionIn an era of high resolution gravity field modelling the dominant error sources in spacecraft orbit determination arenon-conservative spacecraft surface forces, such as: Solar Radiation Pressure, antenna thrust, Earth' albedo,thermal re-radiation, etc. The conventional approach to these problems is to use an empirical blind model whichabsorb all the forces but this approach introduces systematic errors and limit the prediction of the orbit. In the lastyears several wind-box model have appeared, developed based in GPS and Glonass official information, toovercome this limitation.

For Galileo these models are not yet available despite more accurate information can be used to generate them. Inthis activity it is proposed to analyse the ephemerides extension up to one week with centimetre accuracy bymodelling all possible non gravity forces for Galileo In Orbit Validation satellites. This would allow the usage of thoseephemeride parameters for acquisition, and potentially also for coarse navigation, in quasi permanent warm startconditions. A feature that would give GALILEO important advantage compare to other systems with respect to massmarket applications

Modelling of the clock can be analysed as well if necessary to maintain the accuracy.

Following input information is required by force:1.Solar Radiation Pressure force modelled as Wind-Box or finite element.- Surfaces dimension from the Mechanical ICD.- Surfaces properties- Nominal attitude model- On-board attitude determination from telemetry: sun vector, Earth vector and antenna array measured position.2.Antenna thrust- Transmitted power by satellite.3.Heating or cooling effects (responsible for Y-bias and asymmetries)- Thermistor temperature at selected locations.- Radiators dimensions and performance.4.Earth Radiation Pressure (Albedo)- Earth sensor telemetryDeliverablesStudy ReportApplication/Need Date Next EGEP phase starting 2015-2016


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7 - Generic Technologies

7 - 01 - On-board Data Systems

TRP Reference T701-402ED TD TD01Title Prototyping of space protocol(s) for SPIObjectivesThe proposed activity will prototype SPI protocol(s) and physical layers for space applications.DescriptionThe Serial Peripheral Interface Bus or SPI bus is a synchronous serial data link de facto standard, named byMotorola, that operates in full duplex mode. Devices communicate in master/slave mode where the master deviceinitiates the data frame. Multiple slave devices are allowed with individual slave select (chip select) lines.

Based on the result of two running TEC-EDD activities (Modular RTU - GSTP, Standardization of Digital interfaces -TRP) this activity will prototype SPI protocol(s) and physical layers for space applications. A demonstrator will bebuilt and it will be flexible in order to simulate all the conceivable scenarios : SPI as internal backplane bus inside anunit , SPI as serial bus for reprogrammable logic on board (FPGA, NVRAM, ...), SPI as interface with sensors ( e.g.contactless angular sensors, ...), SPI as interface for new ICs to be developed (Wireless Analogue Radio,ADC/DAC, ...). Signal integrity techniques as parity bit, replication or triplication of messages at level of protocol andalso improvement of the physical layer ( e.g. adoption of LVDS differential signalling for intra-unit datacommunication) will be investigated and prototyped.

Test Reports, recommendations ( Technical Note) and material for website will be produced.DeliverablesPrototype

Application/Need DateRemote Terminal Unit-P/L computer-OBC-Instruments units and Sensors for Science,Earth observation, Telecomm, Human Space Flight applications -

TRL 5 by 2016 (SPI is already adopted in some space products)Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-8602, T-7803

Applicable THAG Roadmap Data Systems and On-Board Computers(2011) Consistency with THAG Roadmap No

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7 - 02 - Space System Software

TRP Reference T702-402SW TD TD02Title Verification of Computer-Controlled SystemsObjectivesThe objective is to establish an approach supported by tooling infrastructure for complementary usage of earlyvalidation methods based on models. Specific objectives to be investigated are:- identification of behavioural validation objectives (generic and mission-specific ones) per project phase- identification of the best-suited methods to meet these objectives (e.g., simulation, formal verification, other types ofanalysis)- implementation of tooling infrastructure to ensure consistency and interoperability between the various verificationand simulation tools.DescriptionIn the recent years, an important effort has been put forth by both, ESA and the industry, to evaluate the use ofmodelling techniques for the development of software. At the same time, in practice, little attention is being put to thespecification and analysis of the software behaviour. Modelling is mostly used to capture the software architectureand non-functional attributes but not to capture dynamics and verify functional properties even if there is a strongneed for enforcing early validation of the behaviour of complex computer-controlled systems (e.g., command/controlstrategy, FDIR, initialization sequences, coordination policy between various agents), as confirmed by recent spaceprogrammes. Indeed, such activities allow for early problem-spotting and thus reduce the amount of issues beingdiscovered during the integration and testing phases. Moreover, the risk is reduced when formal techniques areused, since they are based on exhaustive exploration of possible behaviours, whereas testing only targets anon-exhaustive set of user-defined scenarios. Various approaches and tools for early validation based on models doexist (e.g., model-checking, simulation). They have the same general purpose but each is particularly suited forspecific tasks and is based on dedicated models.

The activity shall confirm the applicability and subsequently generalise the use of the functional behaviourspecification, design, verification and implementation of the on-board applications software (in particular the systemmanagement, mission management, FDIR, payload management, power management, thermal control). Severalformal specification/modelling languages and tools shall be taken into consideration (e.g. based on the transitionsystem formalisms) and a large case study shall be developed on a representative on-board software platform(including interaction with AOCS/GNC).

The activity shall address:- Definition of the process including the early system behaviour validation activities (i.e., what is to be done at eachproject phase and what is the relation with the project milestones, how is this process to be tailored depending onproject specificity)- Tool development and integration to ensure consistency and interoperability between the various chosen modelsand tools. For example, if at the beginning of the process the decision is to use SysML, and at a later stage Simulinkis selected for complementary validation purposes, the consistency between these models is to be ensuredautomatically or semi-automatically.DeliverablesPrototype

Application/Need Date Galileo and Bepi-Colombo. The activity is needed to support the next projects also,starting with Proba3, Euclid, etc

Current TRL TRL 3 Target TRL TRL 4 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-7667, T-7666, T-7662, T-7660Applicable THAG Roadmap On-Board Software (2010) Consistency with THAG Roadmap No

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7 - 03 - Spacecraft Power

TRP Reference T703-401EP TD TD03Title Next Generation Solar Cells with an End of Life Efficiency of 30%ObjectivesFurther development of the technology building blocks required for the most promising next generation solar celloptions. Prototype development of at least one cell option reaching 30% EOL efficiency.DescriptionThe state-of-the art GaInP/GaInAs/Ge triple-junction solar cell technology has reached its practical efficiency limits ofaround 30% beginning of life (BOL) and an excellent value of 26.5% end of life (EOL). A significant efficiencyincrease in the order of 3-5% absolute can only be realised by a change of the cell concept. Currently, differentoptions/concepts have been identified which have the potential to arrive at BOL efficiencies clearly beyond 30%which are the UMM (upright metamorphic), IMM (inverted metamorphic), LM (lattice-matched) "conventional"four-junction cell, LM solar cell based on dilute nitride materials and SBT (semiconductor bonding technology)concepts. The differences of the concepts are mainly manufacturing complexity which directly translates into cost,and their maximum efficiency potentials. In other words some of the concepts can be realised easier and cheaperthan others but there is not much scope for an additional efficiency increase in the long term, while others are moreexpensive and require more development effort but have also the potential of an efficiency increase beyond the nexttarget of 33-35%.

In the TRP activity "Next generation Solar Cells with 33% Target Efficiency" (ESA Co. 4000104852) the technologybuilding blocks of all concepts were being developed in a first phase. However an increase to a higher maturity levelin a second phase is needed for the solar cell concept that shows the highest potential to reach the target of arrivingat 33% BOL at the end of the activity. In the mid and long term, though, a solar cell is required with a guaranteedEOL efficiency of 30%. Therefore, the scope of this activity is to increase the maturity level of all the differenttechnology building blocks of all next generation solar cell concepts showing an EOL efficiency potential of 30% andmore. These technology building blocks cover all the full production line of solar cell starting from the sourcematerials like e.g. the substrate, the optimisation of new semiconductor materials in the solar cell epitaxy, the celltechnology, lift-off and layer transfer processes.

Elaborated in more detail the areas that need to be covered are:1. Epitaxy of semiconductor material: For each of the different concepts UMM, IMM, the LM concepts and thesemiconductor bonding concept, new semiconductor materials have to developed which are a different combinationof elements of the 3rd and 5th group of the periodic system. Some of these combinations are known to be difficult tomanufacture in a very high quality and a dedicated development effort is required. Furthermore, some concepts arebased on semiconductor materials which - in contrast to the current solar cell - naturally do not fit together since theirlattice constant are different. Thus, again certain buffer structures have to be developed that account for the thislattice-mismatch of the different materials in the cell structure.2. Handling and technology of ultra-thin solar cells: Substrate removal and layer transfer processes are needed to bedeveloped for at least part of the different concept - the IMM and the semiconductor bonding technology concepts.These building blocks not only need to be developed but also need to be implemented in an industrial frameworkbeing also cost effective. These building blocks might be also applicable to the other concepts especially whenthinking of ultra-thin cells. Additional building blocks in the area of the "technology" are the development ofbroadband anti-reflective coatings. This applies not only to the solar cell but also to the cover glass.

3. Lift-off and substrate reuse: Ideally the substrate removal is performed by a lift-off process which allows forsubsequently reusing the substrate. Thereby, the cost could also be significantly reduced. These building blocks aremost probably required for the IMM and the semiconductor bonding technology concepts in order to be cost effective.But also for the other concepts these building blocks would be advantages when ultra-thin cells are requested toachieve a higher specific power (power/mass).DeliverablesPrototypeApplication/Need Date All spacecraft systems. TRL 5 by 2016.

Current TRL TRL 3 Target TRL TRL 5 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8813Applicable THAG Roadmap Solar Generators & Solar Cells (2009) Consistency with THAG Roadmap Yes

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7 - 04 - Spacecraft Environment & Effects

TRP Reference T704-401EE TD TD04Title Radiation Belt Model Development and ValidationObjectivesSeveral new radiation belt models have been recently released, including the NASA AP-9/AE-9 models. Largedifferences are apparent and before adoption, the models' characteristics and quality needs investigating. In additionvaluable data sets are emerging from European radiation instruments that should be included and compared so thata consistent harmonised model set is established.DescriptionThe current standard radiation models date from the early 1980s and are based on datasets from the 1970s and1960s. Recently the AP-9/AE-9 radiation belt models have been released with significantly different characteristicsand are based on a significantly greater quantity of data. Preliminary investigations of these new models are showingsignificant differences with the ECSS standard models for some standard orbits. During this activity, all new modelswill be subjected to a detailed validation exercise against in-situ datasets including but not limited to ESA and otherEuropean spacecraft and other radiation environment models.

Systems for the use of these new models for both long term radiation effects (e.g. dose, non-ionising dose, solar celldegradation and human effects) and shorter term radiation effects (e.g. internal charging, instrument noise, SingleEvent Effects) will be developed and established in a form compatible with any updating of ECSS-E-ST-10-04C.DeliverablesSoftwareApplication/Need Date All missions support from Radiation Effects. Software Release by 2016.

Current TRL Prototype Target TRL Software Release Duration (Months) 18S/W Clause N/A Ref: to ESTER T-8960, T-8777, T-18, T-8481, T-8547, T-9062

Applicable THAG Roadmap Radiation Environments & Monitoring,Effects Tools & Testing (2009) Consistency with THAG Roadmap No

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7 - 05 - Space System Control

TRP Reference T705-401EC TD TD05Title Navigation on a chipObjectivesThe objective is to propose an architecture for a versatile multi-mission navigation camera suiting most of the needswith high level of integration, and breadboard the proposed design.The activity shall identify :- which detector is the most versatile and suited to fulfil the needs- the synergy with Star Tracker designs and the level of possible re-use- a preliminary electronic architecture identifying the core components needs- the needs in terms of configurability, HW/SW architecture (FPGA, CPU, memories, buses)DescriptionESA is currently developing new image sensors, focussing on the Star Tracker application. Those two detectors,namely HAS3 and Faint Star are both working in the visible range. HAS3 targets high performance, low noise andsnapshot shutter operation, while Faint Star implements logic on-chip for image (rolling shutter) sequencing, readout,background removal and some functions dedicated to Star Trackers such as star centroiding (through photometricbarycentre).

The activity will review for each application the vision-based navigation and image processing algorithms and assessthe feasibility of implementation at HW or SW level, identifying in particular common functions to all applications(which shall target a HW implementation) and custom functions (which could be loaded on a dedicated CPU).

The architecture is meant to be highly configurable in order to deal with different type of missions, from interplanetarynavigation where synergy with Star Trackers is very high to landing cameras.

In order to prepare cameras for future missions requiring navigation, it is proposed to evaluate those detectors andestimate the best architecture to cover very different mission needs.

The activity shall trade-off the best balance between hardware and software processing, using configurableState-of-the-hard FPGAs, CPUs, or an FPGA implementing a CPU core. For highly mission-specific processing, theinvolvement of the future mission OBC CPU shall not be forbidden. As previously mentioned, some functions will beneeded for all applications, and some will be mission specific. The activity shall assess how a generic basic HW/SWimplementation shall be developed, while mission specific "application" could be tailored mission-by-mission, with theaim to reduce or avoid a global revalidation. For this purpose, the possible use and added-value of dual coreprocessors shall be evaluated.

Knowing the missions types will be very different in terms of lighting, field of view requirements and type of targets, itis important to identify how different the different types of optical design will be implemented within a compactstructure. In addition, and knowing the camera is to be an external equipment, the possible added value of splittingthe camera and the electrical processing unit shall be evaluated.DeliverablesBreadboard

Application/Need Date Missions requiring interplanetary Navigation, Rover Nav, Rendezvous or Entry Decent &Landing. TRL 5 by 2018

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7819, T-9174Applicable THAG Roadmap AOCS Sensors and Actuators (2009) Consistency with THAG Roadmap Yes

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7 - 06 - RF Payload Systems


Title Flexible and Autonomous TT&C transponders for multi missionapplications

ObjectivesTo provide a breadboard (proof of concept) of a reconfigurable TT&C transponder which utilises modern digital signalprocessing techniques based on standard ECSS/CCSDS modulation and Spread Spectrum Techniques andmaking use of on-board frequency flexibility and autonomous uplink acquisition for EESS, Near Earth and DeepSpace missions.Description1) BackgroundThe aim of this activity is to develop and consolidate techniques allowing to improve the TT&C transponder flexibilitytogether with the link performances/operations and to reduce the unit procurement cost. A wide range of inputrequirements will be considered, starting from the classical TT&C EESS, Near Earth and Deep Space Missions, butplacing a strong emphasis also on new features addressing:- TLM + PN RNG GMSK modulation (A CCSDS standard is in preparation)- on-board autonomous uplink signal acquisition and recognition of the transmitted up-link data rate- scenarios where there will be Multiple Spacecraft per Aperture (MSPA), such as future missions to Mars and theMoon.

The use of the TLM+ PN RNG GMSK modulation technique allows to downlink simultaneously high rate telemetryand ranging signals in a more efficient mode than those based on suppressed carrier modulation. A study in ESOCis on-going in order to prepare the upgrading of the G/S modem.

Autonomous TTM data rate recognition has been already studied for G/S modem. The implementation of a similarapproach for the on-board receiver will simplify the transponder acquisition and uplink procedure when different TCbit rates are needed which depends on the mission profile.

In the MSPA scenario, different signals are transmitted/received from the same ground station antenna in order tocontrol simultaneously different spacecraft and/or landers at the Moon or Mars. An efficient approach for MSPAmissions requires different solution w.r.t. the classical TT&C architecture which is based on a fixed frequencyscheme and up-link linear phase modulation. To improve the overall system efficiency/performances alternativesolutions can be used. These require transponder implementations which are based on frequency flexibility (considering also the possibility of having a flexible turn-around ratios) or to implement CDMA techniques.

The use of CDMA for missions to Mars has been already discussed in the past as an attractive solution to establishsimultaneous radio links between a single ground antenna and several deep space probes orbiting the planet or onthe planet surface. The spread spectrum techniques allows to access simultaneously different terminals avoiding to acertain extent the typical issues of radio frequency interference when in presence of current CCSDS/ECSS standardsignals.

While intentional RFI to Mars missions have never been experienced, RFI already occurred between ESA and NASAmissions and is expected to increase with the arrival of Indian, Russian and Chinese missions. The use of CDMAscheme can tackle also these issues as different Earth stations can transmit Spread Spectrum signals withoverlapping frequencies using the same approach thus minimizing any effort and constraints in terms of frequencycoordination.

The same approach can be applied also for the downlink (telemetry) by associating a proper spread spectrum codeto each transmitting space borne terminal.

In addition to the classical TC, TLM and RNG, CDMA can be applied also for scientific applications as proposed inthe ESA mission INSPIRE. For instance, a direct space-to-Earth link from a planet allows also for Geodetic SameBeam Interferometry (SBI) techniques, as already proposed for Mars and the Moon. This technique uses a singleEarth antenna to track simultaneously and differentially two or more landers. The uplink signal is received by each ofthe on-board transponders and is relayed back coherently to the same ground station where its phase is measured.The difference between carrier phases cancels almost completely all common noise sources (troposphere,ionosphere, mechanical deformations of the ground antenna, etc.), therefore providing differential distances betweeneach lander pairs with very good accuracies. Such accurate measurements allow refining the rotational model of thecelestial body and their solid tides, adding crucial knowledge for understanding their interior structure. Alltransponders must provide excellent long term stability and have the maximum degree of commonality (to avoiddifferential drifts). They should therefore operate at the same nominal frequency, both in uplink and in downlink (thusminimizing undesired differential delays). For this reason the ideal transponder should support CDMA-like signals(Code Division Multiple Access), which allows full bandwidth sharing for telemetry, telecommands and radio-metricmeasurements simultaneously for all landers of the network without the need of multiple ground antennas.

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It should be noted that this technique is also one of the schemes being proposed as a long-term solution for MultipleSpacecraft Per Aperture (MSPA) support of space missions.

2) Activity PlanThe activity will be organised in two phases; initial study and bread boarding.

a. Initial study:- Study and definition of the algorithm for autonomous uplink acquisition and data rate detection- Study and definition of the digital modulator for TLM+ PN RNG GMSK modulation- Transponder frequency plan and architecture definition including frequency and turn-around ratio flexibility- Study and investigation on the suitable CDMA codes taking into account the acquisition / synchronization aspectsand the interference robustness together with the signal dynamics such as frequency ( Doppler) and amplitudevariations. In this frame the chip rate(s) value(s) and the relationship versus carrier frequency and the data rate(s)shall be investigated. The Link Performances shall be analysed for typical missions to Mars and the Moon in order toassess EIRP, G/T, data rates and coding schemes. In this frame the overall subsystem requirements focusing onon-board units (transponder and antenna) shall be derived as well.- Analysis of the current transponder architecture(s) taking into account the different requirements ofCommunications and Radio Science (Geodetic SBI). The impact of a Dual Mode Transponder (implementing of theCDMA codes but configurable also in Standard Mode using the current ECSS/CCSDS requirements) shall beanalysed lso in terms of complexity, mass, power and operational implications.

b. Bread boarding:- A breadboard of at least of the transponder Digital Signal Processing based on a FPGA device(s) will bedeveloped. In addition to the standard processing, it shall include as a minimum the autonomous uplink acquisitionand data rate detection capability, the TLM+PN RNG GMSK modulation, the frequency flexibility including thedemonstration in order to demonstrate flexible/configurable turn around ratios and the selected spread spectrumcodes for the CDMA applications.- The description of the test set-up for preliminary compatibility tests via RF (S or X-band) with a third partyoperational modem (G/S) shall be defined. It shall be based on standard LAB instruments.- A Roadmap shall be proposed for embedding the above functionality within an operational transponder whilstminimizing the architectural design to existing transponder architectures.DeliverablesBreadboard

Application/Need Date

Future Earth Observation missions (e.g. MTG follow on, Sentinel follow on) and NearEarth and Deep Space missions (Marco-Polo-R, INSPIRE, Moon Landers) would greatlybenefit from a digital unit within a TRSP which can provide in flight frequency flexibilityand/or the implementation of the CDMA techniques.

TRL 5 by 2016.Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-8708, T-7824

Applicable THAG Roadmap TT&C Transponders and Payload DataTransmitters (2012) Consistency with THAG Roadmap Yes

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7 - 07 - Electromagnetics Technology

TRP Reference T707-402EE TD TD07Title Open source cables models for EMI simulationsObjectivesMaking available to the space community SPICE-based cable models to be used for EMI simulations. Implementingstate-of-the-art cables models as SPICE circuits and/or functional blocks, including shields and field-to-cablecoupling, on the basis of the large literature on the subject.DescriptionBack in the '80s and '90s, the development of EMC simulation tools focusing on advanced modelling of cables wasvery active. Advanced modelling meaning distributed-parameters models (as opposed to lumped models), modellingof shields, field-to-cable coupling, etc. Most of those EMC simulation tools focused on cables are/were anyhow notimplemented in SPICE, so cannot/could not be used directly inside a SPICE simulation. A vast majority of those toolsare in addition not available to the space community nowadays, or at a high cost (procurement + training), for anumber of reasons:- The development of some tools (developed under ESA contract) was stopped in the late '90s- Some tools developed by large aerospace companies, or national aerospace agencies, may be availablecommercially but would be expensive in terms of both procurement and training- A majority of tools (if not all) could not/cannot, by design, be interfaced with circuit simulation software involvingnon-linear (active) components such as SPICE

In summary, for EMC simulations of cable harness, the user has to either:- Procure proprietary software and dedicate significant training effort, or- Learn from the broad literature on the subject the methods that can allow him to model cables with one or anotherversion of SPICE, which is feasible but certainly not straightforward.

What would be needed for the space community to get back in touch with EMC-oriented cable simulation is theavailability of a number of sub-SPICE circuits and/or functional blocks easy to import and use in their usual version ofSPICE, either open-source or proprietary. In order to prevent that a commercial use of those models (perfectlyacceptable as such) would result in slightly improved cable models not freely available anymore, a suitable licensewould be needed, compatible with the objective of having model improvements, either ESA-funded, industry-fundedor funded in any other way benefiting to the entire space community.

Activity:1) Literature review of the state-of-the-art of advanced cable modelling via SPICE;2) List of cable models that will be implemented as SPICE circuits and/or functional blocks;3) Development of the SPICE models of interest;4) Test of the developed models on a number of canonical cases suitable to detect modelling errors;5) Creation of import routines for a number of both open-source and proprietary implementations of SPICE;6) Theory manual, User's manual, Tutorials;7) Development of a web-based repository for the developed models and import routines.DeliverablesSoftware, Study ReportApplication/Need Date Industrial competitiveness (All Spacecraft) TRL 5 by 2017

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause Open Source Ref: to ESTER T-50Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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7 - 09 - Mission operation and Ground Data Systems

TRP Reference T709-401GI TD TD09Title Model based operations design, planning and executionObjectivesModelling of the monitoring and control execution is being addressed through future MCS / EGSE data systems.However, model based operation design and planning have yet to be tackled. The aim of this activity is to removedthe void at the conceptualisation level when defining and performing the operations before and during use of theMonitoring and Control Model (MCM). The final goal is a step towards a global and integrated modelling acrossdesign, planning and execution with higher consistency and reduced complexity of operations.DescriptionThe basic idea is to increase more and more the use of conceptual models that describes and represents, in variousways, the systems operated through our monitoring and control systems. The use of models can be beneficial inmultiple ways, such as for simplifications, for more consistencies or for more commonalities across systems.Currently, for example, Spacecraft Monitoring & Control depends very much on the actual spacecraft design and canvary a lot from spacecraft to spacecraft. This results in a high effort for training and re-training the Flight ControlTeam members and makes it difficult to share SPACONS across missions. Applying more abstract models can, tosome extent, be used to harmonise Spacecraft and Ground Systems Monitoring & Control. This approach is highlysupported by mission operators.

Monitoring & Control Models (MCMs) have always been used in operation. However, those have been typicallydefined at very low level of abstraction (e.g. the commanding stack model of the mission control system or thealphanumeric display models (ANDs) for monitoring). Higher level of abstraction and integration of models only startsto be applied in the operation automation systems and are already more used in the M&C systems for the groundstations and related back-end systems.

The MCM of future MCS/EGSE systems will be based on the ECSS-E-ST-70-32C concepts, which include conceptsof system of systems modelisation using various layers of details (but with fractal-like property. i.e. identical at allscales). However, these systems will define only the execution model (i.e. how one interacts with the systems undercontrol. i.e.. The abstracted concepts which are used to execute the operations). How one design and plan theabstract models of the systems is yet to be investigated and developed.

Overall, the questions to be answered by this study are:How can we, in a simple way, allow the operators to- use a coherent and integrated model (of models) of their whole domain of operation?- define the models used by their mission, based or re-using generic models?- model the dynamic and relationships of the systems (including flow of information and change of states) related toM&C in their mission in an integrated way?The study shall at least:a/ Analyse & define suitable M&C Model design methodologies and techniques including planning and taking theEGS-CC Execution MCM as a potential demonstrator.b/ Exercise selected methodologies to selected parts of the systems and sub-systems.c/ Demonstrate, through software prototyping, visual and non-visual definition and interactions with the models,including actual execution up to the real systems.DeliverablesPrototypeApplication/Need Date Future MCS/EGSE, Prototype end of 2015.

Current TRL Algorithm Target TRL Prototype Duration (Months) 15S/W Clause Operational SoftwareRef: to ESTER T-7843Applicable THAG Roadmap Ground Systems Software (2008) Consistency with THAG Roadmap No

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7 - 10 - Flight Dynamics and GNSS

TRP Reference T710-401GN TD TD10Title 3-D ionospheric Total Electron Content (TEC) modellingObjectivesIdentification of a suitable algorithm for 3-D TEC modelling based on near-real time processingDescriptionTaking into account the results from an exploratory study completed in 2010 ("GNSS contribution to next-generationglobal ionospheric modelling"), the present activity aims at identifying a suitable algorithm for generating 3-D TECmaps based on processing data in near-real time (several minutes to a few hours).

This method must overcome the weaknesses identified in the previous activity, by exploring several alternativeapproaches identified before, and further alternatives to be explored in the initial stages of the current activity.

The method must take into account the type of data that will be available for processing in NRT, typicallymulti-system GNSS data from ground and in-orbit receivers and optionally atmospheric sounding data and otherinter-satellite links. The resulting algorithm will bring benefits to a wide variety of missions and applications, notrestricted to GNSS, by providing improved ionosphere corrections in near-real time. Candidate algorithms shall beprototyped to establish their stability and potential accuracy in a realistic scenario.DeliverablesPrototypeApplication/Need Date Multiple usage for Navigation Office POD services in 2016.


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7 - 11 - Space Debris

TRP Reference T711-402GR TD TD11Title System for facilitating collaborative coordinated observationsObjectivesThe goal of the study is to develop a prototype system, i.e. database-controlled mechanisms, to support voluntarycollaborative coordination of observations through distributed sensors with the goal to enable and support thecharacterisation of space debris objects. Such a facilitator will allow loosely connected radar and optical sensor tocollaborate, e.g., for the estimation of attitude motion of larger space debris objects in the frame of ESA studies orIADC activities. The prototype may also serve as a provider of a test-bed for the evaluation of correlation and orbitimprovement algorithms and techniques that are under development.DescriptionThe characterisation of space debris objects, e.g., the determination of area-to-mass ratios, or the observation withdedicated specialised techniques, requires a precise knowledge of the orbit. Such an orbit requires observationspanning over a several orbital revolutions, mostly guaranteed by combining the observations acquired by distributedsensors. In other cases, such as for the determination of the attitude motion, also a coordinated parallel observationwith distributed sensor installations are necessary. These may be also of interest in the context of IADC(Inter-Agency Space Debris Coordination Committee) observation campaigns.

Typically such campaigns aiming at object characterisation are only loosely coordinated, as a participation is purelyvoluntary and on a best-effort basis, without tasking from any entity. A missing tool to facilitate efficient collaborationamong differently skilled observers is a database-controlled mechanism to exchange information between theseloosely connected participants. The following key areas of such a facilitator can be identified: 1) the provision ofaccess to an external independent orbit determination and propagation method to the participants, 2) a passprediction module, available on-demand for the participants, and 3) a data correlation component to support thequality assessment of the acquired observations.

The following steps need to be addressed in the study:1) analyse in depth the requirements from the scientific space debris observer and modelling communities (e.g. inthe IADC) for coordinated, collaborative, observations and other support functions;2) design and implement a prototype database-controlled mechanism supporting survey and follow-up instruments,allowing coordinating distributed collaborative observations of high-interest objects and the support of organising thecollection and dissemination of the data required for various techniques in object characterisation;3) implement links to existing orbit determination and propagation, pass prediction, and data correlation facilities; 4)deploy the prototype in a reference environment, e.g. at ESOC, and demonstrate the capabilities through supportinga voluntary campaign.

Such a voluntary campaign may serve as test-bed for testing correlation techniques under development in otheractivities, and may be exploited for studying and improving related orbit determination approaches (such as throughadmissible regions). A procurement of a limited set of "initial" data shall be foreseen for starting the voluntarycampaign. Both observation techniques, radar and optical, need to be considered. A validation of the capabilities ofthe tool may use past data of a common target.DeliverablesPrototypeApplication/Need Date Support of on-going activities, TRL 5 by 2016

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 12S/W Clause Operational SoftwareRef: to ESTER T-1106, T-1093Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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7 - 12 - Ground Station Systems and Networks

TRP Reference T712-401GS TD TD12Title Ka-Band cryocooled feedObjectivesThe activity is aiming in improving the performance in Ka-Band receive of the DSA2 and DSA3 antennas by morethan 2 dB.DescriptionCurrently both the DSA2 and DSA3 antennas are able to operate in reception over the Ka-Band. The existing feedand LNA systems have been designed separately. The feed system is operated at room temperature while the LNAis operated at 12 K. Ka-Band propagation is strongly affected by weather conditions thus it would be extremelybeneficial improving the present G/T by 2 dB. This will only be possible by an integrated design of the feed and thecryocooled receiver . Improving the Ka band G/T will allow a reduction of the spacecraft transmit power for the samelink performance or/and will provide link budget margin to increase data return by at least 40% (by maximizing thedownlink data rate).

This will be achieved by reducing the loss of the feed system and trying to cryo-cool as much as possible the feedsystem (Including polarizer and autotrack feed network). By doing this an improvement of 1.2dB is expected.Additionally the Ka-Band cryo-LNAs currently installed do not represent the state of the art. By using new generationof InAs (Indium Arsenide) cryocooled LNAs (developed in another TRP activity) another improvement of at least0.8dB is expected.

All future missions operating in Ka-Band (32 GHz) and K band (26 GHz) will benefit from this improvements.DeliverablesPrototypeApplication/Need Date All missions using Ka and K band. TRL 5 by 2016.


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7 - 13 - Automation, Telepresence & Robotics


TitlehArmonised System Study on Interfaces and Standardisation of fuelTransfer (ASSIST)

ObjectivesStudy and preliminary design of standard interfaces for grasping and refuelling spacecraft (SATCOM and non) to becarried out by both Large primes. The intention is to arrive to an industrial standard. Following the preliminary,design, the standard refuelling interfaces shall be bread boarded and validated. Validation includes analysis throughdynamic simulation and grasping tests in representative ground environment.DescriptionIn 2010 the cross-directorate Exploration Scenarios Working Group carried out a survey of space technology thatcould be used across different application domains, including the Space Exploration (robotic or not) one. Besidesother important technologies, Robotic docking and refuelling were identified. In the exploration application domain,Robotic docking and refuelling technologies are essential if space elements, launched by separate means, need tobe assembled and refuelled in space. Furthermore when RDV and refuelling technologies are developed andvalidated for a suitable orbit (i.e. GEO), these could be made available to commercial GEO communication satellitesservicing.

While there is still not much belief in civilian satellite servicing and refuelling, operators are puzzled by the fact thatthe technology is being readied in the military space sector. There is definitely the prospect that satcom satelliteservicing may become reality within a decade.

In the process of acquiring new spacecraft, which when commissioned will last over 15 years, operators areconsidering the opportunity to future-proof their new assets. Refuelling provision on a satcom spacecraft are possiblythe cheapest and less problematic of all servicing provisions. Hence these constitute an affordable way to protectassets acquired now for a changing future in which satellite servicing may have become mainstream. To have anychance to be used in a future, these refuelling provisions need to be standardised across the industry.

Therefore with this activity ESA intends, together with the European satellite producers (which manufacturecommercial but also institutional satellites) to conceive and promote standard refuelling provisions that can beinstalled in present European satellite platforms.

The proposed activity intends to:1) Perform a conceptual design of the provisions2) Architectural definition,3) Breadboard design4) Functional testing5) And possibly filing to a standardisation body of the above concept to achieve the status of recognised standard.DeliverablesBreadboard

Application/Need Date Exploration after 2020. TRL 5 by 2018. (Telecom after 2016 (a standard interface couldalready be inserted in the platform options by that time))

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-1Applicable THAG Roadmap Automation & Robotics (2012) Consistency with THAG Roadmap Yes

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7 - 15 - Mechanisms & Tribology

TRP Reference T715-401MS TD TD15

Title Development of advanced lubricants for space mechanisms based onIonic Liquids

ObjectivesDevelopment of new ionic liquids with improved performance with respect currently available space lubricants. Thenew ionic liquids will be characterized against space engineering applicationsDescriptionIonic liquids have many desirable properties from the point of view of the space engineering applications such asnegligible volatility, high temperature stability (some ionic liquids are stable until 320°C, while PFPE has the massloss of 13.2% at 320°C), desired viscosity index, low melting point, perfect anti-wear properties, decrease frictionfactor [under pressure of 10-3 Pa, for ionic liquids can be of 0.070 while for PFPE is 0.142], are capable oftransferring large loads and ability of good mixing with other organic compounds. Therefore, Ionic liquids arepotentially capable of replacing liquid lubricants used till now in the space engineering that have some disadvantages(e.g. PFPE may decompose under boundary friction conditions).DeliverablesStudy Report, Lubricant SamplesApplication/Need Date For any generic fluid lubricated mechanisms application. TRL 5 by 2017

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8588, T-7846Applicable THAG Roadmap Solar Array Drive Mechanisms (2008) Consistency with THAG Roadmap Yes

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7 - 16 - Optics

TRP Reference T716-404MM TD TD16Title Active Optics correction chain for large monolithic mirrorsObjectivesThe objective is to develop and test an active optics correction chain for large monolithic mirrors comprising the threekey technological building blocks of active optics: Corrective element (e.g. deformable mirror), wave front sensor andcorrection algorithm. The activity will include following steps:(1) To trade-off and develop strategies and concepts for wave front sensing inside an optical space instrument,identifying an efficient and space-compatible technology for use in future active optics correction chains for largemonolithic mirrors. This step will include the manufacturing and testing of a demonstrator of a wave front sensor.(2) To identify and develop a novel corrective technology for use in future active optics correction chains for largemirrors, including the manufacturing and testing of a demonstrator.(3) To develop algorithms in order to efficiently pilot the above selected novel deformable corrective components.(4) To perform the design of the whole active optics correction chain and to manufacture a breadboard in order tovalidate by testing the complete approach.DescriptionThe increasing need for higher image resolution for space applications is driving the entrance aperture of opticalsystems, requiring the use of large primary mirrors either monolithic or deployable (cf Future Technology AdvisoryPanel (FTAP) First cycle report lists large monolithic mirrors as one of the 7 enabling technologies). This trend callsfor the study of crucial technologies aimed at improving the imaging performance beyond what is currentlyachievable by classical optical systems.

Active Optics is a very promising example of such enabling technologies, based on the combination of three keytechnological components:1. Corrective element (e.g. deformable mirror),2. Wave front sensor (in order to characterize the aberrated wave front),3. Algorithms determining the required correction to be applied, based on the wave front sensing results.

Active optics allows correcting for in-flight effects which impact the optical quality of space instruments. In particular,in the case of large mirrors, extreme light weighting will need to be applied, leading to increased effects due to e.g.thermo-elastic deformations, radiation effects on optical materials, gravity release, etc. that need to be identified andcorrected.

Active optics can also decrease the stringent requirements on the manufacturing quality for large optical components( e.g. compensating residual surface figuring errors), reduce structural and thermal design complexity (e.g. relaxingrequirements on structure stability) and reduce the outage period of missions caused e.g. by Sun baffle intrusions oreclipses altering the thermal conditions within the instrument. As such, active optics constitutes a key building blockfor the improvement of high-resolution imaging capabilities of future missions (namely for optical systems involvinglarge mirrors, either monolithic or segmented) and constitutes a crucial generic technology able to find applications inall classes of optical instruments.

In terms of technological developments, concepts and demonstrators for corrective components (e.g. deformablemirrors) for space applications have already been initiated (cf GSTP activity in SD7-TD16 "Demonstrator for activeWFE-correction of an imaging telescope"; to be started in 2014 , CNES/LAM collaboration on deformable mirrors,etc.). However, the other essential parts of the complete Active Optics correction chain have so far remainedrelatively untouched in the context of European space applications, namely: the technology performing the sensing ofthe aberrated wave front, and the strategy to pilot the corrective elements based on the wave front sensing results.Furthermore, novel concepts for deformable components are in need in order to anticipate a potential nextgeneration of active optics specifically tailored for compensation of large optics deformations, creating an alternativeto the current approach on deformable components (e.g. by considering a deformable primary mirror).

The proposed activity aims at 5 strategic and technical goals, encompassing the whole active optics correction chainin the context of large mirrors:1. Trading off strategies and concepts for wave front sensing inside an optical space instrument (through a dedicatedwave front sensor chain or through the PSF information from the instrument sensor itself by use of e.g. phasediversity), enabling wave front correction by active optics for typical large mirror deformations in space environment.2. Exploring novel deformable element concepts in order to identify and develop the next generation of correctiveelements for large monolithic mirrors, aiming at performances superior to currently developed deformablecomponents while achieving increased suitability for space use (higher reliability, lower mass and powerconsumption, etc.).

And, based on the completion of the 2 previous goals:3. Identification and development of algorithms to efficiently pilot the deformable component identified in goal nr 2.4. Development of a wave front sensor chain based on the previous 3 goals, including the manufacturing of ademonstrator.

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5. Validating the whole Active Optics chain through a breadboard combining all selected technologies.

Once completed, this activity would lead to follow-up GSTP activities for each of the key technologies identified. Assuch, this activity constitutes a blueprint as well as an important exploration step for future innovative AO correctionchains for large mirrors. Note that technologies explored and developed by this activity will potentially be applicableas well for phasing and correction of large segmented/deployable mirrors (see also FTAP First cycle reporthighlighting deployable structures as enabling technologies).

The activity will encompass the following tasks, split into 2 phases:Phase 1a)- Identification of wave front sensing technologies suitable for space systems using large mirrors,- Trade-off and selection of the most promising technology (taking into account specific deformation of large mirrorsin space, mass, power, volume, environmental constraints, development and manufacturability, reliability, cost).b) (run in parallel to 1a)- Identification of novel technologies for corrective elements suitable for space systems with large mirrors,- Trade-off and selection of the most promising technology (taking into account specific deformation of large mirrorsin space, mass, power, volume, environmental constraints, development and manufacturability, reliability, cost) andcomparison with current developments.c)- Conceptual design of an AO correction chain for large mirrors involving the selected technologies of 1a and 1b,including identification and preliminary development of algorithms to efficiently pilot the deformable componentidentified in phase 1b.

Note: should the selected corrective component technology prove not realisable for the available TRP budget orschedule, an alternative could be chosen for Phase 2's active optics chain breadboard in the form of the deformablecomponent used in either the current GSTP "deformable adaptive mirror for space instruments"; or its follow-up"Demonstrator for active WFE-correction of an imaging telescope".

Phase 2:a)- Design and realization of a wave front sensing demonstrator using the technology selected in phase 1a,- Characterization and test,- Roadmap to detailed designb)- Design and realization of a correction component demonstrator using the technology selected in phase 1b,- Characterization and test,- Roadmap to detailed designc) Refined conceptual design of an AO correction chain for large mirrors, including refined development of algorithmsto efficiently pilot the deformable component identified in phase 1b.d) Manufacturing and testing of a breadboard of the complete AO correction chain to validate the design.DeliverablesBreadboard

Application/Need DateGeneric technology potentially applicable to all future imaging missions in Science andEarth Observation aiming at high resolution and/or decreased design complexity. TRL 5by 2017.

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 36S/W Clause N/A Ref: to ESTER T-341, T-8443, T-8640, T-7855, T-8441

Applicable THAG RoadmapTechnologies for Optical PassiveInstruments (Stable & LightweightStructures, Mirrors)

Consistency with THAG Roadmap No

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7 - 17 - Opto-Electronics

TRP Reference T717-401MM TD TD17Title Lattice-matched III-V detector arrays with 2.5um cut-offObjectivesDesign, manufacture and characterise a quaternary III-V, 2D detector array.DescriptionPrevious single pixel measurement results from quaternary III-V semiconductor layers grown on lattice-matchedsubstrates have demonstrated low dark current and high quantum efficiency potential. This activity aims to build onthese results by producing and characterising a breadboard 2D detector array with a 2.5 um cut-off wavelength.

Detectors in the 2.5 um region are typically based on Mercury Cadmium Telluride. While these can offer highperformance they are also resource hungry, requiring significant cooling and expensive. A number of differentmaterials from the III-V semiconductor group are used for detection in the short-wave infrared, most noticeablyInGaAs. However, a major difficulty in growing high-quality epitaxial layers is finding a lattice-matched substrate thatreduces defects during the growth process, which in turn limit performance through increased dark current andhot-spot generation. Hence, InGaAs detectors perform best at 1.6 um where the lattice spacing matches the growthsubstrate, resulting in low defect quantity. As the InGaAs cut-off wavelength is increased, the lattice spacing changesinducing a mis-match between InGaAs and substrate causing growth defects. Some quaternary materials (asopposed to tertiary materials like InGaAs) have recently been investigated since they can be lattice-matched atlonger wavelengths and have shown promising results (Ref...). Successful development would lead to higheroperating temperature (hence lower resource) and potentially cheaper detectors for this ever-important waveband forboth Earth observation and astronomy applications.

2D array development is possible by collaboration between research groups and existing detector manufacturers.DeliverablesBreadboardApplication/Need Date Earth Observation, Science. TRL 5 by 2019

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-367, T-7886

Applicable THAG RoadmapTechnologies for Optical RemotePassive Instrumentation (Detectors)2011

Consistency with THAG Roadmap Yes

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7 - 18 - Aerothermodynamics

TRP Reference T718-401MP TD TD18Title Prediction of acoustic loads on space structuresObjectivesThis activity aims at studying the feasibility of predicting acoustic loads on the structure of a space vehicle originatingfrom the supersonic exhaust plume of a thruster rocket engine, including prediction of the aero-elastic response ofthe structure. The following objectives are foreseen: (1) Develop and assess the modelling capability to predict the jetacoustic loads on launch vehicles by computing the generation of sound by the supersonic jet of a launcher engineand the propagation of sound to the launcher body. (2) Develop and assess the modelling capability to predict theinfluence of the jet acoustic loads on the dynamic aeroelastic analysis of structural components.DescriptionFor the design and optimization of a space vehicle structure, acoustic loads prediction methods based on empiricalmodels have been used in the past. These methods rely on experimental data and scaling approaches. Acousticloads prediction methods based on multi-disciplinary first-principle formulations of the unsteady aerodynamics,acoustics, and launch vehicle structural response hold the promise of smaller uncertainty on the design loads,smaller design margins on the structure, and finally improved competitiveness of future launch vehicles.Multi-disciplinary approaches allow a complete and correct superposition of the different loads (e.g. engine vibrationand ambient excitation ...). While a concept and application of such acoustic loads prediction methods has beenformulated, a proof of concept for a more realistic launch vehicle configuration is still to be given. Details of thepropulsive exhaust plume need to be captured, acoustic sources need to identified, and the accurate propagation ofacoustic waves is needed in order to determine the acoustic loads on selected structural parts. The computationaltask of accurately capturing the relevant physics is enormous, and requires besides a large computer also a coherentmulti-physics algorithm optimized for capturing wave phenomena with the lowest possible numerical dissipation anddispersion. The present proposal focuses on a multi-disciplinary approach which combines Computational FluidDynamics (CFD), Computational Aero-Acoustics (CAA) and Computational Structural Mechanics (CSM). Thesedisciplines are capable of capturing the sources of acoustic waves originating from exhaust plumes, direct wavepropagation over a large distance to characterise the acoustic loads on the payload fairing of the launch vehicle, anddetermine the dynamic structural response of this part of a launch vehicle, respectively.

An evolutionary approach will be followed to develop the capability to determine the acoustic loads on a launchvehicle due to the supersonic jet, consisting of the following three main steps:

Step 1:(a) steady RANS computation of mean flow around the launch vehicle,(b) LES computation of isolated supersonic jet to determine the acoustic source,(c) LEE/Euler computation of sound propagation around the launch vehicle, using the results of step a and b asinput.Step 2:(d) hybrid RANS-LES computation of time-dependent flow around the launch vehicle to determine the mean flow andthe acoustic source, taking the possible effect of the mean flow on the acoustic source into account,(e) LEE-Euler computation of sound propagation around the launch vehicle using the results of step a as input.Step 3:(f) hybrid RANS-LES computation of time-dependent flow and sound propagation around the launch vehicle, takingthe possible effect of the mean flow and of acoustic reflections on the acoustic source into account.(g) an aeroelastic analysis approach will be set up that is generic, i.e., it can be applied to any structural component(or even the entire launcher). Within this proposal, the approach will be applied to a particular component that will beselected together with ESA; in particular, the payload fairing is considered a suitable candidate.

To assess the influence of acoustic loads, due to the sound generated by the supersonic jet, on the aeroelasticanalysis, the acoustic loads will be modelled as external excitations of the aeroelastic system. In other words, theacoustic loads are assumed to be independent of the motion of the structures, as it does not seem likely that themotion of the structures will have a significant impact on the sound generation by the jet. On the other hand, theaerodynamic loads, due to the local flow around the structure, will depend significantly on the motion of thestructures. Thus, a two-way coupling of the structure with the aerodynamic loads is used and only a one-waycoupling with the acoustic loads.DeliverablesStudy ReportApplication/Need Date All launchers and spacecraft with chemical propulsion. TRL 5 by 2018

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7901Applicable THAG Roadmap Aerothermodynamic Tools (2012) Consistency with THAG Roadmap Yes

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7 - 19 - Propulsion


Title Model and experimental validation of spacecraft-thruster interactions(erosion) for electric propulsion thrusters plumes

ObjectivesThis study has the following goals:• To identify and master the key physical processes governing electron cooling and electric field build-up downstreamthe thruster in the far field and around the satellite surfaces with their own potentials.• To propose models of electron cooling that, on the one hand, are physically consistent and, on the other hand, aresimple enough to be implemented in SPIS without incrementing much the computational requirements. The mostsuitable case would be a law involving electron temperature and electric potential only.• To implement these electron models in SPIS• To experimentally validate on-ground those models using a typical EP thruster used on Telecom platform.• With the data obtained and the models implemented, to perform system applications including erosion analyses.DescriptionUse of electric propulsion (EP) is becoming a key issue for the European industry in order to remain competitive inthe short to long term on the space satellites market. One of the main constraints for accommodation of electricthrusters and therefore for architecture choice is the erosion induced by the plasma plumes on satellite surfaces,some of which are very sensitive like solar array interconnectors or antenna layers. Also, eroded parts contaminateother satellite surfaces and equipment. Some of the new architectures under study are exotic compared to theplatforms already used and appear to be extremely challenging from the point of view of erosion. Erosion this needsto be assessed as accurately as possible because it will have direct impact on the choice of future architectures andconsequently on competitiveness of European satellites.

Currently, plume induced erosion on satellites is estimated through simulations with plume models which arenecessarily simplified due to industrial and computation constraints. For a given surface material and ion type, thelevel of erosion caused by one ion depends on the ion energy and incident angle. Those two, when reaching thesurface are heavily influenced by the electric field path the ion has followed form the thruster to the surface:simulations shall thus reproduce the electric field map as realistically as possible.

The contribution of the experts in solar generators, materials, thermal systems and payload specialists will bewelcome during the preparation of the activity. This activity has a multi discipline aspect that could be integrated inthe creation of a mini-project on the subject.

It is proposed to develop and have access to plasma models usable in day-to-day industrial processes which areable to reproduce with sufficient accuracy the electric field build-up and potential decay downstream the thruster andaround the satellite. An experimental validation of those models is mandatory to gain confidence of their adequate

Tasks:• To perform a state-of-the art literature research on erosion data available.• To identify and master the key physical processes governing electron cooling and electric field build-up downstreamthe thruster in the far field and around the satellite surfaces with their own potentials.• To propose models of electron cooling that, on the one hand, are physically consistent and, on the other hand, aresimple enough to be implemented in SPIS without incrementing much the computational requirements. The mostsuitable case would be a law involving electron temperature and electric potential only.• To experimentally validate in a vacuum facility those models using a typical EP thruster used on Telecom platform.Plasma plume parameters (ion and electrons characteristics) in the plume far field shall be measured.• With the data obtained and the models implemented in SPIS, to perform system applications including erosionanalyses.• To validate erosion of solar cells, thermal blankets, optic instruments etc. that can be affected by the use of EP in asatelliteDeliverablesStudy ReportApplication/Need Date Telecommunication and science satellites using electric propulsion. TRL 5 by 2017


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7 - 20 - Structures & Pyrotechnics

TRP Reference T720-401MS TD TD20

Title Advanced damage tolerance assessment methodology for compositestructures

ObjectivesTo extend the work performed in the TRP activity Delamination Assessment Tool (DELAT) towards impact damageassessment, and to further define and validate criteria to identify the most damage sensitive composite and bondedhardware (to be subjected to more detailed damage tolerance activities).DescriptionThis activity will build upon the foundation made in the current TRP activity Delamination Assessment Tool (DELAT).In the DELAT activity a damage tolerance methodology for structures made of fibre reinforced plastic material wasoutlined, but the activity focused mainly on residual strength prediction for one type of defect: delamination. Only afirst step towards assessing the effects of impact damage was made.

To complement the DELAT activity, the activity shall address:- Assessment methods for impact damage (both creation and effect of the damage) to potentially sensitive compositehardware.- Predictive methods are needed for both the extent and nature of damage created by impact, and the resultingresidual strength and life performance. This can be a very complex task, still the subject of much research. The goalwill be to select and verify pragmatic existing methods that will help to save significant testing effort, and will bespecifically helpful to distinguish sensitive and ;insensitive hardware.- Tailoring methods for existing standardized impact test methods (defined for e.g. typical aircraft applications) to thewide variety of possible spacecraft structural details are to be investigated as relevant for the activity.- Assessment of recommendations that will be made by the DELAT team.- Definition and validation of criteria to identify damage sensitive composite and bonded hardware, that may warrantspecific mitigation measures like: damage tolerance verification (by analysis or test), inspection, proof testing,protection against impact, etc.- Demonstrations are to be made for a wide range of representative composite/bonded structural elements, bothdamage sensitive and damage insensitive

The aim is to provide recommendations for updating the ECSS-E-ST-32-01 Fracture Control standard, by e.g.extending the low risk category with the aim to allow reduced damage tolerance verification effort where justifiedDeliverablesFinal report, guidelines documentApplication/Need Date Composite/bonded structures in spacecraft and launchers. TRL 5 by 2018

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8843Applicable THAG Roadmap Composite Materials (2005) Consistency with THAG Roadmap No

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7 - 21 - Thermal

TRP Reference T721-401MT TD TD21Title Mini Hybrid Capillary Pumped LoopObjectivesTo design, manufacture and test a Mini Hybrid Capillary Pump Loop, which is composed of more than one minicapillary evaporators and a loop heat pipe (LHP) which is used as the capillary pump. The application of such adevice would be for direct cooling of components within electronic boxes. Compact and thin evaporators are locatednear high dissipating components inside the enclosure, the LHP is located outside the electronic box and thecondenser is directly bolted to the panel heat pipe network. This provides an efficient method of extracting theinternal waste heat.DescriptionThere is a fundamental issue in the electronic box design that the power density is increasing. In addition, systemintegrators prefers the dry thermal interface since it allows the unit to be dismountable. However, the thermalinterface has a conductive limit where the only method of increasing the heat transfer would be to increase thesurface area as well as the contact pressure and reducing the interface filler thickness. These thermal interfacerequirements impact the foot print of the electronic, the bolting method, the interface flatness as well as thecomponent operating temperature. Therefore, there is the need of extracting the waste heat from units withoutincreasing the volume or mass of the units. There are on-going activities using Loop Heat Pipes (LHP) to transportwaste heat from electronic components within an electronic boxes to the unit's base plate. However, this applicationis limited by the foot print of the electronic unit. Furthermore, the LHP has the disadvantage of having the liquidreservoir attached to the evaporator, which needs to be a certain size depending on the length of the LHP's fluidlines. This creates accommodation issues and limitation due the available volume within the electronic box. Inaddition, the LHP requires to be in close proximity of the dissipating component and it is limited when multipledissipating components need to be cooled.

The mini hybrid capillary pump loop with multiple thin capillary evaporators would cool multiple dissipatingcomponents on a Printed Circuit Board (PCB). The LHP, located outside of the electronic box, would act as a pumpproviding the fluid circulation and the fluid inventory for the evaporators. The fluid reservoir or compensationchamber size can freely vary based on the unit's cooling requirements The condenser, with the advantage of beingthin and low mass, could cover a larger surface area onto the panel heat pipe network. This new technology wouldallow to develop higher power density electronic boxes without the restrictions or limitations of the thermal contactconductance while maintaining the components within the allowable temperature limits and keeping the overall masslow.

The activity aims to design and develop an engineering model of such a scheme.DeliverablesEngineering Model

Application/Need Date Future Integrated Electronic Unit Heat Management Systems for Electrical Units TRL 5by 2017.


Applicable THAG Roadmap Two-Phase Heat Transport Systems(2009) Consistency with THAG Roadmap No

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7 - 24 - Materials & Processes


Title Assessment of materials and processes design margins for spacecraftand launchers

ObjectivesThe objective of the activity is to perform a comprehensive review of the design margins which are applied byindustry at materials and processes level during all phases of spacecraft and launcher development. This will beachieved by a review of both the high level ESA standards/requirements and the industrial standards and appliedpractices for materials and processes.DescriptionVarious design margins are applied to materials and processes during the life cycle of a space project, in order toensure an accepted system level safety and reliability. Many diverse examples of such margins could be given, suchas the margin applied to the thickness of radiation shielding material on an electronics box, the margin applied to thethickness or strength of a structural material or the margin applied to the end of life properties of a thermal controlmaterial. In general, the application of these margins tends to increase the complexity of a system design, whichdrives up cost, mass, development time etc. Because margins on materials and processes are generally applied atone of the lowest levels in the spacecraft design and production cycle, there is the risk that additional margins areadded by the system level designers, leading to over-engineered or cost inefficient solutions. Many aspects ofstandard spacecraft design are now rather mature with regards to the materials and processes used, and thestatus-quo is often accepted with regards to the margins applied. However, some commercial companies now startto push the boundaries on the margins back and make successful use of commercial materials and parts which havelittle or no space heritage. Therefore, this would be the time to adopt a more systematic approach to revisit thematerials and processes margins which are applied across ESA space projects and to see what lessons can belearnt from the many previously successful space missions in order to introduce potential cost savings in the future.

The review will focus on identifying the maturity level of the various margins and the levels of uncertainty involved,including areas where the margins could be affected by use of out of date or inaccurate data for materials properties.The overall aim is to identify areas where a refinement or more accurate definition of the margins could have asignificant impact on the spacecraft development programme (e.g. saving on mass, cost, development time etc..)without compromising the required safety and reliability.DeliverablesStudy ReportApplication/Need Date All Launchers and Spacecraft.


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7 - 25 - Quality, Dependability and Safety

TRP Reference T725-402QQ TD TD25Title Reliability of Mechanical Systems and PartsObjectivesThe objective of the study is to define the most suitable methods to analyse and assess the reliability ofnon-electronic systems and parts and to provide methods and procedures for reliability verification by testing. Theoutput of the study (standard/handbook, database and tool) should be applicable to any space mission.DescriptionThe models and assumptions used for the reliability assessment of electronic systems and parts (e.g. constantfailure rates throughout the useful life of the system/part) have a limited validity when applied to the mechanicaldomain. In the non-electronic domain the concepts of mechanical reliability, mechanical failure mechanisms (e.g.fatigue, fracture, wear out, corrosion) and reliability prediction cannot be disjoint from design margins andstress-strength technique, process (throughout the life cycle) performance, architecture/configuration (physicalinterfaces) and physics of failure. Further, the non-electronic systems and parts are often customised and employedunder conditions that can be extremely different both from an operational (e.g. duty cycle and operating mode) andenvironmental (i.e. operational environment) points of view.

The study intends to standardise the approach and to provide a common set of data for the performance of reliabilityanalyses and verification of non-electronic systems and parts for ESA programmes. This shall be achieved by meansof the development of a standard/handbook, a database and associated tool of failure rates/failure mechanisms ofnon-electronic parts.DeliverablesStudy ReportApplication/Need Date All missions. TRL 5 by 2017


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7 - 26 - Spacecraft Avionic System

TRP Reference T708-403SW TD TD08Title CCSDS MO Services, CCSDS SOIS, and SAVOIR for future spacecraftObjectivesThe recently released draft set of CCSDS Mission Operation (in short MO) service specifications advocate newconcepts for development of more integrated software applications for space missions based on definition of servicesthat would be implemented across the ground and the space segment. One of the focuses of the CCSDS MOservice specifications is to separate the semantics of a service, the what;, from the implementation andcommunication technology adopted for its implementation, the how, on a certain deployment configuration, henceallowing possible migration of service deployments from space to the ground or vice versa. The CCSDS MOSpecifications have a strong support from the Ground segment engineering side, mainly in anticipation of thebenefits commonly associated with Service Oriented Architectures, such as increased reuse (hence increasedReturn on Investment), increased interoperability, increase flexibility for adapting faster to the changes of evolvingbusiness (mission) requirements.

On the other hand, the European SAVOIR initiative has proposed an on-board software reference architecture forfuture spacecraft, which is based on the same principles of the Service Oriented Architecture and utilises theconcepts associated with a component model (similar to the OMG CORBA Component Model) in order to addressissues related to deployment configurations.

For current space missions, the development lifecycle of the software systems used for mission operations on theground and the software deployed on-board the spacecraft are more or less detached. The integration between thetwo segments is achieved through establishing well defined interfaces, the so called space-to-ground ICD for eachmission. For almost all current ESA missions, this interface specification is a customization of the well-establishedECSS Packet Utilisation Standard (PUS).

In the frame of the SAVOIR initiative the lower-level communication within the satellite is based on the recent suite ofCCSDS SOIS standards. The SOIS services on-board can be seen in analogy to the ISO communication layers, orto the standardized low-level POSIX operating system services on the ground. They abstract the direct hardwareinterfaces. All three initiatives, SAVOIR, CCSDS MO and CCSDS SOIS have aligned and common objectives, whichare to reduce the effort required for development of software systems for new space missions and the related cost oftheir operation, through

- providing reference architectures for on-board and on the ground mission software systems- standardizing the interfaces of involved components- abstracting from implementation and communication technologies adopted for a particular deployment configuration- increasing interoperability and facilitating software reuse- facilitating an open market for component vendors to provide interoperable but competitive implementations ofstandardized software and hardware components

While the interdependencies of these three initiatives have been contemplated by a dedicated standardisationharmonisation WG and fairly understood at theoretical level, the practical implications of each set of specification onthe others must yet be studied in more detail. In order to make it to achieve a truly integrated and future proof set ofsoftware systems on the ground and in space, it is important to demonstrate that the SAVOIR architecture is alsocompatible with the suite of CCSDS MO Services and that it will be beneficial and possible to smoothly migrate froma PUS-based configuration to a MO-based one. To this end, different approaches for MO adaptation by the SAVOIRcan be considered, depending on the envisaged level of integration between the two sets of specifications. Theimpact of each of these approaches is currently not clear and deserves a thorough analysis, including a detailedassessment of the architectural decisions decided in OSRA on the deployment of the MO Services on-board or onthe ground.

This has been identified as a pre-requisite for any review or comment of the CCSDS MO standards by the flightsoftware community

The objectives of this study can be defined accordingly:

- Devise the envisaged layered architecture of the integrated future mission data systems on the ground and inspace, based on CCSDS MO, SOIS and SAVOIR;- Analyse the different approaches toward adoption of MO within the SAVOIR architecture and elaborate in detail onpractical impact and implications of each approach- Analyse thoroughly and specify the required steps for transition from the current PUS architecture to an MO basedarchitecture (both from a technical and industrial policy perspective)Description

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The activity will include:• Analysis of the CCSDS MO Framework and the existing and envisaged MO service specifications• Identification of the impact of adoption of the CCSDS MO concept on the current SAVOIR architecture. Thisassessment shall include the analysis of the communication aspects both on-board and between the space and theground as well as the implications related to the exposure of selected on-board application components as MOservices, which would facilitate a higher level of integration between ground and space applications.• Elaboration of the updates that would be needed to OSRA and the feedback to the CCSDS MO in order to furtheralign the development of the SAVOIR and CCSDS MO specifications.• Identification of a transition policy to move from PUS based architecture to an MO based architecture

Deliverables:• Impact analysis of MO in SAVOIR (TN)• Proposed changes to CCSDS MO Specifications and OSRA (TN)• PUS to MO transition strategy (TN)• Prototype of modified OSRA with implementation of selected MO services.DeliverablesPrototype

Application/Need Date Strategic. Impact next generation flight and ground software and Standardisation. Shouldbe available in 2015

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-7661, T-7660, T-7840Applicable THAG Roadmap Avionics Embedded Systems (2010) Consistency with THAG Roadmap Yes

TRP Reference T702-403SW TD TD02Title File Management Services interface standardisationObjectivesThe mass memories are generalized in most of the spacecraft's and now used by both platform and payload. Thedefinition of a new standard interface for managing the data storage unit shall benefit in term of flexibility throughequipment interchangeability. The emergence of the new PUS file management service and File Based Operationsconcept is a good opportunity to standardize the mass memory interfaces .

The activities aims at defining a standard set of services to be supported by Mass Memory Devices to match therequirements from platform and payload applications as well as operations (CFDP, PUS, File Bases Operations,etc.).DescriptionSAVOIR is an initiative to federate the space avionics community and to work together in order to improve the waythat the European Space community builds avionics subsystems. In particular, it is aimed at getting equipmentinterchangeability. In particular, the group provides a set of standard avionics external and internal interfaces, thedefinition of building blocks composing the architecture and the functional specification of selected building blocks.

One of the building block of the On-Board Reference Architecture is the Solid State Mass Memory. Several instancesof this building block can coexist in a same spacecraft:- For storing the science data,- For storing the platform applications and housekeeping telemetry - Safeguard mass memory for storing critical data as the current status of the spacecraft to be used in case ofreconfiguration.

All these instantiations of a same building block provides different interfaces and services so their integration in thereference architecture requires a large amount of efforts to implement the upper level of services related to datamanagement as Packet Utilization Services (PUS) defined in ECSS-E-70-41A (large data transfer service, on-boardstorage and retrieval service and in the next version of the standard, the file management service), CCSDS FileDelivery Protocol (CFDP) and to future needs emerging from the File Based Operations concept.

All these services are independent from the data storage units but require a set of common services to access andmanage the data. CFDP assumes a minimum set of capabilities from the virtual filestore as: create file, delete file,rename file, append file, replace file, create directory, remove directory, list the content of a directory. The incomingPUS file management service should require additional services to manage file attributes for protection purpose andfile search.

The proposed study aims at specifying a standard interface for mass memory building blocks that ease theirintegration into the on-board reference architecture.

- The existing applications and services accessing a mass memory storage device shall be identified and

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investigated in order to identify generic functional data stream (for spacecraft management, telemetry, payload datastorage, etc.) and required services. This study shall take into account new services that are not yet implemented insystems (File Based Operations concept) as well as the services required by file management libraries (e.g. RTEMSfile system, ERTFS, VxWorks dosFs and HRFS, ext2/3/4, etc.).- The existing mass memory units shall be identified and investigated in order to identify their characteristics andconstraints (type of memory, maximum capacity, maximum throughput, number of cycles, number and type ofinterfaces, smallest allocable unit, etc.) . In addition, this study shall take into account the next generation of massmemory units providing new features (e.g. RAID 1/5 support, compression, etc.) as well as on-going activities in thedomain of mass memories (TRP study "OBC Mass Memories ")- Taking into consideration the needs of the mass memory users and the characteristics of mass memory units, astandard interface shall be proposed. This work shall take into account the characteristics of recent mass memoryunits that may provide processing capabilities.

The tasks related to this activity are then:1. Establishment of requirements concerning the services in charge to manage files on-board compatible withexisting services (CFDP, PUS Services) and application needs. Identification of representative Use Cases based onthese services.2. Investigation on the characteristics and services provided by existing mass memory units and identification of thefuture trends.3. Specification of a standard interface supporting the needs of applications.4. Development of a functional prototype supporting the new interface. This prototype shall support the interfacepreviously defined and data storage capability.5. Integration with existing services: CFDP, platform application (e.g. logging, OBCP management) and payloadapplications (e.g. science data storage).6. Analysis of the results, assessment and proposition for improvements.7. Produce a SAVOIR interface and functional specification documentDeliverablesPrototypeApplication/Need Date Spacecraft Mass Memories (All Spacecraft). TRL 5 by 2017

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 15S/W Clause N/A Ref: to ESTER T-7671, T-7661Applicable THAG Roadmap Avionics Embedded Systems (2010) Consistency with THAG Roadmap Yes

TRP Reference T701-403ED TD TD01

Title OBC Mass Memories (Solid State Mass Memory board/module integratedin OBC)

ObjectivesA new Solid State Mass Memory board/module fully integrated in the OBC shall be developed taking boost from theseveral R&D activities already concluded or on-going as OBC memory organization, NAND Flash technology forspace, and services as CFDP and Flash system file. Redundancy architecture, high reliability figure, re-usability andeasy upgradeability shall be considered as driving requirements.DescriptionMass memories in space systems are evolving from simple stream tape-like recorders to complex intelligent(sub)systems capable of autonomous operations. This evolution is driven mainly by requirements coming fromcomplex multi-payload missions, where more than the brute performance requirement (speed, capacity), functionalrequirement play a role. OBC-integrated memories are more capability-driven than performance driven. Use ofstandard interfaces for I/O and control (SpW, CAN) is foreseen, so effectively tapping the highest I/O bandwidth at200 Mbps. Capacities are strictly dependent on the type of memory used, for NAND FLASH a single board can hostfrom 500 MByte to 1 T Byte of usable memory (after redundancy). While modular OBCs are already a reality (takee.g. new TAS SMU-V2 or Astrium OSCAR), and while I/O standardization is taking advantage of mixed ASICintegration possibility (like RUAG-s M2), there is still no real across-mission solution for standardized solutions forOBC mass memory modules (leading to what was once called a CDMU). Furthermore, we will soon face anenvironment where DRAM Memory Modules are going to be replaced with NVRAM (FLASH or FRAM) MemoryModules to overcome the SDRAM obsolescence and to increase the memory density while keeping powerconsumption in an acceptable range.

Multi-payload scientific missions (with or without a dedicated PDHU) are the target for this type of development. Theenhanced level of reliability achieved with multiple layer of redundancy (at physical, word, and file system level) ismade with in mind harsh environments (e.g. Jovian orbiters) and to cope with the unknown reliability challenges ofvery long duration planetary missions.DeliverablesEngineering Model

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Application/Need Date JUICE and future spacecraft. TRL 5 by 2017.

Current TRL TRL 3 Target TRL TRL 6 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-9061, T-8480, T-7797

Applicable THAG Roadmap Data Systems and On-Board Computers(2011) Consistency with THAG Roadmap Yes

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7 - 27 - End to End System Design Processes

TRP Reference T708-404SW TD TD08

Title Augmented Reality for AIT, AIV and Operations

ObjectivesThe objective of this study is to bring Virtual Reality and Augmented Reality e.g. the Virtual Spacecraft in form of aDMU (digital mock-up, updated to represent the "as built" status) to later phases of the life-cycle, supporting SystemIntegration and Verification activities, Operations of satellite and crewed missions, and Operator support for futureexploration missionsDescriptionVirtual Reality already plays an important role in ESA projects (e.g. ATV docking) and tools are available (e.g. GEVGod's Eye View). This technology can be improved using the state-of-the-art by looking at different ways to interactwith a virtual world (instead of fixed displays, use head mounted displays, hand held devices). But also by improvingthe level of reality by adding "live" elements (such as telemetry) or digitized model of real objects (e.g. spacecraft).Based on industrial use of relevant technologies (e.g. for Gaia project, ISS) and operational experience in the frameof manned space missions (through the WEAR SDTO, including inputs provided by ESA crew members, Crewinstructors and relevant EAC personnel), Augmented Reality technology is recognised as a useful and valuabletechnology to support AIT/AIV activities as well as operations. In the automotive sector haptic devices are alsoincreasingly used to support design and workshop activities.

In order to bring this technology to our present working environment, mainly three problems need to be addressed ina reliable:1. Robust Registration: Augmented Reality application requires the accurate calculation of the viewer position inorder to overlay the real-world image with virtual graphics which effectively enhance the real world. Accurate andreliable registration of the viewer position in a challenging environment (e.g. assembly / test floor, or the dynamicenvironment of the ISS) is a complex problem that requires further development of this technology.2. Efficient Implementation: One of the keystones of Augmented Reality Applications is wearability. An AR solution isnot useful if the user cannot move freely. This implies the use of either mobile platforms, which in general provideslower computational capabilities than desktop computers, or distributed solutions. This is effectively a trade-offanalysis between system autonomy and computational power, also depending on the possible environment of theapplication.3. Provision of force feed-back requires improvements in the haptic actuators technology to render them morecompact and "wearable", and to ensure their integration with the virtual models used in the application area.

The foreseen applications include Monitoring, Diagnostics, Training and Public Relations. - Monitoring: understand better what the spacecraft is doing, visualise areas of interest either at system, subsystem,unit or parameter level and how dynamically moves (attitude, position, trajectory, etc.). Situational awareness can belargely improved using augmented reality applications- Diagnostics: in case of anomalies use virtual/augmented reality to quickly understand or provide guidelines to whatcaused the anomaly.- Training: the use of virtual reality during the training and simulation campaign can help engineers in betterunderstand overall status and react quicker to simulated anomalies and train new engineers join the flight controlteam. For astronauts training augmented reality has proven to be very usefull.- Public Relations: to reach out and appeal to a wider audience on what is space engineering/operations is about, forexample virtual reality models connected to real data are powerfull PR toolsDeliverablesStudy report and demonstratorApplication/Need Date System AIT/AIV. TRL 5 by 2017


Applicable THAG Roadmap System Modelling and Simulation Tools(2012) Consistency with THAG Roadmap Yes

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TRP Reference T708-405SW TD TD08Title New modeling methods for Simulation, Verification and ValidationObjectives1. Establish a list of Modelling Methods of different domains for (direct) incorporation into the System SimulationFacilities.This includes Modelling Methods in support of databases, System views modelling (UML/SysML) and multi-physicsmodelling.

2. Based on the above list, do an alignment of different Modelling Methods (e.g. mapping of semantics).This includes a mapping between the models for capturing the database entries and the behavioural models fromdifferent nature.

3. Identify the possible extensions to the use-cases of the ECSS TM 10/21 System Simulation Facilities, based onintegration possibilities of domain specific models.Please note that this is not to replace any domain specific engineering but to rather extend the capabilities by thepossibility of running models in context.

4. Identify the problem areas in doing this kind of multi-disciplinary integration of models, both in terms ofintegration/scheduling issues but also in terms of possible performance issues.DescriptionSimulation Modelling Methods are used for doing a mapping or transformation of any real world system into a modelthat can be used in a computational environment.

A methods means a type of language or "terms and conditions" for creating this model. Examples of ModellingMethods are:- System Dynamics Modelling,- Discrete Event Modelling,- Agent Based Modelling,- Finite State Machine Modelling,- Fact Based Modelling,- UML/SysML Modelling, etc...

The ECSS ETM 10/21 describes the modelling and simulation facilities required to support the analysis, design andverification activities on system level.

In doing so a number of concrete and real-life Project use-cases are mapped to specific System Simulation Facilitiesfor which architectures and common elements are identified and described. An example of such a System SimulationFacility would be the commonly known Software Validation Facility. However also during the earlier phases, designand verification support is given by using System Concept Simulators and Functional Engineering Simulators.

Currently different aspects/components of these System Simulation Facilities are supported by different modellingmethods:1) The use of a Model-based approach (MBSE) is supported by the use of UML/SysML modelling methods leading toa consistent set of system views.2) The capturing of data (for example for storage in System/Simulation DataBases) is supported by standards likethe ECSS-E-TM-10-23 and the usage of Fact Based Modelling techniques.3) The behavioural aspects of the System Simulation Facility and in particular the Simulator part of them (e.g. the6dof dynamics model or startracker behavioural model) are supported by modelling methods and tools likeMathworks product family. Reuse of these type of Simulation Models between facilities or between projects aresupported by the Simulation Model Portability standard and reference architectures.

Nowadays the Modellica modelling language is seen as the third generation of system dynamics modelling allowingfor multi-engineering capabilities. Tools like Dymola and Ecosimpro (non-causal system modelling) build opon thismodelling method.

Whereas in the past the System Simulation Facilities development were carried out by dedicated teams based onrequirements specifications, currently there is a tendency to incorporate and integrate more and more the domainspecific models. However, based on different domain specific needs and heritage different engineering disciplinesbring along models but also modelling methods and languages. This all comes together at the system level and moreimportantly challenges the integration/instantiation of these models (in terms of hybrid simulation frameworks butalso performance optimisation issues).DeliverablesStudy ReportApplication/Need Date Innovation in support of System Simulation Facilities


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Applicable THAG Roadmap System Modelling and Simulation Tools(2012) Consistency with THAG Roadmap Yes

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7 - 28 - Electronic Components


Title Investigation into applicable Inspection & Analysis Techniques for FlipChip Devices

ObjectivesIdentification of new suitable methods to inspect flip chipped devices and Identification of suitable methods to carryout Destructive Parts Analysis on Flip Chip devices to determine the quality and suitability of flip chipped devices forflight applicationsDescriptionTechnology is currently being developed to use devices mounted in a flip chip configuration under ECI3. Whilst thereare on-going activities that address the construction and mounting of these devices, there is no current applicableinspection standard that addresses all the PA requirements for this type of construction. Given the small numbers,and often very high cost of the components used, it is considered, like in many space flight production applications,unlikely that statistical process control methods will be satisfactory, and that more typical verification methods will beapplied. Specific areas of concern are the solder joints, created during the mounting of the die to the package, andthe inspection of the active side of the die, after the flip chip mounting process. Also concerning is the use of a heatspreader which is incorporated to dissipate the thermal energy from the devices. Whilst it is understood that real timeX-Ray methods can be used for the inspection of solder joints, the small dimensions will drive the requirement forhigh performing systems and careful examination of the imaged joints. Due to the large number of joints, and theinevitably limited field of view (due to the zoom required), this will be a very slow and laborious process, that may bedifficult to accommodate in a production process.

Inspection of the active side of the die does, however, raise some significant challenges. Current PA requirementsare that the active areas of die are inspected for defects, cleanliness and damage Immediately prior to permanentcovering, which prevents any subsequent inspection. In the case of flip chip, it is anticipated that, the die will besoldered, cleaned (to remove fluxes), and then under filled, after the final possible inspection of the active areas ofthe die. Given that there is a workable solution, albeit time consuming, to the inspection of the solder joints, this studywill primarily consider the issues of inspection of the die surface etc. post flip chip.

Currently, deployed methods of destructive analysis are designed and have been evolved over many years toaddress the analysis methods required to verify the quality of a product constructed with hermetic chip and wiretechnologies, that would include mounting of discrete components with solders or adhesives. Methods such as dieshear and pull testing are not applicable, and traditional visual inspection methods are of limited value as it is notpossible to see the active areas of the die surface or solder joints etc.

The work carried out shall include investigation of current and new methods of inspection and analysis, and examinetheir applicability, limitations and value when applied to flip chip devices. Demonstrations of the methods ortechniques should be included with the final deliverable being a draft DPA procedure or flow that can be developedinto an issued document for use by agencies, institutions and companies tasked with DPA of these components.

The study shall also consider current and emerging technologies that may be used to inspect the active areas of thedie & validate the cleaning (post soldering) and performance of the resin under fill processes.DeliverablesTechnical Report & DemonstratorsApplication/Need Date Flip Chip for Telecom ASIC using 65nm. TRL 5 by 2016

Current TRL TRL 1 Target TRL TRL 3 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-9053, T-9054, T-9106Applicable THAG Roadmap Microelectronics (2011) Consistency with THAG Roadmap No

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Title Prototyping and Characterisation of Radiation Hardened SiC MOSStructures.

ObjectivesThe aim of the activity will be to perform the prototyping and characterisation of radiation hardened (SEE & TID) SiCgate oxide materials through use of an elementary MOS capacitor structure for the optimisation of the gate oxideprocess parameters. The output of this activity shall help to identify the MOS structure required for the development,evaluation and qualification of radiation hardened high-voltage SiC power-MOSFETs in future activities.DescriptionThe study will be focused on the prototyping of SiC MOS capacitor structures with the main goal to characterise theoverall quality and stability of the gate oxide to SiC interface to gate stress as well as the radiation performances ofSiC gate oxide in terms of SEE and TID testing. This study will be preparatory and supporting the planneddevelopments of discrete radiation-hardened SiC power-MOSFETs for use in the space environment and spaceapplications.

The main features of SiC base material are known (high energy gap, high electric field breakdown in combinationwith reasonably high electron mobility and high thermal conductivity) leading to the following expected and in somecases already proven capabilities for power applications, namely: low on-state voltage, low recovery charge, fastturn-on and turn-off, high blocking voltage, higher reliable operating junction temperature & high power density.

On the other hand, the stability and radiation performances of SiC gate oxides are not widely known because SiCMOSFET devices are still at an R&D level or in a pre-industrialisation phase for industrial applications. As a result,this study will have the goal of characterising SiC gate oxides as it is the key performance parameter in the futuredevelopment of radiation-hardened SiC MOSFET devices. This proposed activity is considered a key stepping stonetoward the development of radiation-hard high-voltage (600 Volt and greater) SiC power MOSFETs.

This TRP activity can be divided into the following 4 tasks, namely:

Task1: Prototyping a SiC MOS capacitor structure with different gate oxide processes, different stacks and differentgate oxide layer thicknesses. The prototype devices will be assembled in hermetic packages in order to allow thehigh temperature and radiation testing which shall be conducted under Task 2.

Task2: I-V and C-V characterisation before and after gate stress over temperature will be performed (the reliabilitytest methodology needs to be agreed: e.g. time dependent dielectric breakdown ). The structure will then besubmitted to constructional analysis to investigate the oxide/substrate interface quality after voltage/temperaturestress

Task3: The prototype devices will be characterised under TID testing, with different biasing, dose rate and annealingtemperature conditions.

Task4: SEGR performances vs. irradiation parameters (such as ion species, stopping power, range, flow) will beexamined again using the above test vehicles, prototyped and packaged in Task 1. In all cases an evaluation basedon Titus model will be performed in order to assess its possible validity in the case of SiC substrates.DeliverablesPrototype

Application/Need DateCharacterisation of the SiC MOS structure, will lead directly to the future development ofradiation-hardened SiC MOSFET devices. As such all types of space applications areconsidered, including Earth Observation, Science, Telecoms & Navigation. TRL 5 by2016


Applicable THAG Roadmap Power Management and Distribution(2008) Consistency with THAG Roadmap Yes

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TRP Reference T723-408QE TD TD23Title Radiation Testing of EEE parts in support of ESA R&D activitiesObjectivesTo provide radiation test data on parts developed on ESA contracts or evaluated in the frame of ESA TRPsDescriptionThere is a need of providing test data on parts developed on ESA contracts. For example, several standard ASICshave been developed (CCSDS ASIC, Space wire Router ASIC, LEON3 DARE2 ASIC), but no radiation data isavailable. Radiation assessment is either based on ASIC technology evaluation (CCSDS) or by similarity (Spacewire). However, Single Event Effect (SEE) sensitivity is often design dependent and an assessment based on asimple test vehicle or by similarity is not sufficient. Also radiation testing is part of the evaluation of part consideredfor a space application (LVDS, CAN transceiver,..). In this study we envisage to perform the radiation tests (TotalIonizing Dose (TID), Total Non-Ionizing Dose (TNID), SEE) of standard ASICs and parts evaluated for spaceapplication. This will be a frame contract where Call Of Orders (COO) will be issued as needed.

A similar frame contract has allowed the radiation evaluation of Micro-semi ProASIC3 FPGA, several SRAMs that willbe flown ALPHASAT TDP8 radiation experiment, and testing of a photodiode to support SMOS flight anomaliesinvestigations. And a Single Event Effect test on Space wire RTC has been initiated.DeliverablesTest reportsApplication/Need Date Call for Orders Contract. Developed ESA ASIC technology test subjects. TRL N/A.

Current TRL Not Specified Target TRL Not Specified Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7930, T-9108


TRP Reference T723-406QE TD TD23

Title Utilisation of a Heavy and Light Ion Facility at UCL for ComponentRadiation Studies

ObjectivesTo utilise, improve and maintain the capabilities of the UCL Heavy Ion (HI) and Light Ion (LI) irradiation test facility forthe purpose of characterising SEE effects in EEE components for flight on ESA missions and missions developed byEuropean industry.DescriptionThis activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA andEuropean space missions. Up to 360 hours per year of beam time is available free of charge on a priority basis forESA. Additionally, a minimum of 500 hours per year is available for ESA sub-contractors, research institutes andother interested users at preferential hourly rates. The agency provides the facility with a detailed work programme ofthe test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency).

A third of the 360 free hours (i.e. 120 hours)of beam as well as of the 500 hours at preferred rates will be used indirect support of EEE Components testing developed by the Component Technology Section TEC-QTCDeliverablesOther: annual report, beam time

Application/Need Date Continuation of Frame Contract with UCL Heavy Ion (HI) and Light Ion (LI) irradiationtest facility. TRL N/A.

Current TRL Not Specified Target TRL Not Specified Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7637


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Title Utilisation of the High Energy Heavy Ion Test Facility at JYFL forComponent Radiation Studies

ObjectivesTo utilise, improve and maintain the capabilities of the RADEF High Energy Heavy Ion (HI) irradiation test facility forthe purpose of characterising SEE effects in EEE components for flight on ESA missions and missions developed byEuropean industry.DescriptionThis activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA andEuropean space missions. Up to 240 hours per year of beam time is available free of charge on a priority basis forESA. Additionally a minimum of 500 hours per year is available for ESA sub-contractors, research institutes andother interested users at preferential hourly rates. The agency provides the facility with a detailed work programme ofA third of the 240 free hours (i.e. 80 hours)of beam as well as of the 500 hours at preferred rates will be used indirect support of EEE Components testing developed by the Component Technology Section TEC-QTCthe testcampaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency).DeliverablesAnnual report

Application/Need Date Continuation of Frame Contract with RADEF High Energy Heavy Ion (HI) irradiation testfacility. TRL N/A.




Title Utilisation of the Proton Irradiation Facility at PSI for ComponentRadiation Studies

ObjectivesTo utilise, improve and maintain the capabilities of the PSI High Energy Proton irradiation test facility for the purposeof characterising Single Event Effects (SEE) and Displacement Damage (DD) effects in EEE components for flighton ESA missions and missions developed by European industry.DescriptionThis activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA andEuropean space missions. Up to 240 hours per year of beam time is available free of charge on a priority basis forESA. Additionally, a minimum of 500 hours per year is available for ESA sub-contractors, research institutes andother interested users at preferential hourly rates. The agency provides the facility with a detailed work programme ofthe test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency).

A third of the 240 free hours (i.e. 80 hours)of beam as well as of the 500 hours at preferred rates will be used indirect support of EEE Components testing developed by the Component Technology Section TEC-QTCDeliverablesAnnual report

Application/Need Date Continuation of Frame Contract with PSI High Energy Proton irradiation test facility. TRLN/A.



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7 - 32 - Cleanspace

TRP Reference T724-403QT TD TD24Title Citric Acid as a Green Replacement for Steels PassivationObjectivesThe objective of the proposed study is to evaluate the suitability of the environmental friendly citric acid process forreplacing the health hazardous nitric acid in passivating stainless steels used for manufacturing spacecraft andground support structures on applications requiring corrosion resistance. The selected process applied to widelyused alloys shall demonstrate with significant test evidence to meet the performance and reliability requirementsnecessary for ESA missions.DescriptionStainless steels are major manufacturing materials used in spacecraft and ground support structures on applicationsrequiring corrosion resistance including storage and handling of liquids and waste, propulsions systems, componentswithin thermal protection systems and fasteners such as high-reliability and high strength bolts. Passivation ofstainless steel has two purposes: 1) it is necessary to remove “free iron” contamination left on the surface frommachining and fabrication that can result in corrosion damage and 2) it forms an oxide film that protects the stainlesssteel from corrosion.

Nitric acid is currently the most widely used passivating solution widely adopted in industrial applications. However,nitric acid has multiple environmental, safety, and process disadvantages. Nitrogen oxides (NOx) are consideredgreenhouse gases and are volatile organic compounds (VOCs) that contribute to smog. NOx increase nitrogenconcentration (leading to oxygen depletion) in bodies of water and poses worker safety issues. Nitric acid canremove beneficial heavy metals (nickel, chromium, etc.) from surface of the substrate and requires significanthandling and disposal costs of hazardous materials.

Citric acid passivation has been recently proposed as a green replacement for stainless steels passivation processesin different industrial sectors, including fasteners, medical devices, semi-conductors, automotive and aerospace.Citric acid passivation offers many advantages w. r. t. environmental impacts: it is biodegradable, it is not considereda hazardous waste, it does not create toxic fumes during the passivation process and it does not remove beneficialheavy metals from the surface. Citric acid provides passivation of stainless steel while providing worker andenvironmental safety, versatility, ease of use, less maintenance and lower costs.

The study proposed here refers to an activity of common interest between ESA and NASA in the effort of developingenvironmental friendlier materials, processes and coating systems able to provide the same performances. Thesynergy between the two Agencies is key to optimise costs of the whole test campaign guaranteeing sharing ofactivities and test results and avoiding duplication of efforts.

The present activity, covering the ESA contribution, is split into two phases:Phase 1:• The objective of the first phase is to screen spacecraft as well as launchers systems in order to identify commonlyused stainless steel alloys as well as applications where large materials quantities are required.• Perform for the selected materials candidates Life Cycle Assessment (LCA) in order to assess the health andsafety related impacts of the nitric acid passivation processes currently applied.• Select a citric acid passivation process and the relevant applicable standard to be applied to the selected materialscandidate and perform a Life Cycle Assessment for the selected process.Phase 2:• Submit the selected material candidates passivated using both nitric as well as citric acid routes to a series oflaboratory testing including:• Compare all results with the two materials systems as well as the performed LCA’s.DeliverablesStudy ReportApplication/Need Date TRL5 by 2017.


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TRP Reference T713-402MM TD TD13Title Elastic tether design and dynamic testingObjectivesThe activity proposes to design an appropriately light and strong tether that is also extremely elastic, and to test itsstrength and elastic properties in a laboratory.DescriptionActive Debris Removal is an important branch of the Clean Space initiative within ESA. A number of technologies(net, harpoon, mini-spacecraft with robotic arms) have been proposed and are currently investigated for capturingspace debris that all rely on subsequently "towing" the debris using a tether. Common for all of these is the need fordesigning the tether.

Thorough simulations during internal studies within the agency have shown that a very elastic tether will significantlyhelp during the deorbit burn in a number of ways. Firstly the elasticity will decrease controller bandwidthrequirements, it will also reduce the impulse transferred to the spacecraft when the deorbit engines are first switchedon, and finally they can be shown to significantly improve the ability to recover to a controlled situation at the end of aburn - something that is critical for a multi-burn deorbit strategy.

Commercial shock cords are commonly used to more heavy ships. They achieve both strength and elasticity (up to50% extension in length) by combining a strong and inelastic weave outside an elastic core. The activity proposes tolook at options of using different weaves or combination of materials to design a tether that acts like a commercialshock cord. The main challenge is envisaged to be able to do so while still keeping weight and volume low. Theactivity will comprise:* Investigation and trade-off of different material and weave combinations.* Design and manufacture of one or two sample tethers.* Extensive testing of the sample tether(s) for dynamic and static properties.DeliverablesBreadboardApplication/Need Date TRL5>2016

Current TRL TRL 3 Target TRL TRL 4 Duration (Months) 12S/W Clause N/A Ref: to ESTER T-9003Applicable THAG Roadmap Automation & Robotics (2012) Consistency with THAG Roadmap No

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TRP Reference T719-405MP TD TD19Title HAN-based monopropellant assessmentObjectivesTo manufacture and test a thruster breadboard and verify performance of HAN-based propellants in a European testfacilityDescriptionSince the 1960s the large majority of space monopropellant systems have used Hydrazine as a fuel. The toxicitylevel of this propellant has demanded special measures to reduce safety risks (e.g. SCAPE suits, limited testing withpropellants, extra mechanical barriers, restriction on air transport, etc.). These measures can have significant impactto cost and schedule for ground operations. The propulsion industry has been investigating lower toxicity (green)propellant options to address this problem. In 2011, Europe's Registration Evaluation Authorisation and Restriction ofChemicals (REACH) added hydrazine to their candidate list of substances of very high concern (SVHC), due to itstoxicity. With this step, there is an associated risk that REACH will make hydrazine obsolescent (restrict or prohibit itsuse) in the near to mid-term. This risk places further and more immediate emphasis on the need for greenmonopropellant alternatives.

Four green monopropellants have been identified as key hydrazine replacements. These are Hydrogen Peroxide,LMP-103s, NOFBX (Nitrous Oxide Fuel Blend X), FLP-106 and HAN-based (Hydroxyl Ammonium Nitrate)propellants. For the first two, ESA has already initiated activities for either propellant characterisation or hardwaredevelopment. However, no activities are currently on-going with HAN-based propellants within ESA. HAN-basedpropellant technologies have been developed within the US for over 20 years. The lower toxicity, performancepotentially exceeding the Hydrazine and ADN-based propellant state of art and preliminary indications ofcompatibility with typical standard space propulsion materials makes it an attractive hydrazine replacementcandidate.

The activity shall include:- Purchase Thruster breadboard parts- Assembly of the Thruster breadboard- Purchase of HAN-based propellant- Hot fire test campaign in a European validated facility- Test results evaluationDeliverablesBreadboardApplication/Need Date Alternate green monopropellant thruster. TRL 5 by 2017.


Applicable THAG Roadmap Chemical Propulsion - Green Propulsion(2012) Consistency with THAG Roadmap Yes

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TRP Reference T704-403EE TD TD04Title Space debris from spacecraft degradation productsObjectivesThe main objective of this activity is the assessment of the amount and characteristics of space debris objectsresulting from spacecraft surface degradation. The cause, numbers and size distribution of these products are ofmain interest. The results will serve as input for future space debris population models and for the selection ofmaterials in the context of debris mitigation measures.DescriptionOptical and radar observations from the ground as well as analysis of retrieved hardware have shown an abundanceof space debris objects that seem to result from the degradation of outer spacecraft surfaces. Recent surveys of theGEO and GTO region have found many objects smaller than about 40 cm which have a high area to mass ratio,indicating that they must consist of relatively thin material, like foils. Retrieved hardware has shown that Multi LayerInsulation (MLI)foils as well as S/C paint can severely degrade in space and create large numbers of space debrispieces. Quantitative information on the amount and size distribution of these debris objects is lacking. However, assuch degradation products could form a considerable part of the debris population more information is required forreliable space debris flux models, impact risk assessments and for the selection of materials to mitigate theseeffects.

The main aims of the present study are the understanding of the production mechanism and of the amount and thesize distribution of surface degradation products under space exposure. The main emphasis is on the study of paintsand MLIs typically used on S/C. Experimental degradation studies, including tests under realistic or acceleratedspace environment conditions (Ionising radiation, X-Ray/UV, Thermal cycling) shall be performed. Thecharacteristics of degradation products shall be quantitatively evaluated and presented in a form suitable for use infuture updates of space debris population models.DeliverablesStudy ReportApplication/Need Date Relevant for all spacecraft.

Current TRL Not Specified Target TRL Not Specified Duration (Months) 18S/W Clause N/A Ref: to ESTER T-1105Applicable THAG Roadmap N/A Consistency with THAG Roadmap

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TRP Reference T719-403MP TD TD19Title Thrust Vector Control Systems for solid propellant de-orbit motorsObjectivesTo design and test a Thrust Vector Control System (TVC) usable on solid propellant rocket motors for the purposeof de-orbiting spacecraft, taking IPOL and CleanSpace issues into account.Note: the activity is also applicable to the space transportation domain for the de-orbiting of upper stages.DescriptionIn the scope of the Clean Space initiative (branch 3) and "IPOL"; ESAADMINIPOL(2008)2, Solid Propellant RocketMotors meet the need for controlled de-orbiting of satellites to a pre-designated uninhabited area of the planet, suchas e.g. south Pacific Ocean. Several studies (e.g. CDF) have been performed regarding this topic and have showedthat these systems are an interesting solution to spacecraft that require controlled de-orbit, spacecraft or objects thatdo not have propulsion systems and to de-orbiting cryogenic launcher upper stages (which have to perform thede-orbit manoeuvre in a very suboptimal orbital phase due to the boil-off of the propellant).Large experience exists in Europe already with solid propellants. Since SRM for de-orbiting have relatively highthrust for the de-orbiting application, but low thrust when compared to many other applications and since it isdesirable not to rely on a further RCT sub-system for attitude control, a Thrust Vector Control (TVC) system isneeded to control the spacecraft attitude during the de-orbit burn.Solid propulsion TVC systems adopting actuators to move large flexible-joint nozzles do exist already for many yearsin the launchers domain. In this respect, both Ariane and Vega SRM stages adopt TVC systems based on suchtechnology (pressure driven actuator for Ariane 5 boosters, electric motors for Vega P80, Z23 and Z9). However,these systems can by no means serve as baseline for TVC systems on small SRM for de-orbiting applications. Muchsmaller systems, mainly military systems such as missiles, with vanes in the exhaust stream, seem to be comparableto systems required for de-orbiting spacecraft. This specific application however, calls for long duration burn times(several minutes e.g. 4 minutes) and use of the system after many years in space (10+ years), introducing significantchallenges with respect to the currently existing systems, and in particular completely different issues (e.g.: thrustdeflection capabilities, impact on SRM performance, structural and thermal aspects, power, etc.) w.r.t. the abovementioned TVC subsystem adopted on European launchers. This all reduces the TRL of the overall system andtherefore calls for practical tests to boost up TRL.

This activity involves:Consolidation of the requirements and product functional specification (in close consultation with ESTEC)Design of the breadboard TVC system (including an assessment of the best location of the vanes; at nozzle exit,near the throat or somewhere in between.)Testing of the breadboard TVC system e.g. in static conditions and/or cold flow and testing of specific components inhot flowDesign iterations (up to PDR level), reporting and recommendations (development and qualification plan) forfollowing phases.

The complete development roadmap will include as well (note this is outside the scope of this activity):A)Testing and performance assessment of aluminium free solid propellant (already approved)B) Design and testing of Thrust Vector Control mechanismC)Design and 3 x Engineering Model motor manufacturing and testing to bring the motor up to CDR level.D)Design iteration and 3 x Qualification Model motor manufacturing and testing to achieve qualification level.E)Flight Model motor manufacturing and Implementation in spacecraftDeliverablesPrototypeApplication/Need Date TRL5>2015


Applicable THAG Roadmap Chemical Propulsion - Components(2012) Consistency with THAG Roadmap Yes

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7 - 33 - Space & Energy

TRP Reference T722-401MM TD TD22Title Space and Energy, EnRumObjectivesstudy, elaborate and test mathematical models of energy balances in complex systems. Assess commercialsoftwares for energy fluxes analysis.DescriptionBe it space or terrestrial complex system, the availability of analysis tools to support architecture trade-off, designelaboration and design optimisation is a necessary condition to successful system development. Whichever thespace system, the main constraints are alike and imply specific attention to mass and energy optimisation. This canonly be performed based on an accurate evaluation of the system energy balance (thermal, electrical, radiative,chemical, biological) along the mission. Therefore, it is proposed to study the mathematical models, generic tocomplex system using those various type of energy, which will allow a system energy balance. In addition,commercially available software to compute the energy models will be trade-off. Finally, the selected software andenergy models will be tested within an existing simulation platform. For the sake of this activity, it is proposed to usea closed regenerative life support system as a study case. Indeed, such systems use several of the energy typesconsidered.DeliverablesOther: Mathematical model+software+documentation

Application/Need Date 2018 (Surface Landers and associated payloads), Pressurized environment(Micro-satellitte)

Current TRL TRL 1 Target TRL TRL 2 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-7835Applicable THAG Roadmap N/A Consistency with THAG Roadmap No

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7 - 35 - Technologies Enabling Breakthroughs in Science

TRP Reference T716-403MM TD TD16Title Trade-off for very large space telescope mirrorsObjectivesThe objective is to perform an assessment of feasibility and a trade-off at system-level for the implementation oflarge space telescopes in future science (and Earth observation) payloads fully in line with the needs identified by theFuture Technology Advisory Panel (FTAP). Roadmaps shall be established for the various options for thedevelopment and manufacturing of such telescopes.DescriptionCurrently the size limit for primary mirrors of large telescopes is - due to the available Ariane-5 fairing - typically at3.5m (Herschel). Future science (and most likely also Earth observation missions) will call for larger telescope sizesdue to more demanding requirements on the light collecting efficiency and angular resolution.

Different possibilities can be envisaged to increase the size of telescopes:- maximising the diameter of the rotational symmetric monolithic primary mirror compatible with the dimension ofexisting launcher fairings;- maximising the size of an off-axis elliptical primary mirror by making best use of existing launcher fairing volumesmost likely in combination with an unfoldable secondary mirror;- introducing a segmented primary mirror that will be deployed in-orbit (like JWST) using existing fairings;- increasing the size of a monolithic mirror assuming a larger fairing (diameter 8m) will be available.

System designs shall be established and traded-off to identify the most suitable design and approach for extendingthe light collection efficiency and angular resolution of large space telescopes. The trade-off shall include designcomplexity, risk and manufacturing cost. The primary mirror of the selected concept shall be designed in line withtypical environmental and performance requirements. Roadmaps for all feasible implementation solutions shall beestablished for the development of such a mirror. Development needs for manufacturing and testing facilities shall beidentified.

Two parallel studies shall be implemented. Multi-disciplinary cooperation with support from mechanisms andstructure experts will be implemented for the execution of this activity.DeliverablesStudy Report

Application/Need Date Future space science missions (e.g. exoplanet imaging) and high-resolution Earthobservation missions. TRL 5 by 2017.

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-341, T-8443, T-8640, T-7855

Applicable THAG RoadmapTechnologies for Optical PassiveInstruments (Stable & LightweightStructures, Mirrors)

Consistency with THAG Roadmap No

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7 - 36 - Collaborative Activities


Title Compact impedance matched connectors for SpaceWire LinksDevelopment and ESCC Evaluation

ObjectivesThe objective is firstly to develop an impedance matched compact connector which shall be possible to use as analternative connector for SpaceWire cable assemblies and which ensure optimal EM shield termination as well asallowing higher transfer rates than what is possible with the current micro-d connector. The second objective of thisactivity is to carry out the ESCC evaluation of the connector(s) for SpaceWire cable assemblies, including connectorsplugs and receptacles.DescriptionAt present there are few European compact connector solutions that offer performances required for high speedoperation of SpaceWire as well as meeting the stringent environmental requirements in space applications. TheECSS E-ST-50-12C defines the connectors and cables to be used on a SpaceWire Cable Assembly, respectively asper ESCC 3401/071 and ESCC 3902/003. Recent developments done under the frame of an ESA TRP activity leadto the definition of new cable variants allowing noticeable mass saving, compared to the current variant of the ESCC3902/003. Connectors as per ESCC 3401/071 are not ESCC qualified and do not offer optimal inner shieldtermination compatible with SpaceWire cables (ground continuity, EMC, etc.) and could limit the use of the newSpaceWire cable variants.

Therefore, the development of connectors optimized for new SpaceWire cable variants and compliant with spaceconstraints, is required. The developments shall also take into account constraints of ultra-high speed links in orderto investigate the use of this new connectors in such links. Solutions based on twinax contacts and/or quadraxcontacts may be considered as very interesting candidates.

During this activity, new design and/or new technologies of connectors will be developed. Then the ESCC evaluationof selected new design or technology will be carried out at cable assembly level including receptacles.DeliverablesEngineering ModelApplication/Need Date Any application using spacewire links. TRL5 by 2017.

Current TRL TRL 2 Target TRL TRL 3 Duration (Months) 24S/W Clause N/A Ref: to ESTER T-8823, T-7800, T-9047, T-8382, T-9056

Applicable THAG Roadmap On-Board Payload Data Processing(2011) Consistency with THAG Roadmap No

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Title Development of a miniaturised Gridded Ion Engine subsystem for futurespace missions

ObjectivesThis activity is aimed at the definition of the overall Miniaturised Gridded Ion Engine Propulsion System for theproposed Earth Observation application, the continuation of the development of the thruster, the development of theassociated neutraliser, Power Processing Unit and propellant regulator to reach subsystem PDR (TRL 5).

The activity key objectives are:- to define the subsystem and equipment specification;- to establish the subsystem architecture;- to design, build and test a neutralizer at Engineering Model (EM) level;- to design, build and test a Power Processing Unit at Elegant Breadboard (EBB) level capable to control multiplethrusters, associated neutralisers and flow regulators;- to design, build and test a flow regulator at Engineering Model (EM) level;- to perform a subsystem test of the Mini-Ion Propulsion System using the EM/EBB of all the system equipment;- to define the development plan towards a flight ready 'Mini Ion Propulsion System'.DescriptionSince 2003 ESA has promoted studies in order to establish scientific requirements, identify the most appropriatemeasurement techniques, start the associated technology developments, and define the system scenarios for aNext-Generation Gravity Mission (NGGM)or Euclide for example.

Low-thrust miniaturised Gridded Ion Engine (GIE) with variable thrust has been identified as one of the keytechnologies for the realization of the NGGM and also of other EO and science missions such as Euclide. Inparticular, it allows satellite orbit maintenance at its operational altitude; satellite formation control; implementation ofthe drag-free control at level of each satellite; attitude control of each satellite; laser beam pointing control.

Development up to engineering model level of the miniaturised GIE capable to deliver the required thrust in the range50 microN to 2 milliN has been already initiated by the Agency.However, the successful implementation of a miniaturised GIE into a flight ready micro propulsion system will bedependent on a number of additional elements including Neutralisers, Power Processing Units and suitablepropellant regulators.Those elements are available at TRL 5 only for thrusters operating in the range 10 and 500 µN. Development ofelements suitable for the required extended trust range (up to 2.5mN) shall be initiated.DeliverablesStudy ReportApplication/Need Date Euclid, NGGM, etc. / TRL5>2015


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TRP Reference T721-403MT TD TD21

TitleFlat Loop Heat Pipe Evaporator based on Advanced ManufacturingTechnologies

ObjectivesThe objective is to develop and manufacture a flat Loop Heat Pipe evaporator that would allow the evaporator to bein full contact with the Electronic box baseplate. The manufacturing of the flat evaporator shall use newmanufacturing technics developed over the past years, e.g.. additive layer manufacturing.DescriptionCurrently, the Loop heat pipe evaporators are mainly cylindrical in order to cope with the internal working pressure.All electronic units have a flat thermal interface. This means that an LHP requires an thermal interface adaptor froma rectangular flat surface to a cylindrical shape (e.g. saddle). Therefore, these additional thermal interfaces and thesmall contact area decrease the overall performance of the Loop heat pipe. A large and flat evaporator would allowthe LHP to be in full direct contact with the electronic unit, which would increase significantly the heat flow to the fluid.

In a previous R&D activity, the thin flat LHP evaporator has been studied. The evaporator was manufactured usingconventional manufacturing methods which proved to be unfeasible. With the advancement in Additive LayerManufacturing (ALM), several R&D activities are on-going with the aim to manufacture heat pipes with improved andcomplex capillary structure. Loop heat pipe requires a porous wick with smaller pores size which would be achallenge for the ALM process. However, taking into account the improvements of the technology over the years, itis expected by applying this technology to greatly increase the performance of the LHP and to reduce themanufacturing cost.

The activity aims to design and develop an engineering model of such a flat LHP evaporator.DeliverablesEngineering Model

Application/Need Date Future Integrated Electronic Unit Heat Management Systems for Electrical Units TRL 5by 2019.


Applicable THAG Roadmap Two-Phase Heat Transport Systems(2009) Consistency with THAG Roadmap Yes

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TRP Reference T710-403GN TD TD10Title New Concepts for Non-Real Time On-Board Precise Orbit DeterminationObjectivesConcept study for a non-real time on-board precise orbit determination using GNSS, altimetry data, DORIS,inter-satellite links for satellites in LEO, MEO and GEO.DescriptionCurrent on-board orbit determination concepts are in the most cases an integral part of the satellite avionics.However, it is believed that a capability of on-board precise orbit determination would allow to develop new areas ofapplications. E.g. autonomous station keeping (LEO, MEO and GEO), on-board SAR processing (LEO), missionswith high resolution image processing (LEO) or missions related to atmospheric sounding.

For this reason, this study shall investigate the conceptual approach for an on-board precise orbit determinationsystem which is not a part of the on-board avionics. However, it should be investigated in which way the avionics andthe on-board precise orbit determination system should interface in an optimal way. In this context, the overallintegration and associated interfaces to instrumentation, on-board systems (incl. avionic) and also space to groundinterface should be investigated.

The concept should consider technologies like GNSS, DORIS, altimetry and inter-satellite links, as potential datasources for the on-board precise orbit determination system. In addition, this on-board precise orbit determinationsystem should be based on a non-real time approach with the clear focus on highest achievable accuracy.DeliverablesStudy Report

Application/Need Date Future Missions in Earth Observation, Science, Navigation, Telecommunication. / TRL5by 2018


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TRP Reference T705-404EC TD TD05

Title Star Sensing based Safe Mode

ObjectivesA star tracker based safe mode is a candidate solution for a future generic safe mode, which would allow to reducethe non-recurrent cost of AOCS development. In the case of an interplanetary missions it could also solve theEarth/Satellite communication link issue by providing accurate 3-axis pointing without requesting an expensive highaccuracy gyro. Such a configuration is still immature and questionable and needs to be demonstrated and proven notonly at AOCS functional level but at avionics level. It is anticipated that such a configuration based on multiple startracker heads and a safe ephemerid configuration, would also improve the overall robustness, reliability andavailability (not requiring to bring the satellite into sun pointing safe mode as frequently).DescriptionThe activity shall give the proof of concept and demonstrate the robustness and reliability of a star tracker based safemode, and compare this to conventional safe modes. Typical earth and science observation missions shall beconsidered, (e.g. Sentinels, MTG, Euclid, Gaia, Bepi Colombo) for a generic safe mode configuration, suitable fordifferent orbits (LEO low/medium altitude, GEO, Lagrange, interplanetary). It is expected that entering safe modeshould be driven mainly by high level FDIR (hardware alarms), requiring safe mode for reasons such as safe power,thermal, communication, etc. Lower level FDIR should not require safe mode but rather recovering to a nominal ordegraded mode for improved availability.

The activity shall assess the hardware configuration, considering factors such as number of star tracker heads, fieldof view, blinding/occultation, robustness to radiation and solar flares, redundancy (hot/cold, majority voting),accommodation constraints, etc. It is expected that additional star tracker head(s) is needed to ensure redundancyand availability of sensing in case of failure, blinding, etc. The current APS based star trackers are verified to berobust to worst case solar flares. The need of an additional coarse rate sensor should be assessed, as star trackershave a limited rate performance (especially considering failure cases leading to high rates such as thrust orseparation failures). It is also necessary to safeguard the ephemerides used together with the star tracker attitudedata to resolve the required pointing for safe mode. It is expected that this is implemented in a safe way using thetypical hot redundant safe guard memory in the on-board computer. The activity shall assess the avionicsarchitecture in terms of redundancy and cross-strapping, together with the robustness and fault tolerance andassociated FDIR and software configuration. The assessment shall consider all possible failures, including commonmode failures, as well as operational errors (which could corrupt the ephemerides, that need a safe operationalconcept as e.g. for patching software). The activity shall also simulate the performance of such a star tracker modeas relevant for the studied missions and failure scenarios, including a detailed simulation of the star trackerperformance for the worst case conditions (radiation, rate, ...).

The activity is suggested as a collaborative activity(being multi-disciplinary) with involvement and support fromseveral departments/divisions:TEC-EC AOCS aspeTEC-ED Avionics aspeTEC-SW Software aspectsHSO-O Operational asctsDeliverablesStudy reports, SimulationApplication/Need Date Science and Earth Observation mission over 2017-2020. TRL 5 by 2017.

Current TRL TRL 2 Target TRL TRL 4 Duration (Months) 18S/W Clause N/A Ref: to ESTER T-7816Applicable THAG Roadmap Avionics Embedded Systems (2010) Consistency with THAG Roadmap No

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ANNEX III

TRP WORK PLAN

Justifications for Proposed Tendering Procedure

TRP WORK PLAN 2014-2015: Work and Procurement Plan 2014ANNEX III: Justifications for Proposed Tendering Procedure ESA/IPC(2013)3,add.5

Justification for Proposed Tendering Procedure: DN/CIndustrial Policy Committee

TRP Reference Activity Title Firm Fixed Price (K€) Previous (K€) Proposed BidderT117-407MM Complete Large-area MCT SWIR Detector 800 + 900 Selex ES (UK)

JustificationSelex ES is the prime contractor for current Large-area SWIR detector development, 4000104820/12/NL/RA. The aim in this activity is to use the unique ROICalready produced. Without such synergy, the cost of the activity would increase substantially. The know-how developed by Selex is also key for the success of thisactivity. Therefore, a direct negotiation with Selex will give ESA its best value for investment.

Therefore direct negotiation is applicable under Article 6.1 a) and c) of the contract regulations.

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Justification for Proposed Tendering Procedure: DN/C

TRP Reference Activity Title Firm Fixed Price (K€) Previous (K€) Proposed BidderT316-414MM Miniaturized Imaging LIDAR Systems for landing

applications (Phase 2a) 300 + 450 CSEM (CH)

JustificationContinuation (Phase 2a) of work done at "Miniaturized Imaging LIDAR systems (Phase1)",contract Co#4000103730. The consortium in the previous activity wasCSEM (CH) (Prime), EPFL (CH), Fondazione Bruno Kessler (IT), Laser Zentrum Hannover (DE) and Astrium (F). The objective of the activities related to thistechnology was to design, manufacture and test a miniaturized Imaging Lidar system. The new activity is a continuation of this work after completion of Phase 1,focussing on the detailed design (including manufacturing plans and test plans) of an elegant breadboard.

Therefore direct negotiation is applicable under Article 6.1 c) of the contract regulations.

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TRP Reference Activity Title Firm Fixed Price (K€) Previous (K€) Proposed BidderT723-406QE Utilisation of a Heavy and Light Ion Facility at UCL for

Component Radiation Studies 360 + 2435 Un. Louvain (BE)

JustificationTThe Heavy ion Irradiation Facility (HIF) at the Centre de Recherches du Cyclotron (CRC) of the Université Catholique de Louvain (UCL, Louvain-la-Neuve,Belgium) has been developed under an ESA contract (item 04.3QC.01) starting back in 1994 and commissioned at the end of 1996. Since then it has been inregular operation, supporting ESA programmes and the European Space Industry by providing at least 500 hours of beam time per year, specifically for thecharacterisation and testing of EEE components. The continuation of this contract with UCL will ensure the availability and cover the cost of 240 hours of prioritybeam time, associated support, maintenance and nominal upgrade of the PIF. These 240 hours will be primarily utilised by TRP R&D activities related tocomponent development. In addition it will reserve a minimum of 240 hours of extra beam time for ESA projects and European Space industry users at preferentialhourly rates (subject to separate purchase orders).

The support contract covered 5 years 2008-2013, (180kE/year)(ESA/IPC(2010)3, add.4) and it is now extended until 2015. The justification for the proposedprocedure is based on Articles 6.1.(a) and (c) of the ESA Contract Regulations.

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TRP Reference Activity Title Firm Fixed Price (K€) Previous (K€) Proposed BidderT723-405QE Utilisation of the High Energy Heavy Ion Test Facility at

JYFL for Component Radiation Studies 240 + 800 Un. Jyväskylä (FI)

JustificationThe facility at Jyväskylä provides high energy - high range ions (9.3MeV/a) essential for the test of modern components. It is operated as an industrial facility forthe radiation test of EEE components for space applications.

The Heavy Ion Irradiation Facility (JYFL) at the Department of Physics of the University of Jyväskylä, Finland, has been utilised by ESA for the last years (seeESA/IPC(2003)3,add.1). The facility complements the HIF/LIF at UCL (B) and the PIF at PSI (CH). The continuation of this contract with U.Jyväskylä will ensurethe availability and cover the cost of 240 hours of priority beam time, associated support, maintenance and nominal upgrade of the PIF. These 240 hours will beprimarily utilised by TRP R&D activities related to component development. In addition it will reserve a minimum of 240 hours of extra beam time for ESA projectsand European Space industry users at preferential hourly rates (subject to separate purchase orders).

The frame contract coverred 2011-2013 (120kE/year)(ESA/IPC(2010)3, add.4) and is now extended until 2015 . Direct negotiation is justified according to Article6.1 a) and c) of the Contracts Regulations.

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TRP Reference Activity Title Firm Fixed Price (K€) Previous (K€) Proposed BidderT723-402QE Utilisation of the Proton Irradiation Facility at PSI for

Component Radiation Studies 240 + 1270 Paul Scherrer Institute(CH)

JustificationThe Proton Irradiation Facility (PIF) at the Paul Scherrer Institut in Villigen, Switzerland has been developed and for the past 18 years utilised under ESA contract.Over this time frame it has been in regular operation, supporting ESA programmes and the European Space Industry by providing at least 500 hours of beam timeper year specifically for the characterisation and testing of EEE components.

The proposed activity with PSI (CH) will be a logical continuation of the use of an existing facility dedicated to component testing ESA/IPC(92)1,add.13, 127th IPCfor period 1992-1997; ESA/IPC(97)52,add.2, 160th IPC for period 1998-2002, ESA/IPC(2003)3, add1 for the period 2003-2007 and the period 2008-2010. Theexperience gained in numerous test campaigns carried out to date and its reliable operation with competent support staff have earned the PIF a good reputationand world wide recognition as a reference facility, well deserving continued ESA support.The continuation of this contract with PSI will ensure the availability and cover the cost of 240 hours of priority beam time, associated support, maintenance andnominal upgrade of the PIF. These 240 hours will be primarily utilised by TRP R&D activities related to component development. In addition it will reserve aminimum of 240 hours of extra beam time for ESA projects and European Space industry users at preferential hourly rates (subject to separate purchase orders).

The support contract covered 6 years (2008-2013, 120kE/year, (ESA/IPC(2010)3, add.4) and is now extended until 2015 . Direct negotiation is justified accordingto Article 6.1 a) and c) of the Contracts Regulations.

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Documents

ESA unclassified - For official use ESA/IPC(2013)3,add.5 Att.: … ESAIPC(2013)3,ADD.5-1.pdf · 2014-06-10 · ESA unclassified - For official use ESA/IPC(2013)3,add.5 Att.: Annexes