ESA Unclassified – For official use ESA/IPC(2015)3,add.5 Att.: Annexes Paris, 19 October 2015 (English Only)
EUROPEAN SPACE AGENCY
INDUSTRIAL POLICY COMMITTEE
BASIC TECHNOLOGY RESEARCH PROGRAMME
TRP WORK/PROCURMENT PLAN 2016
The IPC is invited to approve the TRP Work/Procurement Plan 2016 by simple majority of the Member States: AT+BE+CH+CZ+DE+DK+EE+ES+FR+FI+GB+GR+IT+IE+LU+NO+NL+PL+PT +RO+SE
SUMMARY This document is the TRP Work and Procurement Plan for 2016.
REQUIRED ACTION 1.- Member States are invited to approve the attached TRP Work Plan 2016.
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 and in Annex III.
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BASIC TECHNOLOGY RESEARCH PROGRAMME
TRP WORK/PROCUREMENT PLAN 2014
Table of Contents
- Scope of the document - Key to Tables - ANNEX I: Detailed TRP Plan 2016 - ANNEX II: Description of the Activities - ANNEX III: Justification for Non-Competitive Tender (if applicable)
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SCOPE OF THE DOCUMENT This document presents the Work Plan of the Basic Technology Research Programme (TRP) for 2016. The TRP Plan 2016 builds upon the Preliminary Selection of Activities document (ESA-IPC(2015)121) presented for information to the 294th 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 domains of Earth Observation, Space Transportation, Telecommunications, Navigation and Generic Technologies. Application Domains Science and Exploration will be presented separately.
The TRP Preliminary Selection of Activities document (ESA-IPC(2015)121) includes 176 activities for a total of 73M€. 107 activities are currently presented for TRP WP 2016 for a total of 46M€.
The IPC is invited to approve the proposed 2016 Work Plan and the connected procurement actions. ESA/IPC(2015)3,add.5 Page 5 of 8
KEY TO TABLES
The TRP WP/PP for 2016 is presented along the following headings:
– Technologies related to Earth Observation. – 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 Work Plan 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 (ESA/REG/001, rev.3):
C : Open Competitive Tender; (Ref. Article 13.1 ESA Procurement 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).
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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 prospects 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 13.2 ESA Procurement 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 14.1.a,d,e ESA Procurement 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 14.1.c ESA Procurement Regulations)
* See ESA/IPC(2005)87, rev4. Industry has been informed, through the EMITS "News", of the content of that document.
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 equipment/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 equipment, TRP usually concludes with TRL 3/4, GSTP at level 5/6.
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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)
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.
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ESA/IPC(2015)3,add.5 TRP WORK/PROCUREMENT PLAN 2016-201 List of Activities Annex IAnnex I, page 1 of 24
ANNEX I
TRP WP/PP PLAN 2016
List of Activities
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 2 of 24
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1 - Earth Observation
1 - 01 - Microwave Payloads
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Low Side Lobe Level Image Reconstruction in Microwave IPC T106-501ET 500 C(2) N/A Interferometry Multiple RF apertures based on reflectarray antennas for high T107-504EE 450 C N/A resolution SAR instrument Frequency stabilisation of a Quantum Cascade Laser for Supra-THz T107-505EE 400 C(3) N/A applications T107-506EE Large reflector antenna requirements for Earth Observation missions 300 C N/A Understanding and modelling the temporal component of the intensity Open source IPC T107-507EE 350 C(3) and phase of radar signals over land and sea code TOTAL 1 - 01 - Microwave Payloads 2000
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 4 of 24
1 - Earth Observation
1 - 02 - Optical Payloads
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Assessment of the potential use of the high resolution Thermal Infra- T107-501EE 250 C(3) N/A Red (TIR) band IPC T116-501MM Characterisation of contamination induced straylight 600 C(1) N/A Concepts for the in-orbit characterisation of the Instrument Spectral T116-502MM 400 C N/A Response Function IPC T116-504MM Alternative polishing layers for a large breadboard mirror 500 DN/C FR N/A RESOC (FR)
T116-505MM Superblack coatings on real size opto-mechanical structures 300 C(1) N/A TRP 1600KE and EOEP IPD 400KE IPC T117-501MM Large Format Short Wave Infra-Red (SWIR) Detector Array 2000 C(1) N/A co-funded activity T117-502MM Particle Mitigation In High Power Laser Optics 400 C(1) N/A
IPC T117-503MM Control ASIC for Earth Observation Infrared Detector Array 800 C(1) N/A Cosine B.V. (NL), Politecnico di AT, CH, Milano (IT), Logikon Labs (GR), IPC T117-504MM Multi-kHz, multi-beam single photon counting vegetation LiDAR 500 DN/C GB, GR, N/A Entner Elelctronics (AT), TU Wien IT, NL (AT), ID Quantique (CH), Imperial College (GB) T123-501QT Microlenses deposition for backside-illuminated imagers 250 C(1) N/A TOTAL 1 - 02 - Optical Payloads 6000
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 5 of 24
1 - Earth Observation
1 - 03 - Platforms / Others
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 High accuracy image stabilization system for GEO High Resolution T105-501EC 350 C N/A Missions - Preliminary design and performance assessment AC T109-501GD File based operations for EO missions 300 C Operational S/W Enhanced Antenna Tracking receiver for use within the 26 GHz K- T112-501GS 300 C(1) N/A band frequency allocation. TOTAL 1 - 03 - Platforms / Others 950
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 6 of 24
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Preliminary Design and Development of an Avionics prototype for AC T402-501SW 300 C Operational S/W Nano and Micro-Launchers IPC T405-502EC Adaptive Flight Guidance and Control Systems with Reconfiguration 500 C N/A
AC T418-502MP Alumina particulate characterization in flight 300 DN/S FR N/A CNES (FR) + subcontractors
T420-501MS Launch Sound Level Reduction 350 C N/A
AC T421-501MT Polyimide Cryogenic Lines for Launcher Propulsion Systems 300 DN/C AT N/A Magna Steyr (AT)
T423-501QT Supercapacitor for Launcher applications 300 C(1) N/A Open source IPC T424-501QT Particle modelling inside fairings during pre-launch and launch 250 C code TOTAL 4 - 01 - Launchers Oriented Technologies 2300
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 7 of 24
4 - Space Transportation & Re-entry Technologies
4 - 03 - Generic Space Transportation Technologies
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Full Trajectory Structural Load Determination for Reusable Space AC T420-502MS 270 DN/S IT N/A CIRA (IT) Vehicles TOTAL 4 - 03 - Generic Space Transportation Technologies 270
4 - Space Transportation & Re-entry Technologies
4 - 04 - Re-Entry Technologies
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Hypersonic Authority Determination and Control for Aerodynamically AC T405-501EC 270 DN/S IT N/A CIRA (IT) Slender Vehicles Influence of Leading Edge Imperfection on Boundary Layer State of a T418-501MP 240 DN/S DE N/A DLR (DE) Volumetric Waverider Configuration Determination of an In-Flight Measurement System for the AC T418-507MP 285 C(R) DE, IT N/A CIRA (IT), DLR (DE) characterization of reusable vehicles. TOTAL 4 - 04 - Re-Entry Technologies 795
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 8 of 24
5 - Telecommunications
5 - 01 - System / Network / Protocols
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Optimization of the Physical Layer Performance in High Data Rate T506-502ET 200 C(3) N/A Optical Links TOTAL 5 - 01 - System / Network / Protocols 200
5 - Telecommunications
5 - 02 - Space Segment - Platform
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T519-501MP Propulsion Pump Trade-off 250 C(2) N/A
IPC T521-501MT Variable Emissivity Radiator Breadboard 550 C N/A TOTAL 5 - 02 - Space Segment - Platform 800
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 9 of 24
5 - Telecommunications
5 - 03 - Space Segment - Payload
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T506-501ET High Power W-Band TWT 450 C(1) N/A Dual-Band Polarizing Surfaces for Single Feed per Beam broadband T507-502EE 450 C N/A Antennas IPC T520-501MS Solid reflector with metal mesh as reflective surface 500 C N/A Advanced Aluminum Fittings in Carbon Fibre Reinforced Plastic T520-503MS 300 C(1) N/A (CFRP) Tubes TOTAL 5 - 03 - Space Segment - Payload 1700
5 - Telecommunications
5 - 04 - Ground Segment
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Antenna user terminal with Wide Angle Impedance Matching (WAIM) T507-503EE 450 C(1) N/A metamaterial radome. IPC T517-501MM Optical Feeder-link for next generation telecommunication satellites 500 C(2) N/A TOTAL 5 - 04 - Ground Segment 950
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 10 of 24
6 - Navigation
6 - 01 - Systems
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Blind GNSS software receiver tool for field test assessment in harsh T606-509ET 350 C(1) N/A environments T606-510ET Authentication of GNSS signals by radio signal fingerprinting 300 C(1) N/A Simulation Testbed for Evaluation of GNSS Performance in a Railway IPC T606-511ET 500 C(1) N/A Environment IPC T606-512ET Enhanced GNSS signals in Space and user receiver processing 500 C(1) N/A
T606-515ET Tool for GNSS System failure modes investigation 300 C(2) N/A TOTAL 6 - 01 - Systems 1950
6 - Navigation
6 - 02 - Space Segment
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Advanced glass cell technology for extended GNSS atomic clocks T606-502ET 350 C(1) N/A lifetime TOTAL 6 - 02 - Space Segment 350
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 11 of 24
6 - Navigation
6 - 04 - Users
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Carrier Phase Positioning Techniques for Mass Market GNSS T606-501ET 300 C(1) N/A Receivers Advanced open-loop techniques for high-sensitivity GNSS receivers T606-506ET 300 C(1) N/A applied to BOC signals TOTAL 6 - 04 - Users 600
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 12 of 24
7 - Generic Technologies and Techniques
7 - 01 - Onboard Data Systems
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 SpaceWire Network Management Service Suite Definition and T701-501ED 450 C(2) N/A Validation Verification of SEU-mitigation techniques in 3rd/4th generation Flash IPC T701-503ED 600 C(1) N/A FPGAs TOTAL 7 - 01 - Onboard Data Systems 1050
7 - Generic Technologies and Techniques
7 - 02 - Space System Software
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Open source IPC T702-501SW Payload Execution Platform Software 500 C code TOTAL 7 - 02 - Space System Software 500
7 - Generic Technologies and Techniques
7 - 03 - Spacecraft Electrical Power
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 IPC T703-501EP Process Development for Ultra-Thin Solar Cells 1500 C(1) N/A TOTAL 7 - 03 - Spacecraft Electrical Power 1500
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 13 of 24
7 - Generic Technologies and Techniques
7 - 04 - Spacecraft Environments and Effects
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Prototype Passive Field-Effect Electron Emitter for Charging T704-501EE 350 C N/A Alleviation Open source IPC T704-502EE Solar Particle Radiation Advanced Warning System (SAWS) 300 C(3) code TOTAL 7 - 04 - Spacecraft Environments and Effects 650
7 - Generic Technologies and Techniques
7 - 06 - RF Systems, Payloads and Technologies
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 IPC T706-501ET High Performance MEMS Reference Oscillator 750 C(1) N/A Test methodology investigations and parameters influencing Passive IPC T706-502ET 700 C N/A InterModulation (PIM) interference TOTAL 7 - 06 - RF Systems, Payloads and Technologies 1450
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 14 of 24
7 - Generic Technologies and Techniques
7 - 07 - Electromagnetic Technologies and Techniques
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Characterization of the susceptibility of SpaceWire (SpW) links to T707-501EE 350 C N/A common mode TOTAL 7 - 07 - Electromagnetic Technologies and Techniques 350
7 - Generic Technologies and Techniques
7 - 08 - System Design & Verification
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Enabling fully traceable thermal imaging of spacecraft during thermal- T708-503MX 250 C N/A vacuum, thermal balance testing TOTAL 7 - 08 - System Design & Verification 250
7 - Generic Technologies and Techniques
7 - 09 - Mission Operation and Ground Data Systems
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 AC T709-501GE Penetration Testing and Security Awareness Management in a Box 250 C(1) Operational S/W Trade-off and technological analysis/prototyping for the new IPC T709-502GI 550 C Operational S/W generation simulators infrastructure (SIMULUS-NG) TOTAL 7 - 09 - Mission Operation and Ground Data Systems 800
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 15 of 24
7 - Generic Technologies and Techniques
7 - 10 - Flight Dynamics and GNSS
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 AC T710-501GF Navigation concepts for multi-revolution SEP transfers 400 C(1) Operational S/W
IPC T710-503GN Independent generation of Earth Orientation Parameter 500 C(1) Operational S/W TOTAL 7 - 10 - Flight Dynamics and GNSS 900
7 - Generic Technologies and Techniques
7 - 11 - Space Debris
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Extension of the high-fidelity re-entry break-up simulation software AC T711-503GR 300 C Operational S/W based on new measurement types TOTAL 7 - 11 - Space Debris 300
7 - Generic Technologies and Techniques
7 - 12 - Ground Station Systems and Networks
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T712-502GS X-Band Sampling Technology Demonstration 350 C(1) N/A TOTAL 7 - 12 - Ground Station Systems and Networks 350
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 16 of 24
7 - Generic Technologies and Techniques
7 - 13 - Automation, Telepresence & Robotics
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 COntrol and Management of Robotic for Active DEbris removal IPC T713-502MM 1000 C(1) Operational S/W (COMRADE) TOTAL 7 - 13 - Automation, Telepresence & Robotics 1000
7 - Generic Technologies and Techniques
7 - 15 - Mechanisms
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 IPC T715-503MS Magnetically Clean Reaction Wheel 700 C(1) N/A TOTAL 7 - 15 - Mechanisms 700
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7 - Generic Technologies and Techniques
7 - 17 - Optoelectronics
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 IPC T717-502MM Deep-Space Optical Communication compatible multifunction LIDAR 500 C(1) N/A TOTAL 7 - 17 - Optoelectronics 500
7 - Generic Technologies and Techniques
7 - 18 - Aerothermodynamics
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Embedding of improved CFD Code developments into T718-503MP Multidisciplinary Analyses - Feasibility Assessment and Roadmap 170 C(3) N/A Development TOTAL 7 - 18 - Aerothermodynamics 170
7 - Generic Technologies and Techniques
7 - 19 - Propulsion
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T719-501MP Use of Iodine as propellant for Hall Effect Thrusters 400 C(1) N/A TOTAL 7 - 19 - Propulsion 400
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 18 of 24
7 - Generic Technologies and Techniques
7 - 20 - Structures
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 IPC T720-501MS Stress rupture prevention of composite high pressure vessels 500 C N/A TOTAL 7 - 20 - Structures 500
7 - Generic Technologies and Techniques
7 - 21 - Thermal
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T721-501MT Pulsating Heat Pipes 400 C(1) N/A TOTAL 7 - 21 - Thermal 400
7 - Gen eri c Technologies and Techniques
7 - 22 - Environmental Control & Life Support (ECLS) and In Situ Resource Utilisation (ISRU)
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Technology to quantify and qualify microbial contamination on IPC T722-501MM 650 C(1) N/A surfaces TOTAL 7 - 22 - Environmental Control & Life Support (ECLS) 650 and In Situ Resource Utilisation (ISRU)
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 19 of 24
7 - Generic Technologies and Techniques
7 - 24 - Materials and Processes
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T724-506QT Modelling and Simulation of Electronic Assemblies 400 C N/A
T724-507QT Contamination repellent coatings 400 C N/A TOTAL 7 - 24 - Materials and Processes 800
7 - Generic Technologies and Techniques
7 - 25 - Quality, Dependability and Safety
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Redundancy Concepts for Minimum Mass and Acceptable Failure T725-501QQ 250 C N/A Protection. T725-503QQ Reliability Model Enabling Satellite Life Extension and Safe Disposal. 350 C N/A TOTAL 7 - 25 - Quality, Dependability and Safety 600
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 20 of 24
7 - Generic Technologies and Techniques
7 - 26 - Spacecraft Avionic System
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Compact Reconfigurable Avionics : Reconfigurable Data Handling IPC T701-504ED 700 C Operational S/W Core IPC T702-502SW Compact Reconfigurable Avionics : Model Based Avionics Design 650 C Operational S/W
IPC T705-504EC Compact Reconfigurable Avionics: Smart AOCS & GNC Elements 650 C N/A TOTAL 7 - 26 - Spacecraft Avionic System 2000
7 - Generic Technologies and Techniques
7 - 27 - End to End System Design Processes
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Improvement of methodologies for thermo-elastic predictions and IPC T708-501MT 600 C N/A verification AC T708-502GE Paperless E2E Ground Segment Engineering 350 C(2) Operational S/W
IPC T708-506SW Application of co-simulation to support Test and Operations 600 C(2) N/A TOTAL 7 - 27 - End to End System Design Processes 1550
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 21 of 24
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T723-501QT State of the art packaging techniques for high power applications 270 C(2) N/A Prototyping and characterization of optical isolators for visible T723-502QT 250 C(1) N/A wavelengths Humidity resistance assessment of MCT based IR detectors in open T723-504QT 350 C(1) N/A packages. Paul Scherrer Institute (CH). Will be Utilisation of the Proton Irradiation Facility at PSI for Component T723-507QE 120 120 DN/C CH N/A subject to separate Procurement Radiation Studies Proposals. Utilisation of the High Energy Heavy Ion Test Facility at JYFL for JYFL (FI). Will be subject to separate T723-508QE 120 120 DN/C FI N/A Component Radiation Studies Procurement Proposals. Utilisation of a Heavy and Light Ion Facility at UCL for Component UCL (BE). Will be subject to separate T723-509QE 180 180 DN/C BE N/A Radiation Studies Procurement Proposals. Improved robustness passive components for realisation of rad-hard T723-510QT 250 C(1) N/A GaN MMICs TOTAL 7 - 28 - Electronic Components 1540 420
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 22 of 24
7 - Generic Technologies and Techniques
7 - 32 - Clean Space
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 Probabilistic assessment of re-entry break-up analyses and derived T711-504GR 300 C N/A quantities AC T715-502MS REACH treatment of the pyrotechnics initiators powder 275 DN/S FR N/A Dassault (FR)
T715-506MS Assessment of design for demise approaches for reaction wheels 100 C(3) N/A REACHLaw (prime, FI) and VTT AC T724-501QT REACH obsolescence management for Materials & Processes 200 DN/C FI N/A (subco, FI). Development of green polyurethane materials for use in spacecraft T724-502QT 300 C(2) N/A and launcher applications Fluid Gravity (UK), Belstead research Development and testing of materials combination and coatings to AT, BE, IPC T724-503QT 300 C(R) N/A (GB), AAC (AT), VKI (BE), IRS (DE), meet demisability requirements DE, GB DLR Koln (DE), HTG (DE), OGI (AT) TOTAL 7 - 32 - Clean Space 1475
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7 - Generic Technologies and Techniques
7 - 33 - Space and Energy
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 AC T713-503MM NOvelty or Anomaly Hunter (NOAH) 425 C(1) Operational S/W
T718-501MP Design and breadboard test of ultrasound technique 100 C(3) N/A
T718-502MP Challenges related to the design of a reservoir for the transport of H2 200 C(1) N/A Continuous Temperature Measurement Technique - Application to a T721-503MT 350 C(3) N/A Self-Regulating Heating Cable TOTAL 7 - 33 - Space and Energy 1075
7 - Generic Technologies and Techniques
7 - 35 - Technologies Enabling Breakthroughs in Science
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T712-503GS Highly Selective Filter System for Optical Antennas 350 C(1) N/A All-optical diffractive element approach to compact, simple, rapid BEC IPC T717-501MM 600 C(3) N/A creation in space TOTAL 7 - 35 - Technologies Enabling Breakthroughs in 950 Science
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5 List of Activities Annex I, Page 24 of 24
7 - Generic Technologies and Techniques
7 - 36 - Collaborative Activities
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 IPC T710-502GF Future navigation concepts at small bodies 600 C(1) Operational S/W
IPC T720-505MS Large Deployable Reflector for IOD preparation 1000 C N/A Quality Assessment of the new European Space FPGA Software IPC T725-502QQ 650 C N/A Tools Radio Frequency Interference Scenarios, Application Requirements IPC T726-501ET 600 C N/A and Counteraction Techniques Multi-Disciplinary Design and Breadboarding of Technologies for Early IPC T726-502SY 600 C N/A Break-up of Spacecraft During Re-entry TOTAL 7 - 36 - Collaborative Activities 3450
7 - Generic Technologies and Techniques
7 - 38 - Advanced Manufacturing
Approval Programme SW Clause Activity Title Budget (k€) PP Cty Remarks Level Reference Applicability
2015 2016 2017 T720-502MS Thin-Ply-Laminate Composite Structures 450 C N/A
IPC T724-504QT ESA Additive Manufacturing Benchmarking 900 C(3) N/A
T724-508QT Curing on demand polymerisation by switchable stimulus 350 C(2) N/A TOTAL 7 - 38 - Advanced Manufacturing 1700
TRP WORK/PROCUREMENT PLAN 2016-2017 ESA/IPC(2015)3,add.5
Activity Description Annex Annex II, page 1 of 112
ANNEX II
TRP WP/PP PLAN 2016
Activity Description
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 2 of 112 Activity Description
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Activity Description Annex II, page 3 of 112
1 - Earth Observation
1 - 01 - Microwave Payloads Programme T106-501ET TD 06 Reference Activity Title
Low Side Lobe Level Image Reconstruction in Microwave Interferometry Objectives This activity aims to demonstrate the dummy element technique in aperture synthesis radiometry to achieve low noise floor, low side lobes and better image reconstruction accuracy. Description SMOS has shown the importance of achieving low level of noise floor and side lobes for best image quality in aperture synthesis radiometry. One key factor is the similarity between element patterns. During the TRP study on Super-MIRAS a solution was proposed based on dummy elements. This activity includes the following tasks : - To build of a representative part of an aperture synthesis radiometer at L-band with a conventional ground plane and with the proposed dummy element technique. - To measure of the patterns of the active elements. - To perform a full image reconstruction simulation and calculation of the noise floor for an ocean scene and a point source for both configurations. - To demonstrate of the expected better performance of the dummy element technique over the conventional configuration The results of this activity are general, i.e. valid to any type of microwave interferometer. Deliverables
Breadboard Application/Need Date
SMOS follow-on operational mission / TRL-3 by 2017 Duration Current Target 18 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Critical RF Payload Technologies (2004) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 4 of 112 Activity Description
1 - Earth Observation
1 - 01 - Microwave Payloads Programme T107-504EE TD 07 Reference Activity Title
Multiple RF apertures based on reflectarray antennas for high resolution SAR instrument Objectives The objectives of the activity are to trade-off, design and develop a reflectarray based antenna for high resolution SAR instrument. This antenna development shall allow the SAR instrument to have both Along Track interferometry (ATI) and Ground Moving Target Indication (GMTI) capabilities. Description There is a strong interest to investigate antenna solutions for a high resolution SAR instrument with Along Track interferometry (ATI) and Ground Moving Target Indication (GMTI) capabilities. A high resolution SAR instrument with ATI/GMTI capabilities would strongly benefit from the reflect array concept. This is considered as an attractive antenna solution since it exhibits low weight, low cost and low stowage volume. For such a purpose, it is proposed to develop a passive reflectarray antenna with dual polarized elements that shall be designed such that 2 independent beams (one per polarization) are generated, i.e. one moderately broad beam and one pencil beam.
The study consists in : - state of art survey and specifications for the reflectarray based antenna for high resolution SAR instrument with ATI/GMTI capabilities - Trade-off study , design and analysis (RF & structural) of a deployable Ka-band reflectarray antenna (i.e. dual linearly polarized low loss reflectarray elements, stable reflectarray antenna structure, antenna deployment system) - Manufacturing and test of critical elements - Development plan and roadmap Deliverables
Breadboard Application/Need Date
2018 Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Array Antennas (2011) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 5 of 112
1 - Earth Observation
1 - 01 - Microwave Payloads Programme T107-505EE TD 07 Reference Activity Title
Frequency stabilisation of a Quantum Cascade Laser for Supra-THz applications Objectives The objective is to demonstrate the feasibility of the frequency stabilization of a Quantum Cascade Laser (QCL) and demonstrate the improvement of a stabilization loop with respect to passive stabilization. Description The supra-THz (>3 THz) bands have been recently proposed for low Earth orbit THz remote sounding missions such as LOCUS (Low-Cost Upper-atmosphere Sounder). In order to achieve coherent detection, heterodyne receivers at supra- THz frequencies are under development by integrating in a single waveguide cavity a Schottky based mixers fed by a Quantum Cascade Laser (QCL) as Local Oscillator (LO). Thanks to the QCL, enough LO power is available to drive the mixer.
Currently, a simple combination of passive thermal and electrical bias control is proposed for the frequency stabilization of the QCL. In order to achieve the frequency stability that would allow meeting the scientific requirements, phased lock loop systems such as the beating tone of two lasers injected into the QCL shall be investigated.
The activity aims at proposing, manufacturing and testing a frequency stabilization loop for QCLs used as LO of supra- THz Schottky mixers.
The activity consists in: - establishing the state of the art survey for the Schottky based supra-THz heterodyne receivers and QCL LO, - issuing the main mission, receiver and LO performance requirements including frequency stability. - performing trade off analysis and selecting one baseline frequency stabilization loop solution including its integration with the QCL and Schottky mixer. - designing and analysing the selected configuration. - manufacturing and testing the critical breadboard elements - proposing a roadmap and a development plan for the critical elements. Deliverables
Breadboard Application/Need Date
2018 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Technologies for Passive Millimetre & Submillimetre Roadmap No Roadmap Wave Instruments (2010) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 6 of 112 Activity Description
1 - Earth Observation
1 - 01 - Microwave Payloads Programme T107-506EE TD 07 Reference Activity Title
Large reflector antenna requirements for Earth Observation missions Objectives The objectives are to identify EO missions that would strongly benefits from large reflector based instruments, perform preliminary antenna design and derive the associated reflector requirements. The EO specific needs and possible critical elements of the reflector shall be identified to elaborate a development plan. This will be used for further activities with the aim to retire the associated risks and maximise the adequacy of the large reflector development to several missions. Description Next generation of Earth Observation (EO) passive and active microwave instruments will require large reflector antennas. For instance, the power budget is very often a design driver for active instruments, such as synthetic aperture radars, and requires large apertures to minimize the power amplification needed at front-end level. Other system parameters of the SAR instrument, such as radar resolution, sensitivity, and ambiguities, are directly or indirectly impacted by the antenna aperture and its associated performance. Regarding the passive instruments, the real aperture radiometers require also large aperture for high spatial resolution, whereas the companion passive receive antenna of bi-static SAR instruments requires as well large apertures to satisfy the radar link budget. Reflector based instruments enable reduced mass and power budgets, as well as simplification of calibration and instrument electronics. Multifrequency and multipolarisation capabilities can be implemented with limited added complexity. The large reflector activities, undertaken by ESA so far, have been driven mainly by telecommunication needs, which typically require a large reflector antenna to generate multiple adjacent and highly directive beams in order to increase the system throughput on a dedicated terrestrial service area. Although it is expected that there are many common requirements, attention shall be paid to specific needs from EO missions that can be very different, and often more stringent than the telecommunication ones. This activity will study the specific needs of Earth Observation missions in detail, specifically in term of derived large antenna requirements that may have an impact on the design and development of European large unfurlable reflectors. For instance, the LEO environment seen by the vast majority of microwave instruments flying is different from the one seen by the GEO telecommunication payload. Furthermore, whereas the large antenna based telecommunication missions require the multiple beams to be fixed, most of the EO instruments require high beam agility depending on the scene to be observed. This is often done by combining electrical and mechanical scanning of the instrument antenna which are expected to introduce some specific requirements on the large unfurlable reflector in terms of reflector surface shape, and associated accuracy and stability in a dynamic configuration. The impact of other instrument requirements such as the aspect ratio of the beam footprint, the resolution, the sensitivity and the ambiguities shall also be analysed. The activity will consist in : - Identifying EO missions active and passive instruments which may require large aperture antennas - Deriving a limited set of representative instruments with associated requirements - Performing antenna preliminary RF/mechanical/thermal design and analyses on this cases - Elaborating the associated reflector requirements and comparing with the ones derived from telecommunications needs - Performing a preliminary design of the corresponding reflectors with identification of the critical areas deserving specific design, analysis and breadboarding - Proposing a development plan and a roadmap for the identified critical elements Deliverables
Study Report Application/Need Date 2018 Duration Current Target 12 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Telecommunications Reflector Antennas (2009) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 7 of 112
1 - Earth Observation
1 - 01 - Microwave Payloads Programme T107-507EE TD 07 Reference Activity Title
Understanding and modelling the temporal component of the intensity and phase of radar signals over land and sea Objectives The main objective of this activity is to develop reference models for the temporal fluctuations of the radar scatter over natural surfaces, land and sea. These models shall be linked to the appropriate processing tools to in order to enable the generation of meaningful signatures Description An increasing number of SAR mission concepts make use of the phase (or phase derivative) of the signal backscattered from the natural surface. A proper simulation of this temporally variable component is required either to estimate the performance of the concept (e.g. impact of temporal decorrelation in a long track interferometry or for long integration times) or to support the derivation of related surface properties (e.g. sea currents from in SAR or Doppler).
Over land the framework shall be based on a physical model that takes into account the contribution of the stable (in amplitude/phase) and unstable components of the natural target. This decomposition shall be supported by land cover information and shall take into account the spatial resolution of interest. The primary target of this study is complex backscatter for which parametrisation and validation data can be made available using available experimental datasets. The output shall be useable to investigate and reproduce the temporal properties of the microwave scatter over short (synthetic antenna generation), intermediate (orbital convoy) and long (interferometric temporal decorrelation and time series) time scales, spanning from tenths of seconds to days.
Over sea there is a need for a mission agnostic reference model of the microwave sea surface scattering that allows to reproduce the phase/Doppler taking into account a realistic spatio-temporal description of the sea surface. It shall produce as an output the amplitude, phase of the scattered signal as well as able to derive the induced SAR signatures (Doppler, etc.).
This model shall be developed based on state of the art spatio-temporal descriptions of the sea surface and adequate microwave interaction solutions.
The framework shall be developed for frequencies from P- to Ka-band, and parametrised as well as validated for a subset of these frequencies. Experimental data or reference simulations shall be used to feed and validate the models. It is expected that at the end of the study these models will be made available to the scientific community for further developments. Deliverables
Software Application/Need Date All SAR missions in particular those involving: insar (wavemill, SAOCOM-CS), long integration times (GeoSTARe), use of Doppler product ... Duration Current Target Open source 24 2 3 SW Clause (Months) TRL TRL code Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 8 of 112 Activity Description
1 - Earth Observation
1 - 02 - Optical Payloads Programme T107-501EE TD 07 Reference Activity Title
Assessment of the potential use of the high resolution Thermal Infra-Red (TIR) band Objectives This activity aims to investigate the potential of high resolution TIR channels over natural land cover and consolidate the related tools. Description The inclusion of Thermal Infra-Red (TIR) bands may be a solution to be considered in preparation of future high resolution optical imagers. In fact the inclusion of such bands may bring an additional improvement to the retrieval capabilities already offered by VNIR/SWIR and in several cases new mission objectives can be targeted. Optical imagers developed for ASTER, MASTER, TIMS, MODIS and Landsat missions include already few TIR channels, demonstrating great potentialities for retrievals and detections.
In particular, for what concerns natural land cover, there is a need - in order to support the investigations of the Agency and of the scientific community in this field - to provide spectral libraries, analysis tools and first methods for assessing the capabilities of potential hyperspectral TIR bands for retrieving biophysical and biochemical parameters.
This can be achieved by completing the following high level tasks: - definition and parameterization of some vegetation reference scenarios; - generation of spectral signatures for the selected scenarios considering different soil, vegetation condition, different viewing geometry and stage of growth; - analysis of possible co-relation between observable vegetation parameters and the response in the TIR spectral domain using the simulated database of signature; - development and testing of initial retrieval methods using the simulated database of signature (in synergy with VIS/NIR and other observations).
The following outputs are expected: - accurate and well described database of spectral signatures that can be also easily re-used for further investigations in the future; - methods, tools implementing preliminary retrieval methods; - analysis results, methods testing using the database of spectral signatures - guidelines as base for future mission requirements; - clear requirements for potential in-situ campaigns. Deliverables
Other: Study Report - Simulation database Application/Need Date Needed to define clear requirements for any TIR channel over land for future high res TIR imagers. Output (e.g. signatures database) would also support scientific investigations. Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 9 of 112
1 - Earth Observation
1 - 02 - Optical Payloads Programme T116-501MM TD 16 Reference Activity Title
Characterisation of contamination induced straylight Objectives Determine the scatter function dependent on different levels of contamination in order to support straylight modelling for future instrument design and performance assessment during instrument Assembly, Integration, and Test (AIT).. Description With state-of-the-art polishing techniques straylight from surface roughness is decreased and straylight induced by contamination is becoming one of the main contributors to the straylight performance. It is then important to rely on representative models for contamination induced straylight. Typically, industry is using models coming from literature, which can lead to very different results.
The activity shall include the following tasks : - A critical review of the existing models shall be performed. - Bidirectional Reflectance Distribution Function (BRDF) and Bidirectional Transmittance Distribution Function (BTDF) measurements shall be performed on different contaminated samples (mirrors, lenses) with known amounts of contamination (particulate and molecular) after being exposed to a cleanroom environment. - Derivation of scatter functions from the measurements to be used in straylight analysis software. This shall take into account the spectral dependence. - Measurements in different cleanrooms shall be performed and compared (in terms of particle distribution function and scattering function). Deliverables
Technical notes (models overview, test plan, test procedures), Contaminated samples, BRDF/BTDF measurements Application/Need Date
Any kind of optical mission/ TRL 4 2019 Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap System Modelling and Simulation Tools (2012) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 10 of 112 Activity Description
1 - Earth Observation
1 - 02 - Optical Payloads Programme T116-502MM TD 16 Reference Activity Title
Concepts for the in-orbit characterisation of the Instrument Spectral Response Function Objectives Objective is the development of concepts and methods that can be used to characterise the Instrument Spectral Response Function of a typical EO spectrometer instrument in orbit. Description Recent Earth Observation (EO) instruments require an extremely high accuracy for the characterisation of the Instrument Spectral Response Function (ISRF). This leads to lengthy and costly characterisation test programs during the Assembly, Integration, and Test (AIT) phase of the instrument.
This activity will focus on the investigation and development of in-orbit means for ISRF characterisation that could potentially save cost and schedule during on-ground AIT. The activity includes the following tasks : - hardware needs for the instrument and associated requirements - definition of an overall characterisation concept and associated processing algorithms - schedule/cost/risk trade between a pure on-ground characterisation and a combined on-ground/in-orbit characterisation - breadboard demonstrating the characterisation concept Deliverables
Breadboard Application/Need Date
2017 Duration Current Target 18 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 11 of 112
1 - Earth Observation
1 - 02 - Optical Payloads Programme T116-504MM TD 16 Reference Activity Title
Alternative polishing layers for a large breadboard mirror Objectives This activity aims to validate of the previously developed alternative polishing layer technology on a mirror of at least 1m diameter Description Ceramic mirrors of SiC or SiN exhibit a porosity that requires a dense polishing layer. For SiC mirrors, this is typically a thin layer of SiC deposited by CVD that has been occasionally difficult to deposit in good quality.
Therefore, an alternative polishing layer has been developed in a previous activity on smaller samples.
The objective of this activity is the validation of this alternative polishing layer technology on a larger mirror by: - manufacturing a polishing layer on a >1m mirror substrate - polishing to a roughness level and WFE typically required - thermal testing of the mirror to prove durability of the layer Deliverables
Breadboard Application/Need Date
2018 Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Technologies for Optical Passive Instruments Roadmap Yes Roadmap (Mirrors) (2013) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 12 of 112 Activity Description
1 - Earth Observation
1 - 02 - Optical Payloads Programme T116-505MM TD 16 Reference Activity Title
Superblack coatings on real size opto-mechanical structures Objectives The objective of this activity is the application of super black coatings on representative opto-mechanical structures (like mounts or baffles) and verification of their performance by relevant tests. Description Space optical missions require more and more stringent requirements on stray light levels. Light absorbing surfaces (black surfaces) are key for reducing the stray light in optical instruments. They are usually applied on internal and external baffle surfaces. In the recent years some new super-black materials (very absorbing materials compared to existing ones) involving different coating techniques have been developed but not yet fully tested on full size flight hardware.
The recently developed superblack coatings show similar performance whatever the incidence angle is which is very interesting compared to existing black coatings. Moreover, they could potentially be alternative low cost solutions.
The objective of this activity is to apply and optimize recently developed super-black coatings to enable coating of representative surfaces (baffles, mounts) regarding substrate material, shape (corners/edges) and size.
The tasks included in this activity shall focus on: - Optimisation of the application processes regarding the substrate types, sizes and shapes - Manufacturing of demonstrators/breadboards that will use the optimised process to enable the best opto-mechanical properties - Breadboard testing in terms of mechanical performance under specific environment/conditions - Breadboard testing in terms of optical performances (BRDF, TIS, specular reflectance) Deliverables
Breadboard Application/Need Date
Any optical mission and especially EO future missions/ TRL 4 2020 Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Technologies for Optical Passive Instruments Roadmap No Roadmap (Stable & Lightweight Structures) (2013) Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 13 of 112
1 - Earth Observation
1 - 02 - Optical Payloads Programme T117-501MM TD 17 Reference Activity Title
Large Format Short Wave Infra-Red (SWIR) Detector Array Objectives The objective is to design, manufacture and characterisation of a high-performance 2k x 2k pixel SWIR detector array for future Earth Observation missions. Description 1k x 1k SWIR detector arrays are now available within Europe and are being utilised in the current generation of spectral and hypersepctral EO instruments.
The need for larger format arrays however, has been clearly identified and it is also evident that such developments are now feasible within Europe.
This activity aims to exploit these capabilities through the low-risk, further development of current technologies to design, manufacture and characterisation of a high-performance, 2k x 2k pixel Shortwave infrared detector array breadboard. Deliverables
Breadboard Application/Need Date
Earth observation imaging and spectroscopy instrumentation. TRL 6 by 2019. Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Optical Remote Passive Instruments - Detectors Roadmap Yes Roadmap (2011) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 14 of 112 Activity Description
1 - Earth Observation
1 - 02 - Optical Payloads Programme T117-502MM TD 17 Reference Activity Title
Particle Mitigation In High Power Laser Optics Objectives The objectives of this activity are to optimise the ion beam sputtering (IBS) process for high power optics coating by mitigating damage pre-cursors during coating growth and to validate the optimised coating deposition method by damage testing and multispectral confocal microscopy. Description Many scientific publications and experimental findings identify nano-sized defects in optical coatings as initiator for laser- induced damage in the film. A defect originating from sample preparation and/or steps in the deposition process is being heated by the laser pulse. Because of the tiny dimension the induced local temperature increases easily, a plasma is formed and the film bursts in the vicinity of this particular defect.
The outcome of the experience of recent years is that nano-sized defects in laser coatings represent the most mission- challenging parts in space borne laser systems. There are two ways to approach this threat:
1) Careful and thorough investigations to find the most successful vendor to meet the high demands on the involved optics and developing a highly sensitive method to screen all optical components for the several models including the flight model. 2) Mitigating the defects already during the manufacturing process (this approach has not been evaluated).
The work shall be focused on the second approach for antireflective (AR) coatings, as these revealed the most challenges in the development process of the Aladin laser. Also the deposition time for AR coatings is much shorter which favours a thorough investigation as each sample preparation can take place in a reasonable time.
The laser mitigation shall be applied as a pre-deposition treatment for the polished substrates and also as an in-situ routine to work on the defects introduced during the coating layer growth. The success of the particle mitigation shall be monitored by observing the sub surface structure of the optics (~30um depth) by means of confocal microscopy after each step and laser damage threshold testing (LIDT). The LIDT and LIC (laser induced contamination) testing shall be used to estimate the TRL of the developed method. Deliverables
Technical notes + samples Application/Need Date EARTHCARE - TRL 6 in 2018
As this is an improvement of an already TRL 8 coating process, the step of raising the improved method from TRL 4-8 is expected to be without major issues Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Lidar Critical Subsystems (2010) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 15 of 112
1 - Earth Observation
1 - 02 - Optical Payloads Programme T117-503MM TD 17 Reference Activity Title
Control ASIC for Earth Observation Infrared Detector Array Objectives Design, manufacture and test an application specific integrated circuit (ASIC) to provide bias, clocks and video processing and digitisation for the latest generation of European infrared hybrid detector arrays. Description Hybrid infrared detector arrays combing a sensitive diode layer bonded to a CMOS readout circuit are baselined for many current and upcoming Earth Observation missions.
This activity aims to develop a breadboard, using a custom ASIC, capable of providing the necessary clocks and bias voltages to operate the detector as well as providing 4-channel video processing and digitisation, leading to a two-chip (Control ASIC + hyrbid detector) detection system.
The design will be split to allow separate or combined use of bias and clock generation and video processing and digitization functions. Deliverables
Breadboard Application/Need Date
TRL 5 2018. Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Optical Remote Passive Instruments - Detectors Roadmap Yes Roadmap (2011) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 16 of 112 Activity Description
1 - Earth Observation
1 - 02 - Optical Payloads Programme T117-504MM TD 17 Reference Activity Title
Multi-kHz, multi-beam single photon counting vegetation LiDAR Objectives The proposed activity is targeting the development of technologies for a spaceborne multi-beam vegetation LiDAR based on multi-kHz single photon counting (SPC) as an alternative to low-repetition-rate SPC or full waveform retrieval. Description Based on the findings of the previous GSP study 'Laser Altimeter for Earth Observation and Planetary Exploration' the ALART activity has been set up to breadboard and test a multi-beam, multi-kHz SPC LiDAR concept and the related technologies for future Earth Observation laser altimetry missions. During this activity, the basic concept of a multi-kHz single photon counting LiDAR instrument with multiple beams has been established and is being experimentally validated on reduced performance level. The focus is on the global measurement of canopy coverage and properties. In a first demonstration of feasibility, the instrument concept is restricted - for practical reasons - to the use of 3 beams with reduced footprint size at a wavelength of 532nm. The triple beam is generated by splitting the output of a single laser. The envisaged enhancement of measuring capabilities and optimisation of the instrument concept for application in a space mission comprises the investigation of using an alternative, high-power laser source in the 750-800nm wavelength range of largest vegetation albedo and the option of wavelength tuning / multi-wavelength operation in order to measure specific canopy properties. In that context the activity is linked to and will be coordinated with the development of alexandrite laser technology as undertaken in the on-going TRP activity 'Diode-pumped alexandrite laser development for spaceborne LiDAR applications' and its follow-on 'High-energy diode pumped Alexandrite laser development'. With more laser power (and potentially higher pulse repetition rates) available an increase of the number of beams and larger footprints can be targeted. The best performing schemes for the generation of a large number of beams, e.g. by diffraction or by use of MOEMs, can be traded off. Furthermore, increasing the single photon array detector size and number of pixels will be targeted. The ALART activity foresees the basic validation of the instrument concept and final breadboard by measuring canopy (tree) properties from an elevated platform above a dedicated forestall research site in the Netherlands. The representativeness of these tests for the intended spaceborne use is limited due to the comparably small height of the platform (few meters above tree top) and short ranges that can be realised under such circumstances. In order to be able to validate the measurement concept under more realistic conditions this activity shall retain the option to perform an airborne measurement campaign over areas with various types of canopy. The findings of the campaign shall be used to iterate the design of the LiDAR instrument, optimising its performance parameters and the algorithms for data retrieval. Deliverables Other: Upgraded ALART breadboard with enhanced performance, sub-system technology trade-off, performance validation in the field, optimised algorithms for data retrieval Application/Need Date TRL 6 by 2019, responding to canopy LiDAR missions proposed in previous EE7, EE8 (e.g. multispectral canopy LiDAR), technology requirements for future EE9 Duration Current Target 24 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Lidar Critical Subsystems (2010) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 17 of 112
1 - Earth Observation
1 - 02 - Optical Payloads Programme T123-501QT TD 23 Reference Activity Title
Microlenses deposition for backside-illuminated imagers Objectives This activity aims to define the Micro lenses technology and processes and to validate their enhancement of the Back- illuminated CMOS Image Sensors. Description Micro lenses are today widely used within consumer imaging products, not only in order to compensate for non 100% fill factor but also in view of improving MTF (e.g. for back side illuminated devices). Such microlenses are manufactured within the standard flow of CIS foundries. They are mainly directed at pixel pitch in the 1-5 µm range and are unable to efficiently address the usual space applications pitch range- about 5 to 100 µm-, while there is a need for such devices for performance improvements (fill factor, MTF, Parasitic Light Sensitivity, etc.). This proposal addresses specifically Back-illuminated CIS.
The first step of this study is to review the existing European processes dedicated to microlenses deposition on backside illuminated image sensors, in terms of technological capabilities (pitch, available geometry), performances (dead zone/fill factor, transmission, deposition accuracy, uniformity etc.) and space qualification. Based on the selection of the most appropriate process, the second part of the study will consist the procurement of back-illuminated CMOS image sensor wafers, with the intention to deposit microlenses on. The final product will be subjected to a first space assessment, followed by a space evaluation campaign based on the ESCC 9020.
In short, the tasks included in this activity are: - To review existing European processes dedicated to microlenses deposition. - To review and consolidate requirement Specification and Components Production Process Identification as well as reliability analysis. - To draft an Evaluation Test Plan (ETP). - To plan and procure a selected CMOS image sensor that will be used to evaluate the microlens technology chosen. - To design, manufacture/deposit microlenses on a CIS. - To perform a test campaign to evaluate mcrolenses and their enhancement of the CIS based on the ETP plan. Deliverables
Engineering Model Application/Need Date
This covers mainly Earth Observation and science /required by 2017-18 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Technologies for Optical Remote Passive Roadmap No Roadmap Instruments - Detectors (2011) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 18 of 112 Activity Description
1 - Earth Observation
1 - 03 - Platforms / Others Programme T105-501EC TD 05 Reference Activity Title High accuracy image stabilization system for GEO High Resolution Missions - Preliminary design and performance assessment Objectives The objectives of the study are to perform the architectural design of the image stabilization system, including the accommodation aspects and the interfaces with the host platform, a preliminary performance assessment and recommendations for future work. Description In the conventional system approach, image stability requirements are met constraining the platform and instrument to a very quiet thermo-mechanical environment. This is achieved mainly by active and/or passive isolation systems present at source and/or at receiver level, or using low-noise actuator solutions like micro-propulsion. In this precursor study, the image stability will be achieved by a line-of-sight stabilization concept based on a tilt/tip mirror located inside the instrument. Such pointing concept has been successfully implemented in Europe in the special case of small Laser Communication Terminals with Artemis SILEX and EDRS LCT but also more recently in US within the Optical instruments of SDO (Solar Dynamics Observatory) and GOES-R (Geostationary Operational Environmental Satellite-R series). One benefit provided by such a stabilization system is the increased decoupling from the dynamic disturbances created by the platform and other noisy instruments. Another benefit is the simplification of the platform and AOCS design. GEO-HR is a very interesting application with stringent line-of-sight stability requirements (e.g. Relative Pointing Error of 5-10 mas over 10-20 msec) and can serve as a reference mission due to the availability of a preliminary GEO-HR telescope design which will provide valuable inputs to this study. It is envisaged to extend the use of this concept on future Earth Observation or Science missions with different sets of performance requirements (e.g. stability over longer time intervals of few seconds). The main tasks of this activity shall cover: a) the accommodation of the image stabilization system in the GEO-HR telescope; b) the architectural design of the image stabilization system including the use of real-time payload measurement and additional high frequency sensors, the analysis of the sensitivity functions for the controllers and sampling frequency, the selection and sizing of the mirror tilt-tip mechanism actuator (e.g. piezoelectric actuators) and the possible integration and synergies with AOCS (e.g. equipment/information sharing, feed-forwards). As a starting point for the definition of line-of-sight displacements to be compensated by the stabilization system, a platform with a classical low cost AOCS (i.e. based on reaction wheel without active/passive damping) will be considered. Redundancy needs and FDIR aspects shall be taken into account in the proposed architecture as well; c) the development of a high-fidelity simulator to address the architectural design aspects, the controller synthesis and to perform preliminary performance assessment (e.g. image quality, pointing errors, and including additional torque/force exchanged by the tilt/tip mirror actuators with the payload structure); d) the requirement breakdown and justification; e) conclusions and recommendations for future work Deliverables
Other: Study report with mathematical models, s/w simulator and tools. Application/Need Date
GEO-HR, Earth observation missions, meteorogical satellite / 2020 Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap AOCS Sensors and Actuators (2009) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 19 of 112
1 - Earth Observation
1 - 03 - Platforms / Others Programme T109-501GD TD 09 Reference Activity Title
File based operations for EO missions Objectives
The objective of this activity is to analyse the feasibility of file based operations for future EO missions. Description Many Earth Observation (EO) missions have payloads generating a very high quantity of data. Payload and ancillary data (e.g. Navigation Data, Housekeeping telemetry) are stored on-board in the solid state mass memories in the form of CCSDS Space Packets. The mass memory is organised in multiple packet stores each dedicated to a specific type of telemetry (based on the CCSDS Virtual Channel and other characteristics) and handled as a circular buffer. To cope with timeliness requirements, it is important to ensure that at the end of each data downlink over a ground station all the needed payload and ancillary information are available on ground. For EO missions, this very complicated low level managing of the end-to-end downlink is reaching its limits with the frequent requests for a flexible mission planning approach capable of dealing with last minute urgent requests, for example for disaster recovery purposes. Such requirements on flexibility together with the mixture of both urgent and routing data is unique to EO missions and require the introduction of better protocols and operations concepts. The move to higher downlink frequencies (K-band) will increased the need for rapid retransmission capabilities due to decreased link reliability in higher frequency bands. This will also drive the need for more complicated end-to-end protocols to manage the data downlink. The Euclid mission has already realised this, and adopted the CCSDS File Delivery Protocol (CFDP) for their usage. However, due to unique aspects of EO missions, the solution from Euclid cannot be directly applied and until now, no effort has been made to verify if this protocol (CFDP) could be effectively used for this type of missions and satisfying the data processing and timeliness constraints outlined above. Preliminary investigation have been done to extend this approach from payload data to monitoring and control (M&C) domain related to TC and TM, but results were not satisfactory in relation to the performance. Once a suitable concept for using the CFDP protocol for the payload data management, then these preliminary investigations need to be revisited to check if a consistent overall mission concept can be found covering both monitoring and control as well as payload data handling. The activity consists in the following tasks: - analyse current operational concepts for payload data management and downlink for high volume EO Missions - build a catalogue of scenarios/requirements/needs/use cases - analyse the unique features of EO missions and derive an optimal tuning of the CFDP protocol for EO purposes. - define a architecture and operation logic that would demonstrate the benefits of using CFDP - build a simulation data flow prototype to test the approaches for the various scenarios/requirements taking into account typical EO polar orbit mission. - characterise the performance in term of throughput, latency and timeliness for these approaches - identify the modification needed on-board and on-ground to support the proposed approach - identify if/how a file based approach would be equally suited to M&C as for payload data It is required to look at the end-to-end aspects hence involving as well the on-board design. Deliverables
Prototype Application/Need Date
All future EO missions would benefit. Need date: TRL-5 by 2017 Duration Current Target 12 3 4 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 20 of 112 Activity Description
1 - Earth Observation
1 - 03 - Platforms / Others Programme T112-501GS TD 12 Reference Activity Title
Enhanced Antenna Tracking receiver for use within the 26 GHz K-band frequency allocation. Objectives The objective is to develop a tracking receiver compliant with the 26 GHz communications requirements. The activity is mainly focused on but not limited to the narrow beamwidth of the antenna, large bandwidth of the received signal, low energy density near the central frequency, and use of suppressed carrier modulation and the criticality of the phase alignment due to the very high frequency involved. Description Earth Observation (EO) missions will start to use soon the 26 GHz. The higher speed downlink at 26 GHz enables to avoid the downlink bottleneck. When the satellite is using isoflux antennas to download the payload data, the antennas in the Ground Station (GS) need to be big (e.g. 13 m diameter, in order to cope with the reduced link budget. The GS antenna beamwidth will then be very narrow. The use of advanced coding schemes (like VCM and SCCC) facilitates the needed ultra-high downlink data rates, but the price is the very low energy density, that makes it difficult to track the satellite using the standard non- coherent monopulse antenna tracking receivers. Moreover, the very narrow antenna beamwidth of the 26 GHz band reception antennas, that are required, makes the tracking of the fast LEO satellites even more difficult. At low elevation angles, the characteristics of the 26 GHz band signal are particularly hard to track by the monopulse receiver due to the propagation particularities of this band (high atmospheric attenuation and scintillation), but also for the fast dynamics. A significant percentage of the LEO passes, the satellite signal is received in low elevation angles. A monopulse enhanced antenna tracking receiver (eATRK) is required, that is able to extract the required information to control the antenna pointing, from the downlink signal received at the 26 GHz band stations antennas with monopulse feeds. The activity shall define the best structure and algorithms that are required for the eATRK. It shall first analyse the characteristics of the downlink signal received from the LEO satellites at 26 GHz, in order to produce the more efficient architecture. An eATRK shall be designed (with the selected structure and algorithms) and the critical technologies will be breadboarded. The activity is split in two phases. In phase 1: - the downlink signal characteristics will be analysed, and some algorithms and architectures for the eATRK will be proposed. - One architecture will be selected after intensive modelling and simulation. - A preliminary design of the eATRK prototype will be produced. In phase 2: - eATRk prototype will be designed, and the critical technologies will be breadboarded Follow-on GSTP activity will bring the designed eATRK to the operational TRL level. Deliverables
Other: Documentation and breadboard of critical technologies Application/Need Date
26 GHz missions / MTG / Sentinel 3 / EPS-SG / 2018 Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Ground Station Technology (2015) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 21 of 112
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies Programme T402-501SW TD 02 Reference Activity Title
Preliminary Design and Development of an Avionics prototype for Nano and Micro-Launchers Objectives The objective of this activity is to provide an Avionics prototype (SW and GNC aspects) usable in nano-launchers / micro-launchers / sounding rockets and to create a reference implementation to cope with modern and versatile Guidance, Navigation, and Control (GNC), data handling and software systems for micro-launchers. Description With regards to the Avionics aspects, the activity will investigate the use of - COTS processors boards (probably ARM based). Radiation hardening is probably not an issue due to short mission duration. - COTS sensors (GPS, MEMS gyro & accelerometer), probably integrated on the processor board - fast communication buses: e.g. ethernet, TTEthernet, SpW. Study applicability of wireless - COTS satellite communication services (e.g. Iridium) for transfer of telemetry to ground. Explore the use of COTS phone services for transfer of the data in the very early stages of flight and in the last stages of recovery - geolocalization for retrieving of launcher/payload experiment (when applicable) Concerning software and Guidance, Navigation and Control aspects, the activity shall: - investigate the use of modern GNC design technologies (mu, H-Infinity structured, LPV, model based predictive control) - modelise and use advanced sensor fusion (GPS+MEMS) - explore the use of partitioning kernels - develop the concept of Integrated Modular Avionics concept: the use of a COTS OBC with partitioning allows to migrate application logic from the sensors and actuators to OBC partitions. - promote the extensive use of model based design (e.g. with Matlab/Simulink, TASTE or other modern tools) and autocoding techniques
Key general aspects of the studied technologies shall be: - Scalability: e.g. ethernet can be scaled to TTEthernet for use in future Launchers - Trade-off cost efficiency versus reliability and more generally Product Assurance requirements
The work logic can be organized in 3 tasks: 1) Study of options for Avionics and GNC/SW: explore new technologies, assess their maturity and select the promising ones to be investigated further, 2) Design and development of the GNC & SW prototype representative of at least of the Guidance, Navigation, Flight Management and Control. The GNC&SW prototype must be able to run in real time and communicate with the selected sensors/actuators using a real communication bus 3) Test of the GNC&SW prototype on an existing test bed: Deliverables
GNC&SW Prototype Application/Need Date
TRL 3 by 2017 Duration Current Target 12 1 2 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 22 of 112 Activity Description
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies Programme T405-502EC TD 05 Reference Activity Title
Adaptive Flight Guidance and Control Systems with Reconfiguration Objectives The objectives are: 1) To reduce the GNC mission specific complexity by means of a better GNC design using robust and adaptive augmentation GNC system as well to reduce V&V effort by using novel and efficient worst cases analysis methods; 2) Provide a responsive launch capability by means of robust and adaptive GNC to flight environment; 3) Provide and increase launcher reliability in degraded conditions as well in case of unaccounted mission changes. Extend the safety margins by reducing stage re-entry dispersion corridor while maximizing the fault tolerance. 4) Provide a high launcher performance and optimized control effort while increasing the accuracy of the injection and payload delivery; 5) Design verifiable algorithms by providing associated formal verification methods. Description The current launcher missionisation process is costly and needs to be improved. For every launch substantial GNC mission preparation tasks are necessary due to lack of robustness and mission coverage of the qualified GNC flight software. The GNC parameters need to be re-adapted for each flight via a complete GNC re-design loop. This involves also a complete validation and verification loop. Costly and detailed test campaigns need to be re-performed in order to demonstrate compliance of the full set of GNC requirements. The following tasks are foreseen: - Critical review of GNC mission preparation process with the detailed analysis of the Guidance, TVC control, ACS readiness review process to assess for each discipline where limitations need to be revised and overcome. Parameterisation of pre-design mission data shall be performed in order to derive extended model representations that permit full mission coverage. This includes the generation of explicit uncertainty models and model adaptation strategies. - Detailed trade-off analyses for the development of adaptive augmenting flight guidance and control architectures shall be performed. Adaptive augmentation layers shall be structured at each independent auto-pilot function in order to systematically cope with mismatch corrections (e.g. flex mode filters, load attenuator, drift-mode channel, trajectory tracking loop). Model mismatch determination shall rely on estimation and identification functions providing online deviations in the manipulated variables that trigger the adaptation layer. - Development of a full novel adaptive guidance and control architecture that minimises the missionisation and V&V activities. - Development of a second augmenting adaptive architecture, that increments and keeps traditional inner layer structures intact. - Full design of augmented adaptive flight control laws. - Definition of enhanced V&V verification strategies for adaptive flight control laws. This shall include the application of analytic and simulation based strategies. V&V efficiency and coverage shall be demonstrated - Implementation of full adaptive and minimum adaptive augmenting architectures in full 6 dof simulators. Guidance and Trajectory Performance and Safety, Attitude Control Performance & Robustness, Extreme Loads and Failure cases shall be assessed for the full set launcher missions. - Assessment of the intended missionisation improvements of the activity with comparisation in the case of the 3 GNC strategies (1 traditional, 2 adaptive augmented) and quantitative evaluation with respect to the activity objectives. - Critical analysis and recommendations towards industrialisation. Deliverables Other: Technical Note, Simulator, Guidance & Control SW, V&V Analysis SW Application/Need Date Urgent to reduce the huge missionisation effort of launchers (5 teams at ESA, Industry, CNES, ASI, etc.) Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 23 of 112
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies Programme T418-502MP TD 18 Reference Activity Title
Alumina particulate characterization in flight Objectives The objective of the present activity is to conduct a flight test to obtain an accurate characterisation of the alumina particulate size distribution and chemical concentrations through the plume of an ESA launcher.. Description ESA have begun to respond to public and industrial concern and is pursuing activities with the goal of understanding its environmental impact. Scientific studies indicate that launchers will be the major cause of ozone depletion since the application of the Montreal Protocol to ban Ozone Depleting Substances is world-wide applied. One such activity is the GSP: Atmospheric impact of launcher plumes whose goal was to quantify the impact of ESA plumes on the atmosphere using plume and climate models. This activity highlighted that the largest uncertainty with respect to launcher plume depletion of ozone is due to the large uncertainty in the size distribution of alumina particulate within the plume. Alumina participates in heterogeneous reactions in the atmosphere that results in a net loss of alumina. However the scale of the ozone depletion depends on the resident time of the alumina in the atmosphere and the surface area of the alumina that is available for reaction. Both residence time and surface area of alumina are proportional to the size of the particulate. There is an order of magnitude difference between the global ozone loss due to alumina based on different assumptions on size distribution. The current assumptions on the alumina size distributions are based on flight measurements conducted by the Americans in the 1990s. However the engines differ, as do the fuels types and mixtures ratios, the motor configuration (single/multiple) and the upper stage launch vehicle (the aerodynamics of which will change the flow around the rocket). The flight test here proposed will be conducted for the ESA launcher in a similar manner to that of the American tests. The test itself will require that the aircraft traverse the plume of a launcher some 5-10 minutes after launch. This will imply a close cooperation between the project team, Arianespace, ESA and CNES. At this point, ESA and CNES have discussed the logistics of such a flight and a preliminary authorisation for the flight has been given. The activity should take 24 months to include the planning, authorisation, flight test and exploitation of the data. The proposal covers the costs of the science payload, operations at French Guiana and the exploitation of the data. It is foreseen that the costs associated with the aircraft will be covered through cooperation with CNES who have access to a Falcon research aircraft through the Safire cooperation. Potentially, both the Vega and Ariane 5 plumes could be sampled during the campaign assuming that there were two suitable launch scenarios separated close in time. Deliverables
Study Report Application/Need Date
Launcher environmental impact Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Aerothermodynamic Tools (2012) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 24 of 112 Activity Description
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies Programme T420-501MS TD 20 Reference Activity Title
Launch Sound Level Reduction Objectives This activity aims to study the noise reduction methods on the launcher fairing and launch pad during ignition and lift-off, to determine the launcher-spacecraft coupled vibroacoustic response to external sources in order to demonstrate the efficiency of the identified noise mitigation methods. Description The vibro-acoustic environment is the sizing load case for random vibration response of spacecraft secondary structures and sensitive equipment, including antennas and solar arrays. It is often the case that the structural strength of light- weight structures is driven by the vibro-acoustic dynamic response. Even if there has been significant progress in analytical and numerical prediction tools, there is still a large uncertainty on the structural response predictions associated to the knowledge of the propagation paths, the noise sources and the coupling of the spacecraft to the launcher fairing and the air cavity.
Furthermore, recent studies have shown that simple modifications of the ground facility can result in significant noise reduction during ignition and lift-off, by controlling the scattering of waves on the ground facilities and the sound diffusion thereof. Advances in the so-called sonic crystals are showing encouraging results.
The study will include the following main tasks: - Full frequency range characterisation and validation of spacecraft-launcher coupled vibroacoustic response prediction. Low-mid-high frequency methods shall be traded off and evaluated, including deterministic, statistical and hybrid analysis methods. - Sound source and propagation path characterisation during ignition and lift-off. Time and frequency domain, steady and transient loads shall be analysed from flight data. - Noise reduction methods on the launch pad, including scattering and absorption of ground, sound barriers, sonic crystals, water deluge, modifications of launch tower. - Noise reduction methods for the launch fairing, absorption in the cavity and sound effects mitigation on the spacecraft. Deliverables
Other: analysis report, breadboard testing Application/Need Date
All spacecraft and missions, launcher and ground facilities. Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 25 of 112
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies Programme T421-501MT TD 21 Reference Activity Title
Polyimide Cryogenic Lines for Launcher Propulsion Systems Objectives The objective of this activity is to identify and demonstrate improvements of existing concepts for the NGL (Next Generation Launcher) feed-line elements, using fibre-reinforced polyimide materials and building on results from previous activities, notably FLPP. The scope is to establish improvements within given constraints in terms of performance, envelopes, interfaces and environmental loads. Description ESA has been working many years on new materials and technologies for fluid lines for launchers. Within the frame of the Future Launcher Preparatory Programme (FLPP)P-2.1, between 2010 and 2013, the focus was on maturing the technology for a CFRP feed line with a metallic liner (aluminium or stainless steel), as a light-weight alternative to the A5 stainless steel-based design. However, the breadboard test programme was interrupted due to issues with delamination and insufficient liner bonding. While ways to overcome the difficulties were identified and tested, it was decided in FLPP-2.2 to change the approach. Instead, in the first phase of FLPP-2.2, in 2013 and 2014, Magna Steyr investigated in parallel the use of aluminium alloys and polyimide as new technologies for propellant feed lines. The outcome was that, while polyimide showed much potential, FLPP and Magna Steyr decided to focus on aluminium, considering that it is currently at a higher TRL, meaning that it is deemed to fit better with upcoming programmatic decisions on NGL development.
In comparison, the maturity of the polyimide technology is less advanced and was judged to form a next step beyond metallic materials. In Evaluation and Selection of Fibre Reinforced Polyimide Materials for Feed Lines, FLP22-MSE-TN- 06, a detailed assessment of polyimide materials has been performed. According to this investigation, polyimide promises a weight saving potential of approximately 50% compared to stainless steel. An important aspect in design of polyimide propellant lines is, that the compensator elements required to allow certain relative movement of each line segment can possibly be omitted due to the properties of polyimide. This promises fewer components and therefore significantly lower weight and costs compared to the current stainless steel design, but also compared to an aluminum design. It has been the reason to recommend a continued effort on polyimide feed-line technology maturation, which is reflected in the conclusion that has been documented for FLPP. The paramount target is to identify potentials for mass savings and cost reduction by replacing technology used in current European launchers with a design based on validated new technology, whilst preserving reliability.
The activity entails: a) Consolidation of a material data base for fibre-reinforced polyimide for material selection, supported, as required, by material characterisation tests b) Evaluation and validation of manufacturing processes, including manufacturing trials of breadboard hardware c) Design and analysis of propellant feed-line segment, with test results as input for correlation of analytical predictions Deliverables
Breadboard Application/Need Date
Enhancement of future launchers, A6+ or other parallel developments Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Chemical Propulsion - Upper Stage Propulsion Roadmap Yes Roadmap (2003) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 26 of 112 Activity Description
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies Programme T423-501QT TD 23 Reference Activity Title
Supercapacitor for Launcher applications Objectives This activity aims to propose supercapacitors compliant to launcher requirements to replace obsolete technology and/or to achieve mass reduction. Description Supercapacitors (also called ultracapacitors or electrochemical double layer capacitors) are suitable for high power applications (but requiring low energy). These devices are now available on terrestrial market and used in aeronautics (Airbus A380 emergency door opening), in automotive industry. Supercapacitors rely upon the capacity of the electrochemical double layer between an electrolyte and an electrode. The energy stored (5 Wh/kg) is low compared to batteries, but can offer much greater specific power up to 20 kW/kg. The commercial interest of the supercapacitor component is placed at the crossroads between capacitors and Li-Ion batteries, with a balance between the specific energy and specific power, for various possible applications. New supercapacitor technologies, e.g. using ionic liquids instead of organic solvent, are under development. Such new supercapacitors can offer a greater specific energy (> 20 Wh/kg compared to 5 Wh/kg for organic supercapacitor) while preserving high specific power properties. Such devices are of interest for launcher applications. The currently identified markets are mostly actuator and pyrotechnic systems for launchers, and electrical propulsion. Launcher pyrotechnic functions: High power lithium cells or hybrid architecture with supercapacitors of few farads up to 10F will be needed to replace obsolete NiCd batteries for the nominal pyrotechnics lines Developments of supercapacitors up to a few hundred farads are of prime interest for launchers as their use within a hybrid power supply could lead to a drastic gain in mass for the Electro-Mechanical Thrust Vector actuation system (EMTVAS). Combination of secondary batteries and supercapacitors are also foreseen for future launchers to replace primary batteries The activity is envisaged with the following steps: - Survey of existing technologies and selection for intended launcher applications - Development and test of supercapacitor component - Development of adequate packaging in accordance with launcher requirements - Supercapacitor bank will be designed, manufactured and tested Deliverables
Engineering Model Application/Need Date
To be used as soon as the technology is available with relevant TRL. Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Electrochemical Energy Storage (2010) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 27 of 112
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers Oriented Technologies Programme T424-501QT TD 24 Reference Activity Title
Particle modelling inside fairings during pre-launch and launch Objectives The objective of this activity is to develop a modelling technique and tool to predict particulate fall-out inside fairings prior to launch and during launch. For the pre-launch phase, the main goal is to predict the motion of particles inside fairings under ventilation with payloads integrated.. Description For spacecraft systems and subsystems, particulate contamination can cause a number of problems such as obscuration, absorption and emittance changes, scatter from optics, noise on electrical contacts and short circuits. It is therefore required that particulate contamination is controlled under maximum allowable levels, which are derived from performance-loss and failure-preventions analyses. Typically, during the design phase, prediction budgets are established and are maintained until launch as part of the contamination control activities. The prediction budgets are preliminary built on assumptions derived from the experience gained on past projects. The prediction budgets are then consolidated with measurements performed in the controlled environment of the actual AIT. In many cases, the major uncertainty of the particulate predictions are those related to the pre-launch and launch environments. In these specific cases, particle fallout is difficult if not impossible to measure, with the current available techniques, and therefore the experience on which predictions budgets can be build is very poor. However, S/C projects are requesting more and more this uncertainty to be resolved, as the verification of maximum acceptable contamination levels and the implementation of design control measures can only be supported by reliable predictable budgets, which today contain a big question mark for the launcher contribution. The objective of the proposed activity is to develop a modelling technique and tool to predict particulate fall-out inside fairings prior to launch and during launch, and to perform related tests aiming at determining the necessary inputs and at correlating the modelling. For the pre-launch phase, the main goal is to predict the motion of particles inside fairings under ventilation with payloads integrated; this should take into account the geometry of the fairing including the position of ventilation inlets and outlets, the geometry of the payload, ventilation flow-rate, ventilation gas purity. For the launch phase, the main goals are to predict the behaviour of particles present onto internal fairing's surfaces, including the Payload and its interfaces to the fairing, when subjected to the loads of the launch, and to predict their motion and the motion of particles in the gas volume present inside the fairing prior to launch, during and after launch. This should consider the above parameters, valid for the pre-launch phase, mechanisms of particles' detachment from different surfaces, and the transition from viscous to molecular regimes. In particular, testing is expected for determining/confirming the mechanisms of particles' detachment, and more in general, for the validation of the whole modelling technique/tool. Finally, it is also expected that the modelling tool will provide the capability to assess and optimise alternatives to existing fairings' configurations, e.g. by modifying venting paths, aiming at mitigating the risks associated to particulate contamination. Deliverables Other: Study report and modelling tool - The modelling tool can be developed from scratch or be based on existing software, preferably open source Application/Need Date
TRL 3 by 2019
Duration Current Target Open source 24 1 3 SW Clause (Months) TRL TRL code Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 28 of 112 Activity Description
4 - Space Transportation & Re-entry Technologies
4 - 03 - Generic Space Transportation Technologies Programme T420-502MS TD 20 Reference Activity Title
Full Trajectory Structural Load Determination for Reusable Space Vehicles Objectives This activity aims to provide the load analysis of a winged space vehicle with sharp leading edges, including the quasi- static loads definition for all phases of flight and the dynamic characterisation by modal analysis. Description Reusable space vehicles with sharp edges are structurally behaving completely different to expendable launch vehicles. The aero-thermal loads are different due to a prolonged gliding phase in the atmosphere.
For an existing structural layout including control surfaces and support structures the load case analysis shall be done. The loads shall be analysed considering the flight phases: launch (lift-off, ballistic flight, fairing ejection, separation), ascent, re-entry, vehicle parts ejection, pull-up, glide. Local design due to interaction with CMC components is not part of this study, but interface loads have to be generated.
A trimmed aerodynamic & thermal database will be provided along the trajectory, including margins, as an input. The following tasks shall be performed: 1. Specification and generation of reduced FEM-model for load analysis, including interfaces to the launch vehicle 2. Definition of structural loads based upon flight profile, flight mechanics and launch vehicle loads inputs 3. Preliminary definition of test specifications 4. Conclusions and recommendations to the vehicle design authority Deliverables
Study Report Application/Need Date
Reusable vehicles. TRL 6 by 2025 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 29 of 112
4 - Space Transportation & Re-entry Technologies
4 - 04 - Re-Entry Technologies Programme T405-501EC TD 05 Reference Activity Title
Hypersonic Authority Determination and Control for Aerodynamically Slender Vehicles Objectives The objectives of this activity are twofold: 1) The definition of GNC system (including sensors and actuators) requirements, the GNC design and development and the testing of the GNC system and its robustness analysis for HEXAFLY-INT 2) Develop the methodologies and tools for performing flying qualities assessment of hypersonic slender vehicles (HEXAFLY-INT) Description The activity is proposed in the frame of the HEXAFLY activity whose roadmap has been established already by the HEXAFLY-INT EU FP7 program.
The following tasks are foreseen: - Perform flying qualities analysis for an slender vehicle (HEXAFLY-INT). Identify the Centre of Gravity (CoG) location and generate the control surface requirements for trimmability and stability of the vehicle, defining the Angle of Attack (AoA) corridor for a typical re-entry, pull-out and gliding trajectory. For this analysis take into consideration atmospheric, MCI and aerodynamic dispersions, as well as nominal and off-nominal trajectories. -Derive the GNC system requirements (including sensors and actuators) based on the flying qualities analysis of previous task. - Design a robust GNC system for all the parts of the trajectory: re-entry, pull-up and gliding, down to Mach 2 capable of withstand all expected perturbations during flight. - Establish the performance evaluation of the GNC design by means of Monte-Carlo and Worst Case Analysis with 6 DoF simulations - Establish the synthesis and recommendations. Present a summary of the results obtained and conclude with proposal for follow-on tasks to raise to TRL 6 Deliverables
Study Report Application/Need Date Re-usable vehicles TRL 6 in 2025 Duration Current Target 30 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Aerothermodynamic Tools (2012) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 30 of 112 Activity Description
4 - Space Transportation & Re-entry Technologies
4 - 04 - Re-Entry Technologies Programme T418-501MP TD 18 Reference Activity Title
Influence of Leading Edge Imperfection on Boundary Layer State of a Volumetric Waverider Configuration Objectives This activity aims to characterize the effect of imperfections in the leading edge components (steps, gaps) and the degradation of the nominally sharp leading edges due to high thermal loads resulting into premature boundary layer transition. Description The activity shall include the following tasks : - Model design for utilization in a high enthalpy tunnel. The model shall be a scale down of a representative forebody. The leading edge will be set up with exchangeable parts such that leading edges with different shapes can be used. - The flow field past the scaled experimental flight test vehicle (EFTV) fore body will be computed for selected wind tunnel test conditions using Computational Fluid Dynamics (CFD) to support the wind tunnel testing preparation and the design of the leading edge inserts. -The test campaigns shall first focus on the characterization of the boundary layer state and identification of the transition mechanism past the nominally perfect leading edge. The data obtained in these tests will serve as reference case. Flush mounted thermocouples, fast response pressure transducers and optical measurement techniques such as temperature sensitive paint, or schlieren will be applied. Subsequently, the experiments shall focus on the investigation of the influence of leading edge imperfection on the state of the boundary layer. Deliverables
Study Report Application/Need Date Reusable vehicles TRL 6 by 2020 Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Aerothermodynamic Tools (2012) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 31 of 112
4 - Space Transportation & Re-entry Technologies
4 - 04 - Re-Entry Technologies Programme T418-507MP TD 18 Reference Activity Title
Determination of an In-Flight Measurement System for the characterization of reusable vehicles. Objectives This activity aims to develop an In-Flight Measurement System which is capable to assess a High-Performance Glider including the Impact on Wing LE and Ailerons Design Description The in-flight measurement system for re-usable vehicles needs adaptation with respect to a launcher or re-entry vehicle due to the vehicle's prolonged time in the atmosphere. The heat fluxes and loads have a completely different profile. In addition, the thermally loaded slender components such as control surfaces and leading-edges is a particular challenge for the instrumentation layout, as the available space is limited and they are exposed to high aero-thermal loads. Starting from an existing design, a re-assessment of the instrumentation units, sensors, cameras, harnessing shall be performed: it entails the overall layout of the instrumentation, sensors and Data Acquisition System (DAQ) which collects the data stream of each of the sensors and subsystems. The necessary implementation and interface requirements shall be considered the configuration/integration for instrumentation, sensors, harnessing, data exchange including data handling file enabling proper trade-off of data rates, channel definition, sampling frequency, multiplexing. Envisaged sensors are (non-exhaustive): i. Pressure & flight data inside and outside the vehicle ii. Temperature for material panels, inside and outside the vehicle iii. Strain gauges in different components such as wing LE, ailerons, rudders iv. Data from IMU, flight control system, FADS v. Cameras The DAQ and signal processing will treat the analogue and digital data stemming from the scientific experiments along with the data handling and retrieval. Further, the design of slender components (LE, ailerons...) shall consider practical requirements wrt. integration, access and assembly. Particular attention shall hereby be addressed to the stiffness behaviour to confine elastic rotation/deformation under a maximum acceptable value (requirement on maximum elastic deflection) Deliverables
Other: study reports, breadboard, Application/Need Date Reusable vehicles TRL6 by 2025 Duration Current Target 30 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Aerothermodynamic Tools (2012) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 32 of 112 Activity Description
5 - Telecommunications
5 - 01 - System / Network / Protocols Programme T506-502ET TD 06 Reference Activity Title
Optimization of the Physical Layer Performance in High Data Rate Optical Links Objectives Design & optimize a physical layer (modulation, coding, interleaving) specification for high data rate optical communication links that: a) supports efficient data transfer of individual links to/from space, air, and ground users, b) supports also GEO based data relay architectures, where the optical relay serves as a transparent or regenerative link- layer bridge between User Platform and Ground Relay, c) provides variable data rates to support a wide variety of users and missions: The near term goal is few Mbps to several Gbps, but the data rates shall be scalable to support future high-rate (>10 Gbps) users. Description The Consultative Committee for Space Data Systems (CCSDS) Optical Working Group is currently addressing 3 main scenarios for high data rate optical links: i) High Data Rate scenario(Data Relay) ii) High Photon Efficiency (Deep Space) iii) Low Implementation Complexity scenario (LEO-to-ground). For each of these scenarios, a different physical layer is being envisaged due to the different mission, system and cost requirements. The high data rate scenario is the most complex scenario as it is required to support with the same specification a plethora of links from LEO or UAV to GEO or/and GEO to ground feeder links. Each of these links exhibits different channel characteristics and different practical limitations, taking into account the capabilities of the on board GEO processing. Therefore, an optimization of physical layer performance in High Data Rate optical communication links is required. The optimization shall address as a minimum: a) the channel coding b) the size of the interleaver and its interaction with the coding function c) the variability of the data rate to serve the multiple transmission profiles and users
The activity shall define the different system scenarios under the general class of data relay systems that shall be addressed by the physical layer design. This will be complemented by a state-of-the-art review in the optical communication literature, but also in the general erasure channel coding literature. Before deciding on the options that will be included in the physical layer design, the on board resources and capabilities of the satellite payload shall be considered, as the satellite payload architecture will drive the selection of the techniques to be implemented. In that respect, different options for the channel coding need to be considered whenever the coding layer is terminated on board the GEO satellite or on the ground station. After consolidating the frame of the physical layer design, a software simulator shall be developed and tested against known performances. The software simulator shall be employed to optimize the parameters of the high data rate optical link in different channel conditions (e.g. Additive White Gaussian Noise, micro-vibrations channel, strong/weak turbulence channel). Deliverables
Software Application/Need Date
2017 Duration Current Target 15 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 33 of 112
5 - Telecommunications
5 - 02 - Space Segment - Platform Programme T519-501MP TD 19 Reference Activity Title
Propulsion Pump Trade-off Objectives The purpose of this study is to evaluate the different concepts and identify the advantages for telecom bi-propellant systems. The study should trade-off component (pump types) as well as assessing the impact of the propulsion system as a whole. Description The current state of the art for bi-propellant propulsion systems employed by telecom spacecraft is to have a gas regulated system to maintain the propellant feed pressure in the propellant tanks for the Apogee engine burn. For on- station the pressure in the propellant tank is allowed to decay over life (aka blowdown) and thus the thruster propellant inlet pressure (and hence thruster performance) decays over time.
Recently a number of different pump concepts have been proposed to improve the performance of propulsion launcher systems. The idea is to investigate the potential of introducing pumps of this type to replace the gas pressurisation system to supply the correct propellant feed pressure to the thrusters. This would have two major advantages - Firstly to replace expensive and complicated equipment (i.e. gas regulators) as well as reducing the cost of propellants tanks as they would no longer be required to operate at a high pressure. The second advantage is that potentially the feed pressure can be maintained at a constant rate over the entire duration of the mission and thus eliminating the need for a blowdown mode and hence reduction in thruster performance over life.
The output of this activity would be as follows:
- Assess the current state of the art and proposed concepts of propulsion pumps - Assess the impact (pro's and con's) on the propulsion system of introducing pumps , the assessment should cover technical aspects/impacts to the propulsion subsystem well as other platform subsystems i.e. thermal, structural, electrical. In addition any cost impact should also be assessed. - Downselection to a new pump candidate technology. - Produce a technology, cost and schedule development roadmap for the downselected technology, Deliverables
Study Report Application/Need Date
TRL 6 by 2019 Duration Current Target 12 1 2 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Chemical Propulsion - Components (2012) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 34 of 112 Activity Description
5 - Telecommunications
5 - 02 - Space Segment - Platform Programme T521-501MT TD 21 Reference Activity Title
Variable Emissivity Radiator Breadboard Objectives The objective of this activity is to develop a radiator breadboard equipped with variable emissivity tiles. The thermochromic and electrochromic technologies will be investigated, traded-off, and a down selection made. The most promising technology shall be integrated on a radiator breadboard, and tested in a vacuum chamber. The stability of the coated tiles and of the breadboard under representative Utra Violet and radiation for GEO missions shall be evaluated. Description All telecommunications satellite radiators are typically covered with a low solar absorptance and a high infrared emittance coating. Because of the high emittance value, the satellite requires more power/battery for heating during eclipse. A tuneable infrared emittance coating can decrease it during an eclipse and can contribute indirectly to a reduction of the battery mass. A low absorptance coating minimises the solar heat load on the radiator and consequently its size and mass. As the actual radiator dimensions cannot be further increased, it is mandatory to manufacture coatings with a solar absorptance as small as possible tentatively <0.20 at End-of-Life (15 years for GEO).
The activity consists of the following tasks : 1) The study will start with a survey of the State-of-the-Art on thermochromic and electrochromic materials. The best thermochromic (TCH) and electrochromic (ECH) technologies shall be selected for manufacturing.
2) TCH and ECH samples shall be manufactured and submitted to particles and UV radiation tests. Their physical properties (electrical, thermal, ESD) shall be measured and compared to each other before and after the tests. The test results as well as the system aspects of using such technology shall be also be part of the trade-off. One technology shall be selected for the breadboarding of a satellite (reduced) radiator.
3) A breadboard radiator, equipped with TCH or ECH tiles, shall be designed and manufactured.
4) The breadboard radiator shall be tested in near real flight conditions. In necessary, the breadboard will be submitted to particles and UV radiation tests.
5) The thermal performance and adequacy of radiator breadboard shall be evaluated and its performance compared to the current (fixed emissivity) radiator technology. A Roadmap for the qualification of the selected technology (ECH or TCH) shall be prepared. Deliverables Other: ECH/TCH Tiles Selection and Testing, Breadboard Design Trade-Off and Manufacturing, Breadboard Test and Instrumentation Plan, Breadboard Thermal Test Predictions, Breadboard Thermal Test Results, Variable Emissivity Radiator Final Report, Thermochromic and Electrochromic Tiles Roadmap Application/Need Date
Telecom/Need Date 'TRL 3 by 2018'. Duration Current Target 24 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 35 of 112
5 - Telecommunications
5 - 03 - Space Segment - Payload Programme T506-501ET TD 06 Reference Activity Title
High Power W-Band TWT Objectives The objective of this activity is to develop a wideband slow wave structure suitable for high power TWTs operating at frequencies above 60 GHz for a new generation of high throughput telecom satellites. Simulation tools and manufacturing technologies will be investigated, traded-off and down selected. The most promising structure shall be integrated in a TWT breadboard and evaluated. Description The millimeter wave domain is also known as the extremely high-frequency (EHF) spectrum ranges from 30 to 300 GHz. Early works on atmospheric propagation in EHF evidenced encouraging future usage for satellite communications. The allocated W-band for satellite services (71-76 GHz and 81-86 GHz) seems to provide a favourable attenuation window related to oxygen absorption. The exploitation of W-band may offer many advantages for wireless communications, which make it suitable for satellite links, such as: broad bandwidths for high data rate information transfer (e.g. satellite feeder link or point-to-point communications, ISL), high directivity and spatial resolution, reduced transmission power (due to high antenna gain), low probability of interference/interception (due to narrow antenna beam widths), small antenna and equipment size, reduced size of satellite and launch vehicles. Currently no operative W-band satellite communication system has been developed. The W-band can certainly be considered as a frontier for space telecommunication applications. Hence the development of the high power devices for the final amplification stage is critical for the physical layer level design in order to manage the trade-off between power efficiency, spectral efficiency, and robustness against link distortions. The aim of this activity is to investigate on TWT slow wave structures capable of meeting RF power levels in the order of 50 W with 5% of fractional bandwidth, assessing the availability of enabling design tools. Moreover, it is necessary to perform an assessment on manufacture techniques to verify their suitability to the required dimensional tolerances in high vacuum applications. The activity consists of the following tasks: 1) Literature survey on the existing TWT performances and slow wave characteristics. 2) Design and manufacture suitable slow wave structures. 3) Perform cold test measurements. 4) Design and manufacture a breadboard to verify the achieved performances. 5) Final reporting, conclusions and roadmaps towards higher TRL Deliverables
Breadboard Application/Need Date
Broadband broadcasting services / TRL 4 by 2018 Duration Current Target 24 1 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Critical RF Payload Technologies (2004) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 36 of 112 Activity Description
5 - Telecommunications
5 - 03 - Space Segment - Payload Programme T507-502EE TD 07 Reference Activity Title
Dual-Band Polarizing Surfaces for Single Feed per Beam broadband Antennas Objectives The objective of this activity is to investigate innovative dual-band polarizing surfaces to enable high-performance multiple beam antenna based on a single-feed-per-beam concept using only two main reflectors for the full transmit/receive mission. A demonstrator of the most promising configuration shall be manufactured and tested. Description Several past developments related to reflector and feed systems have led to very efficient multiple beam antenna designs for broadband satellite missions based on a single-feed-per-beam configuration which provide high gain, low side lobe level and excellent carrier over interferers (C/I) ratio. This configuration is the current operational state-of-the- art. Its main drawback is that it requires 3 to 4 main reflector apertures thus leaving no or little space for additional missions on board of the satellite. Alternatives based on over-sized reflector designs or multiple-feed-per-beam feed systems are available and provide a full multiple beam coverage with only two apertures, but they lead to compromised RF performance.
In view of the recent developments on polarizing surfaces and polarization selective surfaces for applications in circular polarization, it is considered relevant to investigate these technologies in association with a single-feed-per-beam antenna configuration to combine the focal arrays operating in orthogonal polarisations on a same main reflector aperture using a polarization selective sub-reflector. This could possibly lead to an antenna farm with RF performance similar to the single-feed-per-beam state-of-the-art while using only two main reflector apertures. The main challenge is that such a solution would require a polarizing surface or polarization selective surface providing different properties over the transmit and receive frequency bands. This is due to the use of orthogonal polarizations in these two bands for a given beam. Some preliminary developments seem to indicate that the required property is feasible.
This activity shall investigate further these promising concepts, provide some high-level trade-offs to select the best solution and perform detailed analyses of the selected antenna configuration to demonstrate its compliance with stringent broadband mission requirements. A demonstrator of the polarizing or polarization selective surface shall be manufactured and tested. Performance at antenna level shall be extrapolated from the demonstrator measured results. Deliverables
Breadboard Application/Need Date Broadband applications. Also of interest for broadcasting applications at Ku and C band, now considering multiple beam coverage. Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Telecommunications Reflector Antennas (2009) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 37 of 112
5 - Telecommunications
5 - 03 - Space Segment - Payload Programme T520-501MS TD 20 Reference Activity Title
Solid reflector with metal mesh as reflective surface Objectives The objective of the activity is to develop a reflector with metal mesh as reflective surface. Such reflector shall benefit from the low weight and low acoustic load characteristics of the mesh technology developed for very large aperture. Use of these key features for reflectors in the range of 2-4 meters that can be built with a solid backing structure is considered as strongly relevant for space telecommunication applications from L to Ka-Band. Expected benefit is a significant decrease of the reflector mass. Description There is a strong interest to investigate new design(s) of mesh-based reflectors featuring an extremely small mass. For instance, telecommunication satellites for multiple beam application are using 4 identical offset parabolic reflectors of typically 2 to 3 meters diameter. Therefore, a drastic mass reduction at reflector level would enable operators to embark either additional transponders or to increase satellite lifetime duration. The current state-of-art deployable reflectors of 2 to 3 meters diameter are based on either CFRP woven fabric or triaxial weave surfaces. This activity shall investigate new design of extremely light reflectors for space telecommunication applications ranging from L-band to Ka-Band. This new reflector shall exhibit low loss, low mass, high stiffness, excellent surface accuracy and stability and PIM free characteristics. To meet these challenging requirements, a solution based on a mesh embedded on the resin of an open triaxial CFRP with a suitable opening size from mechanical and thermal point of view could be investigated. As well, implementing the mesh on a conventional stiffening structure is seen to have potential. Such configurations should enable shaping capability and exhibit very low reflective loss and low acoustic load sensitivity. This activity shall benefit from recent R&D activities on European mesh development promoted by ESA in order to increase the TRL of this cornerstone technology for large unfurlable reflectors. This reflector shall be extremely lightweight with a 25% mass reduction as compared to current state-of-the-art reflectors. The activity consists of the following tasks: - Performing a state-of-the-art survey and deriving specifications for the lightweight reflector - Making a trade-off study, performing design and analysis (RF & structural) of the reflector - Manufacturing and testing of representative samples and demonstrator - Preparing a development plan and roadmap for technology development Deliverables
Breadboard Application/Need Date
TRL 4 by 2018 Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Telecommunications Reflector Antennas (2009) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 38 of 112 Activity Description
5 - Telecommunications
5 - 03 - Space Segment - Payload Programme T520-503MS TD 20 Reference Activity Title
Advanced Aluminum Fittings in Carbon Fibre Reinforced Plastic (CFRP) Tubes Objectives The objective of this activity is the development of advanced, cost and mass effective aluminum fittings and joining technologies in CFRP tubes to be applied in high dimensional accuracy demanding applications and large temperature ranges. The activity shall cover the identification of suitable concepts, materials and joining technologies, the preliminary design of the most promising concepts and the development of manufacturing processes including screening on sample level, This shall be followed by the detailed design and analysis of a breadboard to be manufactured and characterized and verified by test. Description The applications of CFRP structures are manifold. They are e.g. used in Payload structures such as antennas, deployable arms and booms, mast, as well as for structural reinforcement of Platforms. These struts require different types of interfaces at their ends such as threads, threaded bolts, lugs and other connection elements. A common approach to realize such interfaces is to integrate aluminum fittings into tubes by adhesive bonding. When it comes to applications with increased requirements such as high dimensional accuracy and/or large temperature ranges, different issues occur preventing the use of the commonly used approach of bonded aluminum fittings. Typical issues are the CTE mismatch of aluminum and CFRP, the resulting overall effective thermal expansion of the strut, structural failure of the adhesive and structural failure of the CFRP tube. A straightforward solution would be to substitute the aluminum fittings with similar fittings made from titanium, Invar or CFRP. However, this will result in a mass penalty due to the higher density or a cost increase due to the more expensive materials, the more demanding manufacturing processes and the increased effort in surface preparation for bonding. Nevertheless, the issues of adhesive failure and tube failure still remain and are especially critical for low temperature applications. Within this activity, advanced fittings and joining technologies for aluminum fittings in CFRP tubes shall be investigated and developed. These concepts shall offer a benefit in mass, cost and manufacturing effort better or at least equal to the commonly used approach but to be applicable for different Payload and Platform applications requiring high dimensional accuracy and a large temperature range. The activity consists of the following tasks: - Identification and review of the state-of-the-art, - Identification of applications and definition of enveloping requirements, - Identification of suitable concepts, materials and manufacturing technologies, avoiding thermal control hardware - Preliminary design of the most promising concepts, - Development of manufacturing and assembly processes, - Screening on sample level, - Detailed design and analysis of the most promising concept, and - Manufacturing and characterization testing of breadboard models. Deliverables
Other: Study Report, Samples, Breadboard Application/Need Date
TRL 6 by 2019 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 39 of 112
5 - Telecommunications
5 - 04 - Ground Segment Programme T507-503EE TD 07 Reference Activity Title
Antenna user terminal with Wide Angle Impedance Matching (WAIM) metamaterial radome. Objectives The objective is to analyse, design, manufacture and test a user terminal antenna including a radome with Wide Angle Impedance Matching (WAIM). The activity shall focus on the WAIM and demonstrate the improvement on antenna scanning performance over a large wide field of view. Description Conventional fully electronic antennas exhibit several limitations when scanning towards the horizon. As example, dipole-like antennas preserve only one linear polarization perpendicular to the ground plane; patch-like antennas exhibit severe scanning losses; hemispherical conformal antennas and dome antennas (lenses with variable thickness or different materials (Luneberg-like))offer good performance but are bulky and heavy.
Recent investigations have shown that a WAIM, based on a doubly uniaxial (magnetic and electric) anisotropic layer, can be optimized for high performance on a large angular field of view. Metamaterials, composed by artificial structures with subwavelength unit cells, can be fabricated to achieve gradually refractive indices. By designing the refractive indices properly, a gradient-index planar slab able to transform spherical waves into plane waves may be derived. Using such a property, the performance of active phased array antenna over a large field of view can be drastically improved. In addition, the integration of the WAIM in the radome is expected to reduce significantly the overall terminal height with moderate impact on cost.
The curvature of the radome shall be exploited in order to maximise the performance, particularly at larger scanning angles. The amplitude and phase law applied to the phased array elements shall also be optimized for every angular direction to best account for parasitic effects and active impedance variations. Possible compensation of cross- polarization by amplitude and phase tuning shall be investigated.
The activity will start with the requirements definition. Then the identification of the most suitable metamaterial layers and a trade-off between RF performance, overall thickness, manufacturability, weight and cost will be performed. On this basis a detailed design, manufacturing and test will be done followed by a comparison (in terms of cost, complexity, RF performance, etc.) with similar antenna without WAIM implementation. It is expected that particular emphasis shall be put on the WAIM design, with a maximum reuse of already existing phased array breadboard. Possible environmental impact on the radome performance shall be assessed. Deliverables
Breadboard Application/Need Date
2018 Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Array Antennas (2011) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 40 of 112 Activity Description
5 - Telecommunications
5 - 04 - Ground Segment Programme T517-501MM TD 17 Reference Activity Title
Optical Feeder-link for next generation telecommunication satellites Objectives The objective of this activity is to mitigate the bottleneck in RF communication bandwidth applicable to telecommunication satellites. The activity shall develop and test the prototype of an optical feeder link system that enables extremely high data rate uplinks to future telecommunication satellites. The prototype shall consist of a data transmission system and an adaptive optical system for atmospheric distortion pre-compensation. Description The use of optical (laser) feeder-links for next generation telecommunication satellites is receiving strong interest from commercial telecommunication providers because it will soon not be possible to support the projected growth in bandwidth using radio frequency bands (e.g. Ka-band). Moving to higher radio frequencies such as the Q/V or W-bands does not dramatically improve available bandwidth, while it increases atmospheric attenuation to a level comparable with the laser communication bands. Cloud coverage can be mitigated by site diversity, namely by using multiple (e.g. 10) feeder-link gateway stations in mutually uncorrelated locations (they must be at least 500 km apart). Studies on the optimum selection of European, Mediterranean and North African locations have already been performed. A second issue for optical feeder-links is atmospheric turbulence, namely the effect that makes stars twinkle at night also distorts laser beams. The light received by the GEO satellite from a ground station undergoes strong intensity fluctuations (fades and surges) that do not support high data rates. This effect can be compensated by adaptive optics (AO), where the beam distortions that ultimately cause intensity fluctuations are measured on ground (using a probe beam from space) and are inversely applied on the uplink beam. This pre-distortion on the uplink beam is then corrected by atmospheric turbulence rendering an undistorted beam reaching the satellite, provided the speed of the AO system is higher than the dynamics of the atmosphere (>300 Hz). Currently implemented AO systems are aimed at correcting the wave-front of starlight (for astronomy) and for optical communication ground receivers (e.g. in the EDRS transportable adaptive optical ground station developed by DLR).
This activity will address the second issue described above by developing the prototype of an optical feeder link station and test it in an atmospherically relevant environment, namely a 14 km communication link between ESAs optical ground station (OGS) and a test station close to the top of mount Teide. Such a link characterises very well the relevant extent of effective atmospheric turbulence. The prototype will demonstrate the feasibility to perform pre-distortion on a feeder-link beam and its correction by atmospheric turbulence. The quality of the service will be measured in the OGS on the return beam by measuring the intensity fluctuations (with and without adaptive optics) and the uncorrected bit error-rate of a single communication channel. The system will be designed to ultimately achieve extremely high data rates by dense wavelength division multiplexing (DWDM); a technology used in terrestrial fibre communication networks. Deliverables
Breadboard Application/Need Date
TRL 9 by 2020 Duration Current Target 18 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Optical Communication for Space (2012) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 41 of 112
6 - Navigation
6 - 01 - Systems Programme T606-509ET TD 06 Reference Activity Title
Blind GNSS software receiver tool for field test assessment in harsh environments Objectives The objectives of the activity are the following: (i) Development of a Software (SW) tool able to recover automatically unknown pseudorandom (PRN) codes from low-noise signal recordings (potentially generated from a Radio Frequency Constellation Simulator (RFCS) and/or high-gain antennas). (ii) Development of a blind GNSS SW receiver able to use automatically the recovered PRN codes for the acquisition and tracking of non-public signals recorded with nominal GNSS antennas in the field, in particular in urban environments (covering harsh propagation conditions with strong fading). The blind GNSS SW receiver shall have the capability to track in parallel public signals (e.g. GPS/Galileo L1) and perform single- and multi-constellation positioning including both public and non-public signals. (iii) Assess the performance of the blind GNSS SW receiver with real field signal recorded in urban propagation conditions, focusing on the assessment of acquisition, tracking and positioning performance of the non-public signals in harsh propagation conditions. Description The possibility to acquire and track signals for which the PRN code is not public (e.g. as for Galileo Public Regulated Service or any other non-public GNSS service) is of high interest in order to be able to assess, with real field signal, new acquisition and tracking techniques that otherwise can only be assessed with a full GNSS receiver with access to those PRN codes. In this context, the recovery of the unknown PRN codes from low-noise signal recordings (e.g. from a Radio Frequency Constellation Simulator (RFCS)) performed in parallel to the signal recordings from a typical GNSS antenna in harsh propagation conditions (e.g. in urban conditions) can be exploited. A blind GNSS SW receiver shall be developed in this activity, including the automatic recovery of non-public PRN codes (from low-noise signal recordings from a RFCS and/or high-gain antennas) and its optimal usage in the acquisition, tracking and positioning of the same non-public signals recorded (for the same time period) in urban environments with nominal GNSS antennas. At least the usage of RFCS shall be considered for the recovery of non-public PRN codes. The blind GNSS SW receiver shall be implemented in Matlab in a modular and open way (i.e. fully accessible and document code) in order to be able to easily update it in the future with new algorithms. The implementation shall be optimized in order to reduce the processing time of the receiver (close to real-time processing shall be targeted). Moreover, the blind GNSS SW receiver shall implement high-sensitivity acquisition and tracking architectures, covering, but not limited to, the usage of state-of-the-art open-loop and multi-correlator architectures. In this context, the acquisition and tracking shall be performed even at low C/No conditions (down to 20 dBHz or even below, depending on the signal structure being tracked). Furthermore, the receiver shall be able to track in parallel public signals (e.g. GPS/Galileo L1) and enable the positioning in single and multi-constellation configurations. Finally, the performance assessment of the receiver shall be performed in representative urban environments. Deliverables
Software Application/Need Date The proposed activity is in line with the European GNSS System Roadmap.
TRL 4 by 2017 Duration Current Target 12 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 42 of 112 Activity Description
6 - Navigation
6 - 01 - Systems Programme T606-510ET TD 06 Reference Activity Title
Authentication of GNSS signals by radio signal fingerprinting Objectives The objective is to identify the most reliable GNSS signal authentication concept based on radio-level signal classification. Description The authentication of GNSS signals poses a challenging problem. Before exploiting a signal (e.g. its pseudo-noise sequence) it would be desirable for the receiver to have assurance quickly (ideally in less than 10-s) and reliably that the signal is actually coming from a navigation satellite and not from a spoofer (e.g. unknown pseudolite, delayed version of the same signal). Classical data-level authentication solutions work after signal demodulation (PN sequence de- spreading), require data-level cryptography (shared secrets) and key management. Furthermore, they cannot combat against delayed versions of the original signal, which is a problem for navigation receivers. Physical-layer authentication techniques like radio signal fingerprinting rely instead on what signals are (no shared secrets). Minimal differences in the physical structure of RF signal transmitters such as in the oscillator, amplifier and delay circuits produce differences in the amplitude, phase and frequency. Such differences can be exploited by adapted receivers to identify and classify the signal source. These techniques could offer an alternative to such data-level techniques with less system impact. These techniques allow to compare a received signal 'signature' against a local database of signatures with certain algorithms and decision criteria/metrics (e.g. fingerprint matcher using Mahalanobis distance). They do not need to process data- level information. They rely on the normal presence of pilots or equivalent repeated symbol patterns in all data frames of wireless systems producing repetitive radio signals. They are a subject of very intense research for what concerns certain security threats (e.g. impersonation, spoofing, intrusion detection) considering context (e.g. SNR conditions, classification objective, parametric and non-parametric statistical features) and implementation complexity for all sort of wireless technologies and standards from RFID tags to ZigBee, Z-wave, Wireless LAN, LTE. GNSS signals by definition are produced by very high quality radio sources. Thus, the feasibility of exploiting small differences between those sources to define well-identifiable signatures, corresponding metrics and apply signal classification techniques needs to be confirmed first. Another line of research could be to exploit the analogue distortions typically used by fingerprinting matching techniques to create an artificial signature in the signal that could be later exploited for authentication, in contrast with the typically proposed solutions based on specific PRN injection. Signal classification techniques basically rely on the processing of RF signal samples, extraction of relevant features and statistical processing with machine learning techniques (e.g. decision-tree, random forests). A survey of those techniques and a selection of a subset for further analysis, simulation and even implementation (e.g. with vector signal receiver platform) has to be performed. As part of the activity, the provision of representative and distinct GNSS signal sources with similar level of quality is crucial. The I/Q samples of recorded GNSS Navigation signals with good SNR as with an In-Orbit Test Station is needed both to generate the local database of 'clean' signatures stored by the classifier and as a signal source to be used on the stimulus side. SNR and multipath conditions need to be considered and realistic scenarios reproduced through simulation and possibly testing/evaluation and channel emulation with a radio platform. The activity consists of the following tasks : 1) to assess the feasibility of employing RF signal fingerprinting as an authentication technique for GNSS signals; 2) to study, simulate and evaluate performance of selected radio signal classification techniques for both high-end and low-end navigation receivers; 3) to propose a reliable GNSS signal authentication concept based on radio-level signal classification Deliverables Other: Simulation Software and Code, Simulation Results for Selected Classification Techniques, Study Report. Application/Need Date The proposed activity is in line with the European GNSS System and Mission Roadmaps. TRL5 by 2018 Duration Current Target 12 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 43 of 112
6 - Navigation
6 - 01 - Systems Programme T606-511ET TD 06 Reference Activity Title
Simulation Testbed for Evaluation of GNSS Performance in a Railway Environment Objectives Development of a simulation testbed to evaluate the performance of algorithms for detection of local feared events (LFEs)and the mitigation of potential errors caused by LFEs on the Position, Velocity and Time measurement in the railway environment. Description The proposed testbed would facilitate testing of receiver performances in a railway environment and testing of receiver technologies, concepts and algorithms for detection and mitigation of local feared events (LFEs), for which it is statistically improbable to observe many types of LFEs in a field test. The proposed activity includes the identification of barriers to mitigate LFEs for railway and trading-off of architectures for the on board system. This includes multi-sensor systems, the use of accurate track data base information, RAIM algorithms, protection levels calculations, etc. Unlike field testing, where variables cannot be adequately controlled resulting in confounded and non-repeatable results, the proposed testbed shall provide the tools to facilitate repeatable testing as well as fault-injection testing in a highly controlled environment. It is envisaged that data obtained from field tests can be used to generate realistic scenarios for testing. Deliverables
Other: Simulation testbed Application/Need Date The proposed activity is in line with the European GNSS Mission Roadmap (EGNOS railway) TRL 3 by 2018 Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 44 of 112 Activity Description
6 - Navigation
6 - 01 - Systems Programme T606-512ET TD 06 Reference Activity Title
Enhanced GNSS signals in Space and user receiver processing Objectives This activity aims - to enhance the current GNSS signal design in order to improve current acquisition and TTFF performance of mass-market receivers and to optimise new signal in space modulations and related user receiver processing : - to study techniques for flexible signal generation and reception, such that can evolve to sustain evolutions of services. - to develop a complete set of SW tools for performance analysis of consumer receivers considering the enhanced signals Description The recent outcomes of the first test campaign on Galileo mass-market receivers have shown preliminary but important trends in relation to the achievable performance by the commercial devices using Galileo signals, including the limitations of the current Galileo signal design and the opportunities for improvement targeting specifically this users in the future generation of Galileo. The proposed activity shall study the enhancement of the current GNSS signal design in order to: a) improve current acquisition and TTFF performance of mass-market receivers (e.g. new signal components enabling fast acquisition scheme or High Sensitivity Techniques). b) optimise new signal in space modulations and related user receiver processing: exploitation of new Modulation schemes, Spread-Spectrum techniques, mapping and multiplexing (e.g. multicarrier, CSK, frequency-hopping, ultra- wideband, meta-signals, SC FDMA, etc.). The outcomes of the current Galileo second generation studies have shown as well some limitations and opportunities for improvement on the definition of new Galileo signals, coming just from the need of supporting Legacy users. Based on that, the activity shall study techniques for flexible signal generation and reception: a flexible signal component that can evolve to sustain evolutions of services, including the design of a flexible receiver able to adapt to the corresponding advanced signal formats/techniques that will come from evolutions of the GNSS systems. Furthermore, the activity shall consider the design of solutions for an efficient protocol to notify in advance to the user receiver the planned modifications of the signal and for the receiver to implement them. The studies performed under the activity on the GNSS signal design will provide inputs to the definition of the future signal as part of the Galileo second generation consolidation activity. Finally, the activity shall develop a complete set of SW tools for performance analysis of consumer receivers performance in terms of acquisition and tracking sensitivity, data demodulation and Time to First Fix in realistic environments (LMS or DLR channel models, time series extracted from real on field tests). The enhanced signals defined as per first objective shall be considered. Note that tools currently available are based on standard receiver architecture and they do not consider advanced processing techniques used in mass-market. The results of this activity shall be considered an input to the consolidation work performed as part of the Galileo 2nd generation system design, in the area of signal design and user performance. Deliverables
Software Application/Need Date The proposed activity is in line with the European GNSS System Roadmap.
TRL 4 by 2018 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 45 of 112
6 - Navigation
6 - 01 - Systems Programme T606-515ET TD 06 Reference Activity Title
Tool for GNSS System failure modes investigation Objectives This activity aims to develop a tool to support investigating the failure modes of GNSS systems and to characterise the tolerance of GNSS systems to failures. Description The activity aims at developing a tool that can investigate the failure modes of GNSS systems. Such tool can then be used for detection of failures, and/or to characterise the tolerance of GNSS system or subsystem architectures to failures. Focus will be given primarily to failures and failure modes that may impact critical services (e.g. Safety-of-Life).
The tool shall be able to model GNSS systems and subsystems (i.e. ground or space segments, elements and/or components) and its failure modes in a modular way. This modularity would then allow the user either to investigate the failure modes at subsystem level, or to create different GNSS architectures whose tolerance to various failure modes can be quantified.
The failure modes shall be modelled into a 'database' and can be used as the building blocks for the more complex modules. In this way, the failure modes can be kept up to date more easily and can be updated independently of each other, while interactions between failure modes can still be modelled.
An aspect to be characterised is the impact of failure modes in the achievable performance, by taking into account the constellation geometry to calculate Position, Velocity and Time. Deliverables
Software Application/Need Date The proposed activity is in line with the European GNSS System Roadmap.
TRL 3 by 2018 Duration Current Target 12 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 46 of 112 Activity Description
6 - Navigation
6 - 02 - Space Segment Programme T606-502ET TD 06 Reference Activity Title
Advanced glass cell technology for extended GNSS atomic clocks lifetime Objectives Increasing of cell robustness for atomic frequency standard lamps and dissociators by analysis and testing of state of the art techniques Description Glass cells are typically used in Frequency Standard, both as reference cell, in the lamps for atomic pumping and as dissociator bulbs. When used in a lamp (RAFS or Mercury ion trap), the cell must be sufficiently resilient for avoiding limitations in the lifetime due to diffusion of material (i.e. Rubidium or Mercury) inside the bulb walls, given the combination of dissociation mechanisms and high temperatures. In the case of dissociators (like in the PHM) the sputtering effect due to ion bombardment of the inner bulb surface is one of the detrimental effects limiting the instrument lifetime. Cell coating or appropriate bulb material selection are the only solution for limiting such phenomena. The existing techniques adopted in the industrial processes (especially for light bulbs) or in literature shall be analysed and solution shall be proposed for both lamps and dissociators. The identified solutions shall be implemented and at least 5 cells shall be manufactured for each solution proposed. Those cells will be integrated on a representative test vehicle. Aging or comparative tests shall be then identified and performed with the aim of assessing the identified solutions effectiveness. Geometry of the cells/bulbs will be provided as an input to the activity. Clock manufacturers shall be involved in the study for bulb geometry and test vehicle definition. Deliverables
Study Report Application/Need Date The proposed activity is in line with the European GNSS Technology Roadmap. TRL 5 by 2018 Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Frequency & Time Generation and Distribution - Roadmap Yes Roadmap Space (2013) Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 47 of 112
6 - Navigation
6 - 04 - Users Programme T606-501ET TD 06 Reference Activity Title
Carrier Phase Positioning Techniques for Mass Market GNSS Receivers Objectives Study and develop Carrier Phase Positioning Techniques to support high accuracy applications for Mass Market GNSS Receivers Description Currently carrier phase positioning techniques assume the utilization of a professional receiver, whose main advantages are the reduced multipath impact and the dual frequency tracking capability. Furthermore, professional receivers have limited capability to track non-line of sight satellites, especially in challenging environments (like urban ones). Most of the GNSS users are nowadays exploiting mass market receivers. Those receivers are characterized by single frequency use (but for the future it could be also dual frequency) a high robustness signal tracking, and low C/No acquisition and tracking thresholds. Those capabilities increase dramatically the satellites availability in challenging environments (e.g. urban environments and urban canyons). However, tracking noise is typically higher, mainly because they are more sensitive to multipath than the professional receivers. The main carrier-phase based techniques are Precision Point Positioning (PPP)and Real Time Kinetic (RTK/WRTK). PPP is in principle a worldwide service while RTK/WRTK is a local/wide area service. Those techniques are normally based in professional receivers. The task included in this activity are firstly to do an assessment of the current PPP and RTK/WRTK state of the art algorithms performance when using mass-market receivers in challenging environments (e.g. urban). Secondly to improve those algorithms. Then, to defined a proof of concept (PoC) with a commercial chipset to test the most important aspects of the improved PPP algorithms and characterize its performance (accuracy and convergence time) in selected and agreed representative scenarios. The conclusions of the PoC shall be used for iterating the algorithms in order to improve them further. Finally, a set of recommendations, algorithms and PoC results shall be provided. Deliverables
Other: Study report and prototype S/W Application/Need Date The proposed activity is in line with the European GNSS System and Technology Roadmaps. TRL 4 by 2018 Duration Current Target 12 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 48 of 112 Activity Description
6 - Navigation
6 - 04 - Users Programme T606-506ET TD 06 Reference Activity Title
Advanced open-loop techniques for high-sensitivity GNSS receivers applied to BOC signals Objectives The activity targets the design and performance assessment of new innovative open-loop techniques for the robust estimation of both code delay and carrier phase and frequency in harsh propagation conditions in the presence of fading and multipath at low C/No conditions. In particular, the tracking of BOC signals and possible problems associated to it shall be considered. Furthermore, multi-correlator architectures shall be considered for this purpose. Description High-sensitivity GNSS receivers architectures are of interest in harsh propagation conditions in order to be able to keep tracking GNSS signals even at very low C/No conditions (typically down to around 10-20 dBHz, depending on the signal being tracked). For this purpose, open-loop techniques can be used in the estimation of the code delay and the carrier phase and/or frequency, targeting a more robust estimation of those observables. In this process, advanced signal estimation techniques can be applied for the optimum exploitation of e.g. multi-correlation samples. This can be of particular interest in the case of BOC and high-order BOC signals, due to the multiple peaks present in the BOC autocorrelation function.
Advanced and innovative open-loop techniques exploiting in an optimum way the multi-correlator architectures shall be proposed and designed in this activity for the robust estimation of both code delay and carrier phase and frequency in harsh propagation conditions in the presence of fading and multipath at low C/No conditions (i.e. below or well below 20- 25 dBHz). The techniques proposed shall consider the tracking of BOC and high-order BOC signals and the problems associated to the unambiguous tracking of those signals at low C/No conditions (even below 20-25 dBHz, depending on the BOC modulation considered). The techniques proposed shall be robust when considering no aiding information is available (i.e. the baseline shall be to consider that no aiding is available). The techniques proposed shall be assessed with SW simulations considering both acquisition and tracking stages or a combination of both if snapshot processing is performed. Those techniques shall demonstrate to be robust in cold start conditions and shall be applicable at satellite tracking level (i.e. not at position level). The performance assessment shall be performed by using realistic channel models.
The results of this activity shall be considered an input to the consolidation work performed as part of the GALILEO 2nd generation system design, in the area of signal design and user performance. Deliverables
Other: Study report and prototype S/W Application/Need Date The proposed activity is in line with the European GNSS System and Mission Roadmaps.
TRL 3 by 2018 Duration Current Target 12 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 49 of 112
7 - Generic Technologies and Techniques
7 - 01 - Onboard Data Systems Programme T701-501ED TD 01 Reference Activity Title
SpaceWire Network Management Service Suite Definition and Validation Objectives The objective is to specify, prototype, and validate a Network Management Service Suite for SpaceWire that integrates all aspects of SpW network management, i.e. network discovery, network configuration, and network FDIR. Description SpaceWire has become a de facto standard for payload systems (including for Command & Control) and its Real-Time derivatives are now being considered for avionics. The capability provided by SpaceWire to develop data handling systems based on high-speed networks allows much greater performance but implies implementing communication bus management techniques specific to SpaceWire. As network management is not part of the basic SpaceWire protocol ECSS-E-ST-50-12C (Rev.1), it must be provided to industry in the form of an additional standard.
The different elements of the SpW network management have been developed separately so far.
The tasks related to this activity are: 1. Merging and consolidation of requirements for a Network Management Service Suite (N-MaSS) covering SpaceWire network discovery, configuration, and FDIR 2. Detailed specification of N-MaSS in the form of a draft ECSS standard 3. Prototyping of the specified N-MaSS 4. Verification (test) the prototyped SpW network management services 5. Validation of the SpW Network Management Service Suite through demonstration of its capabilities in one or more scenario(s) representative of spacecraft data handling (the BepiColombo/Solar Orbiter SpaceWire network and the MTG/MetOp-SG SpaceWire network should be considered as baselines, which leads to quite a number of SpaceWire nodes and switches)
The main deliverables are a SpW N-MaSS specification that shall be in the form of a draft ECSS standard, ready for improvement by the International SpW Working Group before potential adoption by ECSS, a prototype implementation of N-MaSS in a number of master and slave nodes, as well as switches and a demonstrator (HW & SW) of the N-MaSS capabilities. Deliverables
Prototype Application/Need Date Need date = TRL52018
Application = support to design of SpaceWire communications for spacecraft in early development phase such as EUCLID, JUICE, LOFT, Meteosat Third Generation, etc. Duration Current Target 24 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap On-Board Payload Data Processing (2011) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 50 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 01 - Onboard Data Systems Programme T701-503ED TD 01 Reference Activity Title
Verification of SEU-mitigation techniques in 3rd/4th generation Flash FPGAs Objectives The objectives of this activity is the radiation characterization of the 4th generation of Flash FPGAs offered by Microsemi, and the development of methods for verifying the proper implementation of Single Event Upset/Transient (SEU/SET) mitigation techniques applied at Register Transfer Level (RTL) for 3rd and 4th generation Flash FPGA technologies. Description Flash FPGAs combine the reprogrammability and flexibility of SRAM-based FPGAS, with immunity to configuration upsets, low static power and a non-volatile configuration, which are characteristics more common to antifuse-based FPGAs. The latest developments in Flash-based FPGAs, e.g. the 4th generation Microsemi Flash FPGAs (RTG4), offer a high number of high-performance programmable logic resources, large and fast on-board memories, and high performance I/O - SERDES, LVDS, DDR, etc. All the elements are very appealing in high-bandwidth data processing payload applications, but also high performance on-board computing, if these FPGA resources are combined with on- chip processors.
Targeting 3rd generation (ProASIC3) and 4th generation (RTG4) Flash-based FPGA technologies, this activity includes the following tasks:
1. Development of (formal) verification methods for verifying the proper implementation of SEU/SET mitigation techniques applied at RTL level (e.g. TMR, 'safe' Finite State Machines, etc.). Formal methods are indicated as a suitable solution for this problem as they present several advantages compared to stimulus-based simulation methods: the fact that they don't require stimulus vectors in order to verify the equivalence of a mitigated design vs. the original simplifies and shortens the verification task. Even more importantly, formal methods cover the complete design space exhaustively, hence their final proofs are more conclusive compared to simulation- based methods.
2. Extensive radiation test campaign, targeting 4th generation Flash FPGAs, with the following aims: (a) Characterization of SET effects at various clock frequencies under radiation testing: Analysis of SET sensitivity and propagation measurement. Development of different possible SET mitigation techniques to be used in 3rd and 4th generation Flash FPGAs. (b) Characterization of PLL performance (sensitivity) under radiation. (c) Characterization of radiation-induced errors on-chip RAM blocks: analysis of occurrence, and possible patterns, of single and multiple bit upsets in on-chip RAMs.
The test vehicles used as Designs Under Test (DUTs) in this activity shall be selected considering the intended use of these FPGAs in On-Board Computers (OBC) and data handling applications, and could range from on-board interfaces such as SpaceWire/SpaceFibre and CAN, to more complex IP cores such as microcontrollers embedded on chip. Deliverables
Prototype Application/Need Date
Science, Earth Observation, Robotic Exploration, Telecomm Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Data Systems and On-Board Computers (2011) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 51 of 112
7 - Generic Technologies and Techniques 7 - 02 - Space System Software Programme T702-501SW TD 02 Reference Activity Title
Payload Execution Platform Software Objectives The activity aims at specifying, designing and prototyping a generic Payload execution platform compliant to the SAVOIR Avionics System Reference Architecture and On-Board Software Reference Architecture. The resulting execution platform, available to Space European community, shall minimize integration issues with the platform through the standardisation of interfaces and services it supports. Description The Space Avionics Open Interface Architecture (SAVOIR) initiative aims at establishing a streamlined on-board architecture in order to standardize the development of avionics systems for space programmes. The SAVOIR-FAIRE working group defined an On-Board Software Reference Architecture mainly focusing on the main platform computer and in parallel, the On-Board Software Reference Architecture for Payloads (OSRA-P) TRP activity is currently applying the approach defined by SAVOIR-FAIRE to Payloads. This will result in the identification of the functions and services that shall belong to the payloads Component and Execution Platform layers. Recent spacecraft reviews clearly shows that the understanding of requirements contained in the Experiment Interface Document (EID-A) is usually different from a Prime Investigator to another and to the platform provider. This leads to many non-compliances generating delays in the development of instruments and issues in their integration with the platform. The OSRA-P study made a survey and an analysis of several instruments. The first results show a great similarity of hardware and software design of the Instrument Control Units. Most of the instrument interfaces to platform are based on Leon processors (Leon3-FT in ASIC version as UT699 and GR712 or as IP core library implemented in a FPGA), have to manage standard communication interfaces, i.e. SpaceWire and/or MIL-STD-1553B and to support the same subset of Packet Utilisation Standard (PUS) services, e.g. for Telecommand, Telemetry and memory management. The standardisation of the interfaces and services shall ease the integration of the payloads with the platform and the development of payloads by providing them standard building blocks. The activity will provide a clear definition of the payload architecture and the identification and specification of all the services it shall contain. This specification will be used to develop a prototype of the Generic On-board Payload Execution platform targeting Leon multicores and SSDP based computers. As far as possible, the prototype will use existing building blocks (e.g. RTOS, partition kernel, PUS library, OBCP engine, etc.) and will experiment a remote boot using SpaceWire RMAP protocol. The missing functions and services will be developed and integrated in the system. The new developments will follow the ECSS standards in order to ease their proper qualification and reuse. The prototype shall be able to demonstrate the concepts through the execution of representative use cases and to support the future qualification process. It will then be possible to reuse it entirely or partly for the development of new payloads or to use it as a reference implementation supporting both payload and platform developments. The tasks related to this activity are then: 1. Analysis of outputs of related SAVOIR working groups and TRP/GSTP activities related to the domain and consolidation of the services to be provided. 2. Specification of the Generic On-board Payload Execution platform. 3. Definition of representative Use Case to demonstrate the concept. 4. Design, Development, Integration and Test of an implementation of the Generic On-board Payload Execution platform. 5. Demonstration through execution of representative Use Cases. Deliverables Specification: ‘Generic On-Board Payload execution Platform', Software: 'Prototype including reference Software libraries' Application/Need Date A TRL 5 has to be achieved by 2018 in order to consider this new approach in next missions. Open source 15 3 4 Duration (Months) Current TRL Target TRL SW Clause code Applicable THAG Roadmap On-Board Software (2010) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 52 of 112 Activity Description
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 53 of 112
7 - Generic Technologies and Techniques
7 - 03 - Spacecraft Electrical Power Programme T703-501EP TD 03 Reference Activity Title
Process Development for Ultra-Thin Solar Cells Objectives The objective of this activity is to obtain a thin solar cell (target 20 microns) with the same electrical performance as the nominal thickness (140 microns) solar cell. Description The development of manufacturing processes to obtain ultra-thin cells (20-80 microns) is of paramount importance to achieve a significant mass reduction without reducing the fabrication yield. In order to achieve this goal, it is required the interaction of two different technological processes: epitaxial lift-off and layer transfer. The epitaxial lift-off consists in the separation of the active layers (those responsible for the operation of the solar cell) from the substrate, in a way that the latter can be reused. The lift-off can be performed using chemical etch or applying mechanical stress to the structure. The layers lifted from the substrate are very thin and sensitive and for that reason a layer transfer process is needed to guarantee their integrity during the rest of the manufacturing sequence. Most probably there is not a single process capable of producing ultra-thin solar cells that can be applied to all solar cell concepts. Each solar cell design will thus require a dedicated processing route including a dedicated lift-off and layer transfer process. In this activity, the different varieties of processes available for the lift-off and layer transfer, identified in previous activities, shall be applied to build up a full manufacturing process adequate for each one of the most promising concepts of the next generation solar cells and depending on the final product that is intended to fabricate. The following tasks shall be completed: 1- To apply the epitaxial lift-off method most adequate to each one of the most relevant solar cell technologies. 2- To determine the best layer transfer technique, with or without temporal substrate, depending on the particular solar cell’s technology. 3- To define a full manufacturing route for each one of the relevant solar cell’s technologies considering the outcome of Tasks 1 and 2, including the full processing until the final solar cell is obtained. The activity will require that a significant number of solar cells with a minimum target of efficiency are delivered. A cost analysis of the developed process shall be performed and a reliability analysis shall be carried out in order to determine the impact of this new process in the lifetime of the new developed cells. Deliverables
Engineering Model Application/Need Date
Potentially all. TRL6 by 2020. Duration Current Target 24 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Solar Generators & Solar Cells (2009) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 54 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 04 - Spacecraft Environments and Effects Programme T704-501EE TD 04 Reference Activity Title
Prototype Passive Field-Effect Electron Emitter for Charging Alleviation Objectives The objective is to build and test a prototype electron emitter that will use electric field-induced electron emission to reduce the absolute potential of a charged spacecraft. Description Spacecraft electrostatic charging in hot plasma environments leads to the risk of damaging electrostatic discharges and is linked to many serious incidents of anomalies and damage to spacecraft electronics. In principle, the charge can be removed by active emitters (guns) but this adds to the system complexity and cost.
A GSP study used theory and simulation to explore the possibility of a passive system in which naturally occurring potential differences on the spacecraft can be used to drive an electron emitter, which safely lowers the spacecraft potential.
The study showed that such a system should be feasible and produced a conceptual design called SCAPEE.
This proposes use of a system of spikes and a mask to create high electric fields. Carbon nano-tubes provide a further enhancement to the fields that are calculated to be sufficiently high to drive the electron field-emission processes. The next goal for the development of this device is to prove it works in the laboratory. For this, the design must be optimised and a prototype manufactured. Testing will be under vacuum and will characterise the current-voltage characteristics of the device. Deliverables
Prototype Application/Need Date
TRL7 by 2022 Duration Current Target 32 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 55 of 112
7 - Generic Technologies and Techniques
7 - 04 - Spacecraft Environments and Effects Programme T704-502EE TD 04 Reference Activity Title
Solar Particle Radiation Advanced Warning System (SAWS) Objectives The objective of this activity is to advance the technology development of a Solar Particle Radiation Advanced Warning System (SAWS) which can collate and combine outputs from modules providing forecasts of solar phenomena, solar proton event occurrence and solar proton flux and duration characteristics which can be tailored to the needs of different spacecraft and launch operators. Description Increased radiation levels, as a result of space weather, has been recognised as an important risk for spacecraft and launcher operations. Recently threshold levels of solar energetic particle (SEP) flux and solar activity have been considered as a baseline criteria for launches. After the launch of Gaia in 2013, the transfer included manoeuvres reliant upon the AOCS star trackers, operating in interplanetary space and whose reliability could be seriously impacted by radiation storms known as Solar Particle Events (SPEs). As a result, launch criteria include radiation levels provided by nowcasting and forecasting of the environment. Pre-cursor systems have been developed with three forecasting modules which contain one or more models: solar flare prediction, SEP occurrence prediction and SEP characteristic prediction. The three modules shall be evolved further to include: 1/ Extension of the timeframe for the solar flare forecast to cover forecast horizons from 6 to 72 hours and shall cover the whole Earth-facing solar disk making use of previous forecasts where necessary to resolve issues of data quality at the Western limb of the solar disk. 2/ Inclusion of additional data including CME data and high energy solar electron data to improve the accuracy of SEP occurrence prediction tools. 3/ Combination of data-driven statistical analysis, in-situ data and shock-arrival time predictions to improve forecasts of the SEP peak flux and duration characteristics. A detailed validation of all modules shall be performed and the outputs shall be used to develop the Solar Particle Radiation Advanced Warning System (SAWS) - a system combining outputs from different models in a way justified by an analysis of their performance in different scenarios to provide forecasts evolving with time.
The central component of SAWS shall include standardised interfaces for each of the three module classes in order to allow for easy comparison and easy incorporation of future model developments. This approach shall also allow for the de-coupling of the processing and provision of data required by forecasting modules to take advantage of the highest quality data. The central system shall also perform combinations of forecasts on a module level and the provision of consolidated results to the user through a single web portal. Deliverables
Software Application/Need Date
2018
Duration Current Target Open source 24 2 4 SW Clause (Months) TRL TRL code Applicable THAG Radiation Environments & Monitoring, Effects Tools Roadmap Yes Roadmap & Testing (2009) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 56 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 06 - RF Systems, Payloads and Technologies Programme T706-501ET TD 06 Reference Activity Title
High Performance MEMS Reference Oscillator Objectives
To design, realise and test a high performance MEMS reference oscillator Description Today, reference oscillators are based on a quartz resonator which is carefully sheltered in order to provide a very stable environment to this key component which in turn provides a very stable and low phase noise reference. This type of oscillator also called Oven Controlled Oscillator (OCXO) is the core technology in most space products requiring either stable frequency or low phase noise or both. Though far more recent on the market, MEMS oscillators are already as good as TCXO while being much smaller (hybrid assembly as compared to single chip solution). The purpose of this activity is to assess whether this type of MEMS oscillator, with the resonator being protected in a similar way than for the quartz in the OCXO, could deliver performances close to OCXO but with a smaller footprint and lower consumption. The study logic is as follows: - Assessment of commercial MEMS oscillators in protective environment, - Design, fabrication and test of MEMS resonators, - Design, fabrication and test of a high performance MEMS reference oscillator. Deliverables
Breadboard Application/Need Date
TRL5 by 2020 Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
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7 - 06 - RF Systems, Payloads and Technologies Programme T706-502ET TD 06 Reference Activity Title
Test methodology investigations and parameters influencing Passive InterModulation (PIM) interference Objectives The objectives of this activity are the identification and study of all parameters having a direct influence on the generation and the amplitude of passive intermodulation. The outcome of these investigations will be used as baseline for the initiation of the related standard providing industry and Agencies with an agreed test methodology and justified margins allowing reliable qualification of space hardware. Description Passive intermodulation is a real threat to all types of payloads. In some cases, it could even lead to total loss of the spaceship. Despite of this, there is very weak understanding of the parameters that generate this unwanted interference as well as their influence in the amplitude of the interfering signal.
In addition, there is a total lack of agreed testing techniques, procedures and methodologies as well as justified test margins, as has already been recently stated by the European community (National Delegations, satellite operators and Eurospace).
The activity shall assess the impact that radio frequency parameters have on the generation and strength of passive intermodulation interference as well as those emerging variables related to the space environment. In particular, the study will focus on the variation in the amplitude of the interference signal versus:
- Frequency band (from L to K bands), transmitted power and number of carriers - PIM order - Signal characteristics (Continuous wave, pulsed or modulated) - Temperature (ramping), pressure and type of material (at flange or connector)
The work shall also cover all possible scenarios (i.e. conducted such as filters, cables, etc. and radiated such as antennas) where PIM can become a threat to space missions. It will define testing techniques and procedures for all these test cases with strong emphasis on test margins supported and justified with actual test data. Deliverables
Breadboard Application/Need Date
TRL 3 by 2017 Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Microwave Power Breakdown Modelling & Roadmap Yes Roadmap Characterisation (2007) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - Generic Technologies and Techniques
7 - 07 - Electromagnetic Technologies and Techniques Programme T707-501EE TD 07 Reference Activity Title
Characterization of the susceptibility of SpaceWire (SpW) links to common mode Objectives By gathering knowledge and understanding about the common mode susceptibility of SpaceWire links (SpW), this activity will aim to define new criteria to select SpW/LVDS driver components and relevant common mode use requirements that will be considered as inputs for update of the SpaceWire Standard. Description SpaceWire links (based on LVDS for the physical layer) are used extensively on-board Earth Observation, Science and Exploration spacecraft, in particular to transmit science data. MTG and Plato are typical examples out of many. The trend is to use higher data rates over longer cable lengths.
More and more, the components used to drive SpW/LVDS links have a common mode offset voltage (Vos) significantly out of the range specified in the applicable LVDS standard TIA/EIA-644-A, thus potentially reducing the margin between the common mode offset at the SpW/LVDS driver output and the common mode range acceptable by the SpW/LVDS receivers. This margin is supposed to accommodate the 'longitudinal' common mode between driver and receiver. This 'longitudinal' common mode is due to electromagnetic interference. Currently, a great deal of analyses and testing is devoted to confirming the adequate functioning of the SpW links whenever the Vos is out of specification and Request For Deviations (RFD) have to be processed.
The analyses, in particular, involve larges uncertainties, as: - for lack of better knowledge, the DC common mode criteria from the LVDS standard are applied over the whole range from DC up to the frequency of the SpW link of interest, which can be as high as 100 MHz - there is not one unique type of common mode, while all types have to be combined into a budget over a large frequency range
To address this issue, this activity will cover: - the modelling of the phenomena of interest: how do the various kinds of AC common mode interference degrade the signal integrity of SpW links - the definition of adequate test methods for SpW links immunity to AC common mode - a test campaign (characterization of the robustness of various SpW links against different kinds of common mode interference).
The activity will conclude with establishing relevant common mode requirements and their verification. Deliverables
Study Report Application/Need Date
TRL 4 by 2017 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
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7 - 08 - System Design & Verification Programme T708-503MX TD 08 Reference Activity Title
Enabling fully traceable thermal imaging of spacecraft during thermal-vacuum, thermal balance testing Objectives The objective is the research and development of a standardized methodology to perform fully traceable thermal imaging during TB-TV spacecraft testing. This could be also used for thermal imaging of the S/C performed in flight. Description The main tasks of this activity are the following:
1) Metrological assessment and gap analysis of existing thermal imaging methodology, data processing and uncertainty assessment, related but not limited to aerospace applications. Develop validated traceable processes and uncertainty calculations and demonstrate them on a given representative case
2) Assessment of thermal imagers calibration and related traceability to standards and develop validated traceable calibration methods and demonstrate them on a given representative case
3) Assessment of state-of-the art methods to perform materials BRDF characterization and related uncertainty traceable to national standards. Propose and demonstrate validated traceable methods of a given representative case.
4) Assessment of state-of-the art methods to perform calibration of sun simulated sources or IR radiation sources and propose and demonstrate validated traceable calibration methods of a given representative case.
5) Development of a generalized methodology and propose the way forward for the standardization of thermal imaging of spacecraft during TB-TV testing, considering traceability to ITS 90 standards.
The study will be based on the following inputs: - the output of on-going research activities on the subject (TRP study on Infrared camera-based system for 3D thermal measurement) - knowledge of the state-of-the-art methodologies for the characterization of materials BRDF - survey of methods used for calibration of thermal imagers - knowledge of the state-of-the-art for calibration of sun simulation or IR radiation sources
The study output is a validated, alternative and complementing method to contact thermometry, with demonstrated traceability to ITS-90, for validation and verification during spacecraft TB-TV testing. Deliverables
Other: Study report, algorithms, procedures and test results to validate the methodology on a representative test case. Application/Need Date
AIV campaigns of S/C: TRL4 by 2017 Duration Current Target 12 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - Generic Technologies and Techniques
7 - 09 - Mission Operation and Ground Data Systems Programme T709-501GE TD 09 Reference Activity Title
Penetration Testing and Security Awareness Management in a Box Objectives This activity covers the development and demonstration through prototyping of the technology for modular disruptive security testing and user security awareness management for the ground segment. Description Disruptive security testing and penetration testing are essential tools to integrate secure ground segment engineering. They verify the robustness of newly developed as well as legacy software. They are as well core requirements in the new ESA secure software engineering standard. To execute them on operational or productive systems is not advisable since it may impact the business function. The objective of the proposed study is to develop the technology for a customisable virtual environment (the box) that allows penetration testing and security awareness management. The box will be based on a suitable security-specialised operating system and will allow manual and automated execution of customisable security attacks against the software running inside the box. It will produce evidence reports of the successful penetrations and, based on well-known security practises, will suggest countermeasures. The box can either automate the testing (using well-known attacks) or the user can execute it manually. The box will allow the definition of new attack scripts to be added to the list of automated tests. As a second objective, the box will also provide the capability to perform security awareness management. It will be possible to pre-configure a box for specific software and then pass it on to users and stakeholders with step-by-step automated attack pattern instructions. The users can perform the attack themselves and observe the results. The intention is to raise their awareness vis-a-vis the security vulnerabilities of the software products they own or are using. This will help to raise the awareness that it is necessary to invest properly into secure software engineering. The expected Outcomes are: - Development of a penetration testing specialised virtual environment, including all necessary technology to monitor software processes and track in detail the successful and unsuccessful attacks - Graphical toolset that allows definition of automated attack scripts, produces attack traces and evidence records - Awareness management instantiation engine that allows to create specialised copies of the box focused on security awareness management for specific systems and applications. These copies shall be accompanied with a tutorial including a step-by-step description of attacks which can be run by the users themselves. This activity includes the following tasks : - Technology development based on existing technology in the area of security-specialised virtualisation environment (e.g. secure operating systems) - Development of the virtual box implementing the previously identified technology and supporting the functionality stated above - Development of the graphical toolset to support the automation of penetration attack scripts and produce attack traces and evidence records - Development of the awareness management instantiation engine - Execution of a proof-of-concept using one of the critical applications developed by the HSO ground segment engineering department (e.g. mission control system, space debris office software, etc.) with direct involvement of technical officers. Deliverables Software Application/Need Date All ESA software development stakeholders, software developers, software end users and stakeholders (missions, flight control teams). The box would best be available asap to address existing risks and raise security awareness. Target is to reach TRL 6 through a follow up study by 2019. Duration (Months) 12 Current TRL 2 Target TRL 4 SW Clause Operational S/W Applicable THAG Roadmap Ground Systems Software (2008) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 61 of 112
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7 - 09 - Mission Operation and Ground Data Systems Programme T709-502GI TD 09 Reference Activity Title
Trade-off and technological analysis/prototyping for the new generation simulators infrastructure (SIMULUS-NG) Objectives Perform a trade-off analysis to identify the possible paradigms for future infrastructure, and explore architectural and technological solutions, which will form the basis for the design and development of the new generation infrastructure supporting high-fidelity operational simulators. This trade-off needs in particular to take into account ideas for additional capabilities to automatically synchronise in a semi real-time manner the high fidelity simulator models with the real Spacecraft (S/C) status. Such capabilities would potentially allow to accurately detection of on-board anomalies and / or problems in the simulated spacecraft models Description Many key decisions need to be taken prior to starting the actual development of the new generation simulators infrastructure, covering both technical issues as well as looking into innovative ideas for new use cases of Operational Simulators. Performance is a critical aspect of high-fidelity simulators including the need of emulating the continuously more powerful on-board processors, the ever-increasing data generation and down-link rates, and the requirement to support faster than real-time simulations. High-fidelity simulators are complex systems which need to be developed within a short time frame, in order to meet the user needs. It is essential that common elements of the various space segments are designed and implemented insuring model portability and re-usability such that they can be re-used across mission specific simulators. The modernisation of the current technology stack is an objective, while taking into account economic issues and the risk/benefit of migrating already operational mature systems. In addition, methods to achieve a cleaner separation between common infrastructure and mission specific extensions need to be found. Modern technologies offer more advanced solutions relying on shared resources to achieve scalability and consolidation than what is used today. The simulators infrastructure is used as the basis for developing complete simulators but needs to be validated in isolation. This introduces a significant challenge to achieve a proper balance between efficiency and representativity of the validation approach. Traditionally, Operational Simulators have been offline tools used for test, training and validation while their role in anomaly detection has been limited. If a way can be found to keep high fidelity simulators in sync with real spacecraft state (as determined on the basis of telemetry data), this can be changed. For this a proof of concept for a 'synchroniser' that command the simulator until a 'synchronised' state is achieved needs to be developed. Addressing these challenges will be done with an open minded assessment of additional novel features and use cases for high fidelity simulation models in order to determine the most appropriate approach and technologies to design and develop the next generation simulators infrastructure. Deliverables
Prototype Application/Need Date The current generation of simulators infrastructure at ESOC will face obsolescence in the next decade. It is necessary to prepare for the development of a new generation, which is expected to start in year 2018. TRL 4 by 2017 This activity will be very useful for all future missions in particular complicated ones like Juice Duration Current Target 16 2 3 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap Ground Systems Software (2008) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - 10 - Flight Dynamics and GNSS Programme T710-501GF TD 10 Reference Activity Title
Navigation concepts for multi-revolution SEP transfers Objectives The objective of the study is to define efficient navigation concepts for multi-revolution Solar Electric Propulsion transfers covering the large variety of mission requirements and constraints. These concepts shall build on the experience gained with Smart-1. The use of the new developments shall be included when appropriate in terms of operational load, transfer duration, on-board complexity, mass and cost as well as mission robustness. Description Multi-revolution Solar Electric Propulsion (SEP) transfer from the low altitude launcher injection orbit to the final operational orbit is seriously considered or already base-lined for telecom (NeoSat, Electra, Alphabus-extension), Navigation (Galileo next generation) and Earth Observation satellites. With SMART-1 significant experience has been gained to carry out these operations by a fully ground-based approach using conventional radiometric measurements. Meanwhile the boundary conditions for such operations have changed considerably. Engine technology and characteristics have evolved. On-board GNSS based navigation has become standard. Developments are on-going to extend the use of GNSS to higher altitudes even up to GEO. Operations driving mission and spacecraft constraints (attitude control, eclipse handling, parallel payload operations) are different from SMART-1. Several promising operational concepts shall be defined in terms of: - on-board equipment - navigation tasks to be performed on-board by the GNC system - navigation tasks to be performed on ground - tasks to be performed on-ground to support the on-board equipment and GNC system - Interface between the ground and on-board system The concepts shall cover the entire range between pure ground-based and full autonomous approaches. The study shall pay special attention to hybrid concepts with an efficient sharing between ground and on-board functions. It shall include a concept where the orbit is determined and propagated on-board using GNSS and where the thrust direction profile and switching times are calculated optimally on-ground and up-linked to the spacecraft not in absolute times, but relative to the perigee passage time, which is known on-board. It is expected that the synchronization of the thrust with the perigee passage time allows to increase the interval of ground updates from 4 days for Smart-1 to several weeks. For fine targeting to the station position, a few free drift revolutions with small trim manoeuvres should be foreseen at the end. The following aspects of each concept shall be analysed: - navigation performance in terms of fuel usage and targeting accuracy - timeline of operations - ground operational load - on-board processing load - mission robustness - cost for on-board equipment and GNC algorithms - cost for ground system development and operations Pro's and Con's of the different concepts will be identified, quantified and compared to come up with recommendations for the future missions. Deliverables Study report and prototype Software Application/Need Date Future Telecom and Galileo satellites will benefit from it. The results are needed by 2018 as input to spacecraft definition in terms of on-board sensors and GNC algorithms. Duration Current Target 18 2 4 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 63 of 112
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7 - 10 - Flight Dynamics and GNSS Programme T710-503GN TD 10 Reference Activity Title
Independent generation of Earth Orientation Parameter Objectives Development of ESA capability for the estimation and prediction of Earth Orientation Parameter (EOP) to become independent of the International Earth Orientation and Reference Service (IERS). Description Earth Orientation Parameters (EOP) are of fundamental importance for all ESA missions. Currently, the EOPs are obtained from an external entity the Earth Orientation and Reference Service (IERS). The goal of this activity is the development of ESA capability for the estimation and prediction of Earth Orientation Parameter in order to become independent of external services. Several aspects related to this subject topic need to be investigated and further developed. Of particular concern are the following topics:
- The estimation of EOPs based on the combination of different complementary observation types such as SLR, VLBI and GNSS. The study shall analyse the difficulties resulting from the combined processing of different observation types and their contribution to the individual global parameters. Different concept shall be proposed, implemented, prototyped and tested.
- The prediction of EOPs based on empirical and also physical modelling. The prediction of EOP is a very difficult area, which need fundamental development in order to obtain reliable results. In the frame of this activity, different concepts for the prediction of EOPs shall be developed, prototyped and tested. Deliverables
Prototype Application/Need Date
TRL 3 by 2017 Duration Current Target 24 1 3 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - 11 - Space Debris Programme T711-503GR TD 11 Reference Activity Title
Extension of the high-fidelity re-entry break-up simulation software based on new measurement types Objectives The objective of this activity is to bring the current generation of high-fidelity re-entry break-up simulation software in-line with the available observational data, taking into account demise properties of composite materials as ceramics or more specifically carbon-fibre reinforced polymers and the effects of re-radiation of one component on another during the re- entry break-up. Description The current generation of high-fidelity re-entry break-up simulation software is based on wind tunnel testing of different metallic materials and verified with scarce observational data. In recent years, studies have significantly increased the volume of available wind tunnel samples and in-situ observations of temperature distribution during the early phases of re-entry are available. Moreover, some on-ground fragments were recovered after uncontrolled re-entries and analysed. The modelling of polymer demise under atmospheric re-entry conditions based on a finite volume approach has been preliminary analysed and proof-of-concepts are available. This activity shall specifically target the demise of carbon-fibre reinforced polymers, which are heavily used in spacecraft or launcher design where there is a high degree of uncertainty on current state-of the-models. An increased interest in the demise properties of other composite materials. such as ceramics, has been identified during design for demise studies, as they behave very different during the re-entry phase than metals. The effects of re-radiation of one component on another during the re-entry break-up has only been experimentally addressed in some finite volume approaches. Now with the availability of experimental data, a new degree of confidence in the simulation software, and the effect on the on-ground risk, shall be obtained. The improvements and homogenisation of non-metallic material demise models and a large verification activity based on sampled and real world examples will benefit all projects related to satellite, launcher, and component development to assess compliance to the ESA space debris mitigation regulations. The issues stemming from the increased computationally complexity shall be addressed. Deliverables
Software Application/Need Date All ESA missions to be developed and under development, which have to demonstrate compliance to the on-ground risk mitigation requirements.
All studies under CleanSpace initiative, addressing the so-called design for demise methodology, were different tools and approaches are used to assess the efficiency of design choices for reducing the risk during re-entries.
TRL 5 by 2017 Duration Current Target 18 2 4 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 65 of 112
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7 - 12 - Ground Station Systems and Networks Programme T712-502GS TD 12 Reference Activity Title
X-Band Sampling Technology Demonstration Objectives The objective is the development of an analogue to digital converter able to sample RF signals directly at X-band (8 GHz). The benefit will be a ground station architectural simplification by removing frequency converter hardware and filters. As a consequence hardware procurement and maintenance costs will be minimized. The digital front end (including sampling, filtering and digital frequency conversion) can be easily reconfigured for each type of mission and will allow advanced concepts like interferer suppression to be realised. Description The direct sampling of 8 GHz signals will allow all the further signal processing to be conducted in the digital domain, thus implementing a Software Defined Radio (SDR) approach.
The sampling of 8 GHz signals will also allow sampling at 2 Ghz as a by-product. Ka-band (32 Ghz) and K-band (26 GHz) will still be converted to 8 GHz using a single fixed frequency conversion before RF sampling. X-band sampling will allow TTC for earth observation, science in deep space and near earth, and exploration missions in S- or X-band. The Earth Observation wideband payload data sampling (8.025-8.400 GHz) will be included.
The output of this activity will be a proof of concept of X-band sampling through validation at breadboard level.
Potential technologies are photonic time stretch pre-processor followed by multi Giga Sample Per Second (GSpS) Analog to Digital converter. (i.e. up to 5 GSpS available at Texas Instrument)
The tasks included in this activity are: - Define detailed requirements for RF sampling technology - Identify potential technologies and trade them off - Design a breadboard and manufacture it - Validate the performance of the breadboard at 8.5 GHz Deliverables
Breadboard Application/Need Date TTC for earth observation, science in deep space and near earth, and exploration missions in S or X band. Earth observation wideband payload data (8.025-8.400 GHz) will be included. Need date: TRL 4 by 2018; TRL6 by 2022 ; TRL9 by 2025 (for ESTRACK ground station replacement) Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - 13 - Automation, Telepresence & Robotics Programme T713-502MM TD 13 Reference Activity Title
COntrol and Management of Robotic for Active DEbris removal (COMRADE) Objectives The objective of the activity is provide a validated control system of a robotic spacecraft (tasked to perform an Active Debris Removal mission Description The activity shall address the definition, design coding, verification and validation of the mission vehicle management (MVM) software for the Active Debris Removal (ADR) mission. The activity shall comprise the control and management of the spacecraft in combination with the control and management of a robot arm used to grasp, stabilise and hold the target with the aim perform the controlled de-orbit The focus shall be in: - the increase of the compliance to the mission operational and technological constraints - the achievement of high levels of Reliability Availability and Safety of the control software The MVM shall be responsible for: - the control of the complete robotic spacecraft alone up to grasping, and the compound (i.e. robotic servicer + debris) in the following phases of ADR. - the selection and switching of control modes - the Failure Detection, Isolation and Recovery (FDIR). - the operation anomaly detection The following tasks shall be performed: - Consolidation of functional, operational, performance and environment requirements for the ADR mission taking into account the mission objectives and constraints. - Definition of the control architecture, including sensor suite trade-off. This architecture shall also comprise the design of the use and operational modes - Detailed definition and analysis of the control algorithms - Implementation of a Model In the Loop (MIL) simulator with the complete control system architecture - Validation of the simulator and performance tests. - Implementation of a Processor In the Loop (PIL) test bench consisting on the assembly of the modified MIL with a flight representative processing hardware. - Verification and validation with the PIL with all sensors emulated or with representative model units procured for this testing. - Implementation of two Hardware In the Loop (HIL) test benches consisting on the assembly of the PIL and a suitable robot arm on 1) air-bearing proximity testbed 2) dual-robot proximity testbed - verification and validation with the HIL. Deliverables
Software Application/Need Date
ADR: Clean Space/2016 (dDeorbit, eDeorbit) Duration Current Target 24 2 4 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap Automation & Robotics (2012) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
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7 - 15 - Mechanisms Programme T715-503MS TD 15 Reference Activity Title
Magnetically Clean Reaction Wheel Objectives The main objective of this activity is to identify technologies and design options of a magnetically clean reaction wheel and to demonstrate its feasibility through the testing of an elegant breadboard. Description Reaction wheels exhibit dominant magnetic field emissions that shall be reduced to allow the reaction wheel use on magnetically susceptible missions without negative impact on scientific objectives. Conventional reaction wheels use brushless DC motors with relatively high magnetic flux densities in large air gaps without any dedicated compensation or 'magnetic balancing' of the motor magnets. The motor external magnetic field together with contributions from further components, (ball bearings), combine to a significant magnetic dipole moment. Instruments to measure the magnetic fields are very sensitive to interference generated by the reaction wheels. With present designs, reaction wheels are either completely avoided in the spacecraft architecture (e.g. SWARM), or some degradation of the payload performances has to be accepted (e.g. Venus Express, BepiColombo or Solar Orbiter). Minimization of magnetic field effects may require fundamental internal design modifications with focus on the motor and parts made from ferromagnetic materials as primary contributors. The main configuration, the wheel drive electronics and especially spacecraft interfaces should preferably not be affected by such design modifications. With state-of-the-art magnetic system modelling and simulation software, the novel design options (reduction and/or compensation of magnetic sources, shielding, effectiveness of hardware 'de-perming', use of alternative materials, etc.) shall be studied and compared with the existing design status. Moreover, an optimisation of the magnetic design might also have positive effects on other parameters, e.g. reduction of air gaps in the magnetic circuit or reduction of eddy current induced losses, resulting in an increased efficiency and reduced power consumption. The implementation of the critical features in an early breadboard shall allow for preliminary testing and the necessary iterations. Finally, the improvements w.r.t. 'reduced magnetic signature' shall be demonstrated in a fully assembled elegant breadboard Model reaction wheel. The main steps of this activity are : 1) Review of the relevant missions and associated AC and DC magnetic requirements 2) Identify magnetic sources in existing space-qualified reaction wheels and summarize their overall magnetic performance. 3) Optimise magnetic design features using magnetic system modelling & simulation software tools, and perform trade- off analysis regarding other performance parameters and environmental conditions. 4) Implement the novel design options in early sub-assembly breadboards and verify their effectiveness 5) Integrate the new/modified design features in an Elegant Breadboard Model reaction wheel 6) Test the magnetic characteristics of the Elegant Breadboard Model before and after environmental testing 7) Verification of the effectiveness of any reaction wheel level treatments and that of any specific precautions during typical AIT activities including transport and storage. This shall include a mapping/inventory of potential sources that may lead to a re-magnetisation and any other inadvertent degradation of the magnetic signature 8) Critical review of the results and compliance with the requirements, elaboration of a development plan Deliverables
Engineering Model Application/Need Date All spacecraft requiring high magnetic cleanliness, especially solar system exploration / planetary science missions. Need date: TRL 5 by 2018 Duration Current Target 24 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap AOCS Sensors and Actuators (2009) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - 17 - Optoelectronics Programme T717-502MM TD 17 Reference Activity Title
Deep-Space Optical Communication compatible multifunction LIDAR Objectives The objective is to develop a LIDAR add-on system capable of supporting range finding, 3D imaging, velocimetry and lander/penetrator pointing in a laser communication terminal architecture, adding minimum infrastructure requirements. ESA's Asteroid Impact Mission (AIM) shall be used as baseline for the LIDAR implementation. Description A fibre-based deep space optical data terminal incorporates a seed laser, amplitude, frequency and / or phase modulator, optical amplifier and free-space beam forming optic. Provision is also made for coarse and fine pointing. For little additional Size Weigh and Power (SWaP), the architecture can be extended to that of a coherent Laser Imager Distance and Ranging LIDAR. Unlike conventional direct detection and photon counting schemes, it is relatively straightforward with coherent LIDAR to achieve quantum limited detection performance with unsophisticated detectors. In addition the technique is sensitive to optical phase. Availability of phase (and therefore frequency) information allows well established RF sensing and communication techniques to be exploited at optical wavelengths with the associated advantages of lightweight, reliable fibre-optic components and delivery, better directionality from smaller apertures, and higher bandwidths. A breadboard of the 3D imaging mode shall be developed along with convincing paper-based evidence that the other modes are realisable and could be added to the demonstrator. The LIDAR system shall be developed for implementation into the Asteroid Impact Mission (AIM) laser communication terminal (Optel-D) and be used for orbital altitudes between 10 and 100 km above the surface of the Asteroid. Deliverables
Breadboard Application/Need Date
TRL 7 by 2020 Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Lidar Critical Subsystems (2010) No Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
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7 - 18 - Aerothermodynamics Programme T718-503MP TD 18 Reference Activity Title Embedding of improved CFD Code developments into Multidisciplinary Analyses - Feasibility Assessment and Roadmap Development Objectives The objective of this activity is a detailed roadmap based on a thorough analysis of the requirements for numerical predictions methods and a thorough code assessment to improve software tools in terms of modelling and multidisciplinary analysis to calculate cryogenic fluid behaviour in sloshing tanks and cryogenic fuel systems. Description Computational Fluid Dynamics (CFD) codes have been successfully applied in many ESA projects to external flow problems, involving the aero(thermo)dynamic analysis of launch vehicles, as well as to spacecraft for planetary re-entry and landing. Flow regimes range from hypersonic down to transonic/subsonic Mach numbers. Expansion nozzles of propulsion systems require analysis of internal compressible flows for design and optimization, including detailed analysis of the interaction of thruster plumes with ambient sub- trans- or hypersonic flow fields. Today several CFD codes are available which allow for an accurate analysis of compressible flows of gas mixtures including possible chemical reaction between the gaseous species involved. Commercial codes often lack the required solution quality to ensure adequate results in case of highly specialized aerospace applications. Therefore, ESA has a strong interest in the continuous improvement of CFD-based design tools. Accurate prediction of the flow response of storable or cryogenic fuel in tanks of rocket stages of launchers or satellites to external excitations and the resulting GNC commanded AOCS actions and the effects of the resulting sloshing motion on space craft dynamics and the efficiency of GNC and AOCS systems is of high importance. Utilization of state of the art high performance computer infrastructures and the integration of new calculation approaches for incompressible and low Mach number flows for storable and cryogenic fluids, as well as the development of new models for the treatment of two-phase flows are required to accelerate and further optimize the overall spacecraft design process in the future. The specific tasks of the study are: 1- Dedicated assessment of required physical modelling and the related CFD codes suitable for the simulation of cryogenic flows. Downselection of most suitable methods and set of tool, also with respect to multidisciplinary analysis. 2- Selection and prioritization of disciplines to be interlinked with CFD code analyses. A tentative first list in order of priority includes interaction with: Structural /FSI; GNC and AOCS; Thermal analyses; Flight mechanics; Planning of work share for code development activity; Working out and coding of a first fluid dynamics and structural analysis interface so as to have a demonstrator case. 3- Documentation of the roadmap. Deliverables
Study Report Application/Need Date spacecrafts and launchers design Duration Current Target 6 1 2 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Aerothermodynamic Tools (2012) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 70 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 19 - Propulsion Programme T719-501MP TD 19 Reference Activity Title
Use of Iodine as propellant for Hall Effect Thrusters Objectives
A preliminary investigation on iodine as propellant for Hall effect thrusters Description Iodine as a propellant is considered a valid alternative to xenon for electric propulsion application, in particular on Hall effect thrusters. Several advantages when using iodine as opposed to xenon can be enumerated. Iodine and xenon atomic mass and first ionization energy are very close and thruster performances, in terms of thrust density, thrust efficiency and specific impulse, have proved to be almost the same. Iodine is solid at ambient temperature and pressure, with a density about four times the density of xenon stored at 200 bar of pressure and ambient temperature. Hence, the same the thrust mission, iodine requires for storage a smaller, not pressurized tank with respect to xenon. Gaseous iodine at low pressure (up to about 10 kPa) can be obtained by heating the solid propellant at relatively low temperature (up to about 100 °C). Iodine cost is currently 1/15 the cost of xenon and its availability can be considered unlimited for the proposed applications. The iodine condensability potentially reduces pumping requirements in vacuum facilities for on ground testing, yielding a cut in the development costs of the thrusters. However, many issues remain to be assessed before iodine can be widely adopted in space missions. Being a halogen, iodine is chemically active and is not compatible with several materials. Its tendency to condensate on surfaces implies a careful design of the propellant feeding line and thruster injection system, including the cathode. Moreover, spacecraft/plume interaction with the risks of iodine surface deposition and chemical aggression represents a critical issue to be thoroughly investigated.
The following tasks are included: 1) Design and manufacture a prototype of iodine feeding system (tank, heaters, valves, throttling and metering system), suitable for an existing, xenon fed, 100 W class Hall effect thruster, including the cathode. 2) Experimental assessment of the feeding system performances in terms of mass flow rate production and controllability. 3) Review and modify the design of the Hall effect thruster and the cathode, to be compatible for iodine operation (materials, injection systems, etc.) 4) Manufacture the modified thruster. 5) Integration of the thruster with the feeding system. 6) Test of the iodine fed thruster, aimed at a first experimental assessment of the operation and the performance of the propulsion system. Deliverables
Study Report Application/Need Date
any satellite using electric propulsion Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Electric Propulsion Technologies (2009) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 71 of 112
7 - Generic Technologies and Techniques
7 - 20 - Structures Programme T720-501MS TD 20 Reference Activity Title
Stress rupture prevention of composite high pressure vessels Objectives This activity aims to ensure continued safe operation of high pressure/energy COPV exposed to high pressure for long duration, while achieving low mass, through improved understanding of the stress rupture failure mode for CFRP materials. Description Composite overwrapped pressure vessels (COPV) are critical elements (both for safety and mission success) of many space missions. Rupture of such pressure vessels filled with gas at high pressure may result in loss of life or loss of mission and creation of a large amount of space debris due to release of a high amount of energy. This mandates a high level of design reliability. Stress-rupture (or static fatigue) is a sudden failure mode of the composite overwrap that can occur at normal operating pressures and temperatures, i.e. at stress levels below ultimate strength for an extended time. The failure mechanism is complex, not well understood, and difficult to accurately predict due to scatter or detect prior to failure. Many such pressure vessels undergo a significant pressure drop shortly after launch, which reduces the risk of stress rupture. However, in case of reusable systems, or systems that start operation after long delay (e.g. interplanetary missions) the time at or near design pressure can become very long. The stress at design pressure can be as high as 67% of ultimate strength (UTS) (for burst factor (BF) of 1.5). Stress rupture failures have been observed in accelerated test programs at NASA JSC for both Kevlar and carbon overwrapped COPVs. NASA stress rupture test programs are currently under way that should provide additional data availability in 2016, but not all of such test data may become available in Europe due to export restrictions, and the data may not address directly material systems used in Europe. Until test data is available, NASA recommends that the carbon fiber strain remain at or below 50% of the UTS (i.e. burst factor around 2.0!). Applicable pressure vessel standards and range safety requirements (esp. in USA) request that stress rupture risk be mitigated, without providing a clear methodology for compliance. Previous guidelines indicated that at 67% of UTS may in the worst case result in failure after 65 hours, for 10E6 hours lifetime the sustained stress may have to be below 58% of UTS (BF>1.7) The following tasks are included: - To evaluate the of the state-of-art in stress rupture descriptive models (several exist), including scaling laws, and related test data (including e.g. experience in hydrogen storage industry). - To evaluate the state-of-art in stress rupture testing, from strand/sample to sub-scale to full-scale vessel, real-time or accelerated. - To perform accelerated tests on simple specimens, applying well-defined stress levels (e.g. rings, simple sub-scale vessels with representative fibre pattern). Using a number of fibre-resin combinations relevant for European COPV. - To define recommended design and verification method to mitigate the risk of stress rupture. Make recommendations for further testing (e.g. full-scale, longer duration) if necessary for ESA missions. Deliverables
Study Report Application/Need Date High pressure vessels (COPV) of propulsion systems in general, but especially in long duration missions, and reusable systems. Need date ASAP (requirements exist in international standards, incl. USAF range safety). Duration Current Target 12 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Chemical Propulsion - Components (2012) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 72 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 21 - Thermal Programme T721-501MT TD 21 Reference Activity Title
Pulsating Heat Pipes Objectives The objective is to develop Pulsating Heat Pipes that can be embedded into Aluminium, Low-CTE Metals, CFRP, FR4 in order to increase the in-plane thermal conductivity Description Pulsating Heat Pipes (PHPs), when embedded into structures, have the potential to increase significantly the in plane thermal conductivity and to maximise heat spreading. The method of transporting heat from point A to B is completely different from conventional heat pipes. Because no complex capillary meshes are necessary, PHPs can be manufactured with small diameter tubing and a layout in a serpentine shape routing where the fluid pulsates between the hot and the cold section. Thanks to this small diameter (when compared to heat pipes) and possibly use of low Coefficient of Thermal Expansion tubing, they are in principle easier to embed into a thin low CTE laminate. In addition, PHPs fluid selection criteria are not the same as for conventional heat pipes and 'greener' fluids could be used.
The applications for PHPs are wide, from direct chip cooling to Printed Circuit Board (PCB) enhanced thermal conductivity as well as enhanced thermal conductivity in metal and Carbon Fiber Reinforced Polymer (CFRP) structure.
Several space agencies have already been working on Pulsating Heat pipes and have managed to prove that such devices work in a zero-g environment. A few studies at national level have been carried out and it is now necessary to develop this technology at European level.
Within the proposed development activity, it is intended to performed the following work in order to deliver a tested Pulsating Heat Pipe EM that would be embedded within an Glass Fiber Reinforced Polymer (GFRP)and/or CFRP substrate: - Review of the state of the Art, - Review of requirements for various space applications - Material and fluid selection suitable to be embedded into glass and carbon reinforced substrates and operate at the desired temperature range, - Manufacturing and testing of substrates coupons with embedded Pipes - Design, manufacturing and performance testing of Pulsating Heat Pipe prototypes - Detailed design, manufacturing of an engineering model embedded into a GFRP and/or CFRP and tested under relevant environments. Deliverables
Engineering Model Application/Need Date
Generic Technology targeting Electronic boxes and heat spreader for CFRP panels Duration Current Target 24 1 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Two-Phase Heat Transport Systems (2009) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 73 of 112
7 - Generic Technologies and Techniques
7 - 22 - Environmental Control & Life Support (ECLS) and In Situ Resource Utilisation (ISRU) Programme T722-501MM TD 22 Reference Activity Title
Technology to quantify and qualify microbial contamination on surfaces Objectives It is proposed to study the feasibility and to develop a surface sample technology (i.e. between swabs and wipes surfaces samples and the analyser) in order to allow an automated quantification and identification of microbial contamination of flight hardware. This technology will allow to avoid human handling and consequently reduce the risks of microbial contamination. Description Microbial contamination is a generic risk concerning flight hardware degradation, Planetary Protection and potentially crew health. Material surface requires a proper control and monitoring of the microbial cleanliness level. Today, contact plates, swabs and wipes are used for surface sampling. Swabs and wipes samples include mandatory liquid transfer to further extract and detect microorganism. Today, automated miniaturized system, molecular-based, has been developed and offers the possibility to perform multiple laboratory functions on a complete integrated system (i.e. extraction of nucleic acids, amplification, detection). However, this concern only air samples and no technology is available to allow the transfer of surface samples. Existing know-how and technologies available in the field of microbiology, molecular biology, and biotechnologies will be reviewed. Based on this review, the feasibility to develop a technology for surface samples transfer (i.e. small and large volume) will be studied. A design will be proposed and prototype will be manufactured and tested and validated. Swabs and wipes samples from ESA clean rooms and from Planetary Protection project (i.e. ExoMars) can be used. Preliminary concept for future space application will be proposed, critical issues will be identified including technical and safety challenges. Deliverables
Prototype Application/Need Date
Human Exploration, Planetary Protection Duration Current Target 24 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 74 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 24 - Materials and Processes Programme T724-506QT TD 24 Reference Activity Title
Modelling and Simulation of Electronic Assemblies Objectives The objectives of this activity are the development of efficient modelling and simulation techniques predicting the effect of a system's design on its reliability performance and the definition of soldering verification test conditions and pass fail criteria especially for new packages and solder joint geometries Description Efficient modelling and simulation techniques are needed to help predicting the effect of a systems design on its reliability performance. In addition, utilising computational simulations can help to reduce the cost of reliability evaluations for new generation packages and solder materials. Assessment of solder joint reliability in thermal cycling is based on the application of lifetime prediction models. The model generally used by ESA and space industry is the Norris-Landzberg model (modified Coffin-Manson). This model is currently applied in defining accelerated testing regime for all types of assembly configurations and different types of mission profiles. The ever increasing availability of new packages raises concerns on the applicability of this general model to different types of devices and solder joint geometries. Missions for the exploration of the solar system have very different thermal profiles, ranging from very large change of temperature (e.g. rover for planetary exploration) to cycles with very long dwell times (e.g. Solar Orbiter). Different field conditions can trigger different types of failure mechanisms and this should be taken into consideration in the definition of the accelerated testing. Currently only very limited guidelines are available to define limits to the application of the model and definition of the accelerated test conditions.
The questions which should be answered are: - How can the different mission profiles be handled? - How to deal with multi-stresses? - What is the best suited model for a given failure mechanism? - Which parameters are needed for calibrating models and how can they be extracted from experiments? - What tests are best suited for verification of lifetime results? - Formulation and validation of appropriate lifetime models for different mission conditions - Defining guidelines for the application of models to different types of devices
This activity should cover the following tasks: 1. To formulate and validate appropriate lifetime models for different mission conditions (ranging from very large change of temperature to cycles with very long dwell times) 2. To optimize the modelling and simulation processes 3. To define soldering verification test conditions and pass fail criteria 4. To define guidelines for the application of models to different types of device and solder joint geometries Deliverables
Other: study report, lifetime model, guidelines Application/Need Date
TRL 4 by 2018 Duration Current Target 24 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 75 of 112
7 - Generic Technologies and Techniques
7 - 24 - Materials and Processes Programme T724-507QT TD 24 Reference Activity Title
Contamination repellent coatings Objectives The objective of the activity is to evaluate the use of contamination repellent coatings such as to limit the deposition of molecular contamination on sensitive spacecraft materials (e.g. thermal control coatings, optical surfaces, solar cells, etc.). Description In-orbit molecular contamination can rapidly degrade the performance of sensitive sub-systems, such as optical instruments, thermal control surfaces and solar arrays. In existing spacecraft design, most of the effort is concerned with reducing the contamination potential at source e.g. by limiting high outgassing materials, reducing view factors between materials and the surfaces etc. However this is generally a very complex task, and, despite best efforts, contamination in-orbit cannot be fully eliminated. In addition, there is always some probability that an unforeseen contamination event can occur. Mitigation measures, such as decontamination heating can be attempted though not always successful. On the other hand, this issue would be much less worrying if the sensitive surfaces were able to 'resist' to contamination deposits. For such a reason, there could therefore be a fully justified interest to develop coatings which are intrinsically resistant to molecular contamination; this would permit to have most of the sensitive surfaces treated in such a way that contamination is repelled and does not stick to them. Previous studies provide already a certain level of confidence about the feasibility. For optical coatings in space, the activities related to laser induced contamination in high power lasers have shown that the porosity of the coating has a significant influence on the rate of contamination deposition, although not eliminating it completely (dense sputtered coatings are better than e-beam coatings). The effects of surface cross linking on the contamination resistance of a modified polymer surface has also been studied theoretically, and recent work by other investigators also suggests that a fluorinated self-assembled mono-layer coating can act to repel contamination from a surface. Following a review of the available potential techniques, the study should aim at identifying candidate material/coating combinations at first. It is expected that this will also involve modification of the physico-chemical surface of candidate coatings. As the coating thickness will be very thin, other properties shall not be influenced. Test samples of candidate materials should then be manufactured and tested under different controlled contaminating environments. In summary, the tasks to be performed include a review of potential techniques available, identification of candidate material/coating combinations, manufacture of test samples, and contamination susceptibility testing. The major system level benefits that are here identified are the following: - Easier achievement when strict cleanliness requirements are needed - Reduce system level needs for bake-outs if only way to achieve CC requirements - Ease of AIT activities (less prone to cleanliness effects) - In orbit commissioning could be reduced, i.e. a payload could operate earlier - Reduced de-contamination needs in orbit -> reduced power and complexity of design, longer operation time of payloads Deliverables
Study Report Application/Need Date
TRL 3 by 2019 Duration Current Target 24 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 76 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 25 - Quality, Dependability and Safety Programme T725-501QQ TD 25 Reference Activity Title
Redundancy Concepts for Minimum Mass and Acceptable Failure Protection. Objectives The objective of this study is to identify redundancy concepts avoiding passive, non-operating redundancies which allow for a graceful performance degradation in case of failures across all typical spacecraft platform functions, while addressing system mass and cost savings. Description The current redundancy approach is often intended to maintain or re-establish full functionality and performance capability in case of failure of a primary system or equipment. This naturally leads to build and carry system resources that may never be used in case the primary system works reliably throughout its operational life. On the other hand, alternative concepts exist which implement simply the capability of maintaining certain acceptable level of performance (i.e. graceful or acceptable degradation) in case the primary system fails. Instead of primary and secondary units each providing full functionality and performance capability, a set of units is used which all have to function actively to achieve full performance but provide a degraded performance or even functionality in case one or more of these units fails (i.e. performance-centred redundancy approaches). Such graceful degradation could also potentially satisfy the required functional and performance needs to achieve mission success while avoiding to carry passive, non-operating secondary units just for a potential failure case. This is of particular interest e.g. for spacecraft facing stringent mass and budget constraints. The main tasks are to first assess the possibility to implement the spacecraft's platform functionalities in terms of performance, and second to identify for each platform function the most suitable redundancy approach avoiding unused equipment in fault free condition while providing acceptable performance degradation in case of failure. Deliverables
Study Report Application/Need Date
All projects with stringent mass and/or budget constraints. Duration Current Target 18 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 77 of 112
7 - Generic Technologies and Techniques
7 - 25 - Quality, Dependability and Safety Programme T725-503QQ TD 25 Reference Activity Title
Reliability Model Enabling Satellite Life Extension and Safe Disposal. Objectives Spacecraft that survive their nominal lifetime are generally proposed for a mission extension to maximize their return on investment. The objective of this study is develop a spacecraft reliability degradation model and identify its required inputs to enable quantitative risk based decision-making on satellite life extension and safe disposal. The reliability degradation model may also be used to support on-board FDIR, diagnostics, and decision-making after long term storage. Description Estimates of the remaining spacecraft lifetime to support mission extensions decisions are currently made simply based on consumables (e.g. fuel) and basic unit degradation considerations. However, with ever increasing pressure to comply with space debris mitigation regulations (e.g. ECSS-U-AS-10C, ISO24113) more accurate quantitative reliability-based lifetime assessments are needed. A reliability degradation model will be developed to improve the understanding of the spacecraft transition from its useful life period (constant failure rate with time) to its wear out period (increasing failure rate with time) by accurately modelling degradation. The reliability degradation model shall take into account wear out mechanisms impacted by environmental stresses (e.g. radiation), use conditions (e.g. thermal and power cycles), and limited resources (e.g. propellant/consumables, power degradation over time). In addition, the study will identify the needs for appropriate built-in test/redundancy status monitoring, sensor/health status data gathering, and load cycling/usage surveillance systems for life-limited items required to provide sufficient input data to the reliability degradation model for accurate prognostic capabilities of the remaining satellite lifetime and its probability of successful disposal. Deliverables
Study Report Application/Need Date
All spacecrafts operating in protected LEO and GEO regions. Any other spacecraft facing a mission extension review. Duration Current Target 24 1 2 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 78 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 26 - Spacecraft Avionic System Programme T701-504ED TD 01 Reference Activity Title
Compact Reconfigurable Avionics : Reconfigurable Data Handling Core Objectives The Compact Reconfigurable Avionics activity aims at providing a flexible solution for small spacecrafts (typically 150 - 500 kg) allowing reducing the size of their Avionics (Data Handling Core and smart AOCS elements) while fulfilling hi- performance and defined reliability requirements. Within this frame, the objective of the Reconfigurable Data Handling Core development is to design and manufacture a module hosting a high performance microprocessor and high capacity reconfigurable FPGAs. The module will support standardised interfaces (Mil1553B, CAN, SpaceWire) and lower level digital interfaces (sensor buses) used natively or as a bridge to Analog interface devices. This module acts as the execution platform for the Compact Reconfigurable Avionics cross sectorial activity. Description The general approach while designing a Reconfigurable Avionics will follow the general principles: - Implementing by default most of the functions as SW - Using (slave) reprogrammable FPGA(s) as an accelerator to implement too CPU intensive functions - Providing a scalable and versatile I/O system supported by flexible SW drivers - Extending digital I/Os by Analogue Front-ends
The selected hardware platform is the combination of a powerful microprocessor and one or several high-end reconfigurable FPGAs, fulfilling the following needs: - Supporting exploratory and evolutionary designs according to mission needs during early development phases. The advantage at this stage is clearly to reduce costs thanks to using a flight representative and stable hardware platform based on SW defined functions off-loaded when required by blocks implemented in reprogrammable FPGAs - Allowing in-flight reconfigurations for the adaptation to different mission phases and modes. For instance, processing algorithms can be tuned according to evolving needs (science mission) or re-defined during the execution of the mission (e.g. for active de-orbiting). - Enabling a mission recuse in case of FDIR events or failures that could be rescued by a deep reconfiguration or the spacecraft core functions.
The activity consists in developing at EBB level a HW module hosting a high end microprocessor, FPGAs and corresponding support equipment. A selection of IP Cores taken from ESA's portfolio will be implemented and validated on the target. Eventually the Reconfigurable Data Handling core shall be part of the Compact Reconfigurable Avionics test bench installed in ESTEC's Avionics Lab. Deliverables
Prototype Application/Need Date
TRL 4 in 2017. Duration Current Target 18 2 4 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap Data Systems and On-Board Computers (2011) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 79 of 112
7 - Generic Technologies and Techniques
7 - 26 - Spacecraft Avionic System Programme T702-502SW TD 02 Reference Activity Title
Compact Reconfigurable Avionics : Model Based Avionics Design Objectives The activity aims to demonstrate the flexibility, reliability and usefulness of a highly configurable system developed by using Model Based Avionics engineering technology targeting hardware based on a combination of the upcoming multicore processors and large space qualified reconfigurable FPGA(s). The concept shall be demonstrated also for small spacecrafts (typically 150 - 500 kg) to reduce the size of their avionics while being reliable. The objective of the activity is (i) to analyse the architectural trade-off from a system stand point, in order to define the domain of reuse of such a solution, and (ii) to define and assemble the process, methods and tools (and demonstrator) allowing to configure the avionics. Description The hardware technology selected for the study replies to the following needs: - on-board reconfiguration where a mission needs different algorithms at different phases, or when a mission evolves in time, or new algorithms emerge, or when spacecraft contingency needs algorithm update. - on-board hardware support to offload the processor, - on ground, it serves the purpose of generic avionics which is configured and instantiated within some variability, that are configured in the FPGA. The availability of a generic configurable hardware solution allows to think avionics in terms of models that will generate artefacts to configure the hardware. In particular: - model based avionics definition, reusing the previous activity results, - model based software engineering, reusing results of the OSRA/Cordet line of activities - hardware software co-engineering and co-design, reusing results of previous activity - SAVOIR results such as the reference architecture, the standardized sensor/actuator interface, the Electronic Data Sheet mechanism, the IMA/Time and Space Partitioning. In addition, the use of such component raises avionics system level issues such as its impact on (i) the software architecture, (ii) FMECA/FDIR/Redundancy Management/Reconfiguration Module, (iii) operability, patching of FPGA, memory management of the image, etc. and (iv) the network system as the chip may embed routers The activity includes: 1 - definition of the system aspects of the use of a reconfigurable FPGA : a) elaboration of the use cases, definition of user needs, of requirements, of the domain of reuse and the configuration perimeter ; b) RAMS analysis, impact on FMECA/FDIR, reconfiguration policies ; c) Network aspects, role of routers, impact on pin out, configuration of routers, different bus for science and command & control or not, etc. ; d) Operability aspects, how to patch the hardware and associated software in an operational context. 2 - Model based technology: a) reuse and consolidation of the Space Component Model, integration with OSRA ; b) functional modelling techniques, including Matlab/Simulink for AOCS, state machines, etc. ; c) HW-SW co-design techniques reusing result of previous activity, updated with recent research in microelectronic. Interfacing with the models for co-generation of the SW and HW with consistent interface ; d) Consistent model based integration techniques based on the concept of software factory 3- Demonstrator : Using the hardware technology defined in the activity 'Reconfigurable Data Handling core' and the AOCS, sensor and actuators defined in the activity 'Smart AOCS elements', produce a demonstrator that can run in the TEC avionics lab. Deliverables Software Application/Need Date TRL 4 in 2017 Duration (Months) 18 Current TRL 2 Target TRL 4 SW Clause Operational S/W Applicable THAG Roadmap Avionics Embedded Systems (2010) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 80 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 26 - Spacecraft Avionic System Programme T705-504EC TD 05 Reference Activity Title
Compact Reconfigurable Avionics: Smart AOCS & GNC Elements Objectives The Compact Reconfigurable Avionics aims at providing a flexible solution for small spacecraft (typically 150 - 500 kg) allowing to reduce the size of their Avionics (Data Handling Core and smart AOCS elements) while fulfilling high performance and defined reliability requirements. The objective of this activity is to analyse the best possible avionics architecture able to implement AOCS & GNC functional chains with reliable sensors and actuators in a compact and reconfigurable way. Description In 2009, the Nanosat study recommended a high degree of integration between data handling, AOCS and power distribution. Meanwhile, industry has come with innovate solutions where AOCS sensors are miniaturised and can be progressively introduced fully or partially in the central processor, typically coarse gyros, GNSS receivers or the processing part of the Star Trackers, leaving only optical heads or GNSS antennas to be accommodated as external units.
The main tasks of this activity shall cover:
a) the identification of candidate European sensors, off-the-shelf or to be developed, which have the potential to be miniaturised and integrated (star tracker, sun sensor, gyro, accelerometer, optical navigation sensor, magnetic torquers); b) the selection of one candidate AOCS configuration, able to serve a large number of missions in LEO, MEO and GEO (Earth Observation, Telecom, Navigation) and one candidate GNC configuration able to serve a large number of in-orbit servicing (including Clean Space) and Exploration missions; c) the review of electrical and functional interfaces between these units and an innovative Reconfigurable Data Handling Core (powerful microprocessor and one or several high-end reprogrammable FPGAs) and the optimised partitioning of hardware / software elements of the AOCS & GNC functional chains, including redundancy and failure management; d) the high level definition of the various software algorithms, allowing as much as possible on-ground adaptation and in- flight reconfiguration; e) the prototyping of critical hardware and software elements, and adequate testing demonstrating the feasibility of HW miniaturization, integration and reconfigurability.
Eventually these elements will be part of the Compact Reconfigurable Avionics test bench installed in ESTEC Avionics Lab. Deliverables
Breadboard Application/Need Date
TRL4 in 2017 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap AOCS Sensors and Actuators (2009) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 81 of 112
7 - Generic Technologies and Techniques
7 - 27 - End to End System Design Processes Programme T708-501MT TD 08 Reference Activity Title
Improvement of methodologies for thermo-elastic predictions and verification Objectives The objectives are to improve and validate methodologies for end-to-end thermoelastic predictions and verification by analysis and test of Spacecraft structures and to improve predictive capabilities of the analyses, better quantify the associated uncertainties, and provide guidelines and solutions to allow verification by test. Description Predictive capability of thermo-elastic analyses for distortion (stability) and strength is not satisfactory, as shown by the recent examples of GAIA, Pleiades, Herschel, Planck, but also with the on-going work for BepiColombo and Solar Orbiter, while the requirements for stability keep getting more challenging. The analytical models are usually not correlated by tests on ground wrt to thermo-elastic predictive capability, hence the performance verification is limited to analyses and unacceptable/unquantified levels of uncertainty remain. The way to specify thermo-elastic stability and the margin philosophy to apply for distortion and strength performance also need to be improved. The verification of the system and mission end-to-end performance involves many different disciplines including overall system engineering and potentially different elements (platform, payload instruments, sensors, etc.). The study shall address the following topics: - Specification: derivation of the overall stability requirement to the different subsystems/disciplines, allocation of contributions (budgets) to the global performance and the way to specify performance requirements to the different disciplines/subsystem. - Worst case determination - Margin philosophy (on the thermal, structural side as well as on final end-to-end performance) with the understanding of what the typical margins in each domain cover - Uncertainty assessment / predictive capability of the analyses - Data exchange between thermal, structural and optical models and traceability / validation of the transfer of data between the different models. Validation of the engineering processes used. - Way to report from a discipline point of view thermo-elastic performance with the objective of overall end to end performance consolidation at system level (e.g. how to account for uncertainties, systematic and random contributions). - Aspects of the thermal and mechanical modelling and analyses that need particular attention for thermoelastic cases (e.g. structure temperature rather than unit temperature / flexibility in the connections in the structural model) - Identification of best verification strategy, considering contributions obtained through analysis, test capabilities, model calibration; in order to achieve the necessary predictive maturity at system level; specific requirements for model correlation The study shall focus on spacecraft and instruments, and adopt a truly multidisciplinary approach. The study shall make use of the lessons learned and experience on past projects. Analytical methods shall be studied considering uncertainty analyses by e.g. stochastic approaches to identify the critical modelling parameters that influence the results and quantify uncertainties. Test methods shall be identified together with their accuracy, constraints and level of maturity. The methodology and test methods shall be validated by a test on a mockups/existing structures (e.g. STM). The study shall provide guidelines to improve the thermo-elastic predictions and verification. Deliverables
Study Report Application/Need Date
All S/Cs. Need date: asap (no specific mission identified, but Euclid could already benefit)
Duration (Months) 24 Current TRL 2 Target TRL 4 SW Clause N/A Applicable THAG Roadmap Thermal & Space Environment S/W Tools (2002) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 82 of 112 Activity Description
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 83 of 112
7 - Generic Technologies and Techniques
7 - 27 - End to End System Design Processes Programme T708-502GE TD 08 Reference Activity Title
Paperless E2E Ground Segment Engineering Objectives The objective is to develop the architecture of a collaborative, paperless and user-friendly environment targeted to ground segment system engineers, who do not necessarily have or need to have knowledge of formal modelling methodologies and languages. Description The activity shall be based on the Systems Engineering environment VSEE (Virtual Spacecraft Engineering Environment), which covers already the main functionality required for the specific systems engineering process. However, the requirements for the use in a highly concurrent and collaborative environment (such as the case in the Ground Segment Engineering context) are not adequately covered and need to be specifically addressed. In particular aspects concerning short data refresh cycles and concurrent data access need to be covered. In addition, it shall be necessary to define a framework to define front-ends (interfaces) for specific end-user profiles, in order to hide the complexity of the process and data-models underlying the toolset.
The study will therefore focus on: - Benchmarking of the technology to address the aspects of continuous, paperless collaboration - Benchmarking and trade-off for interface frameworks allowing to define a user-friendly environment, which screens out the end-user from formal modelling methodologies and languages as much as possible. The technology must integrate with the ones adopted for other relevant environments already developed by ESA, in particular the VSEE.
Based on these analyses, an overall tool architecture shall be defined. An Alpha version of an integrated environment for E2E ground segment systems engineering, spanning from the MOI (Mission Operation Infrastructure) reference architecture and baselines, to the MOI deployment for mission families and for specific missions within the mission families shall be developed, verified and validated based on a representative mission ground segment data sample. Such environment shall maximise continuous collaboration across ground segment teams and within these teams while implementing all Ground Segment engineering processes (ref. ECSS-E70), throughout the ground segment lifecycle. As mentioned above the architecture will maximise integration of technologies and environments already developed for e.g. the VSEE.
It is foreseen to evolve the Alpha version into a product for mission adoption under GSTP. Deliverables
Other: System design and software alpha version Application/Need Date All ground segment system engineering teams who engineer, deploy, integrate and validate the Mission Operations Infrastructure to serve space missions. Duration Current Target 18 3 4 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap System Data Repository (2014) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 84 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 27 - End to End System Design Processes Programme T708-506SW TD 08 Reference Activity Title
Application of co-simulation to support Test and Operations Objectives Develop a prototype of a Spacecraft Simulator that accurately models a spacecraft covering all engineering domains using co-simulation and that captures the most up-to-date project information in a consistent way to support Design and Development, specifically AIV and Operations phases. This simulator shall be used in the preparation of manual and automated test procedures. The simulator shall ultimately be able to run real-time in parallel, as a Digital Twin, with the actual hardware being tested or operated. It shall also enable the on-line comparison of results from hardware test on ground or in-orbit with simulator results and allow prediction of performance evolution, continuous health monitoring and, in case of deviations, early warnings. Description The approach is to develop a simulation model of the spacecraft already in early phases to support the specification and definition activities, and to evolve it to support Design and Development, specifically AIV and operations phases. Using co-simulation, high fidelity (physical) models or simulators from multiple sub-domains (thermal, power, mechanical) shall be linked. The Functional Mock-up Interface (FMI) for co-simulation is an interface standard from the automotive industry that should be considered. The simulator models shall be able to capture the most up-to-date and detailed project information establishing a configuration 'as flown'. The information used shall be consistent, allowing common overlapping data to be centralized. Different engineering domains have to be covered and simulated in a consistent way. The models must not only be representable on the observable parameters but also be realistic with respect of failures. This Simulator can be used in the Test preparation phase. In the AIV and Operational use case the Digital Twin will run in parallel to the real spacecraft mission. This means that at all times in these phases a representative system executable is available. The simulator shall be able to compare in real-time results from hardware test on ground or from operations in-orbit with simulated data and allow continuous health monitoring and in case of deviations early warning. The prototype shall demonstrate the selected technologies. Co-simulation is an approach for the joint simulation of models developed with different tools where each tool treats one part of a modular coupled problem and data exchange during execution is restricted to well defined communication points. Simulator coupling is used in various fields of application like automotive engineering, microelectronics, mechatronics etc. to ensure that models can be reused across disciplines. Run-time adaption or correlation of a simulator to the actual observed state is a new domain. Health monitoring and the diagnostics of non-nominal behaviour or failures during ground testing is currently done off- line and often not supported with simulators. One of the more generic benefits of a simulation spacecraft model is that it can be duplicated at low cost, to enable parallel preparation and testing thereby improving the overall schedule. It also allows testing of out-of-boundary or non-nominal conditions that are difficult or impossible to achieve with hardware on ground only. The activity shall identify the most suitable technologies concerning the co-simulation and information systems for the problems above. A demonstrator shall be built, using relevant project data. Instead of simulating a full spacecraft, a specific subsystem (instrument, sensor) could be targeted for the first prototype. Deliverables
Prototype Application/Need Date
2017 Duration Current Target 18 1 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap System Modelling and Simulation Tools (2012) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 85 of 112
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components Programme T723-501QT TD 23 Reference Activity Title
State of the art packaging techniques for high power applications Objectives The objectives are to investigate the potential, feasibility, of Ag sintering as a mounting medium and method for high power devices and to demonstrate the function and robustness of the technology for flight applications. Description Today device mounting with adhesives or brazed is limited in their thermal performances and process temperature. Hi power devices with new (GaN) technologies are pushing the current mounting and thermal management methods to the limits, it is therefore required to investigate potential improvement technologies, in this case having been developed and deployed in the automotive sector. Ag sintering is a process, which uses force/pressure/time at comparatively low temperatures to attach die to substrates or heat sinks. Initially the apparent claims for performance and applicability of the process shall be confirmed, then subsequently the process shall be demonstrated on suitable materials to confirm the findings, then the manufactured parts will be exposed to component level testing to validate the construction method. Deliverables
Other: Study reports and test results. Process information including critical parameters Application/Need Date
TRL 5 end 2018 Duration Current Target 18 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Critical RF Payload Technologies (2004) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 86 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components Programme T723-502QT TD 23 Reference Activity Title
Prototyping and characterization of optical isolators for visible wavelengths Objectives The objectives of this activity is to prototype, characterise and perform space assessment of an optical isolator for lasers in the visible range 600-1200nm. Description An isolator is an essential components in many laser application. It is used to reduce or eliminate the effects of optical feedback and reflections of the laser's own energy back onto itself. Feedback can cause a source to become unstable with amplitude fluctuation, frequency shift, mode hopping, noise, and even damage. In particular there is a need for low- loss isolators in the 600-1200nm range, which can also perform reliably at high laser power. This activity will start by performing a literature search and market search, followed by design, prototype and manufacture a laser isolator covering the visible to shortwave infrared range. The isolator is also required to perform reliably in space environment and therefore a preliminary space assessment will be part of the work. Deliverables
Engineering Model Application/Need Date Most space mission requiring the use of laser diodes. This covers E.O, science and telecom applications/required by 2017-18 Duration Current Target 30 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Optical Communication for Space (2012) No Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 87 of 112
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components Programme T723-504QT TD 23 Reference Activity Title
Humidity resistance assessment of MCT based IR detectors in open packages. Objectives This activity aims to perform humidity tests on Infrared detectors in order to understand corresponding failures modes and define relevant tests conditions in order to allow the use of open packages. Description Most of the visible range Charged Couple Devices (CCD) of the ESA instruments are simply attached to a ceramic carrier in an open package.
At the opposite, infrared (IR) detectors based on MCT (Mercury Cadmium Telluride) materials are commonly constituted of two chips bonded together and mounted in an hermetically sealed packages in order to prevent any humidity issues such as delamination, open or short circuits. However, the latest IR designs propose open cavity as a basis in order to improve performances, manufacturing yield and contribute to cost reduction. Therefore it is the responsibility to the space end users of the detectors to implement the needed actions to protect the device from humidity as long as necessary. Those measures, e.g. flushing with nitrogen or dry-air might increase the risk of electrical damages (e.g. Electrical Stress Discharge) and contamination. Therefore, there is a strong interest to characterize humidity sensitivity of IR detectors, to understand failure mode and to identify best practices considering AIT operation and long storage. The activity includes the following tasks : - To review the design of the current devices, - To manufacture the test vehicles - To define the test plan (i.e. test conditions for the humidity testing and the parameters to be characterised) - To perform the characterizations and the humidity tests. - To analyse the test results, understand the failures modes - To provide guidelines and best practices for IR detectors procurement and use Deliverables
Prototypes after testing, tests reports, failures analysis report, draft guideline for test method. Application/Need Date the issue is already a concern for current instrument Duration Current Target 18 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Technologies for Passive Millimetre & Submillimetre Roadmap No Roadmap Wave Instruments (2010) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 88 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components Programme T723-507QE TD 23 Reference Activity Title
Utilisation of the Proton Irradiation Facility at PSI for Component Radiation Studies Objectives To utilise, improve and maintain the capabilities of the PSI High Energy Proton irradiation test facility for the purpose of characterising Single Event Effects (SEE) and Displacement Damage (DD) effects in EEE components for flight on ESA missions and missions developed by European industry. Description This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and European space missions. Up to 240 hours per year of beam time is available free of charge on a priority basis for ESA. Additionally, a minimum of 500 hours per year is available for ESA sub-contractors, research institutes and other interested users at preferential hourly rates. The agency provides the facility with a detailed work programme of the test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency). Deliverables
Study Report Application/Need Date
January 2016
Duration Current Not Target Not 24 SW Clause N/A (Months) TRL Specified TRL Specified Applicable THAG Roadmap Microelectronics (2011) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 89 of 112
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components Programme T723-508QE TD 23 Reference Activity Title
Utilisation of the High Energy Heavy Ion Test Facility at JYFL for Component Radiation Studies Objectives To utilise, improve and maintain the capabilities of the RADEF High Energy Heavy Ion (HI) irradiation test facility for the purpose of characterising SEE effects in EEE components for flight on ESA missions and missions developed by European industry. Description This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and European space missions. Up to 240 hours per year of beam time is available free of charge on a priority basis for ESA. Additionally a minimum of 500 hours per year is available for ESA sub-contractors, research institutes and other interested users at preferential hourly rates. The agency provides the facility with a detailed work programme of the test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency). Deliverables
Study Report Application/Need Date
January 2016
Duration Current Not Target Not 24 SW Clause N/A (Months) TRL Specified TRL Specified Applicable THAG Roadmap Microelectronics (2011) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 90 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components Programme T723-509QE TD 23 Reference Activity Title
Utilisation of a Heavy and Light Ion Facility at UCL for Component Radiation Studies Objectives To utilise, improve and maintain the capabilities of the UCL Heavy Ion (HI) and Light Ion (LI) irradiation test facility for the purpose of characterising SEE effects in EEE components for flight on ESA missions and missions developed by European industry. Description This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and European space missions. Up to 360 hours per year of beam time is available free of charge on a priority basis for ESA. Additionally, a minimum of 500 hours per year is available for ESA sub-contractors, research institutes and other interested users at preferential hourly rates. The agency provides the facility with a detailed work programme of the test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency). Deliverables
Study Report Application/Need Date
January 2016
Duration Current Not Target Not 24 SW Clause N/A (Months) TRL Specified TRL Specified Applicable THAG Roadmap Microelectronics (2011) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 91 of 112
7 - Generic Technologies and Techniques
7 - 28 - Electronic Components Programme T723-510QT TD 23 Reference Activity Title
Improved robustness passive components for realisation of rad-hard GaN MMICs Objectives
The objective of this activity is to increase the SEB capability of UMS GH25 MIM capacitors from 35V to >90V Description UMS GH25 MMIC MIM capacitors are subject to burn out under the presence of heavy ions. A design of experiment set of manufacturing trials shall be undertaken to fabricate different MIM capacitor recipes/structures and test them for SEB robustness. Focus shall be given for MIM capacitor manufactured directly on the SiC substrate as underlying dielectric isolation layers are felt to be the root cause for the low SEB voltages observed to-date. Samples shall be tested for radiation robustness and if successful implemented on the GREAT2 X-band MMIC test vehicle and a possible flight opportunity sought (e.g. CNES next generation Myriade family). Deliverables
Other: Technical notes, test samples Application/Need Date
All application domains requiring the improved performance offered by GaN MMICs Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Critical RF Payload Technologies (2004) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 92 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 32 - Clean Space Programme T711-504GR TD 11 Reference Activity Title
Probabilistic assessment of re-entry break-up analyses and derived quantities Objectives The objective of the activity is to implement a probabilistic methodology to answer the questions on on-ground risk due to uncontrolled re-entries, taking into account the particularity of different break-up assessments, and provide the required confidence in the results. Description During the last decade a multitude of tools have been developed to analyses the break-up of space systems during the re-entry in the Earth's atmosphere. To protect the Earth population from elevated risk imposed by uncontrolled re- entries, guidelines have been proposed and implemented to limited the amount of pieces expected to reach ground during the re-entry. Studies have shown high levels of uncertainties associated with the usage of break-up analysis tools, leading to difficulties in assessing the risk and meeting project requirements on risk mitigation. All currently available break-up simulations are based on the assumption of scaling small scale material sample testing up to full scale components. This assumption has not been systematically tested due to inability to mimic re-entry conditions of larger- sized objects. The study foresees a systematic assessment of the uncertainty associated with the available re-entry break-up analysis tools from the point of the implemented physics, modelling, and assumptions. Systematic comparison of the differences between to available tools and identification of optimal application domain of each tool with the goal of minimising the uncertainties at equipment and system level. The analysis of publically available data is needed to support or adapt the hypothesis if small samples of wind tunnel testing can be scaled up. This results in per tool requirements on the modelling of components, and by extension space systems, as well as the recommended settings to reach the maximum concurrence which scarce physical sample data. The study will investigate the applicability of probabilistic assessment of the on-ground risk for space systems, and components thereof, aiming at on-ground risk analysis by means of confidence interval. Deliverables
Study Report Application/Need Date All ESA missions to be developed and under development, which have to demonstrate compliance to the on-ground risk mitigation requirements. Studies under CleanSpace initiative addressing design for demise methodology Design for Demise studies are already underway during 2015,, and some additional will follow until 2016. ESA's Space Debris Mitigation Guidelines include the on-ground risk assessment, and are due for update during 2016. Therefore this activity must complete by the end of 2016 in order to support ESA's obligation on space debris mitigation. TRL 5 by 2017 Duration Current Target 12 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 93 of 112
7 - Generic Technologies and Techniques
7 - 32 - Clean Space Programme T715-502MS TD 15 Reference Activity Title
REACH treatment of the pyrotechnics initiators powder Objectives This activity aims to identify a pyrotechnics initiator powder compliant with REACH regulation and with extended lifetime up to 20 years. Description The pyrotechnics initiators powder ,MIRA is under REACH concern. As of the 21/09/2017, the Ammonium Dichromate which is contained inside MIRA powder, will not be authorised anymore. Thus, Roxel, the manufacturer of MIRA, will not supply anymore the powder. The MIRA is used on-board Ariane5 (igniters, detonators, squibs) and on-board satellite pyro valves. In addition to the REACH issue, it shall be noticed that the lifetime of the MIRA is 12 years maximum. It is therefore mandatory to identify an alternative to replace the MIRA to solve both the REACH and the life time issue. Zirconium Potassium Perchlorate (ZPP) is considered as a good candidate as its lifetime could reach in principle 20 years based on the feedback from military industry (for example Herakles in France).
This activity includes the following tasks: - Trade-off of potential candidate powders (including ZPP) - Differential Scanning Calorimetry (DSC) tests on powders to derive the aging test parameters - Manufacturing of modified initiators with new powders - Aging test (simulating 20 years lifetime in space between -5 °C and 35 °C, including 6 months at 60 °C at end of life (enveloping case considering science, Earth observation and telecoms missions) => 2 months at 80 °C aging test for the manufactured initiators as an example) - Radiation test (total dose of 2.1 MRads representing an enveloping case based on science, Earth observation and telecoms missions) - Reduced reliability test (One shot test with firing at -160 °C) - Bomb test to demonstrate that the modified initiators can provide the same pressure in a booster charge equipped with propellant powder (GBSe powder or equivalent) Deliverables
Prototype Application/Need Date
TRL6 at 21/09/2017 Duration Current Target 6 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Pyrotechnic Devices (2013) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 94 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 32 - Clean Space Programme T715-506MS TD 15 Reference Activity Title
Assessment of design for demise approaches for reaction wheels Objectives The objectives of this activity are: - Detailed analysis on the behaviour of current, typical reaction wheel hardware during the re-entry, - Complementary testing (at material sample level) and investigation with respect to knowledge gaps, - Identification of viable design concepts to improve reaction wheels demisability through re-entry simulations. Description Following the implementation of Space Debris Mitigation requirements, a re-entering Spacecraft cannot pose an on- ground casualty risk higher than 10-4. If a spacecraft design poses a higher risk on ground it will be required to perform a controlled re-entry at the End of Life, with an enormous system level impact (e.g. the propellant mass can be 3 times bigger than what would be normally necessary for the operational life-time) and maybe even driving the launcher selection and therefore having a very significant cost impact (up to tens of millions of Euros).
Reaction Wheels have been recurrently identified in the systems level analysis and re-entry simulations as one of the typical satellite equipment surviving re-entry and therefore posing a risk on-ground. This risk is very significant for the overall system risk threshold, considering the number of reaction wheels on board of a spacecraft.
The current state-of-the-art Reaction Wheels models used to simulate the demise during the re-entry are too crude and do not allow to identify and assess the drivers for the design of more demisable Reaction Wheels. Furthermore, the knowledge on materials behaviour during re-entry is incomplete and limited to the most commonly used materials. This activity aims to develop and analyse detailed models of existing Reaction Wheels designs to be used in re-entry simulations, and to enhance the knowledge on materials as necessary to have a more accurate understanding of the drivers for the survivability of relevant parts & subassemblies in Reaction Wheels.
Furthermore, this activity shall also identify and analyse possible design changes leading to an improvement in the demisability (or predictability of their demisability) of reaction wheels, in response to the design drivers determined by the modelling. The implementation cost of any proposed changes shall be scoped, and any potential drawbacks with regard to reaction wheel competitiveness (price or performance) shall be identified and discussed. Deliverables
Study Report Application/Need Date
2020 for TRL 6 - Spacecraft in LEO, EOP Sentinels and Earth Explorer class Duration Current Target 9 1 2 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 95 of 112
7 - Generic Technologies and Techniques
7 - 32 - Clean Space Programme T724-501QT TD 24 Reference Activity Title
REACH obsolescence management for Materials & Processes Objectives This activity aims to develop a management tool with controlled access for the entire European space industry that targets materials, processes and consequently technologies facing obsolescence risk by environmental regulations. This will help to identify upstream and precursor elements at risk in the supply chain of spacecraft assemblies and to provide early or timely solutions to mitigate obsolescence. Description Increasing numbers of regulations in Europe (e.g. RoHS, REACH, CLP) are implemented targeting sustainable development, environmental impact and protection of human health. The most imminent implication is the possible obsolescence of qualified materials, processes and technologies, as manufacturers are forced to change materials compositions, alter manufacturing processes or take the decision to remove materials from the European market. The effects to the European Space programmes can be significant in terms of costly new product and process developments and space validation of alternative solutions increasing the schedule and cost risks. REACH exposure of the space industry is mapped through detailed analysis by the Materials and Processes Technology Board (MPTB) under participation of space industry, national space agencies, and ESA. This limits to date the effort to satellite platforms and launchers with direct communication to system integrators and large equipment manufacturers. Major contributors of innovation to space technologies cannot be covered by current efforts - i.e. SMEs - for two reasons, (i) because SMEs often do not have the resources to analyse long-term obsolescence risk by themselves and (ii) direct inclusion of European SMEs in the MPTB would go beyond reasonable scope, impart unreasonable overhead costs to the SMEs and render the MPTB unmanageable. Building on the understanding of upstream manufacturing process (GSP contract for first part of this activity) as well as the work of the MPTB, the current proposal shall focus on the development of a web-based obsolescence management tool including the following functionalities: - Controlled registration system - Allow registered users to verify the REACH status of their materials and processes used, and consequently allow early decisions of replacement and new developments triggered by obsolescence risk - Provide the possibility to include defined materials and processes by registered users into the tool and help them in monitoring their own products (semi-)automatically - Establish a communication link and discussion forum to ESA and the MPTB to address dedicated questions from industry, especially SMEs, on obsolescence risks - Allow to distribute dedicated information from ESA upstream to SMEs and lower tier suppliers via the registered user inventory - Allow ESA to establish a parametric analysis of affected materials and processes to guide new and innovative developments as inputs to R&D programmes, necessary to comply with environmental regulations in an early phase, and with this help European space industry to promote green technologies. Deliverables
Study report, software Application/Need Date
Q1 2018 Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 96 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 32 - Clean Space Programme T724-502QT TD 24 Reference Activity Title
Development of green polyurethane materials for use in spacecraft and launcher applications Objectives The activity aims to develop polyurethane formulations for coating and potting applications with reduced human toxicity by elimination of toxic isocyanate chemistry. This shall at the same time allow further performance enhancement compared to established materials (e.g. environmental stability, permeability, thermal resistance). Description Increasing numbers of regulations in Europe (e.g. RoHS, REACH) are implemented targeting sustainable development, environmental impact and protection of human health leading directly to obsolescence of qualified materials, processes and technologies, as manufacturers are forced to change materials compositions, alter manufacturing processes or take the decision to remove materials from the European market. The REACH roadmap for identification of future substances of very high concern (SVHC) indicates to target a wider range of isocyanates. These are pre-cursor substances for the manufacturing of polyurethanes, which are 2-component materials where the end-user may be exposed to the hazardous isocyanate component. This class of materials is widely used for space (coatings, potting, conformal coatings) and launcher (liners, insulation foam) applications. In anticipation of materials obsolescence in the coming years, the utilisation of green polyurethane chemistry should be pursued. Also, there is an on-going effort in Europe to find suitable substitutes for petrochemicals as raw/precursor material for composites and foams. Recycled polyurethane, a sustainable source, has the potential to offer an environmentally- friendly alternative and examples of research are the activities in the EU RECYPOL programme. Composites and foams are used extensively also in the space industry, even if it can be argued that the volumes are smaller than in other sectors of industry. Nevertheless, ESA is in the process of promoting the use of sustainable technology and considers that a timely approach to replacement of hazardous substances will avoid a crash action on obsolescence. The activity includes the following tasks: - Definition of performance requirements for polyurethanes used on spacecrafts and launch vehicles and formulation of three requirement sets targeting applications as conformal coating, thermal control coating, and foam insulation via spray-foaming. - Revision of state of the art for green and sustainable polyurethane chemistry, including the utilisation of non-toxic isocyanates as well as recycling from industrial production and possibly post-consumer waste. - Trade-off between potential for tailoring of polyurethane material and processing properties and system-level requirements. - Small scale formulation of green polyurethanes for the three target applications, screening testing, and performance optimisation. - Performance demonstration on small demonstrator concepts for the three target applications. Deliverables
Other: Study report, small demonstrator concepts Application/Need Date
TRL 5 by 2018 Duration Current Target 24 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 97 of 112
7 - Generic Technologies and Techniques
7 - 32 - Clean Space Programme T724-503QT TD 24 Reference Activity Title
Development and testing of materials combination and coatings to meet demisability requirements Objectives The objective of this activity is to improve the demisability of spacecraft through the development of material combinations, coatings and surface treatments. Description Demisability is the ability of a spacecraft to be ablated (or demised) during atmospheric re-entry. The risk of human casualty anywhere on Earth due to reentering debris with KE=>15J shall be less than 0.0001. Within the Cleanspace initiative, several TRP activities (covering system, materials, software and design aspects) are on-going with the aim of better understanding the fundamental demisability mechanisms and establish preliminary design for demise guidelines. The running TRP activities on the characterization of demisable materials have helped defining preliminary re-entry testing conditions and associated testing procedures. The intended activity will be based on previous TRP results and aimed at enhancing demisablity of critical space materials and developing and testing new materials combinations.
The activities to be performed shall be as follow:
- Several uncontrolled re-entry profiles from low Earth orbit satellites shall be considered and simulated with currently available software tools(This can be based on literature or IPR of the bidding consortium.) - Critical materials shall be identified -Materials combination shall be developed to meet demisability requirements derived from re-entry simulation campaign(e.g. metal matrix composites, fiber metal laminates, composites with thermoplastics matrix) - Coatings and surface treatments to be applied on critical materials to improve demisability shall be developed(coatings modifying physicochemical and optical properties of materials) - Demisability of the material combinations and the coated materials shall be tested (at coupons level) in Plasma Wind Tunnel test facilities. The test conditions shall be derivate from the re-entry simulations previously performed. The samples shall be tested in the ESA approved test houses following already developed ESA testing procedures. Deliverables
Study Report Application/Need Date
2017 Duration Current Target 18 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 98 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 33 - Space and Energy Programme T713-503MM TD 13 Reference Activity Title
NOvelty or Anomaly Hunter (NOAH) Objectives The subject activity aims at developing and demonstrating an on-board decision software that can make possible for a spacecraft to autonomously select, among the science data it collects, which data is worth retaining of transmitting to ground. Description Space probes are subject to memory/communication constraints that make them unable to deliver to scientists on Earth all the data that the probe could collect. Presently the approach to reduce data sending are: - limitation of the instrument data generation - compression of data (ideally lossless but often necessarily with loss) - arbitrary selection of the data acquisition time/location - arbitrary pruning due to obsolescence of data in the transmission queue All of the above measures can in principle render the spacecraft unable to detect important scientific phenomena it could be witnessing. Ideally the spacecraft should be capable of acquiring any data at any time and have the ability to sift through this data and find the data that has scientific value (so either a novelty or an anomaly) and hence store/send to ground that particular data with highest priority. The GSP/TRP activity 'Mobile Autonomous Scientist for Terrestrial and Extraterrestrial Research (MASTER)' has proven that it is possible to realise with present-day Artificial Intelligence technology a system that can find scientifically interest images in large set of images, when initially trained by scientists.
MASTER has been able to detect scientific interesting images in - an orbital case where it was trained by EO scientist to detect coastal algal blooms in multispectral EO images - a Mars rover application, where it was trained by a geologist to detect outcrops
Based on the technology demonstrated in MASTER the activity shall raise the TRL of the MASTER system towards flight applications. In particular the activity shall focus on: - reduction on the percentage of false negatives and false positives (target 90% true positives) - re-coding of the algorithms in a flight language (C/C++), as the initial implementation was in Matlab - coding of computing-critical algorithm parts into VHDL for FPGA implementation - implementation and demonstration on next-generation flight computer (featuring multicore Leon and BRAVE FPGA) Deliverables
Prototype Application/Need Date ExoMars post-mission (TRL 5 in 2018) Future generations of Earth Explorers Duration Current Target 18 2 3 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap Automation & Robotics (2012) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 99 of 112
7 - Generic Technologies and Techniques
7 - 33 - Space and Energy Programme T718-501MP TD 18 Reference Activity Title
Design and breadboard test of ultrasound technique Objectives Experimental identification of the potential and technical issues associated to the use of ultrasonic tomography for the characterisation of the sloshing motion of cryogenic flows. Description Here it is proposed to perform a system study for the design, built up and test of a breadboard set-up that includes the identification of the potential technical issues associated to ultrasonic tomography and cryogenic flows. A part of the study will be devoted also to the software required for the image processing. Tomographic techniques based on ultrasound are being available for 3D mapping of multiphase flows. If progresses are still needed for improving the image reconstruction algorithms as well as the sensor capabilities, valuable results have been already produced. The technique can be used to perform non-intrusive measurements within metallic vessels. The results obtained with ultrasound tomography highlight its capabilities not only at low holdups of gas or solid but also at high gas fractions since this methods is able to produce valuable results for slug flows in pipe. In particular for cryogenic flows, the ultrasound approach might be very attractive. However, the characteristics of the medium to be investigated need to be well known. Ultrasound methods are based on the acoustic impedance, which is based on the medium density and sound speed. They are well adapted to locate a liquid/gas interface. A last point to be analysed will be the safety of the technique to perform measurements in propergols tanks. Deliverables
Breadboard Application/Need Date spacecraft and launchers propellant tanks Duration Current Target 12 1 2 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Aerothermodynamic Tools (2012) Yes Roadmap Consistent?
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Annex II, page 100 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 33 - Space and Energy Programme T718-502MP TD 18 Reference Activity Title
Challenges related to the design of a reservoir for the transport of H2 Objectives This activity aims to perform the analysis and simulation of the kinetics of storage, extraction and diffusion of molecules and H atoms in solid and liquid materials with state-of-the-art methods, and the results will be used to evaluate the best conditions for the use of innovative materials for H storage. Description This activity proposes to implement a reference model for computer simulation of storage of H2 which takes into account the role of molecular excited states. Different materials will be studied as possible candidates (intermetallic compounds, hydrides, organic liquids, nanotubes) in accordance with the existing practice in industrial applications or proposing alternative materials. The study will look at the formation of H2 in excited states starting from the interaction between a gas of atomic hydrogen and hydride ions, its diffusion in the material, and the in situ formation of excited molecular states of H2 in specific storage materials. These hydrogen-rich compounds are commonly called chemical hydrides and the most accredited between them in industrial chemistry of the storage of hydrogen are the alkali hydrides, sodium borohydride, and organic liquids such as methanol, methylcyclohexane etc. Nanostructured materials will also be simulated. The main method used in these simulations is molecular dynamics. In the international scene such an approach has recently led to the publication of several papers on important journals, highlighting the growing interest in the computer simulation of materials for hydrogen storage. The strength of this project lies on the fact that for the first time the molecular excited states shall be analysed in such simulations. Further, the mathematical approach will be validated with help of selected experimental test cases provided by and in coordination with ARTES 5.2 4D.024. Once the code has been validated, it shall be applied to a choice of materials used as storers vast and heterogeneous: in this way the simulations will lead to direct and effective cataloguing of the storage efficiency of each material, together with new suggested alternative ones. Deliverables
Study Report Application/Need Date spacecraft and launchers fuel tanks. In particular, H2 storage is a key element for fuel cell roadmap for telecom. According to ARTES this activity would be an asset. Duration Current Target 36 1 2 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Aerothermodynamic Tools (2012) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 101 of 112
7 - Generic Technologies and Techniques
7 - 33 - Space and Energy Programme T721-503MT TD 21 Reference Activity Title
Continuous Temperature Measurement Technique - Application to a Self-Regulating Heating Cable Objectives Develop a technique to measure the temperature along a heating line and to detect accurately the exact location of local variations (hot spot, cold spot, partial failure). The technique will be applied to self-regulating cables. Description With the current technology e.g. foil heaters, the continuous measurement of the temperature along any heating line is impossible. Scarce measurements are done by thermistors mounted beside the line at pre-defined locations. If the problem or local variation occur far from the thermistor location, it is impossible to detect the location but also to find easily the cause of the variation or of the local partial failure. The identification will be time consuming, quite uncertain in the outcome and will require costly tests. It is proposed to investigate and to trade-off new measurement techniques such as Frequency or Time Domain Reflectometry (FDR/TDR) among others in order to measure the temperature at any point of a heating line and to use it for the self-regulating cables. To this aim, the technique will require a sensing line. Depending upon the measurement technique, the sensing line may be physically separated from the heating cable or better integrated inside. The study shall predict by mathematical modelling the behaviour of the cable together with the sensing line. It shall manufactured and tested the necessary materials, and the breadboard model of the cable and sensing line. Deliverables
Other: Study report on the investigated techniques + S/W mathematical models + breadboard models Application/Need Date
TRL3 by 2018 Duration Current Target 24 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 102 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 35 - Technologies Enabling Breakthroughs in Science Programme T712-503GS TD 12 Reference Activity Title
Highly Selective Filter System for Optical Antennas Objectives The objective is to assess the most optimum and cost-efficient spectral filtering technique with a bandwidth of a few Angstroem (potentially a narrower, tunable bandwidth to account for the Doppler shift) with high throughput (> 60%) best adapted to a given design of an optical ground antenna and develop a demonstrator prototype for the 1550nm wavelength band. The benefit consists in maximizing the contact duration with the satellite by being able to operate as close to the Sun as possible. Description The spectral filter is a critical element to reject unwanted background and straylight onto the receive detector during day and night operation. The activity consists in elaborating its optimized design (interference filters vs. fiber Bragg gratings vs. volume Bragg gratings) after trade-offs taking into account the overall design of the optical antenna (e.g. numerical aperture of the beam, tunability vs. spectral width, etc.). The overall cost will depend on the performance(selectivity, out-of-band rejection and in-band throughput) of the filter system, which is a significant driver for the surface quality requirements mainly of the primary mirror.
It is a fundamental building block for optical antennas serving (future) missions in all domains (Earth Observations, Science, Telecommunications) that would employ optical links. Asteroid Impact Mission (AIM; launch 2020, Didymos rendez-vous 2022) presents a strategic demonstration opportunity either on ESA's OGS on Tenerife, or on an existing astronomical telescope by providing the optical receiver chain to the site (including the optical filter as one key element). Deliverables
Prototype Application/Need Date TRL 6 by 2020 Very opportune to support the Asteroid Impact Mission presently under Phase A/B1 study. Duration Current Target 20 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Optical Communication for Space (2012) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 103 of 112
7 - Generic Technologies and Techniques
7 - 35 - Technologies Enabling Breakthroughs in Science Programme T717-501MM TD 17 Reference Activity Title
All-optical diffractive element approach to compact, simple, rapid BEC creation in space Objectives First to build an optically streamlined, G-MOT system and sub-Doppler cool dense atomic clouds Then to load the dense ultracold atoms into a conservative optical dipole trap and evaporate to BEC Description A crucial benefit of metrological experiments in space is the extended measurement time, which can only be fully utilized when using specially prepared ultra-cold atomic samples, Bose-Einstein condensates (BECs), having the minimum temperatures allowed by quantum mechanics. By utilizing a new method using Grating Magneto-Optical Traps (G- MOTs) which is fast, simple and compact, the generated BEC will be in an ideal format for space and terrestrial applications. An all-optical grating-based method provides a magnetic-field insensitive route to BEC, and in addition there is the potential for extension to simple optical lattice experiments which form the cornerstone of next generation quantum metrology and quantum computation. Future advanced metrological projects will be enabled: portable clocks and lattice clocks, magnetometers and atom interferometers. The utilization of G-MOTs with DipoleTrap-BECs (DT- BECs) combines two proven components into compact quantum technology. Laser cooled atomic samples have resulted in profound improvements in frequency metrology, however the technology is typically complex and bulky. Advances have been made in developing portable laser cooling apparatus, instilling the advantages of atoms in the micro-kelvin regime, as evidenced by on-going ESA projects in this area. However, simplifying the laser cooling procedures with micro-fabrication technology has, up to now, proved difficult. Micro-fabricated optical elements that greatly facilitate miniaturization of ultra-cold atom technology have recently been developed as part of a small ESA (TAS-TRP) project. Grating Magneto Optical Traps (MOTs) require only a single input beam-line, yet deliver 60 million cold Rb atoms from a cubic centimeter capture volume; comparable performance to an equivalent 6-beam trap and ten thousand times superior to prior micro-fabricated traps. Moreover, sub-Doppler temperatures can be reached in the same apparatus with similar total atom numbers, indicating the technology could be used for reaching high phase space densities ideal for creating quantum degenerate gases, or loading optical dipole traps and lattices. It is proposed to expand on this demonstrated diffractive optical technology towards a streamlined all- optical route to rapidly produce Bose-Einstein condensates (BECs) with a footprint and robust construction suitable for the first step to ultra-precision BEC atom interferometry in the harsh environment of space. This proposal represents the first phase of realizing this developmental vision, directly addressing the recent FTAP First Cycle recommendations (2012). Current high-repetition rate BEC experiments utilize two magneto-optical traps (MOTs), each requiring optical access along three perpendicular axes with five-six view-ports, and each fibered beam-line requires beam expansion and polarization optics. Moreover, magnetic chip traps typically require a vacuum-compatible electrical feed-through and specialized bonding. The same all-optical chip design offers a simple way to form phase-stable single-input-beam 3D optical lattices (for e.g. lattice clocks). These features, combined with simplicity of fabrication and operation, make this route to rapid BEC production a key advance in the development of high-accuracy, portable measurement devices. Deliverables
Breadboard Application/Need Date *TRL 5 by 2019 * depends on which sub-systems are selected to be developed to system level Duration Current Target 24 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Frequency & Time Generation and Distribution - Roadmap Yes Roadmap Space (2013) Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - Generic Technologies and Techniques
7 - 36 - Collaborative Activities Programme T710-502GF TD 10 Reference Activity Title
Future navigation concepts at small bodies Objectives The objective of the study is to come up with navigation concepts optimally tailored for the different types of near object operational scenarios needed by the future missions. Description Several missions requiring navigation in the vicinity of small bodies are currently in preparation at ESA like AIM (binary asteroid), Phootprint (Martian moon) and Cleanspace (non-cooperative debris) or are likely to be proposed in the coming years (Asteroid sample-return). With the Rosetta near comet navigation a solid experience has been gained to carry out these operations by a mainly ground-based approach using conventional Doppler and on-board optical measurements. Meanwhile, developments of on-board GNC algorithms and more advanced sensors are on-going which could improve these type of operations in the future. These concepts to be identified shall build on the experience gained with Rosetta. The use of new on-board sensors and GNC capabilities shall be included when appropriate in terms of science return, operational load, mission duration, on-board complexity, mass and cost as well as mission robustness. The study shall cover single and binary asteroids and comets as well as Martian moons. It shall address approach, far and close observation, lander delivery from distances down to a few 100 m and sample taking. It shall also cover the non- cooperative space debris, with approach, inspection and characterization Several promising operational concepts shall be defined in terms of on-board sensors, navigation tasks to be performed on-board by the GNC system or on-ground, tasks to be performed on-ground to support the on-board sensors and GNC system and interface between the ground and on-board system. The concepts shall cover the entire range between pure ground-based (a la Rosetta) and full autonomous approaches as considered by some industries. The following aspects of each concept will be analysed: - navigation performance - requirements on orbital strategies - timeline of operations - ground operational load - on-board processing load - sensor specification - mission robustness - cost for on-board sensors and GNC algorithms - cost for ground system development and operations Pro's and Cons of the different concepts will be identified, quantified and compared to come up with recommendations for the future missions. Deliverables
Study Report and Prototype S/W Application/Need Date Needed for future mission: AIM (TEC), Phobos-Sample-Return (SRE) and Cleanspace. The results (TRL 4) are needed by 2018 as input to spacecraft definition in terms of on-board sensors and GNC algorithms for e.g. AIM. Duration Current Target 18 2 4 SW Clause Operational S/W (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 105 of 112
7 - Generic Technologies and Techniques
7 - 36 - Collaborative Activities Programme T720-505MS TD 20 Reference Activity Title
Large Deployable Reflector for IOD preparation Objectives The objective of this activity is the detailed design and development of a large deployable reflector of 3 to 7 m projected aperture. The hardware definition shall be suitable for an In Orbit Demonstration to be proposed in a continuation activity. Description Unfurlable deployable antenna reflectors are commercially available from US suppliers. European developments have been carried out to TRL 4 for the deployable structure within GSP, TAS and TRP activities with a strong involvement of ESA and following the recommendations of the Large Deployable Antenna Working Group. European IPR has been demonstrated so far for 6 m aperture. In order to progress the TRL of all the critical elements and components not yet developed in running precursor activities a further step is required, in preparation of IOD. Currently the TRL is 4 for the deployable structure, 2 for the reflecting surface, 3 for the deployment devices.
The activity will start with a review of the potential platforms and launchers to be used for IOD and establish requirements and interface as targets for the EM design. These will include Earth Observation requirements. Critical breadboarding tasks will be performed to verify main functions and materials parameters related to environment (GEO and LEO). The activity will then aim at the design of the demonstrator reflector assembly and critical breadboarding of the elements with the lowest TRL, mainly the reflecting mesh with the shape control network, the deployment and hold down mechanisms and the deployable arm. The full reflector assembly will be designed and built. Functional testing, including deployment repeatability and shape accuracy will be performed.
Hardware to be produced during this activity are: - Breadboards for verification of functional and environmental requirements (including Earth Observation applications) - Demonstrator model of representative quality for a flight demonstrator, to be tested for deployment functions and main critical environments.
It is foreseen that the full testing (RF, structural, environmental) and eventual refurbishment for EQM or PFM will be covered in another activity. Deliverables
Breadboard Application/Need Date
TRL 6 by 2018 Duration Current Target 18 3 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Telecommunications Reflector Antennas (2009) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 106 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 36 - Collaborative Activities Programme T725-502QQ TD 25 Reference Activity Title
Quality Assessment of the new European Space FPGA Software Tools Objectives The objective of this activity is to define and to apply a methodology to assess, from a Quality perspective, these new SW Tools to ensure that they are fit for purpose and can evolve for future applications with sufficient Quality control. Description FPGAs are increasingly being used to implement complex and critical functions on-board the Satellite at both Platform and Payload level. The new European Space FPGA software tool chain is intended to be used in the end to end FPGA Development Lifecycle to ensure that the devices are correctly programmed, starting from the functional specification of the device behaviour through to the final Verification and Validation in the target environment. It is clear that these new Software Tools to be used in this process are fundamental to achieving the quality objectives of the programmed devices in flight. There are numerous instances of FPGAs used on board ESA satellites for a diverse range of applications, including: Mil1553B and SpaceWire interfaces, TMTC Decoders and LEON CPUs or other micro-controllers processors to name a few. The qualification of these programmed devices for use in space is based on an exhaustive Verification and Validation process that attempts to exercise a large set of Test Vectors to ensure that the device functionality, error handling and performance are correct. This end to end process to program and validate the custom devices often relies on proprietary tools that are not subject to a specific qualification exercise.
This study is to encompass the following activities:
- To define the approach and methodology to assess the SW Quality of the new European Space FPGA end-to-end Tool Chain. This shall define how the tools have been developed and maintained; how configuration control is applied; the validation of the tools with respect to the programmed hardware and its successful operation.
- To Apply the methodology and approach from Phase1 within the new European Space FPGA end to end Software Tool Chain. This will ensure that the tools are fit for their purpose and can evolve for future releases maintaining the Quality level. An important part of this phase will involve a Proof of Concept Demonstration based on the tool user manuals and Bench Marks obtained from test vehicles and ESA IP Cores. This will be based on specific Use Cases provided by ESA, as elements of an ESA portfolio of IP Cores. Deliverables
Other: Quality Assessment Methodology, Quality Assessment Report, Demonstrator Test Databases Environment. Application/Need Date Mission Critical platforms and payloads with high levels of complexity and autonomy; Future missions expecting to use the future European Space FPGA technology. Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Microelectronics (2011) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
Activity Description Annex II, page 107 of 112
7 - Generic Technologies and Techniques
7 - 36 - Collaborative Activities Programme T726-501ET TD 26 Reference Activity Title
Radio Frequency Interference Scenarios, Application Requirements and Counteraction Techniques Objectives The objective of this activity is to perform a detailed analysis of applications/services and related interfering scenarios in the areas of Telecommunications, Navigation and Earth Observation. Impacts of RFI shall be duly quantified and interference counteraction requirements shall be critically derived for each application/service, identifying potential synergies among multiple applications. Interference counteraction techniques and implementation options targeting the applications requirements shall be identified and preliminary assessed. Promising concepts for IOD opportunities shall be finally identified and preliminary defined Description Radio Frequency Interference (RFI) impact heavily on a wide variety of space applications/services belonging to different areas, such as Telecommunications, Navigation and Earth Observation. Despite the huge number of interfering signal types, a preliminary classification of Interference may be performed according to the nature of interfering sources: - Intentional interferences. The transmitting events are deliberately performed for attacking other systems (e.g., jamming, spoofing, etc.); - Unintentional interferences. The inference events are caused by signals of space/ground systems other than the interfered system or by signals intended for the interfered systems but transmitted with characteristics (e.g., frequency, polarisation, etc.) not compliant with the system requirements. Intentional interferences are typically in-band emissions, while the unintentional interference may be due to either in- band emissions or excessive out-of-band emissions from services in adjacent bands. The number of interfering events is going to dramatically increase over next years with the constant increase of satellites in orbit (e.g., SATCOM, Navigation and Earth Observation constellations in LEO/MEO), the congestion of already crowded frequency bands due to the new deployment of terrestrial and space systems and the current trend in reducing equipment and installation cost (mainly in commercial systems). In this respect, it should be noted that recent microwave images derived from the operation of Earth Observation passive sensors have shown an increasing number of events where the retrieved data are corrupted by interference. Extremely high levels of interference are experienced in purely passive frequency bands identified where any emissions from active services are prohibited. With SMOS mission, ESA has gained considerable experience in RFI detection, geo-location, flagging and mitigation. The importance of controlling and mitigating RFI is well-known among the satellite community and several stakeholders (including satellite operators, manufacturers and international organisations). They have been actively contributing to raise awareness on interference, coordinating among key players, proposing and promoting technical solutions. Effectively tackling interference is a complex task and should be performed at various levels. The levels reported below are considered generic enough to be valid for any application (i.e., Telecommunications, Navigation, Earth Observation), yet useful for identifying current gaps in technology and defining a comprehensive technology development strategy: - Interference monitoring: it consists in monitoring emissions over an identified frequency range; - Interference detection and isolation: including all steps required to extract the interfering signals; - Interference classification: estimation of main characteristics of interfering signals; - Interference localisation: estimation of location of interfering sources; - Interference mitigation: all steps to counteract the interfering signal (e.g., interference nulling). Despite the efforts of many engineers and researchers, each of the 5 identified interference countermeasure levels still presents major technical challenges to be solved in order to either cover a wider range of applications or to improve actual civil system performance or reduce cost and complexity of actual products/implementations. In this respect, it should be also noted that each RFI counteraction technique is typically based on several key assumptions (for instance, on the nature of interference scenario in terms of interfering signal characteristics such as bandwidth, power level, burstiness of the signal, etc..). Indeed, a one size fits all approach will not address all the interference counteraction levels. The activity shall focus on a comprehensive and detailed analysis of applications/services and related interfering scenarios in the areas of Telecommunications, Navigation and Earth Observation, with the aim of defining quantitatively interference counteraction requirements for each application/service. For the case of Earth Observation applications, the scenarios to be considered will include the communication links (TT&C and payload downlink) and the on-board microwave active or passive sensors. Potential synergies among multiple applications/services and/or domains (e.g., Telecommunications, Navigation and Earth Observation) shall be also duly identified.
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Annex II, page 108 of 112 Activity Description
As a final task, candidate interference counteraction techniques and implementation options shall be identified, analysed and preliminarily traded-off against requirements of each application/service. This comprehensive analysis shall be the basis for the definition of a RFI technology/techniques roadmap aiming at the implementation of the identified RFI techniques. Based on the outcomes of this analysis, a preliminary identification of In-Orbit Demonstration (IOD) opportunities shall be also carried out. This activity shall serve as the fundamental first step to be undertaken before initiating any further study or technological development activities.
The Study Logic of this activity can be summarised as follows: - Identification of applications and related interference scenarios for Telecommunication, Navigation and Earth Observation. A detailed assessment and quantification of RFI impact on identified applications/services shall be also carried out
- Definition of interference counteraction requirements for each identified Telecommunication, Navigation and Earth Observation communications and Earth Observation microwave sensing application. Potential synergies among applications shall be duly identified and summarised
- Survey of interference counteraction techniques and implementation options for SATCOM, Navigation and Earth Observation. A preliminary trade-off among the identified techniques and implementation options shall be carried out targeting the application requirements and synergies derived in Task 2
- Conclusions and recommendations for future activities for on-board, on-ground and hybrid (on-board/on-ground) processing techniques and implementation options. Promising concepts to be potentially put forward for In-Orbit Demonstration (IOD) opportunities shall be identified and preliminary defined. As necessary, the promising concepts requiring dedicated efforts in term of technology or implementation techniques, shall also be identified and preliminary defined. Applicability of the identified IOD concepts to additional applications, such as ship detection, shall be also preliminary investigated Deliverables
Study Report Application/Need Date
TRL 3 by 2017 Duration Current Target 18 1 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
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7 - Generic Technologies and Techniques
7 - 36 - Collaborative Activities Programme T726-502SY TD 26 Reference Activity Title
Multi-Disciplinary Design and Breadboarding of Technologies for Early Break-up of Spacecraft During Re-entry Objectives The objective of this activity is to identify, breadboard and perform initial tests on the most promising technologies and concepts, in the field of passive components, active mechanisms, joining techniques to support the implementation of Space Debris Mitigation measures in the area of Design for Demise. Description There is an increased attention to safeguarding Earth's orbital environment, as reflected by the number of relevant regulations that are being set forward. ESA has published an update of the Space Debris Mitigation (SDM) Policy for Agency Projects in March 2014. It is expected that in the near future more countries will adopt mandatory SDM requirements. ESA's Clean Space initiative has been promoting several engineering activities and technology developments at spacecraft platform level. Clean Space aims to support the compliance with the SDM requirements, hence improving the competitiveness of European industry in the global market Satellites operating in low Earth orbit (LEO) are the most impacted ones by the SDM requirements due to the de-orbit and re-entry requirements. In the case of an uncontrolled re-entry into the atmosphere, the spacecraft may not completely demise during this phase and its parts could reach the ground, posing a casualty risk. Furthermore, the activities carried out within the CleanSat initiative, in which European technology developments for space debris mitigation are coordinated, have shown that all Large Scale Integrators identified increased spacecraft demisability to be a key solution for LEO platforms to ensure compliance to the SDM requirements. Simulations have shown that an early break-up of the main structure of a spacecraft better exposes its parts to the aerothermodynamic forces and increases demisability. Previous studies have indicated that mechanisms and joining techniques of spacecraft main structures play a significant role in initializing this break-up event of the main structure. As a consequence, the following technologies shall be addressed : passive components / materials (e.g. based on shape memory alloys), active mechanisms (e.g. launch locks, active panel opening), joining techniques and joints (e.g. cleats, adhesives, bolted connection, rivet, welds, thermal expansion joints). For each of the technologies listed above, conceptual designs shall be elaborated, requirements for necessary technology developments shall be defined, and a breadboard of the selected technologies developed and tested. In addition, a comprehensive technology roadmap shall be derived for each selected technology. In detail, the activity includes the following tasks: - Establish a database of typical joining techniques and joints, active mechanisms and passive components / materials - Derive test conditions from re-entry simulation campaign results - Test current joining techniques and assess the impact of joints on the break-up event of spacecraft (e.g. through plasma wind tunnel testing) - Based on system level analysis of LEO platforms, establish a set of requirements for joining techniques as well as for the design of active mechanisms and passive components / materials to break up spacecraft structures during re-entry. - Establish possible concepts for joining techniques and joints, active mechanisms and passive components / materials - Perform a trade-off between and derive requirements for all identified concepts w.r.t. system level impact to recommend and select technologies - Develop and test breadboards for the selected technologies - Derive requirements and technology roadmaps for the technologies identified. Deliverables Breadboard Application/Need Date 2018/19 for TRL 6 Spacecraft in LEO (EOP Sentinels and Earth Explorer class) Duration Current Target 18 2 4 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
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7 - Generic Technologies and Techniques
7 - 38 - Advanced Manufacturing Programme T720-502MS TD 20 Reference Activity Title
Thin-Ply-Laminate Composite Structures Objectives Structural application of the new thin-ply composite technologies available for the improvement of mass and stability of spacecraft platform, payload and launcher composite structures. Characterization of mechanical, thermal and electrical properties for structural applications: shear panels, central cylinders, payload adapters, solar array substrates and antenna reflectors. Description Thin-ply products are becoming commercially available by European composite precursor material providers. E.g. thin- ply unidirectional and fabric prepregs are being produced with thicknesses 3 to 4 times lower than conventional prepregs. The providers announce preservation of stiffness, increase of strength by 20 % and stability improvement due to better homogeneity, resin-fiber micromechanical interactions and higher accuracy. Areal densities and thicknesses of unidirectional prepreg are declared as low as 15 gsm and 20 microns. The reduction of thickness allows for mass reduction by better tailoring the laminates during the structural design, especially of the loaded areas such as mechanical interfaces. It has been already understood in precursor activities that typical quasi-isotropic 3-ply laminates of conventional material are equivalent to 12-thin-ply laminates, preserving stiffness but with potential mass reduction and a clear improvement in strength. This requires confirmation for the several applications in sight, taking into account the specific design and performance requirements. Potential applications include spacecraft shear panels to be produced by prepreg technologies, cylinders produced by automatic processes such as tape placement, and specialized products such as solar array substrates, antenna reflectors and wave guides. In the case of highly demanding products such as antenna reflectors and mirrors, the additional aspects to investigate are the effect of thickness in depolarization, passive intermodulation and reflection losses. Phase 1 addressing the material characterization by samples at the level of prepreg product production and fibre or tape placement products, taking into account product requirements (mechanical, thermal and electrical). Phase 2 detailed design, manufacturing and testing of demonstrator models for two of the selected applications Deliverables
Breadboard Application/Need Date
TRL 5 by 2018 Duration Current Target 20 3 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap Composite Materials (2014) Yes Roadmap Consistent?
TRP WP/PP PLAN 2016 ESA/IPC(2015)3,add.5
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7 - 38 - Advanced Manufacturing Programme T724-504QT TD 24 Reference Activity Title
ESA Additive Manufacturing Benchmarking Objectives Understand/Optimize AM end-to-end manufacturing processes, benchmark European AM supply chain, provide training to the AM Space Community Description Additive Manufacturing, or 3D printing is seen as one of the key enabling technologies for Space applications. The basic principle of AM is that material is continuously added to obtain a fit-for-purpose hardware, as opposed to classical processes, where it is machined away from larger, semi-finished products. The technology is typically applied for reducing mass, lead time, or the number of parts for assemblies. The manufacture of parts for Space using AM is taking place already. However, current applications focus on secondary structures or other non-critical applications, manufactured on earth. For future missions, much more components could be manufactured using AM, also including primary structures or other mission-critical parts, even manufactured on orbit, unveiling the vast potential of AM regarding costs and performance. AM processes are complex with a number of parameters influencing the final parts quality. The effects of these parameters have to be assessed in order to lead to a standardisation of the technology. The center will therefore help ESA to: -Benchmark the European AM supply chain -Understand/Optimize AM end-to-end manufacturing processes -Understand/Optimize machines performances, feed stock, processing parameters -Support the standardising exercise of the AM technologies for space application -Reproduce/understand/resolve eventual failures occurring on ESA projects -Provide training to the AM European Space community
The activity includes the following tasks: - Assessment of impact of aluminium and titanium alloy powder quality on geometrical accuracy, physical, and mechanical properties - Investigation of the productivity, quality, and reproducibility of various metal Additive Manufacturing systems - Investigation of various post processing methods and their impact on mechanical properties (associated with cost). - Establishment of a design handbook for SLM and EBM process - Assess capabilities of Direct Metal Deposition (DMD) facilities Deliverables
Study Report Application/Need Date continuous need for a variety of developments at various TRL levels
Duration Current Not Target Not 36 SW Clause N/A (Months) TRL Specified TRL Specified Applicable THAG Roadmap Additive Manufacturing (2014) Yes Roadmap Consistent?
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016
Annex II, page 112 of 112 Activity Description
7 - Generic Technologies and Techniques
7 - 38 - Advanced Manufacturing Programme T724-508QT TD 24 Reference Activity Title
Curing on demand polymerisation by switchable stimulus Objectives The objective of the activity is the development of low-temperature curing resins with extended process/pot life suitable for CFRP manufacturing applications. Description Curing of polymers resins for CFRP composites is for the vast majority of cases stimulated through temperature, whereas the curing temperature is a trade-off between required pot-life, thermal properties, hardware compatibility, and mechanical performance. For example, a high curing temperature leads to very good thermal properties and allows long pot-life, but causes increased internal stress and distortion. Ideally the adhesive is processed as well as cured near room temperature (practically < 100°C), typically followed by a short post-cure. Such resins provide the additional benefit of lower energy consumption, but have a fundamental drawback of reduced pot-life. For manufacturing of large and/or complex shaped hardware, a long processing time or pot-life is required that cannot be achieved with preferred low- temperature curing adhesives. Advanced resin systems, so-called latent systems, show essentially no activity around room temperature, but react very fast after external stimulation, so-called cure on demand. The latter can be achieved by heating, photo irradiation, ultrasonic exposure, electron beam exposure, etc. Even with thermally induced latent systems, a storage stability at room temperature of several months can be achieved with curing temperatures as low as 80°C. Another attractive solution is the use of UV induced polymerisation by introducing the concept of frontal polymerisation. In this case the polymerisation is initiated on the surface of the adhesive, and the exothermic reaction creates a propagation front through the bulk material.
The following tasks are encompassed in this activity : - Revision of state of the art for cure on demand with various external stimuli, including temperature and radiation. - Requirement definition for low-temperature curing adhesives for composite manufacturing. - Resin development for two different initiation systems and performance optimisation following a trade-off materials performance, processing constraints, and hardware requirements. - Performance demonstration on small demonstrator concepts for the two initiator systems. Deliverables
Other: Study report, small demonstrator concepts Application/Need Date
2019 Duration Current Target 24 2 3 SW Clause N/A (Months) TRL TRL Applicable THAG Roadmap N/A N/A Roadmap Consistent?
TRP WORK/PROCUREMENT PLAN 2016-2017 ESA/IPC(2015)3,add.5
Activity Description Annex I, Annex III, page 1 of 5
ANNEX III
TRP WP/PP PLAN 2016
Justifications for Proposed Tendering Procedure
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016 Annex III, page 2 of 5 Justification for Proposed Tendering Procedure
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ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016 Justifications for Proposed Tendering Procedure Annex III, page 3 of 5
Justification for Proposed Tendering Procedure: C(R)
Industrial Policy Committee
TRP Firm Fixed Activity Title Previous (K€) Proposed Bidder Reference Price (K€) T724-503QT Development and testing of materials combination and 300 + 660 Fluid Gravity (GB), coatings to meet demisability requirements Belstead research (GB), AAC(AT), VKI (BE), IRS (DE), DLR Koln (DE), HTG (DE), OGI (AT)
Justification The activity shall be an open competition restricted to companies involved in the precursor activity T724-311QT 'Characterization of Demisable Materials' as the tests shall be performed within the same conditions and facilities. The Article 13.2.a of the ESA procurement regulations is applicable.
ESA/IPC(2015)3,add.5 TRP WP/PP PLAN 2016 Justifications for Proposed Tendering Procedure Annex III, page 4 of 5
Justification for Proposed Tendering Procedure: DN/C
Industrial Policy Committee
TRP Firm Fixed Activity Title Previous (K€) Proposed Bidder Reference Price (K€) T116-504MM Alternative polishing layers for a large breadboard mirror 500 + 620 RESOC (FR)
Justification This is a continuation of TRP activity T116-309MM 'Alternative polishing layers on ceramic materials for high performance optical mirrors' (ESA/IPC(2011)3,add.3 and ESA/IPC(2014)3. The activity aims at demonstrating the feasibility of the previously developed polishing layers on larger mirrors. The Article 14.1.c of the ESA Procurement Regulations is applicable.
ESA/IPC(2015)3, add.5 TRP WP/PP PLAN 2016 Justifications for Proposed Tendering Procedure Annex III, page 5 of 5
Justification for Proposed Tendering Procedure: DN/C
Industrial Policy Committee
TRP Firm Fixed Activity Title Previous (K€) Proposed Bidder Reference Price (K€) T117-504MM Multi-kHz, multi-beam single photon counting vegetation 500 + 500 cosine B.V. (NL), LiDAR Politecnico di Milano (IT), Logikon Labs (GR), Entner Elelctronics (AT), TU Wien (AT), ID Quantique (CH), Imperial College (GB)
Justification This activity is the continuation with the same consortium of the TRP activity T116-306MM 'Advanced Laser Ranging Technologies for Altimetry' (ESA/IPC(2011)3,add.5). In addition the integration of the Alexandrite laser from the Imperial College (GB) (Activity TRP T117- 411MM, ESA/IPC(2011)3,add.5) is envisaged. The Article 14.1.c of the ESA procurement regulations is applicable.