gstp-6 element 1 compendium of potential activities...

Prepared by TEC-TI Reference TEC-T/2013-028/NP Issue 1 Revision 2 Date of Issue 3-12-2013 Status Document Type Distribution

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GSTP-6 Element 1 Compendium of Potential Activities –Application-Specific Service Domains – SD1, SD3, SD4, SD6, SD8, SD9

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GSTP-6 E1 Compendium - SD1, SD3, SD4, SD6, SD8, SD9

Date 3-12-2013 Issue 1 Rev 2


Title

Issue 1 Revision 2

Author Date 3-12-2013

Approved by Date

Reason for change Issue Revision Date

Issue 1 Revision 2

Reason for change Date Pages Paragraph(s)

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Table of contents:

1 INTRODUCTION ................................................................................................................................ 42 SERVICE DOMAIN BACKGROUND ................................................................................................... 53 LIST OF ACTIVITIES ........................................................................................................................ 114 DESCRIPTION OF ACTIVITIES ........................................................................................................204.1 SD1- Earth Observation .................................................................................................................................................. 204.1.1 TD 6- RF Payload and Systems .................................................................................................................................... 204.1.2 TD 7- Electromagnetic Technologies and Techniques ................................................................................................. 234.1.3 TD 12- Ground Station System & Networking.............................................................................................................. 274.1.4 TD 16- Optics ................................................................................................................................................................ 304.1.5 TD 17- Optoelectronics .................................................................................................................................................. 334.1.6 TD 26 – Other: Earth Observation (Systems and ground) .......................................................................................... 344.2 SD3- Human Spaceflight ................................................................................................................................................. 474.2.1 TD 2- Space System Software ........................................................................................................................................ 474.2.2 TD 6- RF Payload and Systems .....................................................................................................................................494.2.3 TD 9- Mission Operations and Ground Data Systems ................................................................................................. 524.2.4 TD 12- Ground Station System & Networking.............................................................................................................. 544.2.5 TD 13- Automation, Telepresence & Robotics .............................................................................................................. 564.2.6 TD 14- Life & Physical Sciences ................................................................................................................................... 604.2.7 TD 22- Environmental Control Life Support (ECLS) and In-Situ Resource Utilisation (ISRU) ...............................694.3 SD4- Space Transportation ............................................................................................................................................. 714.3.1 TD 5- Space System Control .......................................................................................................................................... 714.3.2 TD 14- Life & Physical Sciences .................................................................................................................................... 734.3.3 TD 18 - Aerothermodynamics ....................................................................................................................................... 744.3.4 TD 19- Propulsion .......................................................................................................................................................... 764.4 SD6- Navigation ............................................................................................................................................................... 774.4.1 TD 6- RF Payload and Systems ..................................................................................................................................... 774.4.2 TD 7- Electromagnetic Technologies and Techniques ................................................................................................ 904.5 SD8- Space Situational Awareness .................................................................................................................................. 924.5.1 TD 4- Spacecraft Environment & Effects ...................................................................................................................... 924.5.2 TD 9- Mission Operations and Ground Data Systems ............................................................................................... 1054.5.3 TD 11- Space Debris ..................................................................................................................................................... 1074.5.4 TD 12- Ground Station System & Networking............................................................................................................. 1114.6 SD9 Robotic Exploration ............................................................................................................................................... 1144.6.1 TD 4 Spacecraft Environment and Effects ................................................................................................................. 1144.6.2 TD 5 Space System Control .......................................................................................................................................... 1154.6.3 TD 13 - Automation, Telepresence & Robotics ............................................................................................................ 1174.6.4 TD 15 - Mechanisms & Tribology ................................................................................................................................ 1184.6.5 TD 18 - Aerothermodynamics ..................................................................................................................................... 1194.6.6 TD 21- Thermal ............................................................................................................................................................ 120

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1 INTRODUCTION

During the Council meeting at Ministerial level held in November 2012, the sixth Period of the GSTP was presented (ESA/C(2012)199) and extensively subscribed by the GSTP Participating States with the following framework: GSTP-6 Element 1 - Support Technology Activities for Projects and Industry GSTP-6 Element 2 - Competitiveness GSTP-6 Element 3 - Technology Flight Opportunities GSTP-6 Element 4 - Precise Formation Flying Demonstration This document provides a list of candidate activities to the Work Plan of the GSTP-6 Element 1, following the process outlined in September 2012 IPC: ESA/IPC(2012)98 - Preparing the work plans for the GSTP-6 Element 1. As indicated in this referenced document, Technology development activities in ESA are organised in 9 service domains (SD) and 25 technology domains (TD). This pre-selection complements the GSTP-6 Element 1 – Compendium of Generic Technology Activities issued in February 2012 and corresponds to activities belonging to the following specific service domains:

Earth Observation (SD1) Human Spaceflight (SD3) Space Transportation (SD4) Navigation (SD6) Space Situation Awareness (SD8) Robotic Exploration (SD9)

According to the ESA-wide process described in ESA/IPC(2008)61 rev 1, the activities which are part of this compendium have been pre-selected following an intensive internal exercise started in May 2013 and which included programmatic screening, technical evaluation and consistency checking with technology strategy and THAG Roadmaps. This compendium includes the list and description of 76 activities which are intended to be started in 2014. This compendium is issued to Delegations of GSTP-6 Participating States and their industries for comments. Such comments will be considered in the following updates of the work plan for this GSTP 6 Element 1. The objective is to have a good indication of the developments the Participants intend to support in order to present updates of the GSTP-6 E1 Work Plan with consolidated set of activities to the IPC for approval.

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2 SERVICE DOMAIN BACKGROUND

SD1 – Earth Observation

Background and Main Considerations for Technology Development

Earth Observation is based on the dual mission strategy consisting of two classes of related user driven missions: • Earth Explorer: Earth research oriented missions and missions to demonstrate

new observation techniques prior to operational use; • Earth Watch: operational service driven missions, including operational

meteorology and Copernicus/GMES. Earth Explorer Missions: Four Earth Explorer missions, GOCE, SMOS, Cryosat and SWARM, were launched, providing Europe with new EO capabilities. The developments continue within the ADM-Aeolus and EarthCARE projects, which will provide Europe with new capabilities for advanced active and passive sensors. At the May 2013 PB-EO, the EE- 7 Candidate mission BIOMASS was selected as the 7th Earth Explorer to be implemented. The Call for Proposals for Earth Explorer Opportunity Mission EE-8 was released in 2009, requiring proposed concepts with a high level of technical maturity. This is confirmed by the selection of CarbonSat and FLEX for phase A/B1 studies. Technology development needs are low and are more of a bridging nature. Earth Watch Missions: Concerning Earth Watch and operational meteorology, the Meteosat Second Generation and MetOp satellites continue providing uninterrupted services, while development has been initiated for the next generations. The developments of the Meteosat Third Generation (MTG) as well as MetOp Second Generation (MetOp SG) satellites have started and the projects are now in the implementation phase. As for Copernicus (GMES), the development of the first generation of Sentinels is ongoing with the launches of the A-satellites start in 2014. The needs for future operational missions to complement the Sentinels, in particular in the area of Security, and to prepare the next generation of Sentinels and associated missions are considered in current and near future technology developments. Technology Requirements: Technology development requirements as formulated in the EO Technology Challenges and Plans are still valid. They are focusing on the identified potential ESA EO missions. Future missions are expected to be proposed in response to calls for proposals for Earth Explorer 9 and beyond. The EE 9 call is expected in 2014. The strategic emphasis is on payload and data exploitation technologies. Platform technology is generally covered under generic technology, with the exception of specific payload data handling and transmission systems (e.g. Ka-band equipment) and specific AOCS items (e.g. electrical propulsion). Payload technologies are sometimes common to several service domains, such as EO, Science, Exploration, and Telecom. It is essential to benefit from commonality of needs.

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Technology in the Earth Observation service domain should allow to: • Enable new science, develop new observation techniques and enable cost-effective

missions providing operational services • Cut development, operations and overall costs, by e.g. increasing on-board and

ground operations autonomy, improving on-board and ground segment standardisation (also for interoperability across ESA and non-ESA missions)

• Ensure synergy with other domains (e.g. space science or telecom) Activities in this Compendium

Activities addressed in Earth Observation are related to three topics: RF, Optics, and EO Systems and Ground segment. The breakdown by topics is given in the table.

SD1 Topics number of activities Technology Domains RF 9 TD 6, 7 , 12

Optics 3 TD 16, 17 Systems and Ground Segment 9 TD 26

Table 1: Breakdown of SD1 activities by topics

SD3 – Human Spaceflight and Exploration

Background and Main Considerations for Technology Development

The aim is to ensure a continuation of European activity regarding humans in space, building on the Columbus and ATV programmes, the broader European participation to the International Space Station (ISS) and by preparing the next steps in European Human Spaceflight and Exploration. There are two main inter-related action areas, ISS utilisation and the preparation for Human Exploration. ISS utilization: These activities include the use of the Columbus laboratory and the production and operation of the ATVs. Payloads, developed under ELIPS, will include some minor technology development. Preparation for Human Exploration: Exploration may be defined as the combination of robotic and human activities for the discovery of the solar system. Exploration (especially Human Exploration) poses new challenges for space systems: • Complex system-of-systems, operating without failure and zero maintenance • Long travel time and operation in confined spacecraft and shelters • New operational capabilities: rendezvous/docking, descent, landing, ascent… • Extremely hostile environment of space, long nights, dusty atmosphere • Far from Earth, limited ground support and logistics, long telecom delays… • Large “snowball effect”: 1 kg back to Earth means many kg at launch Such challenges will require major breakthroughs: • New methods/tools for complex systems engineering, verification and validation • A dramatic need to increase efficiency in terms of performance / resources

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• A new approach to operations, autonomy, human–robot interactions, habitats, energy generation and storage, propulsion and propellants, life support systems

• Breakthroughs in health monitoring, physiology, diagnosis and medicine Considerations for technology development: The ISS is being used for research and is also planned to be used as a demonstration test bed for new exploration related technologies. A Lunar Exploration Activities programme is under development, building on the Lunar Lander Phase B1 results. Main technology development requirements are linked to enhancing technologies for the utilisation of human exploration means, preparing Lunar Exploration Activities and, in a broader sense, human spaceflight and exploration. Activities are organised in 4 main topics: • Robotics assistance and tele-robotics • Life and physical Science • Human spaceflight and exploration preparation • Lunar landing missions The Robotics assistance and tele-robotics topic supports the development of ISS experiments/demonstrators and other related Human Exploration Activities. The Life and physical science topic supports the development of experiments and astronaut medical/health devices, treatments and monitoring tools. The Human spaceflight and exploration preparation topic addresses technological issues related to supporting and protecting human life in space. They include areas such as life support, radiation detection/protection and food production and storage. The Lunar Landing topic is helping to prepare technologies needed for the Lunar Exploration Activities programme as well as longer term needs. This topic is not address in this compendium but is covered by activities presented in the GSTP 6-1 Work plan. Activities in this Compendium

The breakdown by topics is given in the table. An additional topic is added for developments related to using the ISS for demonstrations.

SD3 Topics number of activities Technology Domains Robotics assistance and tele-robotics 6 TD 2, 9, 12, 13

Life and physical science 7 TD 14 Human spaceflight and exploration preparation 2 TD 22

ISS Demonstration (GNSS-R) 2 TD 6 Table 2: Breakdown of SD3 activities by topics

SD4 – Space Transportation

Background and Considerations for Technology Development

Future launchers, human spaceflight transportation and re-entry are covered in this service domain. Particular targets for technology developments are Ariane 5 and Vega evolutions, Ariane 6 Next Generation Launcher, the Multi-Purpose Crew

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Vehicle (MPCV), propulsion for exploration and general improvement of aerothermodynamics knowledge. Launchers: Developing future launchers and thus guaranteeing European access to space are essential. Attention is given to continuing and preserving industrial know-how necessary for development and those which are not sustained by on-going development programmes, while preparing possible evolution of the launcher sector industrial setup. Human Spaceflight related developments: Currently, ESA is supplying the Service Module for NASA’s Orion MPCV. European industry participates in ISS vehicle projects and potential exists for contributions to new LEO transportation systems. Examples of development interest areas include increased propulsive performance, mass minimization and improved system autonomy.

Activities in this Compendium

There are 6 activities, focusing on launch vehicle oriented applications and on ‘generic’ needs (i.e. for both launchers and Human Spaceflight).

SD4 Topics number of activities Technology Domains Launch Vehicles 3 TD 5, 18

Generic 2 TD 14, 19 Table 3: Breakdown of SD4 activities by topics

SD6 – Navigation


Technologies related to enhancing, securing and preparing for future navigation systems are developed under this domain. Developments target enhancing current Galileo systems and techniques and preparing the evolutions of Galileo and EGNOS (European Geostationary Navigation Overlay Service). Key drivers for evolutions in Galileo come from mission level considerations (i.e. ensuring existing performance requirements are met and addressing emerging requirements, such as Public Regulated Service) and from system level considerations (i.e. ensuring design-to-cost, managing obsolescence, mitigating risks). These drivers are linked to several directions to take regarding the overall system, the space segment, the ground segment and frequencies, signals and services. Technology developments for navigation address different mission related activity lines: • System (e.g. system architecture, tools, propagation / EMC / interference) • Space Segment (e.g. payload technology, frequency/bandwidth/signal design) • Ground Segment (e.g. antennas / receivers, algorithms) • Users (e.g. receiver technology)


There are ten activities in this compendium related to RF Payloads and Systems (TD 6) and Electromagnetic Technologies and Techniques (TD 7).

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SD8 – Space Situational Awareness


The protection from space threats, including threats to European orbital and ground based infrastructures, is a topic of increasing relevance and growing importance. Related capabilities in Europe are being consolidated and enhanced through 3 lines: Space Surveillance & Tracking, Space Weather and Near-Earth Objects. Space Surveillance & Tracking (SST): ESA is supporting the definition an SST architecture and the development of assets and data services. The SST segment architecture and components are being enhanced with attention placed on cost and on internationally recognized methods and standards. The functionalities are being developed in the sensor network, data processing and user interfaces for services. Activities are being pursued to improve ground-based surveillance radar breadboards. Space debris observations using radars are to be complemented with object detection with wide field-of-view optical telescopes. Space Weather: Building capabilities and services requires new Space Weather space missions and the required instruments. ESA is actively studying missions and identifying instrument flight opportunities and international cooperation opportunities. Precursor services are being further developed by using data collected from different Space Weather missions (e.g. Proba-2, SOHO, GAIA). Near Earth Objects: NEOs are solar system bodies whose orbit brings them close to Earth, representing a potential threat. The aim is to enhance Europe’s capability to contribute to the monitoring the NEO population and assess their impact risk. Actions are being implemented to develop and validate NEO capabilities; they include precursor services, enhanced NEO survey and other observation capabilities and improved methods to predict future orbits and impact risk of NEOs.


15 SSA activities are presented in this compendium related to Space Surveillance and Tracking (SST), Space Weather and NEO.

SD8 Topics number of activities Technology Domains SST 3 TD 11, 12

Space Weather 9 TD 4 NEO 2 TD 4

Common 2 TD 9, 12 Table 4: Breakdown of SD8 activities by topics

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SD9 – Robotic Exploration The MREP-2 programme (Mars Robotic Exploration Preparation-2), was subscribed at the C/MIN 2012, with the objective to reinforce Europe’s position in Mars robotic exploration and prepare for a European contribution to a future international Mars Sample Return mission.

The drivers for the future development activities are the intermediate missions (i.e. the missions following the ExoMars 2016/2018 missions) and the European strategy for future participation to Mars Sample Return. In particular, the proposed GSTP technology activities have a direct link to the envisaged European contribution to Mars Sample Return international mission, while equally serving in many cases the technology preparation of the identified intermediate missions. Activities in this Compendium

The activities presented in this compendium, have been recommended to be implemented in the GSTP Programme as indicated in the Mars Robotic Exploration Preparation -2 Programme Technology Plan. There are 7 activities in this compendium related to several technology domains: Spacecraft Environment and Effects (TD4), Space System Control (TD5), Automation, Telepresence & Robotics (TD13), Mechanisms & Tribology (TD15), Aerothermodynamics (TD18) and Thermal (TD21).

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3 LIST OF ACTIVITIES

SD1- EARTH OBSERVATION TD 6- RF Payload and Systems

GSTP-6 Reference

Title Budget(K€)

G611-006ET Pulsed HPA for Ka-band SAR instruments 900 G611-007ET Miniature filter for L-band radiometer 500 G611-008ET High Power GaN C-band TRM Demonstrator 1,000

Total 2,400

TD 7- Electromagnetic Technologies and Techniques

GSTP-6 Reference

Title Budget(K€)

G611-009EE Advanced End-to-End Testing of Active Transponders 350 G611-010EE Multi-Frequency/Multi-Pixel Integrated Lens Antenna for Microwave

Radiometers 400

G611-011EE Compact Multi-band Feeds for Radiometer Instruments 400 G611-012EE Synthesis, analysis and optimization of slotted waveguide antennas 300

Total 1,450

TD 12- Ground Station System & Networking

GSTP-6 Reference

Title Budget(K€)

G611-013GS Enhanced Antenna Tracking receiver for 26 GHz K-band 600

G611-014GS 8-PSK modulation in ESA TT&C receiver 350

Total 950

TD 16- Optics

GSTP-6 Reference

Title Budget(K€)

G611-015MM BSDF measurement facility 500

G611-016MM Large non-flat monolithic mirrors with ultra-lightweight honeycomb structure

1,000

Total 1,500

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TD 17- Optoelectronics

GSTP-6 Reference

Title Budget(K€)

G611-017MM High stability laser for interferometric Earth Gravity measurements in the context of a Next Generation Gravity Mission (NGGM)

1,700

Total 1,700

TD 26- Other: Earth Observation (Systems and Ground)

GSTP-6 Reference

Title Budget(K€)

G611-018EO Broker Technology enabling discovery and exploitation of Earth Observation data (BT4EEO)

500

G611-019EO Geosounder products, data processing study, and end-to-end performance study

300

G611-020EO Geosounder Requirements Consolidation Study 200 G611-021EO EVOlution of EO Online Data Access Services - EVO-ODAS 1,000 G611-022EO Technology and Atmospheric Mission Platform (TAMP) 500 G611-023EO Multimission Environmental DatA 800 G611-024EO Technologies for the Management of LOng EO Data Time SEries - LOOSE 2,000 G611-025EO FAst Multimission tEstbed architecture - FAME-C 900 G611-026EO ESE ERGOnomic User Interface ESE_ERGO 800

Total 7,000

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SD3- HUMAN SPACEFLIGHT TD 2- Space System Software

GSTP-6 Reference

Title Budget(K€)

G613-003GD METERON Operations Environment M&C component on ISS 750

Total 750

TD 6- RF Payload and Systems

GSTP-6 Reference

Title Budget(K€)

G613-004ET Down-Converter and Analog-to-Digital Converter for GNSS-R 1,000 G613-005ET Beamformer Breadboard for GNSS-R 1,000

Total 2,000

TD 9- Mission Operations and Ground Data Systems

GSTP-6 Reference

Title Budget(K€)

G613-006GD METERON Experiment Specific Data Systems 500

Total 500


GSTP-6 Reference

Title Budget(K€)

G613-007HS Development of low latency communications infrastructure for "real-time" haptic tele-robotic operation

750

Total 750

TD 13- Automation, Telepresence & Robotics

GSTP-6 Reference

Title Budget(K€)

G613-008HS Eurobot upgrade for METERON 3,000

G613-009MM Exoskeleton (XR-2) Bi-manual flight mechatronics system 1,100

G613-010MM Development of QM/FM 3D vision display system 400

Total 4,500

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TD 14- Life and Physical Sciences

GSTP-6 Reference

Title Budget(K€)

G613-011MM Miniaturized real time quantitative PCR: Mini q-PCR 450

G613-012MM Miniaturised turbomolecular vacuum pump for analytical instrumentation 700

G613-013MM 3D x-ray based medical imaging in a space environment 600

G613-014MM Autonomous assistance for medical operations 400

G613-015MM Bio-chemical Analyser for Bio-Burden monitoring 450

G613-016MM Adaptation of a furnace and x-ray diagnostic setup for metallic foams used in a sounding rocket experiment for use on parabolic flights or inside the Large Diameter Centrifuge

500

G613-017MM Chemical Mapping: characterisation of the local concentration distribution in (binary) mixtures

450

Total 3,550

TD 22- Environmental Control Life Support and In-Situ Resource Utilisation

GSTP-6 Reference Title Budget(K€)

G613-018MM MIDASS PHASE B+ 650 G613-019MM Microbial Air Sampler System 450

Total 1,100

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SD4 Space Transportation TD 5- Space System Control


G614-002EC Hybrid navigation breadboard and demonstration 2,000

Total 2,000

TD 14- Life and Physical Sciences

GSTP-6 Reference

Title Budget(K€)

G614-003MM Optical Tomography on bubble formation in cryogenic fuel tanks 600

Total 600

TD 18- Aerothermodynamics

GSTP-6 Reference

Title Budget(K€)

G614-004MP Experimental characterisation of transient flow phenomena in cryogenic fluids

500

G614-005MP Liquid film cooling in MMH-NTO rocket engines 500

Total 1,000

TD 19- Propulsion

GSTP-6 Reference

Title Budget(K€)

G614-006MP 10 kW Hall Effect Thruster 2,000

Total 2,000

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SD6 Navigation TD 6- RF Payload and Systems


G616-001ET Low complexity GNSS Sensor Station beam forming-based tracking receiver

1,800

G616-002ET Advanced GNSS signal implementation platform 1,500

G616-003ET Digital Beam-forming Based Advanced Navigation Receivers 1,000

G616-004ET Advanced hybrid navigation user platform 1,200

G616-005ET Advanced receiver architecture platform 800

G616-006ET Advanced GNSS Reference Station DSP technology platform 1,500

G616-007ET A 300W L band GaN power module and EM SSPA demonstrator 1,000

G616-008ET Compact ultra-high stability atomic clock for Space applications 1,000

G616-009ET Payload simulation tool for complex GNSS RF front-end architectures 450

Total 10,250

TD 7- Electromagnetic Technologies and Techniques

GSTP-6 Reference

Title Budget(K€)

G616-010EE Fixed and mobile calibration and evaluation of multipath and atmospheric GNSS error sources

500

Total 500

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SD8 Space Situational Awareness TD 4- Spacecraft Environment and Effects

GSTP-6 Reference

Title Budget(K€)

G618-002EE H-alpha Solar Telescope Network prototype for Applications (HASTENet) 400

G618-003EE Heliospheric modelling techniques 1,000

G618-004EE Airborne radiation detector 1,000

G618-005EE Wide-field space-based auroral camera prototype 500

G618-006EE Impact effects tools 400

G618-007EE Development of a compact Remote Interface Unit (RIU) - Phase A/B/C/D 650

G618-008EE Combined Radiation Monitor Data Analysis System (CORMODAS) 500

G618-009EE Prototype Compact Wide Angle Coronagraph 700

G618-010EE Fireball Monitor for SSA 600

G618-011EE Phase C/D of 3D Energetic Electron Spectrometer 2,000

G618-012EE Solar X-Ray Monitor Proto-Flight Model and Low-Resolution Imager Design for SSA

600

Total 8,350

TD 9- Mission Operations and Ground Data Systems

GSTP-6 Reference

Title Budget(K€)

G618-013GD General-purpose computing on graphics processing units for SSA Ground Data Systems

300

Total 300

TD 11- Space Debris

GSTP-6 Reference

Title Budget(K€)

G618-014GR Development of semi-analytical methods for orbital lifetime estimation and re-entry propagation

250

G618-015GR Development of an efficient method for mean elements computation from precise orbital data and its associated analytic propagation method

300

Total 550


GSTP-6 Reference

Title Budget(K€)

G618-016GS L-Band SSPA for phased array radar transmitter and dual polarization receiver

1,000

G618-017GS Breadboarding of an intelligent telescope CMOS APS 1,500

Total 2,500

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SD9 Robotic Exploration TD 4- Spacecraft Environment and Effects

GSTP-6 Reference

Title Budget(K€)

G619-003EE Maintenance of the European Mars Climate Database 300

Total 300

TD 5- Space System Control

GSTP-6 Reference

Title Budget(K€)

G619-004EC Further development of Sensor Data Fusion for Hazard Avoidance 700

Total 700

TD 13- Automation, Telepresence & Robotics

GSTP-6 Reference

Title Budget(K€)

G619-005MM Planetary Explorer LOcalisation-navigation Ready for USe (PELORUS) 2,000

Total 2,000

TD 15- Mechanisms & Tribology

GSTP-6 Reference

Title Budget(K€)

G619-006FP Shape Memory Alloy actuators for MSR biocontainer sealing - feasibility demonstration

200

Total 200

TD 18- Aerothermodynamics


G619-007MP Supersonic parachute test on a MAXUS flight 500

Total 500

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TD 21- Thermal

GSTP-6 Reference

Title Budget(K€)

G619-008MT Mini Heat Switch Qualification 400

G619-009MT Ablative TPS Numerical Test Cases - Mathematical Code Assessment & Improvement

300

Total 700

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4 DESCRIPTION OF ACTIVITIES

4.1 SD1- Earth Observation

4.1.1 TD 6- RF Payload and Systems

Service Domain EARTH OBSERVATION Technology Domain 6 RF Payload and Systems Ref. Number: G611-006ET Budget (k€): 900 Title: Pulsed HPA for Ka-band SAR instruments

Objectives: The objective of this activity is to design, manufacture and test a breadboard of a pulsed HPA (High Power Amplifier) meeting the specification for use in the Ka-band SAR instruments (3.5 kW, 14% duty cycle, 500MHz BW).

Description: Synthetic Aperture Radar (SAR) instruments have become essential for Earth Observation purposes since the first instrument in space back in 1978. The operational frequency has evolved from L- to S- and X-band. New frequency bands have been studied in Europe such as P-band for BIOMASS and Ku-band for CoReH2O. Ka-band has been used for Unmanned Aerial Vehicles (UAV) but has not been utilized for SAR from space so far, although the suitability of Ka-band SAR imaging has been proven in various airborne demonstrators and instruments. An ESA internal study on the feasibility of a Ka-band SAR instrument and interferometer has pointed to the need of a Ka-band HPA with capabilities beyond what is currently available on the market. The activity will be divided in two phases.

Phase 1 will cover the following tasks: - Critical review of the trade-off and results of the TRP activity on the feasibility

study of a pulsed HPA for Ka-band SAR; - Identification of a baseline technology (TWTA/EIKA) and design; - Performance prediction by analysis/simulation and tests at subassembly level. - Consolidation and update of the preliminary specification.

Phase 2 will be dedicated to the: - manufacturing and testing of a HPA Breadboard according to the baseline

design agreed at the end of Phase 1 - a detailed programmatic description of the necessary development steps

needed up to Flight Model, together with a realistic estimation of the duration and cost of each development phase.

Deliverables: Breadboard

Current TRL: 3 Target TRL: 4 Duration (months)

24

Target Application / Timeframe :

Ka-band SAR instruments, 2016

Applicable THAG Roadmap: Not related to a Harmonisation Subject

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Service Domain EARTH OBSERVATION Technology Domain 6 RF Payload and Systems Ref. Number: G611-007ET Budget (k€): 500 Title: Miniature filter for L-band radiometer Objectives: The objective is to develop miniaturised high performance filter for L-band

synthetic aperture radiometer applications.

Description: Synthetic aperture radiometer instruments like MIRAS (SMOS) require several similar receivers to be accommodated. In this kind of instrument, the number of elementary receivers correlates with the system performance. Therefore, in order to improve the performance of similar instruments in the future, the miniaturisation and mass saving of the receiver is crucial in order to allow for a larger number of receivers to be accommodated. One key block in the receiver is the high performance RF filter that has to provide very efficient out-of-band interference protection and on the other hand its transfer function has to be reproducible and uniform from unit to unit. Currently, coaxial resonator filters are employed for this function which, however, are big and bulky and they are not any more in line with the miniaturisation objectives of the other parts of the receiver (Integrated digital receiver TRP WP 2013). However, there are potential technologies that can provide the required degree of miniaturisation while maintaining the performance (SAW, BAW, dielectric,…). It is presumed that the RF filter could be located after the low-noise amplifier and the insertion loss is not necessarily a key design parameter. This could open ways for the application of novel efficient design approaches such as pre-distortion and lossy filter theory. This activity aims first at revisiting the L-band elementary receiver requirements for SMOS follower like missions and then flowing down from there the filter requirements. Secondly, taking into account also the qualification aspects, the best technologies and architectures for the miniaturised filter shall be breadboarded. Based on the breadboarding results, the best concept shall be selected for an EM development. Finally, the EM shall be designed, manufactured and tested.

Deliverables: Engineering Model

Current TRL: 3 Target TRL: 5 Duration (months) 18


SMOS/MIRAS type future instruments: SMOS-Ops, Super MIRAS


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Service Domain EARTH OBSERVATION Technology Domain 6 RF Payload and Systems Ref. Number: G611-008ET Budget (k€): 1,000 Title: High Power GaN C-band Transmit/Receive Module Demonstrator Objectives: Design, build and test of a Transmit/Receive-module unit in GaN technology for

next generation of C-band SAR based on given requirements.

Description: Next generation of C-band SAR utilising Digital Beam Forming (DBF) techniques allow significant coverage improvements at high resolution as confirmed in several ESA studies in the field. Several TRP studies in the field of Digital Beam Forming (DBF) have confirmed the feasibility to achieve 400km swath width at 5m x 5m resolution, while Sentinel-1 achieves currently 80km at 5m x 5m resolution. The DBF technological elements are currently under development in the GSTP activity Integrated Tile Demonstrator (ITD) based on extended Sentinel 1 requirements. Within Phase 1 of the activity a partial tile, a recurrent part of the full antenna, is under specification and design. The preliminary specification for the Transmit/Receive Modules (TRM) has identified high peak power requirements of 50Watts which calls for advanced GaN technology in order to achieve this peak power at high efficiency. GaN technology has progressed very well. Relevant European 0.25um GaN technology is under space evaluation and is expected to achieve approval in 2014. The proposed GSTP activity will significantly benefit from the ongoing TRP activity "Single Chip C-band LNA/HPA in GaN technology" in which a key element will be developed on Breadboard level to achieve TRL 3. Existing TRM technology needs to be improved in view the challenges related to the high peak power and related high voltages, which otherwise will result in destructive discharge effects (corona and multipactor). Current technology supports power levels up to 20Watts for which discharge effects are already critical. Furthermore the next generation C-band SAR instruments will introduce advanced instrument calibration techniques allowing calibration while imaging. This results in new challenges for TRMs because very high internal signal isolation is required. Within the activity the next generation of TRMs utilising advanced GaN technology shall be designed, built and tested based on requirements as derived in the activity Integrated Tile Demonstrator (ITD). The TRM shall be tested in thermally representative environment. Robustness against discharge effects shall be demonstrated by test.



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Sentinel 1 follow-on/2018

Applicable THAG Roadmap: Critical RF Payload Technologies (2004)

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4.1.2 TD 7- Electromagnetic Technologies and Techniques

Service Domain EARTH OBSERVATION Technology Domain 7 Electromagnetic Technologies and Techniques Ref. Number: G611-009EE Budget (k€): 350 Title: Advanced End-to-End Testing of Active Transponders Objectives: To develop advanced high accuracy methodologies of radiated end-to-end testing of

ground based active transponders for Earth Observation missions.

Description: Active ground based transponders are used for calibration of SAR instruments or radar altimeters, typically within C and Ku bands. The techniques used nowadays for the calibration of the transponder itself are still performed with theoretical values of known RCS targets for SAR response. In addition, the phase delay of the target (including the contribution of the radiating apertures) is driving stringent requirements on the accuracy of the free-space delay measurement, in particular at Ku Band, not possible to reach with typically used methods, which rely on the measurement of a known target to calibrate the radiated performance. This activity shall yield advanced high accuracy end-to-end testing techniques, that includes the overall radiated delay, identifying needs for future missions, trade-off and Breadboard of critical components necessary to perform the measurements. The techniques developed shall be demonstrated with a representative test object.

Deliverables: Report; Breadboard of critical components


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Earth Observation instruments /2015


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Service Domain EARTH OBSERVATION Technology Domain 7 Electromagnetic Technologies and Techniques Ref. Number: G611-010EE Budget (k€): 400 Title: Multi-Frequency/Multi-Pixel Integrated Lens Antenna for Microwave

Radiometers Objectives: The objective is to demonstrate that multi-frequency and or multi-pixel integrated

lens antennas can result in more performing radiometers in the microwave and millimetre-wave regime. Expected improvements are in sensitivity (25% due to increase number of detectors) and focal plane size reduction (25-30%).

Description: Integrated lens antennas offer an attractive alternative solution as compared to feed horns and could replace them in novel microwave radiometers and allow to design integrated receivers. Recently advancement in lens arrays design and manufacturing and accurate lens antenna modeling could be of benefit to get improved performances. Another interesting recent development in the field of flat lenses could also be used to ease the manufacturing of large focal plane arrays. Therefore, this activity should investigate the novel architectures that combine multi-frequency detectors with focusing elements like lenses and how these elements could be of benefit for multi-frequency radiometers systems. The activity shall start with an investigation of novel architectures for use in radiometer systems using the multi-frequency and multi-pixel integrated antennas and novel flat lenses. A trade-off shall be performed to assess the improvement gained in terms of instrument sensitivity and mass and volume of the focal plane arrays. Next, the most promising architecture shall be subjected to detailed design and analyses and be followed by the breadboarding and testing of the most critical components. The activity shall be concluded by updating the instrument performance taking into account the test results.



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Next generation Metop-SG radiometer instruments-2016-2017

Applicable THAG Roadmap: Technologies for Passive Millimetre & Submillimetre Wave Instruments (2010). Activity B56.

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Service Domain EARTH OBSERVATION Technology Domain 7 Electromagnetic Technologies and Techniques Ref. Number: G611-011EE Budget (k€): 400 Title: Compact Multi-band Feeds for Radiometer Instruments Objectives: To develop a compact multi-frequency and dual-polarisation feed horn for future

microwave radiometer instruments.

Description: Earth Observation radiometers often use multi-frequency feeds to comply to the colocation requirement of certain beams on ground. Besides the colocation requirement there is sometimes also the requirement to have the dual linear polarisation for certain frequency channels. Although this does not impact the design of the feed horn itself, it has a significant impact on the design and complexity of the feed chain excitor part. Similar design issues can be seen in Telecommunication feed horns with receive and transmit capability and often use dual polarisation as well. The constraint these feed horns have is that they form part of a larger array and hence need to have a very compact feeding chain with the lateral dimensions not larger than the feed horn aperture. In a recent ARTES5.2 study a very compact Ka-band feed horn was designed, manufactured and tested operating at 20 and 30 GHz. In this study an assessment shall be done to see what simularities exist between the feed requirements for EO radiometers and Telecommunication array feed horns at e.g. Ka-band. In a following step, a feed horn shall be designed, analysed, manufactured and tested at 18/23 GHz for a future EO radiometer similar to MWI instrument on Metop SG.



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Earth Observation microwave radiometer instruments. 2016.

Applicable THAG Roadmap: Technologies for Passive Millimetre & Submillimetre Wave Instruments (2010)

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Service Domain EARTH OBSERVATION Technology Domain 7 Electromagnetic Technologies and Techniques Ref. Number: G611-012EE Budget (k€): 300 Title: Synthesis, analysis and optimisation of slotted waveguide antennas Objectives: The objective of this activity is the development of a simulation software that meets

the main requirements in terms of synthesis, analysis and optimization of slotted waveguides antennas of future Earth Observation missions.

Description: Slotted waveguide antennas are being considered for several Earth Observation applications such as C-band Wind scatterometer or Synthetic Aperture Radar (SAR). Although several simulations tools are able to model and analyse slotted waveguide antennas, there is no current software that meets the main requirements in terms of synthesis, analysis and optimization for future Earth Observation missions. Therefore, the main objective of this activity is to improve the current tools in order to overcome the current limitations. Some of the requirements that shall be considered (but not limited to) are large arrays, travelling/resonant waveguides including dielectric, both internal Beam Forming Network (BFN) and radiating structures, different feeding networks with several feeding points, scattering parameters to be available (also for mixed transmission lines; i.e. waveguides of different dimensions and mixed with coaxial), prediction of radiation patterns, synthesis including radiation patterns by mask or preferably by cost function (e.g. return loss and pattern requirements (both power pattern and polarisation), active return loss), etc In order to validate the tool, an accuracy assessment of the predicted results by manufacturing and testing of several arrays shall be performed. The work logic for this activity shall be:

- Consolidation of the requirements - Software development - Breadboarding activities of the selected configurations - Testing and test report - Accuracy assessment

Deliverables: Software


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C-band Wind scatterometer, SAR /2016

Applicable THAG Roadmap: System Modelling and Simulation Tools (2012)

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4.1.3 TD 12- Ground Station System & Networking

Service Domain EARTH OBSERVATION Technology Domain 12 Ground Station System & Networking Ref. Number: G611-013GS Budget (k€): 600 Title: Enhanced Antenna Tracking receiver for 26 GHz K-band Objectives: To develop a tracking receiver that copes with the issues of the 26 GHz

communication: mainly but not limited to the narrow beamwidth of the antenna, large bandwidth of the received signal, low energy density near the central frequency, use of suppressed carrier modulation and criticality of the phase alignment due to the very high frequency involved.

Description: Earth Observation (EO) missions are considering to move to the 26 GHz band to avoid the downlink data bottleneck for LEO missions with the new generation of EO sensors producing more data and the increasing spectrum congestion. 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), 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 will define the best structure and algorithms that are required for the eATRK. It will first analyze the characteristics of the downlink signal received from the LEO satellites at 26 GHz, in order to produce the more efficient architecture. An eATRK will be designed (with the selected structure and algorithms) and a prototype will be produced and validated. The activity will be split in two phases. In phase 1:

- The requirements for the eATRK will be reviewed in the first instance. - the downlink signal characteristics will be analyzed, and some algorithms and

architectures for the eATRK will be proposed. - One architecture will be selected after intensive modeling and simulation. - A preliminary design of the eATRK prototype will be produced.

In phase 2: - eATRk prototype will be designed, produced and validated - eATRK first production unit will be produced and tested in a relevant

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environment Some 26 GHz band LEO missions are expected to be flying by the end of the project, that could facilitate the testing in a relevant environment.

Deliverables: Prototype


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26 GHz missions / MTG / Sentinel 3 / EPS-SG / 2018


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Service Domain EARTH OBSERVATION Technology Domain 12 Ground Station System & Networking Ref. Number: G611-014GS Budget (k€): 350 Title: 8-PSK modulation in ESA TT&C receiver Objectives: To study and implement a High performance 8-PSK Trellis Coded Modulation

(TCM) 4D demodulator (lower loss but medium bit rate < 100 Msps) in VHDL for inclusion in the forthcoming generic receiver in ESTRACK, the Telemetry-Tracking & Command Processor (TTCP). This would allow ESTRACK to cover the full ECSS-E-ST-50-05C. RF & mod. Standard, and provide support to the missions using this modulation scheme.

Description: Earth Exploration Service (EES) missions are using 8-PSK TCM 4D modulation in order to transmit its payload telemetry data down to ground. Currently the ESA ESTRACK Network does not support this type of modulation. This activity will develop the VHDL of the receiver, that would allow to incorporate this kind of modulation in the TTCP, making it able to demodulate and decode the signal transmitted by the EES missions, once integrated in the TTCP FPGAs. Losses should be less than 0.3 dB at the selected rates, in order to take the maximum advantage of this efficient modulation scheme. The resulting VHDL code shall be easy to integrate in the TTCP equipment. The activity shall include testing and monitoring and control functions, that are also a requirement from the operational ESTRACK network. The following tasks will be done in the frame of this activity:

- Consolidation of requirements for a 8-PSK TCM 4D in TTCP - Investigation and simulation of suitable architecture - Develop the VHDL code of the8-PSK TCM 4Ddemodulator - Run simulations in VHDL code and compare with C/ MatLab results. - Incorporate the FPGA design in FPGA platform (Commercial Off-the Shelf

COTS or specific development) to produce a prototype of the 8-PSK TCM 4D demodulator.

- Validation of prototype with respect to the initial requirements. It shall be demonstrated that the resulting VHDL code can be integrated in the TTCP platform FPGAs.



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Missions using 8 PSK TCM 4D, 2016


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4.1.4 TD 16- Optics

Service Domain EARTH OBSERVATION Technology Domain 16 Optics Ref. Number: G611-015MM Budget (k€): 500 Title: BSDF measurement facility Objectives: To develop a new BSDF (Bidirectional Scatter Distribution Function) measurement

facility which can measure curved surfaces at several wavelengths using different beam geometries and at angles of incidence up to 85 degrees.

Description: BSDF is typically measured with an instrument called scatterometer. Although there are commercially available scatterometers (e.g. SMS, LightTEC, IOF...), these have certain limitations:

- The use of laser as a light source. This gives a high SNR, but restricts the wavelength range over which the instrument could be used. On the other hand, a broadband blackbody source can be used with several narrow-band filters but this leads to low SNR.

- Limited capabilities in measurement of curved surfaces. Therefore, the measurements are typically done on representative flat samples. With the next generation of Earth Observation instruments using aspheric/free-form surfaces, the capability to measure directly curved surfaces is necessary for accurate stray-light analysis of these instruments.

- Detector field-of-view does not match the spot elongation on the measured sample at high angles of incidence (> 80°).

- Fixed illumination beam geometry: either collimated or focussed beams. The activity comprises the design and development of a new BSDF measurement facility taking into account the afore-mentioned limitations of the currently available systems. In particular, following tasks have to be executed:

- Make a trade-off between different light sources (broadband source, individual lasers, white laser, tunable laser etc.) and identify the technology which gives a high Signal-to-Noise Ratio over a wide dynamic range.

- Design and manufacture an optical system for collimated as well as focussed beam. The opto-mechanical design shall allow to measure curved/aspheric surfaces and to adjust the field-of-view for high angles of incidence.

- Design and manufacture a new compact sample holder which is able to accommodate samples of variable sizes and shapes.

- Identify and implement in the facility an alignment technique ensuring to achieve high repeatability.

- Develop a software for the system which provides as output BSDF, PSD and TIS. A systeem model in FRED/ASAP optical software shall also be generated and delivered to compare the measurement data with theoretical estimates.



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2016. Earth Observation missions

Applicable THAG Roadmap: Technologies for Optical Passive Instruments (Stable & Lightweight Structures, Mirrors) (2008).

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Service Domain EARTH OBSERVATION Technology Domain 16 Optics Ref. Number: G611-016MM Budget (k€): 1,000 Title: Large non-flat monolithic mirrors with ultra-lightweighted honeycomb

structure Objectives: The first objective (Phase 1) is to optimize manufacturing and process choices for

an ultra-lightweighted honeycomb mirror (to be demonstrated with the development and testing of a breadboard of a flat mirror). The second objective (Phase 2) is to demonstrate the feasibility of the transfer of the ultra-lightweighted honeycomb structure technology to non-flat mirror surfaces (sphere, asphere) with the development and testing of a primary mirror demonstrator for geostationary high-resolution imaging applications.

Description: The use of reduction technology for large mirrors located in an optical system entrance cavity (e.g. scan mirror, primary mirror) would be an enabling key factor in the production of large monolithic mirrors (one of the 7 enabling technologies recommended by the FTAP First Cycle report 2012), thereby securing high-resolution imaging capability for space systems in e.g. geostationary orbit. Currently the level of lightweighting needed for such missions is reaching the limit of classical techniques and decreasing optical performances due to lightweighting side-effects. Aluminium as a structural material would most likely not be suited for such applications due to its high coefficient of thermal expansion. An alternative candidate material needs to be identified and incorporated in a large flat demonstrator mirror, with the following purposes:

- Demonstration of the successful transfer of the technology to another structure material,

- Demonstration of the suitability of the mirror to tolerate large thermal variation characteristics of instrument entrance cavity conditions in geostationary orbits.

Identifying and demonstrating a concept for achieving curved figures with such a lightweighting technology would allow significant weight reduction specifically for large primary mirrors. The proposed activity constitutes an important step on the way to extreme lightweighting of mid-size (1-2 meter diameter) and large-size monolithic mirrors. It will encompass the following activities, split into 2 phases: Phase 1 (planar technology):

- Study leading to the selection of materials and its combinations, which are able to ensure optical performance under geostationary environmental conditions;

- Improvement of glass/structure cementing methods; - Production of small-size breadboards to support technological trade-offs for

the previous 2 points; - Production and test of a 1 meter flat demonstrator (to be tested at ambient,

thermal vacuum, vibration, radiation) If Phase 1 is successful, the following Phase 2 will be executed. Phase 2 (curved technology):

- using the results of phase 1, study leading to process and material selection for the production of a curved surface (representative of a typical primary

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mirror), able to ensure optical performance under geostationary environmental conditions.

- Production of small-size breadboards to support technological trade-offs regarding process and materials selection.

- Production and test of a 1-meter off-axis parabolic mirror demonstrator (to be tested at ambient, thermal vacuum, vibration)



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2017. Geostationary high-resolution imaging applications

Applicable THAG Roadmap: Technologies for Optical Passive Instruments (Stable & Lightweight Structures, Mirrors) (2008)

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4.1.5 TD 17- Optoelectronics

Service Domain EARTH OBSERVATION Technology Domain 17 Optoelectronics Ref. Number: G611-017MM Budget (k€): 1700 Title: High stability laser for interferometric Earth Gravity measurements in

the context of a Next Generation Gravity Mission (NGGM) Objectives: The development objectives are concerned with the enhancement up to TRL 5 of

the entire laser system while maintaining the required output power and spectral performance.

Description: The activity is based on the technology developed in the frame of TRP activity 'High-Stability Laser with Fibre Amplifier and Laser Stabilisation Unit for Interferometric Earth Gravity Measurements'. The goal of the activity is the the achievement of a high TRL for the overall system consisting of master oscillator (MO), frequency stabilisation system (FSS) and power amplifier (PA). The 3 main sub-systems shall reach TRL 6 and the integrated system shall achieve TRL 5. The design shall be driven by considerations of environmental compatibility. For the MO subsystem the current baseline is to use a non-planar ring oscillator (NPRO) developed and space-qualified by a European manufacturer for satellite optical communications. The feasibility, advantages and maturity of alternative options for the MO, such as a fibre laser or a DFB laser diode, shall be investigated in the frame of the proposed activity. The high stability laser technology in subject can be of dual use for both a Next Generation Gravity Mission and a gravitational wave mission of eLISA type, requiring only a delta development effort. The key laser performance specifications for both applications are very similar, with the main difference being a higher output power requirement for eLISA, which could be met by either upgrading the PA subunit accordingly or adding a second PA to the current laser design for NGGM.



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2017. Next Generation Gravity Mission (NGGM)

Applicable THAG Roadmap: Formation Flying - Optical Metrology (2008)

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4.1.6 TD 26 – Other: Earth Observation (Systems and ground)

Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-018EO Budget (k€): 500 Title: Broker Technology enabling discovery and exploitation of Earth

Observation data (BT4EEO) Objectives: This project aims to develop, benchmark and prototype a set of new technologies

enabling community-specific discovery, selection and exploitation of Earth Observation (EO) data in the context of other non-space data.

Description: The growing availability of large volumes of EO data, in particular from the upcoming EO missions such as the Sentinels, represents a huge opportunity to further develop the market of geospatial information. At the same time the involvement of new communities represents a huge challenge as new users (with own domain knowledge, and having specific community language) cannot easily discover, and process the right information from the large volumes of available data. In this context, new technological approaches are critically needed to overcome technical barriers and information gaps, in effectively connecting end-users to tailored information meeting their specific needs. This project aims to meet this challenge by designing and developing a Broker Technology able to translate user needs (expressed within specific community language) into geospatial data needs, enabling easy search, discovery and access of EO data from multiple missions in the context of other non-space data (e.g. meteo, in situ sensor, market), and connections (both physical and semantic) between community-specific applications and EO data provision. For example, it is very challenging for a potential user in the Oil & Gas (O&G) industry to mine and extract useful information from Petabytes of EO data, identify which relevant data, products and sampling are available to address its specific problem (e.g. monitoring sea-ice in the Arctic or Caspian Sea). The broker technology has to be based on an in-depth understanding of both user practices, geospatial data access protocols . Such technology would be based on three main elements:

- Broker functions, which shall establish the relations and create the connections between end-users applications and EO data sources, both in archives and from future acquisitions),

- Semantic Search functions, which shall allow the user to effectively navigate the connections and to be presented with the relevant data,

- Visualization functions providing rapid mapping of large volume of data and basic functions (e.g. zoom, pan, sorting, statistical analysis, using of ancillary information, etc.).

- In particular, the broker technology shall empower new capabilities for both end-users and data providers, such as:

- Segmentation of user applications, taking into account business processes, operations, standards and protocols and permitting the mapping of user applications to EO products;

- Knowledge-based technologies to recommend sensors and configurations by EO-based product, i.e. incorporating expertise in the optimum sensors and their configurations for user applications;

- A portfolio of tools to explore and access (through appropriate technologies,

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ontologies and standards) the actual and potential EO data (e.g. EO data catalogues/repositories, multi-mission feasibility analysis and planning for future data, open data, etc.)

- Inter-community interaction (e.g. vendor; user), based on tailoring of emerging Web2.0 technologies.

- The broker technology will be tested in a variety of applications across communities. A particular focus will be on the Oil & Gas industry where there is today a clear demand for such a technology to improve surveillance of oil spills and operations in ice-infested regions.

Data-intensive brokering technologies are critically needed to enable user communities to better understand, evaluate, explore and exploit EO data, thereby opening new opportunities for:

- More effective uptake of EO data and services in existing and new markets, as well as market access for new suppliers,

- Development of the new generation of innovative and agile ground segment infrastructures, with components effectively linking user applications to satellite sensor resourcing and tasking,

- Fostering exploitation of upcoming satellite missions and integrated information services.



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2015. Exploitation of Earth Observation data


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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-019EO Budget (k€): 300 Title: Geosounder products, data processing study, and end-to-end

performance study Objectives: Geosounder products, data processing study, and end-to-end performance study -

support activity for the Geosounder concept ESA-GSTP G511-011EE Multi Frequency high resolution GEO-sounder Demonstrator

Description: A retrieval simulator will be developed to support the end to end performance estimates of a ground-based or space based system. The simulator shall be implemented to facilitate retrieval simulations, and will contain modular code comprising algorithms that already implemented in existing published 2d aperture synthesis and image formation schemes (e.g. SMOS). The simulator shall provide a basis for refining and consolidating the data processing steps and geosounder product specifications, whilst also enabling analysis of the performance consequences of changes in key system specifications - as well any compromising impact on the key mission requirements. The following building blocks are envisaged:

- User Interface (e.g. Orbit or Geolocation, Pointing) - Geophysical Parameter Space - Ancillary Data, e.g. model output from ECMWF - Scene Generation Module - Pointing, Observation System (including Instrument, Calibration and Level 1b

processing) Modules - Level 2 Processing Module - Performance Evaluation/Validation Module

Typical tasks of the end-to-end simulator (E2ES) would include: Task 1: Technical Specification, Detailed Design and Interfaces Task 2: E2ES development and integration Task 3: Geosounder System Verification and Validation Task 4: Support for Mission Performance Assessment Task 5: Support for integration and E2ES verification/validation

Deliverables: Software and study report


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2015. GEO-sounder Demonstrator


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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-020EO Budget (k€): 200 Title: Geosounder Requirements Consolidation Study Objectives: The Geosounder Requirements Consolidation Study will support the activity for the

Geosounder concept development (ESA-GSTP G511-011EE - Multi Frequency high resolution GEO-sounder Demonstrator)

Description: Current generation of sounders are embarked on-board low Earth orbit (LEO) satellites for providing primarily meteorological data for numerical weather forecasting, and on the second level global observations for climate monitoring. Across-track scanning of the antenna beam enables to achieve a wide measurement swath exceeding 2000 km. Sufficient spatial resolutions can be achieved around the nadir with a relatively small antenna size (around 1 m diameter). However, due to the rapidly increasing incident angle for off-nadir observations, the spatial resolution is greatly degraded towards the swath edges. The global coverage is achieved by the combination of high ground-projected speed of the spacecraft on polar LEO combined with the rotation of the Earth. Geostationary observations, unlike those from LEO satellites, have the key potential advantage to provide continuous coverage of the same region, which is essential for nowcasting or tracking of bad weather phenomena. Observations in the microwave (MW) region, going up to sub-millimeter-wave frequencies, are less affected by the presence of clouds, and are used as complements to the TIR observations as described in the previous section. Due to the large aperture size required to achieve a reasonable horizontal resolution, its use has so far been restricted to the case of Low Earth Orbit (LEO) satellites. However, the concept of GEO interferometric observations at mm-wave frequencies is a solution to the problem as this instrument will use a synthetic aperture to achieve the required resolution on-ground. This is the basic concept behind the Geosounder. As an essential input to the system studies and other technical support activities, consolidated mission requirements are needed. The purpose of this study is to provide these data, and to ensure traceability between the system specifications and the user defined needs. The scientific objectives of the mission are grouped into specific themes for Numerical Weather Forecasting and Nowcasting. For each theme, quantitative requirements on atmospheric scientific products will be generated, using expert judgement in the wider science community. Requirements will be summarised and the key driving science applications clearly identified. These scientific user requirements on atmospheric data products will be translated into requirements on optimal combination of channels, their radiometric characteristics, and the time/space resolution of the measurements taken by the sounder. The study shall be initiated in phase with the Geosounder system concept studies to enable positive feedback in relation to trade-off decisions, and resolution of potential conflicting requirements on the basis of scientific criteria. Study Tasks include:

Task 1: Literature review Task 2: Level-2 (geophysical product) Mission Requirement Consolidation Task 3: Level-1 (instrument level) Mission Requirement Consolidation

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Task 4: Impact study of technical trade-offs on Level 2 products Task 5: Industrial Study Support (TBC)

Deliverables: Study Report

Current TRL: Not applicatble Target TRL: Not applicatble Duration (months)

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Multi Frequency high resolution GEO-sounder Demonstrator. 2015

Applicable THAG Roadmap: Not related to a Harmonisation Subject.

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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-021EO Budget (k€): 1,000 Title: EVOlution of EO Online Data Access Services - EVO-ODAS Objectives: This project shall address the evolution of technologies and standards supporting

next generation of EO Online Data Access Services.

Description: Both candidate technologies and standards need to be analysed prototyped and benchmarked taking into account as much as possible the current evolution towards widely adopted geospatial standards. Increasing demands for earth observation data being online, i.e. accessible without delay and through standard interfaces, and evolving IT capacities, technologies and web standards call for further development of existing EO online data access services and standards. New and evolving technologies and standards and open source implementations for online EO data access services shall be tested, prototyped, benchmarked and evaluated with respect to the following five high level requirements:

- The ability for integration in payload data ground segment systems providing back-end interfaces for: typical data upload scenarios such as bulk and continuous ingestion and registration as well as integrating with, linking to and updating of metadata catalogues.

- The ability to integrate heterogeneous primary data originating from different sensor families (SAR, optical low/high resolution, atmospheric, hyperspectral) taking into account their specific properties.

- The ability to integrate different data publication scenarios such as near-realtime, continuously growing time series, and spatial/temporal aggregation/mosaicking on 2D as well as multidimensional datasets.

- The specific functionality for visualising and downloading time series on a scene-by-scene basis as well as the full series with optional spatiotemporal and domain subsets in one step using adequate world reference systems and file formats.

- The performance of ingestion/registration and access functions with defined scenarios and original EO data sets. This evaluation shall result in a further evolution of standards and tools to serve the seamless integration of online EO data in applications.

The technology and standard development shall be supported by extensive benchmarking in order to ensure that follow on implementation projects within the payload data ground segment can support the high data rates and complex interaction scenarios with which EO users are faced. The new technologies addressed by this project will have to be explored and studied in connection with current trend towards open source implementations of geospatial standards.



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2015. Next generation of EO online data access services.

Applicable THAG Roadmap: Not related to a Harmonisation subject.

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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-022EO Budget (k€): 500 Title: Technology and Atmospheric Mission Platform (TAMP) Objectives: The general aim of the project is twofold. On one side there is the need to develop,

prototype, benchmark and test new technologies able to support the implementation of the so-called exploitation platform. On the other side there is the need to assess, validate and demonstrate the potentialities of the concept of exploitation platform across multiple communities.

Description: Although forthcoming missions will provide important information to meteorologists, both operational and scientific, these missions address atmospheric composition and physics. So project main reference communities are all in the field of Atmospheric Science. This project will concentrate on specific technologies needed to demonstrate the "exploitation platform" concept, with particular focus on data management and exploitation needs related to forthcoming missions (EarthCare, Sentinel-4 and Sentinel-5). The "exploitation platform" is an ideal environment for a wide range of communities - that make use of satellite data - to implement their own processing systems. It is envisaged it will permit direct access to a wide set of data, providing at the same time large cloud computation resources for their processing. A scientific end-user will be able to install his/her own algorithms within the platform, especially in case fusion/assimilation between satellite data and other data sources requires high computational resources and storage space. Such an approach allows to dramatically reduce the requirement of extensive and expensive storage and computational resources at user's premises, making use of those made available by EO stakeholders or other third party cloud computing providers. The remote processing can be triggered either through an interactive web user interface and/or through standard processing invocation protocols, e.g. a Web Processing Service (WPS) call. Within the project, the following technology requirement and/or technical issues, related to exploitation platform(s) implementations, shall be addressed:

1. Understand the technology requirements and implementation aspects of data access, data security and users' accounting;

2. Verify how far the Open Geospatial Consortium standards, interoperability concepts and technologies could be implemented, in particular for processors deployment, processing invocation and results retrieval;

3. Enlarge the number of communities involved in the prototyping, demonstration and evaluation of "exploitation platforms" through: - Benchmarking, testing and prototyping relevant technologies and

prototyping and implementing the technical tools that can permit a better use of the system (interfaces, web processing services, etc.);

- Defining a high level roadmap for the prototyping and demonstration of services;

- Demonstrating and validating the usability of the system and identifying its advantages through the prototyping and implementation of one or more demonstrators;

- Informing different scientific communities and promoting the use of the system implementing some reference datasets.

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A number of scientific communities (also from different domains) can benefit from the use of such "exploitation platforms", in particular for accessing and processing next generation of EO data to be provided by forthcoming missions. Demonstrator will permit to promote such a concept among different user communities, complementing already planned facilities. The project should participate in testbeds and complement with benchmarking the HMA standardization coordinated by ESA



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2015. EarthCare, Sentinel-4 and Sentinel-5.

Applicable THAG Roadmap: Not related to a Harmonisation subject

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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-023EO Budget (k€): 800 Title: Multimission Environmental DatA - MEDeA Objectives: The objective is to test, benchmark and develop techniques for systematic and on-

demand processing and exploitation of multimission environmental satellite data jointly with SAR X-band data products on coastal areas (land and sea).

Description: The project shall develop enabling techniques for a set of products related to the marine domain. It shall address the techniques for systematic data integration of X band SAR data with S1 products at lower resolution, but with higher repeat cycle, as well as of Sentinel 2, EROS optical data, S3 multispectral data and in-situ data. The project, assuming that basic systematic pre-processing and co-registration is already performed, shall address data and product processing techniques and the relevant processing environment and database techniques finalised at the extraction and classification of thematic information including the generation of temporal time series. For SAR products, the processing shall address the removal of all the non-homogeneous areas (such as marine areas with ships, coastline, atmospheric fronts and more generally atmospheric artefacts and phenomena) over the homogeneous marine background. The S-3 multispectral data allows to determine parameters such as sea-surface topography, sea-surface temperature, ocean colour with high-end accuracy and reliability mainly focused on coastal domain. Location based data processing techniques shall be benchmarked in order to dynamically include potentially available in-situ data. Several scenarios and demonstration use cases shall be defined for benchmarking purposes, in order to stress the developed tools and techniques for automation of systematic processing and information extraction. This project aims to test technologies, design and prototype the implementation of a monitoring system for maritime ecosystem and coastal environment on EO satellite data, combined with in-situ data and integrated with sea circulation models. The system shall permit the full exploitation of multi-mission data, also from heterogeneous sources. The activity shall include:

- The analysis benchamerking and prototype implementation of automation techniques for systematic processing of large amounts of multimission data including time series over large coastal areas;

- The integration of developed components in a final prototype system; - The final system shall support both routine and on-demand processing, also

in near-real time when requested. Public agencies and institutions could benefit from the use of such developed technologies and of the prototype system. Scientific communities in the field of marine and coastal environment could take advantage from the integration and use of sea circulation models and integration/assimilation of EO multimission data.



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Target Application / Timeframe:

2015. Processing and explotation of Earth Observation Data


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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-024EO Budget (k€): 2,000 Title: Technologies for the Management of LOng EO Data Time SEries -

LOOSE Objectives: This project addresses the technology development, selection and benchmarking

for the management of long time series of EO data.

Description: The continuously increasing amount of long-term and of historic data in EO facilities in the form of online datasets and archives makes it necessary to address technologies for the long-term management of these data sets, including their consolidation, preservation, and continuation across multiple missions. The management of long EO data time series of continuing or historic missions - with more than 20 years of data available already today - requires technical solutions and technologies which differ considerably from the ones exploited by existing systems. Novel technical and organizational solutions for durable efficient handling, storage, and access of long EO data time series are needed. To satisfy new access and data exploitation scenarios, the archiving structures and data models will have to facilitate user-friendly bulk data retrieval, data mining and data analytics, visualization, processing, and accessing localized time series data stacks, as well as displaying and downloading data layers served by standardized spatial data services. New technologies and advanced approaches will have to be studied and proved to be fit for the purpose before implementation into the existing ground segment infrastructure. In order to exploit the valuable EO data time series in the future, new archiving and access technologies will have to be designed, developed, and implemented today. The new technologies addressed by this project will have to be explored and studied in connection with long-term preservation requirements calling for data replication and maintenance of double archive copies. Multiple data copies structured differently, as an example, may be a way to serve specific data access scenarios. This would require the use of alternative indexing schemas and new overall management systems. Project Deliverables:

- Technology benchmarking and development on long time series storage, data management, data retrieval, data mining and data analytics

- Requirements and Design Documents - Developed prototypes software and tests - Validation, Demonstration tests and results



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2017. Processing and explotation of Earth Observation Data


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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-025EO Budget (k€): 900 Title: FAst Multimission tEstbed architecture - FAME-C Objectives: This project addresses the technology development, selection and benchmarking

for the prototyping of a processing/algorithm testbed environment and fast data management layer of Earth Observation products.

Description: Several aggregations of users and specific communities have demonstrated the benefits and identified the requirements for a testbed aiming at the development, testing and finalisation of processors and algorithms in thematic areas of interest such as : hydrology, earthquake, landslide and volcanoes, to study phenomena as the terrain movements and the changes of scenarios. All these requirements would lead to establishing proper thematic data subsets for a multitude of missions; none even if each of them alone can contribute assuring to analyze the phenomena, the combined use of more source of data allows a more complete description of it. So, for the purpose of processor/algorithm development testing and validation, the project foresees the data management, and onward data utilisation beyond the community specific requirements of a multiplicity of data sources. Therefore there is the need to develop the necessary technologies enabling the multi-mission testbed environment and data access technologies, within the whole end-to end process directly managed by the user. This will complement and interface already available processing chains which fulfils the use case of EO data already in archives or processing centres. Therefore this project will study, benchmark and develop as well the basic technologies for fast data access and circulation. In this context it is furthermore necessary to develop enabling technologies finalised at the development and demonstration of the testbed environment for the development and/or the deployment of processors and or algorithms provided by the user enabling the synergic exploitation and the use of EO data received and or collected from different missions with different spatial resolution and acquisition frequency (e.g. S1, Cosmo-Skymed) and available under different data policies. In particular the Cosmo-Skymed mission is a dual use mission. The objective of this project is the technology analysis, benchmark and selection, the architecture definition, prototyping and demonstration of a a processor/ algorithm testbed environment and fast data management layer capable of the handling and circulation of 2-10 Terabytes per day of Earth Observation products with a persistence time in the processor/testbed environment ranging from six months to two years. The testbed will be dedicatedmonstrated addressing to geohazard themes. The architecture shall foresee in particular the possibility:

- to interface (e.g. through specific use cases) with the MM DH project prototype to access archives and collect the dataset

- to hostdevelop, fine tune, test and validate processors and algorithms provided by the user;

- to perform scheduling and processing of multi-purpose (test) processors and/or (test) algorithms;

- to ensure data and process segregation for individual users and/or communities;

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Earth Observation testbeds and thematic data aggregations and platforms have been proposed by universities, industry, research centres and institutions. The proposed architectures expand the classic functionality of the Earth Observation payload data ground segment by separate environments - even geographically distributed - dedicated to processor and algorithm development and associated data management and processing. EO data users have expressed the interest in new data exploitation approaches and the requirement of reducing the burden related to the management of large amounts of EO data and the related processing costs during the processor / algorithm development phase.



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2015. Earth Observation products


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Service Domain EARTH OBSERVATION Technology Domain 26 EO (Systems and ground segment) Ref. Number: G611-026EO Budget (k€): 800 Title: ESE ERGOnomic User Interface ESE_ERGO Objectives: This project addresses the technology selection, development and benchmarking

for the prototyping of next generation user interfaces for EO product and derived information and/or data visualization analysis and access.

Description: The wide availability of wireless and mobile communication and the maturity of handheld devices has changed the day to day connectivity of users including scientific ones. Applications can warn about data availability, completion of processes, results of tests, and so on. Furthermore there are examples of Web-based applications that provide a simple and intuitive way to visualize, analyse, and access vast amounts of Earth Observation data without having to download the data. From the researcher's point of view, a number of interfaces could be developed and tailored, to meet the needs of specific fields of Earth Observation research, and same or part of the interfaces could be part of mobile applications. These applications could as well exploit location based services empoweing the users with multi-modal interaction. The selected technologies shall be demonstrated on protoype user interfaces tailored for use cases within the VITO ESE on-demand processing environment. The issue of more efficient and high-performance computational models should be also addressed in view of transferring applications and services to portable devices, e.g. for deployment onto the Android Operating System of smartphones and tablet computers. From a technology point of view several challenges need to be addressed. First of all the whole interaction model needs to be re-defined possibly splitting functionality across multiple devices and exploiting location based services for the definition of the area of interest. The possible mix of functions developed in multiple programming and data manipulation languages like C, Java, Mathlab, IDL etcetera, has to be addressed as there are language specific features (e.g. compilation versus interpretation or just in time compilation) which need to be addressed taking into account the target platform. Furthermore the evolution of COTS and toolboxes, as well as the emerging meta-languages will have to be taken into account. Furthermore the project shall address the analysis, definition and implementation of state-of-the art user interfaces (mobile/tablet/touch) taking into account an ergonomy analysis via heuristic evalution and interface usability.



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2015. Earth Observation products


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4.2 SD3- Human Spaceflight

4.2.1 TD 2- Space System Software

Service Domain HUMAN SPACEFLIGHT Technology Domain 2 Space System Software Ref. Number: G613-003GD Budget (k€): 750 Title: METERON Operations Environment Monitoring and Control (M&C)

component on the International Space Station (ISS) Objectives: The objectives of this activity are:

- to analyse the options for deploying the required Monitoring and Control (M&C) components of the METERON Operations Environment (MOE) on the ISS, which would allow the Astronauts to participate in METERON system level Monitoring and Control of Robotic Experiments.

- To implement and validate the selected option (e.g. migration vs new development) in support of the future METERON experiments, in particular the OPSCOM-3 and SUPVIS-Eurobot experiment.

Description: The Multipurpose End-To-End Robotics Operations Network, in short METERON,

is an international, multi-agency collaboration project to prepare for future robotic exploration missions. The METERON project is led by ESA and supported by NASA, DLR and Roscosmos. The main objectives of METERON is to evaluate and demonstrate concepts and technologies that are being considered for use in future human exploration in the areas of

- Communications: Issues such as disruption tolerance, delays caused by distance, hard real-time communications (video, haptic data, etc.) and multiple asset communications

- Operations: Issues such as human-in-the-loop rover/robot operations, multi-rover operations, multi-operator interaction, and monitoring and control of systems-of-systems

- Robotics: Issues such as haptic telerobotics, operations of multiple autonomous rovers (at different locations or at the same site), and human/rover collaboration

METERON can be seen as a test-bed for executing experiments in any of the above-mentioned three domains. Any robotic element participating in a METERON experiment comes usually with its own customised monitoring and control. The current METERON Operations Environment (MOE) has monitoring and control (M&C) components, which are deployed at a number of geographically distributed entities, who are involved in coordinated operations of the METERON experiment. Currently MOE M&C component are not deployed on the ISS. MOE incorporates also a set of generic robotic services, which abstract from and encapsulate the proprietary interfaces of different robotic systems and expose a unified interface toward the rest of MOE components. The MOE robotic services are deployed on the ground and on the ISS. Their current specification and implementation has been kept generic. However it is very likely that certain adaptations would be required, once the consumers/providers of these services (i.e. the other MOE components) are relocated from the Ground to the space on the ISS. The METERON software systems on the ISS are deployed on a laptop of type T61P (model specification).

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The deployment of a MOE M&C components on the ISS, which would allow the Astronaut to participate in the coordinated operations of METERON experiments, is not a trivial issue since the current MEO software would need to be adapted with respect to applicable constraints of the ISS environment, such as:

- Limited accessibility to METERON infrastructure on the ISS from the ground - Change of the operating system baseline as compared to the current MOE

baseline on the Ground - Limited bandwidth for upload of the installation/patches/update packages

limits the size of the binary builds of the MOE components and the choice of reused 3rd party and infrastructure software

- Limited computing resources of the available METERON hardware platform T61P (performance issues)

- requirements related to fully automate the deployment and configuration of the applications

- Enhanced Security aspects The objective of this study is to analyse the impact of these requirements on the relevant components of the MOE and evaluate the options for provisioning of MOE M&C components on the ISS in support of the future METERON experiments, in particular the OPSCOM-3 and the SUPVIS-Eurobot experiment and to perform the adaption. In particular, the following tasks shall be done:

- Analyse the constraints applicable to the ISS environment (e.g. limited accessibility, change of operating system baseline as compared to the current MOE baseline, limited bandwidth for upload of the installation/patches/update packages, limited computing resources of the available METERON hardware platform T61P, requirements related to fully automate the deployment and configuration of the applications, etc.) and evaluate their impact on the relevant MOE monitoring and control components;

- Analyse different options for migrating the current implementation of the relevant MOE components vs implementation of new light-weight versions of the required components for deployment on the ISS

- Analyse the impact of deploying the MOE M&C components not only on the Ground but also on the ISS on the METERON robotic services

- Adapt the specification and implementation of the METERON robotic services accordingly

- Adapt the METERON robotic services to use the CCSDS Massage Abstraction Layer (MAL)

- Implement a MAL over BP/DTN (Bundle Protocol/Delay Tolerant Network) transport, suitable to the current ISS bandwidth constrains and adapt the METERON robotic services to use it

- Validate the MOE M&C components on the ISS using system-level simulations

- Support the validation of the MOE M&C Components on the ISS and the adapted METERON Robotic services as part of OPSCOM-3 and SUPVIS-Eurobot experiments



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METERON 2015-2016, future human and robotic exploration missions


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Service Domain HUMAN SPACEFLIGHT Technology Domain 6 RF Payload and Systems Ref. Number: G613-004ET Budget (k€): 1,000 Title: Down-Converter unit for GNSS Reflectometry Objectives: The objective of the activity is to provide a breadboard at TRL-5 of the Down-

Converter unit to be employed in GNSS Reflectometry.

Description: GNSS reflectometry refers to the use of signals from the Global Navigation Satellite Systems reflected off the Earth surface for remote sensing. It is an area of growing interest which goes hand in hand with the intense development of GNSS systems, their technology and applications. ESA has pioneered GNSS reflectometry by proposing this technique in 1993 for mesoscale ocean altimetry, also including wind and significant wave retrievals: the Passive Reflectometry and Interferometry System (PARIS). Since then ESA has conducted many studies and near-ground experiments. More recently a Phase A study was carried out on a free-flying small satellite embarking a GNSS-R based ocean altimeter: the PARIS In-orbit Demonstration mission (PARIS IoD). In the near future another Phase A study will be started on a GNSS REflectometry, Radio Occultation and Scatterometry experiment on board the International Space Station (GEROS). One of the main results of the PARIS IoD Phase study is that high gain is needed to perform accurate mesoscale ocean altimetry using the original PARIS interferometric technique. This, in combination with the fact that several reflection points are to be observed, leads to a technological solution based on a high-gain multi-beam back-to-back antenna array. This solution requires the use of a beamformer followed by a down-converter unit. Each of the beams produced by the beamformer at radio-frequency has to be frequency shifted to a suitable intermediate frequency by the down-converter unit. Because the beams are generated at a set of GNSS frequency bands, typically a lower band (like Galileo E5 or GPS L5) and an upper band (like Galileo E1 or GPS L1), the down-converter unit has to be multi-frequency in general. The output of the down-converter unit is to be fed into a correlator unit which performs the analog-to-digital conversion and final frequency shift to align the Doppler (and delay) of the direct signal to those of the reflected signal. Special care is to be taken in the frequency plan of the down-converter unit to avoid harmonics of the local oscillator signals falling in the different GNSS bands while facilitating the design of the following correlator unit by properly choosing the intermediate frequency. The present activity aims at consolidating the required technology for GNSS-R by breadboarding, up to TRL5, a Down-Converter unit for future ESA's GNSS-R missions. The activity shall include:

- definition of the technical requirements of the Down-Converter unit starting with the high level requirements, including electrical, mechanical and thermalrequirements

- design of the Down-Converter unit, according to the technical requirements - manufacturing of the Down-Converter unit - tests of the Down-Converter unit to prove the fulfilment of the technical

requirements

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This unit could be integrated, in the frame of another follow-on activity, in an airborne demonstrator of an advanced GNSS-R instrument.

Deliverables: Flight representative breadboard


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PARIS IoD, GEROS / 2017


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Service Domain HUMAN SPACEFLIGHT Technology Domain 6 RF Payload and Systems Ref. Number: G613-005ET Budget (k€): 1,000 Title: Beamformer Breadboard for GNSS Reflectometry Objectives: The objective of the activity is to provide a breadboard at TRL-5 of a Beamformer

to be employed in GNSS Reflectometry missions.

Description: GNSS reflectometry refers to the use of signals from the Global Navigation Satellite Systems reflected off the Earth surface for remote sensing. It is an area of growing interest which goes hand in hand with the intense development of GNSS systems, their technology and applications. ESA has pioneered GNSS reflectometry by proposing this technique in 1993 for mesoscale ocean altimetry, also including wind and significant wave retrievals: the Passive Reflectometry and Interferometry System (PARIS). Since then ESA has conducted many studies and near-ground experiments. More recently a Phase A study was carried out on a free-flying small satellite embarking a GNSS-R based ocean altimeter: the PARIS In-orbit Demonstration mission (PARIS IoD). In the near future another Phase A study will be started on a GNSS REflectometry, Radio Occultation and Scatterometry experiment on board the International Space Station (GEROS). One of the main results of the PARIS IoD Phase study is that high gain is needed to perform accurate mesoscale ocean altimetry using the original PARIS interferometric technique. This, in combination with the fact that several reflection points are to be observed, leads to a technological solution based on a high-gain multi-beam back-to-back antenna array. This solution requires the use of a beamformer, a microwave circuit that combines the outputs from the antenna radiating elements with a proper phase to produce a high gain beam pointed in a specific direction. By splitting the output of the antenna elementsseveral beams can be created in parallel and by adding multiplexers the beams can work at the different frequency bands of GNSS systems. The present activity aims at consolidating the required technology for GNSS-R by breadboarding, up to TRL5, a dual-frequency beamformer suited for future ESA's GNSS-R missions. The activity shall include:

- definition of the technical requirements of the Beamformer starting with the high level requirements, including electrical, mechanical and thermal requirements

- design of the Beamformer, according to the technical requirements manufacturing of the Beamformer

- tests of the Beamformer to prove the fulfilment of the technical requirements This unit could be integrated, in the frame of another follow-on activity, in an airborne demonstrator of an advanced GNSS-R instrument.

Deliverables: Flight representative breadboard


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PARIS IoD, GEROS / 2017


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4.2.3 TD 9- Mission Operations and Ground Data Systems

Service Domain HUMAN SPACEFLIGHT Technology Domain 9 Mission Operations and Ground Data Systems Ref. Number: G613-006GD Budget (k€): 500 Title: METERON Experiment Specific Data Systems Objectives: Enhance Meteron Operations Environment (MOE) and METERON robotic services

in support of future METERON Experiments, in particular OPSCOM-3 and SUPVIS-Eurobot experiments

Description: The Multipurpose End-To-End Robotics Operations Network, in short METERON, is an international, multi-agency collaboration project to prepare for future robotic exploration missions. The METERON project is led by ESA and supported by NASA, DLR and Roscosmos. The METERON project aims to evaluate and demonstrate concepts and technologies that are being considered for use in future human exploration in the areas of

- Communications: Issues such as disruption tolerance, delays caused by distance, hard real-time communications (video, haptic data, etc.) and multiple asset communications;

- Operations: Issues such as human-in-the-loop rover/robot operations, multi-rover operations, multi-operator interaction, and monitoring and control of systems-of-systems;

- Robotics: Issues such as haptic telerobotics, operations of multiple autonomous rovers (at different locations or at the same site), and human/rover collaboration.

In this context METERON can be seen as a test-bed for executing experiments in any of the above-mentioned three domains. METERON Operations Environment (MOE) is the envelope name used for a set of data systems both on the ground and on the ISS, which together provide harmonsided, distributed monitoring and control capabilities at system level for METERON experiments. Typically multiple entities (in different geographical locations) are involved in operations of METERON experiments and each robotic system participating in the experiment has its own data systems with proprietory interfaces and man-machine interfaces. In order to abstract from these proprietary interfaces, MOE adopts a set of generic robotic and monitoring and control services, which encapsulate the interface to diverse subsystems. The goal of this study is to specify and implement new METERON robotic services and enhance the METERON Operations Environment in support of the OPSCOM-3 and SUPVIS-Eurobot experiments. In particular, the following tasks shall be done in the frame of this activity:

- Analyse the envisaged scenarios and the related requirements of the OPSCOM-3 and SUPVIS-Eurobot experiments and identify the required enhancements of the MOE and robotic services

- Specify and implement new METERON robotic services in support of the above mentioned experiments

- Enhance MOE monitoring and control components in support of the above mentioned experiments

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- validate the new METERON robotic services and the enhancements of MOE for the above mentioned experiments

- support the system level validation of the above in the context of the OPSCOM-3 and SUPVIS-Eurobot experiments



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METERON (2016), future human and robotic exploration missions


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Service Domain HUMAN SPACEFLIGHT Technology Domain 12 Ground Station System & Networking Ref. Number: G613-007HS Budget (k€): 750 Title: Development of low latency communications system for "real-time"

haptic tele-robotic operation. Objectives: The objectives of this study are the following:

- To refine or define a protocol for transporting "immersive" operations

parameters with as good delay and jitter performance as manageable while still maintaining a high reliability, a defined quality of service(QoS) and a high quality of experience(QoE).

- To take into account the definition of tele-robotic reference scenarios as set

out in the CDF report for the METERON project.

- To study how to relay redundantly the information through multiple available communication channels.

- To study how to to define different service levels implementable depending

on available communication channels.

- To perform near real-time resource management, scheduling and logging of services rendered.

- To provide a monitoring facility where the performance parameters

(latency, jitter, QoS, QoE, information rate etc.) is enumerated throughout the communication sessions and can be reviewed from a control centre.

- To provide a feature where a control centre can interface to schedule, add

and remove resources during the communication sessions.

- To contribute to the development of inter-agency standards for this type of services.

Description: Considering a scenario where humans are orbiting a planetary body in the solar

system, they wish to tele-operate robotic equipment on the surface. This in preparation of a landing site, to assemble some other ground based infrastructure or to immersively perform some tactile feedback research tasks. For such a scenario to offer the sufficient fidelity to perform the wanted tasks it is needed to prepare sensors, actuators, immersive human interface devices and protocols to safely relay the communication between the distributed elements of the system. This study should limit itself to the protocols required for regulation of the information flow and the timely scheduling of the resources in an automated way, either centrally monitored or fully autonomously operated When conducting immersive telepresence robotic operations of a robot/rover from an orbiter it is likely that there will be transitions in the communication chains between the different point to point communications, data relay satellites, robotic elements and ground based infrastructure (used to extend the coverage). An

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example of this could be a robot on the surface of Mars being immersively teleoperated from a manned orbiter via a network of relay satellites. For this type of operation there should be no gaps or delays in data flow to provide as high preceived quality of the service as possible. The first case where this is relevant is METERON (Multi-purpose End-To-End Robotic Operations Network), reference scenario emulation using ISS and exsisting ground based infrastructure on earth. The passes for real-time communication would be relatively short (8 minutes) and it is therefore necessary to concert several ground stations to increase the pass duration. With 3 ground stations that pass duration can be extended to approximately 20 minutes. As stated in the objectives, the activity focus on using or creating a protocol for transporting "immersive" tele-operations parameters with the properties important for such communication. To demonstrate using existing ground and space assets. To put more weight on creating resilience of the network by using redundant but not necessarily identical resources. To have an interface that allows close to real-time resource management, scheduling and logging of services rendered from a control centre. And by doing this also participating in the standardisation within this domain. The activity will take benefit of existing ground and space infrastructure, by applying the minimum transformation necessary.

Deliverables: Software prototype with service management embed.



METERON \ SUPVIS-Eurobot : 2017


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4.2.5 TD 13- Automation, Telepresence & Robotics

Service Domain HUMAN SPACEFLIGHT Technology Domain 13 Automation, Telepresence & Robotics Ref. Number: G613-008HS Budget (k€): 3000 Title: Eurobot upgrade for METERON Objectives: To upgrade the existing "laboratory" human-scale Eurobot (rover/robot) to enable

investigation of rover and robotic tasks in two METERON experiments related to supervisory control and fully immersive telepresence operation in an analogue environment.

- Upgrading of rover/robot software (including flight and ground segment man-machine-interface)

- Upgrading of rover/robot hardware.

Description: METERON (Multipurpose End To End Robotic Operations Network) is a series of experiments in tele-robotics, communications and operations, resulting in a network of flight and ground control stations and robots. These flight and ground elements, the operations with them and the communications between them are developed as preparation for human exploration missions of the future. The series of experiments start out quite simple, with individual robotics elements or communications protocols to be tested standalone. In the end of the series, a complex robot in an analogue site on Earth will be tele-operated from an advanced control station in ISS, in a tele-presence scenario with visual, data and force feedback. This is equivalent to and in preparation for operating a lunar robot from a spacecraft orbiting the Moon. The planned METERON experiments are jointly carried out by the Directorate of Human Spaceflight and Operations, and the Directorate of Technical and Quality Management. They utilise the ISS to investigate three key aspects of an exploration architecture: Operations, Communications and Robotics. As the Eurobot (rover/robot) is the target vehicle for two METERON experiments involving operation from the ISS, it requires upgrading in a number of areas in order to increase its current operational capabilities, and especially to operate as required in an "outdoor" analogue site. In 2011, Eurobot participated in an analogue field-test in Rio Tinto in Spain. Based on this experience, a number of design requirements were identified to improve its capabilities to operate in an external environment. Specific activities to be performed: Software: 1. Upgrade the rover vision system based on parallel TRP studies.

- Performance improvement: The existing vision system (although it can also work outside) is optimised for indoor operation, and works best with a known fixed "target" to which it can localise. For future experiments the vision system needs to be more flexible and reliable. Currently it is very sensitive to ambient lighting conditions as it is colour-based. Other approaches such as shape/target-based localisation (using e.g. OpenCV) where particular physical shapes are analysed in the image, or Infra-Red-based reflection would offer greater robustness and flexibility.

2. Implement an open software architecture and improve software robustness by combining the software on the several Eurobot-mounted computers on the mobile segment (rover/robot) onto a single computer. This activity will include implementation of an updated man-machine-interface for the ground segment

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control software. - Performance improvement: For the initial development of the Eurobot

prototype, several computers each running specific software, were used on the mobile segment. While sufficient to meet the original objectives of the use of the rover/robot, integrating the required software onto a single computer (i.e. reducing the interfaces) would significantly increase the overall reliability of the control system, and simplify the overall configuration of the system (as currently there are several configuration files in different areas).

3. Provide software for the upgrade of the ISS based flight man machine interface already on board from the initial METERON experiments.

Hardware: 4. Replace the Eurobot arms by Dexarm and Kuka arm, including integration of

existing end-effectors: - The existing arms, although adequate for demonstration of simple tasks, if

replaced by more performant arms would allow Eurobot to perform complex tasks more relevant for investigation of planetary surface exploration scenario activities, with force feedback to the operator. Note Dexarm is a flight-qualified robotic arm.

5. Robustness improvement for analogue testing: - Based on the experience gained in the analogue test in Rio Tinto in 2011

several design requirements were identified to improve operation of the rover/robot in the field.

- Rover platform: The platform at the rear of the rover requires modification to enable transportation of equipment to be deployed during a traverse.

- Seat/back-rest: As the backpack on an EVA suit is quite heavy, the astronaut being transported by the rover during the analogue test, found standing tiring. A seat/back-rest would prevent this occurring.

- Camera assembly: With a crew member on-board the rear platform, the forward field of view is obstructed. The positioning/fixation of the rover camera would alleviate this.

- Rear-view mirrors: The capability for the existing rear view mirrors to be adjusted would provide the crew member with an improved rear viewing capability.

- Sensors: The current positioning of the ultrasound sensors is very close to the ground severely limiting the rover/robot to negotiate reasonably rough terrain. Re-positioning of these would remove this imitation. The relative wheel encoder sensors should be absolute ones to allow rover restart if it would get stuck in the analogue field test.

- Joystick: Being required to continuously hold down the "dead-man" button while manually driving the rover/robot becomes a burden when required for long periods during a traverse. A more "crew-friendly" implementation would alleviate this issue.

- Protection of on-board equipment from moisture and dust. - Improvements in power provision (batteries, generator).



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METERON planning aims to perform the supervisory control experiment in 2015, and the operation in an analogue environment experiment in 2016.

Applicable THAG Roadmap: Automation & Robotics (2012)

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Service Domain HUMAN SPACEFLIGHT Technology Domain 13 Automation, Telepresence & Robotics Ref. Number: G613-009MM Budget (k€): 1100 Title: Exoskeleton (XR-2) Bi-manual flight mechatronics system Objectives: It is the objective of this activity to develop a FM hardware unit of a novel robotic

control station centered around an dual arm force-reflective exoskeleton for bi-manual teleoperation of robots over large distances.

Description: Within this activity, the contractor shall design and develop, in close coordination with ESA, a new exoskeleton bi-manual flight hardware for usage on-board the ISS. For this purpose, the contractor will be responsible for the design, integration, verification and testing of the bi-manual exoskeleton. The contractor will develop 4 complete units (2 ground units, 2 flight ready units) of the dual-arm exoskeleton, which consists of each:

- two force reflective exoskeletons (mechatronics,i.e. mechanical and electrical sub-systems) - two adaptive finger force-feedback devices - one back-pack unit including flight computer, control computer and associated electrical units. - one complete housing and cable-harness unit.

The design advancement and development can make use of COTS parts, however needs to comply with safety regulations applicable for ISS payloads. In terms of development, mainly the joint electronics of the exoskeleton shall be up-graded and be custom-designed. A custom power conditioning and management unit shall be developed that is optimized for robotic applications. The other components will make use of design-heritage from a system currently being developed by ESA. This work shall include all development of embedded software necessary for joint torque control at a 5 kHz rate and the software necessary to load motor control software into each joint control unit. The output of this activity will be used in a flight demonstration performed from on-board ISS. The ISS experiment, which will make use of the dual-arm exoskeleton shall demonstrate advanced telerobotic control capabilities of ESA and partners. The on-board control station, developed partially under this contract, will serve as an input device to control multiple robotic devices on ground and to deliver force reflection back to the operator. The dual-arm exoskeleton will interact with the arms and hands of an operator and will be connected to a flight control unit.

Deliverables: Qualification Model


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Service Domain HUMAN SPACEFLIGHT Technology Domain 13 Automation, Telepresence & Robotics

Ref. Number: G613-010MM Budget (k€):

400

Title: Development of QM/FM 3D vision display system Objectives: It is the objective of this activity to up-grade the on-board vision system of the

current HAPTICS-1 payload on ISS with a new flight-model display system that supports depth perception for the operators.

Description: This activity will belong to a series of technology demonstration experiments ESA is performing from on-board the International Space Station. The 3D vision display system will be used as primary interface by crew on-board ISS when performing real-time control of robotic assets on Earth. This way, the vision display system shall be able to support telepresence and the design shall be optimized to enhance situational awareness of crew during the remote control tasks. The contractor shall perform the development, in close collaboration with ESA. As such, the contractor will design, procure, assembly and test the display station and it's operation software to the levels required by ISS payloads. It is the scope to develop a total of 4 display units, 2 of which will be used on ground and 2 of which are in flight ready state. It will be the primary task of the vision display system to display streamed 3D stereo content in real-time to the astronaut from ground. For this purpose, the software has to be compatible with various communication architectures, which will be specified by ESA. Moreover, the vision system has to support user input, in order to intuitively perform camera system control from on-board ISS. The development therefore will make use of COTS hardware (as much as possible) that is adjusted to the flight experiments needs. The functions that the display system has to fulfull are the following:

- camera display in 3D (stereo) in real-time - configurable camera parameters by operator in intuitive manner - tracking of head position of operator to adjust camera control in real-time - selective display of engineering features in camera stream

The contractor shall design and develop, in close collaboration with ESA,

- all hardware necessary to display and capture head motion - all software necessary to operate the vision display system (including a

ground camera system that can be controlled for testing) - all test hardware necessary for qualification, functional testing and calibration

Deliverables: Engineering Model and Flight Model


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4.2.6 TD 14- Life & Physical Sciences

Service Domain HUMAN SPACEFLIGHT Technology Domain 14 Life & Physical Sciences Ref. Number: G613-011MM Budget (k€): 450 Title: Miniaturized real time quantitative PCR: Mini q-PCR Objectives: The objective is the further development of a MEMS based technology for

biomolecular analysis using PCR (Polymerase Chain Reaction). By using existing efforts and progress made already in terrestrial R&D, a breadboard suitable in fit and function for spaceflight applications shall be built and tested.

Description: Biomolecular analysis using PCR (Polymerase Chain Reaction) for amplification and detection of genetic information is a standard tool in life science research. The progress made in MEMS technology offers now the possibility to integrate PCR functions on a single chip. For spaceflight applications, no generic platform for molecular analysis is available for life science research, samples have to be analysed on ground with the constraints of mass for download, sample preservation and storage. To address this limitation and support the needs of a large life science community (i.e. study of effect of radiation, effect of microgravity, cellular biology studies, medical molecular diagnostic, physiological diagnostics, microbial environmental characterisation etc.), it is proposed to study the feasibility to develop a generic miniaturized real time quantitative PCR/RT PCR breadboard. Activity description:

- Existing know-how and technologies available in the field of molecular biology and Lab-on-a-Chip technologies will be reviewed. Special attention will be paid to critical sub technologies like microfluidics, assay chemistry, micro-technology, to design a system for the analysis of small fluidic volumes and with a high level of functional integration. Based on this review, the feasibility to develop a miniaturized real-time quantitative PCR/RT-PCR system will be studied. Use cases will be established

- Design of prototype system - Manufacturing and test. - A preliminary concept for space application will be proposed, critical issues

will be identified and a Design and Development Plan (DDVP) established for reaching flight readiness.

Deliverables: Fully functional breadboard, Design and Development Plan, Commercial

evaluation


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Life science research (ELIPS-5), 2015

Applicable THAG Roadmap: Not related to a Harmonisation subject.

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Service Domain HUMAN SPACEFLIGHT Technology Domain 14 Life & Physical Sciences Ref. Number: G613-012MM Budget (k€): 700 Title: Miniaturised turbomolecular vacuum pump for analytical

instrumentation Objectives: The objective is the development of a miniaturised turbo molecular (tm) vacuum

pump to provide high quality vacuum for analytical instrumentation (GC-MS). Target applications are instrumentation for exploration and human spaceflight (analytical instrumentation, identification of chemical contaminants).

Description: Mass Spectrometers are the working horse and reference instruments for identification of chemical and isotopic species on exploration missions and as well for the identification of hazardous substances during long term space missions in a manned environment. The identification of the species by means of a mass analyser requires a high quality vacuum (10E-8 bar and better). Currently in Europe turbomolecular (tm) pumps are not available below a mass of one kg. Further downscaling requires high machining precision, more stages and higher rotational speeds (>200krpm). A European development would provide non dependency and independence from ITAR restrictions. Capable European industry exist for laboratory instrumentation (mass market), but commercial applications are not yet emerging. However, the availability of small turbomolecular pumps and even small scroll pumps would increase the potential for mobility of analytical instruments, e.g. for security and safety applications and open up market potential. Activity description:

- Review of current technology and improvement potential to reduce mass/power and maintain performance parameters of TM pumps

- Design and manufacturing of a set of pumps - First set of qualification tests (shock, vibration), performance and life test - Destructive analysis of specimen - Design and Development Plan and roadmap for qualification of hardware



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Instrumentation for exploration and human spaceflight (scientific applications and as well safety/hazard monitoring for chemical contamination species) / 2018


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Service Domain HUMAN SPACEFLIGHT Technology Domain 14 Life & Physical Sciences Ref. Number: G613-013MM Budget (k€): 600 Title: 3D x-ray based medical imaging in a space environment Objectives: The objectives of the proposed activity are to develop, demonstrate and validate 3D

x-ray based imaging technologies enabling to work on visual tracking together with motion corrected 3D reconstruction in order to assess bone defects (fractures, bone density loss) as well as soft tissues (muscles).

Description: Preparing for human space exploration will require a very good understanding on one side of the dynamics of the space-flight related physiological deconditioning phenomena (muscle, bone, motor control, cardio-vascular) and on the other side the good assessment of the efficiency of the countermeasures developed. For doing so, accurate analytical and imaging tools will be required in space. Today, the only medical imaging instrumentation available in space is ultrasound imaging. Ultrasound-based techniques offer indeed the advantages to avoid the generation of harmful radiation, devices are rather compact. However, their utilization is very much operator-dependant, their resolution is not as good x-ray based imaging techniques. However, even if known as one of the best available imaging technique, x-ray based imaging technologies have not been used in space so far, mostly because the equipment was bulky, required power levels incompatible with what spacecraft infrastructure could provide, and was generating quite high levels of radiation. In 2008, ESA started working on X-ray acquisition for space through a pQCT system (peripheral Quantitative Computed Tomography), suitable for peripheral measurements on bone quality using microfocus tubes (more efficient). The use of such technology would greatly improve scientific outcomes in the field of life sciences experiments and health monitoring and would also be useful for clinical utilization (as necessary). This proposal aims to go beyond this state-of-the-art on two levels: Software and hardware aspects. Software aspects: Following up on the current developments (TRP activity: X-Ray Based Analytical and Imaging Devices), many software-based optimizations are needed to improve the usability of this system, including:

- Image quality: image quality with the current system is relatively low. Improved reconstruction methods shall definitely improve this weakness, yielding a potential better bone quantification (and suitability for soft-tissue imaging) leading to higher resolution and lower noise images.

- Stitching: specifically for the pQCT setup, the stitching of parts ( images) of the peripheral limb is yet limited and additional development work is needed in order to obtain proper 3D reconstructions of the structures.

- Space Usage Modelling: The space environment and the background radiation and its effect on image quality is required to improve the reconstruction of the images. Space radiation can have a great negative impact on images to be produced by the x-ray device if no countermeasure is associated to the system.

Hardware aspects: The proposed activity would consider to work an alternative system (cone-beam Computed Tomography (CT) based system), consisting of a radiation source and a flat-panel imager. The main focus lies in achieving maximal image quality through software optimization and with minimal system

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requirements and to retrieve the maximal amount of information (e.g. bone quality measures) out of the images using image-processing methodologies. This hardware investigation work will be performed through a classical set of tasks, including requirements review, safety analysis, breadboard concept, design and assembly, testing as well as proposal of a flight concept.



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Testing technologies on ISS in the short term; utilisation for life sciences scientific experiments and clinical on the medium/longer term. Possible terretrial applications and spin off for mobile systems / 2016


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Service Domain HUMAN SPACEFLIGHT Technology Domain 14 Life & Physical Sciences Ref. Number: G613-014MM Budget (k€): 400 Title: Autonomous assistance for medical operations Objectives: The objectives of the proposed activity are to develop, demonstrate and validate

supporting technologies enabling to increase crew autonomy in order to perform a set of medical operations as well as complex scientific procedures.

Description: To support scientific experiments and sometimes for clinical reasons, astronauts often have to accomplish demanding tasks like medical diagnostics and treatment for which usually experts' knowledge is needed. Typical examples are: ultrasound investigations where reliable and repeatable results are difficult to gain. The performance of additional medical acts such as emergency surgeries are also challenging since the crew medical capability will likely be limited to one crew member (emergency surgeon), who shall maintain his skills throughout the mission. For physicians on the ground, skill maintenance is guaranteed through daily practice. It is now acknowledged that assistive technologies will be required to support long duration manned missions. Augmented Reality (AR) is the overlay of computer-generated information with real environment. It is considered as a promising technology for assistance, knowledge maintenance and training. The advantage of augmented reality is that it allows to increase the quality of tasks to be performed without training the Astronauts to full medical experts, to optimise the scientific output and to react correctly in emergency cases. In addition, this technology offers new perspectives for telemedicine services and answer some yet unfulfilled user needs. A number of clinical projects could make use of technologies initially developed to support astronauts. This is the case for telemedicine projects (tele-education, tele-consultation, telemedical support) where, like in space, user communities are lacking immediate medical expertise (e.g. mobile environments [boats], oil rigs, medical deserts, in particular in geographically isolated environemnts). This technology is also complementary to some existing systems offering remote guidance capabilities and offers a real complementary to remotely controlled systems (e.g. robotized tele-echography for ultrasound examinations). One possibility of fulfilling needs using AR (and virtual reality to some extent) has been investigated in the CAMDASS TRP project. The CAMDASS (Computer Aided Medical Diagnostics And Surgery activity) was considered as a first step in the definition of generic technologies for Virtual and Augmented Reality-aided medical diagnosis and treatment. Yet, a number of possible technical improvements have been identified after the testing phase. This activity aims at correcting all major drawbacks identified so far as well as adding a number of additional functionalities not yet available. The tasks include:

- revision of requirements (some were inappropriately too high) - reduction of the system footprint, design simplification - integration of new technologies, spin-in (e.g. Kinect type) - improvement of detection, tracking performances - improvement of accuracy - investigation about integration, evaluation compatibility and performance of

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the system when used with satcom - development of a mobile guidance platform (e.g. tablet PC)

Deliverables:

A system functional model/breadboard, validated in a relevant environment and technical documentation including: state of the art (technical background, review of supported utilisation scenarios), system requirements, design concept, detailed design, test and validation plan, test report, user manual, flight concept and conclusions


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Test on ISS on the short term / Supporting medical operations in the longer term


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Service Domain HUMAN SPACEFLIGHT Technology Domain 14 Life & Physical Sciences Ref. Number: G613-015MM Budget (k€): 450 Title: Bio-chemical Analyser for Bio-Burden monitoring Objectives: The aim is to develop an easy to use hand-held device to scan hardware surfaces to

detect bio burden and contamination on spacecraft hardware surfaces using the auto-fluorescence properties of bio-burden (organic molecules and micro organisms).

Description: The previous BIOCAT activity focused on the identification of autofluorescent biomarkers or biomarkers stained with fluorophores at very low concentrations in the context of exploration missions. The main focus was the preparation of the samples to extend the detection of biomarker detection to different matrices (liquid, solid). The objective of this activity is to develop an easy-to-use handheld device, that does not necessitate any sample preparation or uses minimal sample preparation in order to scan spacecraft hardware surfaces for bioburden during the integration process. This would dramatically reduce the time of analysis of a potential contamination and provide a powerful tool to evaluate the quality of AIV compare to traditional culture based methods and perform a contamination assessment of hardware to prevent health issues on astronauts. This will allow regular, non-invasive control of the cleanliness during the storage of flight hardware before launch. The families of potential markers to be detected shall be very wide and comprise molecules (DNA, proteins, lipids) as well as entire cells (bacteria, fungi). Tasks :

- Identify the spectrum of fluorescence for each family of potential contaminants, refine the measurement requirements

- Optimization of the instrument hardware: Extension of wavelength range and resolution (i.e. increase the number of measurement channels from currently two to eight)

- Manufacturing of a fully functional prototype - Validation test campaign by comparison with culture based methods,

including the capability to discriminate between different bioburden strains (e.g. funghi bacteria strains)



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Hardware for ISS in ELIPS 4-5, further exploration missions / 2016


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Service Domain HUMAN SPACEFLIGHT Technology Domain 14 Life & Physical Sciences Ref. Number: G613-016MM Budget (k€): 500 Title: Adaptation of a furnace and x-ray diagnostic setup for metallic foams

used in a sounding rocket experiment for use on parabolic flights or inside the Large Diameter Centrifuge

Objectives: The objective of this activity is to upgrade the MASER 11 XRMON metallic foam

furnace and diagnostics set-up from the 'Advanced Metallic Foams' project for use on parabolic flights (PF) and also in the ESTEC Large Diameter Centrifuge (LDC) for µ- and hyper-gravity research.

Description: The benefits of micro- and hyper- gravity research can be seen already today in the field of new material production. Understanding gained from a sounding rocket experiment, Maser11 XRMON, was used in the ‘Advanced Metallic Foams’ project in order to establish and patent a more reliable and reproducible production route for metallic foams. The success of this gravity dependent research, employing a furnace and a diagnostic setup, may be extended by adapting the sounding rocket setup to the requirements of parabolic flights (PF) and the Large Diameter Centrifuge (LDC) at ESTEC, allowing experiments to be conducted there. The aim is to develop new approaches to the metallic foam production. In this project, the sounding rocket setup needs to be adapted to and developed further into an engineering model that fits in the LDC compartments and can be used at the same time during parabolic flights. While in the LDC, the volume and size are the main driver, the safety and human interaction aspects are the driver in the parabolic flight environment. These experiments are required by an ELIPS project on metallic and polymeric foam formation and are directly linked to the EVOLUTION project selected by the EU, aiming at improved structural elements for transportation systems.

Deliverables: Engineering Model. Fully functional breadboard consisting of oven and X-ray diagnostics with interfaces compatible with the LDC operational environment



Use of the furnace in PF and LDC in the context of the EU EVOLUTION project in the course of 2015.


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Service Domain HUMAN SPACEFLIGHT Technology Domain 14 Life & Physical Sciences Ref. Number: G613-017MM Budget (k€): 450 Title: Chemical Mapping: characterisation of the local concentration

distribution in (binary) mixtures Objectives: A compact instrument for the measurement of spatiotemporal dynamics of

concentration distributions.

Description: In reduced gravity two-phase flow experiments, an increasing demand is observed to perform studies with binary or multi-component mixtures (miscible or immiscible) beyond single-component liquids, studying the combined effect of capillarity and thermally driven surface-triggered convection. Mixtures can provide superior performance in thermal devices, transport phenomena, etc. which makes them an interesting candidate for future ground and space systems. In these studies, the measurement of the concentration distribution and its spatio-temporal variation are a natural requirement. However, the techniques used in the laboratories on ground utilise bulky equipment. The present study shall aim at elaborating on the various potential methods on characterising liquid (and optimally also gas/vapour) concentration distribution of transient phenomena. Following a trade-off analysis, where the potential inserts of Thermal Platform 1 (Fluid Science Laboratory Experiment Container) are taken as reference applications, a compact measurement device shall be designed that could be realistically accommodated in these inserts. In this study, a compact concentration distribution measurement system shall be built as a follow up to the Thermal Platform 1 inserts.



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These instruments together with modelling and design of an operational system will form the basis of updated replacements for the 'Thermal Platform 1' inserts. First results need to be available in September 2015.


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4.2.7 TD 22- Environmental Control Life Support (ECLS) and In-Situ Resource Utilisation (ISRU)

Service Domain HUMAN SPACEFLIGHT Technology Domain 22 ECLS and ISRU Ref. Number: G613-018MM Budget (k€): 650 Title: MIDASS PHASE B+ Objectives: Based on the preliminary MIDASS space concept, it is proposed to further

characterize the MIDASS development for microbial safety & life support applications.

Description: Microbial contamination is a risk concerning either crew health or hardware degradation for Human spaceflight applications. Crew and material safety require a proper control and monitoring of the microbial cleanliness level (air, surface and water) of manned spacecraft. Over the last years, developments have been made for an automated instrument for rapid microbial detection and identification (i.e. MIDASS: Microbial Detection in Air System for Space). Rapid molecular biology-based techniques prevent the bias of non-cultivable micro-organisms and allow fast time to results and quick implementation of appropriate corrective action if needed. The MiDASS space concept allows a semi-quantitative detection of specific indicators of contamination (i.e. human and environmental origin), as well as an identification of specific Human pathogens in less than 3 hours. Based on the preliminary MIDASS space concept elaborated, in combination with recommendations arising from the early assessment of the safety issues, robust technical solution will be established. Consolidated MIDASS system requirements and system design including mechanical, thermal, structure, electrical designs and safety issues will be defined. Strict mission scenario and strategies will be characterized to allow a firm System Requirement Review (SRR). Identification of the relevant ISS interface requirements with potential impact on MIDASS design will be then analysed. A consolidated design of space flight model will be validated within a flight model Preliminary Design Review (PDR). Based on these validated System Requirement and Preliminary Design reviews (SRR and PDR), a development plan for phase C/D will be proposed.



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Human exploration. A concrete target application is the Microbial Safety in space station. Target date of application 2017.


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Service Domain HUMAN SPACEFLIGHT Technology Domain 22 ECLS and ISRU Ref. Number: G613-019MM Budget (k€): 450 Title: Microbial Air Sampler System Objectives: The proposed activity will exploit the experience of TRP Air Sampling System for

Microbial Contaminants Identification activity in terms of air volume, reduced gravity constraints and detection of viable microorganisms in the air to develop an instrument for continuous sampling of air on board manned spacecraft.

Description: Microbial contamination is a risk concerning either crew health or hardware degradation for Human spaceflight applications. Crew and material safety require a proper control and monitoring of the microbial cleanliness level (Air, Surface and water) of manned spacecraft. Due to the necessary high recirculation rate of the atmosphere and the confined environment, the air was identified as the most favourable vector of microbial contamination. The aim of the proposed activity is to develop and test an air-sampler functional breadboard for microbial detection. State of art in this technological area, references of previous development will be reviewed. Based on this review, system requirement will be defined and critical functions and interfaces will be identified. A design of a breadboard aiming at testing those critical functions and interfaces will be proposed. Breadboard will be manufactured and tested. Generation of calibrated microorganism aerosols (i.e. bacteria and fungi) will be studied. Calibrated aerosols with collection/standard strains and ISS environmental strains will be used. Based on the proof of Breadboard performances, a preliminary design for space application will be proposed and reviewed during Preliminary Design Review (PDR) and safety 0/1 review. Critical issues will be identified including technical and safety challenges in order to elaborate development plan for phase C/D.



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The main target application is the Space Station microbial safety issues and the target date is 2016.


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4.3 SD4- Space Transportation

4.3.1 TD 5- Space System Control

Service Domain SPACE TRANSPORTATION Technology Domain 5 Space System Control Ref. Number: G614-002EC Budget (k€): 2000 Title: Hybrid navigation Breadboard and demonstration Objectives: The objective of this activity is to :

- develop and validate a Proto Flight Model (PFM) standard hybrid INS/GNSS equipment for launcher applications for Ultra Tight coupled Hybrid Navigation, relying on a specific GNSS receiver (e.g. AGGA4 core chip).

- support all hybrid navigation classes using GNSS & IMU data in tight configuration

- support all classes of inertial aiding of the GNSS acquisition and tracking loops (acquisition aiding, ultra tight aiding)

- demonstrate and validate in-Flight a Texus Rocket (or equivalent) - design and to validate this HiNav PFM for possible in flight demonstration

on-board another launcher, in particular for SHEFEX-3, with minor and cost-effective (modular) modifications (e.g. based on the spare equipment)

- be compatible and re-usable for possible HiNav flight equipment for Ariane 5 ME or for Vega

Description: While some off-the-shelf GNSS (GPS) receivers are compatible with the

environment of launchers, missiles and rockets, many unknowns remains for their operational use on ESA launchers:

- their performance in-flight (signal continuity, accuracy, robustness…) - their tolerance to intentional jamming/spoofing and dynamics of the launcher - the sources of perturbations in the atmosphere (<100km) and at higher

altitudes above the constellations (2000km) - the use of Galileo system

For what concerns navigation, performing an adjustment of the inertial unit errors with only the GNSS at the beginning of the flight (e.g. in visibility of Kourou) is enough to improve significantly the accuracy of the navigation on the rest of the trajectory for all the Ariane 5 and Vega known trajectories. Also different methods of hybrid navigations exist. For what concerns the launcher localisation function, the GNSS is considered for answering to safety localisation needs, as well as to provide an independent diagnostic of satellite separation. As a minimum, the activity will consist of the following phases:

- analyse applicable specific TEXUS requirements regarding AIT, operations of the experiment (power, TM/TC, etc), tailor the GNSS experiment objectives as defined in ESA document ‘Launchers GNSS demo-flight high-level requirement’, Issue 2 (26/10/2012) and derive the HiNav experiment specification.

- design and develop of navigator GNSS & processing hardware targeted to TEXUS, as well as of the inertial aiding S/W (acquisition aiding…).

- select, test and integrate an IMU within the HiNav PFM, compatible with the hybrid navigation performances requirements for TEXUS and SHEFEX-3

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- develop and validate the dedicated algorithms, from analysis of the navigation and/or safeguard requirements, in particular highly varying dynamics, demanding atmospheric and ionospheric perturbations (scintillations, tropospheric and ionospheric biases, etc).

- develop, integrate and validate of all necessary functionalities and algorithms of the software, for Galileo, GPS, Galileo-GPS hybridization (note: the algorithm and software testbed facility could be based on a DSpace real time environment, with a processor (AGGA 4) in the loop (PIL).

- integrate, test and validate HiNav PFM, as stand-alone HiNav equipment, but also within the TEXUS platform for launch.

- develop and validate the all necessary TM and Ground Support and Post-Processing, for HiNav in-flight demonstration and validation. In particular, it shall be checked that the ground support allows to reconstruct the trajectory with sufficient accuracy to meet the experiment performance validation objectives

- demonstrate and evaluate the HiNav PFM on-board TEXUS. This includes all the HiNav data capture and post-processing, the analysis and evaluation, for other flight on-board TEXUS and other launchers, at first for SHEFFEX-3 and possibly for Ariane 5ME and/or Vega.

The HiNav PFM equipment shall re-use the in-flight Hybrid Navigation experience of SHEFEX-2 and shall be developed and validated/demonstrated for Galileo and GPS and for the bi-frequency Galileo-GPS hybridization, based on the HiNAV technical specification derived in the ESA TRP activity ‘Hybrid Navigation System Architecture Consolidation’ and on the SHEFEX 2 experiment results. Supported functions towards the launchers such as TEXUS, SHEFEX-3, Ariane5ME, Verta and FLPP, may be the following:

- Safeguard (continuity) function: For the safeguard function no radiation hardening is required, because it is only used for the first 500 sec of the atmospheric phase. A MEMS class IMU is sufficient to ensure the continuity of measurements and

- High precision navigation for FLPP, as far as possible from the Texus and Sheffex-3 launches constraints. This requires an IMU only with sufficient performance, therefore not necessarily a high performances IMU. Analysis of the specification - design compatibility and of the possible necessary upgrades for high precision navigation in GTO and GEO.

Depending on the phase of the launch, the navigation performance requirements may be different. This has been identified in the previous HiNav TRP activities and will be reconsolidated at the start of this activity, in correlation with the TEXUS and SHEFEX-3 launchers requirements.

Deliverables:

System/HW/SW Specification Documents, Equipment Trade-off, Consolidation & Selection Report , Hinav Development Plan , URD & ICD, Test Plan, Detailed Design Justification, Performance Analysis Report, Hinav Test Bench & HWIL Acceptance & Test report, Proto Flight Hinav Equipment, Launcher Integration, Measurement Plan, Post Flight Analysis, Validation and Synthesis


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Future ESA Launchers (Ariane-5 ME, VEGA evolution VECEP, Ariane-6) / 2015

Applicable THAG Roadmap: AOCS Sensors and Actuators (2009)

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4.3.2 TD 14- Life & Physical Sciences

Service Domain SPACE TRANSPORTATION Technology Domain 14 Life & Physical Sciences Ref. Number: G614-003MM Budget (k€): 600 Title: Optical Tomography on bubble formation in cryogenic fuel tanks Objectives: The objective of this study is the design, development and test of a breadboard

capable to determine size, shape and speed of gas bubbles and eventually liquid droplets in cryogenic fuel tanks.

Description: Formation of bubbles in cryogenic fuel tanks is a phenomenon of high importance, in particular for restartable cryogenic upper stages. A characterisation of the bubble dynamics under microgravity is important to validate existing models, however, the appropriate diagnostics to enable such an in situ interrogation is not available at the moment. A previous study on optical tomography as a high resolution diagnostics for crystal growth experiments (TRP activity Fluid Science Stimulation Technology) has shown that a resolution of several micron can be achieved on reference targets and an extrapolation to the observation of the dynamic behaviour of objects in liquids is possible. A previously flown sounding rocket experiment (FLPP Experiment 48) dedicated to assess the bubble behaviour in a liquid oxygen tank was only equipped with a rather basic diagnostic providing basic illumination with one view port. For image reconstruction, a lot of work has been done recently to enhance and optimise algebraic reconstruction techniques and genetic algorithms. In a further step it shall be shown that the design implementation in a cryogenic environment shall enable the interrogation of relevant effects in a realistic environment, paving the way to an implementation in a sounding rocket experiment. The main tasks of the proposed activity are:

- Review of current state of the art of optical tomography and image reconstruction algorithms, requirements definition and trade off

- Preliminary design of measurement set up, taking into account the interface requirements of a sounding rocket module and the cryogenic fuel environment (TEXUS...)

- Design and manufacturing of diagnostic set up: test with reference target/objects)

- Test of set up in a chamber mock up with model fluid under 1g, test of model set up with cryogenic liquid (LOx).

- Flight test under parabolic flight conditions - DDVP for flight experiment



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Sounding rocket flight to support modelling efforts for boiling/sloshing phenomena for Cryogenic Upper Stage Technologies (CUST) activities / 2016

Applicable THAG Roadmap: Chemical Propulsion - Upper Stage Propulsion (2003)

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4.3.3 TD 18 - Aerothermodynamics

Service Domain SPACE TRANSPORTATION Technology Domain 18 Aerothermodynamics Ref. Number: G614-004MP Budget (k€): 500 Title: Experimental characterisation of transient flow phenomena in

cryogenic Fluids Objectives: The objectives of the present activity is to improve the understanding of flow

phenomena occurring during transients, start-ups and shut-downs in propulsion systems with cryogenic fluids.

Descriptin: The study focuses in particular on multiple re-ignition of upper-stages. This entails waterhammer effects or pre-combustion phenomena where propellants undergo drastic changes due to sudden exposure to near-vacuum conditions. To allow proper modelling, detailed experiments need to be created for typical multi-phase, multi-component flow. The present activity is an integral part of a global strategy towards the acquisition of experimental data in order to understand the physics of cryogenic flows and by this means to provide with tools for the design of propulsion components like valves, tanks and propulsion feed lines, among others. Indeed, first experimental investigation for cryogenic flows through injectors have been carried out in the TRP study Multi-Physics Aspects in Propulsion Systems. Experimental characterisation of valves in multi-physics environment are being studied in the GSTP activity Multi-Physics Valve Models. A feasibility experimental study on propellant feed lines exposed to strong pressure gradients in millisecond time is being done in the TRP activity Waterhammer Test in Cryogenic Fluids. Finally, experimental test data for cryogenic flows with strong heat exchange is planned in the GSTP activity Experimental Investigation of Two-Phase Flow. The results of all these activities allow to constitute an experimental database for cryogenic propellant, a key element towards the validation of design tools for propulsion components. The following tasks are foreseen:

- evaluation of the liquid front behaviour during waterhammer prior, during and after impact for different operational conditions;

- evaluation of the (flashing) evaporation front during priming/start-up; - evaluation of atomization processes in flashing conditions at different

conditions; - evaluation of vaporization rates in flashing conditions at different conditions; - extension of correlations for flash atomization; - extension/validation of correlations for flash vaporization.



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Cryogenic chemical propulsion systems

Applicable THAG Roadmap: Aerothermodynamic Tools (2012)

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Service Domain SPACE TRANSPORTATION Technology Domain 18 Aerothermodynamics Ref. Number: G614-005MP Budget (k€): 500 Title: Liquid film cooling in MMH-NTO rocket engines Objectives: The present activity aims at improving the understanding and modelling of liquid

films in MMH-NTO engines.

Description: Monomethylhydrazine (MMH) as fuel and Nitrogen Tetroxide (NTO) as oxidizer is a commonly used rocket propellant combination. Large and mid-size engines such as the Ariane 5G upper stage engine Aestus are re-generatively cooled via cooling channels using the MMH fuel. For smaller engines, this gets more and more difficult, because the available coolant per wall surface area decreases with the engine dimension. Therefore, liquid film cooling of the combustion chamber is usually applied for smaller MMH-NTO rocket engines. Whenever this cooling technique is applied in a rocket engine, it is important to have adequate prediction tools. For liquid film cooling, the main prediction focus is on the liquid film length and the wall heat transfer downstream of the dry-out point. The proper prediction of the heat transfer between hot gases and film is a prerequisite for a good film modelling and often, especially in the case of MMH-NTO chemistry, is very difficult due to the slow and complex combustion process with various chemical species involved. An additional challenge for the modelling of liquid MMH-films is the fact that the evaporated MMH decomposes in a strongly exothermic manner, releasing a far higher decomposition energy than its evaporation consumes. It is proposed to address the following aspects:

- Establish an inert liquid film test case (no chemical reactions) from literature, and or new experiments

- Improve the MMH-NTO combustion modelling based on existing experimental MMH-NTO data

- Elaborating 1D two-phase film-modelling incl. mass and heat transfer e.g. vaporization, condensation; based upon existing model and/or ESA tools such as EcosimPro/ESPSS

- Couple the film models in 2D/3DCFD codes for rocket combustion chambers with validation on available data and possibly extension towards real operational conditions (i.e. combustion)

- Consider 3D effects on film evolution - Attempt to perform resolved CFD simulations of a film, possibly with original

fluids




Mid-size to small rocket engines like Aestus; in the future also Berta / 2016


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4.3.4 TD 19- Propulsion

Service Domain SPACE TRANSPORTATION Technology Domain 19 Propulsion

Ref. Number: G614-006MP Budget (k€):

2000

Title: 10 kW Hall Effect Thruster Objectives: The aim is to advance the qualification of a high specific impulse 10 kW Hall Effect

System. The system performance shall be commensurate with the next generation of high total impulse space missions. The work outcome shall be the performance demonstration of an engineering model thruster and flow control system.

Description: To save propellant mass, maximise payload and mission capabilities, future high total impulse missions will require propulsion systems capable of operating at higher specific impulse (SI) and capable of greater total impulse (Ns) which means higher thrust than those currently being developed and qualified (5 kW). A 10 kW Hall Effect Thruster will be capable to fulfill the requirements of these missions. The principles of operating existing technologies at higher specific impulse and thrust levels have been demonstrated to a limited extent and the constraints imposed by existing technology are generally appreciated. This activity will therefore build on the extensive heritage gained through existing EP programmes with the objective of designing, building and testing a thruster to meet the high specific impulse and total impulse demands whilst overcoming the limitations imposed by current technology. It is essential that this activity be considered in the framework of a complete system that comprises appropriate power supplies and flow control systems. The programme will consist of the following key activities and phases: Phase 1

- Identification of mission requirements and selection of a baseline mission - System level trade-off, technology selection and system architecture definition - Unit specification

Phase 2 - Design and manufacture breadboard thruster (including flow control) and test - Design and manufacture of an engineering model (EM) thruster (including

flow control system) - Performance testing of EM thruster (including the flow control system) for a

time adequate to allow detailed performance characterisation and life time prediction

- Endurance test

Deliverables: Report with mission requirements definition; system level trade-offs, technology selection and system architecture; design report; manufacturing report and endurance test report


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Electric Propulsion advanced upper stages and exploration missions / 2017

Applicable THAG Roadmap: Electric Propulsion Technologies (2009)

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4.4 SD6- Navigation


Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-001ET Budget (k€): 1800 Title: Low complexity GNSS Sensor Station beam forming-based tracking

receiver Objectives: The objectives of this activity are:

- to investigate a potential Ground Station equipment (antenna and receiver) design profiting from beam-forming techniques, offering superior interference and strong-multipath rejection capability, compared to that achieved by current equipment. The aim is to minimize equipment complexity and technological risk, and ensure practical equipment deployment

- to develop a Ground Station HW/SW prototype, fully representative from the functional and performance perspective of an operational equipment, and to validate it under real GNSS signals

Description: RF interference and multipath are relevant error sources affecting the performance

of the GNSS Ground Station equipment in charge of providing ranging observables to the satellite orbit and clock determination algorithms at the Galileo Control Centre. Even though the navigation signal is ‘spread-spectrum’, it is visibly vulnerable to interference, due to its very low power at reception. Excessive interference may provoke loss of lock and false lock in the equipment. Multipath may provoke ranging errors visibly correlated over time, of difficult mitigation at signal processing level or/and at output-observables processing level. The impact of both interference and multipath could be diminished by incorporating beam-forming techniques to the Ground Station equipment (comprising antenna and receiver). Beam-forming techniques could enable efficient spatial + time filtering of RF interference and strong multipath. The activity high level tasks are as follows:

- Consolidate the equipment specification; namely functional, performance and external interfaces requirements

- Define the equipment physical architecture: main physical blocks, related internal interfaces, core hardware blocks transfer function(s) and core processing

- Define the equipment physical detailed design; namely hardware elementary blocks, elementary processing modules, detailed internal & external interfaces

- Develop and verify the equipment - Consolidate the validation scenarios definition - Analyse the equipment performance (code-phase and carrier-phase tracking

errors, probability of loss of lock, probability of false lock, etc), in the above validation scenarios; they shall include at least the operation with real GNSS signals (Galileo & GPS) under nominal RF-environment conditions and extreme RF-environment conditions (in terms interference or/and multipath)


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Galileo Ground Sensor Station (and EGNOS RIMS) / 2016


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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-002ET Budget (k€): 1500 Title: Advanced GNSS signal implementation platform Objectives: The aim of this activity is to define, design, implement, verify and validate a

flexible/re-configurable receiver platform with the twofold objective to test performance of 1) advanced GNSS signal formats/techniques (both at modulation and message level) and of 2) advanced tracking techniques able to flexibly adapt to the corresponding advanced signal formats/techniques.

Description: The GNSS community is investigating new techniques and several formats/techniques (at modulation and message levels) to enhance future GNSS signal in space capabilities. For instance, the TRP activity "ADVISE" and similar studies in the GNSS community have investigated new message/advanced coding/ interleaving techniques (like LDPC, TURBO, Super Orthogonal Turbo codes, etc) as well as new modulation schemes, spread spectrum techniques and mapping (like Continuous phase modulations, Multicarrier signals, Continuous Shift Keying (CSK), etc). They have also started to exploit link layer techniques and data message content structure for improvements of Time To First Fix (TTFF) and robustness of data reception. The claimed performance advantages shall be first studied and traded-off with respect to the enhanced complexity of the system by means of a flexible breadboard capable of implementing :

- advanced GNSS signal formats/techniques (modulation and message) - advanced tracking techniques able to flexibly adapt to the corresponding

advanced signal techniques. The main focus is on the receiver side, in particular on the definition and implementation of mechanisms to flexibly adapt to and track the transmitted advanced signals with the least (eventually non-existent) prior knowledge on the actual transmitted signal, although generation of modernized signals might need to be simulated to support validation and performance assessment. The identification, definition and implementation of advanced techniques (both at signal definition and receiver side level), as well as definition and implementation of concepts allowing required flexibility and upgrade-ability shall be carried out within the activity, together with a final detailed performance assessment of exemplary formats/techniques. The final hardware shall cover:

- Message/Advanced coding/Interleaving and decoding and deinterleaving - Link layer techniques and new data message content structure for

improvements of TTFF and robustness of data reception. - New Modulation schemes, Spread-Spectrum techniques and mapping and

associated receiver techniques - Multicarrier signals and associated receiver techniques.

Seen the many available configuration options and possible parameterizations of the techniques, the breadboard shall allow a flexible reconfiguration of the receiver techniques to cover all the selected SiS formats. The activity shall define and implement mechanisms to flexibly adapt to and track the transmitted advanced signals with the least (eventually inexistent) a-priori knowledge on the actual

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transmitted signal. The validation of the platform shall be carried out at least with standard GNSS signal format/techniques and exemplary advanced techniques/formats related to system implementation cases. Finally, validation results shall be used for detailed performance assessment of the standard and exemplary techniques.

Deliverables: Prototype, associated design report, validation report and test report


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EGNOS/GALILEO evolutions, Galileo GSS and EGNOS RIMS 2016


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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-003ET Budget (k€): 1000 Title: Digital Beam-forming Based Advanced Navigation Receivers Objectives: The goal is to design and manufacture a miniaturised antenna array and a GNSS

receiver that are form-factor compatible with existing FRPA antennas, but that can be used to provide GNSS interference protection and enhanced signal to noise ratio to mobile users.

Description: Many aircraft installed or automotive GNSS receivers use FRPAs (Fixed Reception Pattern Antennas) instead of CRPAs (Controlled Reception Pattern Antennas), due to the size and weight of the CRPA antenna arrays. In a mobile environment, enhanced digital beam-steering algorithms at receiver level are needed to compensate satellite motion and vehicle motion. A step further on the degree of miniaturisation can make such technology also suitable for mobile handheld devices that use chip antennas and single-die assisted GNSS receivers. The project will, first, study the state-of-the-art technologies for tightly packed antenna arrays, where the antenna elements are placed in close proximity (less than half wavelength). The problem of the mutual coupling will be faced in order to minimise the performance degradation in terms of input impedance mismatch, side lobe level, scan blindness, pattern degradation, and radiation efficiency. State-of-the-art digital null and beam-forming signal processing algorithms will also be studied for interference and multipath mitigation at receiver level. The main drivers for optimization will be based on the adaptive steering capability of following the mobile user position and asset changes, the gain in terms of signal to noise ratio, the rejection of interference and the attenuation of reflected signal echoes. The receiver platform will be able to receive signals from multiple constellations (at least GPS and Galileo) and to provide autonomous calibration for different frequencies/signals. The design of the receiver will be able also to accept external inputs for the vehicle pitch, roll and heading. This can be used to provide real-time correction of the digital beam direction while the vehicle is in motion. The form factor and the achievable performance will be designed for single frequency (L1) and double frequency (L1/L5) multi-constellations. In the frame of the activity, the following will be developed:

- a single frequency miniaturised antenna array for mass-market receivers - a dual frequency packed antenna array for automotive and aeronautical users - a receiver platform able to interface with both antennas and with a flexible

architecture able to cope with various null/beam forming algorithms. The antenna and receiver will be verified with proper models representative of the user environments (in terms of interference and multipath) and with on-field test campaign. The on-field testing activity will cover different environmental scenarios, ranging from open-sky to urban canyons conditions.

Deliverables: Antenna and Receiver prototypes, associated design report, validation and test reports


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Future EGNOS and Galileo (Galileo Early Services) / by 2016


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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-004ET Budget (k€): 1200 Title: Advanced hybrid navigation user platform Objectives: The main objectives of the activity is to develop a complete receiver platform for

hybrid positioning and the development of fusion algorithms for PVT computation.

Description: Current positioning technologies are not able to ensure service coverage in different and heterogeneous environment while offering positioning accuracy. The integration of different position technologies appears to be absolutely pivotal to the future location devices. This activity will include the development of an integrated platform, able to produce and process observables from:

- GNSS constellation signals with algorithms representative of mass-market receivers (assisted GNSS, open loop tracking, batch processing, snapshot positioning, power saving algorithms and ephemeris extension)

- Terrestrial positioning signals (WiFi, 3G/4G positioning) - Signals of opportunity processing - MEMS(Micro Electro Mechanical Systems)

The multi-constellation GNSS receiver embedded in this platform will be considered as a sensor within others and overlaying fusion algorithms will be implemented in order to optimise the hybrid position estimate. The platform will embed chip scale sensors to improve performance and keep the form factor suitable for targeted applications. To allow man-portable dead-reckoning devices with improved precision, with and without GNSS, the following sensors will be included:

- chip scale antenna: the antenna and all the RF-FE components are in a low cost single chip package

- chip scale atomic clock: short-term stability and aging characteristic of atomic clocks, but with over two orders of magnitude decrease in size and power consumption. They can improve notably the receiver performance in case of high sensitivity tracking algorithms and integration with inertial sensors.

- chip scale inertial measurement unit and micro-electro-mechanical systems The platform will be at the same time flexible and reconfigurable to allow the experimentation of the various techniques. The integrated platform will be used to assess the performance of the different positioning signals in realistic propagation channels with representative models and on-field testing activities. A complete comparison between performance results of the single positioning techniques and the hybrid one will be presented for the different scenarios and applications. The way of carrying out sensible field trials will be investigated at the start of the activity in terms of user scenarios, channel characteristics and sensors capabilities. A minimum set of experiments to run in the field will be defined to gather meaningful results to assess performance of various hybrid positioning techniques.

Deliverables: Complete breadboard of the receiver platform for hybrid positioning, associated design documentation, validation and test reports


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Navigation receivers, Future EGNOS and Galileo (Galileo Early Services) / by 2016


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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-005ET Budget (k€): 800 Title: Advanced receiver architecture platform Objectives: The objective of the activity is to develop and assess performance of an advanced

GNSS receiver architecture platform with new and state of the art receiver architectures and signal processing algorithms to support user applications in realistic scenarios (e.g. vehicular land, pedestrian).

Description: This activity shall cover the development of an integrated receiving platform with the implementation of the following algorithms:

- Interference Detection/Mitigation/Awareness based on the outcomes of on-going TRP activities (e.g. Interference Mitigation Based On Novel Signal Processing Cancellation and RF Front-end'),

- Multipath suppression/Mitigation based on the outcomes of on-going TRP activities, i.e. ARTEMISA and ROCAT

- NLOS (Non-Line of Sight) tracking detection/mitigation: conditions based on shadowing and LOS blockage effects that can lead to complete loss of tracking or to tracking of echoed signals shall be detected (based on TRP 'Signal Processing Techniques for the Integrity of Land Users')

- Adaptive tracking techniques: linear adaptive filters techniques (based on on-going TRP 'Adaptive Tracking Techniques for Navigation Signals')

- High sensitivity techniques for increasing availability of measurements in non-nominal tracking conditions: such as vector tracking loops and batch processing with external aiding (sensors).

The platform shall embed state-of-the-art chip technologies, being at the same time flexible and reconfigurable to allow experimentation of the various techniques. The receiver platform performance shall be verified in realistic propagation channels with representative models and on-field testing activities. The in-laboratory testing activity shall foresee proper hardware simulators to simulate the scenarios conditions and to reproduce the multipath and interferences models. The on-field testing activities shall thoroughly verify the single algorithm performance in different real environments, representative of the degraded transmission channels.

Deliverables: Receiver Breadboard, design, validation and test reports


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Navigation receivers, Future Galileo and EGNOS (Galileo Early Services) / by 2016


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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-006ET Budget (k€): 1500 Title: Advanced GNSS Reference Station DSP technology platform Objectives: Development of a GNSS multi-frequency/multi-constellation receiving platform for

GNSS reference stations. In particular, the main objectives of the activity are: - The design of an optimised and robust receiver architecture for multiple

GNSS constellations and frequencies - To implement advanced and configurable receiver Digital Signal Processing

(DSP) algorithms, able to cope with severe environmental conditions of multipath, scintillation and intentional/unintentional interference

- A thorough verification of the receiver performance in realistic propagation channels with representative models and on-field testing activities.

Description: A critical element in the design of advanced GNSS receivers for future reference

stations is the increased complexity of the receiving channels, required to acquire, to track and to demodulate navigation messages from an increased number of satellites and constellations, with different frequencies and modulations. At the same time, a reliable and robust tracking is required for continuity and integrity purposes, already at very low elevation angles, where the propagation channel could degrade the receiver performance. An improvement in such performance positively impacts the sizing of the reference stations network and the overall system performance (e.g. number of RIMS stations in the EGNOS data collection segment). This need requires advanced DSP algorithms. In particular, the tracking algorithms currently adopted in reference stations receivers are strongly limited under the main threats identified at Ground Stations, such as ionosphere scintillation, multipath, intentional and unintentional interference. The activity shall focus on:

- The design optimization of the receiver base-band part with - an increased number of channels sufficient to cope with a multi-

frequency and multi-constellation scenario - an increased number of correlators per channel to cope with multi-

correlator techniques, e.g. for multipath mitigation, interference detection, false locks and Evil Wave Form detection

- a configurable channel able to track different signal modulation - additional observables able to characterise and increase the awareness of

the environmental threats - Implementation of multipath suppression/mitigation techniques at signal

processing level - Implementation at signal processing level of interference detection/mitigation

techniques - Robust carrier (phase and/or frequency) and code tracking under strong

scintillation environments - Intentional interference detection algorithms

The activity shall develop a real-time prototype of the ground station receiver. The receiver prototype performance shall be verified with on-field testing activities and simulated propagation channels, based on realistic and representative models. The in-laboratory testing shall foresee proper hardware simulators to reproduce the multipath, scintillation and interferences models (based on synthetic time series and RF playback of grabbed real data). The on-field testing activities shall verify the

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single algorithm performance in different real environments, representative of the degraded transmission channels (multipath, scintillation, and interference).

Deliverables: Receiver Prototype


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Evolution of EGNOS and Galileo Reference Ground Stations (EGNOS V3 Phases C/D, future Galileo) / by 2016


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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-007ET Budget (k€): 1000 Title: A 300W L band flexible power SSPA demonstrator using GaN

technology Objectives: The aim is to develop of a very compact SSPA (engineering model) with 6 dB

flexibility in power using European GaN technology for navigational payloads. This SSPA will also require the development of high power space qualified RF GaN modules. The proposed SSPA will deliver powers up to 300W while achieving 60% reduction in mass and 70% reduction in size compared to a Linearized Traveling Wave Tube Amplifier (LTWTA) with equivalent or higher efficiency.

Description: Recent advances in GaN technology, materials for device packaging and SSPA housing enable flexible power GaN SSPAs (with vertical or horizontal architectures) to be a viable alternative to TWTAs in navigation payloads where powers up to 300 W are required in L bands. Navigation applications, where the mass and footprint are limited, can benefit from these flexible power GaN SSPAs. The development of an engineering model of a 300 W flexible power SSPA using GaN technology is proposed. In this SSPA, RF device/modules will use advanced packaging material. The SSPA housing will also be fabricated with high thermal conductivity materials. The SSPA shall employ a very compact architecture with following targets: power > 300W, overall SSPA efficiency equal to L band TWTA, 70% reduction in footprint and 60% reduction in mass relative to LTWTA. For multicarrier and modulated signals, efficiency comparable or greater than LTWTA at the same linearity level shall be demonstrated. The lower cost of GaN SSPAs, as compared to LTWTA shall be demonstrated. The performance figures mentioned above include the Electrical Power Conditioner (EPC) and associated passive and active components. The first phase of the activity shall include:

- Survey of Flexible Power SSPAs, selection of most efficient circuit architecture suitable for space borne applications.

- Preliminary design of a Flexible Power SSPA - Wafer run, modelling and characterisation of dies, fabrication of packaged

devices/modules, characterisation and modelling of the packaged devices - Design, development and testing of the SSPA final stage and driver stage.

The second phase of the activity shall include: - LCAMP design for linearising the flexible SSPA, LCAMP fabrication/testing - EPC design, EPC fabrication and testing for 300W SSPA - Final assembly and functional testing of the SSPA (with EPC and lineariser) - If required, a complete second iteration including a wafer run - Mechanical, thermal, radiation , multipactor testing of complete SSPA



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Navigation Satellite Systems / 2016

Applicable THAG Roadmap: Critical RF Payload Technologies (2004)

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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems

Ref. Number: G616-008ET Budget (k€):

1000

Title: Compact ultra-high stability atomic clock for Space applications Objectives: The objective of this activity is the design, manufacture and test of a compact time

reference with stability of few parts in 10^15 over one day, and to demonstrate such performance over extended period duration (up to 20 days).

Description: Today, the GNSS clock error requirements are comfortably met with the current on-board atomic clock technologies (PHM and RAFS) whose parameters are refreshed every 100min to 1 day. In the future, it is expected that similar (or improved) error requirements will be required, combined with increased autonomy (up to 20 days). While some techniques are being investigated to address these challenges (e.g. inter-satellite links, clock ensemble..), it is expected that new clock technology with improved stability and compact design can be equally beneficial. It is further expected that clocks with such performance will also significantly improve deep-space navigation through one-way ranging. In the last years, several atomic clock studies have demonstrated that it is possible to achieve improved frequency stability performances within a potentially much more compact design. Identified clock technologies are based on the interrogation of either trapped ions or atoms in the microwave domain. Improved stability is obtained thanks to either increased Q-factor (trapped ions) or augmented signal-to-noise ratio (atoms). All those studies have demonstrated the potential to reach a frequency stability of few parts in 10^15 over one day, with mass-power budget that is comparable (or even reduced) as compared with existing technologies. The proposed activity will be dedicated to the design, manufacture and test of a compact atomic clock to address the future needs of on-board GNSS and deep-space navigation. A full prototype shall be manufactured and tested. Recommendations and plans for further development shall be proposed.

Deliverables: Technical Notes (i.e. Design Description and Justification, MAIT plan and report, Test and Characterization plan and report, Development Plan), Prototype


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On-board GNSS and deep-space navigation / 2018

Applicable THAG Roadmap: Frequency & Time Generation - Space (2005)

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Service Domain NAVIGATION Technology Domain 6 RF Payload and Systems Ref. Number: G616-009ET Budget (k€): 450 Title: Payload simulation tool for complex GNSS RF front-end architectures Objectives: The objective is to develop a detailed simulation tool for complex navigation RF

payload front-ends within a system simulator. This tool will allow to simulate different navigation RF payload front-end architectures and will assess the impact of payload constitutive elements impairments (e.g. linear and non-linear distortions) onto the transmitted navigation signal and on the end-to-end system performances. The tool aims to support the following system/payload engineering activities:

- Design and analysis of future navigation RF payload front-ends - Definition of the most optimized payload architecture for a given Navigation

space segment scenario - System to Payload Requirements flow-down - Prediction of payload performance and refinement of payload design for

performance optimization (including refinement of subsystems specifications) - Detailed and quantitative payload performance requirements definition based

on far-field performance assessment when loading the payload with realistic signal conditions

Description: The tool will be of fundamental importance for the definition of future generations

of navigation payloads to be developed in the 2020s. The replacement of the Navigation satellites gives the opportunity to address emerging challenges (such as flexibility at antenna, signal and RF power levels) as well as to optimize its exploitation with the definition of new services. New technologies have the possibility to be embarked and even new and advanced payload architectures can be defined. The tool shall be based on industry standard simulation platforms (e.g. Matlab/Simulink, ADS, GRASP) and shall allow the interfacing with standard industry RF measurement instruments. In order to accelerate the simulation time, parallel programming shall also be considered. The tool shall be implemented in a modular manner to allow easy set-up of different P/L architectures that it may be needed to investigate for future Navigation space segment scenarios. Payload constitutive elements shall be implemented as building blocks and their combination shall allow to develop and simulate different P/L architectures, e.g. including distributed amplification (Beam Forming Networks, Flexible tubes etc) and different antennas options (single feed per beam, array fed reflector, etc.) The payload constitutive elements shall be simulated at functional and distortion level with the possibility to up-load measurement characteristics. The simulator shall be able to reproduce and analyse the most important navigation signal quality degradation sources appearing in the transmission chain and assess their impact on the End-to-End performances. The simulator will provide flexibility in the operating frequency (e.g. L and C band) and in signal waveforms (simulating all the available and planned GNSS signals) and will permit step-by-step and in-total impact analysis of at least the following impairments:

- phase noise introduced by satellite/receiver clock oscillators - group delay variation over satellite and receiver antenna field of view - linear distortions coming from on-board signal/frequency generators, up-

converter and output multiplexer as well as linear distortions coming from earth-terminal front-end filter and down-converter

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- Drift in amplitude and phase responses owing to temperature variations - Unintentional and intentional RF interference, Multipath and propagation

impairments - Non-linear distortion introduced on the overall Tx and Rx chain, paying

particular attention to the on-board HPA and D/A-A/D converters. Deliverables: Software


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Navigation / 2016


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4.4.2 TD 7- Electromagnetic Technologies and Techniques

Service Domain NAVIGATION Technology Domain 7 Electromagnetic Technologies and Techniques Ref. Number: G616-010EE Budget (k€): 500 Title: Fixed and mobile calibration and evaluation of multipath and

atmospheric GNSS error sources Objectives: Design and development of a multi-instrument facility to evaluate and calibrate

error sources in fixed and mobile environments including: Multipath (bias - slowly varying - and random components), Ionospheric delay and instrumental inter-frequency biases (for all frequencies), Tropospheric delay, Ionospheric scintillation and Noise and interference. This facility will serve for User Performance evaluation, Error characterization and Site Survey and Sensor Station Characterisation.

Description: Current technologies are not able to estimate accurately the error sources from fixed and particularly mobile receivers, for example, for multipath, the high-frequency components can be estimated together (in addition) to noise and interference, but the slowly varying components are more difficult to separate, for ionosphere, ionospheric delay calibration relying on dual-frequency techniques which require a very good estimation / calibration of inter-frequency bias from the receiver which is difficult to obtain and often masking other errors. The efficient use of radiometers or meteorological stations is also required for tropospheric calibration. In addition, the effects of the antenna as installed in a given platform is of critical importance for this evaluation, and the consideration of beam-forming techniques (and its effects on error source evaluation) is instrumental for the majority of activities in system, signal and receiver development as demonstrated in many project and R&D activities in the past. The study shall consider the implementation of differential (time and space) carrier-phase techniques for accurate positioning in mobile users and integration of carrier-phase techniques with inertial sensors for separating environmental effects from other error sources. Other sensors like laser ranging may be also considered. RAIM techniques shall be addressed for identification of erroneous measurements. The activity shall also consider the exploitation of record and replay techniques addressing the errors introduced by such system and the effects of antenna (in order to extrapolate to other antennas). Concepts like OTA measurements shall be also investigated. In terms of measurements, joint multi-antenna measurements using hemispherical, multipath rejecting and possibly beamforming antennas shall be considered. The main deliverable shall be a prototype facility for error sources measurements for integration of fixed or mobile vehicle. Tasks:

- Identification of instrument requirements, architectures and processing algorithms

- Critical evaluation of architectural concepts - Development and procurement of hardware and algorithms - Integration and testing - Qualification, experiment campaign and delivery


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Future EGNOS and Galileo / 2016


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4.5 SD8- Space Situational Awareness

4.5.1 TD 4- Spacecraft Environment & Effects

Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-002EE Budget (k€): 400 Title: H-alpha Solar Telescope Network prototype for Applications Objectives: Establish a ground-based federated, networked capability in Europe for monitoring

of the Sun at H-alpha wavelength dedicated to operational space weather use. Analyse European capabilities, upgrading existing facilities and infrastructure. Integrate into a network proving a unified access system.

Description: Ground based observation of the Sun at the H-alpha line have long been made for scientific purposes. It can provide valuable data supporting Space Situational Awareness if provided as part of a service. While not providing the ideal access to UV and X-ray wavelengths available from space platforms, the relative ease and low-cost of ground based measurements make them very useful contributors to monitoring solar activity through regular, high cadence full disk observations. They allow complementary monitoring of flare and CME onsets and provide good indicators of flare location on the solar disk. Eruptive signatures known as Moreton Waves, indicative of CME (Coronal Mass Ejection) onset, are also seen in these observations. Ground based telescopes can also observe solar magnetic fields. Such observations are emerging as important means of identifying precursors for prediction of flares and CMEs. European institutes operate H-alpha telescopes, but mainly for research purposes. Furthermore, the infrastructure has not been developed to produce data in a guaranteed, continuous monitoring capacity. This activity will analyse existing facilities in terms of existing hardware, software, data availability and telescope seeing conditions. Prototyping of the network will include operation of selected and adapted telescopes and real-time dissemination of the data to a hub for processing into prototype service products for SSA. Automated data processing will be implemented, allowing automated identification of known activity signatures including (but not limited to) flare onset, filament eruption, Moreton wave onset. Linking with non-European resources will be investigated as a means to provide 24-hour coverage of solar activity. Requirements and implementation planning for a dedicated European H-alpha Service Telescope will be established in order to address fully European SSA requirements. This will include preliminary designs for any new instrument or infrastructure technologies required.



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SSA Space Weather ground system; Needed in 2016 to be taken up in next phase of SSA


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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-003EE Budget (k€): 1000 Title: Heliospheric modelling techniques Objectives: The aim is to develop of a physics-based models for operational prediction of the

propagation of CMEs and solar energetic particles to the Earth.

Description: The background solar wind and solar eruptions, such as coronal mass ejections (CMEs), propagating into interplanetary space are the fundamental drivers for space weather phenomena. Induced currents due to variations in the Earth's magnetic field can impact ground systems. Heated plasma can result in the charging of spacecraft and dangerous discharge events, and variations in the electron density in the ionosphere can impact GNSS such as Galileo. In most cases, CMEs take a number of days to arrive but in some instances the CME shock arrival is within 15 hours of the event on the Sun. In addition, Solar Energetic Particles accelerated by CME-driven shocks result in single event effects which can interfere with spacecraft (and aircraft) instrumentation or in some cases permanently compromise their operation. These enhancements can occur over timescales as short as 10-15 minutes. Many physics-based models have been developed for simulating parts of the Sun-to-Earth space weather system, consisting of plasma, fields and energetic charged particles. Depending on the problem, these use a variety of modelling techniques (magnetohydrodynamics, particle-in-cell, etc.). The ESA SEPEM project and the FP7 SEPServer and SWIFF projects have worked to unify and connect these models. An example is models for particle radiation propagation through the heliosphere where interplanetary shocks driven by the CME accelerate particles to high energies. What is lacking in Europe is a "single model" (or unified system) which accounts for all significant phenomena, that can be run in near-real-time and therefore provide warning to end users. This activity will include the development and enhancement of existing physics-based models of Coronal Mass Ejection (CME) onset, structure, propagation and evolution. These will be integrated with shock-particle propagation models for Solar Energetic Particle Events (SEPs). Outputs will include CME arrival times, the density of plasma and the magnetic field strength and direction and predictions of event-time profiles for SEPs at both Earth and non-Earth locations. The modelling environments and methods will be harmonised and validated. Development and deployment will be within a distributed environment.



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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-004EE Budget (k€): 1000 Title: Airborne radiation detector Objectives: The aim is to design and prototype a radiation detector capable of quantifying

radiation doses and energy spectra of the radiation species contributing to human health hazards and effects in electronics. The detector will measure doses and fluxes of neutrons and high energy charged particles resulting from cosmic ray and solar energetic particle interactions in the atmosphere and aircraft material. Ease of integration, standardization and complete calibration will be ensured.

Description: Radiation hazards to crew and advanced electronic systems on aircraft are recognized as space weather hazards in SSA. Conformance to exposure limits is currently verified by application of computational methods. This activity will develop a prototype detector using the most appropriate detection technologies for neutron and charged particle detection, dose measurement, and energy spectra determination. These will be used in monitoring the radiation exposure of crew and electronic systems, validating the analytical methods, and investigating in more detail the hazards during solar particle events and at quiet times due to cosmic rays modulated by the geomagnetic field and atmosphere. Several detector systems have been developed and flown in Europe, and reviewed under the EU EURADOS project. However, they employed a range of detection methods that are difficult to reconcile. This activity with emphasize standardization and sound characterization, calibration and simulation work. Miniaturization techniques will be employed to construct an instrument that is easy to integrate and operate, and in accordance with EURADOS recommendations.



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Space Weather, radiation hazards / 2016


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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-005EE Budget (k€): 500 Title: Wide-field space-based auroral camera prototype Objectives: Design and prototype a camera for embarkation as hosted payload on a polar

orbiter for imaging the aurora at various wavelengths providing performance required for space weather applications within SSA. Accommodation within limited mass and power budgets of hyperspectral capabilities will be investigated.

Description: Remote sensing of the auroral emissions from space is a valuable data source to complement ground based radars, magnetometers and imagers. The data can be coupled with models of ionospheric phenomena to produce information on currents and densities in the auroral regions for use in applications sectors such as power lines, prospecting, navigation and RF communications. Scientific instruments can be large and their resolution exceeds what is required for user-oriented space weather services. This activity will design and prototype a small auroral camera (mass target <3kg, volume < 3 dm3 ) with appropriate field of view, resolution and timing. A wide angle requirement is necessary to capture as much as possible of the auroral oval. The instrument should be deployable on a small satellite or as a secondary payload on a larger platform. Accommodation constraints (interfaces, data rate, power, mass pointing requirements, etc.) will be analysed. Phase C/D planning will also be made.



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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-006EE Budget (k€): 400 Title: Impact effects tools Objectives: The effects a Near-Earth Object (NEO) would have on assets and population when

impacting our planet depends on its size, composition, the impact trajectory and velocity and the impact location. When a potential impact risk from a NEO has been identified, it is important to know if the object could cause damage on the ground and the extend of such damage. Engineering-type tools are needed to analyse the complete process from atmospheric interaction, break-up and energy release in the atmosphere, assessment on which size objects can reach the ground and impact effects on ground. A number of - mainly scientific- related models and tools are available. A review of the existing relevant knowledge and tools was performed during the SSA preparatory phase (ESA contract SSA SN-VII) and a roadmap for the development of missing tools was established. In addition to state of the art scientific tools an operational tool for a quick assessment of impact effects and potential damage is required. This tool shall be able to provide easy to understand but reliable results within minutes.

Description: An operational tool for the quick assessment of effects resulting from impacting asteroids shall be developed. It could be based on a large number of reference cases which are stored in a database. A higher level tool with a user friendly interface could interpolate the stored results for the specified input parameters. This activity will consist of 3 main tasks:

- Develop capabilities which are missing in the existing tools as recommended by the roadmap. Examples are: Electromagnetic pulse effects, acoustic effects, realistic object break-up modelling and the treatment of smaller objects.

- Produce the database of reference cases covering the full range of realistic impact parameters.

- Develop the operational tool for a quick impact risk assessment including the user interface



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SSA-NEO precursor services / 2015


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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-007EE Budget (k€): 650 Title: Development of a compact Remote Interface Unit: Phase A/B/C/D Objectives: Proto-flight model development of a low-mass compact interfacing unit for

provision of power at several voltages to multiple Space Weather/Space Environment instruments and combining of data streams from instruments for provision to the spacecraft bus via a single adaptable interface. Optional on-board data compression and processing to make best use of available data bandwidth.

Description: Space Situational Awareness (SSA) programme studies have identified possible flight opportunities for space weather/environment instruments. Due to the on-going reduction in volume, mass and power consumption of these instruments in many cases, it is possible and desirable to embark multiple instruments in a single payload. The value of in-situ measurements such as those of the geomagnetic field and plasma and radiation environments are greatly enhanced if taken simultaneously at the same point in space. The designers and operators of spacecraft for hosted payloads have a preference for single packages with the benefit of simplified power and electronic interfaces. In addition, depending on the region of space the spacecraft is in along its orbit the required time resolution of different data varies. For example, at some regions of space, the plasma environment is less variable than at others allowing for reduced time resolution. This data bandwidth could be used to downlink stored data or for another instrument. This activity shall develop a Remote Interfacing Unit (RIU) which shall provide power supplies at various voltages required by space weather/environment instruments limiting the mass required for individual instrument voltage transformers. The RIU shall receive data streams from instruments through various protocols (RS422, SpaceWire, MIL-STD-1553 and CAN Bus) and provide data though a single data interface adaptable to hosting spacecraft requirements. The RIU will include (optionally) on-board processing capabilities to reduce the data bandwidth required and therefore increasing the volume of useable, processed data to be downlinked. As a further option the system will include an interface to a dedicated transmitter allowing for independent downlink of data to a SSA or other ground station. The mass, volume and power requirement of such an RIU will depend strongly on the number of instruments to be supported, the ratio of the power conversion needed and the amount of onboard processing capability required. The baseline RIU, to support 4/5 instruments and convert power from a 28 V supply, shall have a mass of no more than 2 kg and a volume envelope of 200 x 20m x 200 mm. The power required by the instrument shall be less than 5 W. Variants of this RIU with a mass of up to 5 kg and 10 W shall also be designed. A proto-flight RIU model shall be built to conform to the requirements of an identified flight opportunity to test a selection of space weather/environment instruments presently under development. This proto-flight model shall undergo standard space environment tests and end-to-end qualification tests with the instruments identified as part of the payload.



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Space Weather, Q3 2015


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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-008EE Budget (k€): 500 Title: Combined Radiation Monitor Data Analysis System (CORMODAS) Objectives: Develop a coherent near-real time radiation environment data resource through

development of a system for importing, cross-validating, fusing and analysing data from a range of European radiation monitors and instruments (e.g. SREMs, EPT, MFS, EMU, HMRM, NGRM, ICARE).

Description: There are a number of different European radiation monitor instruments already flying, or about to fly, each with their own dedicated data (pre-)processing chains and systems. These include the SREM instrument on Proba-1, Integral, and Rosetta; EPT and SATRAM on Proba-V; MFS on AlphaSat and others. These systems are thus far largely disparate, requiring the user to separately access them, while differing data formats are also used that make inter-comparison and data fusion difficult. This activity will utilise those various networked data sources by combining them to a single, near-real time product. Existing capabilities, such as the ODI interface and SEISOP system, shall be used to the extent possible. Task description:

- Analysis of the existing data formats, processing chains and data validation for the various European radiation monitors and collection of user requirements

- Definition and design of a coherent system for merging of the various data sources into a near-real time product providing energetic electron and proton fluxes and spectra in the different orbital environments

- Development of the system and software - Validation of the system and the data products - Maintenance and updates

The end customers will be Space Weather application developers and users, spacecraft radiation effects engineers, mission designers, various instrument PIs, as well as spacecraft operators.


Current TRL: Prototype Target TRL: Software Release

Duration (months)

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Space Weather / 2016

Applicable THAG Roadmap: Radiation Environments & Monitoring, Effects Tools & Testing (2009)

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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-009EE Budget (k€): 700 Title: Prototype Compact Wide Angle Coronagraph Objectives: Design, develop and test a prototype of a small space-based coronagraph consisting

of a white-light telescope and solar occulter providing performance required for space weather applications within SSA.

Description: In a coronagraph, a small disk in the field of view of a telescope is used to obscure the bright Sun, allowing its outer "atmosphere" - the Corona - to be seen, as during an eclipse. From space, coronal plasma emissions are very clear out to several solar radii (Rs) from the Sun's surface because of the lack of atmospheric scattering. Large-scale eruptions of plasma from energetic events on the Sun are easily monitored and measured. The coronagraphs on SOHO and STEREO have become vital elements for space weather forecasting. However, scientific instruments like those are large and their resolution exceeds what is required for user-oriented space weather services. Similarly, the proposed Proba-3 polarizing spectroscopic coronagraph, for high-resolution images of the inner corona down to 0.02 Rs from the limb, is a radically different instrument from that required for SSA, with an emphasis on diffraction and straylight effects removal. This activity will design a coronagraph with appropriate field of view, resolution and timing as defined in space weather system studies (1 Mpixel images, FOV to 20 Rs and image cadence 5 minutes). Strong emphasis will be placed on limiting the mass and volume compared to the existing generation of scientific instruments. A wide angle requirement is necessary to enable estimation of plasma cloud extent and velocity. Pre-development, prototyping and testing of key technologies and elements, including optics and electronics will be undertaken to validate the design and reduce development risk. Stray-light rejection will be optimized so that Earth-directed halo CMEs can be detected on a routine basis. The instrument will be deployable on a dedicated small satellite or as a secondary payload on a larger platform. Accommodation constraints (interfaces, data rate, power, mass, thermal, stability pointing requirements, etc.) will be analysed. Phase C/D planning and costing will also be performed.




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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-010EE Budget (k€): 600 Title: Fireball Monitor for SSA

Objectives: Design and develop an optical monitor and related image processing software to detect, measure and record fireballs from large meteoroids/small Near-Earth Objects when entering the Earth atmosphere. The monitor shall aim to observe Earth from a high space altitude (e.g. GEO).

Description: The Earth is constantly bombarded by objects in all size ranges coming from space. The smaller the objects, the more frequent they are. Ground-based video camera systems typically record several to several tens of meteors per hour. These events are generated by particles in the size range from micrometres to centimetres. Objects in the size range of tens to hundreds of metres are called asteroids and are typically observed far away from the Earth using telescopes equipped with CCD cameras. Objects in the intermediate size range (several decimetres to several tens of meters in size) cause so-called fireballs in the atmosphere. They are too rare to have produced statistically significant observations to date and the precise number flux of particles in this size range is not known very well. On the other hand, they can produce damage on the Earth, like e.g. the impact of the Carancas meteoroid on 15 Sep 2007, an object of about 1 m diameter which produced a 13 m diameter crater very close to a small town in Peru (Borovicka, J., Spurny, P. (2008), The Carancas meteorite impact: Encounter with a monolithic meteoroid, Astronomy and Astrophysics, Vol. 485, Issue 2, 2008). A better knowledge of the expected impact flux is important to assess the impact risk on the Earth. This study will contribute to solving this issue. To get a statistically significant number of observations of fireballs, the detection area has to be as large as possible. One solution is to put a camera into geostationary orbit and monitor the visible atmosphere of the Earth for fireball events. An optical/IR monitor will be designed and developed to detect fireballs from small (about 1 m or larger) near-Earth objects when they collide with Earth. The monitor will be optimised for operation from a location in GEO. It will be able to monitor one complete hemisphere and to determine size and trajectory of the impactors. Starting point of the design will be two completed studies for the development of a wide-angle visible light camera for faint meteors. The optics will be optimised for a field of view covering the complete Earth from GEO (about 18 degrees full angle). The best wavelength for the detection of fireballs (infrared or visible) shall be determined. An important aspect is the on-board data processing and storage which has to cope with a large amount of data and with false events (e.g. city lights, lightning flashes). The study shall include the design and development of the fireball camera and corresponding on-board software. The experience gained from previous studies (e.g. the TRP Smart Panoramic Optical Sensor Head activity) should be used as a starting point.



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Derive population models for large meteoroids and small Near Earth Asteroids. SSA NEO segment / 2016


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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-011EE Budget (k€): 2,000 Title: Phase C/D of 3D Energetic Electron Spectrometer Objectives: The aim of this activity to produce a full-working proto-flight model of the 3D

Energetic Electron Spectrometer.

Description: The 3DEES activity has is creating a 3-d electron sensor is a modular structure consisting of up to 9 sensor modules which each measure fluxes in two orthogonal direction. The full system is capable of measuring electrons responsible for radiation and deep-dielectric charging effects in high spectral and angular resolution, This is needed for characterising electron-dominated regions, as are found in GEO and Galileo orbits, for example. A by-product of the chosen design is that ion measurements are separately obtained from the same instrument. This high resolution sensor is intended to provide an in-orbit reference against which other simpler radiation sensors can be calibrated. The energy range in 0.1 to 8MeV in 16 energy bins and angular resolution in 15 degrees.

Deliverables: Proto-flight model, fully characterised





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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 4 Spacecraft Environment & Effects Ref. Number: G618-012EE Budget (k€): 600 Title: Solar X-Ray Monitor Proto-Flight Model and Low-Resolution Imager

Design for SSA Objectives: Develop a proto-flight model sun-integrating monitor of solar X-rays, with low

mass and data rate, and spectral resolution sufficient for operational use in space weather monitoring and forecasting. Additionally, design of instrument evolution into a low resolution imager to determine the location of activity on the solar disk.

Description: X-ray emission plays an important role in distinguishing the activity on the surface of the Sun and as a result there is a long history of X-ray imagers and radiometers. X-ray imagers include the SXT instrument on-board Yohkoh and the SXI imager on recent GOES satellites. As an alternative to imagers, whole-disk monitors provide a simpler means of capturing the onset and evolution of energetic events on the Sun, and so providing alerts. Monitors (or radiometers) include those on RHESSI and the XRS instrument on all of the GOES satellites. X-ray flares are often a precursor to CMEs and associated interplanetary shocks which can cause high energy particle radiation and disturbances in the near-Earth magnetic and electric fields. In addition, flares directly disturb the ionosphere, which is further disturbed by magnetospheric storms. X-ray emissions in the 0.1-0.8 nm range are used to classify solar flares based on their peak flux as either A, B, C, M or X class flares with X being the largest (or extreme) flares. This activity will execute pre-development of the CXSMO (compact X-ray solar monitor for operations) instrument with a baseline spectrum of 0.05-0.8 nm over multiple (at least 2) channels. Space-based detection of X-rays is a crucial aspect of the SSA Space Weather segment. This instrument will be geared towards monitoring and forecasting of space weather phenomena that could be accommodated easily on various s/c. For space weather operational purposes, near real-time warnings are required and therefore the instrument shall include on-board event detection software. The baseline flare detection requirement is that of GOES, i.e. 7 arc-min for M1, 0.7 arc-min for X1 and 0.07 arc-min for X10 class flares. The monitor should also be capable of detecting B1 class flares. For space weather purposes, measurements with a cadence of 1 minute and timeliness of delivery of 5 minutes are sufficient. This shall allow the instrument to be small (~0.01 m3) and lightweight (<500g), with low power consumption (<2W). A minimum 10 years lifespan will require testing of the component degradation. Later development of the radiometer to include optics to determine the flare location and likely geo-effectiveness should be enabled by inclusion of compatible detector technology such as quadrant photodiodes. This requires the some method of autonomous accurate sun centring to be included in the on-board software in combination with a less stringent instrument pointing requirement. The preliminary design for an extension of the solar X-ray monitor to include a low-resolution imager will be performed. It shall be demonstrated that this is compatible with the proto-flight model design.



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4.5.2 TD 9- Mission Operations and Ground Data Systems

Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 9 Mission Operations and Ground Data Systems

Ref. Number: G618-013GD Budget (k€): 300 Title: General-purpose computing on graphics processing units (GPGPU)for

SSA Ground Data Systems Objectives: Application of general-purpose parallel processor to SSA's intensive computation

activities in order to achieve high performance, scalability, reduced costs, reduced space and reduced power consumption.

Description: Graphics Processing Units (GPUs) are high-performance many-core processors capable of very high computation and data throughput. Once specially designed for computer graphics and difficult to program, today's GPUs are general-purpose parallel processors. The emergence of new programming tools and relatively low-cost hardware is aiding in these efforts, and is introducing many-core computing to a broader range of developments. Application porting to GPUs often achieves speedups of orders of magnitude versus optimized CPU implementations. Given the raw power provided by 100s of cores, various data parallel applications could now take advantage of this massively parallel hardware. Problems in domains like Weather forecast, computational finance, Life-Sciences, are being moved from super computers and computing grids to GPGPU based solutions. Even with the evolution of multi-core CPUs such problems could not be addressed in real-time or practical durations. Due to the inherent data parallel nature of domains below, they fit very well to the GPU architecture, thus resulting into performance gains. Many key ESA domains of activity provide an opportunity for the application of this technology. Virtually any parallel code that uses floating-point arithmetic can benefit from savings in time, improvements in accuracy, savings on cost, space and power. In general experience gained with this technology can be applied to any Ground Data System characterised by this parallel processing (example: calculation of engineering data based on raw data ...). In the SSA programme, all three segments can benefit from GPGPU deployment, namely:

- NEO Detection - Conjunction Prediction Analysis - Re-entry Prediction - Fragmentation Analysis - Catalogue Correlation and Orbit Determination - Space Weather nowcasting/forecasting - Space Weather simulations

While GPGPU utilisation could be considered as a generic research activity, its applicability to a given field is dependent on the type of the problem being tackled. Experienced gained as part of an ESAC traineeship assessment activity* demonstrated that GPU parallelisation pays off when:

- All threads in a warp (a set of identical operations) execute the same instruction at the same time.

- Simple algorithm follows a branchless, floating point computational schema. - The dataset used in the computation is small compared to the processing needs

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Therefore, it is not possible to define a generic problem where GPUs will bring benefits without narrowing down the scope of the problem. In the case of NEO, the utilisation of GPUs provides an excellent computational framework for the detection of objects. More specifically this problem could benefit from the deployment of GPUs to stack images in 360 different directions with hundreds of different angular velocities to increase the SNR of moving objects hiding in the data. Additionally, the particular cases of ESA's SSA/SST Conjunction Prediction Service (CPS) and Re-entry Prediction Services, there is a requirement for the repetitive application of the same processing algorithm against a data set of man-made space objects. As previously described, the nature of these problems represent a perfect fit for GPU constraints. GPUs with its hundreds of cores can be considered to provide off-the-shelf custom hardware for this specific problem. Based on acquired knowledge on GPGPU and SSA algorithms, this proposal focuses on SSA problem areas preliminary considered to be compatible with the aforementioned GPGPU characteristics. Tasks to be performed:

- Use Cases identification: this task shall determine those algorithms currently used in SSA that show the highest potential for GPGPU optimisation.

- Architecture Blueprint: this task shall evaluate available architectures for GPGPU Computing in order to determine the optimal solution for the identified Use Cases

- Analysis: this task shall perform a profiling of the current solutions in order to determine bottlenecks and areas to be migrated to the GPGPU

- Design and Implementation: this task shall carry out the implementation of software prototypes

- Validation: this task shall evaluate performance and accuracy of the GPGPU-enabled solution in order to determine the improvements achieved by the deployment of the technology.

- Final Report: this task shall aim at delivering the final report recording the experience gathered during the execution of the project (solution, PROS and CONS, lessons learnt, conclusions and recommendations for future work)

- *The Process of Parallelizing the Conjunction Prediction Algorithm of ESA's SSA Conjunction Prediction Service using GPGPU - M. Fehr, V. Navarro, L. Martin, and E. Fletcher



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To cope with the increased amount of data generated by extended networks of sensors and data generation capabilities. To enable live/near-live detection and orbit determination of objects in the areas NEO and SST. To enable faster simulation lifecycles and improved accuracy when executing SSA simulations. Early 2015. In order to feed the findings into SSA’s operational solution.


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4.5.3 TD 11- Space Debris

Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 11 Space Debris Ref. Number: G618-014GR Budget (k€): 250 Title: Development of semi-analytical methods for orbital lifetime estimation

and re-entry propagation Objectives: This activity aims to analyse the available semi-analytical propagation methods and

to develop a method that fulfils the requirements of the SST re-entry service.

Description: The process of computing the orbital lifetime of all the objects contained in the SST catalogue is a computationally expensive and time-consuming process that requires the adequate techniques to efficiently obtain suitably precise results. The precision in the computation of the orbital lifetime for objects in different orbital regimes is not the same. Objects in higher orbital regions (e.g. geostationary orbit) would require of a very rough estimation, while objects in lower altitudes require of a very good accuracy. For this reason, different types of propagators may be considered in the process of computing such orbital lifetime, ranging from analytical models to numerical ones, passing by semi-analytical models. In long-term propagations it is very important to include the effects that perturb and degrade the orbit. Numerical methods are usually chosen above analytical methods because they are able to introduce all these terms in the propagation. However these propagators stumble on several difficulties. The second difficulty lies in propagating the state vector of an object for long durations of time (anywhere between weeks and years). With a numerical propagator, each time step shall introduce a very small error that is integrated with the next integration step, and therefore the error grows with the propagated time creating a divergence in the state vector w.r.t the actual physical propagation. Furthermore, the precision required in the computation of the orbital lifetime for objects in different orbital regimes is not the same. A rougher estimation of the orbital lifetime would suffice for objects in higher orbital regions (e.g. Medium Earth Orbit), while objects in lower altitudes require an accurate lifetime prediction due to the high decay-rate. For this reason, different types of propagators should be used in the process of computing such orbital lifetime, ranging from analytical models to numerical ones, passing by semi-analytical models.. The second difficulty lies in the time it takes to propagate the state vector of an object, particularly if there are many disturbing terms in the equation (e.g. high-fidelity gravitational model, solar pressure, atmospheric model, 3rd body perturbations, luni-solar effect, Earth tides, etc.). The time of propagation increases beyond acceptable bounds, particularly when a full database of objects must be propagated within a constrained period of time. Semi-analytical methods have the advantages of both the numerical and the analytical world. They have the potential to be almost as fast as an analytical propagator, but with the possibility to add more disturbance terms in the equations. However, there is still a potential for improvement in the performance of both the execution time as the accuracy achieved.

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The tasks for this activity are as follows: - Task 1: The Contractor shall perform a research to list and assess the

analytical, semi-analytical and numerical propagators that are used for orbit propagation. The following propagators shall be taken into account at the least: Brouwer-Lyddane, Cowell, DSST, HANDE, SALT, USM, SGP, SGP4, SGP8, PPT and the Russian A, AP and NA theories. The research shall address the complexity, the accuracy performance, the execution performance and the potential for hybridisation with other techniques to improve the algorithms in these criteria. The Contractor shall also review the SSA-SST segment requirements and derive a requirements list for the propagator development.

- Task 2: The Contractor shall develop a semi-analytical propagator making use of the results of Task 1.

- Task 3: The propagator shall be validated. A series of benchmark cases shall de designed in collaboration with ESA to test the performance of the new orbit propagator in the scope of SSA-SST against the SSA-SST requirements.

- Task 4: The implementation of the algorithms in the SSA-SST segment shall be done.

- Task 5: The activity shall provide recommendations and a roadmap for the further development of the algorithms for future activities.

Deliverables: Algorithms, Technical Documentation


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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 11 Space Debris Ref. Number: G618-015GR Budget (k€): 300 Title: Development of an efficient method for mean elements computation

from precise orbital data and its associated analytic propagation method

Objectives: This activity aims to develop a theory for efficient orbit propagation that allows to

compute the orbital data of catalogued objects; fulfilling a set of accuracy and time propagation requirements of the overall SST system. A trade-off shall be performed in order to determine the most suitable combination of such requirements.

Description: Today, the number of man-made space objects for which orbital information is provided as part of the publicly available catalogues is greater than 16000. All the scenarios provided by the internationally available evolutionary models of the space debris population represent a growing tendency. The Space Situation Awareness SST segment of the is expected to manage huge amounts of data as part of the man-made space objects catalogue. In order to be able to perform analysis of the population of objects and predict future positions of such objects, it is required to define and develop a compact representation of the orbital data as well as a fast propagation method for such orbital data. Several methods exist for the computation of the mean elements calculated from the orbital data measurements using propagators. The determination of a set of constants of motion for an orbital man-made space object theory is a commonly encountered problem in SST. The mathematical theories of satellite motion are generally given as functions of mean orbital elements rather than osculating elements. In practice, it is the set of initial conditions of position and velocity components at a given epoch time that is readily available, such as those arising from nominal conditions for an orbit insertion or as the output of a stepwise numerical integration techniques for trajectory prediction. Such initial conditions are readily converted, by means of the Keplerian two-body transformations, into osculating orbital elements, but the problem of producing mean elements for use as constants of motion in an analytic development remains in most of the times unsolved. Method previously proposed for the determination of mean orbital elements using spheroidal theory of manmade objects motion directly from either initial conditions or Keplerian osculating elements is shown to be feasible. The methods, originally intended for use with multi-revolution satellite orbits, are actually an iterative procedure involving a first-order Taylor's series expansion of position and velocity components at epoch time. The determination of mean orbital elements by this iterative method is shown to be a valid alternative to methods involving quartic polynomials that arise in the inversion of the integrals of motion and that are solved by successive approximations. Numerical results have demonstrated that convergence of the iterative fitting to initial conditions is rapid and exact for a small number of objects. The spheroidal theory provides an algorithm for the calculation of an accurate reference orbit for any satellite that moves in the gravitational field of an axially symmetric oblate planet. The spheroidal theory is applicable to all bounded orbits of arbitrary inclination and eccentricity. Other studies have developed methods for the utilization of differential coefficients to fit orbital parameters to assumed initial position and velocity vectors that represent trajectories.

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The activity shall be composed of the following tasks: - Investigate and analyse the current state of the art and trade-off and compare

existing orbital propagator methods. This task should also look for alternatives that have not proposed earlier. The constraints to be taken in this work is the huge amount of catalogued data and the ned to propagate of all them at once.

- Using the investigation carried out in T1, develop a new theory for efficient orbit

propagation to make sure that all objects in the catalogue have been propagated quickly at once at with the accuracy required.

- Code the new theory into a software toolbox that can be modular, portable,

extensive, and scalable. - Integrate the toolbox into the SSA SST centre software and make it work

together with the other SST software elements



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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 12 Ground Station System & Networking Ref. Number: G618-016GS Budget (k€): 1000 Title: L-Band SSPA for phased array radar transmitter and dual polarization

receiver Objectives: To develop efficient transmitters to be used in a ground based surveillance radar

consisting of several thousands of elements. Moreover the activity aims at supporting SSA final radar design activities by demonstrating the required technologies for dual-pol multi-beam digital receivers.

Description: The SSA final radar will require very powerful transmitters (order of Megawatts). Each 1% increase on the efficiency mean tenths of kilowatts saved (and operational costs reduced). In parallel, the dissipation is lower and the cost of the cooling systems drops dramatically. Presently there are state of the art topologies for SSPA that allow much better efficiencies (on the power stage) than the typical 40% of the SSPAs presently used in the ground stations (Class A or AB). Novel designs like Class D, E and F show theoretical efficiencies up to 80% and articles show implementations that claim 60-70% efficiency. Unfortunately this is still at academic level. Besides, many parameters of interest for our application are not of interest for other applications and there is no information available (phase stability, phase linearity, etc.). The testing of the prototype shall include the effects of a ground station environment and long duration test in order to assess the reliability and stability of the power stages designed and manufactured. Also, the number of SSPA modules in the transmitter will be in the order of thousands. The physical constraints of a phased array antenna (spacing between radiating elements is fixed to 0.7*wavelength) generates demanding performances to the mechanical and thermal design (electrical design is already covered by another TRP development). Additionally a smart design looking on cost saving during the manufacturing phase will save large amounts of money due to the high number of units to be manufactured. The study shall perform the analysis of the physical constraints and complete the mechanical and thermal design of the module to fulfil the requirements especially on what relates to mechanical and thermal requirements. A prototype shall be built. A first batch of 5 to 10 pre series units will be manufactured after prototype acceptance to analyse the production process yield and allow the integration in the Radar prototype and in- field performance testing. A final SSA radar will be based on dual-polarization receivers and multiple beams observations for both close-monostatic and bistatic configurations. The unknown backscattering behaviour of space debris and the depolarization effects of the ionosphere pose the requirement for dual polarization receivers. This implies the development of compact RX antenna elements capable of receiving the two components, which has not been addressed so far. The optimization of the resulting RX antenna in terms of antenna pattern due to mutual coupling effects and return loss is not trivial. The requirement on multiple beams (eg clusters) comes from the requirement on scanning rate of the area of interest. In general, upgrading SSA demonstrated technologies to the final radar architecture implies the evolution of the available Digital Receiver into a multiple-beam dual-pol Receiver with

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enhanced data communication capabilities. The Digital Receiver is in charge of A/D conversion, Digital Down Conversion, and (Adaptive) Digital Beamforming. The current SSA implementation offers the possibility of handling 9 beams for single polarization. It is based on daisy-chain sub-units connected in hierarchical 2-level network. It is fully scalable, but the available components (ADC, FPGA I/O) might represent bottlenecks in terms of maximum data rate and unit costs. Handling tens or hundreds of beams with full signal bandwidth might lead to requirements that cannot be met by available off the shelf technologies. This needs to be further investigated in order to (i) reduce the risk in final radar procurement, (ii) ensure non-dependence from non-EU or military technologies, and (iii) avoid dramatic cost increase of the single receiver. The proposed activity aims at designing, procuring and developing dual pol multi-beam Digital Receiver boards for testing the entire set of RX functionalities in the final radar configuration.



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Space Surveillance and Tracking, Q4 2015


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Service Domain SPACE SITUATIONAL AWARENESS Technology Domain 12 Ground Station System & Networking Ref. Number: G618-017GS Budget (k€): 1500 Title: Breadboarding of an intelligent telescope CMOS APS Objectives: The objective is to support the ground-based optical observations needed for SSA's

NEO and SST segments with special focus on fast-moving but faint objects. Description: Ground-based optical observations of space objects in the SST and NEO segment

are limited by three main issues: (1) the relative angular velocity of the object with respect to sensor and/or the star background, (2) the signal-to-noise ratio, in particular of faint objects, and (3) the need to precisely register the astrometric position and photometric information associated with the related epochs. Typically, ground-based astronomical observations have more relaxed requirements in these three areas than set by SSA. In order to exploit the full potential offered by APS (CMOS) detectors for SST and NEO observation tasks, this activity shall validate the approach addressed in a completed pre-cursor TRP study by implementing the on-chip logic / processing identified therein. The latter has quantified clear benefits in improved observations strategies both on-ground and in space (incl. shutter-free camera operation with precise epoch registration, possibilities for streak detection and qualification of streak direction, and related image segmentation). Based on the results, dedicated on-chip intelligence is required and shall be developed, the validated on-chip logic shall be implemented into a breadboard and first steps towards a full-scale APS detector shall be identified. The detector development shall finally lead to the operational device for the optical ground station network. The study shall, based on a the results of a previous TRP study on optical observation strategies, and meeting the SSA system requirements and the needs of space debris observations:

- breadboard a demonstrator (of limited dimensions) with the corresponding on-chip functionality (potentially exploring different versions) and the required electro-optical performance

- validate the several different on-chip processing techniques and optimized observing strategies by observing campaigns at exiting suitable observatory (e.g. ESA OGS at Teide)

- identify the development needs and formulation of the steps leading to a full-scale operational SST and NEO detector. Retro-fitting of one of the SSA telescopes shall be considered.



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Ground-based optical sensors for the NEO and SST segments of the SSA program. Need date should be consistent with the foreseen development of the corresponding telescopes: 2017


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4.6 SD9 Robotic Exploration

4.6.1 TD 4 Spacecraft Environment and Effects

Service Domain ROBOTIC EXPLORATION Technology Domain 4 Spacecraft Environment and Effects Ref. Number: G619-003EE Budget (k€): 300 Title: Maintenance of the European Mars Climate Database Objectives: To maintain and keep up-to-date Martian climate existing models which have been

developed under a TRP activity. Description:

Comprehensive models of the Martian atmospheric environment have been developed and used to develop a generic data base of atmospheric data, used in EDL (Entry, Descent and Landing). This database is supplemented with additional models at progressively smaller scales to cover all aspects of mission design, including near ground environment (z<20 m). The boundary conditions for these models need to be continually upgraded as data from current Mars missions become available. Therefore, the aim of this activity is to improve the European Mars Climate Database using the latest data available. New data is also used for upgrade and validation of physical parameterizations used in these models. It is anticipated that some of the effort will be devoted to the improved modelling of dust lifting and transport mechanisms, hence giving access to realistic dust spatial variability.

Deliverables:

Upgraded Martian general circulation model and documentation. Upgraded Martian mesoscale/microscale model and documentation. New version of Mars Climate Database (refined dust scenarios) and validation documentation. Technical notes on scenario studies.


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All Mars missions / 2017


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4.6.2 TD 5 Space System Control

Service Domain ROBOTIC EXPLORATION Technology Domain 5 Space System Control Ref. Number: G619-004EC Budget (k€): 700 Title: Further development of Sensor Data Fusion for Hazard Avoidance Objectives: The goal of this activity is to further develop the fusion of sensor data for hazard

avoidance and piloting initiated under two parallel TRP activities. The activity brings the sensor data fusion techniques for hazard avoidance and piloting from a TRL 3 to TRL 5 through the implementation of the algorithms on a dedicated processor, along with an associated relative navigation scheme; the algorithm will then be test on a real-time PIL, which will include high-fidelity models of passive and active sensors.

Description: Future solar system landing missions will be targeting region of high scientific interest but with significant risk (e.g. craters, boulders, shadowed areas, slopes.) The availability of both cameras and active optical sensors (scanning Lidars, flash Lidar/3-D cameras) with their different characteristics in term of measurement type, rate and field-of-view led to the investigation of hazard detection algorithms that would fuse the data from these two sensor types (and additionally from inertial and altimetric sensors when available) to provide accurate hazard maps to the flight control software. Several sets of sensors pairs, fusion algorithm (fusing sensor data at low- or high level) and scenarios (Mars and asteroid) are being defined, implemented, simulated on SIL platform and benchmarked within the frame of the TRP activity run by two parallel teams. The logical next step is to further test the winning combination(s) performance in a PIL simulation test-bed with a dedicated processor for the HDA and relative navigation software. The main tasks of this follow-up activity shall be :

- to review the results of the two previous activities, including their conclusion on the relevance of the HDA algorithm to relative navigation and to select for both Mars and asteroid missions at most 2 sets of sensors/algorithms (specifically, the reliability of the method(s) in estimating local slope values and identifying dangerous areas with steep slopes shall be the primary selection criterion.)

- to assess whether it is required, for performance reasons, to implement the HDA and/or relative terrain navigation algorithm(s) on a dedicated processor, and in that case, to implement HDA and relative navigation algorithm on the dedicated processor (e.g. FPGA, DSP, LEON-FT);

- making use of ESTEC laboratory dSpace-based test bench, to integrate this processor into a PIL simulation, where the flight control software will be implemented on a LEON2 processor, and high-fidelity models of both optical sensors shall be used. In order to run real-time simulation, it might be necessary to restrict the tests to open-loop simulations only in order to feed high-realism virtual images to the sensor model;

- based on the simulation results, to assess the sensor/algorithm simulations in term of accuracy of hazard detection, accuracy of relative navigation and overall CPU performance.

Deliverables: - Sensor data fusion algorithms and associated real-time software - Sensor data fusion processor - Technical documents, including test documentation

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Mars/asteroid landing missions / 2017


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4.6.3 TD 13 - Automation, Telepresence & Robotics Service Domain ROBOTIC EXPLORATION Technology Domain 13 Automation, Telepresence & Robotics Ref. Number: G619-005MM Budget (k€): 2,000 Title: Planetary Explorer LOcalisation-navigation Ready for USe (PELORUS) Objectives: This activity shall achieve Technology Readiness Level (TRL) 5 for the hardware

logic cores of computer vision algorithms (for use by Martian rovers in visual navigation and localisation) that have been developed in the previous SPARTAN/SEXTANT and COMPASS activities.

Description: The "SPAring Robotics Technologies for Autonomous Navigation (SPARTAN)" activity has implemented in logic cores a series of computer vision algorithms necessary to implement navigation systems for planetary probes. Starting from their mainly sequential description, the algorithms have been turned into vectorial and highly-pipelined cores so that they can work in the latest FPGA devices. The "Spartan EXTension Activity - Not Tendered (SEXTANT), has been extending the number of algorithms used (to allow robustness) and also it has been implementing a landmark-based global localisation scheme. The activity "Code Optimisation and Modification for Partitioning of Algorithms developed in SPARTAN/SEXTANT (COMPASS)", will partition the cores and port it from the present single-FPGA implementation into networks of smaller FPGA devices thus allowing the possibility of using European- sourced FPGAs. At the end of the three activities, the logic cores will be mature for a transition into a hardware/software architecture representative of a real space mission. The PELORUS activity will develop a hardware implementation of the cores based on the new high-density all-European FPGA (planned to be available at the end of 2014). Programme of work:

1. Definition of requirements 2. Co-design of the hardware and software 3. Manufacturing Coding and Assembly of the co-design 4. Testing in relevant environment 5. Closure of activity

Deliverables:

1. Normal project documentation 2. Logic cores and supporting software 3. Hardware implementation 4. Test environment


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MSR / 2017


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4.6.4 TD 15 - Mechanisms & Tribology

Service Domain ROBOTIC EXPLORATION Technology Domain 15 Mechanisms & Tribology Ref. Number: G619-006FP Budget (k€): 200 Title: Shape Memory Alloy actuators for MSR biocontainer sealing -

feasibility demonstration Objectives: Demonstrate the feasibility of using shape memory alloys (SMA) as an actuator to

close/seal the MSR (Mars Sample Return) biocontainer structure as an alternative to current state-of-the-art sealing technologies.

Description:

The following tasks will be done in the frame of this activity: Analysis of required performance of SMA candidates with respect to function

as a mechanism for seal closure of a BioContainment for MSR mission: - Required force to lock the seal - Reliability of function - Tolerance against environment and qualification limit - Temperature, pressure, EMC, radiation - Launch environment - DHMR compatibility

Literature survey of candidate SMAs and application examples. Definition of the test set up

- How to proof function - Develop analytical procedure to proof tightness - Pressure test vs. material research (analyse slice by e.g. SEM, x ray

tomography etc.) Design of the test set-up

- Design of SMA clamp - Analyse resource requirements power, weight etc. - Design of seal structure to be clamped (diameter32 cm) - Design of seals

Deliverables: Documentation and breadboard


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Mars Sample Return / 2019


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4.6.5 TD 18 - Aerothermodynamics

Service Domain ROBOTIC EXPLORATION Technology Domain 18 Aerothermodynamics Ref. Number: G619-007MP Budget (k€): 500 Title: Supersonic parachute test on a MAXUS flight Objectives: The objective of this activity is to demonstrate the capability to test new supersonic

parachute designs in representative conditions for space missions and reduce the reliance on existing non-European parachute systems by using European sounding rockets.

Description: As already proved feasible by the flight of the Sounding Hypersonic Atmospheric Re-entering Kapsule (SHARK) on the MAXUS-8 sounding rocket, the present activity shall make use of the spare payload volume, otherwise used for ballast, to perform a low cost flight test of a supersonic parachute on the MAXUS mission in 2015. Also, an initial internal feasibility study showed that there is possible to test a suitable sized parachute (1m diameter) in the available mass and volume constraints given by MAXUS, therefore there is a very good opportunity to develop state-of-the-art technologies for testing supersonic parachutes in Europe. The proposed activity includes:

- the detailed design of the capsule, parachute and deployment system including instrumentation and avionics

- the procurement (COTS)/development/manufacture of all items above - installation the payload on MAXUS - (launch) - post flight analysis

The following minimum instrumentation is foreseen to obtain flight data for design:

- Timer to measure events from MAXUS separation (initiation) to touchdown

- Video of the deployment and steady state descent, - Accelerations and Angular rates of the capsule, - Axial force during deployment, and - Pressure sensor(s)

Further, since the capsule will be analysed by CFD to assess the wake, heating and the stability for the reference mission, there is also an opportunity to test future mission capsule shape dynamics in relevant conditions

Deliverables: Reports of detail designs, flight data and post flight analysis. Also flight hardware (all items procured/developed/manufactured under the present activity).


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MREP / 2018

Applicable THAG Roadmap: Aerothermodynamics (2012)

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4.6.6 TD 21- Thermal

Service Domain ROBOTIC EXPLORATION Technology Domain 21 Thermal Ref. Number: G619-008MT Budget (k€): 400 Title: Mini Heat Switch Qualification

Objectives: The objective is to develop and qualify a miniaturized heat switch capable of conducting 0.5 to 10W of waste heat to a radiator. The heat switch shall be a passive device, which at a specified temperature, makes a thermal link with a cold sink and reject the excess heat.

Description: Robotic exploration missions that are subject to long diurnal cycles, require the used heat switches to thermally decouple from the cold external environment in order to save energy. A heat switch based on the Loop Heat Pipe technology was developed in the frame of a TRP activity. The technology is currently baselined for the Exomars Rover. The heat switch LHP was designed to transport 10 to 50W of waste heat. However,when managing small power dissipation coming from RHUs or payloads, a dedicated LHP Heat switch may be oversized and too complex for the application. A miniaturized heat switch TRP activity was initiated with a goal to have a mass lower than 60g and would be installed in series between the radiator and the dissipative unit. The heat transport of the device is targeted to be between 0.5W to 10W. The proposed activity, plans to further enhance the design of the mini heat switch based on results from previous developments activities. A qualification model shall be manufactured in order to perform environmental testing as well as extend life testing. In addition, the testing of the mini heat switch shall include an end to end validation using a representative payload and radiator mounted in a appropriate configuration.

Deliverables: Qualification Model and a full set of design and test documentation


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Robotic Exploration Missions/ 2016


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Service Domain ROBOTIC EXPLORATION Technology Domain 21 Thermal Ref. Number: G619-009MT Budget (k€): 300 Title: Ablative TPS Numerical Test Cases - Mathematical Code Assessment &

Improvement Objectives: To assess the reliability of the mathematical codes used to size the thickness of

ablative TPS (Thermal Protection System) on entry heat shields; to refine and possibly reduce the related uncertainties; and to identify relevant areas to improve the codes.

Description: In the frame of the European Ablation Working Group, several simplified numerical ablation test cases have been defined and were used by different partners to assess the performance of available codes for ablative TPS sizing. Those test cases were based on literature data which, however, turned out to be incomplete and in several aspects not consistent. Missing data had to be complemented by assumptions, which strongly limited the suitability of the derived test cases to assess the performance of the mathematical codes used for ablative TPS sizing. In recent years a new European lightweight ablative material has been developed (TRP-DEAM, MREP-DEAM2) specifically tailored for the Earth return capsule of sample return missions. Also for this new material, now called ASTERM, material and test data cannot be made openly available due to industrial confidentiality aspects. However, a similar material exists, called AQ61, which in its physical composition and performance is very similar to ASTERM, but due to its more complicated manufacturing process is not considered as candidate for relevant flight applications. Within a previous TRP activity (Thermal Response Characterisation of Reference TPS Material) a dedicated set of plasma tests has been performed which are intended to be used now to establish numerical test cases based on real test data. While also a basic set of material characteristics of AQ61 is available, material characterisation will have to be completed as part of this activity. In order to rebuild the numerical test case, an integrated solution for charring ablators (including thermo-chemistry), is needed. This can be achieved by the coupling (exchange by files or on the fly evaluation of properties) of a response code for charring ablators with a code for equilibrium chemistry calculations. In order to rebuild the plasma test, the thermal response code must be capable of modelling the test specimen (an axis-symmetric model), and the chemistry code must have the capabilities to model the charring materials used in real ablators (like AQ61, MONA, ASTERM, ...). The following work is to be conducted in this activity:

- Establish a booklet with a set of numerical ablation test cases based on available plasma test results of the AQ61 material

- Where necessary the available data shall be complemented by relevant additional material characterisation

- Coupling of a response code for charring ablators with a code for equilibrium chemistry calculations

- Model and run the above test cases with at least three of the ablative TPS sizing codes available in Europe

- Compare the results with the available plasma test data, assess the code/model performance and identify the weaknesses of the used codes

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- Derive relevant uncertainties based on the test cases and extrapolate these uncertainties to relevant entry analysis

- Identify relevant code improvements and code delta-development The booklet shall be established in progressive steps, starting from a simple test case which is iteratively increasing in complexity. E.g. the ablation-chemistry coupling would be an element of an advanced iteration.

Deliverables: - Booklet with the definition of a set of numerical test cases. - Technical Notes on material characterisation, test case results and code

assessment


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Sample return missions / 2016
