european space agency cosmic vision 2015-2025 technology

EUROPEAN SPACE AGENCY

COSMIC VISION 2015-2025

TECHNOLOGY DEVELOPMENT PLAN

Programme of Work 2009-2013 and related Procurement Plan SUMMARY This document presents the activities in the Basic Technology Research Programme (TRP) and in the Science Core Technology Programme (CTP) supporting the implementation of ESA’s Cosmic Vision 2015-2025 Plan. The Strategic Initiatives (SI) activities and national initiatives activities of relevance to the Science programme are provided for information. This document is provided for information only and is subject to future updates.

December 2011

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1. Background and Scope This document provides an update to the Cosmic Vision 1525 (CV1525) Technology Development Plan (TDP). The plan contains the description of the technology development activities (TDAs) required for the technological preparation of the CV1525 ESA science programme. This plan was first issued in 2008 as ESA/IPC(2008)33,add1 and the last update was presented in ESA/IPC(2010)81,rev.1 approved by November 2010 IPC. The major development presented in this update of the plan concerns the technology development activities identified for the candidate missions selected following the call for the third M-Class (M3) mission. In addition, recommendations by the advisory structure (ESA/SPC(2011)27) on technology development priorities for future missions are addressed through the addition of TDAs in several areas. The activities presented herein are those selected following the TECNET review process conducted in September 2011. Activities under ESA responsibility are presented for implementation. Activities under national member state responsibility are provided for information. A decision on the JAXA-led mission of opportunity, SPICA, is now expected in 2012. As such the TDAs for the SPICA mission contained within this plan will not be implemented before the SPC decision on SPICA is known. The plan covers the period 2009-2013 for the L-Class and M-Class Cosmic Vision mission candidates. The implementation of the L-Class TDAs will consider the down-selection decision in 2012. Critical mission enabling developments, generically applicable to several possible future space science missions are also addressed in this plan. In addition, science related activities identified for under-returned member states and funded by the Strategic Initiatives (StrIn) Programme are included in this plan for information. 2. Cosmic Vision Science Missions 2.1 Evolution of the Cosmic Vision 2015-2025 Plan The Cosmic Vision 2015-2025 plan consists of a number of “Science Questions” to be addressed in the course of the 2015-2025 decade. The future space missions to be implemented to this purpose will result from competitive Announcements of Opportunity (AO hereafter) and following down selection processes, generally made in two steps. The down selection review and decision process is described in ESA/SPC(2009)3, rev.1. The first AO of the CV programme was issued in March 2007, targeting one M-Class and one L-Class mission initially for a launch in 2017 and 2018. From the 50 proposals received, five M-Class (Euclid, PLATO, Marco Polo, Cross Scale and the mission of opportunity SPICA) and three L-Class (IXO, Laplace or Tandem as Outer

Planet mission, LISA) mission candidates were selected for assessment. Subsequently, Laplace was selected as the outer planet mission within the CV programme. In early 2009, the CV1525 plan was updated reflecting the programme funding availability, the technical progress of the studies, the mission technology readiness and the availability of international partners. The revised plan was as following:

- The two launch slots in 2017 and 2018 were confirmed, targeting ESA-led M1 and M2 missions, with a cost cap target to ESA of 450 ME for each mission,

- Solar Orbiter was reclassified as the sixth M-mission candidate for M1/M2, - The three large missions were maintained in the plan as candidates for L1 but

with a large involvement of international partners, essentially NASA and JAXA, and for a target launch year in 2020 subject to partnership consolidation,

Following the completion of the definition studies, the M-Class mission candidates Solar Orbiter, Euclid and PLATO have undergone a review of their design and technological status, their financial and programmatic viability and their scientific performance. All three missions were confirmed to provide high class science and any pair of missions could effectively be implemented in the Science Programme. In a dedicated meeting held in Paris on 4th October 2011, the Science Programme Committee has adopted Solar Orbiter as M1 for a target launch in 2017, and selected Euclid as M2 for a target launch in 2019. The SPICA mission of opportunity (JAXA-led) remains on hold, pending JAXA confirmation and further SPC decision. For the L1 mission, NASA informed ESA in early 2011 of its inability to contribute to this mission. Therefore, the three L1 mission candidates are now subject to a reformulation phase targeting European-led or European-only missions, and making best use of the previous activities. The international collaboration context and the reformulation logic are described in ESA/SPC(2011)28. The way-forward on the L-Class candidates will be decided by SPC in February 2012, where, at most, two L missions would be maintained as L1 candidates, for a final selection in 2014 (TBC) and a target launch around 2022 (TBC). New mission names have been introduced for the reformulation exercise: The X-ray mission (ex-IXO) becomes Advanced Telescope for High ENergy Astrophysics (ATHENA), the gravity wave mission (ex-LISA) becomes New Gravitational wave Observatory (NGO) and the Jupiter mission (ex-Laplace) becomes named Jupiter Icy Moons Explorer (JUICE). The second AO of the CV plan was released in July 2010 with the goal of selecting a third M-Class mission (M3) for launch in 2022. From the 47 proposals submitted, 4 have been chosen for assessment study (see http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=48467) with the first step being internal ESA studies in 2011 followed by industrial studies in 2012. The four candidate missions are Exoplanet Characterisation Observatory (EChO), Large Observatory for X-ray Timing (LOFT), MarcoPolo-R, and Space-Time Explorer and Quantum Equivalence Principle Space Test (STE-QUEST). An evaluation of the technology development requirements of these 4 candidates has been made and forms the basis for the ESA and national TDAs identified in this update of the TDP. As for M1/M2 missions, the down-selection is foreseen in two steps: the first down-selection is planned for mid 2013, and the final selection by 2015.

http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=48467

http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=48467

The execution of the CV plan requires coordinated system and technology development activities on both the spacecraft and the payload, implemented in parallel. Such coordination was successfully and timely implemented for M1/M2 and is expected to be preserved or improved for the future missions under preparation. Figure 2.1/1 summarises the current plan timeline.

2009 2010 2011 2012 2013 2017 2018 2019 2020 2021 2022

Euclid

PLATO

Solar Orbiter

SPICA

M-Class

M1/M2 down-selection

L-Class

JUICE

NGO

ATHENA

Programmaticconsolidation

with JAXA

M1/M2 Selection

M1 Launch

M2 Launch

Way forward proposed to SPCL1 Launch

Second CVProposal Call

M3 Launch

Cosmic Vision 2015-2025 Programme Timeline

EChO

LOFT

MarcoPolo-R

STE-QUEST

M3 Candidate Selection

M3 Down-selection

L1 selection (2014)

M3 Selection (2015)

Euclid

Solar Orbiter

2009 2010 2011 2012 2013 2017 2018 2019 2020 2021 2022

Euclid

PLATO

Solar Orbiter

SPICA

M-Class

M1/M2 down-selection

L-Class

JUICE

NGO

ATHENA

Programmaticconsolidation

with JAXA

M1/M2 Selection

M1 Launch

M2 Launch

Way forward proposed to SPCL1 Launch

Second CVProposal Call

M3 Launch

Cosmic Vision 2015-2025 Programme Timeline

EChO

LOFT

MarcoPolo-R

STE-QUEST

M3 Candidate Selection

M3 Down-selection

L1 selection (2014)

M3 Selection (2015)

Euclid

Solar Orbiter

Figure 2.1/1. Cosmic Vision timeline summary.

The CV1525 mission candidates are summarised in Table 2.1/1 below.

Fields M-class L-class Mission of Opportunity

Solar Orbiter (Solar studies)

JUICE (Jupiter system)

Solar System MarcoPolo-R (Asteroid Sample

Return)

Euclid (Dark Energy)

ATHENA ( X-Ray imaging and

spectroscopy)

SPICA (IR astronomy) On hold, JAXA-

led mission) PLATO

(Exoplanets / Asteroseismology)

NGO (Gravitational waves)

EChO (Exoplanet

characterisation)

LOFT (X-ray

spectroscopy and timing)

Astrophysics

STE-QUEST (Test of

Equivalence Principle and

Universality of Free Fall)

Table 2.1/1: Cosmic Vision 2015-2025 Mission Candidates 3. Cosmic Vision Technology Development Plan 3.1 This Technology Development Plan update This technology plan is an update of ESA/IPC(2010)81, rev. 1 (November 2010) which was defined, as for previous versions, using the ESA End-to-End process as described in ESA/IPC(2005)39, involving a Technology Network (TECNET) of technical and mission experts from ESA. The proposed technological activities are based on:

The critical technologies that were identified based on internal ESA studies, Technology development activities identified by industry in the course of the

mission candidates assessment studies, Technology development activities identified by the science instrumentation

community, through studies done by institutes or consortia in parallel to the industrial studies,

An assessment of the technological needs and maturity with respect to ongoing running activities, urgency and funding availability.

In all cases, only the activities to be placed in 2012 are submitted for approval. Those foreseen to be placed in 2013 are provided for information. 3.2 Implementation Principles and Payload related activities Critical basic technology developments of the spacecraft and science instruments must be completed before entering the Definition Phase. As a general rule, Technology Readiness Level (TRL) 5-6 is expected at the start of the Implementation Phase. In line with SPC/SPRT recommendations, the traditional baseline concerning delivery of instruments to ESA by the Member States is maintained for the Science Programme. The responsibility for the science payloads depends on the mission case. For Solar System and Planetary missions, the payload is constituted of an instrument suite provided by the Member States. For Astrophysics missions, the separation line between ESA and Member States responsibilities is agreed on a case by case basis, and progressively frozen by the end of the Assessment Phase. It depends on the mission concept and on ESA and Member States respective financial constraints. As general rules:

- Large and complex payload elements that are strongly interleaved with the spacecraft design remain under ESA responsibility. This applies to the ATHENA telescope. Similar past examples are the Herschel telescope and cryostat.

- Focal plane instruments are under Member States responsibility. This applies to focal plane instruments such as ATHENA WFI or XMS. The last cryogenic stage(s) which are physically embedded in the instrument are assumed to be part of the instrument assembly.

It is assumed that the Member States will be in charge of the technology developments of the instruments they plan to provide, while ESA will implement the technology developments related to the rest of the spacecraft and payload elements remaining under ESA responsibility. As recommended by SPC/SPRT, a good coordination between the technology developments under Member States and ESA responsibility is imperative, thereby avoiding duplication of effort, enabling identification of missing activities and providing ESA with visibility of the payload development. For the L-Class mission TDAs, phased contracts are used in order to accommodate the down-selection and minimise spending for the mission(s) that will not be down-selected. The baseline approach is to have a single contract for each activity, unless otherwise stated in the work plan. In case of specific interest for the Programme - e.g. risk reduction, investigation of different technical solutions, or for enabling competition on critical hardware in the future phases - the Executive may envisage placing parallel contracts provided that good quality offers are received and subject to budget

compatibility. In such a case, the parallel contract will be reflected in the regular update of the work plan, which occurs as a minimum on a yearly basis, for keeping the IPC and SPC fully informed of the work plan implementation. The activities presented in this plan are in general implemented by consortia within European industry. A summary of the current assumptions on the payload procurement scheme is provided in table 3.2/1 for the selected M and L missions. Category A = ESA payload; Category B = payload provided by Member States; Category C = payload is shared between ESA and Member States.

Mission Payload category

Member state provision

ATHENA (ex-IXO) C Optics under ESA responsibility, cryogenic elements TBD, focal plane instruments

provided by institutes EChO C TBD Euclid C Focal plane assemblies with proximity optics,

(IR and VIS) LOFT B Payload consortium

PLATO C Payload assembly excluding CCD detectors. SPICA C SAFARI cryogenic instrument provided by a

consortium of science institutes. JUICE (ex-Laplace) B Instrument suite

MacroPolo-R B Instrument suite Solar Orbiter B Instrument suite, AO process completed in

2009 and instrumentation selected NGO (ex-LISA) B/C TBD

STE-QUEST B Two payload consortia Table 3.2/1: Current assumptions for payload cases for M and L missions. 3.3 Budgets and implementation constraints ESA technology activities mainly rely on TRP and CTP technology budgets and will be submitted to the Industrial Policy Committee (IPC) for approval and implementation. GSTP is marginally used and some technology system studies on future mission themes may be funded by GSP for supporting the technology development definition when necessary. The TRP budget is devoted to initial technology developments, leading to an experimental feasibility verification of critical functions or to a validation at breadboard level in laboratory environment (TRL 3). In case of components this might be extended e.g. radiation hardening, since otherwise a proof of feasibility is not possible. The CTP budget focuses on reaching a higher level of technology maturity by developing engineering models, tested in the relevant environment, before the start of the definition phase of a scientific project (TRL 5-6).

The Executive will implement the plan according to general procurement principles and geo-return requirements. In particular, some changes in procurement policies are possible in the frame of the measures necessary to structurally recover geo-return deficits, e.g. by the use of the so-called Strategic Initiative for Under-returned Countries. Note that most contracts are placed with consortia with the contract value typically spread over several member states. Payload related technology activities are presented for information; their definition and implementation are under the responsibility of national entities. This TDP has considered the information available from ESA studies and member states. These developments are marked as “National” with the funding scheme being defined by the Member States on a case by case basis. The use of GSTP is appropriate, in particular for complex developments involving several Member States. PRODEX may also be used, as well as direct national funding of national institutes or any other appropriate scheme. Concerning the European Cooperating States (ECS), PECS funding could cover payload developments. Additionally, in order to facilitate the build-up of strategic capabilities in future new member states, limited PECS co-funding of activities funded under TRP or CTP may be considered by ESA on a case by case basis. National support in compliance with the ECS agreement (ESA/C(2001)29) would be required. 3.3.1 Activities funded under Special Measures, Special Initiatives and Strategic Initiatives Programmes A number of mission-specific requirement-driven activities existing within the plan have been identified as a means of addressing under-return within the science programme. These activities are labelled as either Special Measures or Strategic Initiatives (StrIn) (formerly Special Initiatives) under the remarks column of the activity summary tables. Activities indentified as Special Measures address the UK only. Austria, Denmark, Finland, Ireland, Norway, Sweden and Switzerland are currently eligible Strategic Initiative countries. In addition measures to address Greece and Portugal under-return are proposed in ESA/IPC(2011)113. In addition, TDAs which are fully funded by the StrIn programme are addressed in a specific section of the technology plan. In some cases, the activities address identified requirements for the missions currently within the CV programme. In other cases activities addressing generic areas of interest and new enabling technologies, with potential application in the science programme are included. These activities are generally selected through specific calls for proposals initiated by the Strategic Initiative Programme within the target countries. These Strategic Initiative activities are fully funded by the Strategic Initiatives Programme as indicated by the SI under the programme column of the activity summary tables. They are provided for information only in this document with IPC approval in ESA/IPC(2010)118 and ESA/IPC(2011)118.

The activities for Denmark and Ireland are a result of the Special Announcements of Opportunity for those countries held in 2009 and 2010. For Austria the results of the national call (ASAP 2010) are utilised. 3.4 ESA activities for L-class and M-class missions The ESA technology development activities required for the M-class candidate missions are presented. Critical technology developments for the related science instruments that are to be provided by the Member States are covered. Note that the implementation of the SPICA TDAs awaits the respective SPC decision. Activities being implemented are indentified in the remarks column of the summary tables. The technology development activities for the L-class mission candidates are also included, Activities being implemented are indentified in the remarks column of the summary tables. The activities are implemented with the key objective of reaching TRL ≥ 5 before entering the implementation phase. For the practical implementation of ESA TDAs, the proposals for 2012 are firm, whereas the period beyond 2012 is provided for information only. The TDA list will continue to be revisited on a regular basis to reflect the evolution of the CV programme, the system studies and the results of ongoing activities. As a general rule TDAs which have been completed are removed from the plan. 3.5 Addition of activities pre-dating the Cosmic Vision Technology Development Plan Pre Cosmic Vision Technology Development Plan TDAs have been added in this update – T217-059PA, T217-059PA-B and T217-059PA-C concerning NIR large format sensor array (originally approved in ESA/IPC(2008)3 as T215-01MM. 4. Candidate Missions and Science Themes 4.1 Candidate missions This section provides an overview of L-class and M-class mission candidates. More details can be found on the Cosmic Vision web site http://sci.esa.int/science-e/www/area/index.cfm?fareaid=100. 4.1.1 L-class Mission Candidates The three L-class mission candidates have completed the Assessment Phase. NGO (ex-LISA) will track for the first time the elusive ‘gravity waves’ predicted by General Relativity, thus giving birth to a new kind of astronomy from space. Complementing the traditional astronomy studying the electromagnetic spectrum,

http://sci.esa.int/science-e/www/area/index.cfm?fareaid=100

http://sci.esa.int/science-e/www/area/index.cfm?fareaid=100

NGO will attempt to detect the tiny ripples of space-time due to the fundamental force of gravity. The mission is currently undergoing reformulation activities as ESA led mission. JUICE (ex-Laplace) is a mission to Jupiter. The mission concept is based on multiple flybys of a number of Galilean Moons prior to eventually entering into orbit around Ganymede. A payload suite of 11 instruments including remote-sensing and in-situ suites will provide new insight into the Jovian system. The mission is currently undergoing reformulation activities as ESA led mission. ATHENA (ex-IXO) has evolved from the IXO mission concept following the L class reformulation exercise and is the next-generation X-ray space observatory designed to study the hot, million-degree universe (e.g. supermassive black holes, evolution of galaxies and large-scale structures and matter under extreme conditions). The ATHENA concept is based on a fixed structure connecting two identical telescope optics with the focal plane instrumentation consisting of a Wide Field Imager (WFI) and X-ray Microcalorimeter (XMS). The mission is currently undergoing reformulation activities as ESA led mission. 4.1.2 M-class Mission Candidates The three M-Class mission candidates for the first two launch slots (M1, M2) and one mission of opportunity (TBC) are briefly described below: Solar Orbiter will perform near sun in-situ measurements, using instruments to measure the solar wind, energetic particles, magnetic fields and radio- and plasma waves. Solar Orbiter will also produce high-resolution images and spectra of the Sun and its environment, using instruments in the visible, extreme ultra violet and X-rays. The mission is foreseen in collaboration with NASA, who would provide the launcher and a contribution to science instrumentation. EUCLID is an ESA mission which aims to study the geometry and the nature of the dark Universe (dark matter, dark energy) with unprecedented accuracy. For that purpose, the mission investigates the distance-redshift relationship and the evolution of the cosmic structures by measuring shapes and redshifts of distant galaxies out to redshifts ~ 2, or equivalently by looking back on 10 billion years of cosmic history. The EUCLID payload consists of a single 1.2 m diameter telescope and two focal plane instruments, i.e. a visible imager (VIS) and a near-IR photo-spectrometer (NISP). PLATO “PLAnetary Transits and Oscillations of stars” aims to characterise exoplanetary systems by detecting planetary transits and conducting asteroseismology of their parent stars. This is achieved through ultra-high precision, long (few years), uninterrupted photometric monitoring in the visible of very large samples of bright stars. The resulting high quality light curves will be used on the one hand to detect planetary transits, as well as to measure their characteristics, and on the other hand to provide a seismic analysis of the host stars of the detected planets, from which precise measurements of their radii, masses, and ages will be derived. The baseline design consists of a large number of refractive telescopes arranged in a sun-shielded payload module. The payload module interfaces to a service module. PLATO will observe a

very large number of stars and cover an extensive portion of the sky in order to maximize the number of detected transiting exo-planets. This can be translated into three main mission drivers: 1) as large FoV as possible (more stars can be seen the larger the observed sky field is), 2) as large collecting area as possible (a large collecting area results in observing more faint stars with the required high accuracy), 3) long mission lifetime (a long mission lifetime allows for multiple observations of transits of stars in an Earth-like orbit and for several sky fields to be observed during several years). SPICA (Space Infrared telescope for Cosmology and Astrophysics), a JAXA led mission, following on the heritage of Herschel and ISO/ESA, Spitzer/NASA and Akari/JAXA missions. The observatory will be equipped with a 3.2m Ø Ritchey-Chretien telescope. The core waveband is 5 – 210 µm. The telescope is to be operated at a temperature of less than 6K. The telescope and instrument suite are cooled by a cryogenic cooling chain consisting of passive radiative cooling together with a series of mechanical coolers. Because of its high spatial resolution and unprecedented sensitivity, SPICA can address a number of key problems in modern astrophysics, ranging from galaxy and star-formation history to formation of planets and detection of exoplanets. The envisaged European contribution is the provision of the SPICA Telescope Assembly (STA), potential provision of ground segment support and the provision of the SPICA FAR Infrared Instrument (SAFARI) by a consortium of scientific institutes funded by the Members States. The four candidates for the third M-Class launch are described below: EChO is an ESA mission candidate which aims to characterise the atmosphere of known transiting exoplanets, potentially from giant Hot Jupiters down to Super-Earths orbiting in the habitable zone of M-dwarf stars. It will use a 1.2 m telescope, feeding a Vis-IR spectrometer covering the wave lengths from 0.4 to 11 microns with a potential extension to 16 microns. While spatial differentiation of the exoplanet and its host star is not necessary, spectral differentiation will be achieved by making differential measurements of in- and out- of transit frames to cancel the star signal. The Large Observatory For X-ray Timing (LOFT) is intended to answer fundamental questions about the motion of matter orbiting close to the event horizon of a black hole, and the state of matter in neutron stars, by detecting their very rapid X-ray flux and spectral variability. LOFT would carry two instruments: a Large Area Detector with an effective area far larger than current spaceborne X-ray detectors, and a Wide Field Monitor that would monitor a large fraction of the sky. With its high spectral resolution, LOFT would revolutionise studies of collapsed objects in our Galaxy and of the brightest supermassive black holes in active galactic nuclei. MarcoPolo-R is a mission to return a sample of material from a primitive near-Earth asteroid (NEA) for detailed analysis in ground-based laboratories. The scientific data would help to answer key questions about the processes that occurred during planet formation and the evolution of the rocks which were the building blocks of terrestrial planets. The mission would also reveal whether NEAs contain pre-solar material not yet found in meteorite samples, determine the nature and origin of the organic

compounds they contain, and possibly shed light on the origin of molecules necessary for life. The Space-Time Explorer and Quantum Test of the Equivalence Mission (STE-QUEST) is a ESA mission candidate to precisely measure the effects of gravity on time and matter using an atomic clock and an atom interferometer. It tests a fundamental assumption and one of the most fundamental predictions of Einstein's theory of General Relativity, the Equivalence principle through gravitational red-shift tests by comparing high precision clocks on ground and in space, and the free fall of quantum objects by comparing the evolution of ultra-cold atom clouds in free-fall. 4.3 Technology Themes for Future missions Following the outcome of the selection of the M3 mission candidates, the Astronomy Working Group (AWG) and the Solar System and Exploration Working Group (SSEWG) were invited to state their views on new technology development areas and their relative priorities for inclusion in the TDP. These recommendations were collated and presented to SPC in ESA/SPC(2011)27. The inclusion of new technology activities addressing the recommended areas is included in the Technologies Applicable to several Cosmic Vision Missions section of this update. Due to the finite funding available, a subset of the recommendations is addressed in this update of the plan. It is the intention that additional technology areas will be addressed in future updates of this plan. Furthermore, the advisory structure report endorsed strategically important ongoing activities, in the areas of nuclear power, near-infrared detectors and light weight X-ray optics for example. The technology plans are updated to account for the impact of the latest technical and programmatic developments upon these areas. 5. Critical Technologies Table 5/1 and 5/2 present the lists of critical technologies that have been identified for the Cosmic Vision mission candidates. This listing includes both ESA and national TDAs. L-class Missions

Mission Technology area Future Technology development activities Mirror Module ruggedizing and environmental testing X-ray optics mass production processes Mirror module performance Petal breadboard Baffling system, mirror module level

X-ray Optics

X-ray test facilities upgrading Instrument read out electronics (cryogenic) Entrance windows and filters Detector developments – WFI and XMS

ATHENA

Payload

Performance studies, anti-coincidence

methods Closed cycle dilution cooler Cryogenics Cryocooler chain for TES

Components Radiation hard characterization: Digital components Memory Mixed analogue and digital Analog components On board computer

Power LILT solar power systems AOCS Star tracker for high radiation environment

Development of compact, highly integrated instrument and subsystem suites

Payload

Radiation effects on payload – shielding, redundancy, rad-hard component solutions etc. Penetrator impactor and surface delivery system study Ground demonstration of impact survival of key systems Penetrator impactor sub-systems: TMTC, OBDH, thermal, power

JUICE

Penetrator option

Development of ruggedized low resource payloads

Payload Opto-mechanical stability characterization Metrology system High-power laser system Gravitational Reference Sensor Electronics Charge Management

Propulsion Micro-propulsion lifetime characterisation

NGO

EMC Magnetic Gradiometer Table 5/1 L-class mission critical technologies M-class Missions

Mission Technology area Future Technology development activities Development of lightweight ablative material (also in MREP)

Hypersonic aerothermodynamics/ aerodynamic stability Parachute system

Re-entry technologies

UHF patch antenna Autonomous GNC for NEO proximity – navigation, landing and sampling operations

AOCS

GNC hardware – radar altimeter, multi-beam laser Sample acquisition, transfer and containment

MarcoPolo-R

Mechanisms

Earth re-entry capsule spin up ejection (SUEM)

Landing-touchdown system – landing leg with impact attenuation e.g. crushable materials

Payload TBD

Power Solar array based on Bepi Colombo cell technology Testing: high solar flux testing, procedures, facilities Heat shield materials- high temperature/UV Heat shield – feedthroughs, mechanisms

Thermal

Heat rejecting filters

Solar Orbiter

Payload Various national activities for in-situ and remote-sensing instrument suites

Mechanisms Fine steering cryogenics tip-tilt mechanism

Coolers Further development of hydrogen sorption Joule Thompson cooler

EChO

Payload Development of low dark current NIR/MIR wavelength HgCdTe detectors

Communications K-band downlink – spacecraft and ground station developments

Propulsion Cold gas system delta development High dynamic range fast readout CCDs Optics: dichroic beam splitter, visible phase plate, grism Cryolens development

EUCLID

Payload

Cryomechanisms Large-area Silicon Drift Detectors and ASIC

LOFT Payload

X-ray capillary plate collimator High-speed, high dynamic range CCD PLATO Payload Refractive telescope breadboard Lightweight primary mirror demonstrator Cryogenic Mirror Secondary mirror cryogenic refocusing mechanism – SAFARI: Detector development SAFARI: Focal plane read-out SAFARI: 50 mK ADR SAFARI: Cryogenic mechanisms

SPICA (TBC)

Payload

SAFARI: Fourier Transform Spectrometer BB Development of laser for Rb Clock PHARAO microwave source delta dev. PHARAO atom tube delta development Development and space qualification of high finesse reference optical cavity for MOLO

STE-QUEST Payload

Microwave-optical frequency generation using optical frequency comb technology

Delta Development and space qualification of a frequency generation, comparison and distribution unit Development of Laser Source for the Atom Interferometer (AI) Development and qualification of a dual-species Rb 85/87 AI Physics Package

Table 5/2 M-class mission critical technologies 6. Key to table and activity template fields The following table provides a summary of the information contained in the summary tables and activity templates.

Programme: Programme budget foreseen for the activity

IPC Approval: Indicates approval status of activity. “IPC” means approval of that activity is requested in the current document. “N/A” means TDA value is below 500k€ and has had AC approval if applicable. A year entry e.g. “Y2008” indicates prior IPC/AC approval of an activity.

Reference: Unique ESA generated reference for TDA

Activity Title: Title of the proposed TDA

Budget: The total Contract Authorisation (CA) values are given in KEURO, at yearly economic conditions. The year for which the budget is intended is specified.

Procurement Policy (PP):

Procurement Types:

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

C(1)* = Activity restricted to non-prime contractors (incl. SMEs).

C(2)* = A relevant participation (in terms of quality and quantity) of non-primes (incl. SMEs) is required.

C(3)* = Activity restricted to SMEs & R&D Entities

C(4)* = Activity subject to SME subcontracting clause

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

column; (Ref. ESA Contract Regulations)

DN/C = Direct Negotiation/Continuation; the contract will be awarded in continuation to an existing contract; (Ref. ESA Contract Regulations)

DN/S = Direct Negotiation/Specialisation; the contract will be awarded by direct negotiation in implementation of a defined industrial policy or resulting from a sole supplier situation; (Ref. ESA Contract Regulations)

* See ESA/IPC(2001)29, Industry has been informed, through the EMITS "News", of the content of that document.

Country: Indicates the country in the case of a special initiative or direct negotiation.

ITT: The quarter when the ITT is intended to be issued.

SW clause applicability: Special approval is required for activities labelled: either “Operational Software” or “Open Source Code”, for which the Clauses/sub-clauses 42.8 and 42.9 (“Operational Software”) and 42.10 and 42.11 (“Open Source Code”) of the General Clauses and Conditions for ESA Contracts (ESA/REG/002), respectively, are applicable.

Remarks: Additional information of relevance to the procurement e.g. DN with a specific contractor.

Objectives: The aims of the proposed TDA.

Description: Overview of the work to be performed.

Deliverables: Provides a short description of the tangible outcome e.g. breadboard, demonstrator, S/W, test data. A final report is standard for every activity.

Current TRL: Describes the current Technology Readiness Level of the product that is going to be developed in this activity.

Target TRL: The TRL expected for the product at the end of the activity. For equipments TRP usually concludes with TRL 3, CTP at TRL 5/6. However in the case of

components target TRL in TRP could be higher. It is also understood that TRLs do not apply to S/W and tools. For these cases description of SW quality, i.e.: architecture, beta version, prototype, or full operational, achieved at the end of the activity.

Application Need/Date:

Describes the required TRL and date for the technology development of which the respective activity is part of on the base of the maturity required by the application. The general rule is that a requirement specifies the need date for a product. For equipments/payloads this is in general TRL 5/6, - the level generally required for Phase B of a project. The exceptions are components, where TRL 8 (flight readiness) should be achieved. For S/W and tools separate readiness levels are defined below

Technology Readiness Level definition used in this technology development

plan:

TRL 1 - Basic principles observed and reported

TRL 2 - Technology concept and/or application formulated

TRL 3 - Analytical and experimental critical function and/or characteristic proof-of-concept

TRL 4 - Component and/or breadboard validation in laboratory environment

TRL 5 - Component and/or breadboard validation in relevant environment

TRL 6 - System/subsystem model or prototype demonstration in a relevant environment (ground or space)

TRL 7 - System prototype demonstration in a space environment

TRL 8 - Actual system completed and "flight qualified" through test and demonstration (ground or space)

TRL 9 - Actual system "flight proven" through successful mission operations

Technology Readiness Levels for S/W and tools

Algorithm: Single algorithms are implemented and tested to allow their characterisation and feasibility demonstration.

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

Beta Version: Implementation of all the software (software tool) functionality is complete. Verification & Validation process is partially completed (or completed for only a subset of the functionality).

S/W Release: Verification and Validation process is complete for the intended scope. The software (software tool) can be used in an operational context.

Application Mission: Possible mission application/follow-on.

Contract Duration: Duration of the activity in months.

Reference to ESTER: Identifies the related requirement in the ESTER database

Consistency with Harmonisation Roadmap and conclusion:

Identifies the related Harmonisation Roadmap Requirement

Table 6/1 Technology Development Plan Field Description

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Annex 0

Budget Summary Tables

Mission Programme 2010 2011 2012 2013 Total

L-Mission Candidate: JUICE

CTP (7) 1150 1300 2500 0 4950

TRP (15) 2900 3150 150 0 6200

Total 4050 4450 2650 0 11150

L-Mission Candidate: ATHENA

CTP (8) 2000 1000 3900 4000 10900

TRP (4) 750 0 0 0 750

Total 2750 1000 3900 4000 11650

L-Mission Candidate: NGO

CTP (13) 2400 3350 7800 3000 16550

Total 2400 3350 7800 3000 16550

M-Mission Candidate: EUCLID

CTP (5) 2500 2000 0 0 4500

TRP (1) 0 300 0 0 300

Total 2500 2300 0 0 4800

M-Mission Candidate: Solar Orbiter

CTP (4) 500 0 0 0 500

TRP (4) 1050 0 0 0 1050

Total 1550 0 0 0 1550

M-Mission Candidate: SPICA

CTP (5) 0 0 3500 1000 4500

Total 0 0 3500 1000 4500

M-Mission Candidate: Plato

CTP (1) 2500 0 0 0 2500

Total 2500 0 0 0 2500

M-Mission Candidate: ECHO

CTP (4) 0 0 1700 0 1700

Total 0 0 1700 0 1700

M-Mission Candidate: LOFT

Total 0 0 0 0 0

M-Mission Candidate: MarcoPolo-R

CTP (1) 0 0 500 0 500

TRP (2) 0 0 450 850 1300

Total 0 0 950 850 1800

Page 2 of 4

Mission Programme 2010 2011 2012 2013 Total

M-Mission Candidate: STE-QUEST

Total 0 0 0 0 0

Technologies applicable to several Cosmic Vision Missions

CTP (14) 1840 650 3900 2900 9290

TRP (33) 3400 5950 5350 3000 17700

Total 5240 6600 9250 5900 26990

2-16 - Strategic Initiatives

Total 450 3819 0 0 4269

Grand Total CTP 12890 8300 23800 10900 55890

Grand Total TRP 8100 9400 5950 3850 27300

Grand Total ESA 20990 17700 29750 14750 83190

Page 3 of 4

of 4


Annex I – a

List of ESA Cosmic Vision Technology Development Activities

This annex contains per mission a complete listing of the technology development activities that are both running and planned. Annex II contains detailed activity descriptions.

Summary of all new and modified ESA activities seeking approval for 2012


Budget Prog.

IPC Appr.

ESA Ref. Activity Title 2010 2011 2012 2013

PP C'try SW Clause applicab.

Remarks

CTP IPC C203-102EP Qualification of integrated LILT solar cells 0 0 1000 0 C NA

TRP N/A T224-002QI Material compatibility assessment with a hydrogen peroxide sterilisation process

0 0 150 0 C(3) NA Possible StrIn activity

CTP IPC C213-003PA Penetrator development within the framework of a Jovian moon mission - Phase3

0 0 1000 0 C(R) UK NA Phase 2 is C213-002PA. Special Measure for UK

CTP IPC C223-056QE Qualification of radiation tolerant FLASH memory 0 0 500 0 C NA Possible StrIn activity

Total - L-Mission Candidate: JUICE 0 0 2650 0


Budget Prog.

IPC Appr.



Remarks

CTP IPC C216-008MM ATHENA Inner SPO Mirror Module 0 0 2600 0 C(1) NA

Previously approved in ESA/IPC(2009)143 for 2000kE. IPC approval sought for budget increase. Title changed from IXO industrialised mass production process for X-ray Optical Unit (XOU) and activity reformulated for ATHENA.

CTP N/A C216-119PA BessyII 12m Station 0 0 200 0 DN/S DE NA DN/S with PTB(DE)

Total - L-Mission Candidate: ATHENA 0 0 2800 0

Page 2 of 18


Budget Prog.

IPC Appr.



Remarks

CTP IPC C217-026PA Cryogenic testing of existing HgCdTe detectors 0 0 500 0 C(1) NA Parallel contract

CTP IPC C217-026PA-B Cryogenic testing of existing HgCdTe detectors 0 0 500 0 C(1) NA Parallel contract

CTP N/A C221-002MT Performance verification and qualification of vibration free Hydrogen sorption JT cryo-cooler

0 0 400 0 DN/C NL NA DN/C with University of Twente (NL)

CTP N/A C215-118MS Characterisation of actuator behaviour for a cryogenic fine steering tip-tilt mechanism


Total - M-Mission Candidate: ECHO 0 0 1700 0


Budget Prog.

IPC Appr.



Remarks

TRP N/A T218-004MP Marco Polo R earth re-entry capsule dynamic stability characterization

0 0 450 0 C NA Possible StrIn activity

CTP IPC C205-019EC Autonomous GNC Technology for NEO Proximity, Landing and Sampling Operations - Phase 2

0 0 500 0 DN/C ES Operational SW

DN/C with phase1 GMV(ES) led consortium. First Phase was T205-029EC

Total - M-Mission Candidate: MarcoPolo-R 0 0 950 0

Page 3 of 18


Budget Prog.

IPC Appr.



Remarks

CTP IPC C221-001MT Detector cooling system including cryostat and active coolers down to 50mK

0 0 2000 0 C(1) NA Replaces C220-033MC

TRP IPC T217-055PA Development of low dark current MWIR/LWIR detectors

0 0 1700 0 C(1) NA Parallel contract

TRP IPC T217-055PA-B Development of low dark current MWIR/LWIR detectors


CTP IPC C217-027PA Low Noise Equivalent Power TES bolometers for FIR applications

0 0 700 0 C(R) UK NA

CTP IPC C218-001MP Characterisation of radiation for high speed entry 0 0 750 0 DN/C PT NA DN/C with IST-IPFN (PT). Special measure to PT.

CTP N/A C217-028PA Sub-Megahertz linewidth laser for Fundamental Physics Missions


TRP N/A T217-058MM Development and stabilisation of octave spanning optical frequency combs based on silicon-nitride planar high-Q microresonator technology

0 0 200 0 DN/S CH NA DN/S with EPFL(CH)

TRP IPC T207-035EE Large radii Half-Wave Plate (HWP) development 0 0 600 0 C(1) NA Possible StrIn activity

TRP N/A T207-036EE Next generation sub-millimetre wave focal plane array coupling concepts


Total - Technologies applicable to several Cosmic Vision Missions 0 0 8500 0

Page 4 of 18

Removed Activities


Budget Prog.

IPC Appr.



Remarks

CTP IPC C223-057QE Qualification of LEON processor in radiation hard environment

0 0 1000 0 C NA



Budget Prog.

IPC Appr.



Remarks

TRP N/A T216-025MM IXO contamination covers demonstrator 0 0 500 0 NA For information



Budget Prog.

IPC Appr.



Remarks

CTP Y2009 C207-003EE Two-axis Steerable X/K-band High Gain Antenna 0 500 0 0 C NA

Total - M-Mission Candidate: EUCLID 0 500 0 0

Page 5 of 18


Budget Prog.

IPC Appr.



Remarks

CTP N/A C220-033MC Test & Verification of Sub-kelvin cooling chain 0 0 600 0 NA For information

TRP N/A T220-037MC Development of a heatshield concept and material screening for near-sun mission

0 250 0 0 C NA Implementation pending confirmation, following CV M3 selection.

TRP N/A T203-036EP Near-sun power generation: Technology demonstration 0 0 1000 0 NA For information


Page 6 of 18

Complete List of Running and Planned Activities

The following tables are a complete list of those activities which are: Running since 2009 i.e. activities for which contracts have been signed In preparation for implementation Foreseen to be implemented up to and including 2013


Budget Prog.

IPC Appr.



Remarks

TRP Y2006 T215-007MM Demonstration of the deployment of a highly integrated low power ice penetrating radar antenna

600 0 0 0 C(2) IT NA TDA is running. TAS(IT)

TRP Y2008 T201-003ED Low mass SpaceWire 0 0 0 0 C(1) UK NA TDA is running. AXON (UK) + subs. 150 kE in 2009

CTP Y2009 C203-101EP Solar cell LILT design optimisation and characterisation 900 0 0 0 C DE NA TDA is running. AZUR (DE) + subs.

CTP IPC C203-102EP Qualification of integrated LILT solar cells 0 0 1000 0 C NA

TRP N/A T224-002QI Material compatibility assessment with a hydrogen peroxide sterilisation process


CTP Y2009 C213-002PA Penetrator development within framework of a Jovian moon mission - Phase2


CTP IPC C213-003PA Penetrator development within the framework of a Jovian moon mission - Phase3


TRP Y2008 T223-021QM Characterisation of radiation resistant materials Phase 1 0 0 0 0 C(2) FR NA TDA is running. Astrium (FR) + subs. Second Phase is C223-001QM. 500 kE in 2009

CTP Y2010 C223-001QM Validation of radiation resistant materials 0 500 0 0 C(2) NA

TRP Y2008 T222-019QC Survey of critical components for 150krad power system design including delta radiation characterisation of RH power EEE components

0 0 0 0 C(1) ES NA TDA is running. ALTER (ES) + subs. 350 kE in 2009

Page 7 of 18

Budget IPC SW Clause Prog. ESA Ref. Activity Title PP C'try Remarks

Appr. applicab. 2010 2011 2012 2013

TRP Y2011 T203-005EP 150 krad power converter/system design and prototyping 0 350 0 0 DN/S AT NA PP changed to DN/S RUAG (AT). See ESA/IPC(2011)118.

TRP Y2008 T222-018QC Front-end readout ASIC technology study and development test vehicles for front-end readout ASICS

625 0 0 0 C ES NA TDA is running. Arquimea (ES) + subs.

TRP Y2009 T222-013QC Radiation characterisation of front-end readout ASIC 0 350 0 0 C(1) NA

TRP Y2008 T222-017QC Radiation Tolerant analogue / mixed signal technology survey and test vehicle design

725 0 0 0 C ES NA TDA is running. Arquimea (ES) + subs.

TRP Y2009 T222-014QC Radiation characterisation of RT analogue / mixed signal technology

0 350 0 0 C(1) NA

TRP Y2008 T201-004ED DAREplus (Design Against Radiation Effects) ASICs for extremely rad hard & harsh environments

0 1200 0 0 DN/S BE NA TDA is running. IMEC (BE) + subs.

TRP Y2008 T201-002ED Latch up protection for COTS (Commercial, off-the-shelf) digital components

150 0 0 0 C IT NA TDA is running. SITAEL (IT)

TRP Y2008 T222-020QC Radiation characterisation of Laplace critical RH optocouplers, sensors and detectors

0 900 0 0 C(1) FR NA TDA is running. TRAD (FR) + subs.

TRP Y2008 T222-016QC Radiation hard memory 800 0 0 0 C(2) DE NA TDA is running. Astrium (DE) + subs.

CTP IPC C223-056QE Qualification of radiation tolerant FLASH memory 0 0 500 0 C NA Possible StrIn activity

TRP Y2008 T204-009EE Radiation Effects on Sensors and Technologies for Cosmic Vision SCI Missions (REST-SIM)

0 0 0 0 C(2) UK Open sourceTDA is running. QinetiQ (UK). 500 kE in 2009

CTP Y2009 C205-100EC Evaluation of star tracker performance in high radiation environment

250 0 0 0 C FR NA TDA is running. Sodern (FR)


Page 8 of 18


Budget Prog.

IPC Appr.



Remarks

TRP Y2008 T216-026MM IXO mirror module ruggedizing and environmental testing - Phase 1

0 0 0 0 C(1) NL NA TDA is running. Cosine (NL). Second phase is C216-006MM. 1000 kE in 2009

CTP Y2008 C216-006MM IXO mirror module ruggedizing and environmental testing - Phase 2

0 1000 0 0 C NA First phase is T216-026MM

CTP Y2009 C216-004MM Development of IXO Si pore optics and mass production processes

2000 0 0 0 DN/S NL NA TDA is running. Cosine(NL) + subs.

CTP IPC C216-008MM ATHENA Inner SPO Mirror Module 0 0 2600 0 C(1) NA

Previously approved in ESA/IPC(2009)143 for 2000kE. IPC approval sought for budget increase. Title changed from IXO industrialised mass production process for X-ray Optical Unit (XOU) and activity reformulated for ATHENA.

CTP N/A C216-007MM ATHENA petal breadboard 0 0 0 2500 NA For information

CTP Y2010 C216-117MM True Wolter Silicon Pore Optics and Improved Performance

0 0 1100 0 DN/C NL NA Adapted for ATHENA. DN with Cosine (NL) led consortium

CTP N/A C216-120MM High Performance ATHENA SPO Mirror Module 0 0 0 1500 NA For information

TRP Y2006 T216-100MM Micropore Baffle (Tapered Plates Baffle For Silicon Pore Optics)

0 0 0 0 C(2) NL NA TDA is running. Cosine + Micronit (NL). 400 kE in 2009

TRP Y2009 T216-024MM Baffled IXO mirror module 400 0 0 0 C(1) NL NA TDA is running. Cosine (NL) + subs.

CTP N/A C216-119PA BessyII 12m Station 0 0 200 0 DN/S DE NA DN/S with PTB (DE)

CTP Y2008 C216-005MM Panter X-ray test facilities upgrades 0 0 0 0 DN/S DE NA TDA is running. MPE (DE). 300 kE in 2009

TRP Y2008 T216-022MM Large area X-ray window development. 350 0 0 0 C(1) FI NA TDA is running. Oxford Instruments (FI)


Page 9 of 18


Budget PP C'try

IPC Appr.

SW Clause applicab.

Prog. ESA Ref. Activity Title 2010

Remarks 2011 2012 2013

Metrology system for LISA 0 1000 0 0 C(2) NA Special Initiative. TDA is running. DTU (DK) + subs.

DK CTP Y2008 C207-013PW

N/A C214-002PW LISA metrology system end-to-end characterization 0 CTP 0 0 1800 NA For information

CTP Y2008 C207-014PW High-power laser system for LISA 0 30000 0 C(2) NA

CTP Y2010 C217-001MM Tunable laser frequency reference 0 0 1000 0 C(1) NA

CTP Y2010 C215-022PW 0 0 1000 0 LISA Optical Assembly Articulation Mechanism (OAAM)

NA C(2)

CTP Y2008 C207-012PW Opto-mechanical stability characterization for LISA 2400 0 0 0 C(2) NL NA TDA is running. TNO (NL) + subs.

CTP Y2010 LISA Inertial Sensor final design 0DN is proposed with LISA Pathfinder GRS contractor (CGS (IT))

IT C214-001PW 0 0 1200 DN/S NA

1450 0 0 DN/C CH NA Special Initiative. Budget increased to 1450 kE - see ESTEC/AC/452-18. TDA is running. RUAG (CH) + subs.

CTP Y2009 C207-009PW GRS Front End Electronics characterization for LISA 0

0 900 0 0 Special Initiative. TDA is running. Imperial College (UK) + subs.

UK CTP Y2008 C207-011PW Charge Management System for LISA C(2) NA

Compact low noise magnetic gradiometer 0 0 0TDA is running. RAL (UK) + subs. 600 kE in 2009

CTP Y2008 C207-010EE 0 C(1) UK NA

CTP Y2008 C207-016PW Outgassing and Contamination characterization for LISA 0 0 900 0 C(2) NA

CTP Y2009 C207-015PW LISA micropropulsion lifetime characterization 0 0 0 DN/C IT NA DN/C with ALTA (IT) 1900

CTP Y2006 C216-113PW Optical Bench Development for LISA 0 0 0 0 C(2) DE NA TDA is running. Astrium (DE) + subs. 1850 kE in 2009

Total - L-Mission Candidate: NGO 2400 3350 7800 3000

Page 10 of 18


Budget Prog.

IPC Appr.



Remarks

CTP Y2009 C206-005ET Near Earth Space Research X/X/K-Band Transponder Engineering Model

0 1000 0 0 C Operational SW

CTP Y2009 C219-001MP Delta Development of Cold Gas Propulsion for Euclid 500 0 0 0 C IT NA TDA is running. TAS (IT) + subs. Parallel contract

CTP Y2009 C219-001MP-B Delta Development of Cold Gas Propulsion for Euclid 0 500 0 0 C NA Parallel contract

CTP Y2010 C217-002PA Euclid CCD Pre-Development 2000 0 0 0 DN/S UK NA TDA is running. E2V(UK)

CTP Y2010 C217-012PA Euclid CCD radiation testing 0 500 0 0 DN/C UK NA Continuation of running contract with SSTL (UK).

TRP Y2010 T216-101PA Dichroic for Euclid 0 300 0 0 C NA

Total - M-Mission Candidate: EUCLID 2500 2300 0 0


Budget Prog.

IPC Appr.



Remarks

TRP Y2009 T221-108QT Materials Selection and Testing 500 0 0 0 DN/S AT NA TDA is running. DN ARC (AT)

TRP Y2009 T203-111EP High Intensity High Temperature Solar Generator Study 250 0 0 0 C DE NA TDA is running. Astrium (DE)

CTP Y2009 C204-107TC Small high flux test facilities 200 0 0 0 C BE NA TDA is running. ALM (BE)

TRP Y2009 T204-110TC Solar concentrator test facility upgrade study 100 0 0 0 C BE NA TDA is running. CSL (BE)

TRP Y2009 T204-109QE Methodology for high solar flux testing acceleration. Explicitly address combined UV/thermal and accelerated testing, and existing BC facilities.

200 0 0 0 C FR NA TDA is running. Onera (FR) + subs.

CTP Y2009 C216-102MM Heat rejecting entrance window 300 0 0 0 DN/C IT NA TDA is running. Selex Galileo (IT)

CTP Y2006 C205-001PS High Flux Sun Sensor/Sun Filters 0 0 0 0 C(1) BE NA TDA is running. LAMBDA-X/CSL (BE). 400 kE in 2009

Page 11 of 18


Appr. applicab. 2010 2011 2012 2013

CTP Y2006 C216-114PS Validation of Liquid Crystal Variable Retarder for the Solar Orbiter Polarisation Modulation Package (previous title: Solo - Polarisation Modulation Package LCVR)

0 0 0 0 C(1) ES NA TDA is running. INTA(ES) + subs. 250 kE in 2009

Total - M-Mission Candidate: Solar Orbiter 1550 0 0 0


Budget Prog.

IPC Appr.



Remarks

CTP Y2009 C216-024MM SPICA Telescope focussing mechanism for secondary mirror - Phase 1

0 0 250 0 C NA Parallel competitive phase 1: 2 contracts at 250 kE. Subject to SPC confirmation.

CTP Y2009 C216-024MM-B SPICA Telescope focussing mechanism for secondary mirror - Phase 1

0 0 250 0 C NA Parallel competitive phase 1: 2 contracts at 250 kE. Subject to SPC confirmation.

CTP N/A C216-025MM SPICA Telescope focussing mechanism for secondary mirror - Phase 2

0 0 0 1000 NA For information. Single phase 2 contract. Subject to SPC confirmation.

CTP Y2009 C216-022MM Light-weight mirror demonstrator breadboard in Sic 0 0 1500 0 C NA Parallel contract to C216-021MM. Subject to SPC confirmation.

CTP Y2009 C216-021MM Light-weight mirror demonstrator breadboard in HB-Cesic

0 0 1500 0 C NA Parallel contract to C216-022MM. Subject to SPC confirmation.

Total - M-Mission Candidate: SPICA 0 0 3500 1000

Page 12 of 18


Budget Prog.

IPC Appr.



Remarks

CTP Y2010 C217-010PA Development of optimised CCD for PLATO 2500 0 0 0 DN/S UK NA TDA is running. E2V(UK)

Total - M-Mission Candidate: Plato 2500 0 0 0


Budget Prog.

IPC Appr.



Remarks

CTP IPC C217-026PA Cryogenic testing of existing HgCdTe detectors 0 0 500 0 C(1) NA Parallel contract

CTP IPC C217-026PA-B Cryogenic testing of existing HgCdTe detectors 0 0 500 0 C(1) NA Parallel contract

CTP N/A C221-002MT Performance verification and qualification of vibration free Hydrogen sorption JT cryo-cooler

0 0 400 0 DN/C NL NA DN/C with University of Twente (NL)

CTP N/A C215-118MS Characterisation of actuator behaviour for a cryogenic fine steering tip-tilt mechanism


Total - M-Mission Candidate: ECHO 0 0 1700 0


Budget Prog.

IPC Appr.



Remarks

TRP N/A T218-004MP Marco Polo R earth re-entry capsule dynamic stability characterization

0 0 450 0 C NA Possible StrIn activity

CTP IPC C205-019EC Autonomous GNC Technology for NEO Proximity, Landing and Sampling Operations - Phase 2

0 0 500 0 DN/C ES Operational SW

DN/C with phase 1GMV(ES) led consortium. First Phase was T205-029EC

Page 13 of 18


Appr. applicab. 2010 2011 2012 2013

TRP N/A T216-102MM Miniaturized Imaging Laser Altimeter 0 0 0 850 NA For information

Total - M-Mission Candidate: MarcoPolo-R 0 0 950 850


Budget Prog.

IPC Appr.



Remarks

CTP Y2008 C220-032MC 15K Pulse Tube cooler 600 0 0 0 C FR NA TDA is running. Air Liquide (FR) + subs.

TRP Y2008 T220-053MC Advanced 2K JT cooler 0 0 0 0 DN/S UK NA TDA is running. RAL (UK). 700 kE in 2009

CTP IPC C221-001MT Detector cooling system including cryostat and active coolers down to 50mK

0 0 2000 0 C(1) NA Replaces C220-033MC

TRP N/A T217-059PA NIR large format sensor array 300 1200 0 0 C NA Activity origninally approved as T215-01MM in ESA/IPC(2008)3 - 1500 kE.

TRP N/A T217-059PA-B NIR large format sensor array 300 1200 0 0 C NA Activity origninally approved as T215-01MM in ESA/IPC(2008)3 - 1500 kE.

TRP N/A T217-059PA-C NIR large format sensor array 300 0 0 0 NA

Activity origninally approved as T215-01MM in ESA/IPC(2008)3 - 1500 kE. Only Phase 1 implemented. For information.

TRP Y2008 T216-047PA Prototype ASIC development for large format NIR/SWIR detector array.

0 500 0 0 C(1) NA

CTP N/A C216-017PA Optimised ASIC development for large format NIR/SWIR detector array.

0 0 0 1000 NA For information. Follow-on to T216-047PA

TRP N/A T216-048PA Prototype NIR/SWIR large format array detector development.

0 0 0 2000 NA For information

CTP N/A C216-018PA Optimised NIR/SWIR large format array detector development.

0 0 0 0 NA For information, follow-on to T216-048PA, 3ME in 2014.

Page 14 of 18


Appr. applicab. 2010 2011 2012 2013

TRP IPC T217-055PA Development of low dark current MWIR/LWIR detectors


TRP IPC T217-055PA-B Development of low dark current MWIR/LWIR detectors


TRP Y2011 T217-054MM European Low-Flux CIS Development and Optimisation (old title: CMOS APS Operation Optimisation)

0 0 750 0 C(1) NA SD2 contribution to CMOS APS development activity T717-301MM in ESA/IPC(2011)3, add.2

CTP Y2008 C222-034QC CCD radiation characterisation 0 0 0 0 C UK NA TDA is running. SSTL (UK). 500 kE in 2009

TRP Y2010 T217-011PA P-channel CCD performance characterization and radiation testing

0 400 0 0 C NA

CTP N/A C217-025PA Advanced P-channel CCD Development 0 0 0 500 C NA For information

TRP Y2006 T204-007MM TES Spectrometer 0 0 0 0 C(1) UK NA TDA is running. Cardiff University (UK) + subs. 700 kE in 2009

CTP IPC C217-027PA Low Noise Equivalent Power TES bolometers for FIR applications

0 0 700 0 C(R) UK NA

TRP Y2009 T216-049MM Silicon drift detectors for gamma-ray scintillators 0 500 0 0 C(1) IT NA TDA is running. PoliMi (IT) + subs.

CTP Y2010 C217-005PA Enhancement of a silicon photomultiplier module for scintillator detection applications

490 0 0 0 DN/S IE NA TDA is running. SensL (IE)

TRP Y2008 T216-050PA Low-noise scintillator detectors for planetary remote-sensing

0 500 0 0 C(1) NL NA TDA is running. Praesepe (NL) + subs.

TRP Y2008 T204-043EE Rad-Hard Electron monitor 400 0 0 0 C(1) CH NA TDA is running. RUAG/PSI (CH)

TRP Y2008 T204-044PA Solid-state neutron detector 0 0 0 0 C(1) UK NA TDA is running. MicroFab (UK). 300 kE in 2009

TRP Y2008 T216-023MM Back-up IXO optics technology - Phase 1 0 0 0 0 C(1) IT NA TDA is running. INAF (IT) + subs. Second phase is C216-002MM. 1300 kE in 2009

CTP N/A C216-002MM Back-up IXO optics technology - Phase 2 0 0 0 1400 NA For information. First phase is T216-023MM

CTP Y2008 C216-118PA Uniform Coating of High Aspect Surfaces 0 0 0 0 DN/S IE NA TDA is running. Tyndall (IE). 460 kE in

Page 15 of 18


Appr. applicab. 2010 2011 2012 2013

2009

CTP Y2009 C216-071PA Opto-mechanical performance characterisation of IR components in representative environment

0 650 0 0 C(1) NL NA TDA is running. TNO (NL) + subs.

CTP Y2008 C223-035QM Characterisation of ultra-stable materials at cryogenic temperature

250 0 0 0 C DE NA TDA is running. PTB (DE)

TRP Y2008 T223-055QM Materials Charging effects under extreme environments (ultra-low temperatures and high radiation fields)

250 0 0 0 C(1) UK NA TDA is running. QinetiQ (UK)

TRP Y2009 T204-041EE Charging properties of new materials 0 200 0 0 C(1) FR NA TDA is running. ONERA (FR)

TRP Y2009 T204-042EE Computational tools for spacecraft electrostatic cleanliness and payload analysis

300 0 0 0 C(1) FR Open source TDA is running. ONERA (FR)

TRP Y2008 T212-045GS X/K band feed 0 0 0 0 C CH NA TDA is running. MIRAD (CH). 350 kE in 2009

TRP Y2008 T212-046GS X/K/Ka band dichroic mirror 0 0 0 0 C UK NA TDA is running. COBHAM (UK) + sub. 300 kE in 2009

GSTP Y2008 G512-003EC Precise Gravitational Modelling of Planetary Moons and NEO (Near Earth Objects) Asteroids

0 350 0 0 DN/S DE Operational SW

TDA is running. Astos (DE) + subs. (old code: G205-004EC)

TRP Y2008 T205-029EC Autonomous GNC Technology for NEO proximity, Landing and sampling Operations - Phase 1

300 0 0 0 C ES Operational SW

TDA is running. GMV (ES) + subs.

CTP Y2008 C201-030ED High processing power DPU based on high rel. DSP 500 0 0 0 C(1) UK NA TDA is running. Astrium (UK) + subs.

TRP Y2008 T217-051MP Ablation radiation coupling 0 400 0 0 C Open source

TRP Y2008 T217-052MP Kinetic shock tube for radiation data base for planetary exploration

1000 0 0 0 C PT NA TDA is running. IST-IPFN (PT) + subs.

CTP IPC C218-001MP Characterisation of radiation for high speed entry 0 0 750 0 DN/C PT NA DN/C with IST-IPFN (PT). Special measure to PT.

TRP Y2009 T216-033MM High performance frequency dissemination techniques - Phase1

250 0 0 0 C DE NA TDA is running. TIMETECH (DE) + subs. Parallel contract

TRP Y2009 T216-033MM-B High performance frequency dissemination techniques - Phase1

0 250 0 0 C DE NA TDA is running. TIMETECH (DE) + subs. Parallel contract

TRP N/A T217-034MM High performance frequency dissemination techniques - Phase 2

0 0 0 1000 NA For information

Page 16 of 18


Appr. applicab. 2010 2011 2012 2013

CTP N/A C217-028PA Sub-Megahertz linewidth laser for Fundamental Physics Missions


TRP N/A T217-058MM Development and stabilisation of octave spanning optical frequency combs based on silicon-nitride planar high-Q microresonator technology

0 0 200 0 DN/S CH NA DN/S with EPFL(CH)

TRP Y2008 T207-034EE Modular Wide Field View RF Configurations 0 500 0 0 C(1) UK NA TDA is running. Cardiff (UK) + subs.

TRP IPC T207-035EE Large radii Half-Wave Plate (HWP) development 0 0 600 0 C(1) NA Possible StrIn activity

TRP N/A T207-036EE Next generation sub-millimetre wave focal plane array coupling concepts


TRP Y2010 T224-001QT Near-sun mission heat-shield material assessment 0 300 0 0 DN/C AT NA ARC (AT) + subs.


Strategic Initiatives

Budget Prog.

IPC Appr.



Remarks

SI Y2011 S217-048PA A low-noise, low-power Readout ASIC for STIX - the Spectrometer-Telescope for Imaging X-rays on the Solar Orbiter

0 400 0 0 DN/C NO NA

SI Y2011 S217-047PA Prototype ASIC Development for Large Format NIR/SWIR Detector Array

0 400 0 0 DN/C NO NA Possible parallel contract to T216-047PA

SI Y2011 S203-001PA Hybrid solar power generator and energy storage system for space missions (HySolGen)

0 400 0 0 DN/C NO NA

SI Y2010 S214-003PA Next Generation Ion Emitter Modules 0 150 0 0 DN/S AT NA TDA is running. University of Applied Sciences Wiener Neustadt (AT). Strategic Initiative for Austria

SI Y2010 S201-001PA An On-Board Software Platform for the Next Generation of Infrared Astronomy Missions

0 125 0 0 DN/S AT NA Strategic Inititative for Austria

Page 17 of 18

of 18

Budget Prog.

IPC Appr.



Remarks

SI Y2010 S207-107PA High Efficiency Horn Antennas for Cosmic Microwave Background Experiments and Far- Infrared Astronomy

0 162 0 0 DN/S IE NA Strategic Initiative for Ireland

SI Y2010 S217-014PA Novel silicon photomultiplier configurations for high energy astrophysics applications


SI Y2010 S207-001PA Development of a THz Local Oscillator for Space Science Heterodyne Applications


SI Y2010 S217-013PA Feasibility study for novel design of Fibre Coupled Deep UV LEDs for Charge Control of Proof Masses


SI Y2010 S223-058PA Feasibility Study into the Use of InAIN Based High Frequency Transistors for Space Application


SI Y2010 S220-104PA Numerical Simulation Tool for Parachute Performance 0 200 0 0 DN/S IE NA Strategic Initiative for Ireland

SI Y2010 S219-003PA Numerical Modelling Tool for Evaluation of Sloshing-Reaction Control System Coupling


SI Y2010 S215-118PA Robust motion control, with active vibration damping, of under-actuated flexible structures


SI Y2010 S202-001PA Development of a web-based scientific data analysis and distribution tool


SI Y2009 S216-009MM Multilayer coatings for IXO 450 0 0 0 DN/S DK NA TDA is running. DTU Space (DK). Strategic Initiative for Denmark

SI Y2010 S216-116PA Multilayer coated silicon pore optics stack production and test

0 430 0 0 DN/C DK NA Strategic Initiative for Denmark

SI Y2010 S217-015PA Three-dimensional CZT high resolution detectors for high energy astrophysics applications

0 192 0 0 DN/S DK NA Strategic Initiative for Denmark

Total - Strategic Initiatives 450 3819 0 0

Annex I – b

List of National Technology Development Activities for Science Payloads

This annex provides summary tables of the currently identified technology development activities expected to be implemented by member states. The activities included are those thus far identified for the M3-candidates LOFT and STE-QUEST. Detailed activity descriptions are provided in Annex IV.


Prog. Member state(s) ESA Ref. Activity Title SW Clause applicab.

Remarks

National N216-116SY Capillary-plate collimator for the Large Area Detector NA To be revised by Member States

National N217-088SY Large-area Silicon Drift Detectors NA To be revised by Member States

National N217-089SY Ultra-low noise high-speed detector read-out ASIC NA To be revised by Member States



Prog. Member state(s) ESA Ref. Activity Title SW Clause applicab.

Remarks

National N206-001PA Delta development and qualification of Pharao Tube for Next Generation (NG) Pharao

NA To be revised by Member States

National N206-006PA Delta development and qualification of Pharao Microwave source NA To be revised by Member States

National N217-085PA Development and qualification of Pharao-Next Generation Laser Source for Rb atoms


National N206-007PA Delta-development and test of Pharao Next Generation instrument control unit


National N206-008PA Integration, test and verification of Pharao-Next Generation (PNG) clock NA To be revised by Member States

National N217-084PA Development and qualification of a dual-species Rb 85/87 Atom Interferometer Physics Package


National N217-086PA Development and qualification of Laser Package for the Atom Interferometer


National N217-083PA Development and qualification of the Atom Interferometer control electronics


National N217-087PA Integration, test and verification of the Atom Interferometer instrument NA To be revised by Member States

National N206-003PA Development and space qualification of high finesse reference optical cavity and laser head


Page 2 of 4

SW Clause Prog. Member state(s) ESA Ref. Activity Title Remarks

applicab.

National N206-002PA Delta Development and space qualification of a frequency generation, comparison and distribution unit


National N206-005PA Microwave-optical frequency generation using optical frequency comb technology


National N206-004PA Integration, test, and verification of MOLO NA To be revised by Member States


Page 3 of 4

of 4


Annex II

Detailed Description of ESA Cosmic Vision Technology Development Activities

This annex contains a detailed description of those activities under ESA responsibility.


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

Programme: TRP Reference: T215-007MM

Title: Demonstration of the deployment of a highly integrated low power ice penetrating radar antenna

Total Budget: 600

Objectives

Design and demonstrate by test the deployment and stability of the Yagi antenna for a low power ice penetrating radar for Laplace.

Description

The main objective of this activity is to design and demonstrate by test the deployment and stability of the Yagi antenna for a low power ice penetrating radar suitable for the investigation of the icy shell of Europa, one of Jupiter's moons.

Deliverables

Deployable antenna demonstration model

Current TRL: 1 Target TRL: 3/4 Application Need/Date:

2011

Application Mission:

JUICE Contract Duration:

24

S/W Clause: NA Reference to ESTER


Low mass SpaceWire

Programme: TRP Reference: T201-003ED

Title: Low mass SpaceWire

Total Budget: 150

Objectives

Development of a second generation of SpaceWire cable with a reduced mass by a factor 2 to 3

Description

The SpaceWire standard ECSS-E-50-12A currently specifies the construction and the mass of the SpaceWire cable (80g/m). By defining the requirements on the electrical characteristics of the cable, the cable construction and mass should be optimised. This will lead to the construction of a new generation of SpaceWire cables which more adapted to specific applications. The requirements of the electrical characteristics establish in this activity will be used to update the cable specification in the standard.

Deliverables

test data, EQM cables

Current TRL: 3 Target TRL: 5 Application Need/Date:

2011



12


T-8483


N/A

Solar cell LILT design optimisation and characterisation

Programme: CTP Reference: C203-101EP

Title: Solar cell LILT design optimisation and characterisation

Total Budget: 900

Objectives

Page 2 of 76

Development of solar cells with predictable LILT performance

Description

Current state-of-the-art triple-junction solar cells show a non-predictable performance at LILT conditions. Due to the so-called flat spot phenomenon some solar cells have a clearly lower performance than expected by theory. Currently, it seems that a flat spot cannot be detected by room temperature measurements. Thus, in this activity, the triple-junction cell technology shall be adjusted in a way to avoid flat spots. A full characterisation of this adapted solar cells has to be performed and appropriate screening tests will have to be defined to allow a selection of solar cells with a predictable EOL performance at LILT conditions.

Deliverables

Triple-junction solar cell with predictable LILT performance


2013



24



Qualification of integrated LILT solar cells

Programme: CTP Reference: C203-102EP

Title: Qualification of integrated LILT solar cells

Total Budget: 1000

Objectives

Qualification of solar cells for low intensity and low temperature (LILT) applications such as missions to Jupiter.

Description

The qualification of the solar cell under LILT conditions, both on bare cell and solar cell assembly level is the objective of this activity. The qualification shall be performed according to the qualification test plan established in the preceding activity (C203-101EP) which is planned to end in 2012. As a baseline for the qualification it is foreseen to use the 30% cell product from AZUR SPACE Solar Power GmbH which is coming on the market in 2012. It can be expected that with the same modifications that are applied to the 28% cell, the 30% cell will give the same good performance predictability under LILT conditions as the 28% cell. Before qualification this will be validated by a dedicated test programme as a Phase 1 of this activity. In case this test programme is not successful the 28% cell can be used as a backup to enter qualification.

Deliverables

Qualification test report


TRL 6 in 2015



18


T-8533


Yes. See Harmonisation Technical Dossier A10 and A11

Material compatibility assessment with a hydrogen peroxide sterilisation process

Programme: TRP Reference: T224-002QI

Title: Material compatibility assessment with a hydrogen peroxide sterilisation process

Total Budget: 150

Objectives

Planetary protection regulations limit the probability of contamination of the Jovian moon Europa to less than 1E-4 per mission. Should this requirement not be met by implementing sufficient reliability of the flight system avoiding accidental impact on Europa, a low temperature sterilisation process could be envisaged. This activity would assess material compatibility with such a low temperature sterilisation process.

Description

Page 3 of 76

Materials representing a large surface area on the proposed JUICE spacecraft are identified based on the two industrial team's study results. A material test program is established based on standard test procedures for the specific material, its specific use and the particular impact expected from exposing the material to a hydrogen peroxide sterilisation cycle. Test program is carried out and material compatibilities are identified for subsequent use in the JUICE development phase. The activity will be carried out with reference to process ECSS-Q-ST-70-56.

Deliverables

Material test program for review; Material compatibility assessment report.

Current TRL: N/A Target TRL: N/A Application Need/Date:

2013



18



Penetrator development within framework of a Jovian moon mission - Phase2

Programme: CTP Reference: C213-002PA

Title: Penetrator development within framework of a Jovian moon mission - Phase2

Total Budget: 800

Objectives

Development to TRL 4 of penetrator subsystems and a sampling and measurement system for astrobiological investigations on Europa.

Description

In this phase (Phase 2) of the activity, the following work will be performed: i) Requirements definition and detailed design of a miniaturised, shock-resistant, sampling and measurement system for astrobiological investigation on Europa. ii) Detailed modeling of impact processes associated with impacts into icy regoliths and other simulant materials. iii) Subsystem component development and small-scale impact trials (TRL4).

Deliverables

Technical Data pack including: i)Detailed design of astrobiological sampling and analysis system for a Europan penetrator. ii)Modeling and small-scale impact trial reports. H/W: Hardware elements of platform subsystems for small scale trials


2011



9



Penetrator development within the framework of a Jovian moon mission - Phase3


Title: Penetrator development within the framework of a Jovian moon mission - Phase3

Total Budget: 1000

Objectives

Development to TRL 5 of critical penetrator technologies including full scale system-level impact trials.

Description

The previous phase 1 and 2 activities will have brought many of the penetrator technologies to a TRL of 4 with some having achieved TRL5 at the end of the Phase 2 full-scale trials.

Page 4 of 76

However, some technologies remain to be matured sufficiently for example a miniaturised, hardened UHF communications system and batteries that can survive high g-loads. Therefore, further development of these critical subsystems of any future penetrator are required to be undertaken to bring them to TRL 5. In this phase (Phase 3) of the Penetrator development activity, the following work will be performed: 1)Further subsystem component design and breadboarding (e.g. UHF comms system, batteries, antenna, sampling mechanism) and small-scale impact trials (if required), ii) Impact modelling and penetrator design iteration iii) full-scale system level trials to bring all the required critical technologies to TRL5 as well as demonstrate overall survivability and operation of a penetrator system for planetary applications.

Deliverables

Full-scale hardware elements of a penetrator, including structure and sub-systems. Impact trial reports.


2014



24



Characterisation of radiation resistant materials Phase 1

Programme: TRP Reference: T223-021QM

Title: Characterisation of radiation resistant materials Phase 1

Total Budget: 500

Objectives

Assessment and characterisation of radiation resistance of materials to high radiation field of JUICE mission

Description

Selection of materials, testing of materials, derivation of safe operation limit, design data.

Deliverables

Test results, selection of resistant materials, design data.


2012



36


T-8481


N/A

Validation of radiation resistant materials

Programme: CTP Reference: C223-001QM

Title: Validation of radiation resistant materials

Total Budget: 500

Objectives

Assessment and characterisation of radiation resistance of materials to high radiation field of JUICE mission

Description

Based on the outcome of phase 1 design data are to be derived for the selected materials. This comprehends among others stability of thermo-optical properties, radiation resistance vs. mechanical & thermo-mechanical damage (e.g. CTE changes) and dose rate dependences etc. It may also include the review of the outcome of activity Materials Charging effects under extreme environments (ultra-low temperatures and high radiation fields) and derive design data/recommendations of charging issues).

Deliverables

Page 5 of 76

Design data of materials properties for the selected mission case.


2013



36


T-8481


N/A

Survey of critical components for 150krad power system design including delta radiation characterisation of RH power EEE components

Programme: TRP Reference: T222-019QC

Title: Survey of critical components for 150krad power system design including delta radiation characterisation of RH power EEE components

Total Budget: 350

Objectives

TID (Total Ionizing Dose) Radiation characterization of selected critical power system components (MOSFET driver, bipolar transistors,..) up to the 150Krrad level

Description

Power converters and systems are critical parts of any mission. Power systems with Rad-Hard components (MOSFETS and Bipolar transistors) are available however, in many cases not to the radiation levels required for the JUICE mission (150krad). The following activity, aims at characterising these rad-hard EEE components to mission radiation levels and identify radiation related drifts. This information is in subsequent activities employed to design power converter and systems capable of handling the measured drifts in compliance with mission power requirement.

Deliverables

Test plans, Test reports including data analysis, final report, and tested samples


2011



12


T-8480


N/A

150 krad power converter/system design and prototyping

Programme: TRP Reference: T203-005EP

Title: 150 krad power converter/system design and prototyping

Total Budget: 350

Objectives

Design and verify a 150 krad power converter and system compliant with JUICE mission requirements.

Description

In this study results from activities "Delta radiation characterisation of RH power EEE components" and "Survey of critical components for 150krad power converter/system design" are employed to design and verify power converters and systems compliant with mission requirements and radiation levels observed (150krad). The prototype shall be tested up to as a minimum 150krad and subsequently up to failure point.

Deliverables

DC-DC and voltage regulator design, design justification file, verification test plan, final report and hardware


2012



12

S/W Clause: NA Reference to T-8480

Page 6 of 76

ESTER


Front-end readout ASIC technology study and development test vehicles for front-end readout ASICS


Title: Front-end readout ASIC technology study and development test vehicles for front-end readout ASICS

Total Budget: 625

Objectives

Study to identify suitable technologies for front-end readout electronics for TID (Total Ionizing Dose), DD (Displacement Damage) and SEE environment of JUICE.

Description

The front-end readout electronics for the various sensors of the JUICE mission represent (with respect to radiation) a critical part of the mission. These parts are located close to sensors/detectors with associated increased radiation levels. This activity aims at surveying existing technologies employed in the space community and the nuclear / particle physics community to identify suitable technologies for the JUICE mission. The study shall identify and propose technologies most compliant with mission requirements and possible development requirement to bring technologies to the required level. Additionally, the availability of process for third party manufacturing, reliability, packaging and cost shall be important selection criteria.

Deliverables

Final report containing a technology selection list prioritised according to selection criteria. The final report shall in detail justify selection. Final report shall in conclusion propose a technology for further radiation and reliability characterisation.


2011



18


T-8480


N/A

Radiation characterisation of front-end readout ASIC


Title: Radiation characterisation of front-end readout ASIC

Total Budget: 350

Objectives

Reliability and radiation effects (TID and SEE) characterisation of selected front-end readout technology

Description

This activity aims at characterising front-end readout ASIC test vehicle developed under activity "Development of test vehicles for front-end readout ASIC" for reliability and TID / SEE effects in mission operational conditions and radiation levels. For the JUICE mission, requirements in terms of TID are 150krad behind 8mm of Al shielding. In particular, radiation induced degradation of the readout electronics shall be assessed and impact on science requirements identified.

Deliverables



2012



12


T-8480


N/A

Page 7 of 76

Radiation Tolerant analogue / mixed signal technology survey and test vehicle design


Title: Radiation Tolerant analogue / mixed signal technology survey and test vehicle design

Total Budget: 725

Objectives

Study to identify suitable analogue mixed signal technology for 150krad radiation tolerance mission requirement.

Description

A study to identify and select an analogue / mixed-signal process (e.g. SiGe) compliant with the mission 150krad requirement. The selected process shall be compliant with mission requirement in terms of functions and performance. Additionally, the availability of process for third party ASIC manufacturing, reliability, packaging and cost shall be important selection criteria.

Deliverables

Final report containing a technology selection list prioritised according to selection criteria. The final report shall in detail justify selection. Final report shall in conclusion propose a process for further radiation and reliability characterisation.


2011



18


T-8480


N/A

Radiation characterisation of RT analogue / mixed signal technology


Title: Radiation characterisation of RT analogue / mixed signal technology

Total Budget: 350

Objectives

Radiation characterization of test vehicles developed in analog and mixed signal process in order to identify suitability for 150krad mission requirement.

Description

Test vehicles and functions developed in activity T222-017QC "Analogue / mixed signal function / test vehicle design" shall in this activity be characterised for their radiation tolerance (TID, DD and SEE) and reliability performance.

Deliverables



2013



12


T-8480


N/A

DAREplus (Design Against Radiation Effects) ASICs for extremely rad hard & harsh environments


Title: DAREplus (Design Against Radiation Effects) ASICs for extremely rad hard & harsh environments

Total Budget: 1200

Objectives

To increase the maturity of the existing DARE 180 nm library for applications in harsh radiation environments (< 1 Mrad), and provide a suitable digital cell library and technology for SC and PL elements.

Description

During the course of this activity following steps shall be performed on the DARE 180 nm library:

Page 8 of 76

- Design of missing library elements (e.g. dual ported RAM compiler, LVDS I/O, 5V tolerant I/O pads, and others) - Creation of standard pad ring and package solutions. -Design, manufacture and evaluation (including irradiation characterisation) of test vehicle including all new library elements

Deliverables

DAREplus libraries / Design Kit , validated datahandling ASIC manufactured with DAREplus technology, irradiation test plan and reports


2013



18


T-8480


Microelectronics Dossier (1st semester 2007) - AIM A - Deep Submicron ASIC technologies (A1, A2, A8)

Latch up protection for COTS (Commercial, off-the-shelf) digital components


Title: Latch up protection for COTS (Commercial, off-the-shelf) digital components

Total Budget: 150

Objectives

Protection device to increase robustness against Latch-Ups of COTS digital electronic.

Description

COTS components typically follow the latest industry trends, and may become obsolete in just a few years. This is particularly true for memory chips that have market lifetime sometimes of less than one year. Space qualifying electronics is instead a rather lengthy and complex process. Detailed functional and performance test procedures must be developed to characterize the device during environmental testing. The required environmental testing typically includes vibration testing, thermal cycling and thermal vacuum testing, and radiation testing. In addition, a variety of engineering analyses must be completed as part of the acceptance data package. Hence, a very effective strategy for using COTS components in space is to use system-level mitigation techniques to complement the component-level mitigation techniques, to increase system level reusability of COTS modules. Examples of effective system-level techniques include: Error detection and correction (EDAC), Redundancy, Radiation-tolerant circuit designs, Distributed functionality, Fault protection systems. A possible fault protection system for digital parts can be built using COTS Current-Limited, High-Side P-Channel Switches with Thermal Shutdown. Those inexpensive and highly miniaturized switches operate with inputs from +2.7V to +5.5V, making them ideal for both 3V and 5V systems. Internal current-limiting circuitry protects the input supply against overload. Thermal-overload protection limits power dissipation and junction temperature. Current limit is adjustable with great precision and intervention time is on the order of few microseconds. This will be well suited to protect memories against burn out and they can be operated either with autorecovery (during an output short-circuit condition, the switch turns off and disconnects the input supply from the output, the current-limiting amplifier then slowly turns the switch on with the output current limited) or with software controlled recovery.

Deliverables

PFM Hardware


TRL5 by 2012



12


T-8480


N/A

Radiation characterisation of Laplace critical RH optocouplers, sensors and detectors


Title: Radiation characterisation of Laplace critical RH optocouplers, sensors and detectors

Total Budget: 900

Objectives

Page 9 of 76

Radiation characterization of radiation tolerant (minimum 150krad) optocouplers to identify suitability for JUICE mission.

Description

Optocouplers are sensitive to both DD (Displacement Damage) and TID (Total Ionizing Dose). Current radiation tolerant devices are typically tested to dose levels lower than JUICE requirements. Thus, this activity aims at selecting candidate radiation tolerant optocouplers and performing radiation tests on these (TID and DD) to JUICE levels (150krad behind 8mm of Al shielding).

Deliverables


Current TRL: 2/3 Target TRL: 4 Application Need/Date:

2011



12


T-8480


N/A

Radiation hard memory


Title: Radiation hard memory

Total Budget: 800

Objectives

Find, characterise radiation tolerance and assess reliability of memory devices to cover all cosmic vision project requirements (256+ Gbit, TID hard, SEL immunity, SEU, SEFI sensitivity that can be mitigated,..). This study will cover Cross scale and Dark Energy needs, and possibly JUICE (the feasibility to find 150 krad high density memories is still to be demonstrated)

Description

Continuation of Agency memory study to characterize SEE and TID (Total Ionizing Dose) effects in new technologies of high density memories (DDR3+, flash, nanotubes, FRAM, MRAM,..)

Deliverables



2012



36


T-8480


N/A

Qualification of radiation tolerant FLASH memory

Programme: CTP Reference: C223-056QE

Title: Qualification of radiation tolerant FLASH memory

Total Budget: 500

Objectives

NAND-Flash provides non-volatility and the highest storage density of today's semiconductor memory technologies. They also present a relative good tolerance to the space radiation environment. The objective of this activity will be to radiation qualify the next generation of FLASH memory and to secure the supply of memories for the needs of the JUICEmission.

Description

The radiation requirements for JUICE are quite severe, in particular for TID (total ionizing dose, > 150krad), but also SEE (single event effects). TID typically induces a progressive shift of the device characteristics and terminates in non-functionality at high dose. SEE is a random phenomenon, which can potentially induce transient or persistent Functional Interrupts (SEFIs), or latch-up or destruction. Both TID and SEE can have dramatic effects and should be carefully

Page 10 of 76

assessed. The radiation tests of the present generation of NAND Flash memories have shown that NAND Flash are more sensitive to TID than conventional present-day CMOS technologies, mainly because of the internal high voltage circuitry used for cell programming. The high voltage generator, as well as the state machine and all the periphery (register, address and data buffers) are also sensitive to SEFIs. Device destruction have also been observed but in extreme conditions and with a low probability for a space mission. The radiation study for the next generation of NAND-Flash will involve: 1. Selection and procurement of three types of NAND Flash memory candidates from the COTS market (Samsung, Micron, etc) 2. TID testing, investigation of dose rate effects, annealing, memory operation mode during irradiation, part to part variations 3. SEE testing, characterization of SEFIs and destructive events (if any), investigation of angle effects (from normal to grazing) 4. Analysis of radiation results for the JUICE mission, calculation of the in-flight SEE rates (depending on the mission phase). In particular, the TID results will be the bottleneck for the JUICE mission. The TID tests will focus on the device behavior as a function of the operation modes (storage, read, program). The influence of the dose rate and annealing, the part-to-part and lot-to-lot variations will be studied. A FLASH type will be selected in order to meet the mission requirements. One of the lessons learned from the previous and present radiation studies concerns the short lifetime of COTS components, especially in the competitive memory market. Technologies are rapidly evolving, and components are usually obsolete within 3 or 4 years. An important point of the study will be to rapidly select one preferred candidate among three types of NAND-Flash. This will be the objective of the first TID and SEE experiments. The selected candidate will then be purchased in large quantity for the JUICE applications. The following TID and SEE experiments will then concentrate on the selected candidate for an accurate prediction of the memory in-flight behaviour.

Deliverables

T0 + 6 months: Procurement of three types of NAND-Flash T0 + 12 months: Report 1, first TID experiments, T0 + 18 months: Report 2, first SEE experiments, procurement of the selected candidate in large quantity, T0 + 24 months: Report 3, second TID experiments on the selected candidate, T0 + 30 months: Report 4, second SEE experiments on the selected candidate, T0 + 36 months: Final Report, analysis and calculation of the failure rate for JUICE


2015



36



Radiation Effects on Sensors and Technologies for Cosmic Vision SCI Missions (REST-SIM)

Programme: TRP Reference: T204-009EE

Title: Radiation Effects on Sensors and Technologies for Cosmic Vision SCI Missions (REST-SIM)

Total Budget: 500

Objectives

To perform quantitative analyses of the susceptibility of CV payloads to high energy particle radiation and development of specific tools for radiation effects analysis based on Geant4, including greatly improved efficiency with geometry generation and exchange and analysis case definition for integrated use through all project phases.

Description

Many of the technologies proposed for the various Cosmic Vision mission candidates are highly susceptible to radiation-induced effects, including sensors, imaging devices, MEMS (DMDs), highly integrated payloads, cryogenics and other new technologies and mechanisms. Furthermore, some environments are very hazardous (e.g. Jupiter). Effects include radiation damage, background, charge noise, hot pixels, internal charging and activation. Evaluations and are needed for payload design, operation and data analysis. The Geant4 particle transport toolkit and its derivative tools have been successfully used in science mission and payload studies over the last decade.

Page 11 of 76

However, a recurrent problem in science studies is the difficulty of efficiently establishing and iterating (i) spacecraft/payload geometry and (ii) detailed science analysis definition (e.g. for sensors) in time for critical radiation analyses. The present activity aims to remove this problem for future missions by developing efficient front-ends for analysis application definition and geometry creation, and for import and export, so reducing the effort and making it feasible to do such work from the earliest phases of a project (e.g. in CDF) thorough stages of increasingly detailed geometry and application definition. Appropriate CV proposals will be used to define Geant4 strawman geometries and analyses capabilities for the proposed technologies and payloads. For testing and validation, the new capabilities will be applied to first-order radiation analyses of key technologies taking into account the representative mission profiles and radiation environments. The resulting simulation models will be easily amenable to extension and iteration to include refinements to the design, technologies, geometries and mission profiles, thus enabling a continuous and smooth improvement of radiation analyses over the entire mission design lifetime, reducing costly margins on the radiation levels. This approach is planned to extend to the flight of the chosen missions themselves and ultimately all the way to post-mission data analyses.

Deliverables

Detailed radiation effects analyses for all of the proposed Cosmic Vision missions and their technologies; advanced effects analysis and geometry modeling capabilities; strawman Geant4 geometry models of all of the Cosmic Vision mission spacecraft


2011



24

S/W Clause: Open source Reference to ESTER

T-8480


N/A

Evaluation of star tracker performance in high radiation environment

Programme: CTP Reference: C205-100EC

Title: Evaluation of star tracker performance in high radiation environment

Total Budget: 250

Objectives

Review particle environment and simulate effects on star tracker performance

Description

The Jovian environment has a high density of charged particles (mainly electrons). Despite heavy shielding, residual particle interactions with detectors will take place, and in addition secondary photon production will enhance background. It is expected that sensors will loose sensitivity due to a “snow” effect. This shall be simulated (either h/w or s/w) and the feasibility of using currently available star trackers shall be assessed.

Deliverables

Current TRL: NA Target TRL: NA Application Need/Date:

TRL5 by 2013



18



Page 12 of 76


IXO mirror module ruggedizing and environmental testing - Phase 1


Title: IXO mirror module ruggedizing and environmental testing - Phase 1

Total Budget: 1000

Objectives

To demonstrate the flight worthiness of Si x-ray pore optic modules for IXO

Description

- Modeling & analysis of stack adhesion forces. - Improvements to state of the art manufacturing of mirror modules to ensure compatibility with IXO environmental requirements, for instance annealing, contamination control within the limits of the available financial envelope (it is clear that a chip manufacturing type assembly line is coherent with the cleanliness requirements for stacking XEUS modules, but beyond the funding levels available from TRP), bracket/dowel pin modification including: * trade-off new materials compatible with integration (room temp) and operational temp., e.g. HB-Cesic, Si3N4, Si. * lightweighting * compatibility with integration into a petal and possible baffle mounts * compatibility with the requirements of IXO - Procurement of equipment upgrades and any necessary modification of the stacking robot, including for an innermost radii module. - Procurement of sufficient silicon plates and brackets to perform tests and stack modules with the discard of an overhead of plates, such that the stacks of the mirror module to be placed under environmental test are formed from virgin plates (i.e. plates that have not been stacked then separated). - Production of at least 3 (TBD) mirror modules (possibly of different radii), one module with coating compatible with IXO requirements (TBD). - Environmental testing at relevant facilities (mechanical, thermal) with x-ray testing of the modules pre and post each environmental test. - Planning for industrialisation of processes.

Deliverables

Analysis and modeling results. 3(TBD) IXO mirror modules of stacked silicon plates, at least one coated. Results of x-ray, mechanical and thermal testing. Industrialisation plans.


2010


ATHENA Contract Duration:

18


T-8453


N/A

IXO mirror module ruggedizing and environmental testing - Phase 2

Programme: CTP Reference: C216-006MM

Title: IXO mirror module ruggedizing and environmental testing - Phase 2

Total Budget: 1000

Objectives

To demonstrate the flight worthiness of Si x-ray pore optic modules for IXO

Description

- Modeling & analysis of stack adhesion forces. - Improvements to state of the art manufacturing of mirror modules to ensure compatibility with IXO environmental requirements, for instance annealing, contamination control within the limits of the available financial envelope , bracket/dowel pin modification including: * trade-off new materials compatible with integration (room temp) and operational temp., e.g. HB-Cesic, Si3N4, Si. * lightweighting * compatibility with integration into a petal and possible baffle mounts * compatibility with the requirements of IXO - Procurement of equipment upgrades and any necessary modification of the stacking robot, including for an innermost radii module. - Procurement of sufficient silicon plates and brackets to perform tests and stack modules with the discard of an overhead

Page 13 of 76

of plates, such that the stacks of the mirror module to be placed under environmental test are formed from virgin plates (i.e. plates that have not been stacked then separated). - Production of at least 3 (TBD) mirror modules (possibly of different radii), one module with coating compatible with IXO requirements (TBD). - Environmental testing at relevant facilities (mechanical, thermal) with x-ray testing of the modules pre and post each environmental test. - Planning for industrialisation of processes.

Deliverables

Analysis and modeling results. 3(TBD) IXO mirror modules of stacked silicon plates, at least one coated. Results of x-ray, mechanical and thermal testing. Industrialisation plans.


2013



18


T-8453


N/A

Development of IXO Si pore optics and mass production processes


Title: Development of IXO Si pore optics and mass production processes

Total Budget: 2000

Objectives

Development and improvement of automated manufacturing processes to demonstrate that required number of mirror modules can be manufactured in timescale and cost of IXO telescope. Installation of a 20 m robot, consistent with change from XEUS to IXO, with 20 m focal length baseline (robot currently 50 m, optics at 2 m radius).

Description

Elaboration of 2nd generation plate developments & further consideration of industrialisation for mass production, e.g. to reduce plate costs. Examples of issues to be addressed include (non-exhaustively) edge rounding (cleanliness and particle production), tapered ribs (blocking in conical approximation), alternative wedging processes, micro-roughness reduction on mirror/bond surfaces and increase on rib walls, introduction of plate identifiers and alternative bonding methods. Modifications necessary to the automated stacking process to address cleanliness levels. Where appropriate to the level of budget available, the analysis shall lead to procurement and installation of new equipment, for example a high power microscope and sub-micron particle detection system for ribbed plates. Installation of new robot for 20 m FL/ 0.7 m radius, based on existing 50 FL/ 2m radius robot, (new requirements of IXO), to demonstrate technology compatibility with IXO. Procurement Si plates & proof of new processes on samples to demonstrate improved processes (time, cost), compatible with producing bondable plates. Sample characterisation (e.g. SEM, x-ray characterisation, bonding tests). Analysis to show necessary number of mirror modules for IXO telescope can be built in relevant timescale, with appropriate yield (for instance 70-80%) and description of the manufacturing process that would achieve this in an industrial setting.

Deliverables

Design analysis & description of process improvements including estimated costs for installation. Installation of new equipment (where finance appropriate), to include stacking robot for 20 m focal length optics at ~0.7 m radius. Characterisation of samples that demonstrate new processes


2011



18


T-7959


N/A

Page 14 of 76

ATHENA Inner SPO Mirror Module


Title: ATHENA Inner SPO Mirror Module

Total Budget: 2600

Objectives

Development of an inner mirror module for the ATHENA telescope

Description

ATHENA requires silicon pore optics mirror modules (SPO MM) at a number of radial positions. The other main developments concentrate(d) on a middle/outer position, and this activity shall demonstrate the production of an inner mirror module (r about 0.25m TBC). The construction of such inner mirror modules require longer mirror plates, a modified mounting system, etc, and includes specifically a new dedicated robotic stacking system. Furthermore the manufacturing of inner mirror plates required the extension of the current mirror plate production processes. Within this activity, the contractor shall: 1) Analyse the present SPO manufacturing process and identify modifications required to produce SPO MM for inner radii. 2) Elaborate the detailed design for the required inner SPO MMs including the mounting system (brackets and dowel pins) 3) Perform optical modeling of inner radius mirror modules and identify performance limitations. 4) Perform mechanical and thermal modeling of inner radius mirror modules and identify performance limitations. The compatibility with the environmental requirements shall be analysed and assessed. 5) Elaborate the detailed design for the required stacking robot for manufacturing inner SPO MMs. This robot shall allow re-tooling for larger radii. 6) Elaborate the detailed design for upgrading the plate manufacturing process and equipment for the production of mirror plates suited for inner SPO MMs 7) Procure components, assemble and commission new stacking robot 8) Upgrade the mirror plate manufacturing process as required for the inner SPO MM 9) Manufacture mirror plates and SPO MM for inner radii 10) Perform pencil beam and full aperture X-ray tests of all produced stacks and SPO MM to characterise their performance.

Deliverables

Inner mirror module. Stacking robot. Technical Data Package.


2014



24


T-7959


N/A

ATHENA petal breadboard


Title: ATHENA petal breadboard

Total Budget: 2500

Objectives

To demonstrate by breadboarding the achievement of TRL 5 for a petal that meets the requirements for ATHENA

Description

- Detailed design, analysis and modeling of a petal to meet the requirements for ATHENA. - Specification of the alignment and mounting process to mount x-ray Si pore optic mirror modules into the petal using methods that allows their eventual removal and replacement. Procurement of all parts necessary, including suitable manufacturing margin, for petal, mirror modules and/or dummies manufacture and auxiliary equipment - Manufacture of a petal - Demonstration of the integration process of the mirror modules into the petal

Page 15 of 76

- Performance and environmental testing at suitable facilities.

Deliverables

Analysis and modeling results. ATHENA petal populated with TBD mirror modules and/or TBD dummies.


TRL 5 by 2015



24


T-8456


N/A

True Wolter Silicon Pore Optics and Improved Performance


Title: True Wolter Silicon Pore Optics and Improved Performance

Total Budget: 1100

Objectives

This activity shall demonstrate x-ray Silicon Pore Optics (SPO) with an angular resolution beyond the limit of a conical approximation of the Wolter I design. Therefore, SPO with parabolic and hyperbolic mirror surfaces shall be designed, manufactured and tested. By avoiding approximations, the corresponding contribution to the angular resolution shall be significantly reduced. The SPO shall be compliant with the mirror module requirements for ATHENA.

Description

The development of SPO technology, presently based on a conical approximation to the true Wolter I geometry, is approaching a resolution which mandates the move from the conical approximation to true Wolter 1 geometry. This will lead to a corresponding reduction in this contribution to the angular resolution. Preliminary experimental trials and analytical investigations have shown that true Wolter SPO can be manufactured. This activity shall implement the required modifications to the mirror module production equipment and produce a demonstrator mirror module. Within this activity, the contractor shall: 1) Analyse the present SPO manufacturing process and identify modifications required to produce true Wolter mirror modules. 2) Perform optical modeling of true Wolter mirror modules and identify performance limitations. 3) Elaborate the detailed design for upgrading the existing stacking robot for manufacturing true Wolter mirror modules 4) Elaborate the detailed design for upgrading the plate manufacturing process and equipment for the production of mirror plates suited for true Wolter mirror modules. 5) Procure, install and commission all new components for upgrading the stacking robot for manufacturing true Wolter mirror modules 6) Upgrade the mirror plate manufacturing process as required for the true Wolter SPO mirror modules 7) Manufacture mirror plates and mirror module with true Wolter mirror surfaces 8) Perform pencil beam and full aperture X-ray tests of all produced optics to characterise their performance.

Deliverables

Wolter silicon pore optics mirror module Stacking robot for Wolter mirror modules Optical model of a Wolter mirror module


2014



24


N/A


High Performance ATHENA SPO Mirror Module


Title: High Performance ATHENA SPO Mirror Module

Page 16 of 76

Total Budget: 1500

Objectives

This activity shall modify the existing stacking robot facility (currently 20m) to the ATHENA requirements (12 m focal length). The required modification to the mirror plate production equipment and processes shall be implemented. A high performance mirror module for the ATHENA focal length shall be produced and tested.

Description

The facilities used so far to demonstrate the compatibility with the environmental requirements and to optimise the performance for middle/outer mirror modules at 20m focal length shall be modified to the actual ATHENA focal length. This will also include the modifications required to the equipment for producing the mirror plates (e.g. shorter mirror plates required). The above facilities should also consider the eventual flight programme schedule requirements and their implication on the time critical production steps. The modified facilities shall be adequately tested and commissioned, involving the production of test mirror plates, mirror stacks and assembled mirror module(s). The optics shall be tested in X-rays at the ATHENA focal length.

Deliverables

High Performance ATHENA SPO Mirror Module Stacking robot for middle/outer ATHENA mirror modules


2015



24



Micropore Baffle (Tapered Plates Baffle For Silicon Pore Optics)


Title: Micropore Baffle (Tapered Plates Baffle For Silicon Pore Optics)

Total Budget: 400

Objectives

The objective of this activity is to design a baffle for IXO X-ray optics that will minimise straylight within the telescope field of view from continuous and discrete sources located inside or outside the field of view. The contractor will design, manufacture and test tapered silicon plates that meet the specifications.

Description

The main issues to be addressed in the activity will comprise: - Analysis and modeling to formulate the design of the tapered baffle; - Assessment of manufacturing processes, equipment and metrology; - Design & procurement (& modification) of manufacturing hardware and associated tools; - Procurement of materials and long lead items; - Production, coating and bonding of wedged plate samples and stacks of silicon pore-optics to parabolic approximation (based on the specification summarised in Annex A: Functional / Technical Specification); - Metrology of single plate and stacked plate samples using various techniques as appropriate during manufacturing; - Execution by the contractor of plate sample and stack characterisation, at x-ray test campaigns: - At least 2 campaigns on the fixed energy FEM beamline at the PTB laboratory of the Bessy synchrotron facility are foreseen for characterisation of deliverables during this contract: i) bare, tapered plate samples, ii) coated, tapered plate samples, iii) tapered baffle HPOs and iv) coated tapered baffle HPOs; - At least 1 campaign at an independent facility that the contractor shall provide, meeting the requirements in Annex A; - Evaluation of the imaging and baffling performance of an XOU, extrapolated from modeling, characterisation and engineering data and considering manufacturing through lifetime in the space environment, to assess the technology’s limitations as regards baffle length and dimensions; - Establishment of a technical development programme and identification of problem areas necessary to be tackled prior to a flight programme.

Deliverables

Technical data package including design, analysis, manufacturing and test results, summary report, x-ray optic units.


2011

Application ATHENA Contract 18

Page 17 of 76

Mission: Duration:



Baffled IXO mirror module


Title: Baffled IXO mirror module

Total Budget: 400

Objectives

To demonstrate flight worthiness of a baffle system for IXO Si x-ray pore optic modules

Description

- Procurement of all parts, including suitable margin on Si plates, for the manufacture of a baffled IXO Si x-ray pore optic module. - Manufacture and alignment of a baffled x-ray pore optic module to meet the requirements of IXO. - X-ray testing at plate, stack and mirror module level. - Environmental (mechanical and thermal) testing of the baffled x-ray pore optic with x-ray testing performed pre and post each environmental test.

Deliverables

Baffled x-ray pore optic module Results of x-ray, thermal and mechanical testing.


2011



12


T-7854


N/A

BessyII 12m Station


Title: BessyII 12m Station

Total Budget: 200

Objectives

Design and implement a measuring station at the ATHENA focal position (12m)

Description

This activity comprises the detailed design, production drawings, the procurements of the required parts and the assembly of the metrology station. The currently provided metrology stations (5m and 20m) shall remain available. The beamline with the new station shall be commissioned and tested to demonstrate the required performance. In addition a programmatic evaluation for the eventual flight model X-ray test facility at Bessy II shall be elaborated.

Deliverables

FCM beamline with 12m station User manual and detailed technical documentation


Q4 2013



12



Page 18 of 76

Panter X-ray test facilities upgrades


Title: Panter X-ray test facilities upgrades

Total Budget: 300

Objectives

Upgrade of the Panter x-ray test facility to be prepared for IXO (XEUS) focal length

Description

- The Panter test facility will undergo upgrades for the Simbol-X mission and during this facility downtime it must be ensured that the adaptations made are coherent also with the requirements of IXO (XEUS). Modifications with a new collimator and detector configuration are required to enable mirror modules and populated petals to be tested at the correct focal length. Thermal shrouds also need to be installed within the vacuum chamber. - Analysis of the testing requirements and modifications that will be introduced for Simbol-X and design of appropriate equipment installation to meet IXO (XEUS) testing requirements for mirror modules and populated petals. - Procurement, installation, calibration and test of the necessary equipment.

Deliverables

Equipment upgrades to Panter facility


Q4 2012



24


T-7959


N/A

Large area X-ray window development.


Title: Large area X-ray window development.

Total Budget: 350

Objectives

Development of large area, high performance X-ray windows.

Description

Recent GSTP development programme work has resulted in the improvement of low-energy X-ray response of small, membrane and grid supported X-ray windows. For X-ray astronomy missions there is a requirement for larger area windows with improved response. Currently available technology was developed more than a decade ago (as part of the Beppo Sax programme) and would benefit greatly from the application of recent small window work.

Deliverables

Characterised large area, high-transmission X-ray windows.


2013



24



N/A

Page 19 of 76


Metrology system for LISA

Programme: CTP Reference: C207-013PW

Title: Metrology system for LISA

Total Budget: 1000

Objectives

The objective is to characterise the Ultra Stable Oscillator (USO) residual noise, in order to achieve the required performance of the LISA system.

Description

In order to reach the required sensitivity, the LISA system relies on very accurate phase measurements and on a laser frequency noise suppression of several orders of magnitude. The laser frequency noise suppression is allocated to a cascade of (i) laser pre-stabilization, (ii) Arm Locking stabilization and (iii) Time-Delayed Interferometry (TDI). The residual noise suppression that can be achieved with Arm Locking and TDI depends principally on sampling-time jitter, delay, synchronization and time stamping of the phase measurements. The time reference for these tasks is set by the Frequency Distribution System (FDS), which includes an Ultra Stable Oscillator (USO) distributing time information throughout the data sampling and processing within the Phase Measurement System (PMS) and to the Laser Electro-optical Modulator (EOM). In order to achieve the required performance, the USO residual noise has to be characterized as well. Additionally, due to the LISA orbital evolution, the beat note to be measured does not have a constant frequency and consequently the Phase Measurement System (PMS) must be able to track a varying frequency within a range of about 20MHz. From the architectural point of view, because of the required redundancy level a fairly complicated switching system is required. This activity will demonstrate the LISA Phase Measurement System performance and validate the key interface requirements with the Frequency Distribution System. Tasks include design, manufacturing and test of the LISA PMS, with a reduced number of channels, but including redundancy and the a representative switching ability; design and implementation of a phase detection (laboratory standard quality) and clock noise determination algorithm; analysis and definition of the PMS FDS interface and correlation of performance.

Deliverables

Breadboard


2012


NGO Contract Duration:

18


T-663


N/A

LISA metrology system end-to-end characterization


Title: LISA metrology system end-to-end characterization

Total Budget: 1800

Objectives

To validate the actual end-to-end performance of the LISA metrology system in a "photons to bit" fashion.

Description

This activity will validate the requirements of the LISA measurement system and characterize the achievable performances. It will reproduce a LISA-like optical measurement set-up (that will use the LISA phasemetre developed in the frame of the separate "LISA metrology system" activity) to obtain the science(-like) parameters that are received on ground. The ground post processing will also be implemented and the end-to-end performance achieved eventually

Page 20 of 76

characterized.

Deliverables

A development model of the LISA measurement system.


2014


LISA Contract Duration:

18



High-power laser system for LISA


Title: High-power laser system for LISA

Total Budget: 3000

Objectives

The activity aims at developing and testing an Engineering Model of a Laser fulfilling the LISA requirements and ensuring that such a laser can be space qualified without further component, system, manufacturing or assembly processes technology development.

Description

The laser source in LISA has to meet stringent requirements in terms of output power, power stability, quality of light polarization, frequency noise, possibility to be stabilized to external frequency references and ability to modulate sidebands. A single-frequency CW laser with an EOL output power in the order of 1 to 2 W is required. The laser must also provide suitable actuator(s) - allowing a frequency stabilization with a tuning range of about 10GHz and a tuning speed in the order of 10GHz/1000s - and two modes of frequency actuation, slow (BW of 0.1Hz, dynamic range of 1GHz ) and fast (BW of 60kHz, dynamic range = 100MHz). To modulate the sidebands, the laser system must also include an embedded electro-optic phase modulator capable of a modulation index of 1 in broadband mode up to 8GHz and an optical isolator providing a minimum of 30dB isolation. The final scope of the activity is to develop and test an Engineering Model of a Laser fulfilling the LISA requirements and ensuring that such a laser can be space qualified without further component, system, manufacturing or assembly processes technology development. Tasks include consolidation of the achievable performance in the case of a high-power NPRO Nd:YAG laser and in that of low-power NPRO + fibre amplifier; analyses and testing in order clarify the technical issues leading to showstoppers; definition of the effort required to achieve qualification of the design; selection of the preferred laser architecture followed by the development of an Engineering Model and its testing.

Deliverables

Engineering Model


2012



24


T-722,T-726


N/A

Tunable laser frequency reference


Title: Tunable laser frequency reference

Total Budget: 1000

Objectives

To develop a tunable frequency reference for the LISA laser pre-stabilization.

Description

The activity focuses on the development of a stable reference to be used for laser frequency pre-stabilization.

Page 21 of 76

Conventionally, frequency references are fixed, whereas in LISA the arm-locking technique requires it to be tunable in order to follow the changes in the laser frequency caused by the breathing of the arm-length (the Doppler frequency shift). Such changeable reference can be achieved in several ways: either by modifying the length of an optical cavity or by using an adjustable sideband to the laser carrier for stabilisation or by other means. This activity will investigate the optimal way of implementing a variable frequency reference for LISA and will implement and validate it.

Deliverables

A development model of the laser frequency stabilization system that includes the tunable reference.


2013



18


T-7946


LISA Optical Assembly Articulation Mechanism (OAAM)


Title: LISA Optical Assembly Articulation Mechanism (OAAM)

Total Budget: 1000

Objectives

To design and bread-board an articulation mechanism for LISA that copes with the constellation breathing.

Description

In LISA the ideal equilateral triangle formed by the 3 SC will be changing due to the orbits kinematics, thus the relative angle between the adjacent LISA arms will slowly change of about 1.5 degree over 1 year. This is referred to as "constellation breathing". This variation cannot be compensated within the Optical Bench/telescope optical layout and a dedicated articulation mechanism for the active control of the LISA optical line of sight is needed. The slow variation, the relatively large angle and the fact that the noise of this articulation mechanism enters in the LISA performances through the overall Drag Free control impose conflicting requirements such as long stroke, high resolution and high stability to the mechanism, making the design very challenging. This activity will include an analysis phase with trade-offs of the potential design alternatives and an analysis of the apportionment of tasks between optics and mechanism. This will then be followed by the development of a bread-board to demonstrate the feasibility and performances of such articulation mechanism, including its locking mechanism needed to withstand the launch loads.

Deliverables

A bread-board of the OAAM


2012



18



Opto-mechanical stability characterization for LISA


Title: Opto-mechanical stability characterization for LISA

Total Budget: 2400

Objectives

The activity aims at reducing the risks linked to the current LISA optical system performance.

Description

The performance of the current LISA optical system is not evaluated in the classical terms of image quality, but in terms of phase distortion. Some of the parameters enter directly in the LISA performance budget and therefore the analysis, design, implementation and characterization of a representative breadboard including the components that play a direct role in the stability (e.g. the telescope M1 and M2 mirrors and their supporting structure) is a required activity in terms of

Page 22 of 76

risk reduction. The areas covered by this activity are: - Opto-mechanical assembly (M1-M2 and supporting structure) absolute distance and alignment stability characterization when passing from ground condition to flight condition; assessment of predictable structural distortions; capability to correctly focus the optical system in space; - Design, manufacturing and test of a measurement system (Optical Truss) capable to measure the inter-mirror distance (IMD) stability to the required picometre level - Opto-mechanical assembly stability verification in representative flight condition. The pathlength error associated with this noise term appears twice, as the light travels between M1 and M2 twice. Thus picometre level fluctuations in the inter-mirror distance (IMD) are significant in the overall LISA pathlength error budget. Tasks include design of the LISA opto-mechanical assembly and test plan definition, design of a test set-up suitable for the characterization of the identified opto-mechanical assembly critical performance, development of the LISA opto-mechanical assembly breadboard and test set-up, opto-mechanical assembly testing and analysis of test results.

Deliverables

Breadboard


2012



24


T-7875


N/A

LISA Inertial Sensor final design


Title: LISA Inertial Sensor final design

Total Budget: 1200

Objectives

To optimize the LISA Pathfinder (LPF) Inertial Sensor design for compatibility with the LISA architecture.

Description

Some modifications to the Inertial Sensor design are required, with respect to the original LISA Pathfinder design, in order to cope with the different mission characteristics and mechanical design. Due to the LISA longer lifetime, venting to vacuum is unavoidable, hence a modification to the vacuum system in order to accommodate this feature is required; the design of a new mechanical interface with different mounting flanges is also necessary, due to the difference of the LISA Optical Assembly with respect to that of the LPF. Additionally, an optical read-out for the Proof Mass -y and -z axes may be implemented as a risk reduction measure

Deliverables

A development model of the modified LPF Inertial Sensor


2014



12



GRS Front End Electronics characterization for LISA


Title: GRS Front End Electronics characterization for LISA

Total Budget: 1450

Objectives

To validate and optimize the Inertial Sensor (GRS) Front End Electronics system, originally developed for the LISA Pathfinder mission, for LISA

Page 23 of 76

Description

LISA needs a residual acceleration a factor 10 better than LPF in a frequency range that extends to 10-4 Hz, compared to the 3 x 10-3 Hz of the LPF requirement. The FEE, despite fulfilling the LPF requirements, falls short in a few of the LISA requirements, such as the actuation noise. This activity will entail targeted investigations on individual FEE components such as: >20 bit ADC and DAC, reference voltage sources and auto-zero amplifiers, in order to identify design improvements leading to the fulfillment of the LISA specification, both in noise and in frequency. The investigation will also address the optimization of the redundancy concept.

Deliverables

A development model for the Inertial Sensor FEE.


2012



24


T-698


N/A

Charge Management System for LISA


Title: Charge Management System for LISA

Total Budget: 900

Objectives

The objective of the activity is to investigate the possibility to use LEDs for the LISA Charge Management System (CMS).

Description

The current LISA Pathfinder Charge Management System (CMS) is based on UV mercury-vapour lamps. The design of this system is based on the ROSAT and GPB missions, launched respectively in 1990 and 2004. An alternative design for the LISA CMS could be based on Light Emitting Diodes (LED). Compared with mercury lamps, the LED-based CMS offers the advantages of small size, lightweight, lower power consumption, faster response time and longer lifetime. Lifetime in particular is the main disadvantage of the Mercury lamps in the LISA application, as the CMS would require a substantial mass and volume to guarantee the 5-year mission duration with the required redundancy. This activity would therefore investigate the possibility to use LEDs for the LISA CMS, design the system and manufacture a breadboard to be adequately tested.

Deliverables

Breadboard


2013



24


T-7945


N/A

Compact low noise magnetic gradiometer

Programme: CTP Reference: C207-010EE

Title: Compact low noise magnetic gradiometer

Total Budget: 600

Objectives

Design and prototyping of a low noise miniature magnetic gradiometer

Description

Inertial Sensor payloads (LISA) are susceptible to magnetically induced force noise. Their performances (i.e. sensitivity) drive new and challenging requirements for the overall system, whose verification is nowadays affected by instrumentation limitations. Hence new instrumentation for testing (i.e. gradiometer) is needed to achieve testing under

Page 24 of 76

realistic conditions and enhance the significance of the test results. The main need is to measure highly non-dipolar magnetic field gradients and their fluctuations down to sub-mHz frequencies and possibly lower, inside enclosures where little room is available. Compact and sensitive gradiometers would also be valuable tools for CV1525 missions requiring magnetic cleanliness, to be used in complement or instead of dedicated test facilities. Existing fluxgate gradiometers have either too long baselines or limited sensitivity or can measure only one gradient component. The idea is to design an innovative and affordable compact gradiometer capable of measuring 3 to 5 independent components of the 3x3 gradient matrix. This activity will entail the following: (i) Study of existing sensor technologies (e.g. micro-fluxgate) and of signal processing and noise reduction techniques (ii) Technology selection (iii) Gradiometer design (iv) Breadboarding (v) Calibration and performance testing

Deliverables

Technical notes with theoretical findings and gradiometer design; Prototype; Report with calibration and performance test results.


2011



24



Consistent with EMC Dossier

Outgassing and Contamination characterization for LISA


Title: Outgassing and Contamination characterization for LISA

Total Budget: 900

Objectives

The main objective is to verify the outgassing and contamination characteristics of the materials used in the Opto-mechanical payload compartment to assure the ultra-high vacuum level required by the pay-load

Description

The LISA Payload is characterized by strict requirements on vacuum and contamination. The outgassing and contamination characteristics of the materials used in the Opto-mechanical payload compartment (e.g. CFRP, Zerodur, bonding materials, electrical and optical harness) have to be determined in order for the payload to be able to reach the ultra-high vacuum level required and to make sure that the cold telescope optical surfaces and the Optical Bench components will not be contaminated. Additionally, also the contamination characteristics of the micropropulsion plume must be determined in the frame of this activity. Finally, the technology necessary to implement venting of the GRS vacuum enclosure into space (feature not implemented in LPF) has to be identified and fully analysed.

Deliverables

Breadboard


2013



24


T-8391


N/A

Page 25 of 76

LISA micropropulsion lifetime characterization


Title: LISA micropropulsion lifetime characterization

Total Budget: 1900

Objectives

To demonstrate that the FEEPs can withstand the LISA lifetime requirement and are thus suitable to accomplish the LISA mission.

Description

To-date all activities in the micro-propulsion area are focused in demonstrating the performance for Microscope and LISA Pathfinder. The LISA Pathfinder specification covers also LISA requirements, with the exception of the mission lifetime. This activity will therefore verify all micropropulsion system design features that are impacted by lifetime, assess whether any design modification is required and perform the characterization of the micropropulsion system according to the LISA lifetime requirements. At the time of completion of this activity, the micropropulsion system will have been flight-tested on LPF except for lifetime that will have been verified on ground.

Deliverables

A FEEPs cluster fully characterized for lifetime


2013



36


T-1013


N/A

Optical Bench Development for LISA


Title: Optical Bench Development for LISA

Total Budget: 1850

Objectives

The production of a BB of the LISA Optical Bench, including the relevant fiber switching mechanism(s). This BB shall also serve for alignment and alignment verification, for stray-light tests and for interferometer performance assessment.

Description

The current baseline for the LISA optical bench design is based on polarized Mach Zehnder interferometers, as opposed to the LISA Pathfinder (LPF) that adopts a non-polarized scheme. This activity will include a trade of polarized vs. non-polarized optics with the aim of identifying the most suitable approach for the LISA architecture. The optical behaviour of polarizing optical components is known to be a function of the thermal gradient in the component, mechanical stress and wavelength. The direct applicability of the hydroxy-catalysis bonding technique developed for LPF to the polarising optical elements will subsequently be verified for the selected approach. The LISA optical bench system will also accommodate the mechanism(s) used for redundant laser fibre switching and backfibre switching; the performance of such mechanism(s) in term of stability and noise directly affects the scientific measurement and could severely contaminate the LISA performance. The activity will also include the design, manufacturing and testing of an elegant BB of such mechanism(s). Output of the activity will be the trade-off, the design validation by analytical work and simulation and the production of a BB of the LISA Optical Bench, including the relevant fiber switching mechanism(s). This BB shall also serve for alignment and alignment verification, for stray-light tests and for interferometer performance assessment.

Deliverables

BB of the LISA Optical Bench


2011



24



N/A

Page 26 of 76


Near Earth Space Research X/X/K-Band Transponder Engineering Model

Programme: CTP Reference: C206-005ET

Title: Near Earth Space Research X/X/K-Band Transponder Engineering Model

Total Budget: 1000

Objectives

This activity is related to the development of an X/X/K-band Transponder EM for Near Earth Space Research missions which will require the use of the 26 GHz K-band frequency band allocation for high data rate downlinks.

Description

The main technical issue for this transponder is the use of high data rates in K band (26 GHz) for the telemetry down-link. At present the X/X transponder, as developed for the ESA mission Gaia, is limited to a maximum data rate of 10 Mbps. The use of K-band will provide the possibility to increase the scientific data return for this kind of Near Earth Space Research mission in the future. It is envisaged that the EM Transponder will be able to support TC uplink data rates of up to 512 kbps and TM data downlink rates of up to 150 Mbps, using either OQPSK or GMSK modulation formats. NASA already have developments on-going for the Lunar Reconnaissance Orbiter and the James Webb Space Telescope (JWST) in K-band.

Deliverables

An Engineering Model of the X/X/K-band TRSP and the End Item Data Pack


2012


EUCLID Contract Duration:

24

S/W Clause: Operational SW Reference to ESTER

T-8489


Harmonisation dossier for TT&C transponder and Payload Data Transmitters (April 2008, Issue 2, revision 2) - Consistent - Activity B09: Near Earth X/X/K-band Transponder for the 26GHz frequency band: Development of an Engineering Model

Delta Development of Cold Gas Propulsion for Euclid

Programme: CTP Reference: C219-001MP

Title: Delta Development of Cold Gas Propulsion for Euclid

Total Budget: 500

Objectives

Delta development of existing GAIA cold gas propulsion system to augment the thrust range to meet the EUCLID requirements, and to remove ITAR restricted items from the pressure regulator stage.

Description

The EUCLID CDF study identified the need for a proportional control cold gas propulsion system capable of throttling over a range of 2 microN to 2 mN (ie. three orders of magnitude). The existing state of the art is the GAIA system which is designed for a throttling range of 1 - 500 microN. In addition to the need to augment the throttling range, the GAIA system includes ITAR restricted components within the pressure regulator module. Replacement of these components with ITAR free equivalents will require some additional design definition and development activity. This activity will lead to the development and test of an Engineering Model thruster units, meeting the enlarged throttling range requirement, including representative environmental testing (TRL 5). The activity shall include the design definition of a pressure regulation module utilising non-ITAR components, including a detailed assessment of qualification status of the components and identification of any outstanding qualification needs. The activity shall consist of the following main tasks: 1. Review EUCLID propulsion requirements, and define detailed requirements for baseline design. 2. Modify thruster design to augment thrust range to meet EUCLID requirements. 3. Modify pressure regulator design to incorporate ITAR free components. 4. Manufacture, assembly, integration and test of an EM thruster unit. 5. Test data analysis, reporting and qualification planning for thruster and pressure regulator modules.

Deliverables

Hardware: EM Thruster (with augmented thrust range). Documents: Requirement specifications, design files, manufacturing history records, test plans and procedures, test

Page 27 of 76

report, qualification plan, summary report and abstract.


2012



18


T-7979


Aim A9 : High Performance Chemical Micro-thrusters

Delta Development of Cold Gas Propulsion for Euclid

Programme: CTP Reference: C219-001MP-B

Title: Delta Development of Cold Gas Propulsion for Euclid

Total Budget: 500

Objectives

Delta development of existing GAIA cold gas propulsion system to augment the thrust range to meet the EUCLID requirements, and to remove ITAR restricted items from the pressure regulator stage.

Description

The EUCLID CDF study identified the need for a proportional control cold gas propulsion system capable of throttling over a range of 2 microN to 2 mN (ie. three orders of magnitude). The existing state of the art is the GAIA system which is designed for a throttling range of 1 - 500 microN. In addition to the need to augment the throttling range, the GAIA system includes ITAR restricted components within the pressure regulator module. Replacement of these components with ITAR free equivalents will require some additional design definition and development activity. This activity will lead to the development and test of an Engineering Model thruster units, meeting the enlarged throttling range requirement, including representative environmental testing (TRL 5). The activity shall include the design definition of a pressure regulation module utilising non-ITAR components, including a detailed assessment of qualification status of the components and identification of any outstanding qualification needs. The activity shall consist of the following main tasks: 1. Review EUCLID propulsion requirements, and define detailed requirements for baseline design. 2. Modify thruster design to augment thrust range to meet EUCLID requirements. 3. Modify pressure regulator design to incorporate ITAR free components. 4. Manufacture, assembly, integration and test of an EM thruster unit. 5. Test data analysis, reporting and qualification planning for thruster and pressure regulator modules.

Deliverables

Hardware: EM Thruster (with augmented thrust range). Documents: Requirement specifications, design files, manufacturing history records, test plans and procedures, test report, qualification plan, summary report and abstract.


2012



18


T-7979


Aim A9 : High Performance Chemical Micro-thrusters

Euclid CCD Pre-Development


Title: Euclid CCD Pre-Development

Total Budget: 2000

Objectives

Acquire prototype CCD design to optimize performance for Euclid

Description

The detailed geometry of the CCD203 family CCD sensor must be modified to enhance the performance aspects of radiation resistance and MTF uniformity. Charge Transfer Efficiency (CTE) after reference dose of 4x109 protons cm-2 (10MeV equivalent) should be >0.9999. CCD active depth of >40 um shall be considered to achieve acceptable long

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wavelength efficiency and a MTF that is comparable in orthogonal directions. CCD designs will be based on CCD203/CCD204 (already used in a test activity during Euclid assessment phase). Modifications are envisaged for charge injection structures, transfer channel width and array aspect ratio for minimal transfers, all of which have been demonstrated on other devices. Packaging (very likely based on SiC material) issues shall be addressed in order to meet the very stringent thermo elastic requirements existing for Euclid. Proposed activities: - Review results of CCD204 radiation tests. - Determine maximum transfer length for CCD arrays. - Define minimum silicon resistivity requirements for red response and MTF. - Design and procure modified CCD203/204 photolithographic masks. - Test of new structures on engineering batches (e.g. test the injection register on a non-Euclid batch .....) - Procure silicon wafers. Fabricate prototype devices. - Design, procure and assemble dedicated package (SiC TBC). - Assemble and test prototype devices. - Investigate optimum charge injection schemes. - Detailed MTF/spot/extended objects tests to validate the concept with respect to the Euclid performances. - Radiation test prototype devices. - Elaborate a test programme and manufacturing plan for flight model phase

Deliverables

Prototype CCD detector with 4-side buttable architecture and dedicated package

Current TRL: 3/4 Target TRL: 4/5 Application Need/Date:

2011


Euclid Contract Duration:

18



N/A

Euclid CCD radiation testing


Title: Euclid CCD radiation testing

Total Budget: 500

Objectives

The Euclid CCDs (CCD273, E2V) are currently in the pre-development phase. The CCD273 is largely based on the CCD203-82, whose performances and degradation under proton irradiation have been studied in a previous activity. This previous test activity has led to a significant improvement of the knowledge of the device but a large additional effort is needed to improve trap characterization and to provide representative imaging conditions (extended object) for direct comparison with models.

Description

The activity shall: - perform measurements (EPER, FPER...) on existing irradiated and newly irradiated devices (cold and warm) to improve trap characterization - perform optimization of the charge injection operation within the constraints of Euclid - setup a test bench enabling the illumination of the CCD with representative science scenes (point source, extended objects, different magnitudes...) - perform measurements with the above mentioned bench on irradiated and non-irradiated devices to assess the impact on the ellipticity measurement for Euclid (similar approach than the measurements performed on GAIA) - perform modeling of the effect and propose correction method(s) with corresponding validation - provide recommendations on future CCD test and simulations activities

Deliverables

Reports


2011


Euclid Contract Duration:

12



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Dichroic for Euclid

Programme: TRP Reference: T216-101PA

Title: Dichroic for Euclid

Total Budget: 300

Objectives

Development of a dichroic to split visible and infrared light (@ 920 nm) for Euclid telescope

Description

The dichroic for Euclid telescope is a critical components whose feasibility has caused some concern because of the large size required (> 100 mm in diameter), the requirements on efficiency and wavefront error of the reflected light together with the low temperatures (~150 K) at which it will have to work. The concerns are not only the feasibility of the coating but also the effect of the mechanical holder on the final image quality. Development of both dichroic coating and mechanical holder and test of the performance at low temperatures is required.

Deliverables

Plane parallel plate mounted on mechanical holder and containing dichroic coating


2011



9



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Materials Selection and Testing

Programme: TRP Reference: T221-108QT

Title: Materials Selection and Testing

Total Budget: 500

Objectives

The verification of material characteristics and their degradation after exposure to simulated Solar Orbiter environment

Description

Descritpion: This activity builds on the existing and planned materials activities for Phoibos and BepiColombo. The current ITT for Phoibos is open and includes the selection, sample procurement and testing of mostly ceramic-based materials. In the case of Solar Orbiter, the investigation and selection of candidate materials has been already conducted. The present activity adds the identified Solar Orbiter candidate materials to those to be dealt with under the Phoibos Tasks 4, 5 and 6: test plan, sample procurement, test execution and evaluation of results. With respect to BepiColombo, the materials investigated have been primarily fabrics used as part of high temperature MLI, like Nextel, and Titanium for the HGA. The range of temperatures for BepiColombo does not exceed 300°C and therefore the characterisation has to be performed up to the higher temperatures relevant to Solar Orbiter. The present activity, in the form of a CCN to the currently planned Phoibos work, includes the following activities as per document reference SD-PL-AI-0221: - procurement of candidate materials for heat shield and feedthroughs assembly - preparation and execution of screening and ageing tests including combinations of high T + UV + particles, verification of thermo-optical properties at high T, outgassing characterisation, and characterisation of mechanical & electrical properties

Deliverables

Test plans, test reports and used samples


2011


Solar Orbiter Contract Duration:

18



High Intensity High Temperature Solar Generator Study

Programme: TRP Reference: T203-111EP

Title: High Intensity High Temperature Solar Generator Study

Total Budget: 250

Objectives

To devise two alternative Solar Generator configurations concept based on Bepi Colombo state-of-the-art SA technology and Solar Orbiter constraints

Description

The activity consists of a first analysis of the latest information from Bepi Colombo on SA technology against the Solar Orbiter specific requirements and constraints. This will be followed by a design task to provide at least two alternative SA configurations compliant with the Solar Orbiter mission. For each configuration, a risk assessment shall be performed followed by a definition of screening tests to validate local design aspects, and a development & design definition plan for Solar Cells Assemblies.

Deliverables

Analysis report, Design report, Risk analysis report, Input to Screening Test Plan, Input to Solar Cell Assembly Development Plan, Identification of test facilities

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2011



9



Small high flux test facilities

Programme: CTP Reference: C204-107TC

Title: Small high flux test facilities

Total Budget: 200

Objectives

To upgrade an existing high flux small facility based on lamps in order to perform measurements on small elements or samples.

Description

To perform environmental testing on equipments and samples, a Thermal Vacuum chamber called VTC1.5 is being adapted at ESTEC. The Agency intends to fit this facility with a high power sun simulator to test samples at a very high level of irradiance (up to 20 Solar Constants). The solar simulator flux would be generated using high pressure Xenon short arc discharge lamps that have a light spectrum similar to the sun spectrum outside of the atmosphere. An existing LSS lamp module operated with a 32kW lamp would illuminate the test object through an existing 1m-diameter LSS spare window. The objective of the work is to design, procure and install components that combined to the existing elements would make a new sun simulator for the Thermal vacuum chamber VTC1.5. Several items are already available at ESTEC and will be re- used for this system: - the VTC 1.5 vacuum chamber; - the 1m-diameter optical window currently available as LSS spare window; - the lamp module including the primary reflector and electrical gear to strike the lamp; - the lamp module trolley; - the electrical rectifier to feed power to the Xenon lamp and control the lamp module; - the high pressure cooling water system; - the Nitrogen gas supply. The components which are subject of this contract are the window holder, the mechanical housing connecting the window to the lamp module, the fluids and the lamp supply electrical connections. This activity also includes the commissioning of the complete assembled sun simulator following installation on the facility at ESTEC.

Deliverables

Design report, upgrade plan, upgraded facility, verification report


Ready 2011



6



Solar concentrator test facility upgrade study

Programme: TRP Reference: T204-110TC

Title: Solar concentrator test facility upgrade study

Total Budget: 100

Objectives

To investigate the necessary modifications on existing solar concentrator facilities to accommodate high solar flux tests

Description

Descritpion: The activity will investigate existing solar concentrator facilities with the aim to identify the necessary upgrades to provide test capabilities suitable for Solar Orbiter. As such, the activity will address the testing needs for the following test objects: .. Materials samples .. Small objects .. Breadboards up to 50 cm .. Heat shield model (2.5m x 2.5m) The output of this activity will be the findings of the investigation, the performances to be

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achieved, a detailed list of the necessary procurements, and a roadmap to the implementation of the upgrades. N.B. The LSS facility is not contemplated in this activity; however the Test Centre will start an investigation to understand the actual design limits of the LSS in terms of maximum solar flux capability.

Deliverables

Assessment report


Ready 2011



6



Methodology for high solar flux testing acceleration. Explicitly address combined UV/thermal and accelerated testing, and existing BC facilities.

Programme: TRP Reference: T204-109QE

Title: Methodology for high solar flux testing acceleration. Explicitly address combined UV/thermal and accelerated testing, and existing BC facilities.

Total Budget: 200

Objectives

Define testing and combined test methodologies for all Solar Orbiter S/C components, materials and sub-systems exposed to high solar flux during the mission. Identify test facilities in Europe and the needed upgrades, to be compatible with the Solar Orbiter project needs and schedule. Define testing and combined test methodologies for all Solar Orbiter S/C components, materials and sub-systems exposed to high solar flux during the mission. Identify test facilities in Europe and the needed upgrades, to be compatible with the Solar Orbiter project needs and schedule.

Description

The activity shall define which tests and combined tests (i.e. UV Exposure/Thermal) are required to be carried-out on the different baseline (& candidate) Solar Orbiter S/C components, materials and subsystems (excluding the sun shield) that are directly exposed to high solar fluxes (i.e. 20 Solar Constants), to verify their integrity for the complete mission duration (i.e. 300000 hours). The activity does not aim to define the final test conditions and acceptable test acceleration factors to be applied during qualification of those items, as they are in the preliminary design phase. However, the activity shall provide which are presently the acceptable acceleration factors that can be applied for each of the required tests and baseline items. It shall also indicate in which areas a more deep study needs to be carried out to increase those acceleration factors, in case critical items need to be verified for the complete mission duration. The activity output shall also indicate on which areas only confidence tests can be performed, because acceleration tests are limited and full test duration is not feasible because of project schedule constrains. Finally the activity shall define the facilities and facility upgrades (taking as reference the present Bepi Colombo facilities) needed to perform on time (acc. to the Solar Orbiter mission schedule) the required high solar fluxes tests as defined in this study.

Deliverables

Study report and facilities upgrading plan


2011



6



Heat rejecting entrance window


Title: Heat rejecting entrance window

Total Budget: 300

Objectives

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To advance the filter development by improving the WFE, ground cycle life and mounting configuration, as well as to analyse the effect of the currently expected worst case thermal scenarios

Description

The proposed activity builds on the positive results obtained with the Heat Rejecting Entrance Window contract conducted over 2006-2008. Such development work is relevant to the technology needed by missions in a high solar flux environment or with a need for narrow band filtering of the incoming light. It consists of the following: a)IR-Shield coating ground cycle life improvement, to withstand 30 air/vacuum/heating/air cycles. The following aspects shall be evaluated: - coating layer stress analysis - alternative coating design with different materials and lower coating stress - alternative coating procedure (combination of sputtering and e-beam evaporation) - Other possible approaches. For each proposed coating solution 10 samples shall be submitted to the cycling test. b)Refurbishment of current Window_2 to investigate the Wave Front Error non-compliance. This will include an investigation of the mirror impact (WFE of the substrate surfaces before coating), of the bi-metallic bending of the coatings #3 and #4, and of the mounting impact on the WFE. c)Polarization dependency and retardance non-compliance investigation. This activity will include a verification by test of the improved #3 and #4 coatings. d)Thermal Analysis. A new thermal analysis will be done to examine the effect of having the shield partially shading the outer edge of the filter as well as the mount. In addition the failure case off-pointing scenario, as well as the worst case non-operational cold case, will be examined to determine the survivability of the filter and mount. e)Two New Breadboards, with Clear Apertures of Ø 162mm and Ø 86mm, will be constructed for both the VIM High Resolution Telescope and Full Disk Telescope. This activity will include the design of a new mounting structure with a reduced diameter, in order to be able to mount these two filters next to each other, as well as the Structural Analysis, Hardware realization, Coating realization and Coating acceptance tests.

Deliverables

BB with clear aperture of Ø 162mm BB with clear aperture of Ø 86mm all IR-Shield coating test samples Window_2 WFE Characterization report IR-Shield coating optimization report Polarization Test Result Thermal Analysis Report Structural Analysis Report


2011



12



High Flux Sun Sensor/Sun Filters

Programme: CTP Reference: C205-001PS

Title: High Flux Sun Sensor/Sun Filters

Total Budget: 400

Objectives

To design and develop a sun blocking filter for a sun sensor for the Solar Orbiter environment according to Solar Orbiter AOCS requirements

Description

The AOCS of SOLO is required to be very robust, mainly due the fact that a large off-pointing from the sun direction might cause mission failure because of the extreme solar flux. The sun sensors would therefore in particular be needed for safe or survival mode and thus it might be one of two type of sensors used in a hardwired FDIR approach. The sun sensor would need to be compatible with the environment at both 0.22 AU and at 1.5 AU implying a very large

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dynamic range. As development of a sun sensor sustaining directly the required sun flux would be very technological demanding the approach would be to have a sun sensor located behind a filter that would limit a large portion of the heat. If BepiColombo sun sensors are used the filter would need to reject at least 50 % of the incoming heat at 0.22 AU. As the sun sensors will ensure that the pointing of the spacecraft never exceeds the maximum angle the sun sensor would have to have an accuracy of better than 1 degree. Suitable filter material needs to be identified together with a suitable sun sensor covering the large dynamic range. An overall design of the whole sun sensor system (filter + sensor) is required in order to verify that the thermal constraints and requirements are respected.

Deliverables

Tested filter and overall design of integrated filter/sun sensor


2011



12



N/A

Validation of Liquid Crystal Variable Retarder for the Solar Orbiter Polarisation Modulation Package (previous title: Solo - Polarisation Modulation Package LCVR)

Programme: CTP Reference: C216-114PS

Title: Validation of Liquid Crystal Variable Retarder for the Solar Orbiter Polarisation Modulation Package (previous title: Solo - Polarisation Modulation Package LCVR)

Total Budget: 250

Objectives

To validate the use of Liquid Crystal Variable Retarder (LCVR) for the Polarisation Modulation Package (PMP) to be used in Solar Orbiter Instrumentation.

Description

The role of the Polarisation Modulation Package (PMP) is to select 4 independent input polarisation states for the VIM: the vertical, the horizontal, the left circular and the right circular polarisation states. Two PMPs are used in the VIM, one for the High Resolution Telescope (HRT) and the one for the Full Disc Telescope (FDT). The METIS will also use the same PMP. The clear aperture of the LCVR must be compatible with a 50 mm diameter optical beam. The main tasks of the validation program for the PMP are: - Make a trade-off between the different options proposed for the PMP (it is assumed that the qualification of the LCVR at component level to withstand Solar Orbiter environment has already been performed in a preliminary technological program) - Make a detailed design of the PMP package breadboard including the optics, the barrels, the oven with the active thermal control, the electrical interfaces - Manufacturing of the parts - Assembly of the PMP - Performance tests - Environment tests (Mechanical, thermal vacuum, radiation) then control performance tests

Deliverables

BB of the PMP


2011



14



N/A

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SPICA Telescope focusing mechanism for secondary mirror - Phase 1


Title: SPICA Telescope focusing mechanism for secondary mirror - Phase 1

Total Budget: 250

Objectives

Design, development and test of an EM of the M2 focusing mechanism so as to increase the technology readiness to level 5 with fully representative SPICA requirements and environment.

Description

The demanding WFE requirements (diffraction limited performance at 5 um, WFE < 350 nm)and the cryogenic operating temperature (5K) applicable to the SPICA telescope require the adoption of an M2 focusing mechanism to mitigate the risks associated to thermoelastic/manufacturing/ageing effects (also considering the complexity of performing ground tests at the nominal operating temperature and the hot launch conditions). The main functions of the M2 mechanism are: - Support and secure M2 during launch (without power), - Provide 3 DoF correction (focus and tip/tilt) on ground and in orbit, - Maintain stable position without need for power when in orbit. The driving performance requirements are: - Operating temperature 4.5 K (capability to operate at higher temperature 300K for on ground testing), - M2 mirror size: ~ 700 mm diameter, - M2 mirror mass: ~ 10 kg , - Max acceleration: 25 g lateral, 10 g axial (quasi-static loads), - Out of plane stroke: +/- 1 mm, - Out of plane resolution: 0.5 um, - Tip-tilt range: +/- 500 urad, - Tip-tilt resolution: 5 urad, - Mass < 12 kg, - Minimum power dissipation (including X meters harness): < 4 W per actuator (100% duty cycle), - Duty cycle (10 cycles on ground, 10 cycles in orbit), - Mission duration: 5 year. Based on the industrial studies, the following conclusions were achieved: - Trade between 3 and 5 DoF was closed in favour of a 3 DoF mechanism, - Baseline design is with 3 linear actuators, - Baseline design without dedicated Hold Down and Release Mechanism (this shall be achieved via the linear actuators and the supporting structure), - Baseline design without any position sensor (end stop on each DoF used as reference), - Baseline design is a self standing mechanism, - Baseline is launch position in middle of the operating range. The activity is structured in two phases: Phase 1 is parallel competitive (2x 250k) so as to allow for additional trades and preliminary design work. At the end of Phase 1, one contractor is selected to carry out Phase 2 (bread-boarding and testing, 1x 1000k). The main tasks of phase 1 are: - Review of technical specification based on ESA functional specification. - Linear actuator trade-off, definition, and preliminary design and analyses - Mechanism trade-off, definition, preliminary design and analyses.

Deliverables

Technical documentation detailing trade-off and design solution


2012


SPICA Contract Duration:

6


T-8474


Page 36 of 76

N/A


Programme: CTP Reference: C216-024MM-B


Total Budget: 250

Objectives


Description

The demanding WFE requirements (diffraction limited performance at 5 um, WFE < 350 nm)and the cryogenic operating temperature (5K) applicable to the SPICA telescope require the adoption of an M2 focusing mechanism to mitigate the risks associated to thermoelastic/manufacturing/ageing effects (also considering the complexity of performing ground tests at the nominal operating temperature and the hot launch conditions). The main functions of the M2 mechanism are: - Support and secure M2 during launch (without power), - Provide 3 DoF correction (focus and tip/tilt) on ground and in orbit, - Maintain stable position without need for power when in orbit. The driving performance requirements are: - Operating temperature 4.5 K (capability to operate at higher temperature 300K for on ground testing), - M2 mirror size: ~ 700 mm diameter, - M2 mirror mass: ~ 10 kg , - Max acceleration: 25 g lateral, 10 g axial (quasi-static loads), - Out of plane stroke: +/- 1 mm, - Out of plane resolution: 0.5 um, - Tip-tilt range: +/- 500 urad, - Tip-tilt resolution: 5 urad, - Mass < 12 kg, - Minimum power dissipation (including X meters harness): < 4 W per actuator (100% duty cycle), - Duty cycle (10 cycles on ground, 10 cycles in orbit), - Mission duration: 5 year. Based on the industrial studies, the following conclusions were achieved: - Trade between 3 and 5 DoF was closed in favour of a 3 DoF mechanism, - Baseline design is with 3 linear actuators, - Baseline design without dedicated Hold Down and Release Mechanism (this shall be achieved via the linear actuators and the supporting structure), - Baseline design without any position sensor (end stop on each DoF used as reference), - Baseline design is a self standing mechanism, - Baseline is launch position in middle of the operating range. The activity is structured in two phases: Phase 1 is parallel competitive (2x 250k) so as to allow for additional trades and preliminary design work. At the end of Phase 1, one contractor is selected to carry out Phase 2 (bread-boarding and testing, 1x 1000k). The main tasks of phase 1 are: - Review of technical specification based on ESA functional specification. - Linear actuator trade-off, definition, and preliminary design and analyses - Mechanism trade-off, definition, preliminary design and analyses.

Deliverables

Technical documentation detailing trade-off and design solution


2012



6


T-8474


N/A

Page 37 of 76




Total Budget: 1000

Objectives


Description

The activity is structured in two phases: Phase 1 is parallel competitive (2x 250k) so as to allow for additional trades and preliminary design work. At the end of Phase 1, one contractor is selected to carry out Phase 2 (bread-boarding and testing, 1x 1000k). The main tasks of the validation program for the mechanism are: The main tasks of phase 2 are: - Bread-boarding of key technologies. - Preliminary characterisation of the actuator as stand alone unit. - Manufacturing, Assembly and Integration of the mechanism EM. - Testing: o Performance tests: (at ambient conditions and under TV at 4.5K) including resolution, accuracy, precision, motorisation margins, power dissipation, life test-under 1g and with zero g off-loading device. o Environmental tests: (vibration at ambient and TV cycling) with a dummy mirror. o Inspections. - Lessons learnt, implementation plan for QM and FM programmes.

Deliverables

Breadboard demonstrator


2013



9



Light-weight mirror demonstrator breadboard in Sic


Title: Light-weight mirror demonstrator breadboard in Sic

Total Budget: 1500

Objectives

Demonstrate mastery of manufacturing, assembly and polishing of large monolithic mirror using lightweight ceramic technologies. Preliminary thermo-mechanical testing and demonstration of optical surface performance in representative conditions.

Description

The SPICA mission is based on a large cryogenic telescope (primary mirror with a 3.5 diameter, inter-mirror distance ~3 m) operating at ~5K, with the stringent optical performance requirements (diffraction limited at 5 um) and a mass budget of less then 700 kg. Such requirements impose the use of light weighted ceramic materials. It is intended to address the following issues: - Fabrication of large size ceramic optical surfaces. - Specific mechanical and thermal testing (e.g. static load tests, defects characterisation, rupture tests, validation of thermo-elastic properties of representative elements via cooling to operating temperature). - Coating and polishing of optically representative ceramic mirror surfaces, including demonstration of gravity compensation and polishing optimisation. - Specific optical performance testing. These objectives should be achieved via the manufacturing and testing of an M1 bread-board and/or of dedicated testing

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samples, all in representative ceramic materials. The specific nature of the tests and the characteristics of the bread-board may vary depending on the ceramic material (SiC / Cesic) and its specific characteristics and technology readiness. Based on the recent studies, the following conclusions were achieved: - A SiC based primary mirror would not require CVD coating (applied instead to M2, in conjunction with IBF). - Brazing of different mirror elements (SiC100) requires further mechanical validation to fully characterise the brazing properties (e.g. static load testing up to rupture, fracture control). - A HB-Cesic based primary mirror would require demonstration of the infiltration process on a large size structure (> 2m). In this case more emphasis is required on fabrication aspects. - Optimisation of the polishing method is critical to the overall project schedule. - Gravity compensation during polishing requires validation. Technology Heritage: Different levels of technology readiness and heritage exist depending on the specific ceramic material (SiC 100 or Cesic). SiC 100 has been used for the fabrication of the 3.5 m diameter Herschel telescope (cooled down to about 70K) and is flight qualified. SiC 100 has been also used for flight units of JWST-NIRSpec (optical bench and optical elements). Given the segmented approach to M1 manufacturing, no modifications are required to the existing fabrication facilities. Based on the assessment study, CVD coating would not be required for SPICA. This is an important point as in case CVD was required, dedicated facility upgrades would be needed (e.g. 3.5m dia IBF facility) and additional aspects would become critical (e.g. brazing of CVD coated segments), now not covered by this technology development plan. Cesic (both standard/MF-Cesic and HB-Cesic) has more limited heritage (smaller scale structure flown on Spirale (F-DoD), bread-boarding of BepiColombo, GAIA and NIRSpec elements, 600 mm dia HB-Cesic mirror under testing at TAS-F) and would require further work on large scale (> 2m, as suggested by TAS and ECM) structures to achieve adequate technology readiness, with specific emphasis on the manufacturing of the blank mirror (HBCesic is offered for the SPICA telescope). Silicon infiltration of large size and complex geometry green bodies is a high priority issue in the case of HB-Cesic technology. New fabrication facilities (moulding facility, carbonisation furnace) would be required in order to produce the 3.5 m diameter primary mirror. Europe has considerable heritage in the polishing of large mirror. Nevertheless the SPICA combination of large size, demanding requirements and ceramic material is unprecedented and requires some preparation. Gravity compensation approach (given light-weighted structure) is of specific concern. Convergence of the polishing approach is highly critical wrt overall project schedule. The main tasks of the validation program for the mirror demonstrator are: - Trade-off and design activities to fully define the required M1 Bread-board (e.g. mirror segment vs. reduced mirror size, surface shape, etc.) and supports (bipods). - Trade-off and design activities to define the optimised polishing approach. - Manufacturing of all the Bread-Board parts and of any related support equipment. - Parallel procurement of polishing / gravity compensation / test equipment. - Assembly and Integration of the M1 Bread-board. - Mirror polishing activities as required for validating specific critical issues. - Optical characterisation at ambient and cryogenic temperature (TBC). - Mechanical testing at ambient as required to fully validate the fabrication process, to characterise the dimensions of defects and to validate the allowable loads (strength). It is envisaged that the breadboard will include elements of representative size and shape wrt SPICA M1 as well as representative fixation devices. Actual extent of polished area is TBD. Nature of the mechanical tests at ambient depends on actual ceramic material and should be linked to the final STA model philosophy.

Deliverables

1) Large size <= 2m diameter lightweighted ceramic breadboard mirror, fully structurally representative of the Spica telescope primary mirror design with a polished optical surface suitable for cryogenic optical performance testing, with all necessary GSE tooling for safe handling, mounting and testing with gravity compensation mechanisms. 2) Fabrication, production and polishing report emphasizing the schedule drivers. 3) Test and verification report (including all test data) covering mechanical, acoustic, thermal and optical performances (ambient and cryogenic)


2013



18


T-8532


Harmonisation in progress (2. half 2008)

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Light-weight mirror demonstrator breadboard in HB-Cesic


Title: Light-weight mirror demonstrator breadboard in HB-Cesic

Total Budget: 1500

Objectives

Demonstrate mastery of manufacturing, assembly and polishing of large monolithic mirror using lightweight ceramic technologies. Preliminary thermo-mechanical testing and demonstration of optical surface performance in representative conditions.

Description

The SPICA mission is based on a large cryogenic telescope (primary mirror with a 3.5 diameter, inter-mirror distance ~3 m) operating at ~5K, with the stringent optical performance requirements (diffraction limited at 5 um) and a mass budget of less then 700 kg. Such requirements impose the use of light weighted ceramic materials. It is intended to address the following issues: - Fabrication of large size ceramic optical surfaces. - Specific mechanical and thermal testing (e.g. static load tests, defects characterisation,rupture tests, validation of thermo-elastic properties of representative elements via cooling to operating temperature). - Coating and polishing of optically representative ceramic mirror surfaces, including demonstration of gravity compensation and polishing optimisation. - Specific optical performance testing. These objectives should be achieved via the manufacturing and testing of an M1 bread-board and/or of dedicated testing samples, all in representative ceramic materials. The specific nature of the tests and the characteristics of the bread-board may vary depending on the ceramic material (SiC / Cesic) and its specific characteristics and technology readiness. Based on the recent studies, the following conclusions were achieved: - A SiC based primary mirror would not require CVD coating (applied instead to M2, in conjunction with IBF). - Brazing of different mirror elements (SiC100) requires further mechanical validation to fully characterise the brazing properties (e.g. static load testing up to rupture, fracture control). - A HB-Cesic based primary mirror would require demonstration of the infiltration process on a large size structure (> 2m). In this case more emphasis is required on fabrication aspects. - Optimisation of the polishing method is critical to the overall project schedule. - Gravity compensation during polishing requires validation. Technology Heritage: Different levels of technology readiness and heritage exist depending on the specific ceramic material (SiC 100 or Cesic). SiC 100 has been used for the fabrication of the 3.5 m diameter Herschel telescope (cooled down to about 70K) and is flight qualified. SiC 100 has been also used for flight units of JWST-NIRSpec (optical bench and optical elements). Given the segmented approach to M1 manufacturing, no modifications are required to the existing fabrication facilities. Based on the assessment study, CVD coating would not be required for SPICA. This is an important point as in case CVD was required, dedicated facility upgrades would be needed (e.g. 3.5m dia IBF facility) and additional aspects would become critical (e.g. brazing of CVD coated segments), now not covered by this technology development plan. Cesic (both standard/MF-Cesic and HB-Cesic) has more limited heritage (smaller scale structure flown on Spirale (F-DoD), bread-boarding of BepiColombo, GAIA and NIRSpec elements, 600 mm dia HB-Cesic mirror under testing at TAS-F) and would require further work on large scale (> 2m, as suggested by TAS and ECM) structures to achieve adequate technology readiness, with specific emphasis on the manufacturing of the blank mirror (HBCesic is offered for the SPICA telescope). Silicon infiltration of large size and complex geometry green bodies is a high priority issue in the case of HB-Cesic technology. New fabrication facilities (moulding facility, carbonisation furnace) would be required in order to produce the 3.5 m diameter primary mirror. Europe has considerable heritage in the polishing of large mirror. Nevertheless the SPICA combination of large size, demanding requirements and ceramic material is unprecedented and requires some preparation. Gravity compensation approach (given light-weighted structure) is of specific concern. Convergence of the polishing approach is highly critical wrt overall project schedule. The main tasks of the validation program for the mirror demonstrator are: - Trade-off and design activities to fully define the required M1 Bread-board (e.g. mirror segment vs. reduced mirror size, surface shape, etc.) and supports (bipods). - Trade-off and design activities to define the optimised polishing approach. - Manufacturing of all the Bread-Board parts and of any related support equipment. - Parallel procurement of polishing / gravity compensation / test equipment. - Assembly and Integration of the M1 Bread-board. - Mirror polishing activities as required for validating specific critical issues. - Optical characterisation at ambient and cryogenic temperature (TBC). - Mechanical testing at ambient as required to fully validate the fabrication process, to characterise the dimensions of defects and to validate the allowable loads (strength). It is envisaged that the breadboard will include elements of representative size and shape wrt SPICA M1 as well as

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representative fixation devices. Actual extent of polished area is TBD. Nature of the mechanical tests at ambient depends on actual ceramic material and should be linked to the final STA model philosophy.

Deliverables

1) Large size <= 2m diameter lightweighted ceramic breadboard mirror, fully structurally representative of the Spica telescope primary mirror design with a polished optical surface suitable for cryogenic optical performance testing, with all necessary GSE tooling for safe handling, mounting and testing with gravity compensation mechanisms. 2) Fabrication, production and polishing report emphasizing the schedule drivers. 3) Test and verification report (including all test data) covering mechanical, acoustic, thermal and optical performances (ambient and cryogenic)


2013



18


T-8532


Harmonisation in progress (2. half 2008)

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Development of optimised CCD for PLATO


Title: Development of optimised CCD for PLATO

Total Budget: 2500

Objectives

Development of optimised large area CCD detector with low noise operation, large signal capability and high speed multi-node readout.

Description

The PLATO cameras design requires large area CCD detectors (4510x4510 px) with two separated and connected sections to allow for full frame (FF) or frame transfer (FT) modes. Basic requirements include: - Pixel size 18um x 18um; useful pixels in FF 4510x4510; useful pixels in FT 4510x2253; flatness 30um. - Full well capacity of 1Me-, which requires thin oxide and doping. - An anti-reflection coating is required on its sensitive surface which shall be optimised for wavelength longer the 500nm. Specifically the quantum efficiency at 600nm shall be at least 0.9. The operating wavelength range is 500-1000nm. - The CCD shall be compatible with a readout time 3.0 s at a fast rate of 4MHz on the 2 outputs when used in full frame mode with a readout noise of less than18 e- rms. - The nominal operating temperature shall be -70C (TBC). The development of the Detectors shall be based on a prototyping activity which shall take advantage of the existing technologies to result in an optimised custom design which meets the established requirements. The prototyping activity will include: - Detectors and packaging design - Validation of the packaging process - Manufacturing of several batches (5 TBC) each including 24 (TBC) detectors with indication of the yield - Tests, characterisation and confirmation of the detectors performances The prototyping activity will be based on a dedicated CCD Specification document which reports the requirements for flight. An additional important aspect of this activity is the full and unambiguous demonstration of the capability to produce the large number of CCDs required by PLATO at the required rate. This is an essential element in the reduction the development risks of PLATO and this activity must be evidence for the capability of the required yield.

Deliverables

Prototype CCD detector with 4-side buttable architecture and dedicated package


2011


Plato Contract Duration:

15



N/A

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Cryogenic testing of existing HgCdTe detectors


Title: Cryogenic testing of existing HgCdTe detectors

Total Budget: 500

Objectives

Future science missions (astrophysics in particular) require IR detectors with dark current levels several orders of magnitude lower than existing HgCdTe technology. Most existing HgCdTe detectors have however not been tested at deep cryogenic temperatures, implying they have not been evaluated up to their diffusion limit and there is still a potential for improving their performance. The objective of this activity is to investigate the ultimate performance of existing HgCdTe MWIR/LWIR detectors at the lowest cryogenic temperatures at which these detectors will still operate, and measure the minimum dark current levels attainable at these temperatures. It is foreseen to initiate 2 competitive contracts for the activity.

Description

Future science (astrophysics) missions require detectors in the wavelength range between 5 and 11 microns with dark current levels several orders of magnitude lower than what has been shown with existing HgCdTe technology. The goal of this activity is hence to: Perform cryogenic tests on existing IR HgCdTe detectors: - Propose wavelength ranges at which said detectors have not been tested at temperatures lower than 80 K and where the possible improvement in performance has hence the highest potential. - Identify the minimum temperature at which these detectors would still operate and for which further (deeper) cooling will not bring any further gain in performance. - Test these detectors at identified temperatures and measure their performance parameters including dark current levels.

Deliverables

Test report, highlighting optimum performance parameters at identified temperatures (including lowest dark current measured) of proposed existing detectors.


Q4 2012


Astrophysics missions (e.g. ECHO) Contract Duration:

9



Cryogenic testing of existing HgCdTe detectors

Programme: CTP Reference: C217-026PA-B

Title: Cryogenic testing of existing HgCdTe detectors

Total Budget: 500

Objectives

Future science missions (astrophysics in particular) require IR detectors with dark current levels several orders of magnitude lower than existing HgCdTe technology. Most existing HgCdTe detectors have however not been tested at deep cryogenic temperatures, implying they have not been evaluated up to their diffusion limit and there is still a potential for improving their performance. The objective of this activity is to investigate the ultimate performance of existing HgCdTe MWIR/LWIR detectors at the lowest cryogenic temperatures at which these detectors will still operate, and measure the minimum dark current levels attainable at these temperatures. It is foreseen to initiate 2 competitive contracts for the activity.

Description

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Future science (astrophysics) missions require detectors in the wavelength range between 5 and 11 microns with dark current levels several orders of magnitude lower than what has been shown with existing HgCdTe technology. The goal of this activity is hence to: Perform cryogenic tests on existing IR HgCdTe detectors: - Propose wavelength ranges at which said detectors have not been tested at temperatures lower than 80 K and where the possible improvement in performance has hence the highest potential. - Identify the minimum temperature at which these detectors would still operate and for which further (deeper) cooling will not bring any further gain in performance. - Test these detectors at identified temperatures and measure their performance parameters including dark current levels.

Deliverables

Test report, highlighting optimum performance parameters at identified temperatures (including lowest dark current measured) of proposed existing detectors.


Q4 2012



9



Performance verification and qualification of vibration free Hydrogen sorption JT cryo-cooler

Programme: CTP Reference: C221-002MT

Title: Performance verification and qualification of vibration free Hydrogen sorption JT cryo-cooler

Total Budget: 400

Objectives

Upgrade of existing Hydrogen sorption cooler to meet ECHO mission requirements. Environmental test campaign to raise TRL to 5.

Description

Future Science missions requiring high pointing stability such as ECHO are sensitive to the exported vibrations from mechanical coolers. On Planck, the exported vibrations from the 4K JT cooler has been reduced to below 40mN, which is deemed acceptable for ECHO, but the addition of a mechanical Stirling/Pulse Tube pre-cooler which has to be placed close to the payload might increase the exported vibrations above the acceptable levels. To overcome this problem, a vibration free hydrogen sorption cooler is considered as a pre-cooler for the 4K JT baselined for the longer wavelength focal plane cooling (Si:As detectors). The cooler shall be capable of providing 200 mW of cooling power at 18 K, dissipating less than 9W at 90K and 9W at 120K. The requirements are close to the hydrogen sortpion cooler currently under development with the University of Twente and can therefore take advantage of the same design. In the frame of this activity, the existing Hydrogen sorption cooler needs to be adapted to meet the requirements of the ECHO mission by adding additional compressor stages and to verify the performance matching the radiative cooling available. After successful performance verification, an environmental test campaign will be performed to raise the TRL level from 4 (expected after current TRP activity) to TRL 5. In addition, the performance of the sorption cooler at ~30K using Neon shall be measured to verify the suitability of the cooler for cooling MCT detectors at long wavelengths at 30K. Operation at this temperature could simplify the cooling chain.

Deliverables

Breadboard cooler, technical data package detailing performance and qualification test results


2014


ECHO, Astrophysics missions Contract Duration:

18



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Characterisation of actuator behaviour for a cryogenic fine steering tip-tilt mechanism

Programme: CTP Reference: C215-118MS

Title: Characterisation of actuator behaviour for a cryogenic fine steering tip-tilt mechanism

Total Budget: 300

Objectives

This activity aims at the characterisation of a space qualified actuator (e.g. piezo-electric) that would be used in a 2 degree-of-freedom mirror fine steering mechanism operating under cryogenic temperature conditions (<50K).

Description

This activity aims at the characterisation of a space qualified actuator (e.g. piezo-electric) that would be used in a 2 degree-of-freedom mirror fine steering mechanism operating under cryogenic temperature conditions (<50K). Among other science missions, this would largely benefit EChO, by simplifying its fine pointing control and eventually replacing the constraining micro-propulsion solutions. The main effort will be focused on the evaluation of thermo-mechanical behaviour and performances of the actuator in operational conditions, to reach TRL 5, and its capabilities to sustain stresses due to thermal cycles between room and cryo temperatures. A test campaign under cryogenic temperature shall be performed covering at least: - functional and performance test - thermal cycling - life test under operational conditions

Deliverables

Technical data package


2014


ECHO Contract Duration:

12



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Marco Polo R earth re-entry capsule dynamic stability characterization

Programme: TRP Reference: T218-004MP

Title: Marco Polo R earth re-entry capsule dynamic stability characterization

Total Budget: 450

Objectives

To identify different capsule shapes suitable for the Marco Polo R mission and perform a detailed dynamic stability characterization of the selected configuration(s).

Description

The Marco Polo R mission foresees a capsule re-entering the earth atmosphere at high velocity (typically ranging from 11 to 14 km/s) without the usage of a supersonic parachute. In such a situation, the shape of the earth re-entry capsule (ERC) is the result of a difficult compromise between different and conflicting needs: the aerodynamic drag should be as high as possible so to brake high in the atmosphere, the experienced thermal conditions should be confined within the TPS capabilities, and finally static and dynamic stability have to be guaranteed down to the subsonic regime. During the proposed study a preliminary investigation and a subsequent trade-off of different re-entry capsule shapes shall be carried out identifying pros and cons concerning accommodation capability, stability, CoG positioning, thermal exposition, and landing conditions. The focus of the activity shall be the dynamic stability characterization of the ERC. A detailed aerodynamic characterization of the selected configuration(s) shall be obtained with a proper combination of wind tunnel tests (eventually with free oscillation, free to tumble or forced oscillation techniques), free flight models (ballistic and open range tests, drop tests) and CFD simulations.

Deliverables

Reports, recommendations, results of calculations and tests, databases, validated codes and instrumented wind tunnel models, synthesis, recommendations on methodologies.


2014


Marco Polo R, Exploration missions Contract Duration:

24



Autonomous GNC Technology for NEO Proximity, Landing and Sampling Operations - Phase 2

Programme: CTP Reference: C205-019EC

Title: Autonomous GNC Technology for NEO Proximity, Landing and Sampling Operations - Phase 2

Total Budget: 500

Objectives

To develop and validate algorithms for a vision-based navigation system operating in a low-gravity environment (with existing hardware) and confirm/define requirements for hardware delta-development.

Description

The proposed activity will build upon: "Autonomous GNC technology - Phase 1 T205-029EC". This activity is targeting the operational conditions of an asteroid sample return mission such as Marco Polo (as defined in the Cosmic Vision original proposal). Its main achievement is the demonstration of the feasibility and the design of GNC modes ensuring an accurate landing (~ 5-10 m landing ellipse). An attractive feature of the proposed solution is the integrated landmarks-based navigation strategy applicable to relative and absolute navigation. Based on the new MarcoPolo-R scenario, the proposed activity will further the preceding activity by performing the following tasks: - Development, adaptation, validation of existing simulation and testing environment(s) for validation and verification, based on the Phase 1 functional engineering simulator (operational SW) for the MarcoPolo-R scenario. The task will

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include the integration of the autonomous G-N-C components (including Image Processing) developed in the Phase 1 activity. - Development, adaptation of an avionics test bench including a vision-based optical simulator and scene generation tool (PANGU). - Autocoding (production C-code) and validation of all GNC modes of the selected reference mission (MarcoPolo-R), including safe and contingency modes. - Step-wise performance verification & validation of the autonomous GNC system demonstrator. High-fidelity closed-loop simulations, will verify the GNC robustness, performance, autonomy. - Hardware-in-the-loop simulations to verify the GNC performance and validate the observation models. The Image Processing (IP) algorithms will also be implemented using an actual camera. The testing of the navigation modes, tailored for an asteroid sample return mission such as MarcoPolo-R or Phobos/Deimos sample return mission on a test facility and using representative avionics will bring the TRL to 4.

Deliverables

ESA will be provided with an autonomous GNC system demonstrator tailored for an asteroid sample return mission, with validated autonomous G-N-C building blocks that can be re-used for other similar missions as well as with a complete simulation and testing environment(s) suite for the development, verification and validation of GNC systems of future small body missions. Full technical documentations will be delivered, covering specifications, architecture, algorithms, modelling, simulation test results and flight software validation test results. All software developed during the activity will be delivered (source and binary codes).


2014


MarcoPoloR, Exploration missions Contract Duration:

12


T-8071


N/A

Miniaturized Imaging Laser Altimeter


Title: Miniaturized Imaging Laser Altimeter

Total Budget: 850

Objectives

The objective of this activity is to develop a Miniaturized Imaging Laser Altimeter targeting the MarcoPolo-R GN&C application requirements. This includes the manufacturing and testing of a flash imaging lidar breadboard implementing novel detector arrays that can produce 3D images of the target without the need to have mechanical scanners. Such sensor shall merge the functions of visual based cameras and laser altimeter.

Description

The proximity manoeuvres between a spacecraft and a near Earth asteroid (NEA), as foreseen for the MarcoPolo-R mission, are considered critical from the point of view of the GN&C operations. In order to find and track the NEA, maintain stabilized orbits or perform landing and touchdown operations the spacecraft needs to rely on different optical sensors. These optical sensors acquire different type information from the target in order to enable the different GN&C operations. Nowadays visual based cameras and a laser altimeter can be used in conjunction to derive the target image and range, however a novel type of optical sensor can be foreseen to merge both functions in a single sensor. An Imaging Laser Altimeter is a three-dimensional imager, similar to an imaging LIDAR, that combines the image information of the target with the range information for each pixel of the image. This allows the digital elevation map of the target to be defined with high precision and accuracy. While in the past laser range finders required mechanical scanners to scan the target in order to build its complete 3D image, novel detector arrays such as SPAD (single photon avalanche diode) arrays and APS (Active Pixel Sensor) arrays can be now implemented in a scannerless (or flash) sensor configuration. This results in a miniaturized ranging sensor that does not have any moving parts and operates at the same time as a precise laser altimeter and imager. Such imaging laser altimeter sensor is able to measure, with high precision, the distance of the spacecraft from the surface of the NEA, covering at the same time several target points on the asteroid surface (depending only on the detector array format and resolution). In addition to the topographic profile, from which the global shape model can be produced, the sensor can be also used to determine the reflectivity of the surface, as well as the slope and surface roughness. A TRP activity (Miniaturized Imaging LIDAR Systems (Phase 1)) has been initiated to assess novel technologies(including SPAD and APS detector arrays) that shall lead to a significant breakthrough in miniaturization of imaging LIDAR systems. The activity only covers a Phase 1 development that includes: the review and experimental demonstration of novel technologies and the preliminary design of miniaturized Imaging LIDAR systems for different GN&C applications.

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The objective of the proposed activity is to cover a Phase 2 of the technology development and demonstration targeting the MarcoPolo-R mission requirements. This activity shall include the detailed design of a Miniaturized Imaging Laser Altimeter breadboard using the technologies identified and assessed in Phase 1(on the going TRP activity),and then manufacturing and testing of the dedicated breadboard.

Deliverables

Miniaturized Imaging Laser Altimeter detailed design files Miniaturized Imaging Laser Altimeter breadboard


2016 (TRL-5)


MarcoPolo-R Contract Duration:

18


T-7860


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15K Pulse Tube cooler

Programme: CTP Reference: C220-032MC

Title: 15K Pulse Tube cooler

Total Budget: 600

Objectives

The objective is to develop a multistage Pulse Tube cooler capable to pre-cool the advanced JT cooler at a temperature of 15K

Description

2-4K Joule Thompson cooler require pre-cooling at 15K. For that purpose, a 10K Stirling cooler is currently under development, providing more than 200mW at 15K. As an alternative a Pulse Tube cooler starting from cold temperatures is currently under development, but still requires either passive pre-cooling or another active cooler. To overcome this complexity and to provide an alternative to the Stirling cooler under development, a multistage Pulse Tube cooler, starting from room temperature shall be designed, manufactured and tested. A suitable long-life linear compressor shall be developed.

Deliverables

Fully tested EM cooler, documentation


2012


Generic Contract Duration:

24


T-7876


Cryogenic and Focal Plane cooling (2007)

Advanced 2K JT cooler

Programme: TRP Reference: T220-053MC

Title: Advanced 2K JT cooler

Total Budget: 700

Objectives

The objective is to develop a high cooling power Joule Thompson cooler with an operating temperature below 2K

Description

The current 4K cooler developed for Planck is currently based on the first generation of linear compressors. Currently, new linear compressors under development offer the possibility to achieve high cooling powers at temperatures below 2K, offering the capability to use more compact sub-Kelvin cooler and minimising the heatload at the low temperature stages at a comparable mass compared to todays 4K systems. Based on the new generation of long-life linear compressors currently under development, a high power, low temperature Joule Thompson cooler shall be developed, assembled and tested.

Deliverables

Fully tested EM cooler, documentation


2012



24


T-8527


Cryogenic and Focal Plane cooling (2007)

Detector cooling system including cryostat and active coolers down to 50mK

Page 49 of 76

Programme: CTP Reference: C221-001MT

Title: Detector cooling system including cryostat and active coolers down to 50mK

Total Budget: 2000

Objectives

The objective is to develop a flight like cryostat including active cryocoolers for cooling of sub-Kelvin detectors to 50 mK.

Description

To achieve sub-Kelvin cooling of detectors, a cooling chain involving several cooler stages is required. This has been successfully demonstrated for Planck with a large, passive pre-cooled system and a continuous dilution cooler for the last stage. On the contrary, cooling systems required for future astrophysics missions (e.g. ATHENA) need to be compact and integrated into a cryostat to allow testing in the cleanroom and the combination of a JT cooler with a cyclic ADR and/or Sorption cooler to meet a lifetime of 10 years. This activity will therefore focus on a small, compact cryo-chain with a long lifetime to complement the experience gained in the Herschel/Planck programme. In the first phase, a flight like cryostat breadboard compatible with European coolers and future astrophysics mission focal plane array (FPA) requirements shall be developed and manufactured, simulating the various cooling stages down to 2K with ground segment equipment/mass thermal dummies, with the main purpose being to achieve a high efficient insulation. To minimise costs, mass optimisation of classical structural elements (e.g. vacuum vessel) will not be required. Parasitic loads from science harness and non-operating coolers will only be simulated by heaters and/or thermal dummies. After successful verification of the cryogenic performance, a mechanical test campaign shall be performed to increase the TRL of the cryostat to 5. In the second phase, the cryostat will be equipped with the actual engineering model coolers, developed in currently running or previous activities to verify the overall performance of the cryochain, test the dynamic behaviour (e.g cool-down, T-stability) and to verify the compliance with the I/F requirements from the FPA (e.g. magnetic stray-field, exported vibrations ...). Since it is assumed, that all the coolers are already at TRL5, mechanical testing of the complete assembly is not deemed necessary.

Deliverables

Cryostat, documentation, test results

Current TRL: 2-3 Target TRL: 5 Application Need/Date:

2015


Future astrophysics missions e.g. ATHENA

Contract Duration:

24



2007

NIR large format sensor array


Title: NIR large format sensor array

Total Budget: 1500

Objectives

The main objectives of this activity are: - To design, manufacture and characterise (as necessary) MCT test structures to demonstrate the material parameters compliant with specification - To design and manufacture MCT array detectors to the requirements specified - Design and manufacture support equipment as necessary to operate, test and characterise the manufactured detectors. - Test and characterise the manufactured detectors to an agreed test plan with reference to the requirements specified.

Description

Mercury cadmium telluride has proved itself as the material of choice for infrared detectors in the short and medium wave regions of the spectrum. A wide range of device designs are available with varying parameters and of varying sizes. Space missions are utilising these devices but studies of future requirements have identified the need for larger area, high-resolution, very low noise detector arrays that are currently not available within Europe. This activity is the first in an anticipated series of developments that aims to culminate in the availability of a flight quality 2k x 2k large-format NIR detector hybrid and custom ASIC controller. This particular activity aims to develop a prototype detector hybrid as the initial step towards meeting this goal. The wider context of this activity within a larger development programme should be noted. In particular there is the ultimate aim to ensure that a large format NIR detector array is available from an industrialised process within Europe.

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Tithe programme of work is divided into two phases. Suggested tasks for each phase are detailed below. Phase 1 - MCT Material Performance Demonstration The work for phase 1 is organised into three tasks as follows: 1.1 Detector requirements analysis 1.2 Test plan preparation 1.3 MCT material demonstration Phase 2 - Detector Manufacture, Test and Characterisation The work for phase 2 is organised into six tasks as follows: 2.1 Preliminary detector design and trade-off study. 2.2 Test Plan preparation and test bench design. 2.3 Detailed detector design. 2.4 Test bench preparation 2.5 Detector manufacture. 2.6 Detector test and characterisation.

Deliverables

Laboratory prototype of hybridised HgCdTe/CMOS ROIC detector with support electronics. Technical data package with test results.


2013



18



N/A


Programme: TRP Reference: T217-059PA-B


Total Budget: 1500

Objectives


Description

Mercury cadmium telluride has proved itself as the material of choice for infrared detectors in the short and medium wave regions of the spectrum. A wide range of device designs are available with varying parameters and of varying sizes. Space missions are utilising these devices but studies of future requirements have identified the need for larger area, high-resolution, very low noise detector arrays that are currently not available within Europe. This activity is the first in an anticipated series of developments that aims to culminate in the availability of a flight quality 2k x 2k large-format NIR detector hybrid and custom ASIC controller. This particular activity aims to develop a prototype detector hybrid as the initial step towards meeting this goal. The wider context of this activity within a larger development programme should be noted. In particular there is the ultimate aim to ensure that a large format NIR detector array is available from an industrialised process within Europe. Tithe programme of work is divided into two phases. Suggested tasks for each phase are detailed below. Phase 1 - MCT Material Performance Demonstration The work for phase 1 is organised into three tasks as follows: 1.1 Detector requirements analysis 1.2 Test plan preparation 1.3 MCT material demonstration Phase 2 - Detector Manufacture, Test and Characterisation The work for phase 2 is organised into six tasks as follows: 2.1 Preliminary detector design and trade-off study. 2.2 Test Plan preparation and test bench design.

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2.3 Detailed detector design. 2.4 Test bench preparation 2.5 Detector manufacture. 2.6 Detector test and characterisation.

Deliverables



2013



18



N/A


Programme: TRP Reference: T217-059PA-C


Total Budget: 300

Objectives


Description

Mercury cadmium telluride has proved itself as the material of choice for infrared detectors in the short and medium wave regions of the spectrum. A wide range of device designs are available with varying parameters and of varying sizes. Space missions are utilising these devices but studies of future requirements have identified the need for larger area, high-resolution, very low noise detector arrays that are currently not available within Europe. This activity is the first in an anticipated series of developments that aims to culminate in the availability of a flight quality 2k x 2k large-format NIR detector hybrid and custom ASIC controller. This particular activity aims to develop a prototype detector hybrid as the initial step towards meeting this goal. The wider context of this activity within a larger development programme should be noted. In particular there is the ultimate aim to ensure that a large format NIR detector array is available from an industrialised process within Europe. Tithe programme of work is divided into two phases. Suggested tasks for each phase are detailed below. Phase 1 - MCT Material Performance Demonstration The work for phase 1 is organised into three tasks as follows: 1.1 Detector requirements analysis 1.2 Test plan preparation 1.3 MCT material demonstration Phase 2 - Detector Manufacture, Test and Characterisation The work for phase 2 is organised into six tasks as follows: 2.1 Preliminary detector design and trade-off study. 2.2 Test Plan preparation and test bench design. 2.3 Detailed detector design. 2.4 Test bench preparation 2.5 Detector manufacture. 2.6 Detector test and characterisation.

Deliverables



2013

Application Generic Contract 18

Page 52 of 76

Mission: Duration:



N/A

Prototype ASIC development for large format NIR/SWIR detector array.


Title: Prototype ASIC development for large format NIR/SWIR detector array.

Total Budget: 500

Objectives

Development of a cryogenic, prototype control and digitisation application specific integrated circuit predominantly for large area NIR/SWIR detector hybrid.

Description

Both dark energy missions propose the use of the Teledyne Imaging Systems Hawaii-2RG detector and SIDECAR ASIC. These activities would lead to a European supply of NIR/SWIR detector technology for both these and future science missions. The programme has the aim of developing a prototype dedicated control and digitisation ASIC to match the hybrid array development.

Deliverables

Laboratory prototype of control and digitisation ASIC for NIR/SWIR detector array.


2012



18


T-8530


N/A

Optimised ASIC development for large format NIR/SWIR detector array.


Title: Optimised ASIC development for large format NIR/SWIR detector array.

Total Budget: 1000

Objectives

Further development of a cryogenic, control and digitisation application specific integrated circuit predominantly for optimised large area NIR/SWIR detector hybrid.

Description

Following on from the prototype development programme this project would be to develop an optimised and characterised control and digitisation ASIC to match the optimised hybrid array development.

Deliverables

Optimised and characterised control and digitisation ASIC for NIR/SWIR detector array.


2015



24


T-8530


N/A

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Prototype NIR/SWIR large format array detector development.


Title: Prototype NIR/SWIR large format array detector development.

Total Budget: 2000

Objectives

Development of a prototype large area NIR/SWIR detector array using hybrid technology.

Description

Both dark energy missions propose the use of the Teledyne Imaging Systems Hawaii-2RG detector and SIDECAR ASIC. These activities would lead to a European supply of NIR/SWIR detector technology for both these and future science missions. This programme aims at developing a prototype large area hybrid array comprising silicon read-out integrated circuit and HgCdTe photovoltaic sensing layer.

Deliverables

Laboratory prototype of hybridised HgCdTe/CMOS ROIC detector.


2013



24


T-8529


N/A

Optimised NIR/SWIR large format array detector development.


Title: Optimised NIR/SWIR large format array detector development.

Total Budget: 3000

Objectives

Development of optimised large area NIR/SWIR detector array using hybrid technology.

Description

Following on from the prototype development programme this activity is to develop an optimised and characterised large area array hybrid detector for high performance NIR/SWIR imaging and spectroscopy. The array would comprise a silicon CMOS read-out integrated circuit bonded to a HgCdTe photovoltaic sensing layer.

Deliverables

Optimised and characterised hybridised HgCdTe/CMOS ROIC detector.


2015



24


T-8529


N/A

Development of low dark current MWIR/LWIR detectors


Title: Development of low dark current MWIR/LWIR detectors

Total Budget: 1700

Objectives

Future science missions (astrophysics in particular) require IR detectors with dark current levels several orders of magnitude lower than existing HgCdTe technology. New fabrication technologies (e.g. p-on-n structures) are being developed in the Near-IR range that should prove beneficial also at longer wavelengths and will be highly beneficial to future science missions. The objective of this activity is to design, develop and test new HgCdTe MWIR/LWIR detectors optimized for low dark

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currents. These detectors shall exhibit a dark current several orders of magnitude lower than existing European technology, which will be applicable to future science missions in general. It is foreseen to initiate 2 competitive contracts for the total activity.

Description

Future science (astrophysics) missions require detectors in the wave range between 5 and 11 microns with dark current levels several orders of magnitude lower than what has been shown with existing HgCdTe technology. The goal of this activity is hence to: Design, develop and test new HgCdTe detectors: - investigate fabrication and design solutions which would allow meeting such requirements - develop one (or more) detector(s) filling the required wavelength range while implementing the identified design solutions - test this detector(s) at the necessary cryogenic temperature to demonstrate compliancy with requirements

Deliverables

1) One (or more) novel detectors in the MWIR/LWIR wave range with a high QE, low dark current, low noise and a high dynamic range 2) Design reports 3) Test reports


Q4 2014



24



Development of low dark current MWIR/LWIR detectors

Programme: TRP Reference: T217-055PA-B

Title: Development of low dark current MWIR/LWIR detectors

Total Budget: 1700

Objectives

Future science missions (astrophysics in particular) require IR detectors with dark current levels several orders of magnitude lower than existing HgCdTe technology. New fabrication technologies (e.g. p-on-n structures) are being developed in the Near-IR range that should prove beneficial also at longer wavelengths and will be highly beneficial to future science missions. The objective of this activity is to design, develop and test new HgCdTe MWIR/LWIR detectors optimized for low dark currents. These detectors shall exhibit a dark current several orders of magnitude lower than existing European technology, which will be applicable to future science missions in general. It is foreseen to initiate 2 competitive contracts for the total activity.

Description

Future science (astrophysics) missions require detectors in the wave range between 5 and 11 microns with dark current levels several orders of magnitude lower than what has been shown with existing HgCdTe technology. The goal of this activity is hence to: Design, develop and test new HgCdTe detectors: - investigate fabrication and design solutions which would allow meeting such requirements - develop one (or more) detector(s) filling the required wavelength range while implementing the identified design solutions - test this detector(s) at the necessary cryogenic temperature to demonstrate compliancy with requirements

Deliverables

1) One (or more) novel detectors in the MWIR/LWIR wave range with a high QE, low dark current, low noise and a high dynamic range 2) Design reports 3) Test reports


Q4 2014

Application Astrophysics missions (e.g. ECHO) Contract 24

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Mission: Duration:



European Low-Flux CIS Development and Optimisation (old title: CMOS APS Operation Optimisation)


Title: European Low-Flux CIS Development and Optimisation (old title: CMOS APS Operation Optimisation)

Total Budget: 750

Objectives

Optimisation and validation of CMOS APS integration, control and read-out operation.

Description

This activity forms a part of the wider strategic programme to develop and stabilise European capability in providing high-performance and practical CMOS APS detectors for space and related applications. CMOS APS detectors can be designed to operate in a wide variety of ways while the CMOS process allows the integration of increasing levels of on-chip functionality. The aim of this activity is to consolidate the operational and on-chip design functionality and develop the building blocks necessary for the construction of practical CMOS APS devices that can be matched to a wide variety of mission applications.

Deliverables

Technology demonstrator breadboard


2015


Several Contract Duration:

24



CCD radiation characterisation

Programme: CTP Reference: C222-034QC

Title: CCD radiation characterisation

Total Budget: 500

Objectives

Radiation characterisation of CCDs selected for flight on Dark energy mission including qualification to raise TRL level to level 6.

Description

This activity concerns radiation characterization of CCDs (TID, DD, and background noise) selected for a potential Dark Energy mission (probably E2V 20382). CCDs will be tested according to mission requirements (operating and thermal conditions). In particular the effect of radiation on mission scientific requirements shall be analyzed. The funding shall cover as a minimum 2 sets of irradiation test campaigns. This activity shall also assess the contribution from secondary particles (generated in surrounding shielding) to displacement damage.

Deliverables



2011



24


T-7889


N/A

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P-channel CCD performance characterization and radiation testing


Title: P-channel CCD performance characterization and radiation testing

Total Budget: 400

Objectives

The proposed activity shall carry out detailed testing of the p-channel devices currently under investigation to evaluate their intrinsic performances and degradation under proton irradiation to allow direct comparison with the existing characterized n-channel version (204-22). The p-channel CCD technology is potentially less sensitive to proton irradiation and is therefore very interesting for future missions where CCD radiation degradation is of major concern.

Description

The proposed activity shall: - perform detailed measurements for PSF, CTI at multiple temperatures, dark noise - perform image quality evaluation to improve TRL. - perform warm and cold irradiation with pre and post characterization - perform analysis of the results and direct comparison with the existing results of the n-channel version (contract 22437/09/NL/AF) - perform modelling of the degradation under proton irradiation and identification of the different induced trap species - provide recommendation for any future p-channel development activity The different tests shall be carried out on a minimum of 3 devices (TBC) to be provided by the Agency

Deliverables

Reports


2011


Several Missions Contract Duration:

12



Advanced P-channel CCD Development


Title: Advanced P-channel CCD Development

Total Budget: 500

Objectives

P-channel CCD technology is currently being investigated as it promises improved radiation tolerance relative to standard n-channel technology. This activity is aiming at applying the new CCD273 design to p-channel technology, producing prototype devices and carrying out characterisation testing.

Description

The proposed activity shall: - lead to a modified CCD273 design optimized for p-channel technology - provide a wafer selection analysis (bulk, epi) to insure long-term procurement - procure at least 2 types of wafers - manufacture prototype devices on the selected wafers - procure packages and perform assembly of the dies - carry out testing: CTI at multiple temperatures, dark noise, cosmetics - perform irradiation with dedicated pre and post characterization tests - analysis of the results and comparison to the n-channel version.

Deliverables

Reports + packaged devices (five minimum)


2013


Several Missions Contract Duration:

15


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TES Spectrometer


Title: TES Spectrometer

Total Budget: 700

Objectives

To develop the TES detector technology required for future FIR and microwave space missions.

Description

Design single pixel TES detectors (scalable to arrays and including optical coupling) with the required geometry (pixel size, array format) and performance (optical NEP, speed, dynamic range) for 3 possible FIR applications (B-POL, SPICA, FIRI). Fabricate and test one of these designs (to be selected by ESA). Optimise single pixel design and design scalable arrays based on these pixels. Fabricate and test arrays.

Deliverables

TES single pixels and arrays, including design reports, mask design, test reports, final report, final presentation


2011


SPICA/FIRI/B- POL Contract Duration:

24



Low Noise Equivalent Power TES bolometers for FIR applications


Title: Low Noise Equivalent Power TES bolometers for FIR applications

Total Budget: 700

Objectives

The development of low noise equivalent power (NEP) bolometers based on Transition Edge Sensor bolometer pixels and arrays based on Transition Edge Sensors for future FIR missions

Description

The state-of-the-art TES bolometers for FIR applications have demonstrated a dark NEP of ~4 10^-19 W/Hz^-1/2 and minimum pixel sizes of just below 1x1 mm. Measured NEP values are typically 2x worse than predicted, and performance limitations are not well understood. This activity aims to understand the performance limitations and develop more sensitive detectors (NEP ~<1 10^-19 W/Hz^-1/2), while maintaining or possibly reducing the pixel size and response time. A trade-off between the current technology of SiN based TESs and Si-based TESs could be part of this development. In the second phase of this activity, close-packed arrays of TES bolometers will be designed and fabricated, addressing in particular, but not exclusively, the development of high density wiring schemes in the array. In order to measure the optical performance of these highly sensitive devices, a commensurately sensitive set-up with extremely low straylight and EMI levels, as well as an efficient optical coupling scheme must be developed.

Deliverables

Technical Notes, pixel designs, array designs, prototype detectors and arrays, Final Report


2014


SPICA, FIRI Contract Duration:

24



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Silicon drift detectors for gamma-ray scintillators


Title: Silicon drift detectors for gamma-ray scintillators

Total Budget: 500

Objectives

Development and characterisation of SDD detectors for large volume lanthanum halide scintillators.

Description

New developments in lanthanum halide scintillators have resulted in high performance, large volume gamma ray detectors. The current detector modules, however, still use photomultiplier tubes (PMT). Although PMTs have high resolution, they suffer from low quantum efficiency, have large volume and mass and require high bias supplies. An alternative technology is available in the form of the silicon drift diode (SDD) detector. The SDD itself has demonstrated performance but development is required in both the areas of specific array configuration and the application of suitable anti-reflection coatings. If successful, this development would result in the availability of high performance, large volume gamma-ray detectors with lower resource requirement and solid-state detector performance.

Deliverables

Silicon drift diode detector array with high-performance anti-reflection coating.


2012



18



N/A

Enhancement of a silicon photomultiplier module for scintillator detection applications


Title: Enhancement of a silicon photomultiplier module for scintillator detection applications

Total Budget: 490

Objectives

The objective of this proposed activity is to develop a space qualified detection module using SiPMT technology which will act as the detector for scintillator crystals.

Description

The objective of this proposed activity is to build on the initial work and develop a space qualified detection module using SiPMT technology. It is intended that this technology will ultimately serve as a direct replacement for the PMT. The SiPMT technology has many advantages for space, namely single photon sensitivity, low voltage operation (versus kilovolt operation for PMTs), low mass, low volume, modularity and straightforward tailoring of form factor. This proposed activity will involve the design and fabrication of new detector structure optimized for blue detection response. Following confirmation of the detector performance, the detector will be assembled into an appropriate package and full readout electronics designed and incorporated into the detection module. The detector module will then be subjected to a test campaign including thermal vacuum, radiation and reliability with the ultimate aim of demonstrating TRL 6.

Deliverables

Spaced qualified sensor modules, technical data package.


2012


Several Contract Duration:

18



Low-noise scintillator detectors for planetary remote-sensing


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Title: Low-noise scintillator detectors for planetary remote-sensing

Total Budget: 500

Objectives

Low-noise, resource efficient gamma-ray detection system for remote planetary sensing and ground-truth sensing.

Description

Present systems have high internal background, or inefficient detection. Proposed activity foresees development of low-noise and light-weight Lanthanum-Halide detectors.

Deliverables

Prototypes; Technical notes with theoretical findings and manufacturing details; Report with test results.


2012



24



N/A

Rad-Hard Electron monitor


Title: Rad-Hard Electron monitor

Total Budget: 400

Objectives

Rad-Hard radiation monitor

Description

Develop a lightweight highly integrated rad hard radiation monitor capable of a broad range of radiation species monitoring but including good quality registration of electrons, addressing specific requirements of science missions (harsh environments, payload support).

Deliverables

Simulated design, tested prototype


2011



24


T-8547


Harmonisation radiation monitoring; SEENoTC

Solid-state neutron detector


Title: Solid-state neutron detector

Total Budget: 300

Objectives

Direct detection of thermal neutrons from planetary surface in search for water. Detection of solar neutrons.

Description

Detection of water on planetary surfaces has become an essential part of any planetary mission. Current neutron detection systems are bulky, inefficient and use significant s/c resources. Proposed solid-state neutron detectors are very compact, 100% efficient, power economic, and do not require any HV bias.

Deliverables

Prototypes; Technical notes with theoretical findings and manufacturing details; Report with test results.

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2011



24


T-8547


N/A

Back-up IXO optics technology - Phase 1


Title: Back-up IXO optics technology - Phase 1

Total Budget: 1300

Objectives

Development of a back-up technology for the IXO (XEUS) telescope

Description

- Analysis of the requirements for mirror modules of an x-ray telescope composed of stacks of glass shells including coating, mounting and alignment technology and compatible with the requirements for mounting into a petal of the IXO telescope. - Manufacture of mirror modules formed from mounted tandem(s) of stacks of focussing mirror shells, demonstrating ability to meet the requirements of the IXO telescope including environmental. - Manufacture of stacks of coated samples to demonstrate compatibility with coating requirements. - Testing of mirror shells, stacks, mirror modules and coated samples in x-ray to demonstrate material surface properties, coating properties and mirror module focussing in x-ray. - Analysis and elaboration to describe an industrialised manufacturing process to show compatibility with IXO timescales.

Deliverables

Analysis and modelling results. Samples of mirror shells and stacks. IXO mirror module of stacked glass plates. Stack of coated mirror shells. Results of x-ray testing. Industrialisation plans.


2012


X-ray Imaging Missions Contract Duration:

24


T-8452


N/A

Back-up IXO optics technology - Phase 2


Title: Back-up IXO optics technology - Phase 2

Total Budget: 1400

Objectives

Development of a back-up technology for the IXO telescope

Description

- Procurement of materials and installation of necessary equipment to manufacture 2 coated x-ray mirror modules to meet the requirements of the IXO telescope. - Environmental testing (mechanical, thermal) with x-ray testing at an appropriate facility pre and post each environmental test.

Deliverables

Two coated x-ray mirror modules of IXO back up Results of testing (x-ray, mechanical, thermal)

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2014


X-ray Imaging Missions Contract Duration:

16


T-8452


N/A

Uniform Coating of High Aspect Surfaces


Title: Uniform Coating of High Aspect Surfaces

Total Budget: 460

Objectives

The objective of this activity is the development of an optimised process to produce conformally coated samples with a uniform and smooth metallic layer and for high aspect ratio geometries.

Description

Optics for science missions often require high quality metallic coatings on large aspect ratio surfaces to increase the reflectivity. The deposition of noble metals as surface coatings has been extensively studied by a range of methods, where chemical vapour deposition (CVD), has emerged as a leading contender for the conformal coating of non-planar surfaces. However, conventional atmospheric pressure CVD is not without problems, oxygen and carbon content can be significant and conformality of coating is not maintained for structures with very high aspect ratios. Recently the CVD hybrid process Atomic Layer Deposition (ALD) has been employed for iridium coating, a process that can be tuned to a surface driven self-limiting state that results in conformality at even very high aspect ratios. The activity has the objective of developing an optimised process to produce conformally coated samples with a uniform and smooth metallic layer. The activity includes growth and characterization (including novel in-situ methods), and supporting mathematical modelling.

Deliverables

ALD reactor and associated documentation including commissioning and operations. Coated test samples.


2011



24



Opto-mechanical performance characterisation of IR components in representative environment


Title: Opto-mechanical performance characterisation of IR components in representative environment

Total Budget: 650

Objectives

Manufacturing of refractive IR components (optical components and mounts), integration in an optical chain, and testing to demonstrate the opto-mechanical performances in representative environment (cryogenic temperatures and vibration levels).

Description

Future astronomy mission instruments, for example on EUCLID or exoplanet missions, will make use of a number of refractive IR components that shall be exposed to a cryogenic environment. Known IR materials can be considered, but their properties (like for example refractive index and CTE) need to be precisely measured and verified at cryogenic temperatures. In addition mounting and alignment strategies and techniques adequate for the cryogenic and vibration environments need to be developed. During this activity IR materials shall be selected and characterized. IR lenses (both optical components and mounts) shall be designed and manufactured taking into account the representative environment. Several of the manufactured lenses shall be integrated into a representative optical chain breadboard and the opto-mechanical performance of components and of the complete optical chain shall be characterized at representative

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environmental conditions (considering temperature and vibration levels).

Deliverables

IR components and optical chain breadboard


2012


Multiple Contract Duration:

24


T-8442, T-7857


Characterisation of ultra-stable materials at cryogenic temperature

Programme: CTP Reference: C223-035QM

Title: Characterisation of ultra-stable materials at cryogenic temperature

Total Budget: 250

Objectives

To determine accurately the CTE of stable materials at cryogenic temperature

Description

To determine accurately the CTE of stable materials at cryogenic temperature

Deliverables

samples, test results, materials data


2012



24


T-8391


N/A

Materials Charging effects under extreme environments (ultra-low temperatures and high radiation fields)

Programme: TRP Reference: T223-055QM

Title: Materials Charging effects under extreme environments (ultra-low temperatures and high radiation fields)

Total Budget: 250

Objectives

Materials charging can not be predicted at very low temperatures due to low mobility of charged species. Decay times could be very low and for instance photo-induced conductivity could be much significantly lower. Therefore suitable materials must be found. Mission to high radiation field planets/moons require radiation resistant materials. This is crucial and options must be found early in the project so that a sound design can be done.

Description

The activity shall screen/evaluate and downselect suitable materials for the intended mission environment, i.e.: ultralow temperature and high radiation fields. Materials shall be assessed such that results shall be obtained for all missions.

Deliverables

Samples, test results, charging curves/decay curves etc.


2012



24


T-7673


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N/A

Charging properties of new materials


Title: Charging properties of new materials

Total Budget: 200

Objectives

To provide material properties for surface and internal charging analysis for new materials.

Description

In the time-frame of the new science missions, new surface and internal dielectric materials and coatings are expected to be developed. To maintain the ability of existing tools to assess charging effects, charging-related material properties will be measured for these new materials.

Deliverables

study and lists of material properties


2012



18


T-7673


SEENoTC via SPINE

Computational tools for spacecraft electrostatic cleanliness and payload analysis


Title: Computational tools for spacecraft electrostatic cleanliness and payload analysis

Total Budget: 300

Objectives

To develop models and tools, and measure surface properties where necessary, for accurate quantitative evaluation of low-level surface electrostatic charging of science missions.

Description

Cross-scale, Laplace, Tandem and other CV mission are planned to include plasma payloads to investigate the magnetospheres of Earth, Jupiter and Saturn and other solar system plasmas. Electrostatic cleanliness of such scientific spacecraft for correct functioning of plasma measuring payloads requires limiting electrostatic potential perturbations and interference from spacecraft-generated charged particles (e.g. secondary/photo electrons and sputtered ions). This leads to a requirement for low spacecraft potential (typically ~1V), well below the energy of particles being detected, and for spacecraft-induced fluxes well below ambient levels. Control and mitigation of spacecraft perturbation of plasma/field sensors is possible through charge alleviation devices, grounding, material selection and siting of detectors. The open source spacecraft-plasma interaction simulation tool, SPIS, currently has a resolution about one order of magnitude above the required accuracy. Increasing the accuracy to the required level requires significant physics, algorithm and software developments, possibly including better modelling of secondary/photo/sputter emission, better shadowing, control of convergence and increased number of particles per cell and trajectory accuracy. SPIS simulation toolkit has been conceived with a modular approach such that extension of the capabilities and functionalities can be performed without reengineering the whole software.

Deliverables

Numerical model, software, validation, documentation


2011



12


T-8396


SEENoTC via SPINE

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X/K band feed

Programme: TRP Reference: T212-045GS

Title: X/K band feed

Total Budget: 350

Objectives

This activity aims at developing a multi-frequency (X/X/K band) feed breadboard. Such a feed, in its final configuration, will be ultimately installed in ESA Deep Space Ground stations, to provide K-band reception capabilities to any Cosmic Vision mission requiring more than 10 Mb/s downlink telemetry rate. All other bands, performance and modes of operation of the station shall remain unaffected.

Description

In order to add the K-band support to existing Deep Space stations, it is necessary to swap the current X-band feed (transmitting at 7.145-7.235 GHz, receiving at 8.4-8.5 GHz) with an X/X/K band one. While the concept looks relatively straighforward, such a feed (which shall be very low-loss, since it serves also Deep Space missions) has never been developed in the past. The multi-frequency feed here described cannot be procured as a standard device or even designed with standard techniques. This activity has the aim to develop an accurate simulation environment able to model coaxial apertures integrated with multi-port elements (such as OMT, tracking coupler) and to get all the know-how needed to manufacture and to test a prototype of such a feed. The simulation environment shall also take into consideration the following specific aspects: power handling (up to 20 kW RF power in X-band), thermal design, the wideband application (for the K-band allocation).The requirements, in terms of frequency bands and performance, will be defined in such a matter to be closer as possible to the final application.

Deliverables

Simulation environment, feed breadboard, test report, final report


2011



15


T-8489, T-8490


N/A

X/K/Ka band dichroic mirror

Programme: TRP Reference: T212-046GS

Title: X/K/Ka band dichroic mirror

Total Budget: 300

Objectives

This activity aims at developing a multi-frequency (X/X/K band) dichroic mirror. Such a mirror, in its final configuration, will be ultimately installed in ESA Deep Space Ground stations, to provide K-band reception capabilities to any Cosmic Vision mission requiring more than 10 Mb/s downlink telemetry rate. All other bands, performance and modes of operation of the station shall remain unaffected.

Description

The current ESA 35 m stations are structured as a Beam WaveGuide (BWG), covering several S, X and Ka band allocations; in order to add the K-band support, it is necessary to develop a dichoic mirror able to separate the X (7.145 to 8.5 GHz) and K (25.5-27 GHz) bands to the Deep Space Ka-band allocation (31.8-32.3 and 34.2-34.7 GHz). The perforated area of such mirror would be about 1x 1.5 m big, containing about 20000 precision holes. This activity has the scope to develop new dichroic design procedures accounting for both mechanical and electrical performance. The dichroic mirror performance will be simulated considering the full incident fields, as in the final environment. The most critical requirements are in the power handling, Ka-band attenuation, scattering, wide bandwidth, mirror deformation under gravity and its effects of electrical performance. A breadboard dichroic will be manufactured and electrically tested.

Deliverables

Simulation environment, breadboard of the dichroic mirror, test report, final report


2011



15

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T-8489,T8490


N/A

Precise Gravitational Modelling of Planetary Moons and NEO (Near Earth Objects) Asteroids

Programme: GSTP Reference: G512-003EC

Title: Precise Gravitational Modelling of Planetary Moons and NEO (Near Earth Objects) Asteroids

Total Budget: 350

Objectives

The main objective of this activity is to develop precise gravitational models of planetary moons and asteroids target of the subject missions: i.e. the asteroid 2001 SG286, Enceladus, Titan, Jupiter, and Europa. The models will be threefold: - Models for mission analysis tools and techniques. These models are accurate and medium size computational intensive and will provide gravity field data for ESA and Industry astrodynamics tools. - Models for operations and ground control. These models are very accurate and high size computational intensive. They will provide gravity field data for spacecraft maneuvering capability. They will be typically installed in an operational ground segment control center. - Models for on-board autonomous orbit and attitude propagation. These models are relatively accurate and low size computational intensive. They will provide gravity field data for on-board autonomous spacecraft maneuvering capability. The expected main results are a thorough concept validation, and verification allowing increasing the TRL up to 6.

Description

The proposed activity will include as a minimum: (1) Detailed gravity fields functional, operational, performance, environment, etc. requirements use; (2) analysis and trade-off of various gravity field models for the 3 above mentioned concepts; (3) baseline definition and identification of models for the 3 areas identified above; (4) performance validation through simulations. ESA will provide the novel gravity model of the GSP activity mentioned above. The Contactor is expected to provide the gravity models of all required bodies in the corresponding modes (tools, operations, and on-board). Full technical documentations will be delivered, covering specifications, architecture, algorithms, modelling, simulation test results and analysis results. All software developed during the activity will be delivered (source and binary codes).

Deliverables

SW/HW/Prototype


2012



18


N/A


N/A

Autonomous GNC Technology for NEO proximity, Landing and sampling Operations - Phase 1

Programme: TRP Reference: T205-029EC

Title: Autonomous GNC Technology for NEO proximity, Landing and sampling Operations - Phase 1

Total Budget: 300

Objectives

Building upon past and on-going technology development, the main objectives of the activity are the following: - Definition of the envelope of operational conditions that an autonomous GNC may find in a mission to a small, irregular (with unknown rotational state) asteroid. In particular, this envelope will consider orbital dynamics and surface characteristics; - Consolidation of the autonomy approaches elaborated in the system assessment study and derivation of the associated system requirements and constraints down to GNC system level, including equipments such as relative terrain sensors; - Enhancement, validation and calibration of existing simulation and testing environment(s) for validation and verification of the NEO GNC demonstrator, encompassing as a minimum functional engineering simulator, avionics test bench, vision-based optical stimulator (ViSOS), and asteroid scene generation tool (PANGU);

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- Adaptation/maturation of autonomous G-N-C components including Image Processing (IP) and Hazard Avoidance algorithms, already developed at functional prototype level in past or on-going technology activities, for orbit acquisition/insertion, maintenance and transfer in the vicinity of the asteroid as well as for the controlled descent to the asteroid surface, the sampling operations and the ascent phase; - Detailed analysis, design and autocoding (production C-code) of all GNC modes of the selected reference mission (Marco Polo), including re-targeting, safe and contingency modes. - Step-wise performance verification & validation of the autonomous GNC system demonstrator for the selected reference mission: Marco Polo. High-fidelity closed-loop simulations, will verify the GNC robustness performances, autonomy and survability, and validate the overall adequacy of the demonstrator to the mission. This first V&V step shall bring the TRL to 3. Hardware-in-the-loop simulations will verify the navigation performances and validate the observation models. Note: real-time closed loop testing on a representative avionics test bench with electrica/optical stimulation of the navigation sensor(s) is contemplated. This second V&V step shall bring the TRL to 5-6. The expected results are a thorough verification and validation of an autonomous GNC system demonstrator (TRL: 5-6) for the selected reference mission (Marco Polo), the delivery of a library of validated autonomous Navigation, Guidance and Control components for NEO proximity operations, landing and sampling operations and the delivery of a complete simulation and testing environment(s) suite for the development, verification and validation of GNC systems of future small body missions.

Description

Task 1 - Mission analysis and system engineering: characterisation of the mission envelope, definition of mission and operation concepts, consolidation of the mission and system requirements and constraints upon the autonomous GNC system, analysis and trade-off of candidate autonomous GNC systems leading to the selection of the most promising ones and algorithms satisfying functional, performance and operational requirements. Task 2 - Strategies for proximity operations, landing and sampling operations: identify and evaluate (i) families of orbits of interest for asteroid observation, (ii) transfer strategies between the orbits, (iii) global characterization and local (landing sites selection) mapping of the target body, (iv) suitable orbit maintenance strategies, (v) landing strategies from low orbit (incl. rehearsals), and (vi) control strategies during sampling/landing, (vii) ascent phase. A set of strategies for trajectory design and guidance will be selected to cover the full range of possible mission scenarios, including the selected reference mission (Marco Polo). Task 3 - Navigation chain: review and evaluate candidate navigation equipment and algorithms taking maximal advantage of the observation/characterization campaign (possibility to acquire and use reference maps). The navigation equipment(s) to be considered will include at least the far navigation camera used in cruise and approach to the asteroid and the altimeter needed for landing. The benefits and drawbacks of a wide-FOV camera or lidar will be analysed. Note: the vision-based navigation system derived from NPAL and VisNaV studies (ESA contracts 15618 and 20848; current TRL: 4) looks suitable for such a purpose. VisNaV specifications will be upgraded in the frame of this activity. VisNav image processing (IP) and estimation algorithms will be analysed, if necessary new ones will be identified and developed, in order to ensure that they can provide the navigation measurements in the full range of mission scenarios, accounting for the whole range of asteroid shapes, sizes, surface properties and features, rotational states, and illumination and viewing conditions. Moreover, the processing of altimeter measurements will also consider the relevant properties of the asteroid surface; Task 4 - Simulation and Testing environment(s) suite: Enhancement, validation and calibration of existing simulation and testing environment(s) for validation and verification of the NEO GNC demonstrator, encompassing as a minimum functional engineering simulator, avionics test bench, vision-based optical stimulator (ViSOS), asteroid scene generation tool (PANGU); Task 5 - Autonomous G-N-C components: Adaptation of autonomous G-N-C components, already developed validated at functional prototype level in past or on-going technology activities, for orbit acquisition/insertion, maintenance and transfer in the vicinity of the asteroid as well as for the controlled descent to the asteroid surface, the sampling operations and the ascent phase - Note: the development and validation of new G-N-C components for better fulfilling the selected reference mission (Marco Polo) performances requirements are not excluded; Task 6 - Autonomous GNC system detailed design: using Marco Polo as a reference mission the detailed analysis and design of all the GNC modes for proximity operations, landing and sampling operations will be performed. Note: all the required GNC modes will be developed using the validated G-N-C components. Task 7 - Autonomous GNC system demonstrator performances verification and validation: the performance and robustness of the autonomous GNC system for the selected reference mission (Marco polo) will be assessed using a validated high fidelity end-to-end simulation environment. Monte Carlo test campaign will be carried out to ensure that the spacecraft achieves the mission requirements for nominal and contingency scenarios. In the second verification & validation step a demonstrator of the autonomous GNC system will be developed. This demonstrator will consist of autocoding the GNC application software and implementing them in a representative avionics. The Image Processing (IP) algorithms will also be implemented into the vision based camera system developed in the VisNav activity. The real-time closed loop performance of the demonstrator will be performed on the avionics test bench developed in Task 4 which will include the physical camera, optical stimulator (ViSOS) and PANGU. Note: a numerical model of the altimeter is contemplated at this stage of the development. Upon successful completion of the activity, the autonomous GNC system demonstrator tailored for Marco Polo mission will achieve a TRL 5-6 (software). Note: NO provision has been made for optical navigation camera Engineering Model development. Background Several small-body missions currently considered by the Agency such as Don Quijote and Marco Polo, the later being selected for assessment as part of the Cosmic-Vision 2015-2025 programme, are characterized by unique challenges to go beyond the current European state-of-the-art in Navigation, Guidance and Control technologies. The characteristics, in particular the GNC performance and autonomy requirements, of a NEO sample return mission require an increase in

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maturity of the GNC technologies. The TRL objective, 5-6 by 2011, can only be achieved with a close synergy with the Aurora technology programme in particular for the key descent and landing phases. In this respect, several past and on-going GNC activities which are directly relevant to the present proposal are listed below. Past technology activities were conducted in preparation of the ROSETTA mission, such as the Autonomous and Advanced Navigation Techniques (AANT) study which investigated and evaluated autonomous GNC/FDIR strategies and concepts applicable to a wide range of interplanetary missions, while the most recent ones are part of the AURORA programme. These technology activities deal in particular with the development of an Engineering Model of a multi-mission (landing, rendezvous, cruise, mobility) optical camera suitable for NEO missions (TRL: 5-6 by 2011) and the associated Image Processing (IP) algorithms and optical stimulator for the verification and validation of vision based navigation systems (ViSOS), and the development of hazard mapping and re-targeting functions (TRL: 4-5 by 2009). Also, in support of several vision-based navigation system activities, the Agency has funded the development of a terrain simulation tool, namely PANGU for Planet and Asteroid Scene Generation Utility, which is capable of synthesizing the terrain of planets and asteroids realistically. In addition, the tool has been extended to provide radar signal return from a small body. This asset is fundamental to the validation of the objectives of the proposed activity. References - ESA Contract No. 14320 (CCN2), Tool for Terminal GNC Design for NEO Impactor Impactor Missions (CLEON) focusing on the development of a software tool for GNC performance assessment in the terminal phase of a NEO Impactor mission - ESA Contract No. 1946 (CCN1), Autonomous GNC Design for NEO Rendezvous (CLEON+) focusing on the development of a software tool for GNC performance assessment in the terminal phase of an autonomous NEO rendezvous mission - ESA Contract No.17338 (CCN3), Asteroid and Whole Planet Simulation with PANGU dealing with asteroid crater and irregular lighting conditions modelling - ESA Contract No. 9558, Autonomous and Advanced Navigation Techniques (AANT) focusing on autonomous GNC/FDIR strategies and concepts applicable to a wide range of interplanetary missions - ESA Contract No. 15292, Autonomous Navigation for Interplanetary Missions (AutoNav), focusing on the interplanetary phases - ESA Contract No. 20528, Optical Flow Navigation system for Landing, focusing on the final powered descent phase and involving 3D landmarks matching - ESA Contract No. 156188, Navigation for Planetary Approach and Landing (NPAL), focusing on the development of a vision based camera breadboard with features extraction capability - ESA Contract No. 18038 (CCN3), Hazard Avoidance Consolidation Activities, focusing on the development of hazard mapping and re-targeting functions - ESA contract No 20848 Multi-purpose Vision-based navigation sensor architecture definition (VisNaV) dealing with the detailed design of a multi-mission optical navigation camera suitable for landing, rendezvous, cruise/fly-by and mobility

Deliverables

SW (prototype) HW EM (synergy with Aurora programme)


2011


NEO/asteroid landing mission Contract Duration:

18


T8071


N/A

High processing power DPU based on high rel. DSP

Programme: CTP Reference: C201-030ED

Title: High processing power DPU based on high rel. DSP

Total Budget: 500

Objectives

Development of High Processing Power DPU board based on high rel. DSP components

Description

Some science missions like GAIA and DUNE and PLATO in the future require a very high data processing power on-board to perform the required data compression operations. Currently there is no European processor board available that could fulfill this need but different concepts on hardening for radiation introduced errors have been proposed. The processor board to be developed shall be based on a High Rel DSP processor (e.g. from TI) which can be considered radiation hard with respect to total dose and SEL. Errors introduced by other SEE shall be detected and corrected by software in combination with the appropriate measures implemented on board level.

Deliverables

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EM level computer board


2011



18


T-7751


2nd Semester 2006 - On-Board Payload Data Processing - A1

Ablation radiation coupling


Title: Ablation radiation coupling

Total Budget: 400

Objectives

- Improvement of windtunnels and flight MT.; - Demonstration of miniature ablation and convective/radiative heat flux sensors. - Radiation code development. - Physical model validation activities. - CFD validation with ablation and radiation. - Development of coupling techniques, influence of absorption by C3.

Description

Background: Need for high speed ablation / radiation and induced transition. LL Viking and Fire 2. LL of ESA WG on ablation and radiation. Traditional thermal protection system design approach neglects coupling of the radiation flux with the ablating surface energy balance condition, to simulate the response of ablative heat shields in hypersonic flows. When a gas mixture passes through a strong shock wave, it is first dissociated. At still higher velocities some of the atoms and molecules are electronically excited. When the excited electrons make a transition to a lower state a photon is emitted, resulting in shock layer radiation. Under certain entry conditions this radiation field can be strong enough to significantly impact the heating rate at the surface of the entry vehicle. It is therefore critical to measure the response of the TPS materials in extreme conditions via experimental campaigns, and to further develop existing physical models, CFD and radiation simulations in order to have higher fidelity model for aeroheating predictions. Of particular concern is the strong coupling between different processes that needs to be addressed specifically in this study.

Deliverables

Design, technical notes (incl. executive summary), codes, material samples


2012



18


T-8540


Yes

Kinetic shock tube for radiation data base for planetary exploration


Title: Kinetic shock tube for radiation data base for planetary exploration

Total Budget: 1000

Objectives

Development of a European shock tube dedicated to kinetic studies for high temperatures (more than 6000K). At present there is no facility available in Europe.

Description

Shock and expansion tubes are important elements for the investigation of chemical kinetics and radiation associated with planetary entry. Facilities exist in the US, in Russia, Japan, Korea, Australia etc... In Europe, the only facility useful though not optimised for this task (TCM2) was developed for the Hermes program, was used for Huygens and Aurora

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studies, but it has closed. There is a need for a new facility, allowing to perform investigations at a moderate cost, for the conditions foreseen in our future Earth entry missions and Mars entry missions, including aerocapture and aerobraking. A dedicated shock tube shall be specified, developed and instrumented. Tests will be performed for various gas mixtures, to provide spectrally resolved emission and absorption spectra, as a minimum. More advanced techniques shall also be assessed, and demonstrated. The obtained results will be compared with documented results.

Deliverables

EM and Technical notes (incl. executive summary)


2012



24


T-8540


Yes

Characterisation of radiation for high speed entry

Programme: CTP Reference: C218-001MP

Title: Characterisation of radiation for high speed entry

Total Budget: 750

Objectives

Development of accurate models for radiation related to high speed Earth and planetary entry. Development of validation data bases, from measurement in the Vacuum Ultra Violet (VUV) range in particular. Development of recommended kinetic schemes, and assessment of uncertainties. This activity end product is the capability to accurately model the radiative environment of capsules during high speed Earth entry.

Description

Earth and planetary entries at high velocity (typically above 11 km/s) are associated with a large emission of radiation in VUV range. This radiation is subject to absorption by various species in the flow field boundary layer near the vehicle, and the corresponding energy is transported and distributed along the heat shield of the capsule. It is therefore important to improve the knowledge of this specific component of radiation, to prepare the design of future entry vehicles. This activity shall be performed in representative conditions (shock tube), and shall focus on the qualification and calibration of the ESA shock tube facility for the relevant regimes, the development of measurement techniques and the validation of models. The determination of uncertainties shall also be an important target. In the frame of this activity, suitable optical windows, spectrometers and calibration lamps shall be identified and procured for the wavelength range of interest (at least 110 nm - 200 nm, possibly down to 80 nm). COTS and ESA material shall be also considered, provided they offer the required performance in terms of sensitivity, wavelength range and speed, for their application to a shock tube flow (few hundreds of microseconds flow measurement time). This activity end product is the capability to accurately model the radiative environment of capsules during high speed Earth entry. This capability will provide extremely valuable input to future mission design (heatshield sizing, material choice etc.) and technology development activities.

Deliverables

Measurement technique reports and hardware, databases, numerical modules, recommendations on methodologies for radiation characterization, for numerical models and for experimental techniques.


2015


Marco Polo R but also all other hypervelocity entry missions

Contract Duration:

24



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High performance frequency dissemination techniques - Phase1


Title: High performance frequency dissemination techniques - Phase1

Total Budget: 250

Objectives

Phase 1: Paper study to assess requirements to advance current high performance frequency dissemination techniques

Description

The objectives of this activity are to provide a high performance frequency comparison facility with which optical clocks in development around Europe can be compared without compromising the performance of the clock by the comparison. To date, frequency comparisons have been made to a few parts in 10e17. This was achieved over integration times of 10000 seconds and using rf modulation of an optical carrier. This activity used optical fibres as the means of transfer and so is limited to ground based implementations. With the need and plans to build clocks having stabilities of parts in 10e16 (@ 1 second integration) or better, one needs to consider ways and means to exploit the transfer of ultra stable frequencies from ground to space and back to verify the performance of space clocks and high performance ground optical clocks. High performance space-to-ground links, both in the microwave and optical domain should be studied.

Deliverables

The deliverables will be not merely a breadboard but a comparison network to allow the comparison between clocks.


2012


Fundamental Physics Contract Duration:

18


T-8522


N/A

High performance frequency dissemination techniques - Phase1

Programme: TRP Reference: T216-033MM-B

Title: High performance frequency dissemination techniques - Phase1

Total Budget: 250

Objectives

Phase 1: Paper study to assess requirements to advance current high performance frequency dissemination techniques

Description

The objectives of this activity are to provide a high performance frequency comparison facility with which optical clocks in development around Europe can be compared without compromising the performance of the clock by the comparison. To date, frequency comparisons have been made to a few parts in 10e17. This was achieved over integration times of 10000 seconds and using rf modulation of an optical carrier. This activity used optical fibres as the means of transfer and so is limited to ground based implementations. With the need and plans to build clocks having stabilities of parts in 10e16 (@ 1 second integration) or better, one needs to consider ways and means to exploit the transfer of ultra stable frequencies from ground to space and back to verify the performance of space clocks and high performance ground optical clocks. High performance space-to-ground links, both in the microwave and optical domain should be studied.

Deliverables

The deliverables will be not merely a breadboard but a comparison network to allow the comparison between clocks.


2012



18



High performance frequency dissemination techniques - Phase 2


Title: High performance frequency dissemination techniques - Phase 2

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Total Budget: 1000

Objectives

Develop a complete breadboard of the high performance metrology link and using a dedicated test set-up demonstrate feasibility of the proposed technique in the realistic-type scenario. (Follow-on for Phase 1: Design)

Description

The main objective of this Technology Development Activity is to design and develop a metrology link for high performance frequency comparison of optical clocks between space and ground. The results of this TDA are important for both, to support future ESA missions in the field of fundamental physics, such as STE-QUEST mission in the ESA Cosmic Vision, and to provide clocks on ground and onboard satellites with the necessary infrastructure to connect them in a worldwide network (TAI, UTC, Galileo, GNSS, etc.). Such a facility shall provide frequency comparison, time dissemination and ranging of utmost performance, with the goal of reaching frequency uncertainty levels below 10^-18 after 1-2 days or less of integration time. The optical link is expected to deliver a stability of around 5E-15/tau. Focus of these activities shall be the microwave and optical links, with emphasis on the optical domain. The main task of this TDA is: - Breadboard development and testing of a high-performance space to ground metrology link, including the flight segment equipment, the ground terminal hardware and ground infrastructure needs for connecting ground and space clocks in a global network. (shall be based on the final design of the metrology link devised in Phase 1 of this activity with design maturity carried down to PDR level.) The goal of this activity is to bridge the gap between rapid developments in optical clock performance over the last years and time/frequency comparison and ranging techniques on the other side. A giant step in the development of frequency standards in the optical domain over the last couple of years is urgently requiring complementary improvements in the performance of time and frequency transfer techniques. At the moment, the best frequency standards can reach fractional frequency instabilities of a few parts in 10^-17 after about thousands seconds of integration time. Such performance requires the development of new techniques to disseminate time and compare frequency by means of metrology links. Clock comparisons, time transfer and ranging have important applications in metrology, geodesy, Global Navigation Satellite Systems (GNSS) like Galileo and fundamental physics research. High performance clocks and links have been proposed in the ESA Cosmic Vision (STE-QUEST mission) as key technology to probe fundamental laws of physics: gravitational redshift measurements, equivalence principle tests, scale dependent gravity, light propagation tests including Shapiro delay, and other fundamental research such as time variations of fundamental constants, etc. Applications of the clocks and metrology links in Earth observation, GNSS and geodesy have been clearly identified.

Deliverables

Breadbord of the metrology link and test report. Technical data package


2013



24



N/A

Sub-Megahertz linewidth laser for Fundamental Physics Missions


Title: Sub-Megahertz linewidth laser for Fundamental Physics Missions

Total Budget: 450

Objectives

The TDA objective is to design, fabricate and test a sub-megahertz linewidth laser operating at 780 nm with performance meeting the requirements of future Fundamental Physics missions.

Description

The TDA objective is to design, fabricate and test a narrow linewidth laser operating at 780 nm with performance meeting the requirements of future Fundamental Physics missions. Key areas to be addressed are output power, spectral and noise performance as well as device reliability and lifetime. The following major tasks shall be addressed in the activity: - Laser device design - Wafer growth and laser fabrication - Laser characterisation - Device packaging for athermal operation and thermal feedback control - Manufacture of representative number of devices for statistical analysis

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- Reliability and lifetime testing The contractor shall consider both discrete mode 780 nm devices and frequency doubled 1560 nm devices including the frequency conversion element required to reach the desired final wavelength starting at 1560 nm. Key performance requirements: Laser power: > 100 mW Frequency noise: ~100 Hz2/Hz in the 1-1000 Hz frequency band when locked; Long term frequency stability: <10-10; Power spectrum: 90% of power in 400 kHz; Linear polarization: >95%; RIN: -80 dB/Hz in the 1-100 Hz frequency band ; Long term power stability: 10-2; Hermetic package leakage: <<10-8 Pa.l/s; Angular stability of the beams: <10-4 rad; Transverse position stability: <10 um; Gaussian beam: at 90%.

Deliverables

Laser devices, test reports and technical data package


2014


STE-QUEST, Fundamental Physics Contract Duration:

24



Development and stabilisation of octave spanning optical frequency combs based on silicon-nitride planar high-Q microresonator technology


Title: Development and stabilisation of octave spanning optical frequency combs based on silicon-nitride planar high-Q microresonator technology

Total Budget: 200

Objectives

Develop an entirely integrated, octave spanning chip-scale frequency comb. Demonstration of phase coherent octave spanning spectrum with self referencing and including phase noise measurements for comparison.

Description

An Optical Frequency Comb (OFC) suitable for operation in space (and capable of surviving the launch conditions) is of interest to Fundamental Physics missions. Thus far, self-referenced and phase-stabilised OFC systems have been based on the implementation of fiber or bulk femtosecond mode-locked (fs) lasers. These systems are quite complex and require critical real-time control of many parameters to maintain mode locking and cavity length control. A radically different and disruptive approach has been pioneered at EPFL and is based on an implementation that includes a continuous wave (CW) laser and ultra high quality factor (Q) microresonator. A promising platform to achieve a full monolithic integration is the SiN material platform. The major objective is to dispersion engineer the structures in order to enable octave spanning comb operation, in order to achieve self-referencing. A key measurement is in this context the measurement of the phase noise. The project objectives are: to build, develop, operate and characterise fully operational chip-scale frequency comb demonstrator based on silicon nitride waveguide technology.

Deliverables

OFC demonstrator, technical data package


2014



18



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The Harmonisation Tech Dossier has recently been updated with this information.

Modular Wide Field View RF Configurations


Title: Modular Wide Field View RF Configurations

Total Budget: 500

Objectives

To develop large RF coated lenses (in the order of 0.5m) for lens-based telescopes operating at submillimeter-wave frequencies. Investigation of the most-suited lens base material that provides the necessary low losses at cryo- temperatures and has the proper refractive index.

Description

This activity will be targeted to the following main areas: - Study and design of Wide filed of View reflector architectures. - Address critical technological areas identifying potential solutions. - Perform critical breadboard development The activity will start with a careful assessment on the requirements. This activity will identify and select the RF reflective or refractive architectures required to achieve the necessary FOV and sidelobe levels for a future B-pol mission. These solutions/architectures will have to be demonstrated by critical breadboarding (as a minimum at RF representative sample level). A technology roadmap to bring the technology to flight level shall be provided.

Deliverables

Breadboard of large lens including (multi-layer) RF coating


2012


CMB Polarisation Missions Contract Duration:

24


T-8495


Technologies for Passive mm and Submm Wave Instruments

Large radii Half-Wave Plate (HWP) development


Title: Large radii Half-Wave Plate (HWP) development

Total Budget: 600

Objectives

To ensure availability of half-wave plates of sufficient dimension to fulfill the requirements of future Cosmic Microwave Background (CMB) polarization missions.

Description

The Halve-Wave plate proposed as a polarization modulation element in future CMB missions plays a critical role in the overall system performance. This plate is a polarizer modulator which rotates in front of the instruments focal plain detectors. This component allows to measure the B-mode polarization of the cosmic microwave background radiation. This activity will be targeted to the following main areas: - Study and design of Half Wave Plate (HWP) architectures. - Address critical technological areas identifying potential solutions. - Perform critical breadboard development The activity will start with a careful assessment on the requirements. This activity will identify and select the mechanical, thermal and technological solutions and HWP architectures required to achieve the necessary accuracy and stability for a future CMB mission. These solutions/architectures will have to be demonstrated by critical breadboarding (as a minimum at electro and thermo-mechanical representative sample level). Specific attention will need to be given to: Capability to recover the Stokes parameters, capability for foreground removal, cryo operation (if applicable), cooling, power dissipation, noise, wear/tear, diameter, diameter/thickness ratio, anti-reflection coating. A technology roadmap to bring the technology to flight level shall be provided.

Deliverables

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HWP breadboard at sample level, technical data package


2013


CMP Polarisation Contract Duration:

18


T-8595


Fully consistent with the following Dossier: Technologies for (sub) millimeter wave passive instruments

Next generation sub-millimetre wave focal plane array coupling concepts


Title: Next generation sub-millimetre wave focal plane array coupling concepts

Total Budget: 400

Objectives

To develop methods to ensure efficient coupling to large format focal plane arrays.

Description

Observation of celestial features by space telescopes benefits from simultaneous data acquisition by co-located multi-frequency focal plane detector arrays. The benefit comes from the ability to use this co-located data to characterise with low systematic errors the foreground signals of celestial bodies, which is useful to extrapolate their signature at other frequencies, and therefore facilitate their removal when searching for background bodies. Therefore, focal plane elements that are able to operate in various spectral bands are required. At sub-millimetre wave bands, coupling of incoming radiation onto these focal plane elements is achieved by means of either horns or lenses. However, the relatively large size and number of these elements leads to large focal plane array sizes. A potential future B-mode Cosmic Microwave Background mission could be based for example on a dual-reflector telescope system. However, it is not obvious that dual-reflector systems are able to compensate for all aberrations at large offset positions with respect to the telescope’s focal point, therefore making it very difficult to achieve homogeneity of beam patterns across all focal plane detectors. This homogeneity is required to reduce the effect of systematic effects in the combined image obtained by the focal plane array. Therefore techniques to reduce the size of the focal plane are seen as very important enabling technologies. To solve this issue this activity will address the fabrication of multi-frequency/multi-polarization detecting elements. Consequently, the activity shall focus on: - the design of arrays of detecting elements able to operate at various (sub)mm-wave bands and dual polarizations. Methods to interleave several arrays working at different frequencies shall also be investigated. A technology roadmap to bring the technology to flight level shall be provided.

Deliverables

Optimum array layout to reduce size of the focal plane array. Results of the simulations run during the study. Breadboard of representative multi-frequency/dual polarization focal plane array.


2013


CMB Polarisation Contract Duration:

18


T-8595


Fully consistent with the following Dossier: Technologies for (sub) millimeter wave passive instruments

Near-sun mission heat-shield material assessment

Programme: TRP Reference: T224-001QT

Title: Near-sun mission heat-shield material assessment

Total Budget: 300

Objectives

To test under representative conditions the most promising couple of materials assessed within the Materials

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compatibility for the near-sun mission activity.

Description

The aim of this TDA is to address the compatibility of a C/C substrate with a BN coating and the capability of this combination of materials to sustain the thermals-irradiation conditions corresponding to a near-sun encounter mission scenario when used as primary heat-shield.

Deliverables

Test plan - test reports - samples


2012


Near-sun encounter missions Contract Duration:

18



Annex III

Detailed Description of ESA Strategic Initiative Activities

Detailed activity descriptions are provided in this annex for those ESA activities funded by the Strategic Initiative Programme.

Strategic Initiatives

A low-noise, low-power Readout ASIC for STIX - the Spectrometer-Telescope for Imaging X-rays on the Solar Orbiter

Programme: SI Reference: S217-048PA

Title: A low-noise, low-power Readout ASIC for STIX - the Spectrometer-Telescope for Imaging X-rays on the Solar Orbiter

Total Budget: 400

Objectives

The objective of the project is to customise an existing readout integrated circuit (ROIC) design to meet the requirements of the STIX instrument on the Solar Orbiter mission.

Description

The purpose of the work is to develop the detector readout technology for the Spectrometer-Telescope for Imaging X-rays on the Solar Orbiter mission. The main aims of the work will be (1) Simulation of the ROIC performance with regards to noise, dynamic range and power consumption, (2) implementation of the circuit as an Application Specific Integrated circuit, ASIC, (3) manufacture and test of the ASIC, (4) the development of packaging and interconnect to the CZT or CdTe crystal that maintains the performance of the ASIC and is suitable for the environment of the Solar Orbiter, and (4) the development/implementation/tests of firmware and software. The project work will end with the delivery of a flight prototype readout module and associated test result documentation.

Deliverables

Characterised ASIC, technical note and reports.


2012



15



Prototype ASIC Development for Large Format NIR/SWIR Detector Array


Title: Prototype ASIC Development for Large Format NIR/SWIR Detector Array

Total Budget: 400

Objectives

The goal of the project is to develop a prototype control and digitization application specific integrated circuit (ASIC) predominantly for large area near infrared (NIR) and short wavelength infrared (SWIR) detector hybrids.

Description

The goal of the project is to develop a prototype control and digitization application specific integrated circuit (ASIC) predominantly for large area near infrared (NIR) and short wavelength infrared (SWIR) detector hybrids. Two developments are targeted: 1. OSLO-2D - a prototype pixel readout integrated circuit (ROIC) that is compatible with state-of the art mercury cadmium telluride (HgCdTe, MCT) infrared (IR) and silicon PIN sensors. The readout will be implemented in very low-power and low-noise, submicron complementary metal-oxide-semiconductor (CMOS) technology. 2. FPADAC - a prototype focal plane array data acquisition and control system for the OSLO-2D, implemented initially with application specific standard products (ASSP, i.e. FPGA, A/D converters, micro-controllers). The FPADAC design has the option for future implementation in application specific integrated circuits (ASICs) CMOS technology. The FPADAC will provide the following major blocks: analog bias generator, A/D converter, digital control and timing generation, data memory and processing, and digital data interface. The proposed developments aim at a dedicated control and digitization ASIC for NIR/SWIR to ultimately match the Teledyne Imaging Systems HAWAII-2RG detector and the SIDECAR ASIC. The proposed development would lead to a European supply for the NIR/SWIR detector readout technology for future science missions.

Deliverables

Characterised ASIC , Technical Data Package, Tests.


2012

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18


T-8530


Hybrid solar power generator and energy storage system for space missions (HySolGen)


Title: Hybrid solar power generator and energy storage system for space missions (HySolGen)

Total Budget: 400

Objectives

The objective of this project is to continue the development of reversible Solid Oxide Fuel Cell (SOFC) technology for electrical power generation and energy storage space applications.

Description

The project will be divided in three tasks. The first task will work out the design andrequired specification for a SOFC based thermal electricity production unit and a SOFC based unit for energy storage. The specification will give target values for operation conditions such as temperature, fuel compositions and pressure, physical parameters such as size and weight and describe the heat management and required support system. The second task will focus on the reversible oxygen electrode for the SOFC unit. The task aims to develop a reversible oxygen electrode for SOFC without traceable degradation, either in fuel cell mode or electrolyser mode. The third task will be to demonstrate the feasibility of the core technology in the laboratory. The new materials for the oxygen electrode will be implemented in a full scale SOFC.

Deliverables

SOFC technology demonstrator system, technical notes, design specifications and final reports


2012



18



Next Generation Ion Emitter Modules


Title: Next Generation Ion Emitter Modules

Total Budget: 150

Objectives

The aim of the activity is to a re-design and lifetime test of emitter modules whilst incorporating new thermal isolation and addressing areas such as ease of replacement.

Description

AIT is a well known supplier of ion emitter modules for scientific missions including CLUSTER-II, ROSETTA and the upcoming NASA-MMS spacecraft. These modules are used to generate an ion beam with is used to actively control the spacecraft's floating potential (ASPOC) or as the core of a Secondary-Ion-Mass-Spectrometer (COSIMA) to analyse the chemical composition comet dust particles (used on ROSETTA). The core configuration of these modules has remained unchanged for the past 20 years, including the thermal isolation which is based on the LI-900 material (space shuttle heat shield). This material is out of manufacturing for 10 years and not available any more. The activity will include a re-design of the ion emitter modules with a new thermal isolation and include several changes such as an easy emitter replacement. This is mandatory for the preparation of upcoming opportunities such as COSIMA-II which is proposed as an instrument on the NASA Main Belt Comet Mission (AO in summer 2010). The thermal isolation directly influences the power requirement and a key aspect of this activity is to assess if the overall power budget constraints can be met. A COSIMA-II breadboard model (including the most recent micro-capillary ion emitter from the ongoing MMS-ASPOC development) will be produced and subjected to a 2,000 h lifetime test to demonstrate performance.

Deliverables

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Breadboard model ion emitter and technical data package


2012


Planetary science spacecraft and instruments

Contract Duration:

18



An On-Board Software Platform for the Next Generation of Infrared Astronomy Missions


Title: An On-Board Software Platform for the Next Generation of Infrared Astronomy Missions

Total Budget: 125

Objectives

The objective of this activity is to develop on-board data reduction and compression software for the next generation of infrared astronomy missions.

Description

Infrared detector arrays for space applications have grown rapidly in the last few years. With for example the Herschel/PACS instrument, the point has been reached, where the data can no longer be transmitted in raw format or in lossless compressed form, but needs to undergo lossy reduction steps on board in order to fit into the allowed downlink budget. As the data from Far-IR detectors are very different to visual wavelengths, standard techniques are not applicable. In order to take full advantage of the PACS software and data it is proposed to assess the in-flight performance of the relevant PACS software, look at the lessons learned, draw the conclusions and develop a baseline tool - a standard flight software platform based on PACS - to address the needs of the next generation of infrared astronomy missions.

Deliverables

Software tools validated using PACS data. Summary report.


2015


Future IR astronomy missions Contract Duration:

24



High Efficiency Horn Antennas for Cosmic Microwave Background Experiments and Far- Infrared Astronomy


Title: High Efficiency Horn Antennas for Cosmic Microwave Background Experiments and Far- Infrared Astronomy

Total Budget: 162

Objectives

The aim of this activity is the development of new technology solutions for the optimisation of horn antenna feeds and detector-coupling structures for next generation space missions. In particular, the activity will see the development and validation of software for the design of high-efficiency smooth-walled and partially-corrugated horns for future Cosmic Microwave Background (CMB) polarisation measurements, and for the design and analysis of multi-moded feed structures for far infrared and mid-infrared cavity and waveguide coupled detectors such as those intended for SAFARI (SPICA).

Description

This activity will addess the development of new methods for the design and analysis of horn antennas and waveguide structures suitable for applications requiring densely packed array configurations. The following waveguide structures will be studied: (a) General spline profiled, single-moded, smooth-walled and partially-corrugated horns producing very low sidelobe levels and good polarisation purity suitable for array applications particularly addressing mass, volume and

Page 4 of 12

manufacturing issues in CMB B- polarisation experiments. (b) Multi-moded smooth walled horns with low side lobe levels for increased throughput for both CMB and far-infrared applications where diffraction-limited resolution is not required. (c) Modelling of the optical coupling to probe coupled detectors in waveguides and absorber-coupled devices in cavities. The core of the activity will be the development of software for designing optimised horns, smooth-walled or partially-corrugated, to (a) optimise the detector coupling in polarised CMB experiments horns, (b) reduce the variation in performance that is an inevitable result of manufacturing tolerances in traditional corrugated designs, and (c) minimise manufacturing costs and total horn mass. The appropriate optimisation methods incorporating and further developing existing horn analysis software, adapting it for smooth-walled and partially-corrugated, spline-profiled horns and waveguide cavity structures will be addressed. A test subsystem and appropriate components will be manufactured in order to allow approach validation and code verification through measurement of performance in a dedicated millimetre-wave test facility.

Deliverables

Technical Data Package, Software Tool, Test Component Hardware


2012


Cosmic Microwave Background Polarisation, SAFARI (SPICA)

Contract Duration:

24



Novel silicon photomultiplier configurations for high energy astrophysics applications


Title: Novel silicon photomultiplier configurations for high energy astrophysics applications

Total Budget: 200

Objectives

The objective of this activity is to investigate Silicon Photomultiplier (SPM) arrays as low-resource, high-performance scintillator readout detectors for high energy astrophysics applications.

Description

Among the top priorities for high-energy astronomy in the coming decade are sensitive surveys in the hard X-ray/soft gamma-ray (10 keV - 600 keV) and medium-energy gamma-ray (0.1 - 20 MeV) bands. Such surveys will significantly advance our knowledge of a wide variety of non-thermal, high-energy physical processes in the universe. All-sky observations will require a space-borne gamma-ray telescope with a large collecting area and a large detector volume, with a wide field-of-view, good angular and energy resolution, and sophisticated background rejection abilities in order to achieve the required levels of sensitivity. Recent technological advances in the development of both new scintillator materials (e.g., LaBr3:Ce) and new scintillation light readout devices (e.g., Silicon Photo-Multipliers) however, promise to greatly improve the observational capabilities of future scintillator based gamma-ray telescopes, while retaining the relative simplicity, reliability, large collection volumes, and low-costof scintillator instruments. This activity will investigate Silicon Photomultiplier (SPM) arrays as low-resource, high-performance scintillator readout detectors for high energy astrophysics applications. Reference application missions of interest to the high energy community such as the GRIPS mission concept will be utilised in this activity. A detailed software model of the required SPM based calorimeter system will be developed and used to inform the design and development of a building block detector module, based on SensL SPM arrays and LaBr3 scintillators. The data from initial modelling will be used to improve early experiments and as a feedback tool in the process of developing the optimum detector and scintillator parameters. The following major tasks are forseen in this activity: - Review measurement requirements of reference application mission - Perform modelling studies and develop design specification - Procurement, assembly and test of hardware

Deliverables

Scintillator/Detector Model, Characteristed Prototype Modules, Technical Data Package


2012

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High Energy Astrophysics, Gamma Ray

Contract Duration:

18



Development of a THz Local Oscillator for Space Science Heterodyne Applications


Title: Development of a THz Local Oscillator for Space Science Heterodyne Applications

Total Budget: 200

Objectives

The objective of this activity is to develop a low noise source of mm-wave and sub-mm (THz) radiation for use in heterodyne detection applications such as spectroscopic systems and interferometers.

Description

THz heterodyne observation's potential is far from being fully realized due to source-technology limitations. The available solid-state, CW sources with enough power to serve as local oscillators (LOs) above ~1 THz are currently limited to ~10% in bandwidth and ~1.6 THz in maximum frequency. Additionally, the lack of high spectral purity, frequency agile sources hinders laboratory spectroscopy, and receiver/component characterization. The objective of this activity is to develop laser components to overcome these limitations. The work is forseen to consist of the following major tasks: - Study of Commercial Off The Shelf (COTS) components - Baseline study of THz generation using available two section laser diodes - Design of electronic feedback techniques for control of LO generation in two section lasers - Development of second generation bimodal two-section laser diodes - In depth baseline study of second generation components in LO generation The activity will demonstrate LO performance compatible with the requirements of a reference application to be specified by the Agency.

Deliverables

Packaged Devices, Technical Data Package


2012


Laplace, Planetary Atmosphere Sounders

Contract Duration:

18



Feasibility study for novel design of Fibre Coupled Deep UV LEDs for Charge Control of Proof Masses


Title: Feasibility study for novel design of Fibre Coupled Deep UV LEDs for Charge Control of Proof Masses

Total Budget: 200

Objectives

The objective of this activity is to develop a deep UV Fibre Couple Light Emitting Diode (LED) aimed at meeting the requirements of the LISA mission where such a light source is required by the proof mass Charge Management System (CMS).

Description

The current LISA Pathfinder Charge Management System (CMS) is based on UV mercury-vapour lamps. An alternative design for the LISA CMS could be based on Light Emitting Diodes (LED). Compared with mercury lamps, the LED-based CMS offers the advantages of small size, lightweight, lower power consumption, faster response time and longer lifetime. Lifetime in particular is the main disadvantage of the Mercury lamps in the LISA application, as the CMS would require a substantial mass and volume to guarantee the 5-year mission duration with the required redundancy. This main tasks of this activity are: - Growth of 245 nm UV LEDs - Fabrication of integrated reflector microLEDs emitting at 245 nm

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- Packaging of LEDs on submounts to couple low loss UV compatible fibres - Testing of device performance and reliability

Deliverables

Fibre coupled UV LED, Technical Data Package including Test Reports


2012


LISA Contract Duration:

16



Feasibility Study into the Use of InAIN Based High Frequency Transistors for Space Application


Title: Feasibility Study into the Use of InAIN Based High Frequency Transistors for Space Application

Total Budget: 200

Objectives

The objective of this activity is to establish the feasibility of the use of InAlN based transistors for space applications.

Description

The activity consists of a feasibility study into the use of InAlN, rather than AlGaN with the aim of obtaining improved performance and reliability microwave field effect transistors (FETs). The activity will particularly address the promise of increased reliability through utilising the InAlN systems ability to allow the fabrication of very low strain devices. In addition the radiation hardness and high temperature operation of such devices is attractive in harsh environment applications. High frequency InAlN devices will be prepared, fabricated and tested at high frequencies. Thermal testing in the range of -60 to 250 deg C and accelerated storage testing up to 400 deg C will be conducted. Performance modeling of packaged and bare die devices will be undertaken to allow comparison with existing AlGaN devices and identification or area affecting reliability. The activity is forseen to consist of five major tasks: - Preparation of InAlNlayer structures on Sapphire and SiC substrates - Fabrication of devices through appropriate processing - Modelling to investigate device thermal and electrical performance - Device bonding and packaging - Device electical and themal testing

Deliverables

Characterised Packaged Devices, Technical Data Package


2013



24



Packaged Devices, Technical Data Package including performance characterisation measurements

Numerical Simulation Tool for Parachute Performance


Title: Numerical Simulation Tool for Parachute Performance

Total Budget: 200

Objectives

The objective of this proposal is to provide a numerical method for the accurate prediction of the aerodynamic performance of supersonic parachute deployment.

Description

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Aerodynamic deceleration is used in Earth and extra-terrestrial atmospheres for both entry-probes and sample return type missions. Parachutes and inflatable decelerators are mass efficient and are therefore important technologies for any Science mission that requires a planetary descent and landing. The parachute should have a high drag to weight ratio, provide predictable inflation and drag performance and ensure the payload is stable during descent. The parachute will have to inflate and operate in the supersonic flow regime so the prediction of the interaction between the canopy and flow is critical in order to design the landing phase correctly. The objective of this proposal is to provide a numerical method for the accurate prediction of the aerodynamic performance of supersonic parachute deployment. Reference study cases will be defined by the Agency. The major tasks foreseen in this activity are: - Review the current fluid-structure interaction methods available in the public domain and select method(s) to be applied- Selection of a code which implements the chosen method and the parachute/flow physics with sufficient accuracy - Review of supersonic parachute tests and data extraction for model studies - Verification and sensitivity study of model

Deliverables

Software Models/Test Results, Technical Reports


2012


Planetary Entry, Sample Return Contract Duration:

18



Numerical Modelling Tool for Evaluation of Sloshing-Reaction Control System Coupling


Title: Numerical Modelling Tool for Evaluation of Sloshing-Reaction Control System Coupling

Total Budget: 200

Objectives

The objective of this proposal is to develop a validated numerical method, with the focus on the computational fluid dynamics (CFD) implementation, to couple chemical propellant sloshing with the spacecraft reaction control system (RCS).

Description

The focus of this activity is on the CFD implementation of a coupled slosh-RCS control system to optimise the feedback loop between the fuel slosh, the RCS and the attitude control. All spacecraft that use chemical propulsion exhibit some degree of sloshing e.g. low amplitude linear lateral sloshing, high amplitude nonlinear lateral sloshing, low amplitude axial sloshing etc. The minimisation of the sloshing upon the spacecraft pointing performance e.g. following a reorientation maneuver through validation software modelling is the aim of this activity. The following major tasks are foreseen in this activity: - Assess requirements for a coupled sloshing-RCS approach, reviewing the problem from the sloshing and RCS perspectives and identify the most important coupling mechanisms - Development of the coupled approach: assess which codes offer the best sloshing prediction and interface with the RCS; assess the requirements from the CFD solver including the accuracy of the free surface dynamics, ability to interface with the RCS data, control of information and access to the source code/user subroutines; develop a feedback loop between the flow boundary conditions (applied accelerations), measured outputs and RCS simulated thruster forces. - Breadboard testing to include representative hardware in the loop - Feedback of test results into model, refinement of numerical model, production of validated model for slosh-RCS modelling

Deliverables

Validated Software Model, Technical Reports including Hardware Test Results


2013



18



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Robust motion control, with active vibration damping, of under-actuated flexible structures


Title: Robust motion control, with active vibration damping, of under-actuated flexible structures

Total Budget: 160

Objectives

The objective of this activity is to investigate the application of wave-based control to flexible space structures.

Description

Robust control of complex flexible structures, large or small, is a challenging problem of direct relevence to science missions where minimisation of weight is paramount. Typically one is attempting to combine position control and active vibration damping using much fewer actuators than degrees of freedom, and frequently only one actuator, or one actuating body. Then standard control strategies perform poorly and are nonrobust to modelling errors, system variability and non-ideal actuator responses. A relatively new technique called "wave-based control" (WBC) has been developed to address many such problems. It promises elegant, robust, rapid and precise feedback control, which is achieved by understanding, measuring and controlling the two-way energy and momentum interchange between the actuator and the flexible system under control. This activity will investigate the application of wave-based control to flexible space structures. It is envisaged that the deployable structure of the IXO spacecraft will be used as a test case for determining the performance improvements (e.g. structure settling time following spacecraft slewing) and resource savings (e.g. mechanism and structure optimisation). Other potential missions concepts consisting of elements which would benefit from this approach will also be considered. The main tasks to be addressed in this activity are: 1. Apply the wave-based control strategy to models of chosen space structures 2. Investigate active vibration control aspects 3. Investigate the implications for the motion actuators: locations, dynamic responses, energy budget, etc. 4. Investigate the added value in the control information, especially for monitoring system dynamics 5. Consider wider applications of wave-based control in other space applications

Deliverables

Software Models and Tools, Study Report


2012


IXO, Deployable Structure Missions Contract Duration:

15



Development of a web-based scientific data analysis and distribution tool


Title: Development of a web-based scientific data analysis and distribution tool

Total Budget: 200

Objectives

The objective of this activity is the creation of a software system which can be applied to many future ESA space missions where data from multiple sources and in different formats needs to be integrated and new techniques in semantic web representation and analysis of data can be applied to provide new information from the merged data.

Description

Each space mission generates data formatted for the particular needs of the space mission and related scientific research. The scientific community typically has access to this mission data through internet access and via method access methods ranging from FTP, HTTP sockets to web based front ends via a dedicated web site. Many development tools now exist to take a legacy system or data source and provide a web interface to access the data. Therefore current mission data sources based on traditional FTP and HTTP interfaces can easily be extended to also provide a web service based access to information. The aim of this activity is to develop such a system framework with requirements derived from the user community. The framework will be applied to a test website. The major tasks forseen is this activity are:

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- Define, review and agree functional and non functional requirements with user community - Define, review and agree system requirements, along with an assessment of the existing, emerging technologies and standards - Define, prepare, procure and present the architectural design of the system - Implementation of the system framework for integration of distributed data, ease semantic classification, integration of a reasoning engine and provision of semantic searching, web based viewing and access to data via web push technologies - Perform verification of the development framework system, integrate the system into the selected test site server, use the framework to create the test web application and deploy the developed solution to selected scientific community members

Deliverables

Framework System Software, Framework Test Demo Website, Technical Documents


2013



18



Multilayer coatings for IXO

Programme: SI Reference: S216-009MM

Title: Multilayer coatings for IXO

Total Budget: 450

Objectives

The development of multilayer coating for IXO optics with a resultant improvement of reflectivity across a wider X-ray energy range.

Description

Previous work was done for ESA on multilayer coatings addressed the requirements of the XEUS mission candidate. The current Cosmic Vision L-class mission candidate is the International X-ray Observatory, IXO, with different boundary conditions from those of XEUS. With its shorter focal length (~20m, versus 35-50m for XEUS), there is interest to extend the HE response of the IXO optics beyond that provided by the core optics with metal coating. The definition of IXO progressed to a sufficient level to define the IXO telescope optics geometry to the detail required for focused developments and optimisation of the reflective coatings. In fact such developments would appear particularly timely at this time, since they could accompany the system level industrial studies and the further TDP implementation. What would be beneficial for IXO now, is to better understand the coating options for a focal length of 20m configuration optics, with a radius extending from 0.3 to 1.9 m. The incidence angles are thus rather large, compared to standard multilayer coated optics. The envisaged activity would: explore the technical possibilities for multilayer designs, perform simulations of the expected telescope performance, produce samples which would demonstrate the feasibility of the production and measure the characteristics of such coatings; produce coated mirror plates with the required pattern (permitting the bonding to stacks). Ideally the resulting multilayer coating would be finally demonstrated in an optical unit for IXO. In coordination with existing ongoing and planned activities dealing with the development of the IXO optics, coated mirror plates could be supplied by this DK activity and assembled into optical units. As a special case of a multilayer, significant increase in the soft X-ray response below 2 keV can be obtained by a simple C overcoat on both Ir and Pt. Optimisation of the processes involved might merit investigation. An important factor would be the requirement to maintain the angular resolution of the system. Therefore not only reflectometry but also scattering analysis and metrology will be necessary. As an ESA undertaking, the access to the X-ray metrology facilities (Bessy2 in particular) could be provided. This will ensure coherent measurements with results fully compatible and comparable with previous activities in this area.

Deliverables

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multilayer design trade-off description, simulations of the expected layer performance, samples demonstrating production feasibility and coating characteristics; coated IXO samlple mirror plates


2012


IXO Contract Duration:

15



Multilayer coated silicon pore optics stack production and test


Title: Multilayer coated silicon pore optics stack production and test

Total Budget: 430

Objectives

The objective of the activity is the production and test of a multilayer coated mirror stack.

Description

The activity will build upon the preceding Multilayer Coatings for IXO activity and demonstrate the production of a multilayer coated silicon pore optics stack consisting of a TBD number of mirror plates. The optimised multilayer for the innermost radius of 0.25 m and focal length of 20 m will be applied to multiple wedged and ribbed SPO mirror plates such that the plates can be bonded together to form a stack. Particular emphasis will be placed on the optimisation of the masked deposition aspect of the coating process. The mirror module will be subjected to full illumination and pencil beam X-ray and environmental testing.

Deliverables

Technical data package. Multilayer coated SPO mirror stack.


2013


IXO Contract Duration:

12



Three-dimensional CZT high resolution detectors for high energy astrophysics applications


Title: Three-dimensional CZT high resolution detectors for high energy astrophysics applications

Total Budget: 192

Objectives

The objective of this activity is to develop and test a high energy three dimensional position sensitive CZT prototype detector employing a novel read-out scheme.

Description

The development of Compton telescopes and of new concentrating (e.g. multilayer mirror) telescopes for hard X-rays (10 -100 keV) as well as focusing gamma-ray instruments based on Laue lenses operating from ~60 keV up to a few MeV is particularly challenging. The instrumentation for these types of telescopes requires detectors of high efficiency, energy resolution in the order of a few keV and the capability of three dimensional (3D) position sensitivity. Fine spectroscopic performance combined with sub mm position resolution will make it possible to perform 3D reconstructions of the photon interaction. This feature will help to reduce detector background and is essential for the Compton Camera application. Semiconductor detectors based on CdZnTe (CZT) compounds are well suited to meet these requirement. These detectors can achieve excellent spectral performance with energy resolutions approaching those of Ge detectors, albeit without the need to cool them to cryogenic temperatures. CZT pixel and strip detectors have reached sub mm position resolution in 2D imaging configurations.

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of 12

This activity will develop and test a high energy (> 20 keV) 3D position sensitive CZT prototype detector employing a novel read-out scheme. A reference case will be chosen to demonstrate the potential of such detectors to a potential future high energy mission application. The following major tasks are foreseen in this activity: - Requirements consolidation and design specification - Detailed design - Procurement, fabrication and assembly of the CZT detectors - Test and evaluation of the prototype detector, synthesis of results

Deliverables

Characterised Detector Module, Technical Data Package


2012


High energy astrophysics Contract Duration:

16



Annex IV

Detailed Description of National Technology Development Activities

Detailed activity descriptions are provided in this annex for the M3 mission candidates LOFT and STE-QUEST. Additional national activities will be added for the other candidates as and when they are identified.


Capillary-plate collimator for the Large Area Detector

Programme: National Reference: N216-116SY

Title: Capillary-plate collimator for the Large Area Detector

Objectives

To develop an increased open area ratio (OAR) capillary plate X-ray collimator for the Large Area Detector (LAD)

Description

A key element of the LOFT LAD instrument is the capillary-plate X-ray collimator, which is based on the technology of micro-channel plates (MCPs). MCPs have flown on several past missions (e.g., Einstein, EXOSAT, ROSAT,..). A MCP with similar size as that required for LOFT is in operation on the HRC of Chandra. The main difference with respect to existing technology is the LOFT requirement of OAR = 80%, compared to typical OAR between 50% and 70%. Preliminary activities at national level shall be continued to demonstrate the required performance and TRL.

Deliverables

Prototype samples, technical data package


2014


LOFT Contract Duration:

30



Large-area Silicon Drift Detectors


Title: Large-area Silicon Drift Detectors

Objectives

Delta-development of existing large-area Silicon Drift Detectors (SDD) to meet the requirements of the LOFT LAD and WFM instruments.

Description

The primary enabling technology for the LOFT payload (for both the LAD and WFM instruments) is the large-area Silicon Drift Detectors (SDDs). SDDs have been developed for the Inner Tracking System (ITS) in the ALICE experiment of the Large Hadron Collider (LHC) at CERN. LAD detectors require technology developments to increase the size by 43%, the thickness by 50% and the anode pitch by 190% over the established technology, while improving the energy resolution. Further developments are required to reduce the power consumption. Preliminary activities at national level shall be continued to demonstrate the required performance and TRL.

Deliverables

Prototype detectors, technical data package


2014



30



Ultra-low noise high-speed detector read-out ASIC


Title: Ultra-low noise high-speed detector read-out ASIC

Objectives

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Development of Ultra-low noise high-speed detector read-out ASIC for the LAD instrument

Description

A high-density read-out system, based on ASICs (Application Specific Integrated Circuits) is needed for the front-end electronics of the LAD instrument of the LOFT mission because of the requirements of fine pitch, small parasitic capacitance, low-power consumption and the need for tiling. These conditions imply a design with an ultra-low noise and high-speed front-end stage and a digital signal processing section (trigger logic, A/D converters, ancillary functions) with almost negligible crosstalk to the analog section. Preliminary activities at national level shall be continued to demonstrate the required performance and TRL.

Deliverables

Prototype ASIC, technical data package


2014



30



Page 3 of 10


Delta development and qualification of Pharao Tube for Next Generation (NG) Pharao

Programme: National Reference: N206-001PA

Title: Delta development and qualification of Pharao Tube for Next Generation (NG) Pharao

Objectives

Delta development and qualification of Pharao Tube for Next Generation (NG) Pharao

Description

Accommodate new Rb-Atom dispenser and associated technology in Pharao tube as well as qualification thereof. This includes possible changes to getters, the vacuum pump(s), the microwave cavity design Tasks shall include: 1) Identify changes to Pharao vacuum tube, e.g. getters, microwave cavity design (to Rb frequency around 6.8 GHz), vacuum pump. 2) Design and breadboard Pharao Next Generation tube assembly with Rb-Source 3) Test and verify performance levels for Pharao NG up to 5 years lifetime 4) Environment testing for STE-QUEST to TRL 5

Deliverables

Bredboard, technical data package


2014


STE-QUEST Contract Duration:

12



Delta development and qualification of Pharao Microwave source


Title: Delta development and qualification of Pharao Microwave source

Objectives

Delta development and qualification of Pharao Microwave source

Description

The Pharao microwave source needs adaption from 9.2 GHz (Cs frequency) to 6.8 GHz (Rb frequency). This involves the change or tuning of components in the microwave source Tasks shall include: 1) Identify changes to the microwave source, especially necessary component changes, components which can be directly tuned to the new frequency, and components that can be kept unchanged. Investigate the possibility to use an external clock reference (e.g. MOLO) besides the internal USO. 2) Design and breadboard Pharao Next Generation microwave source 3) Test and verify performance levels for Pharao NG up to 5 years lifetime 4) Environment testing for STE-QUEST to TRL 5

Deliverables

Breadboard, technical data package


2014



12



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Development and qualification of Pharao-Next Generation Laser Source for Rb atoms


Title: Development and qualification of Pharao-Next Generation Laser Source for Rb atoms

Objectives

Development of laser operating at Rb wavelengths.

Description

Development of 780 nm laser for Rb 85/87 cooling (linewidths smaller than 1 MHz, few 100mW) and associated verification and testing (including lifetime to guarantee 5 years operation). The laser system shall include an output power and spectrum monitoring system. Tasks shall include: 1) Identify and trade laser technology (e.g. extended cavity w/ original Pharao lasers or direct 780 nm generation) to be used 2) Test and verify performance levels for laser source 3) Environment testing for STE-QUEST to TRL 5

Deliverables

Laser devices, technical data package


2014


STE-QUEST, Fundamental Physics Contract Duration:

24



Delta-development and test of Pharao Next Generation instrument control unit


Title: Delta-development and test of Pharao Next Generation instrument control unit

Objectives

Delta-development and test of Pharao Next Generation instrument control unit

Description

Verify the functionality of the Pharao UGB (instrument control unit) for application in PNG. Tasks shall include: 1) Identify the necessary changes to the UGB to accommodate PNG and breadboard the ICU 2) Test and verify performance levels for Pharao NG up to 5 years lifetime 3) Environment testing for STE-QUEST to TRL 5

Deliverables



2014



12



Integration, test and verification of Pharao-Next Generation (PNG) clock


Title: Integration, test and verification of Pharao-Next Generation (PNG) clock

Page 5 of 10

Objectives

Integration, test and verification of Pharao-Next Generation (PNG) clock incorporating sub-system level developments on laser, tube, microwave source, instrument control unit.

Description

In order to demonstrate the required performance at payload system level, the breadboards developed in the sub-system activities shall be combined on a full scale breadboard or engineering model of the full Pharao system that is flight-representative. Tasks shall include: 1) Integrate the various subsystems of PNG (Tube, microwave source, power supply, ICU, laser system). 2) Test and verify performance levels for Pharao NG up to 5 years lifetime 3) Environment testing for STE-QUEST to TRL 5

Deliverables



2014



12



Development and qualification of a dual-species Rb 85/87 Atom Interferometer Physics Package


Title: Development and qualification of a dual-species Rb 85/87 Atom Interferometer Physics Package

Objectives

Development and qualification of a dual-species Rb 85/87 Atom Interferometer Physics Package

Description

Development and qualification of the dual-species Rb 85/87 Atom Interferometer Physics Package, including the hot atom reservoir, the MOT (1st cooling stage), the ODT/atom chip (2nd cooling stage), the Raman interrogation area (mirrors), magnetic shields, temperature control, vacuum system and all necessary electrical and optical interfaces. Preparation of an ultra-cold BEC atomic sample of 10E6 atoms shall be possible within <5 seconds through all cooling stages. Vacuum shall be 10E-9 - 10E-8 Pa (interrogation area - preparation area). Tasks shall include: 1) Identification of off-the-shelf or custom components 2) Design and breadboarding of vaccum tube with suitable interfaces and environment control 3) Verification of performance, environment and lifetime test (5years) to TRL 5

Deliverables



2014



36



Development and qualification of Laser Package for the Atom Interferometer


Title: Development and qualification of Laser Package for the Atom Interferometer

Objectives

Development and qualification of Laser Source for the Atom Interferometer Atom Source

Description

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Development and qualification of Laser Source for the Atom Interferometer Atom Source, including cooling lasers for the MOT/ODT (1000mW, 1MHz FWHM@1ms, suitable for Rb85,87 operations), Raman Lasers for dual species Rb (85, 87) atomic beam splitting (~200mW, 0.1MHz FWHM(1ms)), optical elements (AOMs, fibres, splitters...) and monitoring and control system for output spectrum and power control. Preparation of an ultra-cold BEC atomic sample of 10E6 atoms shall be possible within <5 seconds through all cooling stages. Tasks shall include: 1) Identification and choice of Laser technology 2) Design and breadboarding of an optical bench housing all Laser Source systems and optical elements, including lasers3) Verification of performance, environment and lifetime test (5years) to TRL 5

Deliverables

Laser devices, technical data package


2014



24



Development and qualification of the Atom Interferometer control electronics


Title: Development and qualification of the Atom Interferometer control electronics

Objectives

Development and qualification of the Atom Interferometer control electronics

Description

Delta-development and qualification of the AI control electronics from Pharao UGB (Pharo control electronics unit). New development of parts that are to be used for the different components on the laser bench, the collection of CCD images of the atom cloud, the experiment control logic, RF subsystem for Raman Laser control, and the photo-diode. Tasks shall include: 1) Identification of off-the-shelf or custom components 2) Design and breadboarding 3) Verification of performance, environment and lifetime test (5years) to TRL 5

Deliverables



2014



15



Integration, test and verification of the Atom Interferometer instrument


Title: Integration, test and verification of the Atom Interferometer instrument

Objectives

Integration, test and verification of the Atom Interferometer (AI) instrument.

Description

Integration of Laser Source, Physics Package, ICU and associated equipment to verify full AI performance.

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Taks shall include: 1) Design of experiment for flight 2) Integration of components into flight representatitve setup 3) Verification of performance, qualification to TRL 5

Deliverables



2014



12



Development and space qualification of high finesse reference optical cavity and laser head


Title: Development and space qualification of high finesse reference optical cavity and laser head

Objectives

Development and space qualification of high finesse reference optical cavity.

Description

Development and space qualification of high finesse reference optical cavity and mounting/housing to be used in the Microwave-Optical Local Oscillator (MOLO) for 1064 nm and integration and test with reference laser source to demonstrate the required performance levels of the full stabilized laser head (laser stabilized to the high-finesse cavity) and space environment qualification. The stability of the output shall be lower than ADEV = 1E-15 between 1s and 100 s integration time after linear drift removal, the frequency drift of the optical reference shall be smaller than 2E-16/s in any interval of 1000s. Tasks shall include: 1) Follow up on results of previous cavity studies and design and breadboard the stabilized laser head, including the choice of reference laser technology (@1064 nm) 2) Test the breadboard to verify required performance levels 3) Environment testing of breadboard (or at least the components) to TRL 5

Deliverables



2014



18



Delta Development and space qualification of a frequency generation, comparison and distribution unit


Title: Delta Development and space qualification of a frequency generation, comparison and distribution unit

Objectives

Delta Development and space qualification from the ACES FCDP to a frequency generation, comparison and distribution unit for locking MOLO to Pharao and distributing the clock signal to MWL, LCT, GNSS, etc.

Description

The Frequency Generation, Comparison, and Distribution Package (FGCD) is the central node of the clock instruments on STE-QUEST and therefore playing therefore a key role within the P/L. The FGCD receives an ultra-stable and ultra-pure reference frequency around 10 GHz from a Microwave-Optical oscillator (MOLO) and generates several coherent reference frequencies to be distributed to other elements on-board by integer frequency division. The signals generated

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are: towards microwave link (1GHz, 100MHz), to MOLO (250 MHz), to laser link coding/modulation (125 MHz) and GNSS Rx (10, 20 MHz). It shall also lock the Pharao Next Generation (PNG) internal USO to the reference using e.g. a digital PLL and measure the MOLO phase-noise against the PNG. FGCD shall also serve as an on-board time-scale, providing epoch pulses at 1Hz and 1kHz, as well as numerical date&time information. On-board time shall be synchronise-able to a UTC reference. Instrinsic stability shall be better than ADEV < 10E-14/tau Nominal on-board frequency offset step size < 10E-15.

Deliverables



2014



18



Microwave-optical frequency generation using optical frequency comb technology


Title: Microwave-optical frequency generation using optical frequency comb technology

Objectives

Development and space qualification of a ultra-stable and spectrally pure coherent microwave-optical generation using optical frequency comb technology.

Description

Development and space qualification of a ultra-stable and spectrally pure coherent microwave-optical generation using optical frequency comb technology, to convert the optical reference input from a stabilized laser head to the microwave domain at the repetition rate of the frequency comb or multiples thereof in the order of 1 to a few 10s of GHz, preferably 10 GHz. Tasks shall include: 1) Identify and trade optical frequency comb technology to be used (e.g. fibre-based, WGMR, Ti:Saphhire) especially with respect to future space qualification, achievable TRL for STE-QUEST, and performance levels in flight. 2) Test the breadboard to verify required performance levels 3) Environment testing of breadboard (or at least the components) to TRL 5

Deliverables



2014



24



Integration, test, and verification of MOLO


Title: Integration, test, and verification of MOLO

Objectives

Integration, test, and verification of stabilized Laser Head and Optical Frequency Comb (OFC) at subsystem level to demonstrate performance and test for environment and lifetime.

Description

Integration, test, and verification of stabilized Laser Head and Optical Frequency Comb (OFC) at subsystem level to demonstrate performance and test for environment and lifetime.

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of 10

Deliverables

Breabboard, technical data package


2014



12



Annex V

Justifications for Proposed Tendering Procedure

and Information Notes

Justification for Proposed Tendering Procedure: DN/S

Industrial Policy Committee

Reference Title Firm Fixed Price (Keuro) Proposed Bidder

C216-119PA Bessy II 12m Station 200 PTB (DE)

Justification: A critical aspect of the silicon pore optics development program is the ability to measure the mirror performance at an X-ray facility. ESA has access to the only suitable facility at Bessy II in Germany. Due to the evolution from IXO to ATHENA it is now required to upgrade the X-ray facility to allow measurements at a reduced focal length of 12 m.

The Physikalisch Technische Bundesanstalt (PTB) controls and operates the Bessy II PTB X-ray facility, including the Fixed Energy Beamline.

Justification for Proposed Tendering Procedure: DN/C Industrial Policy Committee


C218-001MP Characterisation of radiation for high speed entry

750 IST-IPFN(PT) and subcos.

Justification: This activity belongs to the special measures to Portugal for geo-return balance in the Science Programme. Under a running ESA contract the Kinetic Shock Tube facility is being built in Portugal. The proposed new activity is implemented for enabling the effective use of this facility for SRE programmes.



C205-019EC Autonomous GNC Technology for NEO Proximity, Landing and Sampling Operations - Phase 2

500 GMV (ES) and subcos.

The original activity was split in two with Phase 1 funded under TRP with procurement policy of Open Competition. It is now intended to initiate Phase 2, funded by CTP, in direct negotiation with the consortium of Phase 1.



C221-002MT Performance verification and qualification of vibration free Hydrogen sorption JT cryo-coole

400 University of Twente (NL)

Justification: Under a previous ESA contract a vibration free Hydrogen sorption cooler has been developed by the University of Twente (NL). The application of this cooler to the ECHO mission requires dedicated measurements on the existing hardware at Twente.

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Justification for Proposed Tendering Procedure: DN/S Industrial Policy Committee


T217-058MM Development and stabilisation of octave spanning optical frequency combs based on silicon-nitride planar high-Q microresonator technology

200 EPFL (CH)

Justification: The group at EPFL are the European leaders in this technology leader and the sole group currently capable of fulfilling the goals of this activity.

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Information Note regarding the NIR Large Format Sensor Array, T217-059A, -B, -C This activity was originally approved by the IPC as T215-01MM, see ESA/IPC(2008)3, for 1500 k€, envisaging an implementation in two parts: part 1: 300 k€ and part 2: 1200 k€. Following the TEB recommendation and the programmatic needs, it was decided to place three parallel contracts for the first part of the activity, each for a value of 300 k€. The three selected contractors were: (1) CEA-LETI (France), (2) Selex-Galileo (United Kingdom), and (3) Qinetiq (United Kingdom). The contracts for part 1 of the activity required the three contractors to submit an updated proposal for part 2 of the activity. Qinetiq has in the meantime concluded part 1 of the activity, but has closed the respective business area. Therefore, part 2 of the activity is not foreseen with Qinetiq. CEA-LETI and Selex-Galileo have both successfully completed part 1 of the activity and submitted updated proposals for part 2. The TEB is now being convened to evaluate the proposals for part 2 of the activity from both contractors In view of the strategic importance of this activity, it is intended to extend both contracts for part 2, each extension for a value of 1200 k€, provided that the proposals from CEA-LETI and Selex-Galileo are both acceptable. The AC is invited to take note of the intended approach for part 2 of the activity.