european space agency industrial policy...

ESA unclassified ESA/IPC(2010)81 For official use Att.: Annexes

Paris, 14 April 2010 (English only)

EUROPEAN SPACE AGENCY

INDUSTRIAL POLICY COMMITTEE

COSMIC VISION 2015-2025

TECHNOLOGY DEVELOPMENT PLAN

Programme of Work 2009-2012 and related Procurement Plan SUMMARY The present document presents the currently proposed activities in the Basic Technology Programme (TRP), the Science Core Technology Programme (CTP) and national initiatives supporting the implementation of ESA’s Cosmic Vision 2015-2025 Plan. This update of the plan considers the outcome of the M-class mission down-selection process and associated SPC recommendations. REQUIRED ACTION IPC is invited to approve the work plan for the year 2010 and the connected procurement proposals. VOTING RIGHTS AND MAJORITY REQUIRED Simple majority of member States, present and voting.

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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 subsequently updated as ESA/IPC(2009)78 approved by June 2009 IPC and ESA/IPC(2009)143 approved by November 2009 IPC. This version of the TDP presents, in particular, an update of the technology developments required by the Cosmic Vision program following the completion of the M-class down-selection process as outlined in ESA/SPC(2010)3 rev. 1. The activities presented herein are those selected following the TECNET review process conducted in September 2009. Activities under ESA responsibility are presented for implementation. Activities under national member state responsibility are provided for information. The previous version of this plan contained the technology development activities identified for all six M-class mission candidates with the caveat that only the activities related to the actually down selected candidates would be implemented. This was necessary in order to maintain correct phasing between the technology development and overall Cosmic Vision programme schedules. The down-selection decision sees Euclid, PLATO, and Solar Orbiter proceed forward with the clear understanding that only two of these will eventually be proposed for implementation in the framework of the M1/M2 Cosmic Vision launch slots. A decision on the JAXA-led mission SPICA will be made at the June 2010 meeting of the SPC. As such the TDAs for the SPICA mission contained within this plan will not be implemented until the outcome of the SPC meeting is known. The plan covers the period 2009-2012 for both the Cosmic Vision mission candidates and the future science mission themes. 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. Three AOs were foreseen, defining the three “slices” of the plan. The down selection review and decision process is described in ESA/SPC(2009)3, rev.1. The AO for the first slice of the CV plan was issued in March 2007, and from the 50 proposals received, five M-class (including one mission of opportunity) and three L-class (including LISA) mission candidates were selected for assessment. Subsequently, Solar Orbiter was reclassified as the sixth M-class mission candidate

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(ESA/SPC(2008)25) and Laplace was selected as the outer planet mission within the CV1525 programme. The CV1525 plan was updated reflecting the technology readiness and availability of international partners, now envisaging two M-class missions in 2017/2018 and moving the first L-class mission to the second slice of the CV1525 programme. The overall Cost at Completion for the first CV slice is 900 MEuros (e.c. 2008) and the cost cap per mission is less than 450 MEuros (e.c. 2008). The original plan, based on two rounds of competitive down-selections remains valid. The first M-class down-selection has selected the mission concepts to enter the Definition phase and the first L-class downs-selection is expected in 2011. The second down-selection will select the missions to enter the Implementation phase (M-class: 2012-2018, L-class: 2013-2020). This approach allows competition among different mission candidates until the end of the Definition phase, as recommended by the Science Programme Review Team report (SPRT, ESA/C(2007)13). The corresponding process timeline is shown in Figure 2.1/1. L-class missions

M-class missions

2008 2009 2010 2011 2017 2018 2019 20202007

Laplace

Tandem

Lisa

IXO

2012

L1 launch

Euclid

Plato

Cross-Scale

Marco-Polo

M1 launch

Solar Orbiter

Spica

M2 launch

L-class missions

M-class missions

2008 2009 2010 2011 2017 2018 2019 20202007

Laplace

Tandem

Lisa

IXO

2012

L1 launch

Euclid

Plato

Cross-Scale

Marco-Polo

M1 launch

Solar Orbiter

Spica

M2 launch

Figure 2.1/1. Cosmic Vision timeline summary. The CV1525 mission candidates are summarised in Table 2.1/1 below. The three L-class missions are currently running their assessment phase and are competing for a launch in 2020 (second CV slice). All L missions are foreseen with international collaboration (mainly with NASA and JAXA) and with a cost at completion cap for ESA of 650 MEuros (e.c. 2008).

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Table 2.1/1: Cosmic Vision 2015-2025 Mission Candidates

Fields M-class L-class Mission of Opportunity

Solar System

Solar studies (Solar Orbiter)

Jupiter system (Laplace)

Dark Energy (EUCLID)

X-Ray astronomy (IXO)

IR astronomy (SPICA)

Astrophysics Exoplanets / Asteroseismology

(PLATO)

Gravitational waves (LISA)

2.2 M-class Mission Down-Selection Following the completion of the industrial assessment studies, the M-class mission candidates have undergone a review of their design and technological status, their financial and programmatic viability and their scientific performance. This information has been made available to the Advisory Structure who have performed a scientific ranking of the viable candidates which is detailed in ESA/SSAC(2010)1, SOL(2010)2, ASTRO(2010)2 and FPAG(2010)1. On the basis of this ranking, the Executive has proposed to SPC a number of M-class mission concepts to enter Definition phase (ESA/SPC(2010)3 rev. 1). As noted above, the down-selection decision sees Euclid, PLATO, and Solar Orbiter proceed forward in competition for the M1/M2 Cosmic Vision launch slots. An important change in the Solar Orbiter mission scenario sees an increase in closest approach to the sun from 0.23 to 0.29 AU i.e. similar to Mercury at perihelion. This change will allow the maximum re-use of BepiColombo technology, in particular the solar array and cells. As such the TDAs identified for Solar Orbiter are updated to reflect this new baseline. In addition several of the TDAs (heat shield breadboard, feedthroughs, doors and mechanisms, and antenna adaptation study) will be executed within the frame of the industrial studies. The decision on the way forward for SPICA, regarding the potential European contribution to the JAXA-led mission, will be made at the June 2010 SPC meeting. As such those TDAs for SPICA will not be implemented until this further decision is taken, and may be revisited if required. The three phases of mission study and implementation in the CV 2015-2025 Plan are shown in Figure 2.2/1. The successful execution of the plan requires coordinated system and technology development activities on both the spacecraft and the payload, implemented in parallel. The down-selection after the assessment phase and after the definition phase will consider all elements of the mission including the payload. Letters of Endorsement (LOE) and Multi-Lateral Agreements (MLA) will define the commitments and responsibilities of Member States and ESA.

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Figure 2.2/1. The three phases of mission study and implementation in the CV 2015-2025 plan. 3. Cosmic Vision Technology Development Plan 3.1 This Technology Development Plan update This technology plan is an update of ESA/IPC(2009)143 (November 2009) 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,

Dedicated workshops organised by the Agency for structuring payload activities (case of Laplace and IXO)

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

This update of the work plan reflects the changes required in the M-class technology development activities due to the down-selection outcome (ESA/SPC(2010)3 rev. 1). In all cases, only the activities to be placed in 2010 are submitted for approval. Those foreseen to be placed in 2011/2012 are provided for information.

Assessment Phase Definition Phase Implementation PhaseAssessment Phase Definition Phase Implementation Phase

~ 2 years ~ 2 years ~ 5-6 years

Mission selection

Down-selection& Payload AO

Missionadoption Launch

Assessment studies Design consolidation& pre-developments

Development

n missions two missions one mission

ESA /Member States

agreements

LOE MLA

SpacecraftAnd

Payloadactivities

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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 IXO telescope. Similar past examples are the Herschel telescope and cryostat.

- Focal plane instruments are under Member States responsibility. This applies to SAFARI (SPICA), and IXO focal plane instruments such as WFI or NFI. 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. An important point raised during the M-class down–selection (ESA/SPC(2010)3, rev. 1 §5) is that there is currently no funding available in the Member States for the focal plane CCD detectors for Euclid or PLATO. As such it is now envisaged that the procurement and therefore also the technology pre-developments of the CCD detectors will be under ESA responsibility. This is reflected in this update of the plan where, CCD development activities for PLATO and EUCLID previously under national remit become now listed ESA activities funded through CTP. For the L-Class mission TDAs, phased contracts will be used in order to accommodate the down-selection at the end of 2010 and minimise spending for the mission(s) that will not be down-selected. Similarly, the M-class related TDAs contracts will be phased, considering the final selection of the M-class missions in mid 2011.

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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. Table 3.2/1: Current assumptions for payload cases for 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

Solar Orbiter B Instrument suite, AO process completed in 2009 and instrumentation selected

Laplace B Instrument suite PLATO C Payload assembly excluding CCD detectors. EUCLID C Focal plane assemblies with proximity optics,

(IR and VIS) SPICA C SAFARI cryogenic instrument provided by a

consortium of science institutes. IXO C Optics under ESA responsibility, cryogenic

elements TBD, focal plane instruments provided by institutes

LISA A TBD 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 Special Initiative. The 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.

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For IXO and Laplace dedicated workshops were organised, involving potential instrument providers. Furthermore, a consultation process is ongoing in connection with the assessment study activities. The science payload developments under Member States funding are marked as “National”. The funding scheme for these activities is 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. 3.4 ESA activities for L-class and M-class missions ESA technology development activities for the down-selected M-class missions will now be implemented. This also applies to the science instruments that would be provided by the Member States, for which early technology developments may be required for reaching TRL ≥ 5 before entering the implementation phase. Note that the implementation of the SPICA TDAs will await the respective SPC decision. The technology development activities for the L-class mission candidates are being implemented as soon as possible, in view of reaching TRL ≥ 5 before entering the implementation phase. The technology development activities identified for the future mission themes are also being implemented as soon as possible, within budgetary constraints. This is done with a view to reaching TRL ≥ 4 for the identified key technologies before the next Cosmic Vision call. This will thus allow the future mission themes to compete for selection. For the practical implementation of ESA TDAs, the proposals for 2010 are firm, whereas the period 2011-2012 is provided for information only. It is planned to revisit this list on a regular basis and to continue to update the plan with the results of system studies and ongoing activities.

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3.5 Addition of activities pre-dating the Cosmic Vision Technology Development Plan Table 3.5/1 lists a number of older previously approved activities which we now include in this plan for completeness Table 3.5/1 Previously approved activities added to this plan

IPC Approval

Old ESA Ref.

ESA Ref. in this plan

Activity Title

Y2006 L11/3 C216-113PW Optical Bench Development for LISA

Y2006 SO-DE-03 C216-114PS

Validation of LCVRS for the Solar Orbiter Polarisation Modulation Package (previous title: Solar Orbiter - Polarisation Modulation Package – LCVR)

Y2006 SO-AO-01 C205-001PS High Flux Sun Sensor/Sun Filters 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 are currently in the Assessment Phase. 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, LISA will attempt to detect the tiny ripples of space-time due to the fundamental force of gravity. The mission is foreseen to be implemented in collaboration with NASA. Laplace is the outer planet mission to the Jupiter system and is proposed in collaboration with NASA. The mission concept is based on two spacecraft to perform coordinated observations of the Jovian satellites, in particular Callisto, Ganymede, Europa and Jupiter’s magnetosphere, atmosphere and interior. The collaboration scheme is the following: ESA would be in charge of building the Jupiter Ganymede Orbiter (JGO) spacecraft, while NASA would be in charge of building the Jupiter Europa Orbiter (JEO) spacecraft. The science instrumentation on both spacecraft would be shared between NASA and ESA Member States. IXO evolved from XEUS ESA/JAXA mission by merging with the NASA mission Constellation-X. This International X-ray Observatory is the next-generation X-ray space observatory 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 IXO concept is based on a large deployed structure connecting the

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telescope optics with the focal plane instrumentation. IXO is now foreseen in collaboration between ESA, NASA and JAXA. 4.1.2 M-class Mission Candidates The three M-class mission candidates and one mission of opportunity (TBC) are briefly described below: Solar Orbiter will perform closest ever 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. The scientific goals of the Solar Orbiter include 1) the in-situ determination the properties and dynamics of plasma, fields and particles in the near-Sun heliosphere, 2) to survey the fine detail of the Sun's magnetised atmosphere, 3) to identify the links between activity on the Sun's surface and the resulting evolution of the corona and inner heliosphere, using solar co-rotation passes, and 4) to observe and characterise the Sun's polar regions and equatorial corona Solar Orbiter is a specially designed three-axis stabilised spacecraft. To cope with the extreme Solar radiation, a sunshield, always pointing to the Sun with the one-time exception of an anti-sun pointing mode used during the cruise far from the sun, protects the spacecraft and provides openings to let the instruments view the solar disc. The spacecraft provides a thermally stable environment and a stable pointing to the instruments on board. Solar Orbiter will exploit new technologies being developed by ESA for the BepiColombo mission to Mercury, the closest planet to the Sun. Following a cruise phase lasting approximately 3.4 years, the spacecraft will use a series of gravity assists from Venus and the Earth to enter into a 150-day-long elliptical solar orbit from which it can begin its scientific mission. Upon entering the science orbit, closer encounters to the Sun will be achieved, with closest perihelion of 0.29 AU. The spacecraft will perform a close approach of the Sun every five months. Around closest approach, when travelling at its fastest, Solar Orbiter will remain for several days roughly positioned over the same region of the solar atmosphere as the Sun rotates on its axis. Solar Orbiter will use the gravity of Venus to nudge the spacecraft into higher inclination orbits. This will enable the instruments to see the polar regions of the Sun clearly for the first time. This is one of the prime scientific goals of the project. After 7.4 years, Solar Orbiter will view the poles from solar latitudes higher than 30°, compared with 7° at best from the Earth. A set of in-situ and a set of remote sensing instruments will be accommodated within a resource envelope of 180 kg and 180 W. The in-situ instruments consist of detectors for observing particles and events in the immediate vicinity of the spacecraft: the charged particles and magnetic fields of the solar wind, radio and magnetic waves in the solar wind, and energetic charged particles flung out by the Sun. The remote sensing instruments will observe the Sun's surface and atmosphere. The gas of the

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atmosphere is best seen by its strong emissions of short-wavelength ultraviolet rays. Tuned to these will be a full-Sun and high-resolution imager and a high-resolution spectrometer. The outer atmosphere will be revealed by ultraviolet and visible-light coronagraphs that blot out the bright disc of the Sun. To examine the surface by visible light, and measure local magnetic fields, Solar Orbiter will carry a high-resolution telescope and magnetograph. An X-ray imager will also be carried. EUCLID is an ESA mission to map the geometry of the dark Universe. The mission will investigate the distance-redshift relationship and the evolution of cosmic structures. It achieves this by measuring shapes and redshifts of galaxies and clusters of galaxies out to redshifts ~2, or equivalently to a look-back time of 10 billion years. It will therefore cover the entire period over which dark energy played a significant role in accelerating the expansion. Two of the original Cosmic Vision proposals, the dark universe explorer (DUNE) and the spectroscopic all-sky cosmology explorer (SPACE), were aiming at achieving very similar science goals (i.e. unravelling the nature of dark energy) through different techniques of weak lensing and baryon Acoustic Oscillations. Subsequent studies in the course of 2008 resulted in a single mission concept, EUCLID.

The WL (Weak Lensing) technique maps the distribution of dark matter and measures the property of dark energy in the universe by measuring the shape distortion of distant galaxy images by intervening large scale structures. The distortion, referred to as “shear”, shall be statistically evaluated on a large number of galaxies over 20000 sq.deg.

The BAO (Baryonic Acoustic Oscillations) technique uses the scales in the spatial and angular power spectra as “standard rulers” to measure the equation of state and rate of change of dark energy. The power spectra will be obtained by measuring with high precision the redshift of a large number of galaxies on the same sky surface as for the WL.

In order to achieve the scientific goals, EUCLID features three instruments:

VIS: Visible Imager, for the weak lensing, images the sky in steps of 0.5 square degrees, ~0.1 arcsec pixel size.

NIP: Near Infrared Photometer, for the measure of the photo-z, observes the same field as VIS to enable redshift calibration.

NIS: Near Infrared Spectrometer, for the BAO technique, measurement of the redshift distribution of ~108 emission line galaxies across the sky.

The statistical study of structures in a large volume of the Universe requires a survey of the entire extragalactic sky. EUCLID will survey 20 000 deg² of the extragalactic sky in the visible down to 24.5 mag where the average density of galaxies reaches 40 per square arcminutes. A 1.2m diameter telescope feeds all three instruments, and the satellite service module (SVM) based on Herschel and GAIA heritage supports the Payload Module (PLM) for executing the sky scanning law, centralised data handling and traditional SVM functions. The baseline mission sees a 2017 launch from Kourou on Soyuz ST 2-1B. The spacecraft will follow direct transfer into a free insertion large amplitude orbit at

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L2. The orbit will provide 4 hour daily ground station visibility for data downlink via K-band to Cebreros. Key aspects of the EUCLID mission which are driving technology development include:

The optical PSF of telescope should remain very stable with low ellipticity to ensure the galaxy shear measurement requirements are met.

Detector responses must remain very stable. Very high data rate due to wide field and high resolution dictates access to K-

band for data downlink. Spacecraft pointing must be very stable over the measurement cycle.

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 high-precision photometry in the visible waveband, Since the detection of exoplanets is of a statistical nature due to the fact that the percentage of stars with exoplanets is unknown, PLATO will need to observe as many stars of the necessary accuracy and type, as possible. 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 required accuracy), 3) long mission lifetime (a long mission lifetime allows for several sky fields to be observed during several years). While the third driver is related to cost issues and increased risk (degradation of components), the two first points are difficult to combine. During the ESA internal pre-assessment study, the best observation strategy was determined to be the “staring” concept as opposed to a GAIA-like spinning concept. Using this concept, the observations are conducted using several individual telescopes of smaller size in order to comply with the demanding requirements on large FoV and large collecting area. Using a higher number of sub-apertures gives several advantages compared to using one large aperture; it allows meeting the stringent requirements in terms of signal-to-noise and the large sky field size required to observe enough stellar targets. It also achieves a higher level of redundancy since the loss of a telescope will reduce the signal-to-noise ratio, but not cause the mission to fail. The current mission scenario is to launch PLATO using a Soyuz Fregat with the ST fairing, for a direct insertion into a Lissajous orbit around the Sun-Earth L2 with 500.000 km and 400.000 km axes. For this type of orbit, the launcher has a capability of ~ 2140 kg. L2 was chosen for its stable ambient environment in terms temperature, radiation, possibility to have eclipse-free orbits and un-obstructed view to large parts of the sky (Sun, Earth, moon are all located in a relatively small solid angle). The mission is foreseen to have a nominal lifetime of 6 years, which is divided into three different phases. The two first phases are used for long-duration observations, each

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observation focusing on a particular part of the sky (expected to have a high density of cool dwarfs). These sky fields are assumed to be around (210°, -60°) in ecliptic coordinates, which is close to the galactic plane. The duration of each of these observations is several years, in order to repeatedly detect transits with orbital periods similar to the Earth. This is done so as to reduce the likelihood of flagging false transits (there can be other reasons for detection of changes in the stars brightness, either naturally occurring in the star, the stellar environment (e.g. background objects), or artificially induced in the spacecraft payload). The last phase will be a step&stare phase where several different fields with interesting scientific targets will be monitored for a period of several months each. The exact duration of each phase remains to be consolidated in the following phase but the long-duration periods will be between 2-3 years (it is possible to have one long-duration observation of 3 years and the second of 2 years). The step&stare-phase will be at least one year long. In order to continuously observe each sky field for a period of several years, the spacecraft needs to be 3-axes stabilized and be able to rotate around the payload line-of-sight in order to keep the sunshield and solar arrays oriented towards the sun to avoid impinging sunlight on the payload and secure adequate power production. The communication system will also need a steerable antenna to compensate for the different angular positions of the Earth compared to the spacecraft as it orbits in the Lissajous orbit around L2. The foreseen ground station is Cebreros 35-meter antenna. SPICA (SPace Infrared telescope for Cosmology and Astrophysics) is a JAXA led astronomical mission candidate for launch by 2017. SPICA is a far and medium infrared observatory to be operated at L2 (Sun-Earth-Lagrange Point 2). The observatory will be equipped with a 3.5m Ø Ritchey-Chretien telescope. The core waveband is 5 – 210 micron. The telescope is to be operated at 5 K, with a warm launch and subsequent cooling by passive radiation exchange followed by the action of mechanical coolers. SPICA would build on the heritage of ISO, Herschel, Spitzer/NASA and Akari/JAXA missions. SPICA, with its 3.5 m diameter cryogenically cooled telescope, is optimised for mid- and far-infrared astronomy. 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. These objectives are enabled by the large diameter, low temperature telescope, allowing high resolution and high point-sensitivity measurements. SPICA will be launched by JAXA using a HII B launch vehicle. The mission will be orbiting the Sun-Earth second Lagrangian point, which provides a stable thermal environment and maximum uninterrupted observing efficiency. It will allow for long-term, continuous observation of pre-determined field(s). The overall SPICA system level management and responsibility is with JAXA, while ESA is a partner to the project. The scientific goal is to understand how galaxies, stars and planets form and evolve as well as to investigate the interaction between the astrophysical processes that have led to the formation of our own Solar System. The scientific targets are young gas giant planets, proto-planetary disks, galactic and extragalactic star forming regions, luminous IR galaxies, AGN’s and starburst galaxies at high red-shift, and deep

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cosmological surveys. The characterisation of exo-planets in the IR and investigations on the life-cycle of dust are also important objectives. The envisaged European contribution is as follows:

Provision of the SPICA Telescope Assembly (STA) by ESA, including all telescope elements integrated on a dedicated Telescope Optical Bench, the M2 refocusing mechanism and the internal baffles (excluding the Instruments Optical bench – IOB and the external baffle).

Potential provision of ground segment support by ESA, in the form of a DSN ground station (not requiring any technology development).

Provision of the SPICA FAR Infrared Instrument (SAFARI) by a consortium of scientific institutes funded by the Members States.

The STA is 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. The SPICA FAR IR Instrument (SAFARI) is an imaging spectrometer based on a Fourier Transform concept and operating between 30 and 210 um; it is one of the three main focal plane instruments onboard SPICA, together with the MIR coronograph and the MIR imager and spectrometer. SAFARI is presently undergoing an assessment study (phase 0) by a consortium of national institutes. 4.2 Recommended Science Themes In addition to the selected missions described above, a number of Scientific Themes have been identified by the SSAC. These have a high priority for the future of European Space Science, however no mature proposals were available for potential selection as mission candidate. It is only through an adequate technology preparation in the coming years that these Science Themes will develop the potential to be selected for future CV1525 Calls. The ESA Space Science Advisory Structure has informally provided the following priorities: Science Theme: Exoplanets The direct detection of terrestrial-size exoplanets and their spectroscopic characterization (including biosignatures) is a technically challenging subject, bearing however large discovery potential with large public impact. The approach to be taken (e.g. interferometry or coronagraphy, etc) is being defined by a dedicated Exoplanet Roadmap Advisory Team (EPRAT). Science Theme: Fundamental Physics A number of mission proposals were identified, from which the Fundamental Physics Advisory Group (FPAG) recommended to concentrate the effort on mission enabling technologies for the payloads, such as high stability optical clocks. Science Theme: European Venus Explorer (EVE)

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European Venus Explorer (EVE) is an in-situ mission, consisting of one balloon probe, one descent probe and one orbiter. Russian and Japanese contributions are foreseen. The central theme of the mission, which brings all these science topics together, is to understand the evolution of Venus and its climate, with relevance to terrestrial planets everywhere. Science Theme: B-Polarization Satellite Mission (B-Pol) The Cosmic Microwave Background (CMB) and its B-mode polarisation are to be studied by a potential future mission. The related technology activities should exploit insofar as possible the synergies with other developments (for example TES detectors are of interest for both IXO and B-Pol). Science Theme: Probing the Heliospheric Origins with an Inner Boundary Spacecraft (PHOIBOS) The mission is devoted to the study of the solar corona and inner heliosphere, through observations from 0.3 AU to as close as 3 solar radii from the Sun’s surface. The primary science goal is the study of the corona and the understanding of the solar wind mechanisms. Science Theme: Far-InfraRed Interferometer (FIRI) The developments toward FIR interferometry will complement the studies in the other wavelength domains. Again developments for other missions and themes, e.g. for the exo-planet, should be coordinated. 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. Table 5/1 L-class mission critical technologies L-class Missions

Mission Technology area Future Technology development activities Back-up X-ray optics technology Tandem ruggedizing and environmental testing Baffling system, tandem level Petal breadboard X-ray optics production issues X-ray test facilities upgrading

X-ray Optics

Mirror contamination covers Read out electronics – multiple instruments Entrance windows and filters including mechanisms – visible, UV, polarisation Detector developments – multiple instruments – gas pixel, CMOS, CCD, microcalorimeter

Payload

Performance studies, anti-coincidence methods

IXO

Cryogenics Closed cycle dilution cooler

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Cryocooler chain for TES Readout electronics for cryogenic sensors

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

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

Laplace

Penetrator option (subject to confirmation of interest for Laplace)

Development of ruggedised 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

LISA

EMC Magnetic Gradiometer Table 5/2 M-class mission critical technologies M-class Missions

Mission Technology area Future Technology development activities Power Double sided 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

Communications K-band downlink – spacecraft and ground station developments identified

OBDH High Processing Power DPU Propulsion Cold gas system delta development

AOCS Fine Guidance Sensor and System

EUCLID

Payload High dynamic range fast readout CCDs

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NIR detectors development and readout Optics: visible phase plate, grism Cryolens development Cryomechanisms High-speed 16-bit CCD processor/ADC High-speed, high dynamic range CCD

PLATO Payload

Refractive telescope breadboard Lightweight primary mirror demonstrator Cryogenic Mirror Cryogenic refocusing mechanism - secondary mirror

SAFARI: Detector development SAFARI: Focal plane read-out SAFARI: 50 mK ADR SAFARI: Cryogenic mechanisms

SPICA (TBC)

Payload

SAFARI: Fourier Transform Spectrometer BB

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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. Table 6/1 Technology Development Plan Field Description

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. 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. Article 5.1 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. Article 5.2 ESA Contract Regulations)

DN/C = Direct Negotiation/Continuation; the contract will be awarded in continuation to an existing contract; (Ref. Article 6.1.C ESA Contract Regulations)

DN/S = Direct Negotiation/Specialisation; the contract

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will be awarded by direct negotiation in implementation of a defined industrial policy or resulting from a sole supplier situation; (Ref. Articles 6.1.A,D,F ESA Contract Regulations)

* 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/C/290, rev.6), 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.

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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:

TRL1 - Basic principles observed and reported

TRL2 - Technology concept and/or application formulated

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

TRL4 - Component and/or breadboard validation in laboratory environment

TRL5 - Component and/or breadboard validation in relevant environment

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

TRL7 - System prototype demonstration in a space environment

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

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

Technology Readiness Levels for S/W and tools

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

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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

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Annex 0

Budget Summary Tables

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Page 2 of 4

Application/Mission Progr. 2009 2010 Total for

impl. 2011 2012 Total

2-01 - L-Mission Candidate: Laplace

CTP (7) 900 1700 2600 4200 6800

TRP (14) 5900 1300 7200 350 7550

Total 6800 3000 9800 4550 14350

2-02 - L-Mission Candidate: IXO

CTP (9) 4000 3450 7450 3900 11350

TRP (6) 3050 400 3450 500 3950

Total 7050 3850 10900 4400 15300

2-03 - L-Mission Candidate: LISA

CTP (13) 10850 5000 15850 5900 21750

Total 10850 5000 15850 5900 21750

2-04 - M-Mission Candidate: EUCLID

CTP (4) 4000 4000 4000

TRP (1) 100 100 100

Total 100 4000 4100 4100

2-06 - M-Mission Candidate: Solar Orbiter

CTP (4) 1150 1150 1150

TRP (4) 1050 1050 1050

Total 2200 2200 2200

2-07 - M-Mission Candidate: SPICA

CTP (4) 3500 3500 1000 4500

Total 3500 3500 1000 4500

2-09 - M-Mission Candidate: Plato

CTP (1) 2500 2500 2500

Total 2500 2500 2500

2-11 - Future Science Theme: Fundamental Physics

TRP (2) 250 250 750 1000

Total 250 250 750 1000

2-12 - Future Science Theme: B-Polarization Satellite Mission (B-Pol)

TRP (1) 500 500 500

Total 500 500 500

2-13 - Future Science Theme: Probing the Heliospheric Origins with an Inner Boundary Spacecraft (PHOIBOS)

TRP (4) 350 350 1250 1600

Total 350 350 1250 1600

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Page 3 of 4

Application/Mission Progr. 2009 2010 Total for

impl. 2011 2012 Total

2-14 - Future Science Theme: Far-InfraRed Interferometer (FIRI)

CTP (1) 750 750

TRP (2) 1750 1750

Total 1750 750 2500

2-15 - Technologies applicable to several Cosmic Vision Missions

CTP (7) 1850 650 2500 1600 4100

TRP (16) 6000 700 6700 2000 8700

Total 7850 1350 9200 1600 2000 12800

Grand Total CTP 18750 20800 39550 16600 750 56900

Grand Total TRP 17200 2400 19600 4600 2000 26200

Grand Total ESA 35950 23200 59150 21200 2750 83100

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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 – a contains detailed activity descriptions.

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Page 2 of 16

New and Modified ESA Activities

M-Mission Candidate: EUCLID

Budget Prog.

IPC Appr.

ESA Ref. Activity Title 2009 2010 2011 2012

PP C'try ITT SW Clause applicab.

Remarks

CTP IPC C217-002PA Euclid CCD Pre-Development 2000 DN/S UK N/A E2V(UK). Phased contract. Moved from national TDA N216-012MM, see ESA/SPC(2010)3 rev. 1

Total 2-04 - M-Mission Candidate: EUCLID 2000

M-Mission Candidate: PLATO

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP IPC C217-010PA Development of optimized CCD for PLATO 2500 DN/S UK N/A E2V(UK). Phased contract. Moved from national TDA N216-030PA, see ESA/SPC(2010)3 rev. 1

Total 2-07 - M-Mission Candidate: SPICA 2500

Technologies applicable to several Cosmic Vision Missions

Budget Prog.

IPC Appr.



Remarks

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

300 C Operational SW

Moved from Marco Polo as relevant to several missions

Total 2-15 - Technologies applicable to several Cosmic Vision Missions 300

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Page 3 of 16

Removed Activities

M-Mission Candidate: Cross-Scale

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP Y2009 C205-025EC Inertially referenced sensor for spinning spacecraft 1250 C N/A

CTP Y2009 C205-102ET Interspacecraft link (ISL) for ranging and time synchronisation

1000 C N/A

CTP Y2009 C207-001EE Development of a Circular Polarised X-band Antenna with a Torodial Shaped Radiation Pattern

400 C N/A

TRP Y2009 T201-001ED Low power low mass Flash memory 1Tbit 500 C(R) D or CH N/A

Proposed C(R) to Astrium (D) and Syderal (CH) which currently develop the NG Mass Memory Architecture in parallel contracts.

Total 2-08 - M-Mission Candidate: Cross-Scale 3150


Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP N/A T204-027EE 3-D internal charge addition to Geant-4 250 Open source

For information

Total 2-04 - M-Mission Candidate: EUCLID 250

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Page 4 of 16

M-Mission Candidate: Marco Polo

Budget Prog.

IPC Appr.



Remarks

TRP N/A T213-001MM Kinematics and High-dynamics Assessment of Neo sampling (KHAN)

400 C(1) N/A

CTP Y2009 C215-020MM Sample acquisition, transfer and containment system (SATCS)

2000 C(4) N/A T215-030MM and C215-0020MM merged into one activity.

CTP Y2009 C219-001MP Long duration contamination flux asessment for European thrusters

500 C N/A

TRP Y2009 T219-031MC Low-gravity and high-clearance landing/touchdown system

1000 C(2) N/A Old Title: Development of a landing mechanism for low-gravity body

CTP Y2009 C215-115MM Capsule spin-ejection mechanism 700 C(1) N/A

CTP Y2009 C215-021MS Parachute system for Earth re-entry capsule: canopy, packaging and deployment device

1000 C(2) N/A

CTP Y2009 C205-019EC Autonomous GNC Technology for NEO proximity, Landing and sampling Operations - Phase 2

500 C(2) Operational SW

First Phase is T205-029EC

CTP N/A C216-005EC Low-resource GNC sensor concept for small body proximity operations

100 C(1) N/A Follow on activity is C216-006EC

CTP N/A C216-006EC Low-resource GNC sensor development for small body proximity operations

900 N/A For information. Results of this activity will possibly address MREP altimetry requirements.

CTP Y2009 C220-021MC Delta-Development and pre-qualification of a European lightweight ablative material for sample return missions

750 DN/C F or UK N/A Follow-on from TRP 2008 activity (Development of a European Ablative Material).

CTP N/A C207-002EE UHF Recovery Antenna for Earth Re-entry Capsule 350 C N/A For information

Total 2-05 - M-Mission Candidate: Marco Polo 6950 1250

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M-Mission Candidate: Solar Orbiter

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP N/A C205-101EC Radiation Effects on Star Tracker 400 C N/A Old Title: Star tracker

CTP N/A C207-105EE Antenna adaptation study 200 C N/A

CTP Y2009 C207-106EE Antenna adaptation validation 500 C N/A

CTP N/A C201-115ED Space-wire based Solar Orbiter spacecraft simulator 400 N/A For information. Code changed from T201-115ED

CTP Y2009 C215-113MX Feedthroughs, door, mechanisms 600 C N/A Code changed from T215-113MX

CTP Y2009 C220-103MT Heat shield breadboard, manufacturing and testing 700 C N/A

CTP Y2009 C203-117EP High Intensity High Temperature Solar Generator (HIHTG) development - Phase 1

2000 DN/S N/A Phase 2 (C203-118EP) and 3 (C203-119EP) to follow.

CTP N/A C203-118EP High Intensity High Temperature Solar Generator (HIHTG) development - Phase 2

4000 N/A For information

CTP N/A C203-119EP High Intensity High Temperature Solar Generator (HIHTG) development - Phase 3


CTP Y2009 C203-114EP High Intensity High Temperature Solar Cell Assemblies - Single Junction Feasability

800 C N/A Code changed from T203-114EP

CTP Y2009 C203-115EP Spectrum Optimized High Intensity High Temperature Solar Cell Assembly Development - Phase 1

1500 C N/A Phase 2 (C203-116EP) to follow.

CTP N/A C203-116EP Spectrum Optimized High Intensity High Temperature Solar Cell Assembly Development and Qualification - Phase 2


Total 2-06 - M-Mission Candidate: Solar Orbiter 6700 5900 4000

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Page 6 of 16

M-Mission Candidate: Plato

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP Y2009 C215-117MM Technology Feasibility of the Deployable Sunshield Mechanism Components

500 C(1) N/A Implementation will be pending the decision on the baseline payload design.

Total 2-09 - M-Mission Candidate: Plato 500


Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP Y2009 C216-112MM Development of rad-hard TDI CCD for Dark Energy Mission

500 DN/S UK N/A E2V (UK)

CTP Y2009 C216-028MM Development of prototype high speed, 16 bit CCD processor/ADC

750 C(1) N/A Formerly in PLATO. Now applicable to several missions

Total 2-15 - Technologies applicable to several Cosmic Vision Missions 1250

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Page 7 of 16

Complete List of Running and Planned Activities

The following tables are a complete list of those activities which are: Running since 2008 i.e. activities for which contracts have been signed In preparation for implementation Foreseen to be implemented up and including 2012


Budget Prog.

IPC Appr.



Remarks

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


Previously included for information under Technologies applicable to Several Cosmic Vision Missions

CTP Y2009 C219-001MP Delta Development of Cold Gas Propulsion for Euclid

500 C N/A

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

TRP Y2008 T204-028EE Solar/interplanetary electron hazards 100 C(3) N/A TDA is running. Cosine (NL) + subs.

CTP IPC C217-002PA Euclid CCD Pre-Development 2000 DN/S UK N/A E2V(UK). Phased contract. Moved from national TDA N216-012MM, see ESA/SPC(2010)3 rev. 1

Total 2-04 - M-Mission Candidate: EUCLID 100 4000


Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP Y2009 T221-108QT Materials Selection and Testing 500 DN/S A N/A DN ARCS (A) + subs. in competition

TRP Y2009 T203-111EP High Intensity High Temperature Solar Generator Study

250 C N/A

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Page 8 of 16

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP Y2009 C204-107TC Small high flux test facilities 200 C N/A

TRP Y2009 T204-110TC Solar concentrator test facility upgrade study 100 C N/A

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

200 C N/A Special Initiative

CTP Y2009 C216-102MM Heat rejecting entrance window 300 DN/C I N/A Follow-up to previous contract with Selex Galileo

CTP Y2006 C216-114PS

Validation of LCVRS for the Solar Orbiter Polarisation Modulation Package (previous title: Solar Orbiter - Polarisation Modulation Package – LCVR)

250 C(1) N/A TDA is running. INTA(E) + subs.

CTP Y2006 C205-001PS High Flux Sun Sensor/Sun Filters 400 C(1) N/A TDA is running. LAMBDA-X /CSL (B)

Total 2-06 - M-Mission Candidate: Solar Orbiter 2200

M-Mission Candidate: SPICA

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

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

500 C N/A Parallel competitive phase 1: 2 contracts at 250 k€. Subject to SPC confirmation.

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

1000 N/A Single phase 2 contract. Subject to SPC confirmation.

CTP Y2009 C216-022MM Light-weight mirror demonstrator breadboard in Sic 1500 DN/S F N/A Parallel contract to C216-021MM. Subject to SPC confirmation.

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

1500 DN/S D N/A Parallel contract to C216-022MM. Subject to SPC confirmation.

Total 2-07 - M-Mission Candidate: SPICA 3500 1000

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Page 9 of 16

M-Mission Candidate: PLATO

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP IPC C217-010PA Development of optimized CCD for PLATO 2500 DN/S UK N/A E2V(UK). Phased contract. Moved from national TDA N216-030PA, see ESA/SPC(2010)3 rev. 1

Total 2-07 - M-Mission Candidate: SPICA 2500

L-Mission Candidate: Laplace

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP Y2009 C215-100MM Review of Mechanism for steerable HGA in deep space mission

150 C N/A Code changed from T215-100MM

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

600 C(2) N/A

TRP Y2008 T201-003ED Low mass SpaceWire 150 C(1) N/A TDA is running. AXON (UK) + subs.

CTP Y2009 C203-101EP Solar cell LILT design optimisation and characterisation

900 C N/A

CTP Y2009 C213-001PA Penetrator development within framework of a Jovian moon mission - Phase1

500 C(R) UK N/A TDA is running, Astrium (UK) + subs. Special measure for UK.

CTP Y2009 C213-002PA Penetrator development within framework of a Jovian moon mission Phase 2

800 C(R) UK N/A Phase 1 is C213-001PA Special Measure for UK

CTP N/A C213-003PA Penetrator development within framework of a Jovian moon mission Phase 3

3700 N/A For information. Phase 2 is C213-002PA. Special Measure for UK

TRP Y2008 T223-021QM Characterisation of radiation resistant materials Phase 1

500 C(2) N/A TDA is running. Astrium (F) + subs. Second Phase is C223-001QM Special Initiative

CTP N/A C223-001QM Characterisation of radiation resistant materials Phase 2


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Page 10 of 16

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP Y2008 T222-019QC

Survey of critical components for 1 (new requirement: 150krad) Mrad power system design including delta radiation characterisation of RH power EEE components

350 C(1) N/A TDA is running. ALTER (E) + subs.

TRP N/A T203-005EP 1-Mrad (new requirement: 150krad) power converter/system design and prototyping


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


TRP Y2009 T222-013QC Radiation characterisation of front-end readout ASIC 350 C(1) N/A

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


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

350 C(1) N/A

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

1200 DN/S B N/A IMEC(B) + subs.

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


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

900 C(1) N/A Special Initiative. Reference to Tandem removed from title.

TRP Y2008 T222-016QC Radiation hard memory 800 C(2) N/A Special Initiative

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

500 C(2) UK Open source

TDA is running. QinetiQ (UK)

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

250 C N/A Code changed from T205-100EC

Total 2-01 - L-Mission Candidate: Laplace 6800 3000 4550

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Page 11 of 16

L-Mission Candidate: IXO

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP Y2008 T216-023MM Back-up IXO (XEUS) optics technology Phase 1 1300 C(1) N/A TDA is running. INAF (I) + subs.

CTP N/A C216-002MM Back-up IXO (XEUS) optics technology Phase 2 1400 N/A For information. Pending SST recommendation

TRP Y2008 T216-026MM IXO (XEUS) mirror module ruggedizing & environmental testing

1000 C(1) N/A TDA is running. Cosine (NL). Second Phase is C216-006MM

CTP Y2008 C216-006MM IXO (XEUS) mirror module ruggedizing & environmental testing Ph. II

1000 C N/A TDA is running. Cosine(NL) + subs. First Phase in TRP

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

2000 DN NL + subs N/A TDA is running. Cosine(NL) + subs.

CTP Y2009 C216-008MM IXO (XEUS) industrialised mass production process for X-ray Optical Unit (XOU)

2000 C(1) N/A

CTP N/A C216-007MM IXO (XEUS) petal breadboard including 6 tandems 2500 N/A For information

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

400 C(2) N/A Activity was previously approved.

TRP Y2009 T216-024MM Baffled IXO (XEUS) mirror module 400 C(1) N/A

CTP Y2009 C216-009MM Multilayer coatings for IXO 450 DN/S DK N/A Special Initiative, DN with DNSC.

TRP N/A T216-025MM IXO (XEUS) contamination covers demonstrator 500 N/A For information

CTP Y2008 C216-003MM Bessy X-ray test facilities upgrade plan 200 DN/S D N/A TDA is running. PTB (D)

CTP Y2008 C216-005MM Panter X-ray test facilities upgrades 300 DN/S D N/A TDA is running. MPE (D)

TRP Y2008 T216-022MM Large area X-ray window development. 350 C(1) N/A

CTP Y2008 C215-050MM IXO Metrology and Mechanisms 1500 DN/S UK N/A Special measure for UK, DN with Astrium.

Total 2-02 - L-Mission Candidate: IXO 7050 3850 4400

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L-Mission Candidate: LISA

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

CTP Y2008 C207-013PW Metrology system for LISA 1000 C(2) N/A Special Initiative

CTP N/A C214-002PW LISA metrology system end-to-end characterization 1800 N/A DN is proposed with the same TBD contractor that will perform the "LISA Metrology system" activity.

CTP Y2008 C207-014PW High-power laser system for LISA 6000 C(2) N/A Nominal contract (3M€). Parallel contract funded by Special Initiative (3M€).

CTP Y2006 C217-001MM Tunable laser frequency reference 1000 N/A

IPC approval 2006 (ESA/IPC(2006)41) for 500 kE. IPC approval will be sought for increase to 1000 kE and procurement policy change from C(1) to C(2).

CTP Y2006 C215-022PW LISA Optical Assembly Articulation Mechanism (OAAM)

1000 N/A

IPC approval 2006 (ESA/IPC(2006)41) for 800 kE. IPC approval will be sought for increase to 1000 kE.

CTP Y2008 C207-012PW Opto-mechanical stability characterization for LISA 2400 C(2) N/A

CTP N/A C214-001PW LISA Inertial Sensor final design 1200 N/A For information

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

1200 DN/C CH N/A

Approved Y2008. IPC approval required for procurement policy change from C(2) to DN. Special Initiative

CTP Y2008 C207-011PW Charge Management System for LISA 900 C(2) N/A Special Initiative

CTP Y2008 C207-010EE Compact low noise magnetic gradiometer 600 C(1) N/A TDA is running. RAL (UK) + subs.

CTP Y2008 C207-016PW Outgassing and Contamination characterization for LISA


CTP Y2009 C207-015PW LISA micropropulsion lifetime characterization 1900 DN/C I N/A

CTP Y2006 C216-113PW Optical Bench Development for LISA 1850 C(2) TDA is running. Astrium (D) + subs.

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Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

Total 2-03 - L-Mission Candidate: LISA 10850 5000 5900

Future Science Theme: Fundamental Physics

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP Y2009 T216-033MM High performance frequency dissemination techniques - phase1

250 C N/A

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


Total 2-11 - Future Science Theme: Fundamental Physics 250 750

Future Science Theme: B-Polarization Satellite Mission (B-Pol)

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP Y2008 T207-034EE Modular Wide Field View RF Configurations (old title: Low-loss, low-mass, large lenses with anti-reflection coating)

500 C(1) N/A Special Initiative

Total 2-12 - Future Science Theme: B-Polarization Satellite Mission (B-Pol) 500

Future Science Theme: Probing the Heliospheric Origins with an Inner Boundary Spacecraft (PHOIBOS)

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP Y2008 T223-038QM Materials compatibility for the PHOIBOS mission 250 C(2) N/A TDA is running. ARC (A) + subs.

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Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

(high temperature under high UV load)

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


TRP Y2008 T203-035EP Near-sun power generation: Identification of best suitable thermoelectric converters

100 C N/A TDA is running. Astrium (UK) + subs.

TRP N/A T203-036EP Near-sun power generation: Technology demonstration


Total 2-13 - Future Science Theme: Probing the Heliospheric Origins with an Inner Boundary Spacecraft (PHOIBOS)

350 1250

Future Science Theme: Far-InfraRed Interferometer (FIRI)

Budget Prog.

IPC Appr.


PP C'try ITT SW

Clause applicab.

Remarks

TRP N/A T216-039MM FIRI telescope technology pre-development 1000 N/A For information

TRP N/A T216-040MM Long-stroke cryogenic optical delay lines - Phase 1 750 N/A For information, second phase in CTP

CTP N/A C216-029MM Long-stroke cryogenic optical delay lines - Phase 2 750 N/A For information, first Phase in TRP

Total 2-14 - Future Science Theme: Far-InfraRed Interferometer (FIRI) 1750 750


Budget Prog.

IPC Appr.



Remarks

CTP Y2008 C220-032MC 15K Pulse Tube cooler 600 C N/A

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

TRP Y2008 T220-053MC Advanced 2K JT cooler 700 DN/S UK N/A TDA is running. RAL (UK)

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Budget Prog.

IPC Appr.



Remarks

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

500 C(1) N/A

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

1000 N/A For information, follow-on to TRP T216-047PA

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

2000 N/A For information, follow on to 2007 TRP activity

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

N/A For information, follow-on to TRP T216-048PA, 3ME in 2013.

CTP Y2008 C222-034QC CCD radiation characterisation 500 C N/A TDA is running. SSTL (UK)

CTP Y2008 C201-030ED High processing power DPU based on high rel. DSP 500 C(1) N/A Special Initiative

TRP Y2009 T216-049MM Silicon drift detectors for gamma-ray scintillators 500 C(1) N/A

TRP Y2008 T204-043EE Rad-Hard Electron monitor 400 C(1) N/A Special Initiative

TRP Y2008 T204-044PA Solid-state neutron detector 300 C(1) N/A TDA is running. MicroFab (UK)

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

500 C(1) N/A

TRP Y2006 T204-007MM TES Spectrometer 700 C(1) N/A TDA is running. Cardiff University (UK) + subs.

TRP/CTP Y2008 T216-001MM Evaluation of commercial Digital Micro-mirror Device for multi-object spectrometers

DN/S N N/A TDA is running. VISITECH (N) + LAM (F) + TI (US)

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

650 C(1) N/A

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

250 C N/A

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

250 C(1) N/A

TRP Y2009 T204-041EE Charging properties of new materials 200 C(1) N/A For information

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

300 C(1) Open source

Previously approved in ESA/IPC(2008)33,add. 1. IPC is requested to approve Open Source

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Budget Prog.

IPC Appr.



Remarks

software clause.

TRP Y2008 T212-045GS X/K band feed 350 C N/A TDA is running. MIRAD (CH)

TRP Y2008 T212-046GS X/K/Ka band dichroic mirror 300 C N/A TDA is running. COBHAM (UK) + sub.

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

350 DN/S E Operational SW

New activity code, old code - G205-004EC. Activity in GSTP5 Work Plan

GSTP Y2008 G512-002MC Hybrid Cryostat Demonstrator 700 C(1) N/A New activity code, old code - G220-006MC. Activity in GSTP5 Work Plan

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

1000 C N/A

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

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


Special Initiative. Phase 2 is C205-019EC.

Total 2-15 - Technologies applicable to several Cosmic Vision Missions 8900 1350 1600 2000

ESA/IPC(2010)81

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. Detailed activity descriptions are provided in Annex II – b for those candidate missions which are potentially entering definition phase i.e. M-Class candidates. Detailed descriptions of the L-Class national activities will be provided on the ESA Cosmic Vision website as proceedings of the payload workshops organised by ESA.

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

Remarks

National N215-070PA EUCLID Cryomechanisms N/A To be revised by Member States

National N216-072PA Infrared grism design, manufacturing and testing for EUCLID N/A To be revised by Member States

National N217-073PA Hawaii Array Persistence Image Assessment N/A To be revised by Member States

2-04 - M-Mission Candidate: EUCLID



Remarks

National N216-025PA Cryogenic Fourier Transform Spectrometer Bread Board N/A To be revised by Member States

National N216-022MM European submillimetre/FIR ultra-low noise cryogenic characterization facility

N/A To be revised by Member States

National N220-026MC SAFARI SUB-K COOLER N/A To be revised by Member States

National N207-018EE KID based array detector (old title: Safari: Integrated antenna/detector development)


National N215-019PA Cryogenic mechanisms development N/A To be revised by Member States

National N217-081PA Readout Electronics (FDM) for KID based Array Detectors N/A To be revised by Member States

National N217-080PA Cold Readout Electronics (CRE) for Photoconductor Detector N/A To be revised by Member States

National N217-082PA RF Coupling and Efficiency Prediction Tool for Sub-mm / FIR Detectors N/A To be revised by Member States

National N207-083PA Broadband 50/50 Transmission/Reflection Sub-millimetre-Wave Beam Splitter


2-07 - M-Mission Candidate: SPICA

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Page 3 of 4



Remarks

National N216-115MM Refractive telescope breadboard for PLATO N/A To be revised by Member States

2-09 - M-Mission Candidate: Plato

Future Science Theme: European Venus Explorer (EVE)


Remarks

National N223-034QM 3D printing of antenna on balloon or parachute material part N/A To be revised by Member States

National N214-029MM Nephelometer N/A To be revised by Member States

National N214-030MM MEMS based Gas Chromatography/Mass Spectrometer N/A To be revised by Member States

National N219-032MC Reliable low-mass balloon deployment system for Venus probe. N/A To be revised by Member States

National N219-031MC Inflation system for balloon N/A To be revised by Member States

National N223-033QM Development of balloon materials for VENUS environment N/A To be revised by Member States

2-10 - Future Science Theme: European Venus Explorer (EVE)



Remarks

National N217-040PA Breadboard of an ion optical clock N/A To be revised by Member States

National N216-039MM Stimulated Raman transition inducing diode laser N/A To be revised by Member States

National N216-037MM Laser cooling trapping systems N/A To be revised by Member States

National N216-038MM Ultra-narrow frequency stable laser technology for probing optical clock local oscillator transitions


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Remarks

National N216-036MM Critical Optical frequency comb/synthesiser sub-system technologies N/A To be revised by Member States

National N216-035PA Breadboarding of accelerometer based on Atomic Interferometry N/A To be revised by Member States

2-11 - Future Science Theme: Fundamental Physics



Remarks

National N207-041EE Novel focal plane array architecture development N/A To be revised by Member States

National N207-042EE Sub-millimetre-wave Integrated lens/TES detector development N/A To be revised by Member States

National N216-044PA Sub-millimetre-wave TES development N/A To be revised by Member States

National N216-045PA TDM SQUID read-out for sub-mm applications N/A To be revised by Member States

National N207-040EE Large radii Half-wave Plate (HWP) development N/A To be revised by Member States

National N215-043PA Cryogenic Half-wave plate rotation mechanism N/A To be revised by Member States

2-12 - Future Science Theme: B-Polarization Satellite Mission (B-Pol)



Remarks

National N216-048MM Optical generation and distribution of tuneable FIR Local Oscillator N/A To be revised by Member States

National N216-046MM Far IR passive optical components N/A To be revised by Member States

National N216-047MM Large FOV double-Fourier interferometric breadboard N/A To be revised by Member States

2-14 - Future Science Theme: Far-InfraRed Interferometer (FIRI)

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Annex II – a

Detailed Description of ESA Cosmic Vision Technology Development Activities

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

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M-Mission Candidate: EUCLID 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

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

Current TRL: 3 Target TRL: 6 Application Need/Date:

TRL 5 by Q4 2011

Application Mission:

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

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 unit, 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.


TRL 5 by Q4 2011



18

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S/W Clause: N/A Reference to ESTER

T-7979


Aim A9 : High Performance Chemical Micro-thrusters

Two-axis Steerable X/K-band High Gain Antenna

Programme: CTP Reference: C207-003EE

Title: Two-axis Steerable X/K-band High Gain Antenna

Objectives

1. To perform a trade-off between separated X and K-band HGA and dual-frequency X/K-band antenna 2. To design, manufacture and test a breadboard model of the HGA antenna(s) (X or K-band or X/K-band design)

Description

This activity concerns the development of a two-axis steerable HGA for the Euclid mission. At present two options are considered: use of 2 single frequency antennas or a dual-frequency X/K-band antenna. Several reflector based antenna developments have been done in the past for S/X and X/Ka with diameter around 1.3 meters. Considering the gain values needed for this mission, mechanically steerable Direct Radiating Arrays shall be studied as an alternative to reflectors for lower size with expected decrease of volume and cost. An initial trade-off is needed that compares all options in terms of performance budgets (achievable gain, mass, volume, accommodation constraints). After this trade a selection shall be made for the most suitable HGA candidate and shall be proposed for further design and analysis tasks. The following tasks are foreseen: - Trade-off between separated or combined X- and K-band antenna and selection of the baseline. - Design and analysis of the selected HGA with all its constituents including the dual-frequency rotary joint (if needed). - Definition of the HGA breadboard - Manufacture and test of the Euclid HGA breadboard

Deliverables

Study report Euclid HGA breadboard


TRL 5 by Q4 2011


Euclid Contract Duration:

18



Solar/interplanetary electron hazards

Programme: TRP Reference: T204-028EE

Title: Solar/interplanetary electron hazards

Objectives

Investigate the potential for energetic electrons produced by the Sun or elsewhere (e.g. Jupiter) causing internal or surface charging at near earth interplanetray locations

Description

Studies of the energetic electron environment (10keV-1MeV) at L1 and L2 (e.g. JWST) have so far been somewhat superficial. Since so many astrophysics and fundamental physics missions are planned for L2, L1 and other -near 1AU locations, it is proposed to collect data and theoretical information on energetic electrons in these regions and produce a quantitative model for use in charging and radiation background investigations. Herschel-Planck radiation monitor data will be included.

Deliverables

Numerical model, software, validation, documentation

Current TRL: s/w (pre-study) Target TRL: s/w (beta) Application Need/Date:

TRL 5 by Q4 2011



12

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T-19


N/A

Euclid CCD Pre-Development

Programme: CTP Reference: C217-002PA

Title: Euclid CCD Pre-Development

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 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 (eg 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:

TRL 5 by Q4 2011


Euclid Contract Duration:

18



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Page 5 of 60


Materials Selection and Testing

Programme: TRP Reference: T221-108QT

Title: Materials Selection and Testing

Objectives

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

Description

Description: 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: - 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


TRL 5 by Q4 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

Objectives

To devise two alternative Solar Genrator 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


TRL 5 by Q4 2011

Application Solar Orbiter Contract 9

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Mission: Duration:



Small high flux test facilities

Programme: CTP Reference: C204-107TC

Title: Small high flux test facilities

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

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

N/A



6



Solar concentrator test facility upgrade study

Programme: TRP Reference: T204-110TC

Title: Solar concentrator test facility upgrade study

Objectives

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

Description

Description: 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 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.

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Deliverables

Assessment report


N/A



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.

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.

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


N/A



6



Heat rejecting entrance window

Programme: CTP Reference: C216-102MM

Title: Heat rejecting entrance window

Objectives

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

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- 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 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 PHI 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


TRL 5 by Q4 2011



12



Validation of LCVRs for the Solar Orbiter Polarisation Modulation Package (previous title: Solo - Polarisation Modulation Package - LCVR)

Programme: CTP Reference: C216-114PS

Title: Validation of LCVRs for the Solar Orbiter Polarisation Modulation Package (previous title: Solo - Polarisation Modulation Package - LCVR)

Objectives

To validate the use of LCVR for the 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

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2011



14



N/A

High Flux Sun Sensor/Sun Filters

Programme: CTP Reference: C205-001PS

Title: High Flux Sun Sensor/Sun Filters

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 Solar Orbiter 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 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

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SPICA Telescope focussing mechanism for secondary mirror – Phase 1


Title: SPICA Telescope focussing mechanism for secondary mirror – Phase 1

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

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

TRL 5 by Q4 2011


SPCIA Contract Duration:

6


T-8474


N/A

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SPICA Telescope focussing mechanism for secondary mirror – Phase 2


Title: SPICA Telescope focussing mechanism for secondary mirror – Phase 2

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 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


TRL 5 by Q4 2011


SPCIA Contract Duration:

9


T-8474


N/A

Light-weight mirror demonstrator breadboard in Sic


Title: Light-weight mirror demonstrator breadboard in Sic

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).

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- 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)

Current TRL: 4-5 Target TRL: 6 Application Need/Date:

TRL 5 by Q4 2011


SPICA Contract Duration:

18


T-8532


Harmonisation in progress (2. half 2008)

Light-weight mirror demonstrator breadboard in HB-Cesic


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

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

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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 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)

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TRL 5 by Q4 2011



18


T-8532



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Development of optimised CCD for PLATO


Title: Development of optimised CCD for PLATO

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 18μm x 18μm; useful pixels in FF 4510x4510; useful pixels in FT 4510x2253; flatness 30μm. 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

Optimised CCD detector prototypes and demonstration of the production capability for FMs.

Current TRL: 3 to 4 Target TRL: 6 Application Need/Date:

Q2 2011


Plato Contract Duration:

15



N/A

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L-Mission Candidate: Laplace

Review of Mechanism for steerable HGA in deep space mission


Title: Review of Mechanism for steerable HGA in deep space mission

Objectives

Review current capabilities and constraints with current mission profile and environment

Description

The transfer time to Jovian is 5.9 years. Possibly the antenna would only be deployed after JOI, which would imply a qualification issue. Furthermore, the Jovian environment is dominated by high electron density. It is not known how lubricants and other components would react to such a particle environment, which is cold. The activity should review the mechanism capabilities with respect to the mission requirements and provide an identification of necessary development/qualification issues.

Deliverables

Development plan and possibly investigations with h/w (demonstration)


TRL5 by 2012


Laplace Contract Duration:

12



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

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:



24



Low mass SpaceWire

Programme: TRP Reference: T201-003ED

Title: Low mass SpaceWire

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

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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


TRL 6 by 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

Objectives

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


2012



24



Penetrator development within framework of a Jovian moon mission - Phase1


Title: Penetrator development within framework of a Jovian moon mission - Phase1

Objectives

Study and preliminary design of the overall penetrator + delivery system in the context of the Laplace mission.

Description

This activity forms Phase 1 of a penetrator development activity where a full system study of the penetrator and delivery system trades within the constraints of the Laplace mission will be undertaken. Penetrators, combined with their delivery systems, consitute small spacecraft, carrying hardened subsystems and scientific instrumentation that impact planetary bodies at high speeds and bury themselves a few metres into the surface. They have the potential to provide both a significantly less costly alternative to soft landers (by virtue of their simplicity and reduced mass requirements) and the possibility of multiple penetrators in a single mission at different locations to form a network of stations on the surface. The penetrator is put in context of the Jovian ESA Cosmic Vision mission Laplace, and targets the delivery into the surface of a Jovian moon. This activity will be an investigation of the complete system (i.e. penetrator and deployment system, itself consisting of

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the control system and the motor). Here the overall system aspects, the required resources and the structure and key elements of the technology developments will be addressed. Starting from the required payload, the penetrator will be dimensioned and the deployment system requirements defined. Questions to be discussed include.: AOCS including altimetry system and control aspects, dispersion corrections, specifications of the tolerable errors after stabilisation and before penetrator release, etc. An analysis of the expected behaviour of the penetrator during the quite extensive free fall shall be included - this is particularly important in view of the required alignment of the penetrator axis with the velocity vector at impact, and the risk of a flat spin. The accommodation on Laplace will have to be respected, and a solution for the penetrator system concept must be compatible with the corresponding mission system and scientific requirements. A review will conclude the activity: this will ideally be concurrent with the Laplace system study last phase, when the Laplace system is better understood and an evaluation of any resources for such a payload element would be available. Based on the preliminary compatibility analysis and the feasibility evaluation of the penetrator including deployment system, the decision to progress into phase 2 would be taken by ESA.

Deliverables

Report from study including system requirements and preliminary design specifications of a complete penetrator and delivery system.


2010



9



Penetrator development within framework of a Jovian moon mission Phase2


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

Objectives

Development to TRL 4 of a penetrator (structure + platform elements)

Description

In this phase (Phase 2) of the activity, the following work will be performed: i) Detailed modelling of impact processes associated with impacts into icy regoliths and other simulant materials. ii) Subsystem (not science payload) component development and small-scale impact trials (TRL4).

Deliverables

i) Hardware elements for small scale trials, ii) Modelling and small-scale impact trial reports.


2013



9



Penetrator development within framework of a Jovian moon mission Phase3


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

Objectives

Development to TRL 5 of a penetrator (structure + platform elements) including full scale system-level impact trials.

Description

In this phase (Phase 3) of the activity, the following work will be performed: 1)Further subsystem (not science payload) component development and small-scale impact trials (if required), and ii) full-scale subsystem level trials (TRL5).

Deliverables

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


2013



18



Characterisation of radiation resistant materials Phase 1

Programme: TRP Reference: T223-021QM

Title: Characterisation of radiation resistant materials Phase 1

Objectives

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

Description

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

Deliverables

Test results, selection of resistant materials, design data.


TRL 5 by 2011



36


T-8481


N/A

Characterisation of radiation resistant materials Phase 2

Programme: CTP Reference: C223-001QM

Title: Characterisation of radiation resistant materials Phase 2

Objectives

Assessment and characterisation of radiation resistance of materials to high radiation field of Laplace 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

design data of materials properties for the selected mission case.


TRL 5 by 2011



36


T-8481


N/A

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Survey of critical components for 1 (new requirement: 150krad) Mrad power system design including delta radiation characterisation of RH power EEE components

Programme: TRP Reference: T222-019QC

Title: Survey of critical components for 1 (new requirement: 150krad) Mrad power system design including delta radiation characterisation of RH power EEE components

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 Laplace/Tandem missions (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


TRL5 by 2011



12


T-8480


N/A

1-Mrad (new requirement: 150krad) power converter/system design and prototyping


Title: 1-Mrad (new requirement: 150krad) power converter/system design and prototyping

Objectives

Design and verify a 1Mrad-hard (new requirement: 150krad) power converter and system compliant with Laplace/Tandem mission

Description

In this study results from activities "Delta radiation characterisation of RH power EEE components" and "Survey of critical components for 1Mrad (new requirement: 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


TRL5 by 2011



12


T-8480


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

Objectives

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

Description

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The front-end readout electronics for the various sensors of the Laplace/Tandem missions 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 Laplace/Tandem missions. 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.


TRL5 by 2011



18


T-8480


N/A

Radiation characterisation of front-end readout ASIC


Title: Radiation characterisation of front-end readout ASIC

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 Laplace/Tandem missions, 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



TRL5 by 2011



12


T-8480


N/A

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


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

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.

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TRL5 by 2011



18


T-8480


N/A

Radiation characterisation of RT analogue / mixed signal technology


Title: Radiation characterisation of RT analogue / mixed signal technology

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



TRL5 by 2011



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

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: - 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


TRL5 by 2011



18


T-8480


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

ESA/IPC(2010)81

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


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

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 2010



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

Objectives

Radiation characterization of radiation tolerant (minimum 150krad) optocouplers to identify suitability for Laplace 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 Laplace/Tandem requirements. Thus, this activity aims at selecting candidate radiation tolerant optocouplers and performing radiation tests on these (TID and DD) to Laplace-Tandem levels (150krad behind 8mm of Al shielding).

Deliverables



TRL5 by 2011



12


T-8480


N/A

ESA/IPC(2010)81

Page 24 of 60

Radiation hard memory


Title: Radiation hard memory

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 Laplace (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



TRL5 by 2011



36


T-8480


N/A

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


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

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. 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 modelling capabilities; strawman Geant4 geometry models of all of the Cosmic Vision mission spacecraft


TRL5 by 2011



24

S/W Clause: Open source Reference to ESTER

T-8480

ESA/IPC(2010)81

Page 25 of 60


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

Objectives

Review particle environemnt and simultate effects on star tracker performance

Description

The Jovian environment has a high density of charged particles (mainly electrons). Despite heavy shielding, residual particle interations 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 kindof snow effect. This shall be simulated (either h/w or s/w) and the feasibility of using currently avaibaly star trackers shall be assessed.

Deliverables


TRL5 by 2012



18



ESA/IPC(2010)81

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L-Mission Candidate: IXO

Back-up IXO (XEUS) optics technology Phase 1


Title: Back-up IXO (XEUS) optics technology Phase 1

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 (XEUS) 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 (XEUS) 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 (XEUS) timescales.

Deliverables

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


TRL 4 by 2009


IXO (XEUS) Contract Duration:

16


T-8452


N/A

Back-up IXO (XEUS) optics technology Phase 2


Title: Back-up IXO (XEUS) optics technology Phase 2

Objectives

Development of a back-up technology for the IXO (XEUS) 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 (XEUS) telescope. - Environmental testing (mechanical, thermal) with x-ray testing at an appropriate facility pre and post each environmental test.

Deliverables

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


TRL 5 by 2011



16


T-8452


N/A

ESA/IPC(2010)81

Page 27 of 60

IXO (XEUS) mirror module ruggedizing & environmental testing


Title: IXO (XEUS) mirror module ruggedizing & environmental testing

Objectives

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

Description

- Modelling & analysis of stack adhesion forces.- Improvements to state of the art manufacturing of mirror modules to ensure compatibility with XEUS environmental requirements, for instance annealing, contamination control within the limits of the available financial envelope (it isclear 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 XEUS- Procurement of equipment upgrades and any necessary modification of the stacking robot, including for aninnermost 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 XEUS 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 modelling results. 3(TBD) IXO (XEUS) mirror modules of stacked silicon plates, at least one coated. Results of x-ray, mechanical and thermal testing. Industrialisation plans.


TRL5 by 2009



18


T-8453


N/A

IXO (XEUS) mirror module ruggedizing & environmental testing Ph. II


Title: IXO (XEUS) mirror module ruggedizing & environmental testing Ph. II

Objectives

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

Description

- Modelling & 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 isclear that a chip manufacturing type assembly line is coherent with the cleanliness requirements for stacking IXO 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 modelling results. 3(TBD) IXO (XEUS) mirror modules of stacked silicon plates, at least one coated. Results of x-ray, mechanical and thermal testing. Industrialisation plans.


TRL5 by end 2009

Application IXO (XEUS) Contract 18

ESA/IPC(2010)81

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Mission: Duration:


T-8453


N/A

Development of IXO (XEUS) Si pore optics and mass production processes


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

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


TRL4 by end 2010



18


T-7959


N/A

IXO (XEUS) industrialised mass production process for X-ray Optical Unit (XOU)


Title: IXO (XEUS) industrialised mass production process for X-ray Optical Unit (XOU)

Objectives

Development of an industrialised mass production process for mirror modules for IXO (XEUS) telescope

Description

Assessment of facility, manpower, equipment requirements for scaling up to XOU mass production. Development of a robotic system for an automated process to produce XOUs on a mass scale. Procurement and demonstration of industrial robot (or parts there-of) in suitable cleanroom facilities. Assessment of risks and mitigation routes for the industrialised process in a flight production programme.

Deliverables

Key elements of XOU production chain General production plan.

Current TRL: 2 Target TRL: 4 Application TRL 4 by 2009

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Need/Date:



12


T-7959


N/A

IXO (XEUS) petal breadboard including 6 tandems


Title: IXO (XEUS) petal breadboard including 6 tandems

Objectives

To demonstrate by breadboarding the achievement of TRL 3/4 for a petal that meets the requirements for IXO (XEUS)

Description

- Detailed design, analysis and modelling of a petal to meet the requirements for IXO.- Specification of the alignment and mounting process to mount x-ray Si pore optic tandems into the petal using method that allows their eventual removal and replacement.- Procurement, installation and modification of any new equipment necessary for manufacturing mirror modules at outermost radii (new mandrels, dies, etc.) (2m and innermost radii tooling procured in other activities.)- Procurement of all parts necessary, including suitable manufacturing margin, for petal, mirror modules and dummy manufacture.- Manufacture of a petal, 6 (TBD, 9 tandems increases cost by 900k) tandems (uncoated) and TBD dummies (to fill other slots) and alignment and mounting of the tandems (& dummies) into a petal that meets the requirements for IXO, including environmental. Two tandems each will be manufactured to inner, 2m and outer radii and be integrated to fill the cells in their petal row where modelling shows that the highest vibration load and highest thermal load are experienced.- X-ray testing at Si stack, mirror module and petal level at suitable facilities.- Elaboration of a route to industrialised XEUS petal production.

Deliverables

Analysis and modelling results. IXO (XEUS) petal populated with TBD mirror modules and TBD dummies. Results of x-ray testing. Industrialisation plans for petal production.


TRL 3/4 for IXO (XEUS) petal by mid 2011



24


T-8456


N/A

Micropore Baffle (Tapered Plates Baffle For Silicon Pore Optics)


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

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 modelling 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:

ESA/IPC(2010)81

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- 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 modelling, 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, analaysis, manufacting and test results, summary report, x-ray optic units.

Current TRL: Target TRL: Application Need/Date:


IXO Contract Duration:

18



Baffled IXO (XEUS) mirror module


Title: Baffled IXO (XEUS) mirror module

Objectives

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

Description

- Procurement of all parts, including suitable margin on Si plates, for the manufacture of a baffled IXO (XEUS) Si x-ray pore optic module. - Manufacture and alignment of a baffled x-ray pore optic module to meet the requirements of IXO (XEUS). - 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.


TRL 5 by 2011



12


T-7854


N/A

Multilayer coatings for IXO


Title: Multilayer coatings for IXO

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.

ESA/IPC(2010)81

Page 31 of 60

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

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




15



IXO (XEUS) contamination covers demonstrator


Title: IXO (XEUS) contamination covers demonstrator

Objectives

To demonstrate contamination covers for the protection of the optics of the IXO (XEUS) telescope

Description

- Design, modelling and analysis of large covers to meet the requirements of the IXO (XEUS) optics during ground operations, launch, cruise and operation mission stages; roll-back covers using failsafe mechanisms could be considered. - Design of attachment to petal or optical bench. - Manufacture of a contamination cover and demonstration of design. - Characterisation of the cover's performance both while installed (particle tightness, humidity), and during opening to expose full aperture.

Deliverables

Analysis and modelling results Contamination cover demonstrator Characterisation results.


TRL 3/4 by 2011



18

ESA/IPC(2010)81

Page 32 of 60


T-8457


N/A

Bessy X-ray test facilities upgrade plan


Title: Bessy X-ray test facilities upgrade plan

Objectives

Upgrade of the Bessy x-ray test facility to facilitate characterisation of IXO (XEUS) mirror modules

Description

This activity comprises the installation of a four-crystal monochromator on the (currently fixed energy) Bessy beamline.

Deliverables

FCM available for IXO (XEUS) work

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

Ready end 2010



24


T-7959


N/A

Panter X-ray test facilities upgrades


Title: Panter X-ray test facilities upgrades

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

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

Ready end 2010



24


T-7959


N/A

Large area X-ray window development.


Title: Large area X-ray window development.

Objectives

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

ESA/IPC(2010)81

Page 33 of 60

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.


TRL5 by 2012



24



N/A

IXO Metrology and Mechanisms


Title: IXO Metrology and Mechanisms

Objectives

To capture the requirements for the IXO deployable structure mechanisms and associated metrology, and breadboarding of proposed solution.

Description

In parallel with IXO assessment system study, requirements for mechanisms and metrology will be captured, and a baseline design for the deployable booms and associated metrology will be made. In a second phase, a set of tests will be made of breadboard concepts to both pre-qualify hardware solutions, and to retire the risk of eventual flight qualification issues, using scalable tests (e.g. reduced length, mechanism unit testing, scaled optical tests with movable platforms etc.)

Deliverables

Design and test data packages including analysis and test results. Breadboard hardware demonstrator.




24



ESA/IPC(2010)81

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L-Mission Candidate: LISA

Metrology system for LISA

Programme: CTP Reference: C207-013PW

Title: Metrology system for LISA

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


TRL5 by 2010


LISA Contract Duration:

18


T-663


N/A

LISA metrology system end-to-end characterization


Title: LISA metrology system end-to-end characterization

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 phasemeter 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 characterized.

Deliverables

A development model of the LISA measurement system.


June 2013



18


ESA/IPC(2010)81

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High-power laser system for LISA


Title: High-power laser system for LISA

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


TRL5 by 2011



24


T-722,T-726


N/A

Tunable laser frequency reference


Title: Tunable laser frequency reference

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. 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.


Q2 2013



18


T-7946

ESA/IPC(2010)81

Page 36 of 60


LISA Optical Assembly Articulation Mechanism (OAAM)


Title: LISA Optical Assembly Articulation Mechanism (OAAM)

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


end 2012



18



Opto-mechanical stability characterization for LISA


Title: Opto-mechanical stability characterization for LISA

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 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-machanical 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

ESA/IPC(2010)81

Page 37 of 60


TRL5 by 2010



24


T-7875


N/A

LISA Inertial Sensor final design


Title: LISA Inertial Sensor final design

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


June 2013



12



GRS Front End Electronics characterization for LISA


Title: GRS Front End Electronics characterization for LISA

Objectives

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

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.


TRL5 by 2011



24


T-698


N/A

ESA/IPC(2010)81

Page 38 of 60

Charge Management System for LISA


Title: Charge Management System for LISA

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


TRL5 by 2011



24


T-7945


N/A

Compact low noise magnetic gradiometer

Programme: CTP Reference: C207-010EE

Title: Compact low noise magnetic gradiometer

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 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.


TRL5 by 2011

ESA/IPC(2010)81

Page 39 of 60


Lisa Contract Duration:

24



Consistent with EMC Dossier

Outgassing and Contamination characterization for LISA


Title: Outgassing and Contamination characterization for LISA

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


TRL5 by 2011



24


T-8391


N/A

LISA micropropulsion lifetime characterization


Title: LISA micropropulsion lifetime characterization

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


Q2 2013



36


T-1013


ESA/IPC(2010)81

Page 40 of 60

N/A

Optical Bench Development for LISA


Title: Optical Bench Development for LISA

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

ESA/IPC(2010)81

Page 41 of 60


High performance frequency dissemination techniques - phase1


Title: High performance frequency dissemination techniques - phase1

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.


TRL 4/5 by 2012


Fundamental Physics Contract Duration:

18


T-8522


N/A

High performance frequency dissemination techniques - phase 2


Title: High performance frequency dissemination techniques - phase 2

Objectives

Phase 2: Build and test hardware according to requirements resulting from phase 1 study

Description

Build hardware of a space-to-ground link according to findings of phase 1; create test set-up for this hardware and execute tests.

Deliverables

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


TRL 4/5 by 2012


FP Contract Duration:

18

S/W Clause: Reference to ESTER


N/A

ESA/IPC(2010)81

Page 42 of 60


Modular Wide Field View RF Configurations (old title: Low-loss, low-mass, large lenses with anti-reflection coating)


Title: Modular Wide Field View RF Configurations (old title: Low-loss, low-mass, large lenses with anti-reflection coating)

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


TRL5 by 2011


B-Pol Contract Duration:

24


T-8495


Technologies for Passive mm and Submm Wave Instruments

ESA/IPC(2010)81

Page 43 of 60

Future Science Theme: Probing the Heliospheric Origins with an Inner Boundary Spacecraft (PHOIBOS)

Materials compatibility for the PHOIBOS mission (high temperature under high UV load)


Title: Materials compatibility for the PHOIBOS mission (high temperature under high UV load)

Objectives

To develop test methodology and characterise materials for the VENUS environment

Description

Develop test methods, select materials (e.g. TPS, extreme temperature MLI, ceramic adhesives etc.), evaluate materials , provide design data

Deliverables

Test results, samples, selection of materials


TRL 6 in 2010


Phoibos Contract Duration:

18


T-8516


N/A

Development of a heatshield concept and material screening for near-Sun mission

Programme: TRP Reference: T220-037MC

Title: Development of a heatshield concept and material screening for near-Sun mission

Objectives

The objective is to assess the feasibility of a sunshield for a spacecraft approaching the Sun down to a distance of several Sun radii. Suitable sunshield concepts shall be developed and assessed together with the screening and relevant characterisation of adequate materials. Preliminary requirements are a heat flux up to > 5 MW/m2 for long duration and dust impacts of 500 km/s.

Description

A specific sunshield needs to be developed for a solar orbiter approaching the Sun down to a distance of several solar radii. Such sunshield might be based on a hot structure made by e.g. CMC- or UHTC-materials, but will likely require some active thermal protection mechanism. The work could follow the following step-wise approach: - Requirements consolidation for heatshield - Screening and assessment and identification of a suitable heatshield concept - Derivation of requirements for heatshield materials - Screening for suitable high temperature materials including basic testing - Selection of most suited material(s) followed by detailed material characterisation - Refinement of the heatshield concept and analytical verification

Deliverables

Material samples, documentation


TRL5-6 by 2012



18


T8513


N/A

ESA/IPC(2010)81

Page 44 of 60

Near-sun power generation: Identification of best suitable thermoelectric converters


Title: Near-sun power generation: Identification of best suitable thermoelectric converters

Objectives

Near-sun missions such as Solar Orbiter will necessitate development of new power generation techniques, for which options include thermo-photovoltaics, thermoelectric materials and Stirling engines. This activity will perform preliminary analysis to determine candidates for further development, which will be performed in a second phase.

Description

Preparation Phase: Investigate the applicability of the candidate power generation technologies to -Solar Orbiter- and other future ESA missions using the expertise of TEC-EPG and TEC-MCT respectively in photovoltaic and thermo-electric materials. Select two or more technologies for development to higher TRL (100k euros, TRL 1 in 2009).

Deliverables

Design and Study note


TRL4 by 2012



6


T-8515


N/A

Near-sun power generation: Technology demonstration


Title: Near-sun power generation: Technology demonstration

Objectives

Near-sun missions such as Solar Orbiter will necessitate development of new power generation techniques, for which options include thermo-photovoltaics, thermoelectric materials and Stirling engines. This activity will perform further development, as a follow on to the preliminary analysis in Phase 1.

Description

Demonstration Phase will involve focused development of one or more power generation technologies to breadboard level . At least two different technologies shall be assess in detail (500k euros per technology, TRL 4 in 2012).

Deliverables

Breadboard prototype and development roadmap


TRL4 by 2012


PHOIBOS Contract Duration:

24


T-8515


N/A

ESA/IPC(2010)81

Page 45 of 60


FIRI telescope technology pre-development


Title: FIRI telescope technology pre-development

Objectives

To develop and push lightweight mirror and telescope technology consistent with an areal density one order of magnitude less than currently available.

Description

The stated need for FIRI is to have three 3.5 m class telescopes operating under cryogenic conditions down to 25 microns. This is exceedingly challenging and requires a specific technological leap to achieve. SiC is a proven technology for 3.5 m class telescopes (Herschel), but the areal density is too high. The Herschel telescope has a total mass of 300 kg. FIRI has an individual telescope mass budget of 100 kg. Further lightweighting of the qualified SiC process is not feasible, so alternative materials such as C/Sic, CeSic, CFRP or combinations of these or others will have to be investigated. The approach shall be than to: 1) Investigate suitable material systems compatible with the achievement of low areal densities, and down-select a number of candidates for evaluation and test, 2) produce a number of samples and propose a test program to verify their performances at laboratory level, 3) evaluate the outcome of the tests and propose a roadmap and technology development plan consistent with reaching TRL 5 for two alternative technologies (prime and backup) by 2011.

Deliverables

Test samples and study report including roadmap.


TRL 5 in 2011


FIRI Contract Duration:

24


T-8506



Long-stroke cryogenic optical delay lines - Phase 1


Title: Long-stroke cryogenic optical delay lines - Phase 1

Objectives

To design, develop and test a breadboard representative in form/fit/function of an engineering model (EM) of a long-stroke optical delay line (ODL) compatible with cryo-vacuum operation (<5K). The breadboard shall include two separated ODLs, one fixed and one dynamic.

Description

An optical delay line (ODL) is a high-precision opto-mechanical system that is able to introduce well-defined optical path variations without introducing significant wavefront errors, beam tilt and beam lateral deviation, in the full actuation range. ODLs are used to cophase the beams of the different arms of an interferometer and to adjust the optical path difference with sufficient accuracy and precision. Optical imaging interferometers have been proposed at ESA and NASA/JPL to increase the angular resolution (<1arcsec) of instruments operating in the FIR region of the electromagnetic spectrum (25-300um). Optical interferometers allow achieving this extremely high angular resolution by combining the light coming from several small telescopes placed at distances from each other equal to the diameter of the synthesised telescope. Optical delay lines have already been developed at ESA for DARWIN mission up to TRL5. However, the requirements of a nulling interferometer working at 6-20um differ significantly from those of an imaging interferometer at FIR (25-300um), especially when the same ODL is also used as a Fourier transform spectrometer to provide high spectral resolution (>1000). This activity shall design, develop and test a breadboard of a representative engineering model (EM) of a long-stroke optical delay line (optical stroke up to +/-500mm depending on the required spectral resolution), with free beam diameter ~10cm, field of view (in the sky) >1arcmin and resolution and stability requirements compatible with an imaging interferometer working in the FIR wavelength range (25-300um). Concepts to integrate sub-band splitting (4 sub-bands) shall be investigated and implemented. The overall design shall minimize the required mechanical stroke, the overall size/mass and the dissipated power consumption (<20mW at 5K).

Deliverables

ESA/IPC(2010)81

Page 46 of 60

Breadboard (one dynamic ODL and one fixed ODL), Data Technology Package


TRL5 in 2015



24


T-8504


N/A

Long-stroke cryogenic optical delay lines - Phase 2


Title: Long-stroke cryogenic optical delay lines - Phase 2

Objectives

To design, develop and test a breadboard representative in form/fit/function of an engineering model (EM) of a long-stroke optical delay line (ODL) compatible with cryo-vacuum operation (<5K). The breadboard shall include two separated ODLs, one fixed and one dynamic.

Description

An optical delay line (ODL) is a high-precision opto-mechanical system that is able to introduce well-defined optical path variations without introducing significant wavefront errors, beam tilt and beam lateral deviation, in the full actuation range. ODLs are used to cophase the beams of the different arms of an interferometer and to adjust the optical path difference with sufficient accuracy and precision. Optical imaging interferometers have been proposed at ESA and NASA/JPL to increase the angular resolution (<1arcsec) of instruments operating in the FIR region of the electromagnetic spectrum (25-300um). Optical interferometers allow achieving this extremely high angular resolution by combining the light coming from several small telescopes placed at distances from each other equal to the diameter of the synthesised telescope. Optical delay lines have already been developed at ESA for DARWIN mission up to TRL5. However, the requirements of a nulling interferometer working at 6-20um differ significantly from those of an imaging interferometer at FIR (25-300um), especially when the same ODL is also used as a Fourier transform spectrometer to provide high spectral resolution (>1000). This activity shall design, develop and test a breadboard of a representative engineering model (EM) of a long-stroke optical delay line (optical stroke up to +/-500mm depending on the required spectral resolution), with free beam diameter ~10cm, field of view (in the sky) >1arcmin and resolution and stability requirements compatible with an imaging interferometer working in the FIR wavelength range (25-300um). Concepts to integrate sub-band splitting (4 sub-bands) shall be investigated and implemented. The overall design shall minimize the required mechanical stroke, the overall size/mass and the dissipated power consumption (<20mW at 5K).

Deliverables

Breadboard (one dynamic ODL and one fixed ODL), Data Technology Package


TRL5 after 2013



24


T-8504


N/A

ESA/IPC(2010)81

Page 47 of 60


15K Pulse Tube cooler

Programme: CTP Reference: C220-032MC

Title: 15K Pulse Tube cooler

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 coolers 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


TRL6 by 2011


Generic Contract Duration:

24


T-7876


Cryogenic and Focal Plane cooling (2007)

Test & Verification of Sub-kelvin cooling chain

Programme: CTP Reference: C220-033MC

Title: Test & Verification of Sub-kelvin cooling chain

Objectives

The objective is to verify the end to end performance of a complete cryogenic chain from room temperature down to 50mK

Description

To achieve cooling from room temperature down to 50mK, various cooling stages at various temperatures and using different technologies are required. To verfiy the proper operation of the complete chain and to characterise the transient behaviour, a test cryostat shall be designed including the 50mK cooler attached to a 2K JT cooler, developed in the previous technology activities. The test cryostat shall also allow to install either a 10K Stirling, 15K pulse Tube or Hydrogen sorption cooler and shall provide a simulator of a cryogenic radiator. At least one of the mentioned 1JT pre-cooler stages shall be implemented and the complete cooling chain performance shall be tested. It is assumed that all coolers used in this activity are provided as CFE.

Deliverables

Fully tested cryochain, documentation, test results


TRL4 by 2013



24


N/A



ESA/IPC(2010)81

Page 48 of 60

Advanced 2K JT cooler

Programme: TRP Reference: T220-053MC

Title: Advanced 2K JT cooler

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 tetsted EM cooler, documentation


TRL6 by 2011



24


T-8527



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

Programme: TRP Reference: T216-047PA

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

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.


TRL5 by 2011



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.

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.

ESA/IPC(2010)81

Page 49 of 60

Deliverables

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


TRL 4/5 by 2012



24


T-8530


N/A

Prototype NIR/SWIR large format array detector development.


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

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.


TRL5 by 2011



24


T-8529


N/A

Optimised NIR/SWIR large format array detector development.


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

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.


TRL 4/5 by 2012



24


T-8529


N/A

ESA/IPC(2010)81

Page 50 of 60

CCD radiation characterisation

Programme: CTP Reference: C222-034QC

Title: CCD radiation characterisation

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 the 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



TRL5 by 2011



24


T-7889


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

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 fulfil 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

EM level computer board


TRL 5 by 2010



18


T-7751


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

Silicon drift detectors for gamma-ray scintillators


Title: Silicon drift detectors for gamma-ray scintillators

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

ESA/IPC(2010)81

Page 51 of 60

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.


TRL5 by 2013



18



N/A

Rad-Hard Electron monitor


Title: Rad-Hard Electron monitor

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


TRL 5 by 2011



24


T-8547


Harmonisation radiation monitoring; SEENoTC

Solid-state neutron detector


Title: Solid-state neutron detector

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.


TRL5 by 2011



24


T-8547

ESA/IPC(2010)81

Page 52 of 60


N/A

Low-noise scintillator detectors for planetary remote-sensing


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

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.


TRL5 by 2011



24



N/A

TES Spectrometer


Title: TES Spectrometer

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

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

TBD


SPICA/FIRI/B- POL Contract Duration:

24



Evaluation of commercial Digital Micro-mirror Device for multi-object spectrometers

Programme: TRP/CTP Reference: T216-001MM

Title: Evaluation of commercial Digital Micro-mirror Device for multi-object spectrometers

Objectives

To conduct a readiation evaluation campaign for micro-mirror MOEMS, covering procurement, testing and evaluation, and analysis of future development requirements.

Description

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Multi-object spectrometers rely critically on optical MEMS devices (Digital Micro-mirror Devices (DMDs)) to significantly increase the performance of the instrument. Such devices are currently available on the commercial market (e.g. for video-projection), however they are not qualified for space applications. The proposed activity will evaluate the mechanical, electronic and optical performance of specific identified devices available on the market with regard to influences of mechanical, radiation, thermal (including cryogenic) and vacuum environments. In the frame of the Cosmic Visions 15-25 ESA Space Science programme, the need for MEMS based digital optical modulators was identified for multi-object spectroscopy. This is of particular importance to the study of dark energy in the universe, which was identified as a high priority objective. The technology baselined for NIRSPEC on JWST e.g. is limited to an order of magnitude less simultaneous targets. The results of this activity (the assessment of current devices with regard to their failure modes) will also form an important input in the definition of future technology activities this sector.

Deliverables

Test Report


TRL5 by 2011



12


T-8470


N/A

Opto-mechanical performance characterisation of IR components in representative environment


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

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 environmental conditions (considering temperature and vibration levels).

Deliverables

IR components and optical chain breadboard


2011


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

Objectives

To determine accurately the CTE of stable materials at cryogenic temperature

Description

ESA/IPC(2010)81

Page 54 of 60

To determine accurately the CTE of stable materials at cryogenic temperature

Deliverables

samples, test results, materials data


TRL5 by 2011



24


T-8391


N/A

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


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

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.

Current TRL: 2 Target TRL: 4 to 5 Application Need/Date:

TRL 5 by 2011



24


T-7673


N/A

Charging properties of new materials


Title: Charging properties of new materials

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


TRL5 by 2011



18


T-7673


SEENoTC via SPINE

ESA/IPC(2010)81

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Computational tools for spacecraft electrostatic cleanliness and payload analysis


Title: Computational tools for spacecraft electrostatic cleanliness and payload analysis

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

Current TRL: s/w (pre-study) Target TRL: s/w (beta) Application Need/Date:

TRL5 by 2011



12


T-8396


SEENoTC via SPINE

X/K band feed

Programme: TRP Reference: T212-045GS

Title: X/K band feed

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 in 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 straightforward, 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


TRL5 by 2011

Application Generic Contract 15

ESA/IPC(2010)81

Page 56 of 60

Mission: Duration:


T-8489, T-8490


N/A

X/K/Ka band dichroic mirror

Programme: TRP Reference: T212-046GS

Title: X/K/Ka band dichroic mirror

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


TRL5 by 2011



15


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

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.

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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

Current TRL: 2 - 3 Target TRL: 5/6 Application Need/Date:

TRL6 by 2011



18


N/A


N/A

Hybrid Cryostat Demonstrator

Programme: GSTP Reference: G512-002MC

Title: Hybrid Cryostat Demonstrator

Objectives

The objective is to develop a small hybrid cryostat compatible with European launchers to provide a vibration free cryogenic environment in orbit and verify operations at breadboard level

Description

Small sfHe cryostats, which would be sufficient for in-orbit operations do not provide sufficient capacity to survive the launch on European launchers, since no late access is possible. Hybrid Cryostats (e.g. sfHe-solidHydrogen) offer the possibility to create a cold environment before launch, therefore minimising the loss of Helium during LEOP. Based on the sfHe cryostats already build (Herschel/ISO), all elements for building such a cryostat should be available, but there is no experience in Europe, how such cryostats can be conditioned (i.e creating solid hydrogen ) and how this can be performed at the launch pad, to guarantee that the time between last access and actual launch does not lead to cryostat conditions which could lead to a loss of mission. A small hybrid cryostat shall be developed and build at breadboard level. Cryostat operations required for a future flight/launch campaign shall be tested and compatibility with current European launch operations shall be verified.

Deliverables

Cryostat BB, documentation, verified procedure for ground tests and launch campaign


TRL6 by 2014



24




Kinetic shock tube for radiation data base for planetary exploration

Programme: TRP Reference: T217-052MP

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

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 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

ESA/IPC(2010)81

Page 58 of 60

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)


TRL 5 by 2011



24


T-8540


Yes

Ablation radiation coupling

Programme: TRP Reference: T217-051MP

Title: Ablation radiation coupling

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


TRL 5 by 2011



18


T-8540


Yes

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

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

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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); - 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 survivability, 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

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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 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)


TRL 5 by Q4 2011



18


T8071


N/A

ESA/IPC(2010)81

Annex II – b

Detailed Description of National Technology Development Activities

Detailed activity descriptions are provided in this annex for those M-Class missions candidates which are entering the definition phase.

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Page 2 of 10


EUCLID Cryomechanisms

Programme: National Reference: N215-070PA

Title: EUCLID Cryomechanisms

Objectives

Prequalify filter wheel mechanisms

Description

Review mechanism requirements for number, location/rotation accuracy, filter and optical element dimensions and masses, operational schedules for exchange speed and total lifetime cycles.

Deliverables

Preliminary design, identify critical items, breadboard


TRL 5 by Q4 2011



18



Infrared grism design, manufacturing and testing for EUCLID


Title: Infrared grism design, manufacturing and testing for EUCLID

Objectives

Design and manufacturing of a prototype of a transmissive grating (grism) operating in the wavelength range from 1 to 2 micron; testing under operational environmental conditions

Description

The Near Infrared Spectrograph (NIR) is one of the instruments on EUCLID. It will make use of several grisms mounted on a wheel. The grisms have to operate in the wavelength range of 1 - 2 microns. The resolving power shall be in the order of 500. The effective efficiency of the grating shall be >75% peak and >50% over the whole spectral range. The length of the grism shall be >100mm. The operational temperature of the grism is ~150K. The activity encompasses: - Review of the performance requirements, - Design of the grism covering the required wavelength range and fulfilling thermal requirements, - Grism fabrication, - Performance and environmental tests.

Deliverables

Fabricate prototypes (2 grisms (1 spare)). Performance test, environmental test


TRL 5 by Q4 2011



10


T-8442, T-8444, T-7861


Hawaii Array Persistence Image Assessment


Title: Hawaii Array Persistence Image Assessment

Objectives

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Page 3 of 10

Verify Hawaii array image persistence and irradiation performance are consistent with EUCLID operational modes

Description

Review operational modes, integration times and sampling schemes. Procure representative devices (correct wavelength cut off)and readout ASICS. Test at representative temperature and large dynamic range in flat fields and random PSF simulations.

Deliverables

Test results


TRL 5 by Q4 2011



12



ESA/IPC(2010)81

Page 4 of 10


Cryogenic Fourier Transform Spectrometer Bread Board


Title: Cryogenic Fourier Transform Spectrometer Bread Board

Objectives

The Mach-Zehnder Fourier Transform Spectrometer (FTS) - including the cryogenic FTS Scan Mechanism - is a critical core of the SAFARI instrument. This activity shall further mitigate the risk towards the overall instrument development by 1) improving the optical and optomechanical technology readiness level for the Mach-Zehnder FTS 2) demonstration, test and verification of the optical and spectroscopic performances as required for SAFARI.

Description

This activity will opto-mechanically design, develop and test the SAFARI Fourier Transform Spectrometer at breadboard level. It will investigate an optimum optical design using toroidal and aspheric surfaces. The SAFARI breadbord will interface with the delay-line scan mechanism and will be tested at a wavelength of 10.6 micron at relevant cryogenic temperatures. The tests will prove that the specified performance parameters such as wavefront error, interference contrast and longitudinal and lateral pupil movement in the interferometer over the actuation range of the scan mechanism can be achieved. The breadboard will also verify the positioning accuracy and noise level of the delay line at different actuation speeds and at cryo temperatures. In addition the activity will investigate optimum Mach-Zehnder beamsplitter, filter and reflective surface materials for the SPICA wavelength band. A demonstrator of the SAFARI imaging FTS shall verify the performances can be achieved and are compliant with SAFARI requirements. It should allow experimental verification of performance predictions for different operational modes and support the definition of calibration strategies and the onboard data processing

Deliverables

Breadboard of SAFARI FTS, cryogenic performance test report and SAFARI roadmap.


TRL 5 by Q4 2011



12


T-8479


N/A

European submillimetre/FIR ultra-low noise cryogenic characterization facility

Programme: National Reference: N216-022MM

Title: European submillimetre/FIR ultra-low noise cryogenic characterization facility

Objectives

Setup a European Cryogenic Characterization Facility for ultra-low noise sub-mm/FIR detectors (arrays).

Description

Characterization of sub-mm/FIR detectors (arrays) is currently approached in an ad-hoc and uncoordinated fashion implying uncertainties about different measurement results and meanings. Seldom is an optical measurement at ~ 1x10-19W/sqrtHz achieved reliably and reproducible. Because of the various ongoing technology development activities (e.g., TES, KID), such as for SAFARI as one example, it will become important to setup a European centre performing the characterization of cryogenic sub-mm/FIR detection systems and to avoid duplication of effort and funding. Validation of the test set-up is a driver. The facility should operate for at least 5 years and it should also allow for the measurement of complex radiation patterns and allow to derive several performance parameters (beam efficiency, coupling efficiency, reflection, NEP-s).

Deliverables

An European lab for ultra-low noise submillimetre/FIR detection characterization.


TRL 5 by Q4 2011



60


N/A

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N/A

SAFARI SUB-K COOLER

Programme: National Reference: N220-026MC

Title: SAFARI SUB-K COOLER

Objectives

Prototype development of the SAFARI sub-K cooler. Verification of the I/Fs between sub-K cooler and the 2-4K Joule Thomson cooler.

Description

Sub-K instrument coolers currently under development require recycling a He3 sorption cooler at a constant time interval. During the recycling a higher than average heat load needs to be evacuated by the pre-cooler. However, Joule-Thomson (J-T) coolers that are the pre-cooler baseline, operate in a relatively small temperature range. In order to verify the correct transient behaviour of the cooling chain of JT-cooler plus sub-K cooler, an I/F demonstrator shall be developed that simulates the JT-cooler used to pre-cool the sub-K cooler. Based on the test results, the operation of the sub-K cooler shall be optimised to minimise the impact on the J-T cooler and to establish the correct I/F requirements (including margins) for the J-T coolers. For the SAFARI cooler the activity requires coordination with JAXA. The specific SPICA/SAFARI requirements imply the need for a prototype development of the SAFARI sub-K cooler with the SPICA-specific (multiple) thermal interfaces. The detailed sub-K cooler requirements, especially base temperature (50 to 150 mK) and heat load will depend on the detector technology selection.

Deliverables

Fully tested EQM, documentation.


TRL 5 by Q4 2011



24


T-7969


N/A

KID based array detector (old title: Safari: Integrated antenna/detector development)

Programme: National Reference: N207-018EE

Title: KID based array detector (old title: Safari: Integrated antenna/detector development)

Objectives

The objective of this activity is the development of KID detector arrays with integrated antennas that enable optimum coupling over wide bandwidth.

Description

Kinetic Inductance Detectors (KIDs) have the potential of improved sensitivity in the order of an NEP of 10-19 W/sqrtHz in large format micro-machined integrated antenna arrays as they are needed for SPICA/SAFARI. The objective of this activity is the development of KID detector arrays with integrated antennas that enable optimum coupling over wide bandwidth. The activity requires close cooperation by the two different disciplines of KID technology (material science) and antenna coupling in order to perform the trade-offs, design, analysis, manufacture, and testing that shall lead to the integrity of an integrated KID focal plane array detector. It shall investigate design alternatives and establish a baseline design, assess different fabrication technologies for the integrated antennas and different experimental verification techniques. Subsequently, the electrical performances of the integrated arrays shall be verified by testing. This includes analysis of the test results, explaining any deviations in test results from predictions, and design adjustments or corrections as needed. The activity shall achieve TRL>=5 by Q3/2011. A development roadmap to bring the technology to flight level shall complete the activity.

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Deliverables

KID detector arrays with integrated antennas. Design trade-off, test, verification documentation.


TRL 5 by Q4 2011



18


T-8475


Technologies for (sub) millimeter wave passive instruments - 2nd Semester 2006

Cryogenic mechanisms development


Title: Cryogenic mechanisms development

Objectives

Prototyping and testing of the cryogenic FTS scan mechanism for the SPICA-SAFARI instrument with its overall optical design. The objective is to achieve TRL>=5, demonstrating the system in the relevant space environment, at low temperature (<5 K), with minimised power consumption and with the cryogenic harness not exceeding maximum acceptable heat loads.

Description

The SAFARI instrument proposed for the SPICA mission contains a cryogenic scan mechanism playing a critical role in the overall system performance. The mechanism scans the optical path to achieve the required resolution. The critical items of this mechanism are the working environment and the accuracy. The setup is cooled below 5 K, and the power dissipation of the mechanism must be minimised. The positioning of the mirrors is to be accurate within sub-micron range. Optical parts must be positioned within that range, and the mechanism shall move in the same accuracy range. Cool down from ambient must not affect performance. The development should be based on existing/proven magnetic bearings technology to achieve TRL>=5 of a prototype to be achieved by Q3/2011.

Deliverables

BB


TRL 5 by Q4 2011



20


T-8478


N/A

Readout Electronics (FDM) for KID based Array Detectors


Title: Readout Electronics (FDM) for KID based Array Detectors

Objectives

Development of Readout Electronics (FDM) for KID based Array Detectors.

Description

For the ongoing development of Kinetic Inductance Detectors (KID) the readout electronics applying Frequency-Division Multiplexing (FDM) are crucial. For the concept of FDM and Fast Fourier Transform Spectrometry (FFTS) the TRL needs to be improved to demonstrate feasibility in the SPICA/SAFARI application context. Pixel-array demonstrator camera system(s) with FDM-FFTS shall be developed, integrated and tested in representative environment (e.g., ground based telescopes) in order to achieve for the concept at least TRL>=5 by Q3/2011. The activity shall cover the complete detector system of sensors plus electronics. This includes demonstrating the feasibility to achieve the functionality and performance of laboratory test equipment used so far in set-ups and of commercial processing boards (e.g., FFTS) in instrument flight electronics, possibly including ASICs.

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The principle of FDM is relevant also for Transition Edge Sensor (TES) based detectors. Although the applications of SAFARI and IXO require different FDM implementations and optimizations, significant synergies exist that make the activity important for both cases of SAFARI applying KID or TES based detectors.

Deliverables


TRL 5 by Q4 2011





Cold Readout Electronics (CRE) for Photoconductor Detector


Title: Cold Readout Electronics (CRE) for Photoconductor Detector

Objectives

Development of cryogenic CRE Test Chips and Proton Irradiation Tests.

Description

Cryogenic test chips shall be designed that perform the front-end readout and multiplexing in a Ge:Ga detector demonstrator system at minimized added noise. Capacitive Trans-Impedance Amplifiers (CTIA), Buffered Direct Inject (BDI) also known as Feedback Enhanced Direct Injection (FEDI), and Direct Injection (DI) type channels are readout alternatives that need to be implemented in test chips in order to compare and verify the most suitable concept which allows minimization of the CRE noise effect that determines the overall noise performance of the detector assembly. After integration of the test chips into the photoconductor detector the assembly shall be subjected to proton irradiation with subsequent performance tests. Phase 1 Design and development of optimized CRE for readout noise optimization. Phase 2 Proton irradiation of the integrated detector assembly and subsequent performance verification.

Deliverables

Optimised CRE, irradiation test results.


TRL 5 by Q4 2011



9



RF Coupling and Efficiency Prediction Tool for Sub-mm / FIR Detectors


Title: RF Coupling and Efficiency Prediction Tool for Sub-mm / FIR Detectors

Objectives

Develop an accurate RF coupling and efficiency prediction tool for ultra-low noise submm/FIR detectors and detector arrays.

Description

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Prediction of the performance of sub-mm/FIR detectors and detector arrays is currently performed in a qualitative fashion. Efficiencies well above 100% are routinely obtained, clearly implying invalid assumptions in the models used. Claims of sensitivities surpassing the needed requirements have to be treated with care as a consequence. Because of the various ongoing hardware technology development activities (e.g., TES, KID), such as for SAFARI as one example, it will become important to develop a dedicated tool for the accurate performance prediction of cryogenic sub-mm/FIR detection systems. Validation by measurements of the prediction tool is essential.

Deliverables

Validated tool.


TRL 5 by Q4 2011



20



Broadband 50/50 Transmission/Reflection Sub-millimetre-Wave Beam Splitter


Title: Broadband 50/50 Transmission/Reflection Sub-millimetre-Wave Beam Splitter

Objectives

Development of a broadband 50/50 transmission/reflection beam splitter covering the full SPICA SAFARI instrument band.

Description

The performance of the Mach-Zehnder FTS depends critically on beam splitter characteristics.Two beam spiltters are needed for beam separation and recombination in Mach-Zehnder interferometer. A broadband 50/50 transmission/reflection performance is required because all SAFARI spectral bands are to pass through a single pair of beamsplitters. Standard FT-IR/THz instruments use thin Mylar film as beam-splitter (with thicknesses of a few um to a few 10s of um typically) tuned to maximise efficiency in specific FIR/sub-mm bands. Over the past decade, groups have developed bi-layer Mylar+Si coating or Mylar+Ge coating to improve efficiency and spectral extent of FIR beam-splitter but still not in a band-pass range as required by SAFARI. Although Si is absorbing in the FIR, thin film (sub-wavelength thickness) could provide a first baseline to reach typical efficiency of 4RT>90% over nearly the full band, limiting the loss of contrast in the interferometer. In the SPIRE instrument the beamsplitter design uses two metal meshes in a Fabry-Perot configuration designed to meet the 50% transmission and 50% reflection criteria of an ideal intensity beam splitter. Bandwidth requirement is different from SAFARI.

Deliverables

Design, manufacture and test of a broadband submillimetre-wave 50/50 beam splitter.


TRL 5 by Q4 2011



18



ESA/IPC(2010)81

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Refractive telescope breadboard for PLATO

Programme: National Reference: N216-115MM

Title: Refractive telescope breadboard for PLATO

Objectives

Bread-boarding of a 6 lens telescope, with large diameter lenses and at low working temperature.

Description

It is foreseen to design, manufacture and test a complete telescope in order to identify critical issues and verify manufacturing techniques and mounting methods (i.e. lens mounting to telescope barrel) during phase A/B1. This will allow for a higher level of confidence in the ability to manufacture a high number of telescopes in a timely manner, should PLATO be down-selected for implementation (PLATO consists of many sub-apertures, i.e. individual telescopes, which together form the global aperture). The TBB should optimally be as advanced as an engineering model in order to be able to perform testing and verification. The TBB will consist of 6 spherical (TBC) lenses mounted in a barrel using glue. The working temperature will be ~ 150-170K. The first lens need to be radiation-hardened to minimize darkening effects which will reduce transmittance and thus reduce photon flux to detectors. The following critical points need to be addressed 1) Manufacturing and polishing of relatively large lenses, up to 120 mm (TBC) with correct and accurate optical properties and dimensions 2) Mounting of the individual lenses (glue) to the telescope structure 3) To verify and assess alignment of lenses based on mechanical interfaces mastering without assist of optical testing 4) To verify predictions of defocus generated in operating environment by vacuum and temperature gradients (no refocus will be possible in-flight) 5) Qualification of glued parts at 150-170K (operating temperature). 6) Behaviour characterisation of coatings at operating temperature. 7) To consolidate planning in view of the production of a large number of units. Test activities The following tests/activities are foreseen to verify the above-listed issues: 1) To assemble and disassemble the telescope (to greatest extent possible) multiple times in order to statistically verify that the optical quality can be reached with only mechanical tools for telescope/lens alignment, or if the optical testing needed can be reduced. The cycle to be tested is: mechanical alignment - optical quality measurement - dismounting 2) To measure the thermal and vacuum balance to correlate/verify optical modelling 3) Thermal cycling (TBD) to demonstrate correct behavior of the opto-mechanical components at operational temperature (the telescope has to be mechanically assembled with the correct -misalignment- on-ground, which will then achieve the correct focal length in-flight in cold operating conditions.) 4) Mechanical tests to show compliance with launch conditions in the Soyuz Fregat launcher (using ST-faring).

Deliverables

BB of the telescope tested under relevant conditions.


TRL 5 by Q4 2011


Plato Contract Duration:

18


T-7857, T-8442, T-7760


Technologies for optical passive instruments (harmonised in 2008/2009)

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ESA/IPC(2010)81

Annex III

Justifications for Proposed Tendering Procedure

ESA/IPC(2010)81

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Justification for Proposed Tendering Procedure: DN/S Industrial Policy Committee

ESA Reference Title Firm Fixed Price (Keuro) Proposed Bidder

C217-002PA Euclid CCD Pre-Development 2000 E2V (UK)

Justification:

E2V (UK) are the sole European suppliers of the scientific CCD detectors with the performance required for the Euclid mission.

Justification for Proposed Tendering Procedure: DN/S Industrial Policy Committee

ESA Reference Title Firm Fixed Price (Keuro) Proposed Bidder

C217-010PA Development of optimized CCD for PLATO 2500 E2V (UK)

Justification:

E2V (UK) are the sole European suppliers of the scientific CCD detectors with the performance required for the PLATO mission.