COSMIC VISION 2015-2025

TECHNOLOGY PLAN

Programme of Work 2008-2011 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), the General Support Technology Programme (GSTP) and suggested national initiatives supporting the implementation of the first slice of ESA’s Cosmic Vision 2015-2025 Plan.

Page 2

Page 2 - Intentionally left blank

Page 3

1. Background and Scope

This document provides an update to the Cosmic Vision 1525 (CV1525) ESA Science Programme future missions technology preparation plan, first issued last year as ESA/IPC(2008)33, add1. This plan is submitted to the June 2009 SPC. The evolution of the CV1525 programme is taken into account, – essentially SPC recent decision to include Solar Orbiter as Medium (M) class mission and the outer planet Large (L) mission down-selection - the findings of the associated system study activities and the progress with the international coordination. The plan covers the period 2008-2011 for both the L/M missions under assessment and the future science mission themes.

2. Cosmic Vision Plan 2015-2025

2.1 Cosmic Vision 2015-2025 plan Evolution

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 would 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. In the course of the studies conducted in 2008, and of discussions held with international partners, it became evident that the implementation plan for the first slice of CV1525 had to be modified:

• First, no L mission can be implemented in 2018, as originally foreseen; this is due to the availability of the international partners (whose participation is essential to implement any L mission) and to the mission’s technology readiness status. Both factors require that the L missions are moved to the second slice of CV1525, with the implementation of the first L mission not before 2020. • Second, most of the M mission candidates selected for an Assessment study will require an ESA Cost at Completion (CaC) well in excess of the 300 M€ originally assumed (and likely of order 400-450 M€). • Third, following the difficulties encountered on Bepi Colombo, the SPC decided in November 2008 to not cancel Solar Orbiter, but rather to include Solar Orbiter as a M mission candidate for the 2017-2018 M launch slots of the CV plan. Therefore, there are now six M class missions that are competing for 2017-2018 launches, including Solar Orbiter. At least two M missions will be implemented under the following Programme constraints (e.c. 2008): the overall Cost at Completion for the first CV slice is 900 MEuros and the cost cap per mission is less than 450 MEuros.

Page 4

The original plan based on two rounds of competitive down-selections is maintained, the first to select the mission concepts to enter the Definition phase and the second to select the ones to enter Implementation phase. 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 1.

L-class missions

Laplace

Tandem L1 launch Lisa IXO

M-class missions

Euclid Plato M1 launch Spica Marco-Polo M2 launch Cross-Scale Solar Orbiter

2007 2008 2009 2010 2011 2012 2017 2018 2019 2020 Figure 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)

Table 2.1/1: Cosmic Vision 2015-2025 Mission Candidates Fields M Class L Class Mission of Opportunity Space Plasmas Jupiter system (Cross-Scale) (Laplace) Solar System NEO sample return (Marco Polo) Solar studies (Solar Orbiter) Dark Energy X-Ray astronomy IR astronomy (Euclid) (IXO) (SPICA) Astrophysics Exoplanets / Gravitational waves Asteroseismology (LISA) (Plato)

Page 5

2.2- Cosmic Vision Technology Plan update

The technology plan updates with respect to its last version (ESA/IPC(2008)33, add1, June 2008) reflect the major evolutions of the Cosmic Vision plan: 1- SPC decision to include Solar Orbiter in the M-class mission candidates for a launch in 2017-2018. The Solar Orbiter technology activities have been revisited and are now part of this plan, as are those of the other M missions. 2- Down-selection of the mission to the Jupiter system as the future Outer Planet mission (L-mission candidate for a launch in 2020, in collaboration with NASA and potentially JAXA)) 3- Evolution of the X-ray observatory mission, now called IXO and foreseen in collaboration with NASA and JAXA (L-mission candidate for a launch in 2020) 4- A few changes in some activities related to future science mission themes that could be implemented in the second or third CV slice. Regarding the other five M-class missions, no changes have been implemented yet, awaiting the completion of the assessment system studies. It is foreseen to revisit their technology plan (as done for Solar Orbiter) by end 2009. However, the corresponding technology activities will be placed in 2010-2011 only for the missions that will have been down-selected by SPC for entering the Definition Phase (A/B1) For all missions, only the activities to be placed in 2009 are submitted for approval. Those foreseen to be placed in 2010-2011 are provided for information.

2.3 M-Class candidate Solar Orbiter

At its June 2008 meeting (ESA/C(2008)70) Council was informed by the Director General that it would be proposed to consider Solar Orbiter as one of the potential missions for implementation around 2017. Up to then, Solar Orbiter was in the plan with a 300 M€ cost cap and a planned launch date of 2015. In the course of 2008 it had however become clear that neither of these conditions could be attained. Following the impact on the Science Program’s budget of the mass problems experienced by BepiColombo and the attendant redesign, an alternative approach was necessary to allow Solar Orbiter to remain in the planning.

In November 2008 SPC therefore decided (ESA/SPC(2008)25) to make Solar Orbiter a candidate in the competition for the 2017 M launch opportunity of the CV plan, with the same budgetary constraints as the other M mission candidates.

The Solar Orbiter mission will be subject to the same review process as the M mission candidates selected in 2007. All M mission candidates will undergo a review of their design and technological status, their financial viability and their scientific performance. This information will be made available to the Advisory Structure who will have to perform a scientific ranking of the viable candidates. On the basis of this ranking, the Executive will propose to SPC a number of M mission concepts to enter Definition phase.

Page 6

2.4 L-Class candidate Laplace

In February 2009 a down-selection took place between the two L-class missions Laplace (mission to the Jupiter system) and Tandem (mission to the Saturn system). Both missions had been proposed as collaborations with NASA. An intensive joint ESA/NASA study was made in 2008 and was concluded by a joint decision to retain the mission to the Jupiter system as candidate for the L1 launch slot in 2020.

The activities related to the former Tandem are removed from the plan.

As a potential future additional element to the Laplace mission, penetrators will be studied, and the related activity will be implemented as a special measure for geo- return balance. A phased activity is therefore placed in this technology plan, addressing these novel surface deployment devices. Further to the context of a Jupiter mission like Laplace, such technology has potential in other planetary missions, including Mars.

2.5 L-Class candidate IXO

Following discussions among ESA, NASA and JAXA, in July 2008 the XEUS mission study (originally proposed as an ESA-JAXA collaboration) and the Constellation-X study (a candidate mission in NASA) joined forces to purse the definition of an International X-ray Observatory (IXO).

IXO is a single deployable spacecraft, contrary to the XEUS concept. Accordingly, the formation flying technology developments will no longer be required. The change in focal length from about 35 to 50 meters for XEUS, to 20 to 25 meters for IXO requires the adjustment of one activity in scope and budget.

An Instrument Technology Development Workshop for IXO was held at ESTEC on 30-31 March 2009, involving ESA’s delegate members, IXO instrument representatives and ESA, NASA & JAXA project representatives. This workshop identified the critical items in the payload area, established a development strategy and identified the possible funding sources. The result is reflected in the updated technology development activities described in the annexes of this document.

2.6 Technology Plan Implementation Principle

The preparation of mission adoption, which includes approval of payload and mission CaC, is conditioned on a successful outcome of the assessment and definition study phases. The study progress of a science instrument must be properly phased with that of the overall spacecraft, regardless of which entity is funding the instrumentation activities.

Critical basic technology developments of the spacecraft and science instruments must be completed before entering the Definition Phase. In the context of Cosmic Vision studies and for what regards ESA technology activities, this is essentially applicable to L missions, since M missions are supposed to rely on demonstrated

Page 7

technologies. As a general rule, Technology Readiness Level (TRL) 5-6 is requested at the start of the Implementation Phase.

The responsibility for the science payloads depends on the mission case. It is considered in three categories, depending on the payload procurement scheme, as identified in table 2.6/1.

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. A good coordination between the technology developments under Member States and ESA responsibility will be imperative, avoiding duplication of effort and enabling decisions on missing activities.

Each mission candidate will be evaluated through two parallel industrial assessment system studies, leading to the down-selection of candidate missions and eventually the mission selection. However, implementing the SPC/SPRT recommendations, some modifications have been introduced with respect to payload developments: New instruments development will be closely monitored and the assessment of the payload’s technology readiness will be part of the mission assessment and definition, synchronized with the spacecraft development activities, as indicated in figure 2.

Table 2.6/1: Payload cases, as resulting from the science proposals. Category A = ESA payload; Category B = Payload provided by institutes; Category C = Payload is shared between ESA and institutes.

Mission Payload Member state provision category Marco-Polo B Instrument suite Cross-scale B Instrument suite Solar Orbiter B Instrument suite LAPLACE B Instrument suite PLATO C* Focal planes, and potentially the whole instruments, TBC. EUCLID C* Focal planes (IR and VIS), TBC. SPICA C Telescope provided by ESA. SAFARI cryo instrument provided by science institutes under ESA management. IXO C Optics under ESA responsibility, cryogenic elements TBD, focal plane instruments provided by institutes LISA A TBD (*) Note for PLATO and EUCLID, the Payload could also fall in the category A. The effective scheme will be elaborated in the assessment phase and the Payload category may be changed from C to A depending on the actual Member States involvement.

Page 8

Mission Down-selection Mission selection & Payload AO adoption Launch

Assessment Phase Definition Phase Implementation Phase ~ 2 years ~ 2 years ~ 5-6 years

Spacecraft And n missions two missions one mission Payload activities Assessment studies Design consolidation Development & pre-developments

ESA / Member States LOE MLA agreements

Figure 2: The three phases of mission study and implementation in the CV 2015-2025 Plan does require coordinated system and technology 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, i.e. including the payload. Letters of Endorsement (LOE) and Multi-Lateral Agreements (MLA) will define the commitments and responsibilities of Member States and ESA.

3. Selected Missions and Science Themes

3.1 Selected missions

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 spacecrafts to perform coordinated observations of the Jovian satellites, in particular Callisto, Ganymede, Europa and Jupiter’s 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 telescope optics with the focal plane instrumentation. IXO is now foreseen in collaboration between ESA, NASA and JAXA.

CROSS-SCALE proposes to employ multiple spacecrafts to make simultaneous spatial and temporal measurements of the plasma near Earth to address fundamental questions such as how shocks accelerate and heat particles or how magnetic

Page 9

reconnection phenomena generate or convert energy. The proposed mission would be complemented by JAXA SCOPE mission.

MARCO POLO is a sample return mission from an asteroid of primitive class. It consists of a main spacecraft and a re-entry capsule. The main spacecraft embarks a sample collection device and a suite of instruments. The mission objectives are to characterise a near-earth object at multiple scales and return a surface sample to study the origins and evolution of the Solar System, the role of minor bodies in the process, the origin and evolution of Earth and of life itself. A collaboration with JAXA is under investigation.

Solar Orbiter will produce images of the Sun at an unprecedented resolution and perform closest ever in-situ measurements, using instruments in the visible, extreme ultra violet and X-rays, complemented by in-situ sensors. It will be deployed in a n elliptical orbit around the Sun, with the perihelion as low as 0.23 AU and with increasing inclination up to more than 30° with respect to the solar equator. The mission is foreseen in collaboration with NASA, who would provide the launcher and a contribution to science instrumentation.

EUCLID: Two of the original 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, which implements both techniques, and which is currently undergoing an assessment study. The mission involves a ~1.2m diameter Vis/IR telescope with a wide field (0.5 sq deg) visible imaging channel with 0.1 arcsec resolution. A coaligned near-IR channel performs lower resolution broad band photometry, and a third instrument performs slitless spectroscopy for redshift measurements.

PLATO is a proposal for the next-generation planet finder, consisting of a photometry mission that will detect and characterise transiting exoplanets as well as measure the seismic oscillations of their parent stars. The mission will enable observing rocky exoplanets around relatively bright stars and characterize the star/planet system. Observations of the mission will be complemented by ground- and space-based follow-up observations.

SPICA is a JAXA led mission consisting of a medium and far-infrared observatory with a large-aperture cryogenic telescope. The mission is conceived to perform wide field, high sensitivity photometric mapping at high spatial resolution, spectral analysis and coronagraphy of planets and planetary disks as well as the origin of the universe. The European contribution to the programme includes the large telescope, the SAFARI focal plane instrument and a potential contribution to the spacecraft operations.

3.2 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

Page 10 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 to be 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. Note: the updates received form the FPAG in November 2008 have been considered in this updates plan.

Science Theme: European Venus Explorer (EVE) A Venus deployed balloon experiment.

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 BPOL).

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.

4. Critical Technologies

Table 4/1 and 4/2 present the lists of critical technologies that were identified within the CV proposals.

Page 11

TABLE 4/1: L CLASS MISSIONS Mission Technology area Future Technology development activities Back-up X-Ray optics technology Tandem ruggedizing and environmental testing X-Ray Optics Baffling system, tandem level Petal breadboard X-Ray Optics Production Issues X-ray test facilities upgrading IXO Back-up cryo detector (NFI) Detection systems/ NFI: TES read out and follow on Instruments WFI: prototype and package Auxiliary Instruments Metrology Optical Metrology Last stage cooler Cryogenics Cryocooler chain for TES Readout electronics for cryogenic sensors Components Radiation hard characterization: - Digital components - Memories - Mixed analogue and digital Laplace - Analog components Power LILT solar power systems

Deployment systems/ Development of compact, highly integrated Payloads/Instruments instrument and subsystem suites Penetrators for Jovian Moons: ground demonstration of impact survival of key systems LASER Opto-mechanical stability characterization Metrology system High-power laser system

Propulsion Micro-propulsion Life Time Characterisation LISA Instrument Charge Management

Page 12

TABLE 4/2: M CLASS MISSIONS Mission Technology area Future Technology development activities Development of lightweight ablative material Marco-Polo Development of a CMC/hot structure-based heat Re-entry technologies shield Hypersonic aerothermodynamics/ aerodynamic stability Navigation instrumentation elements Payload/Instruments Surface and sub-surface sampling, Sample transfer / capture Landing Technologies Solar Orbiter Testing High solar flux testing, procedures, facilities Thermal shielding Heat shield materials, mechanisms, sub- systems, entrance windows Solar power Solar cells, generator Antennas Antenna adaptation and validation Optics Digital Mirror Device EUCLID OBDH High Processing Power DPU Rad-Hard CCD Development Detection systems NIR detectors development & readout High dynamic range fast readout CCDs GNC (Guidance x-band transponder (low-mass<0.85kg and Navigation Control) data rates up to 3.5Mbit/s) X-band ranging with low-mass Cross-Scale 1-5 N high Isp=308s, mass= 0.28 kg thrusters hybrid Mon-3 hydrazine, low-power valve Star mapper for 15RPM, low mass spinning S/C Detection Combined ion/electron electrostatic analyser system/Instruments Components Radiation-tolerant memory Telescope assembly verification and testing Cryogenic refocusing mechanism Optics SAFARI: Fourier Transform Spectrometer BB Detection systems SAFARI: Detector development SPICA SAFARI: Focal plane read-out Cryogenics SAFARI: 50 mK ADR SAFARI: Cryogenic mechanisms

Page 13

5. The Technology Plan

5.1 Elaboration of the Technology Plan

¾ ESA TECNET process

The Technology Plan has been defined 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 identified in each CV proposal • An ESA internal verification of the identified critical technologies needs • An assessment of the technological needs and maturity with respect to ongoing running activities, urgency and funding availability.

The resulting technology plan represents the minimum developments required to confirm the feasibility of the CV candidates, over the period 2008-2011. The exercise was done for the entire spacecraft, including the science payload regardless of which entity would ultimately fund the science payload.

¾ ESA and Member States respective responsibilities

In line with the SPRT/SPC recommendations, the technology developments related to science instruments to be provided by the Member States should be conducted through national funding. The Plan indicates which TDAs fall under ESA and Member States responsibilities respectively. Generic technology development activities of strategic importance that are not tailored to a specific mission are undertaken by ESA. Typical examples are the development of infrared detectors or generic technologies for planetary exploration.

For the selected missions and also for the identified future mission themes, one needs to draw the separation line defining the spacecraft elements that would be provided by the Member States for implementing the technology plan. This can readily be achieved for missions corresponding to Payload Categories A (all ESA missions, GAIA-type case) and B (planetary or solar system missions, with instrument suite provided by the Member States). In the Category A case, all technology development activities should be implemented by ESA. This scheme applies to LISA, and could be retained for PLATO and EUCLID depending on the Member State position on the payload of these two missions. In the Category B case, all technology development activities related to the science instruments should be implemented by the Member States. This scheme applies to all planetary and solar system missions in the plan.

The difficulty arises for Astrophysics missions for which the payload falls into Category C. For the selected missions, this applies to SPICA and IXO. The general approach for defining the separation line between ESA and Member States responsibilities was the following: i) Large and complex payload elements that are strongly interleaved with the spacecraft design remain under ESA responsibility. This applies to the

Page 14

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

For the specific cases of PLATO and EUCLID, the actual contributions of the Member States are expected to be defined or confirmed by the end of the Assessment Phase. This is not for the time being a blocking point for implementing the technology development plan, since no or minor specific technology developments are foreseen over the period 2008-2009 for these two missions.

It is important to recall that the current definition of the payload related technology activities represents ESA technical evaluation based on the CV science mission proposals and must be viewed as a “starting point” submitted to SPC for evaluation. It is expected that the Member States will review the proposed activities by involving the relevant experts from the potential instrument providers (national institutes). The payload part of the plan would then be refined, upgraded and endorsed by the SPC as a “Member States Plan” with an agreed implementation scheme. This review process has started, and in fact the IXO related part is updated in this document. As for ESA TDAs, the payload related plan would be updated on a regular basis, depending on the technical progress and programmatic constraints.

¾ ESA activities for L and M missions

No ESA technology activity is foreseen for the M missions before the down-selection at the end of 2009. This logic is consistent with the M mission selection process, since the technology readiness was an important selection criterion for these missions. This does not apply to the science instruments that would be provided by the Member States, for which technology developments may be required for reaching TRL ≥ 5 before entering the implementation phase.

The technology developments for L missions are implemented as soon as possible, in view of reaching TRL ≥ 5 before entering the implementation phase.

The technology developments for the future mission themes are also implemented as soon as possible, in view of reaching TRL ≥ 4 before the next CV call for enabling their selection.

For the practical implementation of ESA TDAs, the proposals for 2009 are firm, whereas the period 2010-2011 is provided for information only. It is planned to revisit this list on a regular basis and update the plan with the results of system studies and ongoing activities. The next revision is planned for the end of 2009, when the M- class assessment study results are available.

Page 15

5.2 ESA Technology Development Activities: role of TRP/CTP/GSTP budgets

ESA technology activities mainly rely on TRP and CTP technology budgets. GSTP is marginally used and some system studies on future mission themes will 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 TRP budget is in particular most adapted to the preparation of the future science mission themes.

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 3).

The GSTP is proposed for the complementary development of non-critical spacecraft equipments and continued development of some payload technologies which have been started in the TRP.

The executive will implement the plan according to general procurement principles and georeturn requirements. In particular, some changes in procurement policies are possible in the frame of the measures necessary to structurally recover georeturn deficits, e.g. by the use of the so-called Special Initiative.

5.3 Member States Technology Development Activities on Science Instrumentation

The science payload developments under Member States funding are marked as “National”. The funding scheme for these activities is gradually being defined by the Member States and is expected to be discussed in a dedicated SPC Workshop on 1st October 2009, and finalised by November 2009.

The use of GSTP is recommended when 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.

5.4 Overview of the proposed activities until 2012

Initially ESA supported technology activities will focus on the L-class missions and prospective themes, as M-class mission candidates were required to have a higher level of maturity at the time of proposal. Exceptions are developments which are applicable to several M-class missions and can be viewed as generic activities i.e. sensors, planetary entry technologies and cryogenics.

However, the selection mechanism does require that the maturity of instrument technologies can be verified at time of the down-selection, the plan therefore recommends that nationally supported instrument developments should be implemented when necessary even for M missions.

Page 16

L-Class Candidate: IXO The most critical development identified is the development of the X-ray optics including proper manufacturing/verification techniques and a suitable backup solution.

L-Class Candidate: Laplace The most critical technologies identified are the development of electronic components and techniques able to cope with the high radiation dose expected in particular in the Jupiter environment. If no solution can be found, the feasibility of the mission is in doubt.

L-Class Candidate: LISA The most urgent need for LISA is to continue the work on the elements that will not be tested as part of the LPF, in particular the development of the high power Laser system.

M-Class Candidate: Euclid Initial testing on existing micro mirrors and sensor developments are already firmly planned as part of the last TRP cycle. Due to its importance for future science missions the development of the NIR infrared sensor will be continued within this cycle.

M-Class Candidate: Cross-Scale Apart from the star tracker for spinning spacecraft, no major developments are required.

M-Class Candidate: Marco Polo The key technologies related to entry are dealt with under the heading generic, due to communalities with other CV mission candidates (Eve) Therefore, activities within TRP and CTP will focus on the sampling mechanism and landing mechanism. Nationally supported activities should cover the complete range of instruments.

M-Class Candidate: Plato Key technologies are the high speed, high dynamic CCDs and readout electronics.

Mission of Opportunity: Spica As mission of opportunity ESA’s direct involvement is limited to providing the telescope. However, significant developments are required for the proposed SAFARI instrument, in particular on detectors.

Technologies applicable to several Science Missions Several key developments have been separated from the initial mission focus, allowing the implementation of a consistent technology effort. These technologies are applicable in particular to several CV missions. Furthermore, there is a high likelihood that they will be required for missions in the second CV slice. This includes: planetary entry technologies (e.g. Marco Polo, Tandem), cryocoolers (e.g. IXO, Spica), and detector technology with wide range application.

Page 17

Prospective science mission themes Investment into the prospective themes is in order of the priority provided by the SSAC.

Science Theme: Exoplanets The technology development activities will be planned on the basis of the recommendation of the Exoplanet working group, expected to be available later in 2009.

Science Theme: Fundamental Physics Most critical developments are on the payload side in particular the development of optical clocks for space use.

Science Theme: European Venus Explorer (EVE) Entry technologies are covered within the generic theme. The key technologies for the balloon envelope and its payload are assumed to be provided nationally.

Science Theme: B-Polarization Satellite Mission (B-Pol) All critical technologies are on the instrument side.

Science Theme: Probing the Heliospheric Origins with an Inner Boundary Spacecraft (PHOIBOS) Initial developments centre around the heat shield technology and near sun power generation system.

Science Theme: Far-InfraRed Interferometer (FIRI) The key to the mission is to demonstrate the feasibility of the double Fourier interferometer, which is on the instrument side and needs to be nationally funded. TRP and CTP are foreseen for the mirror and the optical delay lines.

Page 18

KEY TO TABLES

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

Programme: Programme budget foreseen for the activity

Budget: The total Contract Authorisation (CA) values are given in KEURO, at yearly economic conditions.

Procurement Policy:

• 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 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.

Page 19

Activity Template

Together with the activity description the following information is reported:

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 NASA TRL level of the product that is going to be developed in this activity.

Target Activity: The NASA TRL level expected for the product at the end of the activity. For equipments TRP usually concludes with TRL 3, GSTP at level 5/6. However in the case of components target TRL level in TRP could be higher. It is also understood that TRL levels do not apply to S/W and tools. For these cases description of SW quality, i.e.: architecture, beta version, prototype, or full operational, achieved at the end of the activity.

Application Need/Date: Describes the required TRL level and date for the technology development of which the respective activity is part of on the base of the maturity required by the application. The general rule is that a requirement specifies the need date for a product. For equipments/payloads this is in general TRL 5/6, - the level generally required for Phase B of a project. 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, as stated by NASA, to be achieved at end of the activity for

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

Page 20

Readiness Levels for S/W and tools

Algorithm Single algorithms are implemented and tested to allow their characterisation and feasibility demonstration. Prototype A subset of the overall functionality is implemented to allow e.g. the demonstration of performance. Beta Version Implementation of all the software (software tool) functionality is complete. Verification & Validation process is partially completed (or completed for only a subset of the functionality). S/W Release Verification and Validation process is complete for the intended scope. The software (software tool) can be used in an operational context.

Estimated Duration: Duration of the activity (e.g. 24 month)

Application: Possible mission application/follow-on.

Dossier 0 Reference: Identifies the related Dossier 0 Requirement

SW clause applicability: Special approval is required for activities labeled: 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.

Harmonisation Roadmap: Identifies the related Harmonisation Roadmap Requirement

Page 21

Annex 0 - Technology Plan by Mission Total Application/Mission Program. 2008 2009 2010 2011 Total Approved

2-01 - L-Mission Candidate: Laplace CTP (6) 700 700 5900 6600 TRP (16) 6100 6100 700 350 7150 Total 6800 6800 6600 350 13750

2-02 - L-Mission Candidate: IXO CTP (7) 3500 3500 4500 1400 9400 TRP (5) 2650 2650 900 3550 Total 6150 6150 5400 1400 12950

2-03 - L-Mission Candidate: Lisa CTP (8) 10000 10000 1900 11900 Total 10000 10000 1900 11900

2-04 - M-Mission Candidate: Euclid TRP (2) 100 100 250 350 Total 100 100 250 350

2-05 - M-Mission Candidate: Marco Polo CTP (3) 0 1500 1500 3000 TRP (4) 300 300 2000 2300 Total 300 300 3500 1500 5300

2-06 - M-Mission Candidate: Solar Orbiter CTP (11) 500 500 2800 1700 5000 TRP (8) 1050 1050 1000 200 2250 Total 1550 1550 3800 1900 7250

2-07 - M-Mission Candidate: Spica CTP (3) 0 3500 3500 Total 0 3500 3500

2-08 - M-Mission Candidate: CrossScale CTP (1) 0 1250 1250 Total 0 1250 1250

2-09 - M-Mission Candidate: Plato CTP (2) 0 2500 2000 4500 Total 0 2500 2000 4500

2-10 - Future Science Theme: European Venus Explorer (EVE) Total 0 0

Page 22

Total Application/Mission Program. 2008 2009 2010 2011 Total Approved

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

2-14 - Future Science Theme: Far-InfraRed Interferometer (FIRI) CTP (1) 0 750 750 TRP (2) 0 1750 1750 Total 0 1750 750 2500

2-15 - Technologies applicable to several Cosmic Vision Missions CTP (11) 442 2350 2792 2250 4600 9642 TRP (16) 442 5250 5692 2700 8392 Total 884 7600 8484 4950 4600 18034

Former Darwin mission TRP (3) 0 0 Total 0 0

Tandem GSP (1) 0 0 TRP (5) 0 0 Total 0 0 0 Grand Total CTP 442 17050 17492 26100 11950 55542 Grand Total TRP 442 16550 16992 10550 1300 28842 Grand Total ESA 884 33600 34484 36650 13250 84384

Page 1

Annex I – a List of ESA Cosmic Vision Technology Development Activities

New or Modified Activities

IPC SW Clause Prog. ESA Ref. Activity Title 2008 2009 2010 2011 PP C'try ITT Remarks Appr. applicab. 2-01 - L-Mission Candidate: Laplace Penetrator development within framework of a CTP IPC C213-001PA 500 C(R) UK Q3 N/A Restricted to UK Jovian moon mission Phase1 Review of Mechanism for steerable HGA in TRP N/A T215-100MM 150 C N/A deep space mission Evaluation of star tracker performance in high TRP N/A T205-100EC 250 C N/A radiation environment 2-02 - L-Mission Candidate: IXO Development of IXO (XEUS) Si pore optics and CTP IPC C216-004MM 2000 DN/C NL Q3 N/A Cosine + subs mass production processes 2-06 - M-Mission Candidate: Solar Orbiter CTP IPC C216-100MM Heat rejecting entrance window 300 DN/C I Q3 N/A Selex/Galileo CTP N/A C220-100MT Small high flux test facilities 200 C N/A DN ARCS (A) + subs in TRP IPC T223-100QM Materials Selection and Testing 500 DN/C A Q4 competition Methodology for High Solar flux testing acceleration. Explicitly address combined TRP N/A T220-101MT 200 C N/A UV/thermal and accelerated testing, and existing BC facilities. TRP N/A T220-102MT Solar concentrator test facility upgrade study 100 C N/A High Intensity High Temperature Solar TRP N/A T203-100EP 250 C N/A Generator Study 2-11 - Future Science Theme: Fundamental Physics High performance frequency dissemination TRP N/A T216-033MM 250 N/A techniques- phase1 2-11 - Future Science Theme: B-Polarization Satellite Mission (B-Pol)

Page 2 of 22

Modular Wide Field View RF Configurations TRP Y2008 T207-034EE (old title: Low-loss, low-mass, large lenses with 500 C(1) Q3 N/A anti-reflection coating) 2-15 - Technologies applicable to several Cosmic Vision Missions Development of rad-hard TDI CCD for Dark CTP IPC C216-112MM 500 DN/S UK Q3 N/A E2V Energy mission

Removed Activities

IPC SW Clause Prog. ESA Ref. Activity Title 2008 2009 2010 2011 PP C'try ITT Remarks Appr. applicab. 2-01 - L-Mission Candidate: Laplace TRP T201-001ED Highly Integrated Platform Control processor For information Former Darwin mission Y2007 MMO-643 Hogh Stability optical benches for Darwin TRP Y2007 T203-06MM Passive otpical components for interferometry TRP Y2007 T203-09SC Wavefront tilt sensor TRP Y2007 T203-19MM FIR linear detector array Tandem Titan Montgolfiere Stabilisation and Autonomous Operational This activity will be proposed to the GSP Y2008 T205-010EC GNC Concepts SW GSP GSTP G203-001EP Stirling Converter Technology Development N/A Relevant for Saturn & Aurora Stirling Engine Radioisotopic Power System TRP Y2008 T203-006EP N/A Requirement Study Microwave propagation toolbox for planetary TRP T207-011EE N/A For information atmospheres Radiation characterisation of RT digital CMOS TRP Y2008 T222-015QC N/A technology TRP Y2008 T203-007PA Novel Low Power Radioisotope Power Generator N/A

Page 3 of 22

Optimized electrical power conversion for RHU TRP Y2008 T203-008PA N/A based systems.

2-01 - L-Mission Candidate: Laplace

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. Penetrator development within framework of a CTP IPC C213-001PA 500 C(R) UK Q3 N/A Restricted to UK Jovian moon mission Phase1 Characterisation of radiation resistant materials CTP N/A C223-001QM 500 For information Phase 2 Penetrator development within framework of a CTP N/A C213-002PA 4500 For information Jovian moon mission Phase2 Solar cell LILT design optimisation and CTP N/A C203-101EP 900 For information characterisation Characterisation of radiation resistant materials TRP Y2008 T223-021QM 500 C(2) N/A Second Phase CTP Phase 1 1-Mrad (new requirement: 150krad) power TRP N/A T203-005EP 350 For information converter/system design and prototyping Radiation characterisation of front-end readout TRP N/A T222-013QC 350 For information ASIC TRP Y2008 T222-016QC Radiation hard memory 800 C(2) N/A Latch up protection for COTS (Commercial, off- TRP Y2008 T201-002ED 150 C N/A the-shelf) digital components TRP Y2008 T201-003ED Low mass SpaceWire 150 C(1) N/A DAREplus (Design Against Radiation Effects) TRP Y2008 T201-004ED ASICs for extremely rad hard & harsh 1200 DN/S N/A IMEC (B) + subs environments Radiation Effects on Sensors and Technologies Open TRP Y2008 T204-009EE 500 C(2) for Cosmic Vision SCI Missions (REST-SIM) source TRP Y2008 T222-017QC Radiation Tolerant analogue / mixed signal 725 C N/A

Page 4 of 22

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. technology survey and test vehicle design Front-end readout ASIC technology study and TRP Y2008 T222-018QC development test vehicles for front-end readout 625 C N/A ASICS Survey of critical components for 1 (new requirement: 150krad) Mrad power system TRP Y2008 T222-019QC 350 C(1) N/A design including delta radiation characterisation of RH power EEE components Radiation characterisation of Laplace/Tandem TRP Y2008 T222-020QC 900 C(1) N/A critical RH optocouplers, sensors and detectors Radiation characterisation of RT analogue / TRP N/A T222-014QC 350 N/A For information mixed signal technology Review of Mechanism for steerable HGA in deep TRP/CTP N/A T215-100MM 150 C N/A space mission Evaluation of star tracker performance in high TRP/CTP N/A T205-100EC 250 C N/A radiation environment Total 2-01 - L-Mission Candidate: Laplace 6800 6600 350

2-02 - L-Mission Candidate: IXO

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. CTP N/A C216-002MM Back-up IXO (XEUS) optics technology Phase 2 1400 Pending SST recommendation CTP Y2008 C216-003MM Bessy X-ray test facilities upgrade plan 200 DN/S D N/A PTB (D) Development of IXO (XEUS) Si pore optics and CTP IPC C216-004MM 2000 DN/C NL Q3 N/A Cosine + subs mass production processes CTP Y2008 C216-005MM Panter X-ray test facilities upgrades 300 DN/S D N/A MPE (D)

Page 5 of 22

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. IXO (XEUS) mirror module ruggedizing & CTP Y2008 C216-006MM 1000 C N/A First Phase in TRP environmental testing Ph. II IXO (XEUS) petal breadboard including 6 CTP N/A C216-007MM 2500 For information tandems IXO (XEUS) industrialised mass production CTP N/A C216-008MM 2000 For information process for X-ray Optical Unit (XOU) TRP Y2008 T216-022MM Large area X-ray window development. 350 C(1) N/A TRP Y2008 T216-023MM Back-up IXO (XEUS) optics technology Phase 1 1300 C(1) N/A TRP N/A T216-024MM Baffled IXO (XEUS) mirror module 400 For information IXO (XEUS) mirror module ruggedizing & TRP Y2008 T216-026MM 1000 C(1) N/A Second Phase in CTP environmental testing TRP N/A T216-025MM IXO (XEUS) contamination covers demonstrator 500 For information Total 2-02 - L-Mission Candidate: IXO 6150 5400 1400

2-03 - L-Mission Candidate: Lisa

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. CTP Y2008 C207-010EE Compact low noise magnetic gradiometer 600 C(1) N/A Opto-mechanical stability characterization for CTP Y2008 C207-012PW 2400 C(2) N/A LISA CTP Y2008 C207-013PW Metrology system for LISA 1000 C(2) N/A CTP Y2008 C207-014PW High-power laser system for LISA 3000 C(2) N/A GRS Front End Electronics characterization for CTP Y2008 C207-009PW 1200 C(2) N/A LISA CTP Y2008 C207-011PW Charge Management System for LISA 900 C(2) N/A

Page 6 of 22

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. Outgassing and Contamination characterization CTP Y2008 C207-016PW 900 C(2) N/A for LISA CTP Y2008 C207-015PW LISA micropropulsion lifetime characterization 1900 N/A For information Total 2-03 - L-Mission Candidate: Lisa 10000 1900

2-04 - M-Mission Candidate: Euclid

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. Open TRP N/A T204-027EE 3-D internal charge addition to Geant-4 250 For information source TRP Y2008 T204-028EE Solar/interplanetary electron hazards 100 C(3) N/A Total 2-04 - M-Mission Candidate: Euclid 100 250

2-05 - M-Mission Candidate: Marco Polo

IPC Budget SW Clause Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. 2008 2009 2010 2011 applicab. Autonomous GNC Technology for NEO Operational First phase in TRP, second phase in CTP N/A C205-019EC proximity, Landing and sampling Operations - 500 SW CTP if mission selected Phase 2 Delta-Development and pre-qualification of a CTP N/A C220-021MC European lightweight ablative material for sample 1000 N/A Follow-on from TRP 2008 activity return missions CTP N/A C215-020MM Development of a sample acquisition and transfer 1500 N/A For information

Page 7 of 22

IPC Budget SW Clause Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. 2008 2009 2010 2011 applicab. system for sample return mission to a low-gravity body Ph. 2 Autonomous GNC Technology for NEO Operational TRP Y2008 T205-029EC proximity, Landing and sampling Operations - 300 C Only first phase in TRP SW Phase 1 Development of a landing mechanism for low- TRP N/A T219-031MC 1000 N/A For information gravity body Development of Integrated landing impact TRP N/A T219-032MC 500 N/A For information attenuation structures for capsule Development of a sample acquisition and transfer TRP N/A T215-030MM system for sample return mission to a low-gravity 500 N/A For information body Ph. 1 Total 2-05 - M-Mission Candidate: Marco Polo 300 3500 1500

2-06 - M-Mission Candidate: Solar Orbiter

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. CTP N/A C205-101EC Star tracker 400 For information CTP IPC C216-102MM Heat rejecting entrance window 300 DN/C I Q3 N/A Selex/Galileo Heat shield Breadboard, manufacturing and CTP N/A C220-103MT 700 For information testing High Solar Flux generator prototype CTP N/A C203-104EP 1500 For information manufacturing and validation testing CTP N/A C207-105EE Antenna adaptation Study 200 For information CTP N/A C207-106EE Antenna Adaptation validation 500 For information CTP N/A C204-107TC Small high flux test facilities 200 C

Page 8 of 22

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. DN ARCS (A) + subs in TRP IPC T221-108QT Materials Selection and Testing 500 DN/C A Q4 competition Methodology for High Solar flux testing acceleration. Explicitly address combined TRP N/A T204-109QE 200 C UV/thermal and accelerated testing, and existing BC facilities. TRP N/A T204-110TC Solar concentrator test facility upgrade study 100 C High Intensity High Temperature Solar TRP N/A T203-111EP 250 C Generator Study TRP/CTP N/A T203-112EP Solar Generator screening tests 600 For information TRP/CTP N/A T215-113MX Feedthroughs, door, mechanisms 600 For information High Intensity High Temperature Solar Cell TRP/CTP N/A T203-114EP 800 For information Assemblies Space-wire based Solar Orbiter spacecraft TRP/CTP N/A T201-115ED 400 For information simulator Total 2-06 – M-Mission Candidate: Solar Orbiter 1550 3800 1900

2-07 - M-Mission Candidate: Spica

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. CTP N/A C216-022MM Light-weight mirror demonstrator breadboard 2000 N/A For information SPICA STA: Telescope assembly verification and CTP N/A C216-023MM 500 N/A For information testing; demonstration of critical areas. SPICA Telescope focusing mechanism for CTP N/A C216-024MM 1000 N/A For information secondary mirror Total 2-07 - M-Mission Candidate: Spica 3500

Page 9 of 22

2-08 - M-Mission Candidate: Cross Scale

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. Inertially referenced sensor for spinning CTP N/A C205-025EC 1250 N/A For information spacecraft Total 2-08 - M-Mission Candidate: Cross Scale 1250

2-09 - M-Mission Candidate: Plato

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. Development of optimised high speed, high CTP N/A C216-026PA 500 2000 N/A For information dynamic range CCD. Development of prototype high speed, 16bit CCD CTP N/A C216-028MM 2000 N/A For information processor/ADC Total 2-09 - M-Mission Candidate: Plato 2500 2000

2-11 - Future Science Theme: Fundamental Physics

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. High performance frequency dissemination TRP N/A 750 For information techniques - phase 2 High performance frequency dissemination TRP N/A T216-033MM 250 C N/A techniques- phase1 Total 2-11 - Future Science Theme: Fundamental Physics 250 750

Page 10 of 22

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

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. Modular Wide Field View RF Configurations TRP Y2008 T207-034EE (old title: Low-loss, low-mass, large lenses with 500 C(1) Q3 N/A anti-reflection coating) Total 2-12 - Future Science Theme: B-Polarization Satellite Mission (B-Pol) 500

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

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. Materials compatibility for the PHOIBOS TRP Y2008 T223-038QM 250 C(2) N/A mission (high temperature under high UV load) Near-sun power generation: Identification of best TRP Y2008 T203-035EP 100 C N/A suitable thermoelectric converters Near-sun power generation: Technology TRP N/A T203-036EP 1000 N/A For information demonstration Development of a heatshield concept and material TRP N/A T220-037MC 250 N/A For information screening for near-Sun mission Total 2-13 - Future Science Theme: Probing the Heliospheric Origins with an 350 1250 Inner Boundary Spacecraft (PHOIBOS)

Page 11 of 22

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

IPC Budget SW Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. Clause 2008 2009 2010 2011 applicab. CTP N/A C216-029MM Long-stroke cryogenic optical delay lines 750 N/A First Phase in TRP b) IXO mirror would not be built by cR, who are technology developers TRP N/A T216-039MM FIRI telescope technology pre-development 1000 N/A but will not take on an industrial manufacturing role TRP N/A T216-040MM Long-stroke cryogenic optical delay lines 750 N/A Second Phase in CTP Total 2-14 - Future Science Theme: Far-InfraRed Interferometer (FIRI) 1750 750

2-15 - Technologies applicable to several Cosmic Vision Missions

IPC Budget SW Clause Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. 2008 2009 2010 2011 applicab. Optimised ASIC development for large format CTP N/A C216-017PA 1000 N/A Follow-on to TRP T216-047PA NIR/SWIR detector array. Optimised NIR/SWIR large format array CTP N/A C216-018PA 3000 N/A Follow-on to TRP T216-048PA detector development. Near Earth Space Research X/X/Ka-Band Operational CTP N/A C206-005ET 1000 For information Transponder Engineering Model SW 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 Development of rad-hard TDI CCD for Dark CTP IPC oldN216-012MM 500 DN/S UK Q3 N/A E2V Energy mission CTP Y2008 C222-034QC CCD radiation characterisation 500 C N/A C Characterisation of ultra-stable materials at CTP Y2008 C223-035QM 250 C N/A cryogenic temperature

Page 12 of 22

IPC Budget SW Clause Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. 2008 2009 2010 2011 applicab. High processing power DPU based on high rel. CTP Y2008 C201-030ED 500 C(2) N/A DSP Only if confirmed by IXO (XEUS) CTP N/A C205-031EC High Accuracy Star Tracker 1250 N/A mission study Activity proposed to GSTP-5 Work GSTP Y2008 G220-006MC Hybrid Cryostat Demonstrator 700 N/A Plan Precise Gravitational Modeling of Planetary Operational Activity proposed to GSTP-5 Work GSTP Y2008 G205-004EC 350 Moons and NEO (Near Earth Objects) Asteroids SW Plan TRP Y2008 T212-045GS X/K band feed 350 C N/A TRP Y2008 T212-046GS X/K/Ka band dichroic mirror 300 C N/A Prototype ASIC development for large format TRP Y2008 T216-047PA 500 C(1) N/A NIR/SWIR detector array. Prototype NIR/SWIR large format array detector TRP N/A T216-048PA 2000 N/A Follow on to 2007 TRP activity development. Development & testing of bonding and coating technologies of high temperature materials (C/C, TRP Y2008 T223-054QM 250 C(2) N/A C/SIC, ablative materials etc. ) under extreme conditions TRP Y2008 T220-053MC Advanced 2K JT cooler 700 DN/S N/A RAL (UK) Silicon drift detectors for gamma-ray TRP N/A T216-049MM 500 N/A For information scintillators TRP Y2008 T217-051MP Ablation radiation coupling 400 C Open source Kinetic shock tube for radiation data base for TRP Y2008 T217-052MP 1000 C N/A planetary exploration Materials Charging effects under extreme TRP Y2008 T223-055QM environments (ultra-low temperatures and high 250 C(2) N/A radiation fields) TRP N/A T204-041EE Charging properties of new materials 200 N/A For information Computational tools for spacecraft electrostatic TRP Y2008 T204-042EE 300 C(1) N/A cleanliness and payload analysis

Page 13 of 22

IPC Budget SW Clause Prog. ESA Ref. Activity Title PP C'try ITT Remarks Appr. 2008 2009 2010 2011 applicab. TRP Y2008 T204-043EE Rad-Hard Electron monitor 400 C(1) N/A TRP Y2008 T204-044PA Solid-state neutron detector 300 C(1) N/A Low-noise scintillator detectors for planetary TRP Y2008 T216-050PA 500 C(1) N/A remote-sensing Evaluation of commercial Digital Micro-mirror VISITECH (N) + LAM (F) + TI TRP/CTP Y2008 T216-001MM 884 DN/S N N/A Device for multi-object spectrometers (US) Total 2-15 - Technologies applicable to several Cosmic Vision Missions 884 8650 4950 4600

Page 14 of 22

Annex I – b: List of National Technology Development Activities for Science Payloads

Page 15 of 22

2-01 - L-Mission Candidate: Laplace

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National G207-002EE Low mass wide-band spectrometer N/A To be revised by Member States National N207-001EE Electromagnetic tools for microwave subsurface sounding of planetary bodies N/A To be revised by Member States 2-01 - L-Mission Candidate: Laplace

2-02 - L-Mission Candidate: IXO

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N216-002PA NFI: TES Follow On N/A To be revised by Member States Readout electronics for cryogenic sensors National N216-003PA N/A To be revised by Member States development Readout electronics for cryogenic sensors National N216-004PA N/A To be revised by Member States qualification National N216-005PA WFI Breadboard for IXO (XEUS) N/A To be revised by Member States National N220-010MC 50mK continuous EQM cooler N/A To be revised by Member States National N220-011MC Closed cycle dilution cooler N/A To be revised by Member States Development of back-up cryogenic detector for National N216-006MM N/A To be revised by Member States IXO (XEUS) Narrow Field Instrument (NFI) National N216-007MM VIS Filter on Xray Detector Surface N/A To be revised by Member States National N216-008MM X-POL ASIC readout for integrated gas cell N/A To be revised by Member States Development of processor for IXO (XEUS) High National N216-009MM Time Resolution Spectrometer (HTRS) Si Drift N/A To be revised by Member States Diodes National N216-049PA Cryogenic anti-coincidence sensor development NA To be revised by Member States National/GSTP France N216-HTRS01 Readout electronics for the IXO HTRS Funding in place for 2009 (F) National France N216-HTRS02 Readout electronics for the IXO HTRS Funding in place for 2009 (F)

Page 16 of 22

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National France N216-HTRS03 ASIC design for the IXO HTRS Funding to be requested in 2010 (F) Only necessary if high-energy response of mirror is increased; National France N216-HTRS04 Hybridization of CdTe and SDDs funding to be requested in 2010 (F) Proposal submitted in October 2008, funds obtained 03-12.09. National/GSTP Germany oldN216-009MM Onboard Processing IXO HTRS extension will be submitted for 2010 (D) National/GSTP Germany N216-HTRS06 Performance Studies for IXO HTRS & WFI Funding in place for 03.2009-12.2009 (D) National/GSTP Switzerland N216-HTRS07 Design of a compact filter wheel for the HTRS Funded for 2009 (CH) National/GSTP Germany N216-WFI01 DEPFET Active Pixel Array Development Funding in place (D) National/GSTP Germany N220-WFI03 Thermal Concept Development Funding in place (D) National/GSTP Germany oldN216-007MM UV/Optical blocking filter / entrance window Funding in place (D) National/GSTP Germany N216-WFI05 Filter Sled Development Funding in place (D) National/GSTP UK N216-WFI06 DAQ electronics Need to verify funding situation with Uni Leicester (UK) National/GSTP Germany N224-WFI08 Quality Assurance Funding in place (D) Anticoincidence system for IXO/HXI and National/GSTP France N216-HXI01 Funding in place (F) background studies WFI/HXI, HXI detector front end electronics Part Funding has been requested but spending profile needs to be National/GSTP France N216-HXI02 I reviewed with CNES (F) WFI/HXI, HXI detector front end electronics Part Funding has been requested but spending profile needs to be National/GSTP France N216-HXI03 II reviewed with CNES (F) WFI/HXI, HXI detector front end electronics Part Funding has been requested but spending profile needs to be National/GSTP France N216-HXI04 III reviewed with CNES (F) National Italy oldN216-008MM XPOL - GPD Funding in place (I) National Italy N216-XPOL02 XPOL - FW Funding in place (I) National Italy N216-XPOL03 XPOL - BEE Budget to be approved later (I) National Italy N216-XPOL04 XPOL - CE Budget to be approved later (I) National Italy N208-XPOL05 XPOL - Test/Calibration Budget to be approved later (I) Optimization of the TES-based micro-calorimeter National Netherlands oldN216-002PA Funding in place (NL) array for IXO/XMS Optimization of Frequency-Domain-Multiplexed National Netherlands oldN216-003PA Funding in place (NL) read-out electronics for Micro-calorimeter arrays National Germany N216-XMS01 SQUID development for cryogenic sensor readout Funding to be secured for 2010; Germany only ready to fund

Page 17 of 22

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. incase of scientific interest in instrument (D); to be secured for 2010 National/GSTP Netherlands N216-XMS03 Qualification activities on detector arrays Funding in place; Activity is running (NL) National/GSTP Netherlands oldN216-004PA Qualification activities on read-out electronics Funding to be requested later (NL) Development of electrical interconnections for the This critical activity is not funded yet (possible interest UK, F, National N216-XMS04 (cold) detector components Fin, NL) (partly approved Fin funding 150 Finnish GSTP?) partial funding in place; need to verify necessity for follow-up National oldN220-011MC Closed cycle dilution cooler funding (F) originally this was assumed to be an ESA supplied item; actual National TBD N220-XMS16 optimize full cooling chain need for this activity depends on international conditions and needs to be reviewed National Italy oldN216-049PA Cryogenic anti-coincidence sensor development Initial funding in place (I) Need to confirm Prodex or Uni of Geneva funding by 04/09 National Switzerland N216-XMS05 design of compact filter wheel for XMS (CH); Support by XMS team to optimize the result will be provided National UK N216-XMS06 develop polarization sensitive filters Funding not in place (UK) National UK N216-XMS07 demonstrate performance of beam diverter Funding not in place (UK) MIS Based Micro-Calorimeter Array of 16x16 National/GSTP France oldN216-006MM Funding in place (F) pixels. Large (32x32 pixels) MIS Based Micro- National/GSTP France N216-XMS08 Funding to be requested later (F) Calorimeter Array for IXO/XMS First Acquisition chain for the MIS Based Micro- National/GSTP France N216-XMS09 Funding in place (F) Calorimeter Array Optimized Acquisition chain for the 32x32 pixels National/GSTP France N216-XMS10 Funding to be requested later (F) MIS Based Micro-Calorimeter Array National UK N216-XGS01 p-channel CCDs Funding not in place (UK) National UK N216-XGS02 EM CCDs for soft X-ray spectroscopy Funding not in place (UK) National UK N216-XGS03 Light blocking filters Funding not in place (UK) National UK N216-XGS04 X-ray Sensitive CMOS Imagers - Phase 1 Funding not in place (UK) National UK N216-XGS05 X-ray Sensitive CMOS Imagers - Phase 2 Funding not in place (UK) 2-02 - L-Mission Candidate: IXO

Page 18 of 22

2-04 - M-Mission Candidate: Euclid

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N216-012MM Development of rad-hard TDI CCD for EDEM. N/A To be revised by Member States 2-04 - M-Mission Candidate: Euclid

2-05 - M-Mission Candidate: Marco Polo

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N216-014PA Cameras N/A To be revised by Member States National N216-015PA Laser Altimeter N/A To be revised by Member States National N216-016PA Mid IR Fourier mapping spectrometer N/A To be revised by Member States National N204-013PA Neutral Particle Analyser N/A To be revised by Member States National N216-017PA Visible Near IR imaging spectrometer N/A To be revised by Member States 2-05 - M-Mission Candidate: Marco Polo

2-07 - M-Mission Candidate: Spica

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N215-019PA Cryogenic mechanisms development N/A To be revised by Member States National N216-020PA Safari: Detector development N/A To be revised by Member States National N216-021PA Safari: Focal plane read-out N/A To be revised by Member States National N207-018EE Safari: Integrated antenna/detector development N/A To be revised by Member States

Page 19 of 22

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N220-026MC 50mK EM Cooler N/A To be revised by Member States National N220-027MC 50mK pre-cooler simulator 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 N216-023MM BIB detectors and cold readout for SPICA N/A To be revised by Member States National N216-024MM SPICA European Science Instrument Fourier transform spectrometer breadboard N/A To be revised by Member States National N216-025PA Cryogenic Fourier Transform Spectrometer Bread Board N/A To be revised by Member States 2-07 - M-Mission Candidate: Spica

2-08 - M-Mission Candidate: Cross Scale

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N204-028EE Combined ion/electron electrostatic analyser study N/A To be revised by Member States 2-08 - M-Mission Candidate: Cross Scale

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

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N223-033QM Development of balloon materials for VENUS environment N/A To be revised by Member States National N219-031MC Inflation system for balloon 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 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 2-10 - Future Science Theme: European Venus Explorer (EVE)

Page 20 of 22

2-11 - Future Science Theme: Fundamental Physics

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. To be revised by Member National N216-035PA Breadboarding of accelerometer based on Atomic Interferometry N/A States To be revised by Member National N216-036MM Critical Optical frequency comb/synthesiser sub-system technologies N/A States To be revised by Member National N216-037MM Laser cooling trapping systems N/A States Ultra-narrow frequency stable laser technology for probing optical clock local To be revised by Member National N216-038MM N/A oscillator transitions States To be revised by Member National N216-039MM Stimulated Raman transition inducing diode laser N/A States National Breadboard of an ion optical clock 2-11 - Future Science Theme: Fundamental Physics

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

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National N215-043PA Cryogenic Half-wave plate rotation mechanism 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 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 2-12 - Future Science Theme: B-Polarization Satellite Mission (B-Pol)

Page 21 of 22

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

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. a) 20 m robot built under this activity will be to a large part a repeat build of already Far IR passive optical developed technology, necessitated by the change imposed by the modification from National N216-046MM N/A components XEUS to IXO requirements, and therefore necessarily it needs to be built by the already existing consortium c) 20 m robot built under this activity will be ESA property and would be made Large FOV double-Fourier National N216-047MM N/A available to industrial consortia bidding for future IXO activities, under open interferometric breadboard competition Optical generation and National N216-048MM distribution of tunable FIR N/A To be revised by Member States Local Oscillator 2-14 - Future Science Theme: Far-InfraRed Interferometer (FIRI)

Tandem

SW Clause Prog. Member State(s) ESA Ref. Activity Title Remarks applicab. National G207-003EE Low resource deep space atmospheric sounder N/A To be revised by Member States National T213-012MM Heatflow Control System N/A For information Tandem

Page 22 of 22

Annex II – a: Detailed Description of ESA Cosmic Vision Technology Development Activities

2-01 - L-Mission Candidate: Laplace Item ID# : 228 Programme: CTP Reference: C219-001PA 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 with their delivery systems are 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 onto 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 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 behavior 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. Application Current TRL: 2 Target TRL: 3 2010 Need/Date: Application Contract Laplace 9 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 31 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/Tandem 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).

Page 2 of 104

Deliverables Design data of materials properties for the selected mission case. Application Current TRL: 2 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract Laplace 36 Mission: Duration: Reference to S/W Clause: N/A T-8481 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 229 Programme: CTP Reference: C219-002PA Title: Penetrator development within framework of a Jovian moon mission Phase2 Objectives Development to TRL 5 of a penetrator (structure + platform elements) including full scale system-level impact trials. 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), and iii) full-scale subsystem level trials (TRL5). Deliverables i) Hardware elements of a penetrator, including structure and sub-systems. ii) Modeling and impact trial reports. Application Current TRL: 3 Target TRL: 5 2013 Need/Date: Application Contract Laplace 27 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 232 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 these 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 Application Current TRL: 3 Target TRL: 5 2012 Need/Date: Application Contract Laplace 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 3 of 104

Item ID# : 31 Programme: TRP Reference: T223-021QM Title: Characterisation of radiation resistant materials Phase 1 Objectives An assessment and characterisation of radiation resistance of materials to high radiation field of Laplace mission is required. The asessment results will be used to produce design data 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. Description Selection of materials, testing of materials, derivation of safe operation limit, design data. Deliverables Test results, selection of resistant materials, design data. Application Current TRL: 2 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract Laplace 36 Mission: Duration: Reference to S/W Clause: N/A T-8481 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 60 Programme: TRP Reference: T203-005EP 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 Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 136 Programme: TRP Reference: T222-013QC 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.

Page 4 of 104

Deliverables Test plans, Test reports including data analysis, final report, and tested samples Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 140 Programme: TRP Reference: T222-016QC 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 Test plans, Test reports including data analysis, final report, and tested samples Application Current TRL: 2 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract Laplace 36 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 154 Programme: TRP Reference: T201-002ED 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 particurlarly 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.

Page 5 of 104

Deliverables PFM Hardware Application Current TRL: 3 Target TRL: 5 TRL5 by 2010 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 155 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 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 Application Current TRL: 3 Target TRL: 5 TRL 6 by 2011 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: N/A T-8483 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 158 Programme: TRP Reference: T201-004ED 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 Application Current TRL: 3 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Laplace 18 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER

Page 6 of 104

Consistency with Harmonisation Roadmap and conclusion: Microelectronics Dossier (1st semester 2007) - AIM A - Deep Submicron ASIC technologies (A1, A2, A8)

Item ID# : 178 Programme: TRP Reference: T204-009EE 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 modeling capabilities; strawman Geant4 geometry models of all of the Cosmic Vision mission spacecraft Application Current TRL: 2 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Laplace 24 Mission: Duration: Reference to S/W Clause: Open source T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 208 Programme: TRP Reference: T222-017QC 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. Current TRL: 2 Target TRL: 3 Application TRL5 by 2011

Page 7 of 104

Need/Date: Application Contract Laplace 7 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 209 Programme: TRP Reference: T222-018QC 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 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. Application Current TRL: 1 Target TRL: 2 TRL5 by 2011 Need/Date: Application Contract Laplace 6 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 210 Programme: TRP Reference: T222-019QC Survey of critical components for 1 (new requirement: 150krad) Mrad power system design including Title: 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 Application Current TRL: 2 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER

Page 8 of 104

Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 211 Programme: TRP Reference: T222-020QC Title: Radiation characterisation of Laplace/Tandem critical RH optocouplers, sensors and detectors Objectives Radiation characterization of radiation tolerant (minimum 150krad) optocouplers to identify suitability for LAPLACE TANDEM 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 Test plans, Test reports including data analysis, final report, and tested samples Application Current TRL: 2-3 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 138 Programme: TRP Reference: T222-014QC 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 Test plans, Test reports including data analysis, final report, and tested samples Application Current TRL: 3 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: N/A T-8480 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 230 Programme: TRP/CTP Reference: Title: Review of Mechanism for steerable HGA in deep space mission Objectives Review current capabilities and constraints with current mission profile and environment Description

Page 9 of 104

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) Application Current TRL: 4 Target TRL: 4 TRL5 by 2012 Need/Date: Application Contract Laplace 12 Mission: Duration: Reference to S/W Clause: n/a ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 231 Programme: TRP/CTP Reference: Title: Evaluation of star tracker performance in high radiation environment Objectives Review particle environment and simulate effects on star tracker performance Description The Jovian environment has a high density of charged particles (mainly electrons). Despite heavy shielding, residual particle interactions with detectors will take place, and in addition secondary photon production will enhance background. It is expected that sensors will loose sensitivity due to a kind of snow effect. This shall be simulated (either h/w or s/w) and the feasibility of using currently availably star trackers shall be assessed. Deliverables

Application Current TRL: 4 Target TRL: 4 TRL5 by 2012 Need/Date: Application Contract Laplace 18 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 10 of 104

2-02 - L-Mission Candidate: IXO

Item ID# : 98 Programme: CTP Reference: C216-002MM 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) Application Current TRL: 4 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract IXO (XEUS) 16 Mission: Duration: Reference to S/W Clause: N/A T-8452 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 100 Programme: CTP Reference: C216-003MM 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 Application Current TRL: NA Target TRL: NA Ready end 2010 Need/Date: Application Contract IXO (XEUS) 24 Mission: Duration: Reference to S/W Clause: N/A T-7959 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 104 Programme: CTP Reference: C216-004MM 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

Page 11 of 104

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 Application Current TRL: 3 Target TRL: 4 TRL4 by end 2010 Need/Date: Application Contract IXO (XEUS) 18 Mission: Duration: Reference to S/W Clause: N/A T-7959 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 112 Programme: CTP Reference: C216-005MM 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 Application Current TRL: NA Target TRL: NA Ready end 2010 Need/Date: Application Contract IXO (XEUS) 24 Mission: Duration: Reference to S/W Clause: N/A T-7959 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 120 Programme: CTP Reference: C216-006MM Title: IXO (XEUS) mirror module ruggedizing & environmental testing Ph. II Objectives

Page 12 of 104

To demonstrate the flight worthiness of Si x-ray pore optic modules for IXO (XEUS) Description - Modeling & analysis of stack adhesion forces.- Improvements to state of the art manufacturing of mirror modules to ensure compatibility with IXO environmental requirements, for instance annealing, contamination control within the limits of the available financial envelope (it is clear that a chip manufacturing type assembly line is coherent with the cleanliness requirements for stacking XEUS modules, but beyond the funding levels available from TRP), bracket/dowel pin modification including: * trade-off new materials compatible with integration (room temp) and operational temp., e.g. HB-Cesic, Si3N4, Si. * lightweighting * compatibility with integration into a petal and possible baffle mounts * compatibility with the requirements of IXO - Procurement of equipment upgrades and any necessary modification of the stacking robot, including for an innermost radii module.- Procurement of sufficient silicon plates and brackets to perform tests and stack modules with the discard of an overhead of plates, such that the stacks of the mirror module to be placed under environmental test are formed from virgin plates (i.e. plates that have not been stacked then separated).- Production of at least 3 (TBD) mirror modules (possibly of different radii), one module with coating compatible with IXO requirements (TBD).- Environmental testing at relevant facilities (mechanical, thermal) with x-ray testing of the modules pre and post each environmental test.- Planning for industrialisation of processes. Deliverables Analysis and modeling results. 3(TBD) IXO (XEUS) mirror modules of stacked silicon plates, at least one coated. Results of x-ray, mechanical and thermal testing. Industrialisation plans. Application Current TRL: 3 Target TRL: 5 TRL5 by end 2009 Need/Date: Application Contract IXO (XEUS) 18 Mission: Duration: Reference to S/W Clause: N/A T-8453 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 121 Programme: CTP Reference: C216-007MM 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 modeling 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 a 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 modeling 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 modeling 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 Application Current TRL: 2 Target TRL: 5 (XEUS) petal by Need/Date: mid 2011 Application Contract IXO (XEUS) 24 Mission: Duration: Reference to S/W Clause: N/A T-8456 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 13 of 104

Item ID# : 212 Programme: CTP Reference: C216-008MM 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 robotised 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. Application Current TRL: 2 Target TRL: 4 TRL 4 by 2009 Need/Date: Application Contract IXO (XEUS) 12 Mission: Duration: Reference to S/W Clause: N/A T-7959 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 91 Programme: TRP Reference: T216-022MM Title: Large area X-ray window development. Objectives Development of large area, high performance X-ray windows. Description Recent GSTP development programme work has resulted in the improvement of low-energy X-ray response of small, membrane and grid supported X-ray windows. For X-ray astronomy missions there is a requirement for larger area windows with improved response. Currently available technology was developed more than a decade ago (as part of the Beppo Sax programme) and would benefit greatly from the application of recent small window work. Deliverables Characterised large area, high-transmission X-ray windows. Application Current TRL: 3 Target TRL: 6 TRL5 by 2012 Need/Date: Application Contract IXO (XEUS) 24 Mission: Duration: Reference to S/W Clause: N/A ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 97 Programme: TRP Reference: T216-023MM 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 focusing mirror shells, demonstrating ability to meet the requirements of the IXO (XEUS) telescope including environmental.

Page 14 of 104

- 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 focusing in x-ray. - Analysis and elaboration to describe an industrialised manufacturing process to show compatibility with IXO (XEUS) timescales. Deliverables Analysis and modeling 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. Application Current TRL: 3 Target TRL: 4 TRL 4 by 2009 Need/Date: Application Contract IXO (XEUS) 16 Mission: Duration: Reference to S/W Clause: N/A T-8452 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 99 Programme: TRP Reference: T216-024MM 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. Application Current TRL: 1 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract IXO (XEUS) 12 Mission: Duration: Reference to S/W Clause: N/A T-7854 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 120 Programme: TRP Reference: T216-026MM 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 - Modeling & analysis of stack adhesion forces.- Improvements to state of the art manufacturing of mirror modules to ensure compatibility with IXO environmental requirements, for instance annealing, contamination control within the limits of the available financial envelope (it is clear that a chip manufacturing type assembly line is coherent with the cleanliness requirements for stacking 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.

Page 15 of 104

HB-Cesic, Si3N4, Si. * lightweighting * compatibility with integration into a petal and possible baffle mounts * compatibility with the requirements of IXO- Procurement of equipment upgrades and any necessary modification of the stacking robot, including for an innermost radii module.- Procurement of sufficient silicon plates and brackets to perform tests and stack modules with the discard of an overhead of plates, such that the stacks of the mirror module to be placed under environmental test are formed from virgin plates (i.e. plates that have not been stacked then separated).- Production of at least 3 (TBD) mirror modules (possibly of different radii), one module with coating compatible with IXO requirements (TBD).- Environmental testing at relevant facilities (mechanical, thermal) with x-ray testing of the modules pre and post each environmental test.- Planning for industrialisation of processes. Deliverables Analysis and modeling results. 3(TBD) IXO (XEUS) mirror modules of stacked silicon plates, at least one coated. Results of x-ray, mechanical and thermal testing. Industrialisation plans. Application Current TRL: 3 Target TRL: 5 TRL5 by 2009 Need/Date: Application Contract IXO (XEUS) 18 Mission: Duration: Reference to S/W Clause: N/A T-8453 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 119 Programme: TRP Reference: T216-025MM Title: IXO (XEUS) contamination covers demonstrator Objectives To demonstrate contamination covers for the protection of the optics of the IXO (XEUS) telescope. These covers will serve to protect the optics during ground operations, launch, cruise and operation mission stages. Description - Design, modeling 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 modeling results Contamination cover demonstrator Characterisation results. Application Current TRL: 1/2 Target TRL: 4 TRL 3/4 by 2011 Need/Date: Application Contract IXO (XEUS) 18 Mission: Duration: Reference to S/W Clause: N/A T-8457 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 16 of 104

2-03 - L-Mission Candidate: Lisa

Item ID# : 202 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. Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Lisa 24 Mission: Duration: Reference to S/W Clause: N/A ESTER Consistency with Harmonisation Roadmap and conclusion: Consistent with EMC Dossier

Item ID# : 214 Programme: CTP Reference: C207-012PW 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

Page 17 of 104

• Opto-mechanical assembly stability verification in representative flight condition. The pathlength error associated with this noise term appears twice, as the light travels between M1 and M2 twice. Thus picometre level fluctuations in the inter-mirror distance (IMD) are significant in the overall LISA pathlength error budget.

Tasks include design of the LISA opto-mechanical assembly and test plan definition, design of a test set-up suitable for the characterization of the identified opto-mechanical assembly critical performance, development of the LISA opto- mechanical assembly breadboard and test set-up, opto-mechanical assembly testing and analysis of test results. Deliverables Breadboard Application Current TRL: 3 Target TRL: 5 TRL5 by 2010 Need/Date: Application Contract Lisa 24 Mission: Duration: Reference to S/W Clause: N/A T-7875 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 215 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 Application Current TRL: 3 Target TRL: 5 TRL5 by 2010 Need/Date: Application Contract Lisa 18 Mission: Duration: Reference to S/W Clause: N/A T-663 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 216 Programme: CTP Reference: C207-014PW

Page 18 of 104

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 Application Current TRL: 3 Target TRL: 5-6 TRL5 by 2011 Need/Date: Application Contract Lisa 24 Mission: Duration: Reference to S/W Clause: N/A T-722,T-726 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 218 Programme: CTP Reference: C207-009PW Title: GRS Front End Electronics characterization for LISA Objectives This activity will assess the suitability of the current Front-End Electronics (FEE) components to the LISA requirements and identify and test alternatives in case they prove not to be adequate. Description The residual acceleration required by LISA must be a factor 10 better than that required of LISA Pathfinder. To this end, the GRS Front-End Electronics (FEE) must strictly fulfill all LISA requirements. Currently, for example, the actuation noise measured in the LPF GRS FEE is not compliant with the LISA specification. Even though in LISA there will be no direct actuation along the x (drag free) axis – that could be impacted by this excess noise - the GRS electrodes facing the Test Mass x face will be used for the Test Mass attitude control and thus individual gain fluctuation of each electrode might lead to a non-zero force applied to the Test Mass. This activity will assess the suitability of the current FEE components such as ADC and DAC, reference voltage sources and auto-zero amplifiers to the LISA requirements and identify and test alternatives in case they prove not to be adequate. The redundancy concept will also be revisited for the LISA design. Deliverables Engineering Model Application Current TRL: 4 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Lisa 24 Mission: Duration: Reference to S/W Clause: N/A T-698 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 19 of 104

Item ID# : 219 Programme: CTP Reference: C207-011PW 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 Application Current TRL: 3 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Lisa 24 Mission: Duration: Reference to S/W Clause: N/A T-7945 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 220 Programme: CTP Reference: C207-016PW 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 Application Current TRL: 3 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Lisa 24 Mission: Duration: Reference to S/W Clause: N/A T-8391 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 217 Programme: CTP Reference: C207-015PW Title: LISA micropropulsion lifetime characterization Objectives

Page 20 of 104

The activity shall verify all micropropulsion system design features that are impacted by lifetime and assess possible design modifications. 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 Engineering Model Application Current TRL: 6 Target TRL: 8 TRL8 by 2013 Need/Date: Application Contract Lisa 36 Mission: Duration: Reference to S/W Clause: N/A T-1013 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 21 of 104

2-04 - M-Mission Candidate: Euclid

Item ID# : 170 Programme: TRP Reference: T204-027EE Title: 3-D internal charge addition to Geant-4 Objectives To allow assessment of electric fields and potentials on 3-D objects (especially thick optical components) within a realistic spacecraft shielding. Description The 3-D radiation transport code GEANT-4 can simulate electron and proton penetration to give deposited current in internal materials. Until now tools have been 1-D, but 3D effects are important. A 3-D circuit model will be created to calculate the electric fields, current and potentials in 3-d objects. DMDs will also require detailed charging analysis. Deliverables model SW as stand alone tool, related SW documentation, input and output files of test cases Application Current TRL: s/w (pre-study) Target TRL: s/w (beta) TRL5 by 2011 Need/Date: Application Contract Euclid 18 Mission: Duration: Reference to S/W Clause: Open source T-8396 ESTER Consistency with Harmonisation Roadmap and conclusion: SEENoTC

Item ID# : 176 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 interplanetary 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 Application Current TRL: s/w (pre-study) Target TRL: s/w (beta) TRL5 by 2011 Need/Date: Application Contract Generic 12 Mission: Duration: Reference to S/W Clause: N/A T-19 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 22 of 104

2-05 - M-Mission Candidate: Marco Polo

Item ID# : 36 Programme: CTP Reference: C205-019EC Title: Autonomous GNC Technology for NEO proximity, Landing and sampling Operations -Phase 2 Objectives 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 Background Several small-body missions currently considered by the Agency such as Don Quijote and Marco Polo, the later being selected for assessment as part of the Cosmic-Vision 2015-2025 programme, are characterized by unique challenges to go beyond the current European state-of-the-art in Navigation, Guidance and Control technologies. The characteristics, in particular the GNC performance and autonomy requirements, of a NEO sample return mission require an increase in 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. During the cours activity, the following tasks shall be performed: Task 1 - Mission analysis and system engineering. Task 2 - Strategies for proximity operations, landing and sampling operations. Task 3 - Navigation chain. Task 4 – Simulation and Testing environment(s) suite Task 5 – Autonomous G-N-C components Task 6 – Autonomous GNC system detailed designs. Task 7 – Autonomous GNC system demonstrator performances verification and validation 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.

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 modeling - 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) Application Current TRL: 2-4 Target TRL: 5-6 TRL5 by 2011 Need/Date: Application Contract Marco Polo 18 Mission: Duration: Reference to S/W Clause: Operational SW T-8071 ESTER

Page 23 of 104

Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 81 Programme: CTP Reference: C220-021MC Delta-Development and pre-qualification of a European lightweight ablative material for sample Title: return missions Objectives The objective is to complete the development, and subsequently characterise and pre-qualify a European ablative heatshield material for the Earth return capsule of sample return missions (e.g. Mars, comets, asteroids), able to cope with the stringent environment (typical peak heat fluxes of 10-20MW/m2 and heat loads up to 200MJ/m2) while conforming to the mass budget. The development shall be based on the material developed in a previous TRP-activity (expected to be completed by end of 2009). The pre-qualification shall include an extensive plasma test campaign. Description Though proposed specifically for Marco Polo such development would generally serve sample return missions with a high speed Earth re-entry (e.g. MSR) and possibly also human return missions (CSTS) or Venus exploration missions. A TRP activity has already been approved (in SD-4) with TO from TEC-MCT with planned COR1 in 03/08 (budget 400kEuro). The already approved activity will prepare the ground (requirements consolidation, development of manufacturing routes, preliminary material development and characterisation). The activity proposed here will represent the logical follow-on to complete the material development and pre-qualification. The work should follow the following step-wise approach: - Capability assessment of the material developed in the previous activity - Iterative fine-tuning of the material composition to match the refined technical requirements (from Marco Polo feasibility studies) - Extensive sample characterisation campaign (thermal, mechanical, outgassing, etc.) - Breadboard design and manufacturing of flat-plate assemblies with tile interfaces - Extensive pre-qualification campaign including plasma testing in stagnation and flat plate configuration - Assessment of advanced ablative heatshield concepts based on the newly developed material - Refinement of a selected heatshield concept and analytical verification Deliverables Material samples, documentation Application Current TRL: 3 Target TRL: 6 TRL5-6 by 2011 Need/Date: Application Contract Marco Polo 18 Mission: Duration: Reference to S/W Clause: N/A T-8283, T-8538 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 95 Programme: CTP Reference: C215-020MM Development of a sample acquisition and transfer system for sample return mission to a low-gravity Title: body Ph. 2 Objectives Development of an end-to-end breadboard for a sample acquisition and transfer mechanism on a NEO in micro-gravity Description Mission concept immature and methods for sample collection, transfer & containment are all poorly scoped and may need substantial development (in a number of activities). Target TRL: 5 by 2011. Shall be coordinated with ongoing GSTP activity. Will include design, breadboarding and testing in relevant environment (parabolic flight) Deliverables Technical Notes (incl. executive summary), Breadboard, test results Application Current TRL: 3 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract Marco Polo 24 Mission: Duration: S/W Clause: N/A Reference to T-8486

Page 24 of 104

ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 36 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 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 electrical/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;

Page 25 of 104

Task 6 – Autonomous GNC system detailed design: using Marco Polo as a reference mission the detailed analysis and design of all the GNC modes for proximity operations, landing and sampling operations will be performed. Note: all the required GNC modes will be developed using the validated G-N-C components. Task 7 – Autonomous GNC system demonstrator performances verification and validation: the performance and robustness of the autonomous GNC system for the selected reference mission (Marco polo) will be assessed using a validated high fidelity end-to-end simulation environment. Monte Carlo test campaign will be carried out to ensure that the spacecraft achieves the mission requirements for nominal and contingency scenarios. In the second verification & validation step a demonstrator of the autonomous GNC system will be developed. This demonstrator will consist of autocoding the GNC application software and implementing them in a representative avionics. The Image Processing (IP) algorithms will also be implemented into the vision based camera system developed in the VisNav activity. The real-time closed loop performance of the demonstrator will be performed on the avionics test bench developed in Task 4 which will include the physical camera, optical stimulator (ViSOS) and PANGU. Note: a numerical model of the altimeter is contemplated at this stage of the development. Upon successful completion of the activity, the autonomous GNC system demonstrator tailored for Marco Polo mission will achieve a TRL 5-6 (software). Note: NO provision has been made for optical navigation camera Engineering Model development.

Background Several small-body missions currently considered by the Agency such as Don Quijote and Marco Polo, the later being selected for assessment as part of the Cosmic-Vision 2015-2025 programme, are characterized by unique challenges to go beyond the current European state-of-the-art in Navigation, Guidance and Control technologies. The characteristics, in particular the GNC performance and autonomy requirements, of a NEO sample return mission require an increase in 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 modeling - 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) Application Current TRL: 2-4 Target TRL: 5-6 TRL5 by 2011 Need/Date: Application Contract Marco Polo 18 Mission: Duration: Reference to S/W Clause: Operational SW T8071 ESTER

Page 26 of 104

Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 70 Programme: TRP Reference: T219-031MC Title: Development of a landing mechanism for low-gravity body Objectives Development of a landing attenuation system for low-gravity body Description The primitive low-gravity bodies envisaged for MARCO POLO have very different surface properties from a comet therefore the heritage from Philae is not relevant (+the lander may not anchor on the surface). This activity shall therefore build upon the assessment study to infer the most appropriate design and start development and testing of a breadboard. Background: Need to take samples from a NEO. Different scenarios have to be investigated; one of them would be to land with legs on the body. Alternatives shall be studied and traded-off

Functional spec: damp the landing, avoid bouncing (or control it to allow sample collection), and allow sample collection on the surface (possible need to hold on the surface). Multiple landing shall be possible (reusable system). Very low gravity field. Lander mass 300 kg to 1t. Low velocities (30cm/s vertical and 5cm/s horizontal).

Technical specificities: gravity is a stabilizing component during landing which is not available here. Loads are very low due to low gravity and low velocities allowing mass optimization on the structure. Surface characteristics may be quite different from a Comet (heritage from Philae can not be directly applied).

Other related previous/future studies: X38 landing gear. Philae landing legs. MSR lightweight landing legs with Sener ongoing (end planned April 2008). Coming: Landing system development. 1ME. 2008-2010- Design and BB tests of a legged landing system for Moon/Mars. Mass 800kg-1.6t.

Activity proposed: Development of landing system allowing sample collection for very low gravity applications. - Investigate technical concepts to allow sample collection (landing, impacting, ...) - Analyse the impacts of very low gravity on stability and design trade-offs of the landing system (foot print, number of contact points, damping function integration, ...). - Propose technical solutions to hold the lander on the body (anchor, glue, Van der Wals forces as for Gecko climbing on the roof) to perform the sample collection, for a limited duration (e.g. <1h) while still allowing re-attempts. - Trade-off on the design for Marco Polo (impact points configuration, attenuation, folding/deployment if necessary, ...) - Design and analyses of a very lightweight landing system for Marco Polo application. Monte Carlo analyses of landing cases varying all parameters (terrain, velocities, ...) to check robustness. - Manufacturing of a Breadboard of the full lander and landing system. - Test of the Breadboard with gravity compensation. Current TRL: depends on the solution retained. Deliverables documentation, Breadboard model Application Current TRL: 2 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Marco Polo 24 Mission: Duration: Reference to S/W Clause: N/A T-8488 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 71 Programme: TRP Reference: T219-032MC Title: Development of Integrated landing impact attenuation structures for capsule Objectives Development of Integrated landing shock attenuation structures for return capsules. (e.g. based on hollow spheres) Description Background: Need to bring the samples back to Earth without parachute. Functional spec: damp the impact on Earth and preserve the samples. Velocity around 40m/s. Mass of the return capsule

Page 27 of 104

50-80 kg. Mass of the samples 10-100g (vs 500g for MSR).

Technical specificity: New type of shock of high intensity and medium duration. Typically half sine of 1000g for 5ms (phenomena around 100Hz) or 250g for 20ms (around 25 Hz), with large deformations (typically displacement of 0.1m). It corresponds to a crash type of impact. No need of biocontainment (HUGE simplification wrt MSR)= mass optimization.

Other related previous studies: MSR Aurora activities on Sample Container (MecanoID), Biocontainer (Verhaert), but without integration between them. Proposed activity in SD3 for integrated MSR integrity analysis of sample vessel/sample container/biocontainer, but without looking at the damping function (the landing load is taken as a spec).

Activity proposed: Study of the integrated damping system at Earth impact. - Trade-off on the level of damping: lower level, longer duration, higher displacements vs higher level, shorter duration, lower displacements, depending on the system susceptibility to the accelerations (electronic for a beacon or only structural strength). - trade-off on the integration of the damping function (material, honeycomb, foam, hollow spheres, accommodation in the design / directivity of the shock) - Tools and methodologies for the analyses. Identification of potential need of material characterization at high strain rate. - Design and analyses of a Marco Polo earth impact damping system. - Manufacturing and impact tests of a breadboard (several might be needed for several destructive tests).

Note, the sample container is not studied here, as it is a simplification of the MSR one (no RF/battery needed, no autonomous mechanisms for opening/closing/locking, no retroreflector for rendezvous, less stringent reqt on thermal control). The design should be studied, but is not as critical as MSR or the damping function.

Priority is HIGH. The priority indicated in the initial table has to be modified (discussed and agreed with D. Agnolon) from Medium to high as this is an enabling function for the mission. Deliverables documentation, Breadboard model Application Current TRL: 3 Target TRL: 5 TRL 5 by 2010 Need/Date: Application Contract Marco Polo 18 Mission: Duration: Reference to S/W Clause: N/A T-8542 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 95 Programme: TRP Reference: T215-030MM Development of a sample acquisition and transfer system for sample return mission to a low-gravity Title: body Ph. 1 Objectives Development of an end-to-end breadboard for a sample acquisition and transfer mechanism on a NEO (Near Earth Object) in micro-gravity Description Mission concept immature and methods for sample collection, transfer & containment are all poorly scoped and may need substantial development (in a number of activities). Target TRL: 5 by 2011. Shall be coordinated with ongoing GSTP activity. Will include design, breadboarding and testing in relevant environment (parabolic flight) Deliverables Technical Notes (incl. executive summary), Breadboard, test results Application Current TRL: 3 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8486 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 28 of 104

2-06 - M-Mission Candidate: Solar Orbiter

Item ID# : 312 Programme: CTP Reference: C205-101EC Title: Star tracker Objectives To verify the performance of the reused ST under the Solar Orbiter environment Description Description: The activity as defined in document reference SOL-F-ASTR-TN-0002 is considered as priority. There is no activity in the pipeline to which this one can be related. However, there is one activity on the definition of test methodologies for displacement damage that can provide useful feedback to this activity. The structure of the proposed work is as follows: .. Assessment of BepiColombo star tracker against the Solar Orbiter environment conditions .. Identification of critical technologies and the screening test levels to be applied .. Establishment of a test plan .. Execution of the test plan .. Evaluation of test results Deliverables Assessment report, test plan, test evaluation report Application Current TRL: 3 Target TRL: 5 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 300 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 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: 1) Combination of sputtering and e-beam evaporation 2) Ion beam assistance 3) Alternative materials. 3) Other possible approaches. For each proposed solution 10 samples shall be submitted to the cycling test. b) Refurbishment of current Window_2 and Wave Front Error re-measurement, New Window_2 to improve Wave Front Error c) Retardance & Fast Axis Angle Measurement d) Thermal Analysis for a Clear Aperture of Ø 160-170mm including consideration of the survival case (20s of direct sun exposure of a sector of the mounting ring) and a tilting of 15°. e) New Breadboard with Clear Aperture of Ø 160-170mm including: Design, Thermal Analysis, Structural Analysis, Hardware realization, Coating realization, Coating acceptance tests, Breadboard testing. 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

Page 29 of 104

Polarization Test Result Thermal Analysis Report Structural Analysis Report Application Current TRL: 3 Target TRL: 5 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 303 Programme: CTP Reference: C220-103MT Title: Heat shield Breadboard, manufacturing and testing Objectives To demonstrate the thermal performance of a portion of the heat shield under 20 SC Sun and equivalent IR illuminations Description Description: The Heat Shield thermal performances are predicted with significant uncertainty, coming from the intrinsic uncertainty of multilayer properties (as Front Shield and MLI on support panel), of contact conductance (as between the Heat Shield and Spacecraft) of the critical feed-through thermal paths. Therefore, only a thermal balance test allows measuring the Heat Shield performances, to assess the uncertainties and the correlation of mathematical models.

Solar simulation will be performed in a solar concentrator, for accurate reproduction of the orbital solar flux (spectrum and intensity), but within the constraints of the small size of available facilities, the duration of the test and the weather variability. Infra-red simulation will be performed in a standard vacuum chamber, for full-scale size, full control of parameters, and short duration, but at the cost of the representativity of the solar flux on the first layer of the Heat Shield, which must be simulated using infra- red heaters. The two sets of results will be correlated. The test item will be a portion of the Heat Shield around one representative feedthrough, including the support panel and front shield layers, with the selected materials, in order to reproduce with the two different thermal balance techniques the impacts of feedthrough heat flux on the Heat Shield thermal performances and to verify the thermal design of the feed- through and doors, as well as the materials characteristics, and sensitivity to small interface variations. Deliverables Thermal mathematical models, breadboard design report, test reports, test correlation reports, one heat shield breadboard Application Current TRL: 4 Target TRL: 5 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 308 Programme: CTP Reference: C203-104EP Title: High Solar Flux generator prototype manufacturing and validation testing Objectives To validate one solar generator configuration for Solar Orbiter mission through analyses and testing Description Based on the output of HIT Solar Generator Study and Cell Assemblies plus the results from the screening test campaign, the

Page 30 of 104

design of the solar generator prototype shall be performed. The prototype shall be subject to a test campaign to verify its performance under representative environment. Deliverables Design report and supporting analyses, Test/verification plan, Test report, Manufactured and tested Solar generator prototype Application Current TRL: 3 Target TRL: 6 2012 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 309 Programme: CTP Reference: C207-105EE Title: Antenna adaptation Study Objectives The activity objective is the evaluation of the BepiColombo antenna technologies under the environment and requirements of Solar Orbiter. The results of this activity will allow determining up to which distance and temperature Solar Orbiter can reuse the antenna technologies and identify eventual design changes or delta-qualification required. Description Description: Solar Orbiter mission is planning to reuse all of the antenna technologies that are being developed under the BepiColombo TDA. This includes the HGA, MGA and LGAs. However, due to the different environmental requirements (i.e. higher temperatures are foreseen for Solar Orbiter) and the fact that no Radio Science Experiment (RSE) is implemented for SO, the reuse of the antenna technologies has to be reassessed. It could be that due to the lack of the RSE certain antenna technologies are overqualified (e.g. Low-CTE waveguides), but this might be acceptable from a cost point of view. The first part of the activity shall be devoted to the determination of the minimum distance from the Sun up to which the BC antenna technology can be reused without performing any design changes or delta-qualifications. In the second part the original SO requirements shall be applied and the Contractor shall then identify the necessary design changes and/or delta- qualifications for meeting these requirements. It is expected that the maximum temperature for SO will be significantly higher than for BC mission. Therefore, the following analyses will have to be performed for all BepiColombo antennas (HGA/MGA and LGAs) under Solar Orbiter Environment for different antenna orientations and distances, including: .. Thermal analysis .. Thermo-elastic analysis taking into account o Materials/technology resilience to Solar Orbiter environment o Allowable deformation for communications (stringent shape requirements from Bepi RSE instrument are not applicable to Solar Orbiter) o RF analysis taking into account the maximum deformation of the antenna elements Deliverables Assessment report Application Current TRL: 4 Target TRL: 5 2010 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 310 Programme: CTP Reference: C207-106EE

Page 31 of 104

Title: Antenna Adaptation validation Objectives The objective of this follow-on activity is first to perform the identified delta-qualifications on the BepiColombo antennas (or technologies) and secondly to validate the proposed antenna design updates by Verification of the performed analysis through testing of representative antennas Evaluation of test results and correlation of RF/thermal analysis with measurement results Description In the precursor activity “Antenna adaptation study” all BC antennas (HGA, MGA and LGAs) have been subjected to the new Solar Orbiter environment requirements including the relaxed thermal stability requirements (no RSE). This has resulted in a number of antenna design updates and proposed delta-qualifications. It can be assumed that delta- qualifications are needed to account for the increased maximum temperature. To verify the compliance of the technology for this new mission, the electrical performances of the antennas shall be derived by breadboard testing in the relevant radiation and thermal environment. To reduce cost it is acceptable to define and test representative antennas instead of the real ones. This will then be followed by an analysis of the test results, providing explanations for the deviations of the test results from the results predicted and propose corrective actions wherever possible. The validation activity includes the following elements: Verification of above analysis through testing of representative antennas. Evaluation of test results and correlation of thermal analysis with measurement results Deliverables Test plan, test report, correlation report Application Current TRL: 5 Target TRL: 6 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 306 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 Description: The activity aims at reusing some existing elements in the ESTEC Test Centre, such as the alignment facility for LSS lamps and a quartz window of 1m diameter. The main idea is to install the quartz window at the end of the alignment beam tube and then fit a small thermal vacuum chamber with its related pumping equipment to the assembly. The Test Centre has already a concept for such an upgrade and they will issue an RFQ for the procurement of the missing elements and assembly of all parts. The activity will thus concentrate on the procurement, installation and validation of the upgraded facility. Deliverables Design report, upgrade plan, verification report Application Current TRL: N/A Target TRL: N/A 2010 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 301

Page 32 of 104

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 as per document reference SD-PL-AI-0221: Deliverables Test plans, test reports and used samples Application Current TRL: 2 Target TRL: 4 2010 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 304 Programme: TRP Reference: T204-109QE Methodology for High Solar flux testing acceleration. Explicitly address combined UV/thermal and Title: accelerated testing, and existing BC facilities. Objectives To upgrade the STAR facility up to Solar Orbiter environmental testing needs Description The STAR facility allows testing under simultaneous high temperature, UV and particles. The facility is being upgraded to meet the requirements of Bepi Colombo, but still needs further upgrading to meet those of Solar Orbiter. The activity will comprise the following tasks: 1) Identification of additional requirements to respond to the specific needs of Solar Orbiter; 2) Procurement and execution of the upgrades identified and 3) Verification of performance using reference samples Deliverables Assessment report, upgrade plan, verification report Application Current TRL: N/A Target TRL: N/A 2010 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 33 of 104

Item ID# : 305 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. Deliverables Assessment report Application Current TRL: N/A Target TRL: N/A 2010 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

T204-110TCItem ID# : 313 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 Application Current TRL: 2 Target TRL: 3 2010 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 34 of 104

Item ID# : 314 Programme: TRP/CTP Reference: T203-112EP Title: Solar Generator screening tests Objectives To minimise the Solar Generator development risk through a series of screening tests on local design solutions as proposed in HIT Solar Generator Study. Description Based on the output of HIT Solar Generator Study, prototypes shall be designed reflecting local design solutions. This will be followed by the manufacturing of the prototypes, the definition of the necessary screening tests and their execution. Altogether, the evaluation of these tests will provide a risk mitigation to the design and development of the solar generator of Solar Orbiter mission. Deliverables Prototypes Design report Screening Test plan Evaluation report Manufactured prototypes Application Current TRL: 3 Target TRL: 4 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 302 Programme: TRP/CTP Reference: T215-113MX Title: Feedthroughs, door, mechanisms Objectives To investigate the high temperature effect on the feedthorugh assembly (FT, door and mechanism), with special attention to the bearings and their lubrication, as well as the performance of any components used to tune the thermal balance of the design Description The activity includes the following elements as per document ref. SOL-S-ASTR-TN-0007 • Design of a breadboard of a feedthrough, door and its mechanism, starting from the design produced in the definition phase. • Procurement and manufacturing of the breadboard • Production of a test plan that includes the following: Resonance search, sine and random vibration Thermal balance Functional checks Performance test at high temperature Life testing • Evaluation of test results and correlation of thermal analysis with measurement results Deliverables Thermal mathematical models, breadboard design report, test reports, test correlation reports, one complete feedthrough assembly breadboard Application Current TRL: 4 Target TRL: 5 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 35 of 104

Item ID# : 307 Programme: TRP/CTP Reference: T203-114EP Title: High Intensity High Temperature Solar Cell Assemblies Objectives To design and test the final solar cell assemblies for the two alternative Solar Generator design concepts identified in Solar Generator Study activity Description Based on the output of Solar Generator Study, a detailed solar cell assemblies design shall be performed, addressing all the necessary processes and technologies, including laydown. This will be followed by the establishment of a development plan and its subsequent execution. The activity will conclude with the validation of the design through testing. Deliverables Design, development and verification plan, Design report, Test/verification plan, Test report, Manufactured and tested Solar Cell Assembly samples Application Current TRL: 4 Target TRL: 5 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : 311 Programme: TRP/CTP Reference: T201-115ED Title: SpaceWire based Solar Orbiter spacecraft simulator Objectives To mitigate the risk of the payload data bus by developing a payload simulator Description Description: The proposed activity aims at developing a spacecraft simulator based on a generic SpaceWire topology and capable of handling a high number of users (i.e. at least 10 instruments). The simulator topology shall be representative of the architecture proposed for Solar Orbiter, so it represents a first test case. The simulator shall be also electrically representative to allow interface testing not only at traffic level, but also at the physical layer of the protocol. Three activities have been identified in TEC-ED which have some relation with the herein proposed activity. - Development of a payload board with integrated computer (IPPM) and SpaceWire protocol (on FPGA) - Demonstrator for TEC-ED laboratory - SpaceWire traffic simulator: software only, Solar Orbiter case will be addressed as test case. Activity is to be kicked-off beginning of 2009. The TDA shall comprise the following tasks: - Identification of minimum set of elements to be contained in the simulator based on Solar Orbiter architecture - Design of a spacecraft simulator - Manufacturing - Testing and validation. Deliverables Design report, test plan, test evaluation report, spacecraft simulator Application Current TRL: 4 Target TRL: 5 2011 Need/Date: Application Contract Solar Orbiter Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 36 of 104

2-07 - M-Mission Candidate: Spica

Item ID# : 108 Programme: CTP Reference: C216-022MM Title: Light-weight mirror demonstrator breadboard Objectives 1) To demonstrate mastery of manufacturing, assembly and polishing of a large monolithic mirror assembled from segments using lightweight ceramic materials technologies. 2) To verify optical surface performance characteristics under warm and cryogenic conditions (5K) Description The SPICA mission is based on a large cryogenic telescope assembly (3.5m diameter primary mirror, inter-mirror distance ~ 3 m) operating at ~ 5 K. The telescope performance requirements include diffraction limited performance at 5 micron (at the operating temperature of 5 K), thus calling for a rather stringent WFE (< 350 nm in the central part of the accessible FoV). Given the size of the telescope, the mass constraints and the operating temperature, the use of light- weighted ceramic materials is envisaged for the mirror fabrication. The size of the primary mirror obliges the use of a segmented assembly approach (similar to Herschel) to enable efficient production of such a large optical surface. This approach has already been successful using SiC technology, but for much longer operational wavelengths. Alternative candidate technologies such as C/SiC or CeSiC have not yet been used in the production of optical surfaces this large. The short wavelength (5 micron) of SPICA demands a much improved surface preparation and polishing process, while specific mirror areas (e.g. in proximity of the telescope mountings) are likely to require particular analysis and investigation. In consideration of the stringent image quality requirements, it is envisaged that breadboarding of specific telescope elements and associated performance characterisation (at room as well as at nominal operating temperature) will be required, including issues related to surface polishing and material characterisation at low temperatures. Deliverables Breadboard parts or sub assemblies of a large 3.5 m mirror, manufactured and polished to flight standard requirements. Application Current TRL: 3/4 Target TRL: 6 TRL 6 in 2011 Need/Date: Application Contract Spica 12 Mission: Duration: Reference to S/W Clause: N/A T-8532 ESTER Consistency with Harmonisation Roadmap and conclusion: Harmonisation in progress (2. half 2008)

Item ID# : 114 Programme: CTP Reference: C216-023MM Title: SPICA STA: Telescope assembly verification and testing; demonstration of critical areas. Objectives 1) Analysis of test and verification requirements vs. availability of facilities, 2) Demonstration of critical test configurations, procedures and tooling under cryogenic conditions 5K < T < 70K, 3) Identification of long lead items (e.g. large cryogenic compatible optical flat), and preparation for early procurement. Description The SPICA mission is based on a large cryogenic telescope assembly (3.5m diameter primary mirror, inter-mirror distance ~ 3 m) operating at ~ 5 K. The telescope performance requirements include diffraction limited performance at 5 micron (at the operating temperature of 5K), thus calling for a rather stringent WFE (< 350 nm in the central part of the accessible FoV). Given the size of the telescope assembly, the operating temperature and the image quality requirements, AIV/T activities will pose unprecedented challenges, well beyond what done for the corresponding Herschel telescope. More specifically, the verification of performance on ground will require a joint ESA/JAXA effort, with an optimised test sequence and taking into consideration the availability of existing test facilities. Final optical verification will anyhow require accurate WFE measurements compatible with a cryogenic test facility and capable of characterising the telescope performance over a large size. Deliverables Test facility readiness Herschel class test Qualification and Application Test facility ready Current TRL: facility qualified Target TRL: verification to meet Need/Date: for use in 2011 and available (at SPICA

Page 37 of 104

CSL, B) requirements Application Contract Spica 12 Mission: Duration: Reference to S/W Clause: N/A T-8473 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 115 Programme: CTP Reference: C216-024MM Title: SPICA Telescope focusing mechanism for secondary mirror Objectives 1) To produce a qualifiable demonstrator of a focusing mechanism from available technologies 2) To verify its mechanical qualification warm and 3) To test and verify its performance under representative cryogenic conditions. Description The SPICA mission is based on a large cryogenic telescope assembly (3.5m diameter primary mirror, inter-mirror distance ~ 3 m) operating at ~ 5 K. The telescope performance requirements include diffraction limited performance at 5 micron (at the operating temperature of 5K), thus calling for a rather stringent WFE (< 350 nm in the central part of the accessible FoV). Given the stringent image quality requirements, the cryogenic operating temperature and the launch loads, the use of a focusing mechanism on the secondary mirror is required. Such a mechanism will be located on the M2 support structure, operate at 5K with minimum heat dissipation and enable refocusing as required to achieve the nominal telescope optical performance after launch and cool down. Given the tight development time (L=2017 - M class candidate), the focusing mechanism shall take advantage from existing design / technologies. The TDA aims to identify an optimised design meeting the requirements and to build a demonstrator, proving performance in a representative environment as required to achieve TRL=5. Deliverables Breadboard demonstrator Application Current TRL: 3/4 Target TRL: 5 TRL 6 for 2011 Need/Date: Application Contract Spica 12 Mission: Duration: Reference to S/W Clause: N/A T-8474 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 38 of 104

2-08 - M-Mission Candidate: Cross Scale

Item ID# : 159 Programme: CTP Reference: C205-025EC Title: Inertially referenced sensor for spinning spacecraft Objectives To develop a flexible star sensor for spinning spacecrafts. Description Current star trackers have the ability to support spinning spacecraft but with the limitation in maximum spin rate and with the sometimes critical limitation of requiring the spin axis and the detector columns to be rather well aligned. This restraint can be a killer if the resulting FoV swept by the STR encompasses the sun or if there are very high nutation rates. It is proposed to investigate a design for a more flexible star sensor for spinning spacecraft that maintains the accuracy and convenience of the current fully autonomous star trackers while eliminating the accommodation constraints. Deliverables HW BB Application Current TRL: 2 Target TRL: 4/5 TRL 4/5 by 2011 Need/Date: Application Contract Cross Scale 15 Mission: Duration: Reference to S/W Clause: N/A T-8544 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 39 of 104

2-09 - M-Mission Candidate: Plato

Item ID# : 11 Programme: CTP Reference: C216-026PA Title: Development of optimised high speed, high dynamic range CCD. Objectives Development of optimised large area CCD detector with low noise operation, large signal capability and high speed multi-node readout. Description The Plato concept appears to be consolidating towards a staring concept with a reduced number of large area CCD detectors. Detector development is required to take existing technologies and bring them together into a custom design that meets the mission requirements. This activity would build upon the prototype development to produce an optimised and characterised design. Deliverables Optimised CCD detector with high speed, low noise performance and multi-node readout capability. Application Current TRL: 4-5 Target TRL: 6 TRL 5/6 by 2012 Need/Date: Application Contract Plato 24 Mission: Duration: Reference to S/W Clause: N/A T-8472 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 89 Programme: CTP Reference: C216-028MM Title: Development of prototype high speed, 16bit CCD processor/ADC Objectives Prototype development of a 16bit 4 MHz ADC based processor and controller for the Plato CCD Readout Description The Plato CCD readout has been baselined as 4MHz in order to ensure bright stars do not saturate. The dynamic range requires 16 bit digitisation. Performance of similar systems have been demonstrated with 2MHz readout, and with highly integrated controller/driver . Such systems require further development for speed requirements and detailed study for the high accuracy photometric performance (differential and integral linearity of analogue electronics and ADCs). Deliverables Prototype CCD drive & control electronics, with processor and ADC integrated as board with FPGAs and other ASICs Application Current TRL: 4 Target TRL: 6 TRL5 by 2012 Need/Date: Application Contract Plato 18 Mission: Duration: Reference to S/W Clause: N/A T-8471 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 40 of 104

2-11 - Future Science Theme: Fundamental Physics

Item ID# : 223 Programme: TRP Reference: 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. Application Current TRL: 3 Target TRL: 5 TRL 4/5 by 2012 Need/Date: Application Contract FP 18 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 224 Programme: TRP Reference: T216-033MM 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. Application Current TRL: 3 Target TRL: 5 TRL 4/5 by 2012 Need/Date: Application Contract Fundamental Physics 18 Mission: Duration: Reference to S/W Clause: N/A T-8522 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 41 of 104

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

Item ID# : 50 Programme: TRP Reference: T207-034EE Modular Wide Field View RF Configurations (old title: Low-loss, low-mass, large lenses with anti- Title: 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 Application Current TRL: 2 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract Bpole 24 Mission: Duration: Reference to S/W Clause: N/A T-8495 ESTER Consistency with Harmonisation Roadmap and conclusion: Technologies for Passive mm and Submm Wave Instruments

Page 42 of 104

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

Item ID# : 33 Programme: TRP Reference: T223-038QM 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 Application Current TRL: 3 Target TRL: 6 TRL 6 in 2010 Need/Date: Application Contract Phoibos 18 Mission: Duration: Reference to S/W Clause: N/A T-8516 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 61 Programme: TRP Reference: T203-035EP 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 Application Current TRL: 1 Target TRL: 2 TRL4 by 2012 Need/Date: Application Contract Phoibos 6 Mission: Duration: Reference to S/W Clause: N/A T-8515 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 62 Programme: TRP Reference: T203-036EP 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

Page 43 of 104

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 assessed in detail (500k euros per technology, TRL 4 in 2012). Deliverables Breadboard prototype and development roadmap Application Current TRL: 2 Target TRL: 4 TRL4 by 2012 Need/Date: Application Contract Phoibos 24 Mission: Duration: Reference to S/W Clause: N/A T-8515 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 83 Programme: TRP Reference: T220-037MC Title: Development of a heatshield concept and material screening for near-Sun mission Objectives (NOTE: Requirements are still very unclear and feasibility of such mission is not demonstrated)

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 Application Current TRL: 1 Target TRL: 3-4 TRL5-6 by 2012 Need/Date: Application Contract Phoibos 18 Mission: Duration: Reference to S/W Clause: N/A T8513 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 44 of 104

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

Item ID# : 109 Programme: CTP Reference: C216-029MM Title: Long-stroke cryogenic optical delay lines 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 Application Current TRL: 2-3 Target TRL: 4-5 TRL5 after 2013 Need/Date: Application Contract Firi 24 Mission: Duration: Reference to S/W Clause: N/A T-8504 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 106 Programme: TRP Reference: T216-039MM 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

Page 45 of 104

TRL 5 for two alternative technologies (prime and backup) by 2011. Deliverables Test samples and study report including roadmap. Application Current TRL: 2 Target TRL: 3 TRL 5 in 2011 Need/Date: Application Contract Firi 24 Mission: Duration: Reference to S/W Clause: N/A T-8506 ESTER Consistency with Harmonisation Roadmap and conclusion: Harmonisation in progress (2. half 2008)

Item ID# : 109 Programme: TRP Reference: T216-040MM Title: Long-stroke cryogenic optical delay lines 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 Application Current TRL: 2-3 Target TRL: 4-5 TRL5 in 2015 Need/Date: Application Contract Firi 24 Mission: Duration: Reference to S/W Clause: N/A T-8504 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 46 of 104

2-15 - Technologies applicable to several Cosmic Vision Missions

Item ID# : 17 Programme: CTP Reference: C216-017PA 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. Deliverables Optimised and characterised control and digitisation ASIC for NIR/SWIR detector array. Application Current TRL: 4 Target TRL: 6 TRL 4/5 by 2012 Need/Date: Application Contract Euclid 24 Mission: Duration: Reference to S/W Clause: N/A T-8530 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 18 Programme: CTP Reference: C216-018PA 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 perfromance 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. Application Current TRL: 4 Target TRL: 6 TRL 4/5 by 2012 Need/Date: Application Contract Euclid 24 Mission: Duration: Reference to S/W Clause: N/A T-8529 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 67 Programme: CTP Reference: C206-005ET Title: Near Earth Space Research X/X/Ka-Band Transponder Engineering Model Objectives This activity is related to the development of an X/X/Ka Transponder EM for Near Earth Space Research missions which will use the 26 GHz frequency band allocation. Description The main technical issue for this transponder is the use of high data rates in Ka band for the telemetry down-link. At

Page 47 of 104

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 Ka-band will give the possibility to increase the scientific data return for this kind of Space Research mission in the future. NASA already have developments on-going for the Lunar Reconnaissance Orbiter and the James Webb Space Telescope (JWST) in the Ka frequency band. Deliverables An Engineering model of the X/X/Ka band TRSP and the End Item Data Pack Application Current TRL: 3 Target TRL: 6 TRL6 by 2010 Need/Date: Application Contract Generic 18 Mission: Duration: Reference to S/W Clause: Operational SW T-8489 ESTER Consistency with Harmonisation Roadmap and conclusion: Harmonisation dossier for TT&C transponder and payload data transmitters (22 January 2007) - Consistent - Activity B09: Near Earth X/X/Ka band Transponder for the 26GHz frequency band Engineering Model

Item ID# : 74 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 cooler require pre-cooling at 15K. For that purpose, a 10K Stirling cooler is currently under development, providing more than 200mW at 15K. As an alternative a Pulse Tube cooler starting from cold temperatures is currently under development, but still requires either passive pre-cooling or another active cooler. To overcome this complexity and to provide an alternative to the Stirling cooler under development, a multistage Pulse Tube cooler, starting from room temperature shall be designed, manufactured and tested. A suitable long-life linear compressor shall be developed. Deliverables Fully tested EM cooler, documentation Application Current TRL: 2 Target TRL: 6 TRL6 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-7876 ESTER Consistency with Harmonisation Roadmap and conclusion: Cryogenic and Focal Plane cooling (2007)

Item ID# : 85 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 verify 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

Page 48 of 104

Application Current TRL: 2 Target TRL: 4 TRL4 by 2013 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A N/A ESTER Consistency with Harmonisation Roadmap and conclusion: Cryogenic and Focal Plane cooling (2007)

Item ID# : 222 Programme: CTP Reference: oldN216-012MM Title: Development of rad-hard TDI CCD for Dark Energy mission Objectives Development of prototype large area CCD detector with low noise operation, suitable for operating in a TDI mode with high uniformity and fidelity in terms of MTF performance. Description Description: Discussions of a potential merger between US and European Dark Energy missions revolve around an ambitious visible wavelength focal plane imager to be developed from European contributions. Performance requirements include an unprecedented resistance to radiation damage that otherwise may prevent the maintenance of optical PSF, as a consequence of signal charge trapping and trailing. A second feature is the tailoring of detector MTF to ensure a smooth and well sampled optical PSF. This can be achieved if a high resistivity substrate is used for CCD fabrication and a control of undepleted detection volume achieved through voltage control. Initial demonstration fabrication of p-channel CCDs has been limited by poor quality silicon, but indicates a ~3 improvement in charge transfer performance. This activity envisages the design of prototype CCDs with representative Euclid pixel structures that can be later scaled to flight-sized CCDs on selected silicon wafers. Demonstration of performance before and after proton irradiation will be required. Deliverables Prototype CCD detector with 4-side buttable architecture, highly uniform response with TBC TDI structures to maximise radiation tolerance. Application Current TRL: 3-4 Target TRL: 4-5 TRL5 by 2012 Need/Date: Application Contract Euclid 18 Mission: Duration: Reference to S/W Clause: N/A T-8467 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 133 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 Test plans, Test reports including data analysis, final report, and tested samples Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration:

Page 49 of 104

Reference to S/W Clause: N/A T-7889 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 147 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 To determine accurately the CTE of stable materials at cryogenic temperature Deliverables samples, test results, materials data Application Current TRL: 1 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8391 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 156 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 fulfill this need but different concepts on hardening for radiation introduced errors have been proposed. The processor board to be developed shall be based on a High Rel DSP processor (e.g. from TI) which can be considered radiation hard with respect to total dose and SEL. Errors introduced by other SEE shall be detected and corrected by software in combination with the appropriate measures implemented on board level. Deliverables EM level computer board Application Current TRL: 2 Target TRL: 4 TRL 5 by 2010 Need/Date: Application Contract Generic 18 Mission: Duration: Reference to S/W Clause: N/A T-7751 ESTER Consistency with Harmonisation Roadmap and conclusion: 2nd Semester 2006 - On-Board Payload Data Processing - A1

Item ID# : 160 Programme: CTP Reference: C205-031EC Title: High Accuracy Star Tracker Objectives To develop a bespoke high accuracy star tracker for demanding missions which can not take advantage of a FGS in the instrument focal plane.

Page 50 of 104

Description High accuracy mission requiring a high accuracy inertially referenced sensor. Payload optics cannot be used due to need for sensing observations in visible. A very high accuracy STR is required. This should be very low power dissipation and mountable on the optical bench of the payload. Current 'baseline' estimates: - Separate OH and Electronics - < 0.5 Watt OH dissipation - 5 to 8 degree Full Cone FoV - 0.1 to 0.2 sec update rate - Autonomous quaternion out operation - < 1.5Kg OH and baffle - 40 deg SEA baffle - approx 0.1 arcsec performance - GSE development also required Deliverables HW E(Q)M Application Current TRL: 3 Target TRL: 6 TRL 5/6 by 2011 Need/Date: Application Contract Generic 21 Mission: Duration: Reference to S/W Clause: N/A T-7815 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 84 Programme: GSTP Reference: G220-006MC 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 Application Current TRL: 2 Target TRL: 4 TRL6 by 2014 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A ESTER Consistency with Harmonisation Roadmap and conclusion: Cryogenic and Focal Plane cooling (2007)

Item ID# : 161 Programme: GSTP Reference: G205-004EC Title: Precise Gravitational Modeling 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.

Page 51 of 104

The models will be threefold: • Models for mission analysis tools and techniques. These models are accurate and medium size computational intensive and will provide gravity field data for ESA and Industry astrodynamics tools. • Models for operations and ground control. These models are very accurate and high size computational intensive. They will provide gravity field data for spacecraft maneuvering capability. They will be typically installed in an operational ground segment control center. • Models for on-board autonomous orbit and attitude propagation. These models are relatively accurate and low size computational intensive. They will provide gravity field data for on-board autonomous spacecraft maneuvering capability. The expected main results are a thorough concept validation, and verification allowing increasing the TRL up to 6. Description The proposed activity will include as a minimum: (1) Detailed gravity fields functional, operational, performance, environment, etc. requirements use; (2) analysis and trade-off of various gravity field models for the 3 above mentioned concepts; (3) baseline definition and identification of models for the 3 areas identified above; (4) performance validation through simulations.

ESA will provide the novel gravity model of the GSP activity mentioned above. The Contactor is expected to provide the gravity models of all required bodies in the corresponding modes (tools, operations, and on-board). Full technical documentations will be delivered, covering specifications, architecture, algorithms, modeling, simulation test results and analysis results. All software developed during the activity will be delivered (source and binary codes). Deliverables SW/HW/Prototype Application Current TRL: 2 - 3 Target TRL: 5/6 TRL6 by 2011 Need/Date: Application Contract Generic 18 Mission: Duration: Reference to S/W Clause: Operational SW N/A ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 5 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 on 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 Application Current TRL: 1 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract Generic 15 Mission: Duration: Reference to S/W Clause: N/A T-8489, T-8490 ESTER

Page 52 of 104

Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 6 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 Application Current TRL: 1 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract Generic 15 Mission: Duration: Reference to S/W Clause: N/A T-8489,T8490 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 19 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. Application Current TRL: 3 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Generic 18 Mission: Duration: Reference to S/W Clause: N/A T-8530 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 53 of 104

Item ID# : 20 Programme: TRP Reference: T216-048PA 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. Application Current TRL: 3 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8529 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 35 Programme: TRP Reference: T223-054QM Development & testing of bonding and coating technologies of high temperature materials (C/C, Title: C/SIC, ablative materials etc. ) under extreme conditions Objectives To develop & improve bonding & coating technologies sustaining the hard environmental re-entry / flight conditions. Description Select and develop bonding & coating technologies for large and complex shapes, testing of representative materials configurations, downselecting of best candidates, manufacturing of breadboard and testing Deliverables Test results, samples, selection of materials, breadboard. Application Current TRL: 3 Target TRL: 6 TRL 6 in 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8516 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 79 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 today’s 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

Page 54 of 104

Fully tested EM cooler, documentation Application Current TRL: 2 Target TRL: 6 TRL6 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8527 ESTER Consistency with Harmonisation Roadmap and conclusion: Cryogenic and Focal Plane cooling (2007)

Item ID# : 92 Programme: TRP Reference: T216-049MM 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 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. Application Current TRL: 3 Target TRL: 5 TRL5 by 2013 Need/Date: Application Contract Generic 18 Mission: Duration: Reference to S/W Clause: N/A ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 123 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.

Page 55 of 104

Deliverables Design, technical notes (incl. executive summary), codes, material samples Application Current TRL: 2 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract Generic 18 Mission: Duration: Reference to S/W Clause: Open source T-8540 ESTER Consistency with Harmonisation Roadmap and conclusion: Yes

Item ID# : 125 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, developped and instrumented. Tests will be performed for various gas mixtures, to provide spectrally resolved emission and absorption spectra, as a minimum. More advanced techniques shall also be assessed, and demonstrated. The obtained results will be compared with documented results. Deliverables EM and Technical notes (incl. executive summary) Application Current TRL: 1 Target TRL: 4 TRL 5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8540 ESTER Consistency with Harmonisation Roadmap and conclusion: Yes

Item ID# : 145 Programme: TRP Reference: T223-055QM Materials Charging effects under extreme environments (ultra-low temperatures and high radiation Title: 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. Application Current TRL: 2 Target TRL: 4 to 5 TRL 5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration:

Page 56 of 104

Reference to S/W Clause: N/A T-7673 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 171 Programme: TRP Reference: T204-041EE 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 Application Current TRL: 3 Target TRL: 6 TRL5 by 2011 Need/Date: Application Contract Generic 18 Mission: Duration: Reference to S/W Clause: N/A T-7673 ESTER Consistency with Harmonisation Roadmap and conclusion: SEENoTC via SPINE

Item ID# : 175 Programme: TRP Reference: T204-042EE 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 modeling 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 Application Current TRL: s/w (pre-study) Target TRL: s/w (beta) TRL5 by 2011 Need/Date: Application Contract Generic 12 Mission: Duration: Reference to S/W Clause: N/A T-8396 ESTER Consistency with Harmonisation Roadmap and conclusion: SEENoTC via SPINE

Page 57 of 104

Item ID# : 181 Programme: TRP Reference: T204-043EE 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 Application Current TRL: 1 Target TRL: 3 TRL 5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8547 ESTER Consistency with Harmonisation Roadmap and conclusion: Harmonisation radiation monitoring; SEENoTC

Item ID# : 204 Programme: TRP Reference: T204-044PA 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. Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A T-8547 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 206 Programme: TRP Reference: T216-050PA 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;

Page 58 of 104

Report with test results. Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Generic 24 Mission: Duration: Reference to S/W Clause: N/A ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 146 Programme: TRP/CTP Reference: T216-001MM Title: Evaluation of commercial Digital Micro-mirror Device for multi-object spectrometers Objectives To conduct a radiation evaluation campaign for micro-mirror MOEMS, covering procurement, testing and evaluation, and analysis of future development requirements. Description 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 Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Generic 12 Mission: Duration: Reference to S/W Clause: N/A T-8470 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 59 of 104

Annex II – b : Detailed Description of National Technology Development Activities

Page 60 of 104

2-01 - L-Mission Candidate: Laplace

Item ID# : 48 Programme: National Reference: G207-002EE Title: Low mass wide-band spectrometer Objectives Several potential future science missions (e.g. EXOMARS, Venus entry probe reference mission, Jovian mission) have identified a (sub)mmw sounder as a candidate payload for orbital science. The current allocated payload resources for deep-space missions are very limited although the scientific case for submmw instruments has been demonstrated and consolidated both internally and externally. This is a follow-on activity of a GSTP activity entitled: "Wideband Spectrometer ". The objective of this activity is to implement the next phase already foreseen in the precursor activity. Description This activity is devoted to the design and practical implementation of wide-band spectrometer system. It will start with a detailed design taking into account the lessons learned in the precursor activity. The activity will be followed by breadboarding at of a full-scale breadboard. Special emphasis will be given to low mass and low power consumption. Deliverables Low Resource Spectrometer demonstrator Application Current TRL: 3 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Laplace 24 Mission: Duration: Reference to S/W Clause: N/A T-8482 ESTER Consistency with Harmonisation Roadmap and conclusion: Technologies for (sub) millimeter wave passive instruments - 2nd Semester 2006

Item ID# : 57 Programme: National Reference: N207-001EE Title: Electromagnetic tools for microwave subsurface sounding of planetary bodies Objectives To set-up / update EM tools enabling the assessment of the performance of subsurface radar sounding of planetary bodies Description Echo sounding is a complex technique that can contribute to the 3D knowledge of the inside of planetary bodies. However, most of the interaction models used to support this technique are either simplistic or highly dedicated to one kind of configuration / environment. This simulator could be used as a benchmark for testing retrieval algorithms, error mitigation techniques of for assessing the alleged performance of subsurface radar sounders. This activity aims at building up a tool that can simulate accurately the microwave echo returned from a penetrable medium, when observed at nadir. Based on a high-level system description, it should be possible to use this tool both for the simulation of the shapes of echoes for active sounders and for the computation of the undesirable effects of penetration depth on microwave altimetric data. This model development should be applicable to planetary bodies of interest for future missions (Europa / Titan) and should use their best available geophysical description as input parameters. Issues of interest shall include dense media, volume scattering, perturbing surface echoes, refraction, ambiguities (list not exhaustive). The availability of adequate modeling tools is critical if one wants to support the definition of requirements and/or to have some real visibility in the assessment of the would-be performance of a radar subsurface sounder. Indeed the geophysical variability of the propagating medium and issues in the microwave interaction can lead to orders of magnitudes in terms of variations of e.g. the strength of the scattered signal. Deliverables Modeling tool prototype Application Current TRL: 2 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract Laplace 18 Mission: Duration: Reference to S/W Clause: N/A ESTER

Page 61 of 104

Consistency with Harmonisation Roadmap and conclusion: N/A

Page 62 of 104

2-02 - L-Mission Candidate: IXO

Item ID# : 93 Programme: National Reference: N216-007MM Title: VIS Filter on X-ray Detector Surface Objectives Validate the optimum light shield to be deposited onto the low-energy X-ray detector Description While the deposition of metals onto a Si detector - Aluminium in particular - could be regarded as standard at detector manufacturers (be it as contact metal or as a light shield), the specific requirements of X-ray detection pose particular problems which are far from trivial. Unlike "standard" light shields, the required VIS filter must be transparent to X-rays especially at low Energies (at least as low as 100eV, preferably lower) and be free of any pin-holes. Activity ill include evaluation of realistic optical and UV light levels from the sky 2. More precise modeling of layer properties (AL, SiO2, Si3N4, LTO,...) 3. Deposition techniques: min. - max layer thickness, homogeneity, pin hole statistics, etc. 4. Fabrication of test samples, test of the samples and comparison with models 5. Quality assurance and control of the layers, test under extreme conditions. Finally testing and characterisation at BESSY synchrotron facility. This, combined with the state of development at MPE Garching as the DEPFET developer / supplier warrants a focused development. Deliverables Optimized VIS filter technology, ultimately delivered on the soft X-ray DEPFET detector breadboard for IXO (XEUS) to be integrated in activity XE-12. Application Current TRL: 3 Target TRL: 5 TRL 5 by 2011 Need/Date: Application Contract IXO (XEUS) 12 Mission: Duration: Reference to S/W Clause: N/A T-7965 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 94 Programme: National Reference: N216-008MM Title: X-POL ASIC readout for integrated gas cell Objectives To develop a proximity ASIC to be integrated in a gas cell and used to measure X-ray photon polarisation directly. To develop an associated algorithm to solve for photo-electron track direction (and hence photon polarisation) which may be implemented on-board (in form of ASIC or embedded S/W) Description During the course activity, the following tasks shall be performed: - Develop a new version of the XPOL readout ASIC. This will not be a totally new design, but an optimization of an existing component for higher throughput. Aim is to achieve 20 kHz event rate. This may be achieved by reducing the event window by a factor two and by an increase of the clock speed also by a factor of two - Develop on-board photo-electron track angle calculation. This will be achieved by implementing zero suppression on the FPGA controlling the ASIC read-out and by designing flight software to run on existing space qualified DSP processor. Deliverables Demonstration X-POL ASIC for integrated gas cell. Associated algorithms for evaluating photo-electron angle on board which may be implemented in ASIC or embedded S/W Application Current TRL: 3 Target TRL: 4 TRL 5 by 2012 Need/Date: Application Contract IXO (XEUS) 24 Mission: Duration: Reference to S/W Clause: N/A T-8466 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 63 of 104

Item ID# : HTRS-002 Programme: National Reference: N216-HTRS02 Title: Readout electronics for the IXO HTRS Objectives Design and prototype a digital shaper for silicon drift detectors Description The scope of this activity is to design and prototype a digital shaper (based on DSPs or FPGAs). The signal output from the charge amplifier is digitized with a fast ADC, and processed as to reconstruct the arrival time and the energy of each photon. The Deliverables prototype Application Current TRL: TRL3 Target TRL: TRL5 Need/Date: Application Contract IXO-HTRS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HTRS-003 Programme: National Reference: N216-HTRS03 Title: ASIC design for the IXO HTRS Objectives Design and prototype of an ASIC with multiple charge sensitive amplifiers and fast ADCs Description To make the HTRS design as compact as possible, it is plan to design an ASIC regrouping several charge sensitive amplifiers and several ADCs. The signal out of the ADCs could then be sent to the processor in charge of the digital shaping. Such activity w Deliverables prototype Application Current TRL: TRL2 Target TRL: TRL5 Need/Date: Application Contract IXO-HTRS 36 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HTRS-004 Programme: National Reference: N216-HTRS04 Title: Hybridization of CdTe and SDDs Objectives Design and prototype of compact detector made of a stack of an SDD array and CdTe based semiconductor detector Description If a high-energy extension is foreseen for the mirrors, then the SDD array will have to be complemented in a similar way as for the WFI, with a higher Z semiconductor detector located underneath. Among the potential high-energy semiconductor detectors, CdTe Deliverables prototype

Page 64 of 104

Application Current TRL: TRL2 Target TRL: TRL5 Need/Date: Application Contract IXO-HTRS 36 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XPOL-001 Programme: National Reference: oldN216-008MM Title: XPOL - GPD Objectives Design and prototyping of a higher counting rate GPD Description The purpose of the XPOL is to provide, in the energy range 2 – 10keV, polarization measurements simultaneously with spectral measurements ( E/dE of ~5 @6 keV) and timing information at few microseconds level. XPOL is based on a Gas Pixel Detector (GPD), a Deliverables Preliminary GPD Architectural Design; Report on GPD parameter configuration definition; GPD Requirement document; Test report on thermal test on best working temperature; Test report on Window safety margin; GPD Preliminary Technology readiness document; Application TRL5 by Q2 2012 Current TRL: 5 Target TRL: 6 Need/Date: TBC Application Contract IXO-XPOL 16 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XPOL-002 Programme: National Reference: N216-XPOL02 Title: XPOL - FW Objectives Design of a Filter Wheel and Calibration source Description The Filter Wheel other then closed position - for internal background monitoring - and open position, is provided also with a diaphragm for obscuring the side of the field and possible non interesting bright sources and with a beryllium filter to reduce Deliverables Preliminary Filter wheel Architectural Design.; Filter wheel Requirement Document.; FW Preliminary Technology readiness document; Application TRL5 by Q2 2012 Current TRL: 6/7 Target TRL: 6/7 Need/Date: TBC Application Contract IXO-XPOL 18 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 65 of 104

Item ID# : XPOL-003 Programme: National Reference: N216-XPOL03 Title: XPOL - BEE Objectives Design and prototyping of the Back End Electronics Description The Back End Electronics (BEE) is the FPA unit that contains the I/F Electronics (I/FE) boards and the HV Power Supply (HVPS) board. It interfaces both the GPD and the Control Electronics unit. These activities consist of designing and prototyping of a B Deliverables Preliminary BEE Architectural Design. BEE Requirement document. BEE Preliminary Technology readiness document BEE - Final Technology readiness document Application TRL5 by Q2 2012 Current TRL: 7 Target TRL: 7 Need/Date: TBC Application Contract IXO-XPOL 29 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XPOL-004 Programme: National Reference: N216-XPOL04 Title: XPOL - CE Objectives Design and prototyping of the Control Electronics Description The Control Electronics (CE) is a data processing unit which also controls the whole instrument. It interfaces both the instrument and the spacecraft, so it is the central node of XPOL. These activities consist of designing and prototyping of a CE Deliverables Preliminary CE Architectural Design. CE Requirement document. CE Preliminary Technology readiness document CE - Final Technology readiness document Application TRL5 by Q2 2012 Current TRL: 7 Target TRL: 7 Need/Date: TBC Application Contract IXO-XPOL 29 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XPOL-005 Programme: National Reference: N208-XPOL05 Title: XPOL - Test/Calibration Objectives Test and Calibration of the GPD and Calibration source prototypes

Page 66 of 104

Description These activities consist of testing and calibration of the GPD prototypes and the Calibration source prototypes. List of the activities: Calibration source test; Radiation hardness test of ASIC; Survival capability test of GEM; GPD Vibration/shock/Acoustic Deliverables Test Report on radiation hardness on ASIC; Test Report on survival capability of GEM; Test report on Vibration/shock/Acoustic test; Test report on thermal and thermal vacuum cycle; Test report on calibration and performance test; Final Technology readiness Application Current TRL: Target TRL: Need/Date: Application Contract IXO-XPOL 11 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : N216-002PA Programme: National Reference: oldN216-002PA Title: Optimization of the TES-based micro-calorimeter array for IXO/XMS Objectives Improve pixel geometry to obtain 2.5 eV for E < 6 keV. Optimize process control for the production of the large central array Description Optimization of TES-pixels in small arrays by investigation of alternative absorber-TES coupling schemes, and TES current distributions. Optimize process control and solve wiring density issues through production of large arrays (32 x 32) Deliverables Detector breadboard comprising a 32x32 TES array with representative pixels with an energy resolution of 2.5 eV Application Current TRL: 4 Target TRL: 5 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : N216-003PA Programme: National Reference: oldN216-003PA Title: Optimization of Frequency-Domain-Multiplexed read-out electronics for Micro-calorimeter arrays Objectives Further optimization of ultra-low noise SQUID-based read-out electronics using Frequency-Domain-Multiplexing Description Continue development of SQUID multiplexed readout for large (32x32) TES microcalorimeter array. This includes: - Optimization of the digital AC-carrier generation and feedback loop algorithms (performance vs power); - Further development of cryogenic LC-f Deliverables FDM read-out breadboard enabling the multiplexed readout of 2 x 32 pixels (incl. 2 x 32 LC-filter chip, 2 SQUIDs, 2

Page 67 of 104

LNA's, AC-bias/Feedback board) Application Current TRL: 3 Target TRL: 5 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-004 Programme: National Reference: N216-XMS04 Title: Development of electrical interconnections for the (cold) detector components Objectives Demonstration of feasible interconnections between the different micro-machined components in the XMS cold head (2D or 3D) Description For an efficient packing of the detector components of the XMS instrument, interconnections between these components (e.g. Detector array, LC-filters, SQUID) is important. As part of this activity the interconnections will be demonstrated. Also feasibility Deliverables Interconnections at the appropriate scale (size/pitch) for the XMS detector head Application Current TRL: 2 Target TRL: 5 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-011 Programme: National Reference: oldN220-011MC Title: Closed cycle dilution cooler Objectives The objective is to develop a closed cycle dilution cooler based on the Planck 100mK cooler. First phase (2008-2009) aims at proving the concept + fully characterising the system Description A novel concept might enable a closed cycle dilution cooler which could enable the use of a Planck dilution cooler system for long life missions as e.g. IXO. Within the first phase of the activity, a proof of concept of the closed cycle shall be shown. A Deliverables Proof of concept validation. Characterisation of the main parameters of the system. Associated documentation 4 in 2009 Application Current TRL: 3 Target TRL: (potentially 6) by TRL6 by 2013 Need/Date: 2011 Application Contract IXO SPICA 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 68 of 104

Item ID# : XMS-016 Programme: National Reference: N220-XMS16 Title: optimize full cooling chain Objectives to provide optimized cooling chain based on European components Description A large variety of cooling chains is feasible. These are currently studied in Japan, the US and Europe. In Europe different cooling chains architectures will be studied as part of the industrial mission studies under contract of ESA. This activity will pr Deliverables thermal/mechanical model for European cooling chain Application Current TRL: Target TRL: 4 Need/Date: Application Contract 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : N216-049PA Programme: National Reference: oldN216-049PA Title: Cryogenic anti-coincidence sensor development Objectives Study and development of a Cryogenic Anticoincidence detector for the TES NFI of IXO. This is requested in order to reject the particle background in the TES detector. The anticoincidence detector will be mounted closely behind the micro-calorimeter a Description Two options are studied: 1) A thermal detector with a Si absorber with TES sensor and SQUID read out. 2) Si pin with JFET readout, as already flown on SUZAKU XRS.

Option 1, which is the Baseline, offers the advantage of being based on the same sensor Deliverables Trade-off study documents, the detector prototype and results from performance tests. Application Current TRL: 3 Target TRL: 5 TRL 5/6 by 2011 Need/Date: Application Contract IXO-XMS 36 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-005 Programme: National Reference: N216-XMS05 Title: design of compact filterwheel for XMS Objectives provide realistic baseline for IXO filterwheel Description The objectives are two-fold: trade-off between filter wheel with 12 slots and filter wheel with 8 slots in which two filters can rotate; trade-off between integrated door/filterwheel combination and separate door and filterwheel Deliverables

Page 69 of 104

design drawings Application Current TRL: 5 Target TRL: 6 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-006 Programme: National Reference: N216-XMS06 Title: develop polarization sensitive filters Objectives lower the energy range for which polarization sensitive (dichroic) filters are available to below 6 keV and prove their long term stability Description Dicrhoic polarization sensitive filters have been developed and their performance is close to the expected predictions. So far the energy range has been 9 keV and above. The purpose of the activity is to lower the energy range to 1.6 to 4.6 keV (narrow b Deliverables Dichroic filters with an energy response below 6 keV and appropriate test reports Application Current TRL: 3 Target TRL: 5 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-007 Programme: National Reference: N216-XMS07 Title: demonstrate performance of beam diverter Objectives Demonstrate the capability to produce multi channel optics with the correct radius Description Micro channel plate optics is a well established technology (e.g. BeppiColombbo). The purpose of this activity is to provide a demonstrator for the required optics to divert the beam for a focal length of 20 m. No energy calibration or special coatings to Deliverables micro channel plate beam diverter and test report Application Current TRL: 5 Target TRL: 6 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 70 of 104

Item ID# : XGS-001 Programme: National Reference: N216-XGS01 Title: p-channel CCDs Objectives

Description

Deliverables CCDs for rad testing Application Current TRL: 3 Target TRL: 5 Need/Date: Application Contract IXO, Euclid, Plato 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XGS-002 Programme: National Reference: N216-XGS02 Title: EM CCDs for soft X-ray spectroscopy Objectives

Description

Deliverables CCDs for testing at synchrotron Application Current TRL: 4 Target TRL: 5 Need/Date: Application Contract IXO 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XGS-003 Programme: National Reference: N216-XGS03 Title: Light blocking filters Objectives

Description

Deliverables CCDs for optical testing Application Current TRL: 4 Target TRL: 5 Need/Date: Application Contract IXO 12 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 71 of 104

Item ID# : XGS-004 Programme: National Reference: N216-XGS04 Title: X-ray Sensitive CMOS Imagers - Phase 1 Objectives

Description

Deliverables CMOS Test structures for evaluation Application Current TRL: 3 Target TRL: 4 Need/Date: Application Contract IXO, Planetary rovers/orbiters 12 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XGS-005 Programme: National Reference: N216-XGS05 Title: X-ray Sensitive CMOS Imagers - Phase 2 Objectives

Description

Deliverables CMOS Prototype Imagers Application Current TRL: 4 Target TRL: 5 Need/Date: Application Contract IXO, Planetary rovers/orbiters 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-001 Programme: National Reference: N216-XMS01 Title: SQUID development for cryogenic sensor readout Objectives Further development and optimization of low noise SQUID-current sensors operable at <100mK Description Continue development of SQUID current sensors for multiplexed readout of large format (32x32) TES microcalorimeter array. This development will implement design proposals obtained in previous activities (ESA TRP 5417) Deliverables SQUID-current sensors with power dissipation <10nW for multiplexed readout of 32x32 TES microcalorimeter array. Two new design options will be pursued, the 1st design aiming at a minimum input referred current noise of <2.5pA/rtHz, and the 2nd design simple Current TRL: 3 Target TRL: 5 Application

Page 72 of 104

Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HTRS-001 Programme: National/GSTP Reference: N216-HTRS01 Title: Readout electronics for the IXO HTRS Objectives Design and prototype of one complete analog electronic chain for a single Silicon Drift Detector Description The HTRS will be exposed to very high fluxes so that to minimize the deadtime per event a very fast shaping amplifier must be used, with time constants as short as 50 ns. The scope of this activity is to develop a complete analog readout chain to run a Si Deliverables prototype Application Current TRL: TRL4 Target TRL: TRL5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-HTRS 12 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HTRS-005 Programme: National/GSTP Reference: oldN216-009MM Title: Onboard Processing IXO HTRS Objectives Design and prototype of a module for Onboard data processing of HTRS Description The complexity of the data output of HTRS, mainly dictated by its high rate, requires a careful implementation of the onboard data processing module. We plan the development and testing of such a module with main emphasis on the science aspects of the data Deliverables Prototype Application Current TRL: TRL4 Target TRL: TRL6 TRL6by2012 Need/Date: Application Contract IXO-HTRS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HTRS-006 Programme: National/GSTP Reference: N216-HTRS06 Title: Performance Studies for IXO HTRS & WFI

Page 73 of 104

Objectives Numerical simulations to study the performance of the IXO HTRS and WFI for bright sources. Determination of pile-up limits, input into pixel design, count-rate estimates and compression algorithms. Description Because of the large HTRS countrates, pile up can be an issue. The purpose of the study is to make available a full end to end simulation for scientific and technical studies to be used in the design of the instrument. Deliverables software prototype Application Current TRL: N/A Target TRL: N/A TRL5 by 2011 TBC Need/Date: Application Contract IXO-HTRS 10 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HTRS-007 Programme: National/GSTP Reference: N216-HTRS07 Title: Design of a compact filter wheel for the HTRS Objectives Compact filter wheel design Description Study of the mechanical design of a compact filter wheel, building upon existing technologies under development for ASTRO-H Deliverables Engineering design Application Current TRL: TRL6 Target TRL: TRL9 TRL5 by 2011 TBC Need/Date: Application Contract IXO-HTRS 6 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : WFI-001 Programme: National/GSTP Reference: N216-WFI01 Title: DEPFET Active Pixel Array Development Objectives Development of a DEPFET-based Active Pixel Sensor Array for the IXO WFI Description The sensor array for the IXO WFI is based on a 1024 x 1024 pixel matrix of 100 x 100 µm2 sized DEPFET pixels. The sensor will be implemented as a monolithical array on a 6-inch wafer, but will be logically divided into two hemispheres, each read out independently. Each hemisphere will be logically subdivided into 8 sectors of 128 rows x 512 x columns size that are going to be read out by one analog front-end ASIC each. The AFE ASICs perform read-out, amplification, shaping and serialization of the detector signal. Selection of detector pixels for read-out is performed by the control front- end ASICs through correct row-wise application of the relevant voltages. Currently two paths of AFE options exists: CAMEX, an AFE ASIC with very long heritage (XMM, SOHO, ABRIXAS, eROSITA) and consequently high TRL, and VELA / ASTEROID, a new AFE ASIC family development with improved speed and intrinsic radiation hardness. Technical issues are increase in physical and logical size of the detector, and improvement of detector performance (energy resolution and speed). Current status: Laboratory breadboard prototypes of small size are routinely being operated spectroscopically with very good energy resolution. Detector breadboards equipped with VELA / ASTEROID have been operated with very high speed and

Page 74 of 104

excellent energy resolution. Prototype devices of logical WFI sector dimensions (128 columns x 512 rows) have been produced, but not yet operated. Increased area device prototypes (~10 % WFI area) have been produced and characterized. Tasks to be performed in this activity: - Operation and characterization of WFI sector prototypes - Replacement of CAMEX by VELA / ASTEROID as standard DEPFET AFE - Radiation damage study - Production of full scale mechanical samples - Production of large area prototype devices (>50 % WFI area, production underway, availability scheduled for mid 2010) - Yield determination Deliverables Fully integrated and operated WFI sector prototypes Documentation characterizing WFI sector devices Documentation of radiation damage study Documentation of yield determination Large area prototype sensor Full scale mechanical sample Application Current TRL: 4 Target TRL: 6 TRL5 by 2011 TBC Need/Date: Application Contract IXO-WFI 24 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : WFI-003 Programme: National/GSTP Reference: N220-WFI03 Title: Thermal Concept Development Objectives Development of a thermal concept of the IXO WFI & HXI assembly Description The IXO WFI and HXI instruments share one position on the MIP, with the HXI observing hard X-rays transmitted through the WFI detector. The WFI's FPA is operated at a temperature of 210 K, while the HXI, situated only a few centimeters behind the WFI, is Deliverables Mechanical model of WFI camera head Thermal model of WFI camera head Components of mechanical model Application Current TRL: 3 Target TRL: 5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-WFI 24 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : WFI-004 Programme: National/GSTP Reference: oldN216-007MM Title: UV/Optical blocking filter / entrance window Objectives Development of a UV/optical blocking filter for the WFI detector. Description Optical or UV photons absorbed in the WFI detector can lead to an energy shift. While the energy shift is correctable if the optical flux is known, the resulting degradation of energy resolution is not. An internal study has shown that for the

Page 75 of 104

parameters Deliverables Coating Process Documentation Pin-hole free coating prototypes Characterization of coatings Application Current TRL: 4 Target TRL: 6 TRL5 by 2011 TBC Need/Date: Application Contract IXO-WFI 24 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : WFI-005 Programme: National/GSTP Reference: N216-WFI05 Title: Filter Sled Development Objectives Development of a filter sled for the IXO WFI Description The IXO WFI will need four filter positions: OPEN, CLOSED, CALIBRATE and FILTER. The CALIBRATE position will hold calibration sources for the WFI (55Fe) and HXI (241Am). The FILTER position will hold an optical filter that will reduce optical photon flux Deliverables Technical specifications for filter sled Industry study documentation Application Current TRL: 3 Target TRL: 5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-WFI 24 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : WFI-006 Programme: National/GSTP Reference: N216-WFI06 Title: DAQ electronics Objectives Development of DAQ electronics for the IXO WFI DEPFET array Description The DAQ electronics of the DEPFET array needs to perform a large number of steps after digitization, most of which will be performed by several FPGAs or ASICs. Currently these steps are performed in software running on PC hardware. Parts of the pending de Deliverables IXO WFI ADC cluster breadboard Report on FPGA prototype algorithm study Application Current TRL: 4 Target TRL: 5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-WFI 24 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 76 of 104

Item ID# : WFI-008 Programme: National/GSTP Reference: N224-WFI08 Title: Quality Assurance Objectives Development, study and implementation of IXO WFI QA concept Description To prevent critical parameter changes at a later stage, a QA concept has to be developed at an early stage. Besides general QA, this concept will also cover areas like radiation monitors on the FPA and contamination compliance of all detector components. Deliverables Documentation of QA concept Application Current TRL: 4 Target TRL: 5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-WFI 24 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HXI-001 Programme: National/GSTP Reference: N216-HXI01 Title: Anticoincidence system for IXO/HXI and background studies Objectives The objective of this development is to build a breadboard of the HXI anticoincidence system, based upon technological activities and intensive background simulations.. Description The scientific performances of the IXO mission will necessitate a very low detector background level. This will imply thorough background simulations, and efficient background rejection systems. It necessitates also a very good knowledge of the detectors Deliverables breadboard, simulations reports Application Current TRL: TRL2 Target TRL: TRL5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-HXI 36 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HXI-002 Programme: National/GSTP Reference: N216-HXI02 Title: WFI/HXI, HXI detector front end electronics Part I Objectives The objective of this development is to build a analogue front end ASIC chip test for HXI using a Low power, low noise and radiation hard deep submicronic technology. Description Technology Development Activity part I

Page 77 of 104

The scientific performances of the IXO/HXI Hard X-Ray imaging spectrometer of the WFI/HSI instrument on board IXO mission will necessitate high density pixel detectors with high spectral resolution and high time tag Deliverables breadboard, simulations and test reports Application Current TRL: TRL2/3 Target TRL: TRL4 TRL5 by 2011 TBC Need/Date: Application Contract IXO-HXI 18 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HXI-003 Programme: National/GSTP Reference: N216-HXI03 Title: WFI/HXI, HXI detector front end electronics Part II Objectives The objective of this development is to build a specialized AFE ASIC chip test adapted to the HXI requirements according to choice with respect to strip or pixel detectors (at CdTe level) and strip detector (at Si detector level) for HXI front end electr Description Technology Development Activity part II

According to the optimal definition of the HXI in cooperation with WFI teams and HXI Japanese Leader Team (Takahashi et al.) and once the ASIC technology is identified at CEA, evaluated and approved by the project, Deliverables breadboard, simulations reports Application Current TRL: TRL4 Target TRL: TRL5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-HXI 18 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : HXI-004 Programme: National/GSTP Reference: N216-HXI04 Title: WFI/HXI, HXI detector front end electronics Part III Objectives The objective of this development is to build a Integrated ADC ASIC chip test. Description Technology Development Activity part III

One innovative challenge for the IXO/HXI era is to develop a fully integrated detector including ADC. This ADC has to be studied in details in terms of architecture, performance. This TDA intends to trigger the de Deliverables breadboard, simulations reports Application Current TRL: TRL2/3 Target TRL: TRL4 TRL5 by 2011 TBC Need/Date: Application Contract IXO-HXI 24 months Mission: Duration: Reference to S/W Clause: ESTER

Page 78 of 104

Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-003 Programme: National/GSTP Reference: N216-XMS03 Title: Qualification activities on detector arrays Objectives Qualification of 5 x 5 pixel detector arrays for thermal cycling, vibration, radiation, and storage Description Exposure of small (5 x 5 pixel) baseline detector arrays to thermal cycling, vibration, radiation interleaved with cold DC characterization, and X-ray measurements Deliverables Qualification reports and qualified 5 x 5 pixel arrays Application Current TRL: 3 Target TRL: 5 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : N216-004PA Programme: National/GSTP Reference: oldN216-004PA Title: Qualification activities on read-out electronics Objectives Qualification of components for FDM readout Description Pre-qualification effort on SQUID-based current amplifiers, LC-filters, and the interconnections between them and the TES-array. Deliverables Qualification reports and Qualified components Application Current TRL: 3 Target TRL: 5 Need/Date: Application Contract IXO-XMS 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : N216-006MM Programme: National/GSTP Reference: oldN216-006MM Title: MIS Based Micro-Calorimeter Array of 16x16 pixels. Objectives The objective of this development is to build 16x16 X-ray micro-calorimeter arrays multiplexed and 2 sides abutting based on space proven MIS technologies. Description Inheriting from PACS/Hershel on Si based bolometer large arrays, and improving on Suzaku/XRS2 design, we are developing large arrays of micro calorimeters. We already succeeded in developing a first 8x8 sensors array that was hybridized with a Tantalum ab

Page 79 of 104

Deliverables A) complete Detector array (with Absorber hybridised onto the sensors) B) Report on measurements on these prototypes Application TRL4 by mid 2010 Current TRL: TRL2/3 Target TRL: TRL4 Need/Date: TBC Application Contract IXO-XMS 18 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-008 Programme: National/GSTP Reference: N216-XMS08 Title: Large (32x32 pixels) MIS Based Micro-Calorimeter Array for IXO/XMS Objectives The objective of this development is to capitalize on the16x16 realization to build a complete 32x32 X-ray micro- calorimeter arrays multiplexed and 2 sides abutting based on space proven MIS technologies. Description After the success of the 8x8 batch and optimizing from our 16x16 realization, we will optimize our design and produce 32x32 matrices with their associated cold readout electronics. This 32x32 2 sides abutting multiplexed matrix is necessary to fulfill th Deliverables A) complete 32x32 Detector array (with Absorber hybridised onto the sensors) B) Report on measurements on these prototypes Application Current TRL: TRL2 Target TRL: TRL5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-XMS 18 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Item ID# : XMS-009 Programme: National/GSTP Reference: N216-XMS09 Title: First Acquisition chain for the MIS Based Micro-Calorimeter Array Objectives The objective of this development is to build a complete cold readout electronic chain including a 32:1 multiplexer and an online fast logic to control the data acquisition. Description In the framework of our MIS based micro-calorimeter development, we will realize a complete cold readout chain. This chain will first adapt the impedance using HEMTs (High Electron Mobility Transistors with GaAs/GaAlAs junction), then it will amplify and Deliverables A) complete readout electronic chain B) Report on measurements on this chain Application TRL4 by mid 2010 Current TRL: TRL2/3 Target TRL: TRL4 Need/Date: TBC Application Contract IXO-XMS 18 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 80 of 104

Item ID# : XMS-010 Programme: National/GSTP Reference: N216-XMS10 Title: Optimized Acquisition chain for the 32x32 pixels MIS Based Micro-Calorimeter Array Objectives Inheriting form our previous Acquisition chain design, the objective of this development is to build a, optimized cold readout electronic chain including a 32:1 multiplexer and an online fast logic to control the data acquisition for the large ( up to 32x Description In the framework of our MIS based micro-calorimeter development, after the first iteration of the readout electronic chain done, we will realize a complete cold readout chain for the large (32x32) MIS microcalorimeter array. Iterations on HEMTs and SiGe A Deliverables A) complete readout electronic chain B) Report on measurements on this chain Application Current TRL: TRL2 Target TRL: TRL5 TRL5 by 2011 TBC Need/Date: Application Contract IXO-XMS 18 months Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 81 of 104

2-04 - M-Mission Candidate: Euclid

Item ID# : 90 Programme: National Reference: N216-012MM Title: Development of rad-hard TDI CCD for EDEM. Objectives Development of prototype large area CCD detector with low noise operation, suitable for operating in a TDI mode with high uniformity and fidelity in terms of MTF performance. Description The Dark Energy mission requires a visible imaging detector with very high requirements on image response uniformity. Pending more detailed mission studies the operation may be in a scanning or a step-and-stare mode. Whether the choice if specifically for a TDI optimised format or normal imaging, a number of large area CCD detectors are required with very high packing density. Detector development is required to take existing technologies and bring them together into a custom design that meets the mission requirements. This activity would build upon the prototype development to produce an optimised and characterised design. Deliverables Prototype CCD detector with 4-side buttable architecture, highly uniform response with TBC TDI structures to maximise radiation tolerance. Application Current TRL: 3-4 Target TRL: 4-5 TRL5 by 2012 Need/Date: Application Contract Euclid 18 Mission: Duration: Reference to S/W Clause: N/A T-8467 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 82 of 104

2-05 - M-Mission Candidate: Marco Polo

Item ID# : 26 Programme: National Reference: N216-014PA Title: Cameras Objectives breadboard or critical component development Description A fast design iteration shall provide confidence on this camera suite to fit into the Marco Polo resource budgets and possible environmental constraints (e.g. close-up imager during sampling) Deliverables Design iteration possible breadboarding of critical parts (especially close-up imager). Application Current TRL: 4 Target TRL: 5-6 TRL5 by 2011 Need/Date: Application Contract Marco Polo 24 Mission: Duration: Reference to S/W Clause: N/A T-8487 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 27 Programme: National Reference: N216-015PA Title: Laser Altimeter Objectives breadboard or critical components development of a laser altimeter Description The currently best developed laser altimeter in Europe, the BeLa instrument on BepColombo does not satisfy the requirements of Marco Polo. The instrumented is operated much closer to the surface (< 2 km) and will be also used during the approach to the surface of the asteroid. The power consumption of the BeLa laser the surface is too demanding (50W), especially during autonomous operations while approaching the surface. The specific requirements will be defined by the mission baseline. As a minimum the development of a new laser source is required. Most of the of the system parameters and components could be adopted. New instrument concepts like "LAPE" should be investigated and traded against mission requirements and programmatics. Deliverables Breadboard or critical components set-up representing a TRL of >5, standard documentation and test. Application Current TRL: 2 Target TRL: 5-6 TRL5 by 2011 Need/Date: Application Contract Marco Polo 24 Mission: Duration: Reference to S/W Clause: N/A T-8487 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 28 Programme: National Reference: N216-016PA Title: Mid IR Fourier mapping spectrometer Objectives breadboard or critical component development Description

Page 83 of 104

The proposed instrument concept does not require any moving mirrors or prisms due to the use of beam-shearing prisms. Despite the development activity in the UK an instrument design for Marco Polo is not existing thus has to be developed and breadboarded from scratch. This activity will demonstrate the feasibility and compliance of a mapping spectro with the scientific, volume, mass and environmental specifications. A representative breadboard of a flight instrument will be designed and manufactured. The breadboard will undergo testing in operational environmental conditions in order to demonstrate that the required scientific performances are met. Deliverables Breadboard or critical components set-up representing a TRL of >5, standard documentation and test. Application Current TRL: 3-4 (?) Target TRL: 5-6 TRL5 by 2011 Need/Date: Application Contract Marco Polo 24 Mission: Duration: Reference to S/W Clause: N/A T-8487 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 29 Programme: National Reference: N204-013PA Title: Neutral Particle Analyser Objectives breadboard or critical components development Description The instrument consists of two channels covering the energy range from smaller a few eV to 10 to 1000 eV. The efficiency of ion deflection in the respective environment has to be demonstrated. The ionising efficiency of the nanotube system and grating system (with slits of nanometric dimensions) has to be demonstrated. The MCP may be critical tbc. The overall system performance has to be demonstrated. Future development should take full advantage of existing experience form the sub-unit (ELENA) on BepiC. Deliverables tested Breadboard or critical components set-up representing a TRL of >5 Application Current TRL: 3 Target TRL: 5-6 TRL5 by 2011 Need/Date: Application Contract Marco Polo 24 Mission: Duration: Reference to S/W Clause: N/A T-8487 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 30 Programme: National Reference: N216-017PA Title: Visible Near IR imaging spectrometer Objectives breadboard or critical component development Description The currently proposed instrument is an extremely light-weight version of an imaging spectrometer covering the range of 0.4 to 3.3 um. The spectral resolution λ/Δλ should be larger than 100. The anticipated weight is 1 kg only which is challenging, therefore a substantial development effort is required. The whole instrument requires an end to end design and development plan, breadboarding and testing phase. The instrument will work at distances below 10 km (down to 100 m) from the asteroid. A targeted ground resolution of 1-2 m shall be achieved at a distance of 2 km (TBC). Heritage: Rosetta/ Bepi Colombo/ Hayabusa Deliverables Breadboard or critical components set-up representing a TRL of >5, standard documentation and test. Application Current TRL: 2 Target TRL: 5-6 TRL5 by 2011 Need/Date:

Page 84 of 104

Application Contract Marco Polo 24 Mission: Duration: Reference to S/W Clause: N/A T-8487 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 85 of 104

2-07 - M-Mission Candidate: Spica

Item ID# : 10 Programme: National Reference: N215-019PA Title: Cryogenic mechanisms development Objectives Breadboarding and pre-qualification of cryogenic mechanisms for the SPICA-SAFARI instrument required by the overall optical setup. The objective is to achieve TRL=5, demonstrating that the breadboard setup will work in a relevant space environment, and that the mechanism can work at low temperature (<5 K) and the power dissipation of this mechanism to a low level compatible with the associated cryogenic cooling budget. Description The SAFARI instrument proposed for the SPICA mission contains cryogenic mechanisms playing a critical role in the overall system performance. One of the main mechanisms is a mirror scanning mechanism. The main function of this mechanism is to scan the optical path to achieve the stated 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 should be minimised, it should not disturb the functional temperature. The positioning of the mirrors should be very accurate (µm range). This means that optical parts shall be positioned within that range and the mechanism shall also move in the same accuracy range. Cool down from ambient should not influence the setup. The above mentioned constraint and requirements also apply to other mechanisms, such as filter wheel and beam steering mechanism. The design of these units should be based on existing/ proven technology or on modest development programmes, in view of achieving TRL=5 by the end of 2009. Existing technology can be conventional mechanical roller bearings in combination with a cryogenic steppermotor. If the speed is low the power dissipation can be minimised. An alternative is magnetic bearings. An advantage is that there is no physical contact between the mechanical parts. Due to this fact the power dissipation is minimal. No physical contact can also mean no temperature transfer. In continuously rotating mechanisms this can be a problem. Deliverables BB Application Current TRL: 2 Target TRL: 5 TRL5 by 2011 Need/Date: Application Contract Spica 20 Mission: Duration: Reference to S/W Clause: N/A T-8478 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 14 Programme: National Reference: N216-020PA Title: Safari: Detector development Objectives Develop ultra low noise TES single pixel and large format array for FIR detection. Description Develop NEP = 100 zeptoW/sqr(Hz) TES single and large array detectors using low thermal conductance SiN leg MEMS technology. Deliverables Detector breadboard component comprising cryogenic (~ 100 mK) single pixel and, subsequently, scalable array of TES MEMS detectors with NEP ~100 zeptoW/sqr(Hz) Application Current TRL: 3 Target TRL: 5 TRL5 by 2012 Need/Date: Application Contract Spica 36 Mission: Duration: Reference to S/W Clause: N/A T-8475 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 86 of 104

Item ID# : 15 Programme: National Reference: N216-021PA Title: Safari: Focal plane read-out Objectives Develop cryogenic readout electronics for the zepto-detectors Description Develop ultra-low noise cryogenic multiplexing readout electronics capitalizing on IXO (XEUS) NFI development. The readout will be possible FDM-based. Deliverables Detector breadboard component comprising cryogenic scalable mutliplexing readout for array of TES MEMS zepto- detectors. Application Current TRL: 3 Target TRL: 5 TRL5 by 2012 Need/Date: Application Contract Spica 24 Mission: Duration: Reference to S/W Clause: N/A T-8476 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 42 Programme: National Reference: N207-018EE Title: Safari: Integrated antenna/detector development Objectives One of the challenges to achieving improved detector sensitivity with bolometric detectors is the extremely low levels of electromagnetic power expected on SPICA (on the order of 1E-16 W). Superconducting thermal detectors, such as TES bolometers, Kinetic Inductance Detectors and Cold Electron Bolometers have the potential to offer improved sensitivity in large format micromachined integrated antenna arrays. The objective of this study is to ensure the availability of integrated antennas that have near perfect matching with the bolometer detectors over a wide bandwidth. Description This activity comprises of trade-off, design, analysis, manufacture, and test of integrated antennas.

It shall investigate Design Alternatives and Establishing the Baseline Design, assess different fabrication technologies for these integrated antennas and different experimental verification techniques. After this, the electrical performances of the integrated antennas shall be derived by testing. This will be followed by an analysis of the test results, providing explanations for the deviations of the test results from the results predicted and correct them wherever possible. Finally a roadmap to bring the technology to flight level will be provided. Deliverables integrated antenna plus bolometer array Application Current TRL: 2 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract Spica 18 Mission: Duration: Reference to S/W Clause: N/A T-8475 ESTER Consistency with Harmonisation Roadmap and conclusion: Technologies for (sub) millimeter wave passive instruments - 2nd Semester 2006

Item ID# : 76 Programme: National Reference: N220-026MC Title: 50mK EM Cooler

Page 87 of 104

Objectives to bring the 50mK BB to flight standard Description 50mK coolers are currently under development and will have further follow-up activities in the frame work of the IXO (XEUS) project. Similar effort should be undertaken with the specific needs for B-POL. This activity should cover the design, fabrication and testing of an EM equivalent model. Deliverables fully tested EQM, documentation Application Current TRL: 2 Target TRL: 4 TRL4 by 2010 Need/Date: Application Contract Spica 12 Mission: Duration: Reference to S/W Clause: N/A T-7969 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 77 Programme: National Reference: N220-027MC Title: 50mK pre-cooler simulator Objectives The objective is to verify the I/F between 50mK cooler and 2-4K Joule Thompson cooler Description The 50mK cooler currently under development still requires to recycle a He3 sorption cooler at a constant time interval. During this times, a higher than average heatload needs to be evacuated by the pre-cooler. On the contrary, JT coolers currently baselined as pre-cooler, can only operate in a small temperature range. In order to verify the correct transient behaviour of the system JT cooler-50mK cooler, a I/F demonstrator simulating a Joule Thompson cooler shall be developed and used to pre-cool the 50mK cooler. Based on the test results, the operation of the 50mK cooler shall be optimised to minimise the impact on the JT cooler and to establish the correct I/F requirements (including margins) for the JT coolers. Deliverables Joule Thompson I/F simulator, validated I/F requirements between 50mK cooler and JT pre-cooler Application Current TRL: 2 Target TRL: 4 TRL4 by 2010 Need/Date: Application Contract Spica 12 Mission: Duration: Reference to S/W Clause: N/A T-7969 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 86 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 submillinetre and FIR detector (arrays) Description Characterization of submillimetre and FIR detectors and arrays is currently approached on an ad hoc basis and never has an optical measurement of ~ zept0W/sqr(Hz) been achieved. In view of the many technology development activities being planned for SPICE, FIRI and B-Pol it is imperative that a European centre be setup to perform the characterisation of cryogenic submillimetre and FIR detection systems without effort and funding duplication. Such a facility should operate for at least 5 years and purchase or gather the required equipment. This includes: cryostats, submillimetre/FIR sources and filters, magnetic shields and room temperature readout electronics. Deliverables

Page 88 of 104

An ESA lab for ultra-low noise submillimetre/FIR detection characterization. Application Current TRL: 2-3 Target TRL: 5 TRL5 by 2012 Need/Date: Application Contract Spica 60 Mission: Duration: Reference to S/W Clause: N/A N/A ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 87 Programme: National Reference: N216-023MM Title: BIB detectors and cold readout for SPICA Objectives Develop 2D array Si:As BIB detectors in the 5 - 20 micromn range Description The MIR Camera and Spectrometer on SPICA will require detectors with assumed MIRI (JWST) performance. In the 5 - 20 micron range, one could use the Si:As BIB (blocked impurity band) detectors currently developed for Darwin. This technology is being developed in Europe (IMEC) and could be an alternative to US competitor for SPICA. Further technology development is required to reproduce US state-of -the-art result and insure future European independence. One dimensional arrays are being characterized as we speak using readout based on PACS. Two dimensional array need to be demonstrated and dedicated cold readout electronics developed. Deliverables 2D array S:As BIB detector array and cold readout electronics Hybrid chip Application Current TRL: 4 Target TRL: 5 TRL5 by 2012 Need/Date: Application Contract Spica 24 Mission: Duration: Reference to S/W Clause: N/A T-8475 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 113 Programme: National Reference: N216-024MM Title: SPICA European Science Instrument Fourier transform spectrometer breadboard Objectives 1) To secure the optical and optomechanical technology readiness level for the Mach-Zehnder Fourier Transform Spectrometer sub-system of this instrument 2) To demonstrate, test and verify optical performance of the FTS vs requirements Description The Mach-Zehnder Fourier Transform Spectrometer sub-system of the proposed European Science Instrument (ESI) for SPICA has been identified as a risk element in the programme with respect to its TRL. Further effort is therefore required to improve this TRL so as to mitigate the risk towards overall development of the ESI. The two main areas of concern are a) extending the qualified performance range of the optical elements to shorter wavelengths <= 5 microns under cryogenic conditions and b) ensuring a reliable and qualified performance of the optical path length scanning mechanism. Deliverables Breadboard components tested and qualified in a representative cryogenic environment. Application Current TRL: 3/4 Target TRL: 5 TRL 6 by 2011 Need/Date: Application Contract Spica 16 Mission: Duration: Reference to S/W Clause: N/A T-8479 ESTER Consistency with Harmonisation Roadmap and conclusion:

Page 89 of 104

N/A

Item ID# : 201 Programme: National Reference: N216-025PA Title: Cryogenic Fourier Transform Spectrometer Bread Board Objectives The cryogenic FTS BB shall demonstrate the imaging and spectroscopic performance capabilities required for SAFARI Description Building on Herschel/SPIRE and Akari heritage, a proof-of-concept demonstrator for the SAFARI imaging FTS must successfully verify the performance specified for SAFARI; moreover, it should allow experimental verification of performance predictions of different operational modes and allow the definition of calibration strategies and onboard data processing. Deliverables Cryo BB including mechanism control, detector readout and data postprocessing (FT) Application Current TRL: 3 Target TRL: 5 TRL6 by 2011 Need/Date: Application Contract Spica 24 Mission: Duration: Reference to S/W Clause: N/A T-8475 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 90 of 104

2-08 - M-Mission Candidate: Cross Scale

Item ID# : 182 Programme: National Reference: N204-028EE Title: Combined ion/electron electrostatic analyser study Objectives Develop instrument to measure in low electron flux environments through increasing geometry factor and defection efficiency. Description Study of insertation of deflector plates in existing plasma instruments to enhance geometric factor to measure in low electron flux environments (tailbox). Design should be lightweight and low power. US instrument on THEMIS, but European development needed. Deliverables simulated design, tested prototype Application Current TRL: 1 Target TRL: 3 TRL 5 by 2011 Need/Date: Application Contract Cross Scale 24 Mission: Duration: Reference to S/W Clause: N/A T-8492 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 91 of 104

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

Item ID# : 32 Programme: National Reference: N223-033QM Title: Development of balloon materials for VENUS environment Objectives To develop and preliminary evaluate balloon material for EVE Description Select candidates for high temperature acid resistant materials combinations, testing in representative conditions, upscale possibilities Deliverables Test results, samples, selection of materials, breadboard. Application Current TRL: 3 Target TRL: 6 TRL 6 in 2011 Need/Date: Application Contract Eve 24 Mission: Duration: Reference to S/W Clause: N/A T-8507 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 72 Programme: National Reference: N219-031MC Title: Inflation system for balloon Objectives To develop an inflation system for a balloon in Venus atmosphere. Description Balloon inflation system based on tank or chemical system or cold gas generators.

Description: The exploration of the Venus surface and atmosphere will take great advantage of a balloon. Concepts for such balloons have been described, for example using Phase Change Fluid, ensuring an oscillating travel through the Venus atmosphere. The inflation system for such a balloon needs to be developed, as it will encompass features specific to the Phase Change Fluid and the Venus environment. The activity shall consolidate the requirements for the inflation system. A trade-off between available concepts (fluid storage, chemical system or gas generators) shall be performed. A preliminary design of the inflation system shall be performed. On the base of this preliminary design and identified critical aspects, a breadboard shall be designed, manufactured and tested. A development plan for this inflation system shall conclude the study.

Output: requirements, trade-off, design documentation, breadboard (test results and hardware) Deliverables requirements, trade-off, design documentation, breadboard (test results and hardware) Application Current TRL: 2 Target TRL: 4 TRL 4 by 2011 Need/Date: Application Contract Eve 24 Mission: Duration: Reference to S/W Clause: N/A T-8509 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 73 Programme: National Reference: N219-032MC

Page 92 of 104

Title: Reliable low-mass balloon deployment system for Venus probe. Objectives To develop a deployment system for a balloon in Venus atmosphere. Description Balloons could provide important platforms for the exploration of Venus surface and atmosphere. However, such balloons need to be deployed in a reliable manner, without penalising the mass of the descent module. This activity shall provide the preliminary design of a deployment system for a Venus balloon. The requirements for such a deployment system shall be defined. In order to consolidate these requirements, breadboard testing shall be performed to identify balloon folding concepts, compaction levels, deployment velocity, etc. Based on consolidated requirements, a preliminary design for the balloon deployment system shall be performed. The study shall be completed with a breadboard testing of the balloon deployment with simulated operational conditions. Deliverables Requirements, conceptual breadboards, preliminary design and validation by breadboard. Application Current TRL: 2 Target TRL: 4 TRL 4 by 2011 Need/Date: Application Contract Eve 24 Mission: Duration: Reference to S/W Clause: N/A T-8512 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 146 Programme: National Reference: N223-034QM Title: 3D printing of antenna on balloon or parachute material part Objectives Address the compatibility of the balloon material with the printing inks and the subsequent finishing techniques. Scale-up and validation of the printing techniques of material antenna on balloon and parachute material. Description 1) Define the best direct printing techniques. 2) Validate the choices at sample level in in-service conditions 3) Enlarge sample size and address the reliability of the 3D printing technique selected Deliverables samples, test results, materials data Application Current TRL: 3 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract Eve 24 Mission: Duration: Reference to S/W Clause: N/A T-8507 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 183 Programme: National Reference: N214-029MM Title: Nephelometer Objectives The objective of this activity is to achieve a fully functional breadboard of a miniaturised nephelometer for the measurement of the backscattering and the total scattering in the Venus atmosphere. Description To develop a nephelometer working at Venus environmental conditions with high accuracy is quite a challenge. Ideally the nephelometer should give turbidity, back- and total scattering values for several (?) wavelength. Depending on the actual optical properties of the gases/vapours to be measured the required optical pathlength may be difficult to achieve. Furthermore depending on the parameters to be measured also a preprocessing of the gas (as drying, removal of acid droplets etc has to be performed).

Page 93 of 104

Deliverables Breadboard Application Current TRL: 3 Target TRL: 5 TRL 4/5 by 2012 Need/Date: Application Contract Eve 18 Mission: Duration: Reference to S/W Clause: N/A T-8511 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 184 Programme: National Reference: N214-030MM Title: MEMS based Gas Chromatography/Mass Spectrometer Objectives The objective of this activity is to achieve a fully functional breadboard of a miniaturised Gas Chromatograph and Mass Spectrometer system for in-situ chemical analysis in harsh environment (Venus) based on MEMS technology and to be tested in a relevant environment. Description Gas chromatographs in conjunction with a spectral mass analyser for the identification of organic and inorganic compounds have been flown or are flying already on several space missions, e.g. Huygens and Rosetta, and are in the process of being built and qualified, as for the Mars Science Lab (NASA) and for ExoMars (ExoMars). These instruments are already miniaturised and optimised in terms of mass and power consumption to a high extent. MEMS based technology however offers a potential to further reduce resource consumption and cost. This would enable for instance environmental monitoring using a swarm type of mission. As for applications in human spaceflight, the potential of MEMS based devices is the increased mobility. Deliverables Breadboard Application Current TRL: 2 Target TRL: 4 TRL 4/5 by 2012 Need/Date: Application Contract Eve 18 Mission: Duration: Reference to S/W Clause: N/A T-8511 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 94 of 104

2-11 - Future Science Theme: Fundamental Physics

Item ID# : 7 Programme: National Reference: N216-035PA Title: Breadboarding of accelerometer based on Atomic Interferometry Objectives Develop a laser-cooled Mach-Zender atom interferometer for space Description System design of future breadboard of an atom accelerometer. Identification and design specifications of key components: Cooling/trapping/manipulation laser system/vibration stabilisation. Phase 1 : specification of key components characteristics. Phase 2 : assembly of EBB. Breadboarding of accelerometer based on Atomic Interferometry: breadboarding could be based on portable Bose- Einstein Condensate (BEC) setup developed for ongoing drop tower experiments. Ultimate accelerometer requirements depend on pointing and position stability of the atom source. These issues are currently being investigated in TRP activity and will be available soon. Activity should focus on pushing results obtained so far (which are limited by either gravity or drop tower time), further miniaturisation, and initiate space worthiness tests. This activity shall take advantage from results of potential previous studies on this topic performed by ESA and/or on national level. Deliverables Breadboard a portable laser-cooled Mach-Zender atom interferometer for space. Application Current TRL: 3 Target TRL: 5 TRL 4/5 by 2012 Need/Date: Application Contract Fundamental Physics 36 Mission: Duration: Reference to S/W Clause: N/A T-8519 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 190 Programme: National Reference: N216-036MM Title: Critical Optical frequency comb/synthesiser sub-system technologies Objectives Develop critical optical frequency comb/synthesiser sub-system technologies for space optical clocks Description The primary objective of developing a frequency comb/synthesiser for space is to support the implementation of an optical atomic clock in space. The availability of a clockwork capable of counting the very high frequency (100's THz) from an optical clock as opposed to a microwave clock (9GHz) is a key enabling technology that has led to the development of optical clocks on ground. To develop a space optical clock requires a space compatible frequency comb. This technology is already available as compact elegant breadboard. The present activity shall address all the criticalities of the comb technology for space applications and progress towards an EM of a space-compatible optical frequency comb to be tested in a relevant environment (vibrations, thermal, radiation, etc.). Deliverables a frequency comb forming a self-contained element Application Current TRL: 3 Target TRL: 5 TRL 4/5 by 2012 Need/Date: Application Contract Fundamental Physics 18 Mission: Duration: Reference to S/W Clause: N/A T-8525, T-8522 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 95 of 104

Item ID# : 193 Programme: National Reference: N216-037MM Title: Laser cooling trapping systems Objectives Cooling and trapping systems (traps and lasers) to realise both single ion and neutral atom (lattice) optical clocks need to be developed with a view to meet performance, reliability and dependability. Description Study new cooling and trapping systems for single ion and neutral atom clocks (preferably based on e.g. Sr, Yb, Sr+, Yb+). Proceed with most promising ion/neutral atom to in-depth study. This activity shall take advantage from results of potential previous studies on this topic performed by ESA and/or on national level. Deliverables breadboard Application Current TRL: 2 Target TRL: 4 TRL 4/5 by 2012 Need/Date: Application Contract Fundamental Physics 18 Mission: Duration: Reference to S/W Clause: N/A T-8524 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 194 Programme: National Reference: N216-038MM Title: Ultra-narrow frequency stable laser technology for probing optical clock local oscillator transitions Objectives The objective of the activity is to provide coherent sources at a desired wavelength/s corresponding to clock transition/s of interest with a linewidth of < 1 Hz (or considerably less in a pre-determined time frame). Description Provide coherent sources at a desired wavelength/s (tbd) corresponding to clock transition/s of interest with a line width of < 1 Hz (or considerably less in a pre-determined time frame). This activity shall address all critical areas connected to space qualification and progress towards an EM of a space-compatible system (laser locked on high finesse cavity) to be tested in a relevant environment (vibrations, thermal, radiation, etc.). This activity shall take advantage from potential previous studies within ESA and also studies at national level. Deliverables breadboard demonstrator Elegant Bread Board (EBB) Application Current TRL: 2 Target TRL: 4 TRL 4/5 by 2012 Need/Date: Application Contract Fundamental Physics 18 Mission: Duration: Reference to S/W Clause: N/A T-8523 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 195 Programme: National Reference: N216-039MM Title: Stimulated Raman transition inducing diode laser Objectives Solid state laser, possessing high short term frequency stability, high beam quality for large beam area and narrow line width for inducing Stimulated Raman transitions. Additionally long lifetime for operations (7 yrs), high power output, high power conversion efficiency. Description The main aim of this activity should be the demonstration of the beam splitting function by performance evaluation of ultra stable lasers with ultra stable and precise phase control. The combination of wavelength, line-width, frequency

Page 96 of 104

stability and phase with an excellent wave-front quality are aspects to be targeted in this activity. (The realisation of a Cold Atom demonstrator requires the parallel development of compact and reliable lasers for cooling (BEC) and packet splitting and re-combining (interferometer).) This activity shall take advantage from results of potential previous studies on this topic performed by ESA and/or on national level. Deliverables Breadboard hardware with verification in "drop tower" environments. Application Current TRL: 3 Target TRL: 5 TRL 4/5 by 2012 Need/Date: Application Contract Fundamental Physics 18 Mission: Duration: Reference to S/W Clause: N/A T-8521 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 226 Programme: National Reference: Title: Breadboard of an ion optical clock Objectives Design a breadboard of an ion optical clock Description Phase 1: System design of future breadboard of ion optical clock. Identification and design specifications of key components: ion trap and laser system - frequency stable laser for interrogation - frequency synthesis and frequency chain - microwave frequency dissemination and comparison system. Phase 2: Breadboarding of a miniature space ion clock, assembly of key components. Deliverables Phase 1 : Technical note with breadboard design and sub-components specifications (mass, size, power, interface). Phase 2 :EBB Application Current TRL: 2 Target TRL: 4/5 2015 Need/Date: Application Contract FP 24 Mission: Duration: Reference to S/W Clause: ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 97 of 104

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

Item ID# : 9 Programme: National Reference: N215-043PA Title: Cryogenic Half-wave plate rotation mechanism Objectives Breadboarding and pre-qualification of a cryogenic half-wave plate rotation mechanism for the B-Pol instrument required by the overall optical setup. The objective is to achieve TRL=4, demonstrating that the breadboard setup will work in a laboratory environment, and that the mechanism can work at low temperature (<4 K) and the power dissipation of this mechanism to a low level compatible with the associated cryogenic cooling budget. Description The Cryogenic Halve-wave plate rotation mechanism proposed for the B-Pol mission is playing a critical role in the overall system performance. This mechanism shall continuously rotate a heavy filter disc (sapphire) which is placed in front of the instruments vocal plain detector. The disc will be placed close to the vocal plane detector and the working temperature of this detector is below 1 K. Therefore it is necessary to cool the filter to 4 K or even lower then 4 K. Therefore the power dissipation of the mechanism should be at a low level compatible with the cryogenic cooling budget. The rotation speed is up to 20Hz. The generated micro vibrations should be minimised. The natural frequency of the mechanism should be taken into account. When the natural frequency is below the 20Hz problems during startup may occur. The mechanism has to run through it natural frequency during this startup. It is most likely that this mechanism can not be build out of conventional technology. For instance a conventional mechanical bearing in combination with a cryogenic motor will not meet, in all terms, the power dissipation requirement associated to the cryogenic cooling budget. Active magnetic bearing is an alternative. No contact between the moving parts will minimise the power dissipation. But alternatives should be found to bring the filter at the 4 K temperature level. During continuously rotation the magnetic bearing side effects, hysteretic and Eddy current losses, will introduce additional power dissipation. This is particularly problematic, since the contact-less type of suspension would not allow the dissipation of any heat produced on the rotating part, except by radiation (almost negligible in that environment). A mechanism based on High Temperature Superconducting Bearings (HTS BM) could be a valid starting point for this mechanism. This type of mechanism was used in former experiment, but only on a smaller scale. Extrapolation of this mechanism could be a trade off for the B-Pol mechanism. Important to know is that most of these mechanisms are at a laboratory level and never used for space applications. A potential problem could be the magnetic flux density, which will require a special design or magnetic shielding. Deliverables BB Application Current TRL: 2 Target TRL: 4 TRL5 by 2011 Need/Date: Application Contract B-pol 24 Mission: Duration: Reference to S/W Clause: N/A T-8496 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 23 Programme: National Reference: N216-044PA Title: Sub-millimetre -wave TES development Objectives Develop polarising antennas/quasi-optics for submillimiter TES detector array. Description Different TES and antenna coupling approaches exist. For instance micro-strip coupled TES can be combined with corrugated horns to provide a high optical efficiency with low cross-polarisation. Deliverables Design of submillimetre coupling scheme for TES arrays (up to 200 pixels) in the frequency range 70 - 350 GHz and realize technology demonstration breadboard. Application Current TRL: 2-3 Target TRL: 5 TRL 4 by 2011 Need/Date: Application B-pol Contract 24

Page 98 of 104

Mission: Duration: Reference to S/W Clause: N/A T-8493 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 24 Programme: National Reference: N216-045PA Title: TDM SQUID read-out for sub-mm applications Objectives Develop readout for submillimetre TES-base detector array. Description Possibly this activity can benefit from similar developments on FDM/TDM SQUID (time/frequency domein multiplex) read-out. Also SiGe ASICS might be considered for multiplexer control. Deliverables Detector breadboard component comprising cryogenic readout/multiplexing electronics for submillimeter TES array (200 pixels). Application Current TRL: 4 Target TRL: 5 TRL 4 by 2011 Need/Date: Application Contract B-pol Mission: Duration: Reference to S/W Clause: N/A T-8494 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 47 Programme: National Reference: N207-040EE Title: Large radii Half-wave Plate (HWP) development Objectives To ensure availability of Half-wave plates of sufficient dimension to fulfill the requirements. Description This activity will be targeted to the following main areas: • Study and design of Half Wave Plate (HWP) architectures. • Address critical technological areas identifying potential solutions. • Perform critical breadboard development The activity will start with a careful assessment on the requirements. This activity will identify and select the mechanical, thermal and technological solutions and HWP architectures required to achieve the necessary accuracy and stability for a future B-pol mission. These solutions/architectures will have to be demonstrated by critical breadboarding (as a minimum at electro and thermo-mechanical representative sample level). A technology roadmap to bring the technology to flight level shall be provided. Deliverables HWP breadboard at sample level Application Current TRL: 2 Target TRL: 3 TRL5 by 2012 Need/Date: Application Contract B-pol 18 Mission: Duration: Reference to S/W Clause: N/A T-8595 ESTER Consistency with Harmonisation Roadmap and conclusion: Technologies for (sub) millimeter wave passive instruments - 2nd Semester 2006

Item ID# : 52

Page 99 of 104

Programme: National Reference: N207-041EE Title: Novel focal plane array architecture development Objectives To study novel architectures for focal plane arrays with large number of detectors without sacrificing image quality. Description To achieve the radiometric sensitivity requirements when imaging large scenes, a large focal plane array filled with detectors is needed operating at many different frequencies. To limit the image quality degradation the array size cannot be to large and it might be useful to investigate novel frequency separation architectures by either using multi-frequency elements or multi-layer structures. Deliverables Critical breadboard of Focal plane imaging detector array Application Current TRL: 1 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract B-pol 24 Mission: Duration: Reference to S/W Clause: N/A N/A ESTER Consistency with Harmonisation Roadmap and conclusion: Technologies for Passive mm and Submm Wave Instruments

Item ID# : 56 Programme: National Reference: N207-042EE Title: Sub-millimetre-wave Integrated lens/TES detector development Objectives To study the various antenna-coupled TES detector designs, either by a feed horn or integarted lens, and investigate the optimum type of feeding (e.g. microstrip) for such detectors. Description Different TES and antenna coupling approaches exist. For instance micro-strip coupled TES can be combined with corrugated horns to provide a high optical efficiency with low cross-polarisation. Deliverables Detailed antenna-coupled TES detector design and Elegant Breadboard Application Current TRL: 2 Target TRL: 3 TRL5 by 2011 Need/Date: Application Contract B-pol 24 Mission: Duration: Reference to S/W Clause: N/A T-8493 ESTER Consistency with Harmonisation Roadmap and conclusion: Technologies for Passive mm and Submm Wave Instruments

Page 100 of 104

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

Item ID# : 105 Programme: National Reference: N216-046MM Title: Far IR passive optical components Objectives To design, develop and test passive optical components for an imaging interferometer at FIR wavelength range (25- 300um). Description Several studies (e.g., FIRI, SPIRIT, SPECS) have been conducted at ESA and NASA/JPL to assess concepts and to design an optical instrument operating in the FIR region (25-300um) with improved angular resolution (<1arcsec), compared to current FIR missions (e.g., Herschel). These studies concluded on an optical design based on an imaging interferometer, with maximum baselines ranging from 10’s of meters up to 1000’s of meters (depending on the angular resolution requirement). To properly combine the optical beams coming from the spacecraft collectors separated by the baseline distance, passive optical components are needed in the beam combiner spacecraft. For example, beam router (to route/split/separate the science and metrology bands), hollow retroreflectors, science beam combiner, sub-band splitters, antireflective coatings, etc. Some heritage in FIR components exists from Herschel instruments (e.g., SPIRE, PACS, HIFI), but the optical requirements will be more stringent for an imaging interferometer (e.g., better WFE, relative spectral response) compared to single telescope mission.

This activity shall design, develop and test samples of the passive optical components abovementioned assembled in proper mountings. These passive optical components shall be compatible with the requirements of an imaging interferometer at FIR wavelength range (25-300um), e.g., free beam diameter 6-10cm (TBD depending on the location in the optical chain), field of view (in the sky) >1arcmin, broadband operation (>1 octave), etc. Component samples shall be tested under representative environment in order to assess potential performance degradation due to cryogenic conditions. Deliverables Samples of passive optical components, Data Technology Package Application Current TRL: 2-3 Target TRL: 4-5 TRL 5 by 2015 Need/Date: Application Contract Firi 24 Mission: Duration: Reference to S/W Clause: N/A T-8505 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 107 Programme: National Reference: N216-047MM Title: Large FOV double-Fourier interferometric breadboard Objectives To perform the optical design of the overall instrument (i.e., a direct detection interferometer) and to develop and test a representative interferometric breadboard for the demonstration (at VIS-NIR) of imaging and spectroscopy over a large field of view with high spatial and spectral resolution in monochromatic and broadband operation. Description The FIR (far Infrared) region of the electromagnetic spectrum will be explored by current and future ESA missions (Herschel, SPICA) consisting of a single telescope with an aperture diameter of ~3.5 meters. Although instruments in Herschel and SPICA are expected to provide major advances in sensitivity, they will lack the angular resolution required to resolve objects of fundamental interest in astrophysics (e.g., cosmic FIR background radiation, dust structures in planetary systems, star formation end evolution, etc.). Therefore, the need for high-resolution imaging spectroscopy in the FIR region (25-300um) arises as the next challenge, which can be fulfilled by an imaging interferometer scanning through the UV plane. ESA and NASA/JPL have investigated the technical feasibility and the design of imaging interferometers at FIR wavelengths (FIRI, SPIRIT, SPECS), with maximum baselines ranging from 10’s of meters up to 1000’s of meters. One particular concept investigated both at ESA and NASA/JPL is the combination of an imaging interferometer (providing high spatial resolution) with a Fourier transform spectrometer (providing high spectral resolution) and a detector array (providing spatial multiplexing to achieve large FOV). A proof-of-concept-demonstrator is being developed and tested by

Page 101 of 104

NASA/JPL (WFII – wide field imaging interferometer).

The present activity shall perform the optical design of the overall instrument of a direct detection interferometer and shall develop and test a representative interferometric breadboard for the demonstration of imaging and spectroscopy over large field of view (>1arcmin) with high spatial resolution (<1arcsec), spectral resolution (>1000) and a central wavelength in the visible or the NIR (considering monochromatic and broadband operation, polarized and unpolarized light sources). This activity shall be divided into two phases: Phase 1: optical design of the overall instrument and preliminary design of the breadboard (including methodologies/algorithms to retrieve the object information from the interferometric data), Phase 2: detailed design of the breadboard, manufacturing, assembly and testing. Deliverables Breadboard, Data Technology Package Application Current TRL: 1 Target TRL: 3 TRL 5 by 2015 Need/Date: Application Contract Firi 24 Mission: Duration: Reference to S/W Clause: N/A T-8505 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Item ID# : 111 Programme: National Reference: N216-048MM Title: Optical generation and distribution of tunable FIR Local Oscillator Objectives To design, develop and test a FIR wave LO generation and distribution unit applicable to imaging interferometers using heterodyne-detection schemes. Description Large effective apertures (>20 meters) are needed to increase the angular resolution to be able to resolve fundamental astrophysics objects in the FIR region (far Infrared, 25-300um), e.g., cosmic FIR background radiation, dust structures in planetary systems, star formation end evolution, etc. An imaging interferometer with baselines >20 meters could provide sufficient spatial resolution by properly scanning the UV plane. To avoid cryo-cooling of the entire optical interferometer and to increase the spectral resolution to ~1E6, schemes using heterodyne detection have been proposed as an alternative to approaches based on direct detection. In a heterodyne detection system, the sky radiation is mixed with a Local Oscillator (LO) in a non-linear mixer, such that the spectrum of the target object is down-converted from THz frequencies down to GHz frequencies, which is then further amplified and processed at IF (intermediate frequency). The HIFI instrument (Heterodyne Instrument for the FIR), a very high-resolution spectrometer in Herschel, employs heterodyne detection and operates in several bands within the 500 GHz - 2 THz region. The ALMA interferometer (Atacama Large Millimeter Array), a millimetre and sub-millimetre wave interferometer consisting of 64 antennas outfitted with low-noise heterodyne receivers operating in the 30 GHz – 1 THz range, will possibly use optical techniques for generating and distributing millimetre and sub-millimetre wave LO signals.

This activity shall design, develop and test a FIR LO generation and distribution unit using optical technologies and techniques, which can be tuned from 1 to 12 THz (TBC). The phase noise performances shall comply with phase stability requirements applicable to interferometers based on heterodyne-detection schemes, taking into account a low splitting factor (<5). The simultaneous generation of several LOs shall also be investigated. Deliverables Breadboard, Data Technology Package Application Current TRL: 2-3 Target TRL: 4 TRL 5 by 2015 Need/Date: Application Contract Firi 18 Mission: Duration: Reference to S/W Clause: N/A T-8505 ESTER Consistency with Harmonisation Roadmap and conclusion: N/A

Page 102 of 104 Work Plan 2008-2011 ANNEX III : Justification for Proposed Tendering Procedure

Annex III : Justifications for Proposed Tendering Procedure Justification for Proposed Tendering Procedure: C(R) Industrial Policy Committee

TRP Reference Title Firm Fixed Price (Keuro) Proposed Bidder

C219-001PA Penetrator development within framework of Jovian 500 Restricted to UK moon mission, Phase 1 companies

Justification:

The subject activity is proposed as a SRE Directory initiative to address the UK geo-return situation.

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

TRP Reference Title Firm Fixed Price (Keuro) Proposed Bidder

C216-004MM Development of IXO (XEUS) Si pore optics and 2000 Cosine (NL) + mass production processes Micronit (NL) + Soess (D) + KT (D) + Zeiss (D) + DTU (DK) + Xenocs (F) + Fisba (CH)

Justification:

The subject activity builds on developments undertaken within previous contracts awarded to a consortium led by cosine in open competition. The scope of the activity is refined: a) 20 m robot built under this activity will be to a large part a repeat build of already developed technology, necessitated by the change imposed by the modification from XEUS to IXO requirements, and therefore necessarily it needs to be built by the already existing consortium b) 20 m robot built under this activity will be ESA property and would be made available to industrial consortia bidding for future IXO activities, under open competition c) broad industrial consortium exists in this activity with members from NL, D, CH, DK, I, F

It should be mentioned, that this does not pre-empt the competition on the eventual IXO mirror FM programme. The IXO mirror would not be built by cR, who are technology developers but as a consortium will not take on an industrial manufacturing role.

Article 6.1.C of the ESA contract regulations is applicable.

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

TRP Reference Title Firm Fixed Price (Keuro) Proposed Bidder

C216-100MM Heat rejecting entrance window 300 Selex/Galileo (I)

Justification:

The activity is a continuation of a previous contract. Article 6.1.C of the ESA contract regulations is applicable.

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

Page 103 of 104

TRP Reference Title Firm Fixed Price (Keuro) Proposed Bidder

C216-112MM Development of rad-hard TDI CCD for Dark Energy 500 E2V (UK) mission

Justification:

E2V is the only source for space qualified CCDs in Europe. Article 6.1.A is applicable.

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

TRP Reference Title Firm Fixed Price (Keuro) Proposed Bidder

Materials Selection and Testing 500 DN ARCS (A) + subs in competition

Justification:

The subject activity aims at verifying the compatibility of materials with the environmental conditions encountered by the Solar Orbiter. Following an open competition a contract (Contract Number 22330) was awarded at the beginning of 2009 to a team led by Austrian Research Centre Seibersdorf for TRP activity T223-038QM aiming at verifying the "material compatibility under high temperature and high UV load" for the Phoibos mission. Requirements for the Phoibos mission are more stringent than for Solar Orbiter. Giving the similarity of the two activities and the Austrian return situation within the manadatory budgets it is proposed to have the subject activity being led ARCS. Subcontractors shall be selected in competition. 6.1.f of the ESA contract regulations is applicable.

Page 104 of 104