1. Space Research Centre EDDICAM Interests in EDDINGTON Professor Alan Wells and Dr Matthew Burleigh Space Research Centre, University of Leicester.

2. Space Research Centre EDDICAM Possible Contributions to EDDICAM from University of Leicester. 1. Planet Search Science- Dr Matthew Burleigh. 2.CCD and Focal Plane Expertise 3. Close R & D relationship with UK CCD supplier (Marconi Applied Technologies-UK) 4.Radiation effects System, mission and sensor implications. Screening design and verification. 5.FPC development. Planning, procurement or build in-house, calibration, integration and test.

3. Space Research Centre Relevance of our CCD Capabilities to EDDICAM 1. Flight packaging of CCD’s into mosaic arrays Each Device pre-selected and calibrated Whole array calibration Flat field, QE, CTE. 2. Thermal Control to <1C. Passive Control with Thermal Radiator (EPIC) Active Control with TEC, Heat Pipe and Radiator (SWIFT) 3. CCD Radiation Response. Radiation shielding design tools. Evaluation of CCD radiation tolerance. Evaluation of charged particle background effects on imaging response. Application-specific CCD development with MAT for radiation tolerance.

4. Space Research Centre CCD Package and Camera Assembly 2000-02. NASA SWIFT XRT CCD batch procured from MAT. Selection and qualification performed in-house. CCD bonded to 5-stage thermo-electric cooler provides CCD operating temperature =-105C Active cooling of TEC hot junction coupled to space radiator by heat-pipe. CCD/TEC unit space qualified for SWIFT Focal plane camera assembly incorporates fixed light filter and radiation shielding. Storage and launch under vacuum for launch safety and contamination control. Hardware built through sub-contracts. Assembly, test, calibration and qualification in- house. Drive electronics built by US partner, to our system specification Protoflight model space qualified for SWIFT.

5. Space Research Centre CCD Package and Camera Assembly 1992-96. XMM-NEWTON EPIC Camera Array of 7, 2.5*2.5 cm 2, 600* 600 pixel CCD 22. 40  pixels. CCD designed by MAT to UL requirements CCDs procured from MAT, screened, tested and calibrated in-house. 4 FM and 2 DM EPIC focal plane cameras built in-house. Radiation screening incorporated. Passive radiator cooling system (-100C CCD operation). Electronics built by space industry to our detailed specification based on in-house prototype heritage.

6. Space Research Centre CCD Package and Camera Assembly 2000-01. Muon Neutrino Mass Experiment 6cm * 6cm array planar array of CCD’s. CCD Camera for Pion Beam Experiments at Paul Scherrer Institute. Drive electronics built under contract by SME to in-house design specifications.

7. Space Research Centre Radiation Effects Radiation dose: Degrades CTI; which affects centroiding accuracy. Affects Read-Noise Background events affect centroiding.

8. Space Research Centre Cosmic Background Events in CCD image Distort Telescope Source Locations Evaluation of effects needed for EDDICAM.

9. Space Research Centre EDDICAM Development Plan Involving Industry Advantages Fabrication of 4 identical flight cameras better suited to an industrial procurement. (High repetitive workload can overload institute resources-EPIC experience). Reproducibility of multiple cameras should be achievable with industry QA and configuration control. Schedule risks accordingly reduced. ESA might be expected to pay for industry procurement for EDDICAM or major sub- systems. Disadvantages Efficient industry development would require a comprehensive & detailed specification. Changes to requirements or recovery from problems are expensive and a serious source of schedule risk. Industry unlikely to have all necessary scientific and technological skills to undertake all required development tasks. Software developments are especially high risk. Need major management inputs from ESA and the EDDICAM system team.

10. Space Research Centre Development Plan Institute Consortium Development Need to set up a well structured EDDICAM Science system Team (could be drawn from several institutes). Advantages Design under control of science system team. Immediate access to highly relevant in-house expertise. Track record important. Access to already-available calibration facilities. Ability to respond quickly to evolving requirements or for problem solving. Close coupling between hardware and software development tasks. Dedicated experimental teams in institutes with proven track record in space instrumentation programmes. Disadvantages High work-load to produce multiple cameras. (serial production is the norm). Multi-institute collaborations carry a high cost and time overhead. Project schedule determined by weakest partner. Complex management arrangements. Dependence on national funding.

11. Space Research Centre A Possible Approach, The EXOSAT MEDA Model. Science team (UL & MPE) provided and controlled all system requirements, developed procurement specifications and were responsible for calibration and verification. Prototypes were built in-house supported by institute contracts to industrial partners. Prototype test data used to define and refine industrial procurement specifications for flight models. Flight hardware built under by an industrial instrument prime contractor (who also managed sub-contractors). Multiple detectors built under this scheme. Science system team supported the industrial contractor with off-line testing, problem solving, technical and management support and feedback of test results into the industrial procurement. Science system team led the calibration of the flight hardware and all software developments. ESA paid for the industrial contracts. National agencies paid for the science support in the institutes and for the off-line R & D. Would this model offer some possibilities for EDDICAM?

12. Space Research Centre Work Packages Declaration of Interest. Priority Areas 1. CCD procurement and selection. Management of CCD procurement from MAT. Over- seeing device selection via in-house test programme. 2. CCD focal plane packaging. Transfer of expertise. Radiation shielding analysis. Assessment of thermal design requirements and support with thermal analysis. Support of industrial activities, as appropriate. Acceptance testing. 3. Calibration support. Preferably in collaboration with a partner with facilities/experience in photometric calibration. 4. Science system support and software development for planet search imaging and background subtraction. 5. Design support and fabrication of prototype focal plane camera. Additional areas if required: 6. Support for front end electronics design, specification and fabrication. 7. System support for industrial contractor for flight model cameras. 8. System support for flight model CCD drive electronics.