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COROTCASE ARCHITECTURE

COROTCASE ARCHITECTURE. COROTCASE product is composed of four sub-assembly Structure Electronics units Thermal equipment Electrical equipment (harness and wirering brackets). Thermal equipment. Box Temperature : 0° to 40°C Temperature stability : ±4°C/orbital. INTERNAL ALVEOLE

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COROTCASE ARCHITECTURE

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  1. COROTCASE ARCHITECTURE COROTCASE product is composed of four sub-assembly • Structure • Electronics units • Thermal equipment • Electrical equipment (harness and wirering brackets)

  2. Thermal equipment Box Temperature : 0° to 40°C Temperature stability : ±4°C/orbital • INTERNAL ALVEOLE • 3 Thermal doublers (thermal inertia & heat distributor) • Under BS2, BEX1 et BEX 2 (+Yp) • Under BCVCAM et BCVETN (+Zp) • Under MDPU1 et MDPU2 (-Zp) • Thermal braids (link +Zp to +Yp)not represented in the picture • MLI • Heaters and thermistancesassembly

  3. Thermal equipment Box Temperature : 0° to 40°C Temperature stability : ±0.15°C/orbital No noise generation at every frequencies • EXTERNAL ALVEOLE(fine thermal control needed by BCCs and BS1) • 2 Thermal doublers(thermal inertia & heat distributor) • Under BS1.1 et BCC1 • Under BS1.2 et BCC2 • 2 RADIATORS • 2 Thermal braids(Link shield and EP of COROTCAMto COROTCASE). • Thermal isolation stand-off ( PERMAGLASS) At every screw which areused to link the thermalsdoubler to the structure • MLI • Heaters and thermistances assembly • FOCAL BOX RADIATOR • 1 Al panel • 2 isolation radiator supports • 1 thermal bus(thermal inertia & heat distributor from FB to is radiator) • MLI

  4. FOCAL BOX Functional temperature : -40°C to -55C Temperature stability: ±0.005°C/orbital • 1 Box • 4 CCD arrays 2048*2048 ( Ref : EEV 4280)(2 for the EXOPLANET and two for the SISMO program) • 1 Prism upper the EXOPLANET chain • 1 Window (Particular protection and tightness). • 1 Thermal isolation ring • 1 Flexible support ring(mechanical filter for resonance frequenciesand thermal elastics yields) • Thermal regulation • 1 thermal braid • 1 active regulation (positioned to the thermal braid) • 1 bus and radiator (on COROTCASE) • Regulation electronics boxes (BS1.1 and BS1.2 see COROTCASE)

  5. Dioptric objective Temperature :~ 20°C Stability temperature : 0.5°C/heure • Aluminium alloy body • Five lenses • Rings separation • Entrance pupil • Calibration LEDs • Electrical connectors(Thermal elements and calibration LEDs)

  6. Camera thermal controlsynthesis • MLI cover every internal and external part of the camera(Flexs and harness also) • 1 Thermal PI regulation line  (using heaters and thermal captors) • 2 Thermal braids principally dedicated to the thermal dissipation of the EP to the radiator mounting on COROTCASE • 1 Thermal braid for the thermal dissipation of the Focal Box • Isolated Stand-off (PERMAGLASS) at every links between the shield and the interface ring

  7. 180° rotation on Zs S ZOF YJ2000 XJ2000 XOF 180° rotation on Xs 180° rotation on Xs 180° rotation on Zs Zs- Ys+ Xs+ Zs- Ys+ Xs+ . . Ys+ Xs+ Ys+ Xs+ Zs- Zs- Difficultiesfor the thermal control • 4 different inertial attitudes of the satellite ( exploratory 1 & 2, Central 1 & 2) • Variation of the solar aspect angle of the different panels during long time observation • Temperature stability requirements • Complex thermal control, with analyses of multiple cases

  8. Main perturbations for the thermal control of the internal alveol • Solar flux (mean level for the year) is critical for the level and the total consummation • Solution • Put radiator on the maximumstable faces(max stable sink temperatureon a year) • Results • Functional temperature10°C to 30°C (compliant) • Orbital stability±2°C/orbital (compliant) • Consummation~30W (very low but no requirements today)

  9. Main perturbations for the thermal control of the external alveol & FB (radiator) • Solar and albedo orbital fluxes by telescope faces reflections on the radiators induce critical stability • Solution • Special coating on telescope reflection faces • maximal minimisation of radiation sizing • No heating for nominal acquisition case • Results • Functional temperature10°C to 30°C (compliant) • Orbital stabilitybetter than ±0.15°C/orbital (compliant) Compliant to the requirements using a passive thermal control

  10. BCCs Stability Under construction and validation by scientist

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