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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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slide1

COROTCASE ARCHITECTURE

COROTCASE product is composed of four sub-assembly

  • Structure
  • Electronics units
  • Thermal equipment
  • Electrical equipment (harness and wirering brackets)
thermal equipment
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
thermal equipment1
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
focal box
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)
slide5

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)
camera thermal control synthesis
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
difficulties for the thermal control

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
main perturbations for the thermal control of the internal alveol
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)
slide9

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

bccs stability
BCCs Stability

Under construction and validation by scientist

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