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The Corot Space instrument

The Corot Space instrument. Description of the Corot mission. Corot is a small mission of the CNES integrated on the PROTEUS spacecraft, launched by a Soyuz in mid-2006. Mass : 300kg / Power : 300W / Polar Orbit : 896km / Life Time : 2.5 years

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The Corot Space instrument

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  1. The Corot Space instrument SDW2005, 19-25 juin, Taormina

  2. Description of the Corot mission • Corot is a small mission of the CNES integrated on the PROTEUS spacecraft, launched by a Soyuz in mid-2006. • Mass : 300kg / Power : 300W / Polar Orbit : 896km / Life Time : 2.5 years • 3 French laboratories involved : LESIA, LAM and IAS • With collaborations : Belgium, Spain, Austria, Brazil,… • Two scientific objectives : • Asteroseismology : studying the internal structure of stars • Exoplanet search (transit). • The instrument : • Afocal telescope (2 parabolic mirrors off axis). • Camera : dioptric objective, focal plane with 4 E2V CCDs 4280. • Electronics : CCD readout, thermal control, data processing… • On board software. SDW2005, 19-25 juin, Taormina

  3. The Camera of Corot. • Main components of the Camera : • The Dioptric Objective, made of 6 lens, images the FOV on the CCDs. • The Focal-Box contains the CCDs, the prism and the active thermal control of the CCDs • The front End Electronics generate the clocks and the bias voltages for the CCDs. • The thermal drains allow the cooling of the CCDs and the front end electronic (to dedicated radiators). • The mechanical interface sets the CCDs to achieve the optimal de-focus. • The Shield protects the CCDs against protons and cosmic rays. • Thermal components like MLI, thermal probes and heaters allow the thermal control. SDW2005, 19-25 juin, Taormina

  4. Tests performed. Thermal : * Validation of the internal and external interfaces. * Validation of the active thermal control of the Focal-Box. * Validation of the passive thermal control of Electronic. * House-Keeping reference. Optical : * Validation of the CCDs positions inside the focal-box and gap between the two parts of the field. * Effect of DO temperature on the shape of the PSF. * Dispersion of prism. * Absolute transmission of the camera at different wavelengths. Electrical : * Readout noise of and cross-talking between two CCD outputs. * Electro-Magnetic-Compatibility test with all the flight electronics. Calibration : long term experiment. Status : flight model delivered and integrated on the telescope for final optical set-up. SDW2005, 19-25 juin, Taormina

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