Microscope - Extreme Stability Requirements For FEMTO-G Measurements

Paper number

IAC-07-C2.7.03

Author

Mr. Pierre W. Bousquet, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mr. Benjamin Pouilloux, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mrs. Catherine Serieys, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mrs. Elise Bellouard, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mr. Christian Puillet, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mr. Jean-Bernard Dubois, Centre National d'Etudes Spatiales (CNES), France

Year

2007

Abstract

Microscope is a 200 kg microsatellite which belongs to the CNES Myriad family. It is dedicated to a fundamental physics experiment. The satellite development is currently in Phase B. Launch is planned for 2010.

The scientific objective of the mission is to test – for the 1st time in space - the Equivalence Principle (EP) with an accuracy 100 times better than that achieved in ground tests. The instruments developed by ONERA are composed of two differential electrostatic accelerometers operating at finely stabilised room temperature. Their relative accuracy is in the 10-15 g range. Continuous measurements will be madeover periods of weeks. Furthermore, the satellite motion and attitude are precisely controlled by a Drag Free system which uses 12 micro-thrusters developed by ESA.

After summarising the basic principles behind the scientific measurements, this paper will present the mechanical and thermal architecture of the satellite, which exhibits significant modifications with respect to the standard Myriad design. The major specifications will be presented, and we will show how the spacecraft configuration has been designed to satisfy the payload interface requirements, particularly for mechanical stability, thermal insulation and micro-cracking avoidance. The performance validation test plan will be presented, with results of elementary tests already performed. 

Finally, we will briefly describe an original de-orbiting system which Microscope will carry in order to comply with the Space Debris Code of Conduct. It consists of a deployable wing made of light-weight aluminised kapton membrane, deployed by an inflatable mast, which will enhance the atmospheric drag of the satellite after the end of its mission.

The contents of this paper correspond to an activity currently running at CNES. It will focus on detailed mechanical and thermal definition and performances not previously presented at a conference. 

Abstract document

IAC-07-C2.7.03.pdf

Manuscript document

IAC-07-C2.7.03.pdf (🔒 authorized access only).

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