ACCELERO-STELLAR HYBRIDIZATION FOR MICROSCOPE DRAG FREE MISSION

MICROSCOPE is CNES fourth microsatellite based on MYRIADE platform. Its mission is dedicated to the test of the Equivalence Principle (EP) with an improved accuracy of 10-15. Therefore the satellite attitude requirement is very stringent and the payload accelerometric measurements need to be used in the control loop. This paper deals with one of the most critical issue in MICROSCOPE attitude and acceleration control: the accelero stellar hybridization in spinning mission mode.