Calibration of MICROSCOPE Original Research Article

The MICROSCOPE mission is planned for launch in early 2009. It aims to verify the Equivalence Principle to an accuracy of 10−15, which is currently difficult to obtain on Earth because of the intrinsic limitations of the torsion pendulum and disturbing phenomena, like seismic activity. In space the experiment can take advantage of the quiet environment provided by a drag-free satellite. The instrument used for the test is a differential electrostatic accelerometer composed of two inertial sensors with test-masses made of different materials: one in Platinum–Rhodium alloy, the other in Titanium alloy. The space experiment will also benefit from a second differential accelerometer with both test-masses of the same material, which will be used as a reference instrument to characterise the disturbing signals and sensitivities. The in-orbit calibration of the instrument is mandatory to validate the space test and several procedures have been previously proposed, taking advantage of the satellite propulsion system or the a priori knowledge of natural in-orbit applied accelerations. Due to the actual configuration of the MICROSCOPE propulsion system, the possibility of accurate satellite manoeuvres is limited but sufficient. This paper presents the necessary compromise between the knowledge of satellite and instrument parameters and the calibration procedures. The scenario of the MICROSCOPE in-orbit calibration phase is finely defined in agreement with the required performances for the EP test accuracy.