T-SAGE : the challenging payload of the Microscope micro satellite
- Paper number
IAC-08.B4.2.10
- Author
Mr. Manuel Rodrigues, Office National d’Etudes et de Recherches Aérospatiales (ONERA), France
- Coauthor
Dr. Bernard Foulon, Office National d’Etudes et de Recherches Aérospatiales (ONERA), France
- Coauthor
Mr. Pierre Touboul, Office National d’Etudes et de Recherches Aérospatiales (ONERA), France
- Coauthor
Mrs. Françoise Liorzou, Office National d’Etudes et de Recherches Aérospatiales (ONERA), France
- Coauthor
Mr. Vincent Lebat, Office National d’Etudes et de Recherches Aérospatiales (ONERA), France
- Coauthor
Mr. Ratana Chhun, Office National d’Etudes et de Recherches Aérospatiales (ONERA), France
- Year
2008
- Abstract
T-SAGE (Twin Space Accelerometer for Gravitation Experiment) is the payload of the MICROSCOPE mission dedicated to the in orbit test of the Equivalence Principle (EP). This first fundamental physics space mission ever launched to sense the EP should in 2011 largely improved the based ground experiments with an accuracy of 10-15. The instrument embarks two pairs of test-masses made of Platinum Rhodium alloy and Titanium alloy. These masses are simultaneously used to test the universality of free-fall and to serve as inertial reference for the drag-free and attitude control of the spacecraft. Based on electrostatic accelerometers developed in ONERA, T-SAGE has been designed with challenging technologies for the electronics and for the sensor core: exhibiting respectively a few tens of nanovolts noise and a few micro-volts per degree thermal sensitivity, and micrometers geometrical accuracy. The Engineering Model has been produced, integrated and tested in laboratory. The integration process has been improved in order to achieve the required 20 micrometer accuracy for the test-mass centring. In addition, a specific test-mass blocking device has been developed and tested in order to cope with the high levels of vibration during the launch phase. The sensor core has to be preserved from any defects that could reduce the in orbit performance. This paper will tackle the achievements attained up to the instrument phase C review by firstly presenting the improved flight model design. Results from the reliability after launch vibrations of the mechanical configuration will be presented as well as from the first operation of the engineering model. Perspectives on the instrument development will be drawn detailing the verification of the most critical aspects concerning the operation and the performance of the payload.
- Abstract document
- Manuscript document
IAC-08.B4.2.10.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.