Abstract:

Gyroless attitude determination systems are often utilized in micro-satellites. The key of such configuration is to conquer environmental disturbing moments and improve attitude determination accuracy. The principle of how the steady remanence affects the attitude determination for gyroless microsatellites is analyzed, and the calibration model of satellite remanence and magnetometer bias is established. The calibration algorithm is realized by extended Kalman filter using magnetometer and sun sensor.

Key words: remanence , calibration,  , attitude , determination,  , gyroless , algorithm,  , micro , satellite,  , magnetometer