Study on Attitude Determination Method of Satellite During Yaw Maneuver

During satellite yaw maneuvers, the angular velocity of the star changes greatly, and the conventional steady-gain Kalman filtering method is difficult to meet the need of high-precision attitude determination. To solve this problem, a high-precision calibration algorithm of gyro in orbit is designed, and a sequential UD decomposition filtering algorithm is applied to the attitude determination of satellite during yaw maneuver. The new algorithm uses sequence UD decomposition to compute the error covariance matrix and filter gain matrix in real time to ensure the positive symmetry of the covariance matrix and prevent filter divergence. The simulation results show that compared with Kalman filtering with constant gain, the sequential UD decomposition filtering algorithm significantly improves the attitude determination accuracy during yaw maneuvers. The new algorithm has the advantages of small computation and good numerical stability, which is convenient for on-orbit computer real-time calculation, and has important engineering application value.