High Accuracy Attitude Estimation and Control for Spacecraft under Strong Atmosphere Perturbations

This paper investigates the high accuracy attitude estimation and control problem for spacecraft under strong atmosphere perturbation. Firstly, the atmosphere perturbations are analyzed and the attitude dynamic and kinematic equations are introduced. Then, three-axis fiber gyro and star sensor are adopted and the extended Kalman filter (EKF) are used for high accuracy attitude estimation. The reaction wheels are adopted and the magnetic torque rods are used for magnetic unloading, the feedback control law is put forward based on the feedback linearization method. Finally, numerical simulations are carried out and the results show that the proposed methods are effective and feasible, which can realize the high accuracy attitude estimation and control for spacecraft.