Abstract:

In order to satisfy the agile satellite for earth observation with the ability of large-angle/large-position rapid maneuver and high-precision control performance, an algorithm for the agile satellite attitude estimation is presented. The kinematics equation of the agile satellite is derived based on the dual number. The gyro and star-sensor measurement models are proposed. By the linearization of the state and measurement equations, the adaptive iterated extended Kalman filter (AIEKF) is applied to estimate the attitude and attitude angular velocity of the agile satellite with the measurement data of the gyro and star-sensor. The simulation results demonstrate that the proposed algorithm can provide an effective estimation of the state noise, the observation noise, the gyro measurement noise, the attitude and attitude angular velocity of the agile satellite. Attitude determination of the agile satellite is completed in the attitude rapid maneuvering mode.