Time-Fuel Optimal Trajectory Based Attitude Maneuver Control for Flexible Spacecraft

This paper investigates the attitude maneuver control for flexible spacecraft, in which the torque saturation and unknown parameter uncertainties are considered. Firstly, a time-fuel optimal trajectory is developed such that a PD controller based on the trajectory is proposed. Then, in order to suppress the vibration of flexible appendages, a structure filter is designed for the first order elastic mode. Simulation results show that the high-precise attitude control and vibration suppression are achieved successfully. Considering the inertia parameter errors, the effectiveness of the developed optimal trajectory is demonstrated.