Abstract：Attitude and vibration control of the three-axis-stabilized flexible spacecraft should deal with attitude kinematics coupling and torque coupling, dynamic coupling of the flexible modes with the rigid body, and parameter uncertainty caused by the large flexible appendages. Based on ‘Bandwidth Insulation Method’, attitude controller and vibration controller are designed independently. The influence of vibration to attitude is considered as a time-variant disturbance. The attitude controller consists of the fast and slow loops as angular velocity and attitude angular in terms of singular perturbation theory. Further an integral SDRE controller to resist strong disturbance is designed for the two loops. To control the flexible vibration, a PPF (Positive Position Feedback) controller related to the independent modes is constructed, which ensure the robustness of the system for the uncertainty of the structure or the parameters. Finally, the simulation results show the good performance of the attitude stabilization in spite of the disturbance torque, and the fast decay of vibration.
李 洋;仇原鹰;张 军;彭福军. 一种挠性航天器的自适应姿态控制与振动控制[J]. , 2009, 28(12): 178-182.
LI Yang;QIU Yuanying;ZHANG Jun;PENG Fujun. Adaptive Attitude Control and Active Vibration Control for the Flexible Spacecraft. , 2009, 28(12): 178-182.
2009, Vol. 28 
