Attitude control of flexible spacecraft considering rigid-flex coupling parameters

In order to suppress appendages´ vibration of a flexible spacecraft during attitude control and meet the control requirements of high pointing accuracy, high stability and rapidity of maneuver for spacecraft, an attitude control scheme with initial attitude guidance (IAG) is proposed. And a new attitude control scheme with rigid-flex coupling parameters is designed which is independent of modal information. The stability of the attitude control system is proved based on Lyapunov theory. Simulation results show that the presented attitude control scheme with IAG can suppress the flexible appendages´ vibration and improve the rapidity and stability of flexible spacecraft. The control algorithm is robust to disturbances and parameter uncertainties and easy to implement.