Abstract:Macro fiber composites (MFC) have a good application prospect in active vibration suppression of spacecraft. Discrete form of the rigid-flexible coupling dynamic equation with MFC was built using Hamilton principle and the load simulation method of piezoelectric actuator. The active control was applied by using linear quadratic regulator (LQR) control algorithm. The results show that under impulse loads applied to the flexible body of the spacecraft, the flexible vibration of spacecraft can be quickly suppressed by MFC actuator and meanwhile the attitude stability of the central rigid body is maintained. That is, the cooperative control of flexible and attitude motion can be realized. The active control method based on MFC also has better control effects for high frequency response. For the spacecraft dominated by the flexible body, the active control method based on MFC is superior to the passive control method. This method has more advantages for spacecraft with complex flexible body and is more suitable for engineering application.