基于压电纤维复合材料的航天器动力学建模与振动抑制

压电纤维复合材料(MFC)在柔性航天器的振动主动抑制中具有很好的应用前景。利用哈密顿原理和压电驱动的载荷比拟方法,建立了带MFC压电驱动的离散形式的刚柔耦合动力学方程,采用线性二次型最优控制(LQR)算法进行主动控制。结果表明：在航天器的柔性体受到脉冲载荷激励条件下,使用MFC驱动器可以实现航天器挠性振动的快速抑制,并且同时保持中心刚体姿态的稳定性,即能够实现挠性振动与姿态运动的协同控制。基于MFC的主动控制方法对于高频响应也具有较好的控制效果。对于柔性占优的航天器,采用MFC的主动控制优于被动控制。本文方法在处理具有复杂柔性体的航天器时更具优势，更适合于工程应用。

Dynamics modeling and vibration suppression of spacecraft based on macro fiber composites

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.