基于主动约束层阻尼控制的大型挠性航天器动力学模型

Dynamics Model of Large Flexible Spacecrafts Using Active Constrained Layer Damping Control

以大型挠性航天器简化模型——中心刚体和固接板混合系统为对象,同时考虑板表面粘贴的主动约束层阻尼结构,根据拟坐标拉格朗日方程,建立了包含所有高阶小量的完整动力学模型。建模时,采用混合坐标描述中心刚体和主动约束阻尼板的运动,用Golla-Hughes-Mctavish模型描述阻尼材料的复模量。基于该动力学模型可进行空间柔性板振动的主动约束阻尼控制器设计和大型挠性航天器的姿态动力学研究。

The simplified model of large flexible spacecraft——the hybrid system of rigid body with flexible panels which were partially bonded with active constrained layer damping treatments, was studied. By virtue of quasi-coordinates Lagrange＇s equations, the dynamics equations including all of the high order terms were derived. In the process of modeling, the motions of the rigid body and the active constrained layer damping plates were decribed by hybrid coordinates, the complex modulus of damping material was described by Golla-Hughes-Mctavish（GHM） model. Based on these dynamics equations, the active constrained layer damping vibration controller of the solar panels can be designed, and also, the attitude dynamics of large flexible spacecraft can be studied.