中国空间科学技术

中国空间科学技术

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基于主动约束层阻尼控制的大型挠性航天器动力学模型

刘志臻;李东旭;   

  1. 国防科学技术大学航天与材料工程学院,国防科学技术大学航天与材料工程学院 长沙410073,长沙410073
  • 发布日期:2007-04-25

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

Liu Zhizhen Li Dongxu (School of Aerospace & Matherials Engineering,National University of Defence Technology,Changsha 410073)   

  • Online:2007-04-25

被引次数

22

摘要： 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。

关键词: 混合坐标, 拟坐标拉格朗日方程, 主动约束层阻尼板, 动力学模型大型挠性航天器

Abstract: 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.