可变构型复合柔性结构航天器动力学建模研究  

Mathematical Modeling of a Class of Variable Structure Spacecraft with Flexible Multibody Appendages

作　　者：史纪鑫[1] 曲广吉[1] 

机构地区：[1]中国空间技术研究院总体部,北京100094

出　　处：《宇航学报》2007年第1期130-135,共6页Journal of Astronautics

基　　金：总装备部十五预研项目(413200203)

摘　　要：针对中心刚体加复合柔性结构类航天器采用混合坐标法和子结构模态综合法,建立了可变构型复合柔性结构航天器低阶动力学模型。获得的柔性动力学方程及其各类耦合系数矩阵,适用于全星级可变构型系统和部件级复合柔性附件系统的控制系统设计与仿真,该模型具有阶数低和工程实用的特点。A low order mathematical model for a class of flexible multibody spacecraft is obtained by hybrid coordinate and component mode synthesis. The generic spacecraft considered consists of a main rigid body to which a number of flexible muhibody appendages are attached. The model and flexible coupling coefficients developed can be used for analysis and simulation of many realistic spacecrafts. The model is low-order and adapts to control system design for this kind of variable structure spacecraft.

关 键 词：航天器 柔性航天器动力学 模态综合 混合坐标法 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]