复合柔性结构航天器动力学建模研究  

Dynamics Modeling of Spacecraft with Composite Flexible Structures

作　　者：曲广吉[1] 程道生[1] 

机构地区：[1]中国空间技术研究院空间飞行器总体设计部,北京100086

出　　处：《中国工程科学》1999年第2期52-56,共5页Strategic Study of CAE

摘　　要：柔性航天器动力学建模的传统方法是采用混合坐标法 ,针对中心刚体带大型柔性附件类的航天器 ,这种方法在理论建模和工程应用方面都获得了极大的成功。在中心刚体加柔性附件类航天器柔性动力学研究成果基础上 ,通过计及柔性体与柔性体连接点间的复合位移变形 ,利用混合坐标法建立了复合柔性结构航天器动力学模型 ,其软件系统DASFA 2It is a conventional method to build dynamic models of flexible spacecraft with hybrid coordinates. This kind of modeling has gotten a great success both in theory and practice to spacecraft with rigid main body and large flexible appendages. However, modern spacecraft are becoming much bigger and more and more complicated. Their developing trend in structure is: 1. Rigid main body is attached by flexible module, to which kinds of large flexible appendages are fixed. This kind of spacecraft is a complicated structure system composed of rigid main body and composite flexible structures; 2. The flexible multi modules main body, taking on a lower stiffness, and several kinds of large flexible appendages attached to it make the whole spacecraft as an all flexible structure system. It is impossible to build the dynamic equations of a spacecraft by its flexible modes, when some of its flexible appendages are not fixed to the rigid main body directly. In order to take full advantage of the achievement of spacecraft dynamics of rigid main body with flexible appendages, this paper makes dynamic models of composite flexible structure spacecraft by hybrid coordinates with taking into consideration the composite transition of linking point between flexible bodies. The corresponding computing software DASFA 2 0 has been used in space engineering design and analysis. [

关 键 词：航天器 复合柔性结构 柔性动力学 混合坐标法 建模 设计 LAGRANGE函数 

分 类 号：V423[航空宇航科学与技术—飞行器设计]