摘要
依据 Kane方程 ,提出带有多个柔性矩形板的复杂航天器的动力学建模方法。该方法是依据 3个假设条件得到的。通过引入矩形板在中面内不可伸展的假设 ,并在适当的阶段进行线性化处理 ,可在动力学方程中自然地引入“动力刚化”项。数值仿真的结果为航天器的设计提供了重要的理论依据。
Dynamic modeling method of complex spacecraft with flexible rectangular plates is obtained according to Kane's equations. The method is based upon three hypotheses. 'Dynamic stiffening terms' are automatically incorporated into the dynamic equations by introducing the inextensible hypothesis of the rectangular plates in their mid-planes. The numerical simulation results provide theoretical fundamentals for the design of spacecraft. The modeling method in this paper may be naturally extended to the other flexible multi-body systems.
出处
《中国机械工程》
EI
CAS
CSCD
北大核心
2000年第6期650-653,共4页
China Mechanical Engineering
关键词
航天器
伸展机构
柔性体
动力学
spacecraft unfolded mechanism flexible body dynamics
