摘要
本文以子结构离散的柔性多体系统动力学为基础，引入与碰撞有关的约束条件导出了描述碰撞过程的柔性多体系统的动力学方程。通过仿真计算可得到空间伸展机构撞击阶段的时间、构件在碰撞阶段的动力学响应；并从与约束方程相关的Ｌａｇｒａｎｇｅ乘子获得撞击力的变化规律。从而可较全面地描述空间伸展机构整个接触碰撞动力学过程。
In this paper,the substructure method is used to obtain a general non linear dynamic equation of flexible multibody system The constrained conditions with impact are led into the equation to derive the dynamic equation describing the process of impact The impact time and dynamic reaction of bodies are calculated The time history of impact force is obtained from the Lagrange multiplier in relation to the constraint of impact A contact impact dynamics simulation of a spacecraft deployable mechanism with two flexible components is used to illustrate the method in detail
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1997年第3期14-19,25,共7页
Journal of Astronautics
基金
国家教委博士点专项基金
国家自然科学基金
关键词
空间伸展机构
伸展机构
接触碰撞
多体动力学
Spacecraft deployable mechanism Contact impact dynamics Substructure method
