| 空间伸展机构接触碰撞的动力学分析 |
| |
| 引用本文： | 刘锦阳,洪嘉振.空间伸展机构接触碰撞的动力学分析[J].宇航学报,1997,18(3):14-19,25. |
| |
| 作者姓名： | 刘锦阳 洪嘉振 |
| |
| 作者单位： | 上海交通大学工程力学系 |
| |
| 基金项目： | 国家教委博士点专项基金,国家自然科学基金 |
| |
| 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。本文以伸展机构的两个构件碰撞过程的仿真为例详细介绍各种建模方法与计算方法。
|
| 关 键 词： | 空间伸展机构 伸展机构 接触碰撞 多体动力学 |
DYNAMIC ANALYSIS OF SPACECRAFT DEPLOYABLE MECHANISM WITH CONTACT IMPACT |
| |
| Liu Jinyang,Hong Jiazhen.DYNAMIC ANALYSIS OF SPACECRAFT DEPLOYABLE MECHANISM WITH CONTACT IMPACT[J].Journal of Astronautics,1997,18(3):14-19,25. |
| |
| Authors: | Liu Jinyang Hong Jiazhen |
| |
| Abstract: | 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 |
| |
| Keywords: | Spacecraft deployable mechanism Contact impact dynamics Substructure method |
| 本文献已被 CNKI 维普 等数据库收录！ |
|
