| 引用本文: | 陈书敏,王长青,扎伯罗特诺夫·尤里,等.空间双体系绳系统展开阶段末端星姿态动力学分析.[J].国防科技大学学报,2020,42(2):98-106.[点击复制] |
| CHEN Shumin,WANG Changqing,Zabolotnov Yuriy,et al.Attitude dynamic analysis of the end-bodies of space tether system in deployment[J].Journal of National University of Defense Technology,2020,42(2):98-106[点击复制] |
|
| |
|
|
| 本文已被：浏览 6994次 下载 5457次 |
| 空间双体系绳系统展开阶段末端星姿态动力学分析 |
| 陈书敏1,2,王长青1,2,扎伯罗特诺夫·尤里2,3,李爱军1,2 |
|
(1. 西北工业大学 自动化学院, 陕西 西安 710129;2. 中俄国际空间系绳系统研究中心, 陕西 西安 710129;3. 萨马拉国家研究型大学 空间与火箭技术学院, 俄罗斯 萨马拉 443082)
|
| 摘要: |
| 为了研究空间系绳系统展开过程中末端星的姿态运动,采用第二类拉格朗日方程建立系统展开及末端星角运动的数学模型,分析展开阶段末端星的姿态动力学特性。建模时将系绳末端连接的母星与子星视为尺寸不可忽略的刚体,且母星质量远大于子星质量,系绳视为有质量的刚性杆。利用该数学模型可以分析系绳系统的展开过程,研究影响末端星姿态运动的主要因素,包括姿态角初始扰动以及末端星动/静不对称性。仿真结果表明,系绳展开时末端星姿态角初始扰动及动静不对称性可能会导致姿态角失稳,出现系绳缠绕星体的情况。仿真结果可以为展开阶段末端星姿态控制提供参考。 |
| 关键词: 空间系绳系统 展开过程 第二类拉格朗日方程 末端星姿态 动态及静态不对称性 |
| DOI：10.11887/j.cn.202002013 |
| 投稿日期：2018-10-10 |
| 基金项目:中央高校基本科研业务费资助项目(3102017JC06002)；陕西省重点研发计划资助项目(2017KW-ZD-04) |
|
| Attitude dynamic analysis of the end-bodies of space tether system in deployment |
| CHEN Shumin1,2, WANG Changqing1,2, Zabolotnov Yuriy2,3, LI Aijun1,2 |
|
(1. School of Automation, Northwestern Polytechnical University, Xi′an 710129, China;2. China-Russia International Research Center of Space Tether System, Xi′an 710129, China;3. School of Space and Rocket Technology, Samara National Research University, Samara 443086, Russia)
|
| Abstract: |
| In order to analyze the attitude motion of end-bodies in deployment of STS(space tether system), based on the Lagrangian equations of the second kind, the mathematical model of deployment of the system and the angular motion of end-bodies were developed, to analyze the attitude dynamics of end-bodies in deployment. Since the sizes of satellites are not negligible in actual space missions, the mother-satellite and sub-satellite connected by tether were regarded as rigid bodies with certain sizes, and the mass of the mother-satellite is much larger than the sub-satellite in modeling. Besides, the tether is regarded as a rigid rod with a certain mass. The mathematical model was used to analyze the deployment process of STS, and to analyze the main influence factors to the attitude motions of end-bodies including the initial disturbance of attitude angles, and the dynamic or static asymmetry of end-bodies. Simulation results demonstrate that either the initial disturbance or the dynamic and static asymmetry of end-bodies in deployment can cause the attitude angles instability, or even cause the tether enwinding satellites. The simulation results can provide reference for the attitude control of satellites in deployment. |
| Keywords: space tether system deployment Lagrangian equations of the second kind attitude of the end-bodies dynamic and static asymmetry |
|
|
|
|
|
