空间双体系绳系统展开阶段末端星姿态动力学分析

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。

Attitude dynamic analysis of the end-bodies of space tether system in deployment

In order to analyze the attitude motion of end-bodies in deployment of Space Tether System (STS), the mathematical model of deployment and the angular motion equations of end-bodies are developed based on the Lagrangian equations of the second kind. Since the sizes of satellites are not negligible in actual space missions, the mother satellite and daughter satellite connected by tether are regarded as rigid bodies with certain sizes, and the mass of the mother satellite is much larger than the daughter satellite. Besides, the tether is regarded as a rigid rod in modeling. The mathematical model is used to analyze the deployment process of STS, and the main influence factors to the attitude motions of end-bodies are studied, which includes the initial disturbance of attitude angles, the dynamic and static asymmetry of end-bodies. Simulation results demonstrate that either the initial disturbance of end-bodies or the dynamic and static asymmetry may cause the attitude instability of end-bodies in deployment, even lead to the enwinding of the tether around satellites. The simulation results can provide reference for the satellites attitude control of the STS.