基于平动点轨道的绳系卫星编队重构仿真  

Simulation of Reconfiguration of Tethered Satellite Formations in Libration Point Orbits

作　　者：赵军[1] 蔡志勤[1] 齐朝晖[1] 

机构地区：[1]大连理工大学,工程力学系,工业装备结构分析国家重点实验室,大连116024

出　　处：《系统仿真学报》2011年第12期2805-2811,共7页Journal of System Simulation

基　　金：国家自然科学基金(10972045)

摘　　要：针对位于日地系统共线平动点附近三维周期轨道上的旋转绳系卫星编队,利用数值仿真研究其重构阶段的动力学稳定性问题。编队系统为一个母卫星和n个子卫星通过长度可变系绳连接的轮辐状结构,基于Hill限制性三体问题建立姿态与轨道耦合的动力学模型,分别针对留位以及包含展开和回收的编队重构阶段,利用非线性数值仿真研究其姿态稳定性。研究表明系统留位姿态稳定,展开不稳定,回收稳定,较小的母卫星轨道高度及绳长变化速度更有利于姿态稳定。Simulation of dynamical stability of spinning tethered satellite formations during reconfiguration stage was researched.The system consists of a parent satellite and n subsatellites,connected together in a hub-spoke configuration via variable-length tethers,where the parent satellite follows three-dimensional periodic orbits near the second libration point of the Sun-Earth system.Based on the Hill＇s restricted three-body problem,a new dynamical formulation was developed,which could be utilized for the nonlinear coupling motion analysis of the orbital motion and tether libration.The attitude stability during station-keeping and reconfiguration stage was investigated.The results demonstrate that the attitude motion is stable during station-keeping and retrieval but unstable during deployment,and the small orbital amplitude and the small tether length rate is more helpful to its attitude stability.

关 键 词：平动点轨道 绳系卫星编队 展开/回收 姿态稳定性 数值仿真 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]