日地系统L_2点Halo轨道绳系卫星编队动力学  

Dynamics of tethered satellite formations on halo orbits near L_2 point of Sun-Earth system

作　　者：赵军[1] 蔡志勤[1] 齐朝晖[1] 黄琳琳[1] 

机构地区：[1]大连理工大学,大连116024

出　　处：《应用力学学报》2010年第1期1-7,共7页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金(10972045)

摘　　要：研究平动点附近周期轨道上旋转多体绳系卫星编队系统的非线性耦合动力学问题。编队系统为各卫星质量接近的轮辐状结构,位于日地系统第二平动点附近,整个系统的旋转保持系绳处于张紧状态,建立Hill限制性三体问题的绳系编队系统动力学模型。针对处于留位阶段的典型对称三星编队,在位于较大Halo轨道上无控制力作用的情况下,进行母卫星轨道运动与系绳摆动耦合运动的动力学模拟,分析轨道方向、卫星质量比、系绳长度以及初始旋转速度对编队系统整体稳定性的影响。The nonlinear coupling dynamics of tethered satellite formations on periodic libration point orbits is presented. The system is arranged in a hub-spoke configuration, in which the tethers are kept tighten by spin of whole system and the parent satellite follows three-dimensional periodic orbits near the second libration point of the Sun-Earth system. We develop the dynamic model of the system in the Hill restricted three-body problem. The numerical simulations of the coupling motion of the parent satellite and tether librations are carried out for a symmetrical three-satellite case on larger Halo orbits in station-keeping stage. The effects of the direction of orbits, the mass ratio, the lengths of tethers and the initial spinning rate, on the stability of system, are demonstrated by numerical results.

关 键 词：Hill限制性三体问题 平动点周期轨道 绳系卫星编队 动力学仿真 

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]