Halo轨道编队保持控制方法及仿真分析  

Simulation and Keeping Control Method for Halo Orbits Formation

作　　者：张跃东[1] 孟云鹤[1] 陈琪锋[1] 戴金海[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《计算机仿真》2011年第4期92-95,共4页Computer Simulation

基　　金：国家自然科学基金(10702078);国防科技大学预研基金(JC08-01-05)

摘　　要：开发深空探测,研究对近地建立空间站。针对地月L1点空间站与绕飞航天器的构型保持控制问题,共线平动点附近的运动具有较强的不稳定性,太阳引力摄动对Halo轨道编队构型具有较大的影响。为实现Halo轨道编队的稳定飞行,根据Floquet模态理论设计了Halo轨道编队保持控制器,在分析消除模态4最优控制策略的基础上,研究了Floquet模态之间的内在耦合关系,进一步提出了模态相消控制策略,降低了保持控制燃耗。在限制四体模型下,对太阳引力摄动下的Halo轨道编队保持控制问题进行了数值仿真,仿真结果表明:保持控制器可实现Halo轨道编队相对运动构型保持,且具有较高的控制精度,不存在误差积累现象。The keeping control for formation configuration between space station and surrounding spacecraft near L1 point in Earth-Monn system is studied.Sun perturbation has great influence on the configuration of Halo orbits formation due to the instability of the motion around the collinear libration points.For keeping the formation near nominal configuration,the keeping control for Halo orbits formation is designed based on Floquet modes theory.Based on the analysis of optimal impulse control strategy for eliminating mode 4 in halo orbits,the inner coupling relations between Floquet modes is discussed and the control strategy of eliminating Floquet mode pairs proportionally is put forward for reducing the fuel consumption.Simulation on the keeping control problem of Halo orbits formation is carried out under the restricted four body model.Results show that keeping control for Halo orbits formation can be achieved by Floquet control method with high precision and without error accumulation.

关 键 词：平动点编队 太阳引力摄动 模态 保持控制 

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]