Halo轨道编队构型重构最优控制研究  

Study on Optimal Control for Halo Orbits Formation Reconfiguration

作　　者：张跃东[1] 孟云鹤[1] 桂忱[2] 戴金海[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]长沙理工大学,湖南长沙410004

出　　处：《国防科技大学学报》2011年第4期24-29,共6页Journal of National University of Defense Technology

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

摘　　要：变长度的测量基线与空间构型的多样性是航天器以编队方式执行深空探测任务的优势之一,该优势的发挥与航天器编队构型重构能力密切相关。针对Halo轨道编队构型重构问题开展研究,分析了Halo轨道编队的构型特性,推导了Halo轨道编队构型重构最优控制的Hamilton方程,基于第一类生成函数构造了最优控制Hamilton方程的迭代求解方法;分别在圆型限制性三体模型和双圆型限制性四体模型中,对地月Halo轨道编队构型重构的最优控制问题进行了仿真计算,验证了迭代求解方法的有效性;仿真结果表明,太阳引力摄动对地月Halo轨道编队构型重构的控制能耗具有较大的影响,选取恰当的重构时机可降低控制能耗。Changeable measurement baseline and diversity of space configuration are advantages of spacecraft formation implementing deep-space exploration mission. They are closely related to the reconfiguration capability of spacecraft formation. Aimed at the issue of optimal control for Halo orbits formation reconfiguration, this study firstly analyzed the configuration characteristics of Halo orbits formation, then the Hamiltonian equation of optimal control for Halo orbits formation recordiguration were deduced. Iterative method for solving the Hamiltonian equation was built based on the first generating function. Simulation of optimal control for Halo orbits formation reconfigurafion in the Earth-Moon system was carried out, and the validity of this iterafive method was verified. Simulation results show that sun perturbation has huge influenee on the fuel consumption of optimal control during the process of Halo orbits formation reconfiguration, and the fuel consumption can be reduced by selecting the reconfiguration times correctly.

关 键 词：平动点 Halo轨道编队 构型重构 最优控制 生成函数法 

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]