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位于地月L2点周期轨道的中继星将首次为“嫦娥4号”月球背面着陆探测任务提供通信中继服务。中继星转移轨道设计是中继任务实施的关键环节。针对中继星转移轨道存在转移时间、近月点高度和halo轨道振幅等约束条件,系统研究了基于月球近旁的地月L2点转移轨道设计方法。首先基于限制性三体模型,分析了halo轨道族与着陆点可见性关系;然后将月球近旁转移轨道分为地月直接转移段和地月动平衡点附近周期轨道拟流形入轨转移段,采用带有状态约束的微分修正算法对这两段轨道进行拼接,得到了从地球附近至目标轨道族的月球近旁转移轨道;最后,针对南族halo轨道分析了halo轨道振幅和月球飞越高度对转移轨道设计的影响,以及转移轨道的入轨相位分布。仿真结果表明:月球近旁转移轨道设计方案具备工程上的可行性与优越性。该方案可以为实际工程任务和应用提供参考。
For the first time, a relay star located in the L2 cycle of Earth Moon will provide a communication relay service for the “Chang’e-4” lunar back-ground exploration mission. Relay star transfer orbit design is the key link in the implementation of relay task. Considering the existence of transfer time, the height of the moon in recent months and the halo amplitude of the orbit, the method of designing the L2 orbit transfer trajectory of the moon and the moon is systematically studied. Firstly, based on the restricted three-body model, the relationship between the halo orbit group and the landing point is analyzed. Then the lunar orbits are divided into the orbit transfer segment of the lunar-moon direct transfer segment and the quasi- The two orbits were spliced by using the differential correction algorithm with state constraints to get the orbit near the moon from the Earth to the target orbit. Finally, the halo orbit amplitude and the lunar flying height were analyzed for the halo of the Nansha The impact of orbit design and the orbital phase shift of the transfer orbit. The simulation results show that the design scheme of lunar orbit transfer orbit has the engineering feasibility and superiority. The program can provide reference for practical engineering tasks and applications.