地月L2点Halo轨道支持的登月轨道优化设计

摘要

针对低成本月球探测任务轨道设计问题,基于不变流形提出了地月L2点Halo轨道支持的登月方案,并研究了轨道优化设计方法.建立了3脉冲从近地停泊轨道(LEO)到环月轨道(LLO)的不变流形转移轨道数学模型;设计了全局遍历初值搜索和局部梯度优化的串行优化设计方法,并采用圆型限制性三体模型(CR3BP)优化了一条从LEO出发,通过稳定流形轨道、地月L2点Halo轨道、不稳定流形轨道,最终抵达LLO的燃料最优转移轨道;给出了仿真实例,仿真结果验证了文章所述方法的正确性.研究结论可为未来低成本地月转移或Halo轨道空间站支持的登月方案提供参考.%The derived invariant manifold of Halo orbits near the collinear liberation points is known for the low energy consumption in deep space exploration missions. In this paper, a lunar landing scheme based on Halo orbit near L2 point of Earth-Moon system was proposed and the design optimi-zation was discussed. Firstly, a mathematical model of trans-lunar trajectory based on invariant man-ifold from low earth orbit ( LEO) to low lunar orbit ( LLO) with 3 impulses was established. Then, a serial optimization method including the global traversal initial value search and the local gradient optimization was designed. A trans-lunar trajectory with the advantage of optimal fuel consumption departure from LEO through the stable manifold, Halo orbit near L2 of Earth-Moon, unstable mani-fold, and final arrival to LLO was obtained by optimization with the application of CR3BP. The reli-ability of the method was verified by the simulation data. The conclusions can serve as a reference for the design of the low-cost trans-lunar trajectory and the lunar landing based on the space station parking in Halo orbit near L2 of Earth-Moon in the future.