地月L2点Halo轨道支持的登月轨道优化设计

Trans-lunar Trajectory Optimization Based on Earth-Moon L2 Halo Orbits

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 optimization was discussed. Firstly,a mathematical model of trans-lunar trajectory based on invariant manifold 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 manifold,and final arrival to LLO was obtained by optimization with the application of CR3 BP. The reliability 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.