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Analysis of direct transfer trajectories from LL2 halo orbits to LLOs

机译：从LL2 Halo轨道直接转移轨迹对LLO的分析

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摘要

A convenient procedure for designing the direct transfer trajectory from lunar L2 point (LL2) halo orbit to a low lunar orbit (LLO) is presented in this paper. The trajectory characteristics are analyzed to support the manned lunar missions design aimed at lunar surface global access. The concise procedure is established based on the circular restricted three-body problem (CR3BP) model. An analytical algorithm is employed to estimate an initial maneuver vector for approaching the Moon in its close vicinity. An iteration process is adopted to generate favorable trajectory that satisfies the constraints at perilune. By introducing a number of intermediate coordinate frames, an algorithm to compute the arriving LLO inclination and right ascension of ascending node (RAAN) is proposed. The orbital inclination and RAAN in this paper are defined and established in the J2000 frame rather than in the synodical frame. Numerical results show that, regardless of value of out-of-plane amplitude (Az) of the halo orbit, the overall maneuver cost of the trajectory largely depends on departure position, and it has two minima around 0.65 km/s. Further study shows that the values of the arriving LLO inclination and RAAN largely depend on the choices of the departure time and the value of Az. The periodicity, due to the natural motion of the Moon, is discovered to play a role in this time dependency. It is concluded that the fuel optimal trajectory permits access to almost any final lunar orbit, including a polar orbit, by means of varying the departure time and Az value.
机译：本文提出了一种从月球L2点（LL2）HALO轨道的直接传输轨迹的方便步骤，本文介绍了低月球轨道（LLO）。分析轨迹特性以支持旨在瞄准月球表面全球访问的人工农历任务设计。简明的程序是基于循环限制的三体问题（CR3BP）模型建立的。采用分析算法来估计其近距离接近月亮的初始操纵载体。采用迭代过程来产生良好的轨迹，满足Perilune的约束。通过引入多个中间坐标帧，提出了计算到达的LLO倾斜度和右提升的升序节点（RAAN）的算法。本文中的轨道倾斜和拉南在J2000帧中定义和建立，而不是在揭示帧中。数值结果表明，无论光环轨道的平面外振幅（AZ）的值如何，轨迹的整体机动成本在很大程度上取决于出发位置，它有两项最小值约为0.65公里/秒。进一步的研究表明，到达LLO倾斜度和拉南的价值主要取决于出发时间的选择和AZ的价值。由于月球的自然运动，在这个时代依赖中发挥作用的周期性。得出结论，燃料最佳轨迹允许通过不同的出发时间和AZ值来访问几乎任何最终月球轨道，包括极性轨道，包括极性轨道。

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