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Lunar exploration phase Ⅲ: Launch window and trajectory design for a lunar lander

机译：月球探索阶段Ⅲ：月球着陆器的发射窗口和轨迹设计

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摘要

The lunar exploration phase Ⅲ mission is a part of the China Aerospace Science and Technology Corporation's lunar exploration program that will perform a soft-landing and sample return from the Moon to test the key technologies that are required for human lunar missions. This paper focuses primarily on the trajectory design and orbital launch window generation for a lunar probe that are consistent with the constraints imposed by third phase of lunar exploration. Two categories of trajectories are explored: Earth-to-Moon and Moon-to-Earth. With the patched conic technique, the analytical and modified analytical models of the transfer trajectories are developed. The requirement of high-latitude landing for the return phase trajectory is considered in the modified model. By varying the initial input conditions and with a fast convergence iteration scheme, different characteristics of the transfer trajectory are generated. The orbital launch windows are established to study the mission sensitivities to time and fuel consumption and to provide a launch timetable that is compatible with this mission's requirements. The lunar surface stay time is analyzed for different conditions. The high-fidelity gravitational model is introduced to demonstrate the accuracy and convergence behavior of the analytical solution. The design method can also be used as a ba.sis for the future human lunar missions.
机译：月球探索三期任务是中国航天科技公司月球探索计划的一部分，该计划将进行月球软着陆并从月球返回样品，以测试人类登月任务所需的关键技术。本文主要关注月球探测器的轨迹设计和轨道发射窗口的产生，这与月球探测第三阶段所施加的约束是一致的。探索了两类轨迹：地对月和月对地。利用贴片圆锥技术，建立了转移轨迹的解析模型和修正解析模型。在修正模型中考虑了高纬度着陆对返回相轨迹的要求。通过改变初始输入条件并采用快速收敛迭代方案，可以生成转移轨迹的不同特性。建立轨道发射窗口的目的是研究任务对时间和燃料消耗的敏感性，并提供与该任务要求兼容的发射时间表。分析不同条件下的月球表面停留时间。介绍了高保真引力模型，以证明解析解的准确性和收敛性。该设计方法还可以用作未来人类登月任务的基础。

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