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中文摘要：
对环月轨道共面交会的载人登月任务中,着陆器（LM）奔月零窗口与轨道参数精确快速设计方法进行了研究。任务采用人货分离奔月模式,着陆器于载人飞船到达环月轨道前抵达环月共面交会轨道,着陆器近月点一次共面减速完成近月制动。提出一种三层快速精确奔月窗口搜索方法：第一层采用地心二体轨道理论解析计算月窗口及奔月轨道参数初值,作为正确性基本参考;第二层采用改进的双二体解析动力学模型求解月窗口内奔月轨道参数变化规律;第三层采用高精度轨道动力学模型和SQP_Snopt优化求解奔月零窗口及轨道参数精确解。仿真结果表明,本文提出的三层逐级奔月窗口搜索方法能快速精确求解载人登月任务中着陆器奔月窗口及精确轨道参数,也揭示了影响着陆器奔月窗口的主次因素和规律,为中国未来载人登月工程提供参考。
英文摘要：
An accurate and rapid approach to lunar module （LM） trans-lunar injection （TLI） window and orbit parameter design is derived for manned lunar landing mission based on low lunar orbit coplanar rendezvous and docking （RVD）. The pattern that astronauts are separated from cargo is adopted. LM arrives at the lunar coplanar RVD orbit earlier than the crew exploration vehicle （CEV）. LM completes the braking on the LLO RVD plane with only one impulse at perilune. A strategy of three-level cascade searching for LM TLI windows is proposed. The month window and orbital initial parameters of TLI are obtained in the first level. Further initial solution for month window and orbital parameters are obtained with an improved double two-body analytic model in the second level. The high precision dynamics solution for zero window and orbital parameters are optimized by SQP_Snopt algorithm. Simulation results show that the rapid and accurate three-level cascade searching approach for LM TLI windows and orbital parameters is effective for manned lunar landing mission. The influential factors and fundamental patterns of TLI window are revealed to supply references to China＇s manned lunar landing mission in the future.
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