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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。
In the manned lunar orbit lunar orbit coplanar rendezvous mission, the lander (LM) to the moon zero window and the orbit parameters accurate and rapid design method were studied. The task of separation of people and goods to the moon mode, the lander arrived in lunar orbit before the manned spacecraft arrived at the lunar January coplanar orbit, the lander at a point in recent months to achieve deceleration in recent months braking in recent months. A fast and accurate three-storied Moon window searching method is proposed. The first layer uses the geocentric two-body orbit theory to analyze and calculate the initial values of the lunar window and lunar orbit parameters as the basic reference of correctness. The second layer adopts the improved double body The kinetic model was used to solve the variation of lunar orbit parameters in the lunar window. The third layer was solved by using the high precision orbit dynamics model and SQP_Snopt optimization solution to the lunar zero window and the orbital parameters. The simulation results show that the proposed three-level step-by-step window search method can quickly and accurately solve the lunar window and exact orbit parameters of manned lunar missions, and reveal the primary and secondary factors that affect the lander’s going to the moon window Law, provide a reference for China’s future manned lunar landing project.