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针对意义重大但目前尚无成功先例的月球背面载人登月任务,通过建立地惯系三体动力学模型,采用微分修正法迭代计算,设计了未来载人登月任务的候选自由返回轨道;通过建立旋转系三体动力学模型,利用“类Halo轨道截面”法,得到了从自由返回轨道以最低能耗转移到L2点halo轨道的拼接轨道。仿真计算结果显示所优化设计的搭载中继星的载人自由返回探月轨道既能满足任务安全要求,又能以最小能耗布设中继星座并提供中继任务支持。设计方法和结果可对未来月球背面载人着陆探测任务安全轨道设计和月球中继星座的设计方面提供参考。
Aiming at the task of lunar lunar manned lunar landing, which is of great importance but no successful precedent at present, to set up the terrestrial dynamical three - body dynamical model and adopt the iterative method of differential correction to design the candidate free returning orbit for the future manned lunar mission. By establishing the three-body dynamical model of the rotating system and using the “Halo orbital section method”, the spliced orbit with the minimum energy consumption transferred from the free return orbit to the halo of point L2 is obtained. The simulation results show that the optimally designed manned free return lunar orbit with relay star can meet the mission safety requirements and deploy the relay constellation and provide the relay mission support with minimum energy consumption. The design method and results can provide references for the design of the safety trajectory of the lunar back-manned manned landing mission and the design of the lunar relay constellation.