载人登月应急返回轨道倾角优化设计

Optimization design of inclination orbit of human lunar landing emergency return trajectory

针对载人登月短期全球访问任务,月面上升过程存在上升舱与返回舱异面交会问题。以减小调面机动燃料消耗为目标,利用三垂线定理给出上升轨道与目标轨道的最小平面夹角(楔角)求解公式,考虑应急返回任务需求,以降低整个任务期间最坏的平面夹角为目标,给出全月面到达着陆轨道与上升轨道倾角求解方法。仿真结果表明,所提方法计算简单,精度高,可为载人登月任务设计和分析提供参考。

For missions of short-term visits to the moon,the lunar ascent stage requires the ascending module to Rendezvous and dock interface with the cabin in non-coplanarity.A solution to solve for the change of the angle of ascent plane（referred to as wedge angle）was proposed,and wedge angle of the ascending orbit was given by using the three-line theorem to reduce the demand of the emergency return task to reduce the worst plane of the whole mission period.The method of solving the inclination of the landing track and the ascending orbit was given.The simulation results show that the proposed method is simple and accurate,providing reference for the design and analysis of human lunar landing.