中国空间科学技术

中国空间科学技术 ›› 2026, Vol. 46 ›› Issue (2): 108-117.doi: 10.16708/j.cnki.1000-758X.2026.0029

• 载人月球探测专刊 • 上一篇    下一篇

载人登月应急返回轨道特性与再入区域研究

王海了1,3，徐明1,2,3,*，曾豪4，田林4，彭祺擘5   

  1. 1.北京航空航天大学宇航学院, 北京100191
    2.北京航空航天大学沈元学院, 北京100191
    3.航天器设计优化与动态模拟技术教育部重点实验室, 北京100191
    4.北京空间飞行器总体设计部, 北京100094
    5.中国航天员科研训练中心, 北京100094
  • 收稿日期:2025-09-18 修回日期:2025-10-01 录用日期:2025-11-04 发布日期:2026-03-20 出版日期:2026-03-31

Investigation of emergency return trajectory characteristics and reentry areas in crewed lunar landing missions

WANG Hailiao1,3，XU Ming1,2,3*，ZENG Hao4，TIAN Lin4，PENG Qibo5   

  1. 1.School of Astronautics, Beihang University, Beijing 100191, China
    2.Shen Yuan Honors College, Beihang University, Beijing 100191, China
    3.Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technology, Ministry of Education, 
    Beijing 100191, China
    4.Beijing Institute of Spacecraft System Engineering, Beijing 100094, China
    5.China Astronaut Research and Training Center, Beijing 100094, China
  • Received:2025-09-18 Revision received:2025-10-01 Accepted:2025-11-04 Online:2026-03-20 Published:2026-03-31

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摘要： 载人登月任务与传统月球探测任务的重要区别之一是要全程保障航天员的人身安全。如果在绕月飞行期间发生意外，需要具备能够满足再入与落点约束的应急返回能力，这构成一个复杂的月地转移轨道设计问题。利用一种结合参数化方法与Quasi-Lambert问题求解的轨道设计方法，对考虑再入和落点约束的月地返回轨道的返回族特性与再入区域进行了系统研究。该方法能够在绕月飞行过程的任意时刻，参数化生成针对地球指定目标落点的月地转移脉冲逃逸轨道。在此基础上，针对不同转移时间，对轨道族的速度增量需求与地球可达落点区域进行了系统计算与分析，并结合不同月相条件下的赤纬变化规律，评估了轨道的可行性与落点分布特征。结果表明，对于2d、3d和5d转移时间的轨道族，所需速度增量分布与地球自转及月相演化存在显著的短周期与长周期耦合震荡特性。进一步地，在不同月相赤纬条件下，地球可行落点的分布存在明显差异，为确保任意时刻均具备应急返回能力，目标落点纬度应控制在北纬20°以下；若需实现更高纬度落点，则必须要求应急时刻的月相赤纬处于特定范围内。

关键词: 月地转移轨道, 应急返回轨道, 载人登月任务, 再入落点分析, Quasi-Lambert问题

Abstract: One of the key distinctions between a crewed lunar mission and traditional lunar exploration missions lies in the requirement to ensure astronaut safety throughout the mission. In the event of an emergency during lunar orbitoperations, it is essential to possess a return capability that satisfies both reentry and landing constraints, which constitutes a complex Earth-Moon transfer trajectory design problem. This study employs a trajectory design method that combines a parametric approach with the solution of the Quasi-Lambert problem to systematically investigate the family characteristics and reentry regions of Earth-Moon return trajectories under such constraints. The proposed method enables the parametric generation of impulsive escape trajectories from lunar orbit at any epoch, targeting designated landing sites on Earth. On this basis, the velocity increment requirements and reachable landing regions associated with trajectory families of different transfer times are computed and analyzed. Furthermore, the feasibility and distribution characteristics of the landing sites are assessed by incorporating the declination variation patterns under different lunar phase conditions. Results demonstrate that for trajectory families with transfer times of 2, 3, and 5 days, the required velocity increments exhibit pronounced short-period and long-period coupled oscillations influenced by Earth's rotation and lunar phase evolution. Moreover, under different lunar phase declination conditions, the distribution of feasible Earth landing sites shows significant variation. To ensure emergency return capability at any epoch, the target landing site latitude should be restricted to below 20° N. If higher-latitude landing sites are desired, the lunar phase declination at the emergency epoch must fall within specific ranges.

Key words: Earth-Moon transfer trajectory, emergency return trajectory, crewed lunar mission, reentry landing analysis, Quasi-Lambert problem