直接再入大气的月球返回轨道设计研究  

Design of Moon Return Trajectory with Direct Atmospheric Reentry

作　　者：张磊[1] 于登云[2] 张熇[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]中国航天科技集团公司,北京100048

出　　处：《航天器工程》2010年第5期50-55,共6页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：直接再入大气的月球返回轨道是月球采样返回任务普遍采用的飞行方案。文章将月-地转移轨道设计与再入大气仿真相结合,通过两级修正策略和落点匹配使月球返回轨道既满足再入界面约束又满足再入点地理位置约束。两条分别采用弹道式和弹道-升力式再入的月球返回轨道的计算结果表明,此方法是有效的。The moon-return trajectory with direct atmospheric reentry is widely adopted in the moon sampling missions. The simulation of atmosphere reentry is integrated with the design of moon-to-earth transfer trajectory. The two-stage correction strategy and the landing-point match method are researched and used in the design process of moon return trajectories which accords with both reentry interface and landing-point location constrains. Two examples validate the effectiveness of the proposed approach.

关 键 词：月球采样返回 轨道设计 月地转移 再入大气 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]