航天器工程2019，Vol.28Issue(1)：10-18,9.DOI:10.3969/j.issn.1673-8748.2019.01.002
探测器月地转移入射变轨策略优化设计
Optimization Design of Spacecraft Trans-earth Insertion Strategy
汪中生 1孟占峰 1高珊 1周文艳1
作者信息
- 1. 北京空间飞行器总体设计部,北京 100094
- 折叠
摘要
Abstract
In a typical lunar sample return mission,one-impulse or two-impulse strategy can be adopted for the trans-earth insertion maneuver.It is found in this study that the use of an engine with large magnitude thrust is necessary for one-impulse strategy,which however may lead to poor orbital control performance.It is proposed in the study that the one-impulse strategy be re-placed by a two-impulse strategy,with about one-day time difference between the execution times of the two maneuvers.The paper first addresses the basic design procedure of one-impulse strate-gy,then an optimization procedure is introduced for the design of two-impulse strategy,with nu-merical examples for the purpose of illustration.Also discussed in the paper are the design proce-dures of three-impulse trans-earth insertion strategy and low-energy moon-to-earth transfer tra-j ectory.Based on the comparison study of these strategies,the appropriate trans-earth insertion strategies are recommended for the lunar sample return missions.关键词
月球采样返回/月地转移入射变轨策略/优化设计Key words
lunar sample return/trans-earth insertion strategy/optimization design分类
航空航天引用本文复制引用
汪中生,孟占峰,高珊,周文艳..探测器月地转移入射变轨策略优化设计[J].航天器工程,2019,28(1):10-18,9.
