航空学报 > 2014, Vol. 35 Issue (8): 2243-2250   doi: 10.7527/S1000-6893.2014.0085

直接再入大气的月地返回窗口搜索策略

郑爱武1,2, 周建平3   

  1. 1. 航天飞行动力学技术重点实验室, 北京 100094;
    2. 北京航天飞行控制中心, 北京 100094;
    3. 北京航空航天大学 宇航学院, 北京 100191
  • 收稿日期:2013-09-21 修回日期:2014-05-03 出版日期:2014-08-25 发布日期:2014-05-16
  • 通讯作者: 郑爱武,Tel.:010-66362455-602,E-mail:awzheng@163.com E-mail:awzheng@163.com
  • 作者简介:郑爱武女,博士,高级工程师。主要研究方向:航天测控任务分析总体、轨道设计和精密定轨。Tel:010-66362455-602,E-mail:awzheng@163.com;周建平男,博士,中国工程院院士,博士生导师。主要研究方向:载人航天总体。
  • 基金资助:

    国家自然科学基金(11173005,11203003)

A Search Strategy of Back Windows for Moon-to-Earth Trajectories Directly Returning to the Earth

ZHENG Aiwu1,2, ZHOU Jianping3   

  1. 1. Science and Technology on Aerospace Flight Dynamics Laboratory, Beijing 100094, China;
    2. Beijing Aerospace Control Center, Beijing 100094, China;
    3. School of Astronautics, Beihang University, Beijing 100191, China
  • Received:2013-09-21 Revised:2014-05-03 Online:2014-08-25 Published:2014-05-16
  • Supported by:

    National Natural Science Foundation of China (11173005, 11203003)

摘要:

结合从月球停泊轨道直接返回地球的月地转移轨道设计,提出了一种月地返回窗口的搜索策略。首先基于双二体模型,结合月地转移轨道快速设计进行当天最小再入角的计算,根据当天最小再入角的计算结果初步判断返回窗口,然后指定再入角约束,在初步返回窗口内搜索满足两端约束条件的双二体月地转移轨道。然后将该轨道作为初值,基于受摄双二体模型,采用数值积分和微分改正法进一步求解精确的月地转移轨道。最后根据精确轨道计算结果,特别是速度增量,进一步确定返回窗口。这种策略大大加快了计算返回窗口的效率,可以在大范围内快速搜索返回窗口。通过对2017年1月和2月返回窗口的搜索及对结果的分析,最终给出了满足最省燃料和3天连续返回的窗口建议。

关键词: 月地转移轨道, 轨道设计, 轨道转移, 受摄双二体模型, 数值积分, 微分改正

Abstract:

Based on the design of Moon-to-Earth trajectories which directly return to the Earth from the Moon parking orbit, a search strategy for back windows is presented. First, combined with the rapid design of Moon-to-Earth transfer trajectories based on double two-body model, an initial back window is primarily estimated according to minimum reentry angle calculations at that day. If the minimum reentry angle is within the reentry corridor, then the double two-body trajectory which meets the constraints at both ends is searched with the prescribed reentry angle constraint. The results are used as initial values for subsequent precise design of Moon-to-Earth transfer trajectories based on perturbed models. The precise trajectory is obtained by using numerical integration and differential correction. The back window is further determined by the results of the precise trajectories, especially the velocity increment. This strategy greatly accelerates the computational efficiency of the back window, and the window can be quickly found in a wide range. Through the search and results analysis of back windows in January and February 2017, a feasible back window which satisfies fuel-optimal and three consecutive return possibilities is finally proposed.

Key words: Moon-to-Earth trajectories, trajectory design, orbital transfer, perturbed double two-body model, numerical integration, differential correction

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