中国空间科学技术

中国空间科学技术 ›› 2021, Vol. 41 ›› Issue (3): 9-15.doi: 10.16708/j.cnki.1000.758X.2021.0032

• 研究探讨 • 上一篇    下一篇

部署retro-GEO巡视器的月球借力飞行轨道分析

贺波勇1,2,*，马鹏斌1，杜卫兵1，李恒年1   

  1. 1 西安卫星测控中心 宇航动力学国家重点实验室，西安710043
    2 西北工业大学 航天学院，西安710072
  • 收稿日期:2020-08-06 修回日期:2020-09-08 接受日期:2020-12-30 出版日期:2021-06-25 发布日期:2021-06-25
  • 通讯作者: Email: heboyong@yeah.net E-mail:heboyong@yeah.net
  • 作者简介:贺波勇（1989- ），男，助理研究员，博士后，研究方向为航天轨道动力学与空间安全, heboyong@yeah.net。
  • 基金资助:
    国家自然科学基金（11902362）;全军博士后资助项目（JB2020194）

Transfers analysis of deploying a retrograde GEO monitorsatellite by Moon swing-by

HE Boyong1,2,*，MA Pengbin1，DU Weibing1，LI Hengnian1   

  1. 1 State Key Laboratory of Astronautic Dynamics, Xi′an Satellite Control Center，Xi′an 710043,China
    2 School of Astronautics，Northwestern Polytechnical University，Xi′an 710072，China
  • Received:2020-08-06 Revised:2020-09-08 Accepted:2020-12-30 Published:2021-06-25 Online:2021-06-25
  • Contact: Email: heboyong@yeah.net E-mail:heboyong@yeah.net

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摘要： retro-GEO是指逆行（retrograde）地球静止轨道（geostationary Earth orbit, GEO），该轨道与GEO轨道高度相同或相近，但倾角为180°，安装在retro-GEO卫星上的巡视器可每12h对GEO带空间资产附近碎片环境安全预警。直接西向发射retro-GEO卫星存在地面测控和发射能耗较大的困难。基于平面四体模型，为降低设计变量敏感性，以近月点参数为设计变量，建立了部署retro-GEO巡视器的月球借力飞行轨道设计模型，利用轨道动力学模型延拓策略，得到该类轨道绕月后返回地球飞行时长只能约为114.79h，该结论可用于求解该类轨道高精度轨道动力学模型解。

关键词: 逆行GEO, 碎片预警, 轨道设计, 月球甩摆, 模型延拓

Abstract: Retro-GEO refers to the retrograde geostationary Earth orbit (GEO), which has the same or similar height as that of the GEO, but with an inclination of 180 °. A monitorsatellite on retroGEO can give early debris warning for the GEO assets every 12 hours. RetroGEO launched directly in the westward has great difficulties in ground tracking and control, as well as launch energy cost. Based on a four body model, and in order to reduce the sensitivity of design variables, a transfer to retro-GEO design model by the Moon swing by was proposed applying the trans-lunar orbital elements at the moment of perilune. The result obtanined by using orbital dynamics model continuation shows a natural property of such orbits, that is the return duration from perilune must be about 114.79 hours. The conclusion can be used to solve this kind of orbit with a high precision orbital dynamics model.

Key words: retrograde GEO, debris warning, orbit design, Moon swingby, model continuation

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