| 日-地系拉格朗日点任务及其转移轨道设计方法 |
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| 引用本文： | 刘建忠.日-地系拉格朗日点任务及其转移轨道设计方法[J].导弹与航天运载技术,2009(1). |
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| 作者姓名： | 刘建忠 |
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| 作者单位： | 北京宇航系统工程研究所,北京,100076 |
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| 摘 要： | 绕日-地系拉格朗日点的深空探测任务越来越多,这些任务的目标轨道一般为Halo轨道或Lissajous轨道.介绍了3种从地球停泊轨道出发到拉格朗日点的转移轨道设计方法,并进行了对比.最后以Az=-800 000 km的Halo轨道为例,验证了直接转移轨道设计方法的有效性.
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| 关 键 词： | 日地系统 拉格朗日点 转移轨道 Halo轨道 Lissajous轨道 |
Missions of Sun-Earth Lagrange Points and Design Method of Transfer Trajectory |
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| Liu Jianzhong.Missions of Sun-Earth Lagrange Points and Design Method of Transfer Trajectory[J].Missiles and Space Vehicles,2009(1). |
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| Authors: | Liu Jianzhong |
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| Affiliation: | Beijing Institute of Space System Engineering;Beijing;100076 |
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| Abstract: | Missions of deep-space exploration surrounding Sun-Earth Lagrange points are increasing.Target orbits of these missions are generally the Halo orbit or the Lissajous orbit.Three methods of transfer trajectory design between parking orbit and Lagrange points are introduced and compared.The Halo orbit of Az=-800 000 km is used as an example to verify the validity of direct transfer orbit design. |
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| Keywords: | Sun-earth system Lagrange points Transfer trajectory Halo orbit Lissajous orbit |
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