| 日地平动点卫星两脉冲转移轨道设计 |
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| 引用本文： | 李明涛,郑建华,于锡峥,高东.日地平动点卫星两脉冲转移轨道设计[J].北京航空航天大学学报,2009,35(7):865-868. |
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| 作者姓名： | 李明涛 郑建华 于锡峥 高东 |
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| 作者单位： | 中国科学院,空间科学与应用研究中心,北京,100190;中国科学院,空间科学与应用研究中心,北京,100190;中国科学院,空间科学与应用研究中心,北京,100190;中国科学院,空间科学与应用研究中心,北京,100190 |
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| 摘 要： | 研究基于最小二乘微分修正方法的平动点卫星两脉冲转移轨道设计,推导了考虑高度和航迹角约束的微分修正公式,讨论了该方法的收敛性.以日地L1点附近的Halo轨道为目标轨道,在圆型限制性三体问题模型下设计了其转移轨道,系统地研究了HOI(Halo Orbit Insertion)点和Halo轨道幅值对转移轨道的影响,给出了HOI点的选择策略,并讨论了应急情况下快速转移轨道设计.数值仿真验证了方法的有效性,选择Halo轨道靠近地球侧的点作HOI点可以获得飞行时间适中的转移轨道.
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| 关 键 词： | Halo轨道 转移轨道 微分修正 不变流形 |
| 收稿时间： | 2008-06-03 |
Two impulses transfer trajectory design for Sun-Earth libration point missions |
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| Li Mingtao,Zheng Jianhua,Yu Xizheng,Gao Dong.Two impulses transfer trajectory design for Sun-Earth libration point missions[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(7):865-868. |
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| Authors: | Li Mingtao Zheng Jianhua Yu Xizheng Gao Dong |
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| Institution: | Center for Space Science and Applied Research, Chinese Academy of Sciences, Beijing 100190, China |
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| Abstract: | Two impulses transfer trajectory design based on the least differential corrections method was studied,differential correction equation with the altitude and the flight path angle constraints was concluded,and the convergence of the method was discussed.Halo orbit around the L1 libration point of the Sun-Earth system was taken as the objective orbit,two impulses transfer trajectory was designed in the framework of the circular restricted three-body problem.Effect of Halo orbit insertion(HOI) point and ampli... |
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| Keywords: | Halo orbit transfer trajectory differential correction invariant manifold |
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