| 全星历模型下拟Halo轨道设计 |
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| 作者姓名： | 杨洪伟 李京阳 宝音贺西 |
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| 作者单位： | 清华大学航天航空学院, 北京 100084,清华大学航天航空学院, 北京 100084,清华大学航天航空学院, 北京 100084 |
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| 摘 要： | 本文给出了全星历模型下适用于地月系统和日地系统的拟Halo轨道的设计方法。设计过程以限制三体模型下Halo轨道作为初值并以多点并行打靶法求解全星历模型下拟Halo轨道。采用多点并行打靶法中给出了一类新的可行约束条件,在数值仿真算例中,地月和日地系统L2点附近4圈目标拟Halo轨道均在分钟量级时间内收敛,表明了算法的有效性。
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| 关 键 词： | 全星历模型 打靶法 Halo轨道 轨道设计 |
| 收稿时间： | 2015/9/28 0:00:00 |
| 修稿时间： | 2015/10/17 0:00:00 |
Quasi Halo Orbit Design in Full Ephemeris Model |
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| Authors: | YANG Hongwei LI Jingyang and BAOYIN Hexi |
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| Institution: | School of Aerospace Engineering, Tsinghua University, Beijing 100084, China,School of Aerospace Engineering, Tsinghua University, Beijing 100084, China and School of Aerospace Engineering, Tsinghua University, Beijing 100084, China |
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| Abstract: | A method of designing the quasi Halo orbits in the full ephemeris model, which can be applied in both the earth-moon system and sun-earth system, is presented. In the design process, a Halo orbit designed in the restricted three-body model is taken as initial guess, and then a multiple shooting method is used to design in the full ephemeris model. A new feasible constraint condition is given. By numerical simulations, the quasi Halo orbits with four circles are both obtained about one minute for the earth-moon system and sun-earth system respectively, showing the effectiveness of the present algorithm. |
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| Keywords: | full ephemeris model shooting method Halo orbit orbit design |
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