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Low energy trajectory optmization for CE-2'S extended mission after 2012
Li, Mingtao; Zheng, Jianhua
Department空间技术部
Source PublicationProceedings of the International Astronautical Congress, IAC
2012
Pages5692-5699
Language英语
ISSN0074-1795
ISBN9781622769797
AbstractCE-2, the second lunar satellite of China, has been the first satellite in the world to transfer from lunar polar orbit to the Sun-Earth L2 libration point. CE-2 will remain in the L2 Lissajous trajectory until the end of 2012, when about 120 m/s delta-v will be left. This paper studies trajectory optimization for CE-2's extended mission after 2012. The primary goal of this work is to design a suitable trajectory that maximizes science data return in different regions of the Sun-Earth-Moon system. The mission design should encompass as many regions as possible. Both the invariant manifolds of libration point and lunar gravity assist are used to design the low energy trajectories. A multiple regions exploration scenario including four main phases is proposed. First, the satellite follows the unstable manifolds to leave the Sun-Earth L2 Lissajous trajectory. After the first lunar flyby, the satellite enters into an Earth high elliptic orbit, from which geomagnetic tail and space environment could be studied. With another one or two lunar flyby, the spacecraft follows the stable manifolds to the Sun-Earth LI Halo orbit, from which solar physics could be studied. Finally, the spacecraft follows the unstable manifolds to leave the Sun-Earth LI Halo orbit, and fly towards the Sun- Earth L4 libration point. The spacecraft encounters an asteroid on the way to the L4 point. This paper also discusses the trajectory optimization for Chang'e 2's practical flight to the Toutatis asteroid, about 22 m/s delta-V is saved compared to the baseline trajectory. Hence the saved delta-V could be used for trajectory correction maneuvers to insure the probability of the successful asteroid flyby. This work demonstrates practical applications of advanced astrodynamic concepts in the Sun-Earth-Moon system, including chaotic three-body orbits, periodic three-body orbits, gravity assist, and the conic patched method. The result is a practical mission design of a grand tour for the Sun-Earth-Moon system using limited fuel resources. Copyright© (2012) by the International Astronautical Federation.; CE-2, the second lunar satellite of China, has been the first satellite in the world to transfer from lunar polar orbit to the Sun-Earth L2 libration point. CE-2 will remain in the L2 Lissajous trajectory until the end of 2012, when about 120 m/s delta-v will be left. This paper studies trajectory optimization for CE-2's extended mission after 2012. The primary goal of this work is to design a suitable trajectory that maximizes science data return in different regions of the Sun-Earth-Moon system. The mission design should encompass as many regions as possible. Both the invariant manifolds of libration point and lunar gravity assist are used to design the low energy trajectories. A multiple regions exploration scenario including four main phases is proposed. First, the satellite follows the unstable manifolds to leave the Sun-Earth L2 Lissajous trajectory. After the first lunar flyby, the satellite enters into an Earth high elliptic orbit, from which geomagnetic tail and space environment could be studied. With another one or two lunar flyby, the spacecraft follows the stable manifolds to the Sun-Earth LI Halo orbit, from which solar physics could be studied. Finally, the spacecraft follows the unstable manifolds to leave the Sun-Earth LI Halo orbit, and fly towards the Sun- Earth L4 libration point. The spacecraft encounters an asteroid on the way to the L4 point. This paper also discusses the trajectory optimization for Chang'e 2's practical flight to the Toutatis asteroid, about 22 m/s delta-V is saved compared to the baseline trajectory. Hence the saved delta-V could be used for trajectory correction maneuvers to insure the probability of the successful asteroid flyby. This work demonstrates practical applications of advanced astrodynamic concepts in the Sun-Earth-Moon system, including chaotic three-body orbits, periodic three-body orbits, gravity assist, and the conic patched method. The result is a practical mission design of a grand tour for the Sun-Earth-Moon system using limited fuel resources. Copyright© (2012) by the International Astronautical Federation.
Conference Name63rd International Astronautical Congress 2012, IAC 2012
Conference DateOctober 1, 2012 - October 5, 2012
Conference PlaceNaples, Italy
Indexed ByEI
Document Type会议论文
Identifierhttp://ir.nssc.ac.cn/handle/122/2946
Collection空间技术部
Recommended Citation
GB/T 7714
Li, Mingtao,Zheng, Jianhua. Low energy trajectory optmization for CE-2'S extended mission after 2012[C]:International Astronautical Federation, IAF, 94bis Avenue de Suffren, Paris, 75015, France,2012:5692-5699.
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