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Designing of the Optimal Energy Escaping Orbit from Moon L2 Point in Elliptical Three-body Problem
Received date: 2013-07-25
Revised date: 2013-10-17
Online published: 2013-11-22
Supported by
National Nature Science Foundation of China (11172077); Innovative Team Program of the National Nature Science Foundation of China (61321062)
To solve the problem that it is hard to save energy by making full use of the elliptical orbit dynamics of the Earth-Moon system in the escaping orbit design of a moon probe under a circular restricted three-body environment, a dynamic model is extended to an elliptical three-body model for which the dynamic equation and the orbit energy is given. The relationship between the orbit energy of the probe and the Moon's phase is constructed by deriving the variation of the orbit energy during the escaping process. It is found that from the same original cislunar orbit, the launching energy will change mainly with the distance between the Earth and the Moon while the energy variation during the escaping process is closely related with the Earth-Moon relative speed. Then it is concluded that the optimal escaping orbit exists when the Moon comes close to its perigee. To design the optimal escaping orbit the Poincare section method is introduced. By solving the relationship between the Moon's phase and the corresponding energy need for escaping, the optimal solution is given with iteration. From the simulation it is found that when the Moon's true anomaly reaches 283°, up to 8% of energy can be saved with the elliptical three body model as compared with the circular restricted three-body model, which is in good agreement with the theoretical results, and the advantage is obvious.
JING Wuxing , LIU Yue . Designing of the Optimal Energy Escaping Orbit from Moon L2 Point in Elliptical Three-body Problem[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014 , 35(6) : 1496 -1504 . DOI: 10.7527/S1000-6893.2013.0433
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