Design and analysis of a direct transfer trajectory from a near rectilinear halo orbit to a low lunar orbit |
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Authors: | Lin Lu Haiyang Li Wanmeng Zhou Jianghui Liu |
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Affiliation: | 1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;2. China Astronaut Research and Training Center, Beijing 100094, China;3. The PLA Unit 91395, Beijing 102443, China |
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Abstract: | A near rectilinear halo orbit (NRHO) is regarded as a potential orbit for a future deep space station that can effectively support sustainable crewed lunar exploration missions. In this paper, the L2 southern NRHOs are selected as the research object, and a direct transfer trajectory from an NRHO to a low lunar orbit (LLO) is designed and analyzed. First, based on the circular restricted three-body problem, the characteristics of NRHOs are discussed including geometric behaviour, stability and synodic resonance. Second, optimal direct transfer trajectories are obtained by combining a local gradient optimization with a numerical continuation strategy. A reachable domain calculation model is established. Finally, simulations are carried out to verify the feasibility of the trajectory design method. The relationship between the velocity change and the reachable domain is further analysed through simulation calculations. |
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Keywords: | Near rectilinear halo orbit Circular restricted three-body problem Optimal direct transfer trajectory Reachable domain calculation |
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