CHANG'E-2 lunar escape maneuvers to the Sun–Earth L2 libration point mission |
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| Institution: | 1. Science and Technology on Aerospace Flight Dynamics Laboratory, Beijing 100094, China;2. Beijing Aerospace Control Center, Beijing 100094, China;1. University of Basilicata, School of Engineering, 10, Ateneo Lucano Street, 85100 Potenza, Italy;2. National Research Council, Institute of Methodologies for Environmental Analysis (IMAA), c/da S.Loja, 85050 Tito Scalo (PZ), Italy;1. Solar System Missions Division, ESA/ESTEC, Noordwijk, Netherlands;2. Office for Support to New Member States, ESA/ESTEC, Netherlands;3. Science Payload Instrument Section, ESA/ESTEC, Netherlands;1. Institute of Space and Astronautical Science, Sagamihara, Kanagawa 252 5210, Japan;2. Planetary Exploration Research Center, Chiba Institute of Technology, Chiba, Japan;3. Hokkaido University, Hokkaido, Japan;4. Senshu University, Tokyo, Japan;5. University of Tokyo, Tokyo, Japan;7. Okayama University, Okayama, Japan;1. Institute of Solar-Terrestrial Physics SB RAS, Irkutsk, Russia;2. Research Centre for Astrophysics and Geophysics MAS, Ulaanbaatar, Mongolia;3. Irkutsk State Technical University, Irkutsk, Russia |
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| Abstract: | This paper addresses lunar escape maneuvers of the first Chinese Sun–Earth L2 libration point mission by the CHANG'E-2 satellite, which is also the world's first satellite to reach the L2 point from a lunar orbit. The lunar escape maneuvers are heavily constrained by the remaining propellant and the condition of telemetry, track and command, among others. First, these constraints are analyzed and summarized to design a target L2 Lissajous orbit and an initial transfer trajectory. Second, the maneuver mathematical models are studied. The multilevel maneuver schemes which consist of phasing maneuvers and a final lunar escape maneuver are designed for actual operations. Based on the scheme analysis and comparison, the 2-maneuver scheme with a 5.3-h-period phasing orbit is ultimately selected. Finally, the mission status based on the scheme is presented and the control operation results are discussed in detail. The methodology in this paper is especially beneficial and applicable to a future multi-mission instance in the deep space exploration. |
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| Keywords: | CHANG'E-2 Lunar escape maneuver Sun–Earth libration point Lissajous orbit |
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