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.

    Highlights CHANG'E-2 is 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. A maneuver scheme with a 5.3-h-period phasing orbit is selected to escape the Moon. The whole delta-V is far below that can be provided by the remaining propellant. The maneuver scheme is appropriate and efficient, and the operation is successful.


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    Title :

    CHANG'E-2 lunar escape maneuvers to the Sun–Earth L2 libration point mission


    Contributors:
    Liu, Lei (author) / Liu, Yong (author) / Cao, Jianfeng (author) / Hu, Songjie (author) / Tang, Geshi (author) / Xie, Jianfeng (author)

    Published in:

    Acta Astronautica ; 93 ; 390-399


    Publication date :

    2013-07-23


    Size :

    10 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English