The invention provides an MEO constellation phase control method. The method comprises the following steps: 1 inputting historical phase difference data of a satellite to be controlled and a referencesatellite, and determining a phase difference; 2 establishing and determining a relationship between the phase difference of the satellite to be controlled and the reference satellite; 3 determininga semi-major axis deviation between the satellite to be controlled and the reference satellite; and 4 determining semi-major axis control quantity of the to-be-controlled satellite. According to the method, the MEO constellation historical phase information is utilized to establish a phase evolution model, a MEO constellation phase control strategy based on the historical phase is provided, the phase control strategy is determined through the historical phase data evolution law, and errors caused by initial orbit and forecast are avoided.

    本发明提供一种MEO星座相位控制方法,包括步骤一:输入需控制卫星与基准星历史相位差数据,确定相位差,步骤二:建立并确定需控制卫星与基准星相位差的关系,步骤三:确定需控制卫星与基准星半长轴偏差,步骤四:确定需控制卫星半长轴控制量,本发明利用MEO星座历史相位信息,建立相位演化模型,提出了一种基于历史相位的MEO星座相位控制策略,通过历史相位数据演化规律确定相位控制策略,该方法避免了初始轨道及预报带来的误差。


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    Title :

    MEO constellation phase control method


    Additional title:

    一种MEO星座相位控制方法


    Contributors:
    LI QUANJUN (author) / TIAN XIN (author) / WANG JIANWEI (author) / DUAN YUXING (author) / ZHANG YING (author) / KONG DALIN (author) / SHI LEI (author)

    Publication date :

    2021-01-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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