The embodiment of the invention discloses a method and device for initially arranging an orbit to a circular orbit of a full-electric propulsion moonlet and a medium. The method can comprise the following steps: calculating through a Gaussian perturbation equation to obtain a control thrust angle required for keeping the height of an apogee unchanged and lifting the height of a perigee when a satellite is in an initial elliptical orbit; on the basis of a symmetric propulsion strategy nearby an apogee, working starting and ending moments of each orbit are calculated according to the working duration of each orbit of an electric propulsion engine of the satellite; and obtaining the perigee height increment lifted by each orbit of the satellite according to the thrust acceleration determined by the control thrust angle until the satellite reaches the target orbit height.

    本发明实施例公开了一种全电推进小卫星初始布轨至圆轨道的方法、装置及介质;该方法可以包括:通过高斯摄动方程计算获取卫星处于初始椭圆轨道时用于保持远地点高度不变且抬升近地点高度所需的控制推力角;基于远地点附近对称推进策略,根据卫星的电推进发动机的每轨工作时长计算每轨的工作起止时刻;根据所述控制推力角所确定的推力加速度获取卫星的每轨所抬升的近地点高度增量,直至卫星达到目标轨道高度。


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    Title :

    Method and device for initially distributing orbit to circular orbit of all-electric propulsion moonlet and medium


    Additional title:

    全电推进小卫星初始布轨至圆轨道的方法、装置及介质


    Contributors:
    WU FAN (author) / XU LONGWEI (author) / CAO XIBIN (author) / WANG FENG (author) / CHEN JIAN (author) / QIU SHI (author) / GUO JINSHENG (author) / XI RUICHEN (author)

    Publication date :

    2022-04-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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