The embodiment of the invention discloses a near-circular orbit satellite electric propulsion orbit injection method which comprises the following steps: in an orbit period, removing satellite attitude adjustment time, and obtaining time of single thrust applied to a satellite and a finite thrust coefficient; according to the initial values of the semi-major axis, the eccentricity rate and the perigee argument of the satellite orbit and the target values of the semi-major axis, the eccentricity rate and the perigee argument, calculating a semi-major axis variation and an eccentricity rate vector variation; the total speed increment of the first group of tangential thrust and the second group of tangential thrust and the latitude argument of the midpoint of the arc section applied by the first group of tangential thrust and the second group of tangential thrust are calculated according to the semi-major axis variation and the eccentricity rate vector variation; according to the total speed increment of the first group of tangential thrust and the second group of tangential thrust and the latitude argument of the midpoint of the arc section applied by the first group of tangential thrust and the second group of tangential thrust, the starting latitude argument and the shutdown latitude argument of the first group of tangential thrust and the second group of tangential thrust are obtained through calculation; and calculating the starting times of the first group of tangential thrust and the second group of tangential thrust, and selecting a satellite electric propulsion orbit maneuvering injection execution strategy.

    本发明实施例公开一种近圆轨道卫星电推进入轨方法,包括:在一个轨道周期内,去除卫星姿态调整时间,获得施加在卫星的单次推力的时间和有限推力系数;根据卫星轨道的半长轴、偏心率和近地点幅角的初始值,半长轴、偏心率和近地点幅角的目标值计算得到半长轴改变量和偏心率矢量改变量;根据半长轴改变量和偏心率矢量改变量计算得到第一组和第二组切向推力的总速度增量、第一组和第二组切向推力施加弧段中点的纬度幅角;根据第一组和第二组切向推力的总速度增量、第一组和第二组切向推力施加弧段中点的纬度幅角计算得到第一组和第二组切向推力的开机和关机纬度幅角;计算第一组和第二组切向推力的开机次数并选择卫星电推进轨道机动入轨执行策略。


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    Title :

    Near-circular orbit satellite electric propulsion orbit injection method


    Additional title:

    一种近圆轨道卫星电推进入轨方法


    Contributors:
    ZHAO SHUGE (author) / LIU QI (author) / LI XIAOYU (author) / MAO QINGTANG (author) / HUANG SIMING (author) / WANG CHONG (author)

    Publication date :

    2023-10-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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