The invention discloses a variable double-vector attitude control method for a large elliptical orbit satellite, and the method comprises the steps: determining satellite orbit operation tasks, segmenting a satellite orbit according to different satellite orbit operation tasks, and obtaining satellite orbit segments of different tasks; constructing a reference coordinate system corresponding to each task satellite orbit segment, and constructing a satellite body attitude coordinate system; and tracking the reference coordinate system corresponding to each task satellite orbit segment through the satellite body attitude coordinate system so as to perform satellite attitude control. The satellite attitude can be planned according to satellite task characteristics, illumination conditions and satellite angular momentum conditions in different height sections of the large elliptical orbit.

    本发明公开了一种大椭圆轨道卫星可变双矢量姿态控制方法,该方法包括:确定卫星轨道运行任务,并根据不同的卫星轨道运行任务对卫星运行轨道进行分段,得到不同任务的卫星轨道段;构建各个任务卫星轨道段对应的参考坐标系,并构建卫星本体姿态坐标系;通过卫星本体姿态坐标系对各个任务卫星轨道段对应的参考坐标系进行跟踪,以进行卫星姿态控制。本发明能够根据大椭圆轨道不同高度段卫星任务特点、光照条件和卫星角动量情况规划卫星姿态。


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    Title :

    Variable double-vector attitude control method for large elliptical orbit satellite


    Additional title:

    大椭圆轨道卫星可变双矢量姿态控制方法


    Contributors:
    HE YIKANG (author) / LI DETING (author) / MA XUEYANG (author) / ZHOU ZEYA (author) / PAN XIAODONG (author) / LIN SHUYU (author) / XIE KAN (author) / ZHOU LIANWEN (author)

    Publication date :

    2023-04-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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