The invention belongs to the technical field of satellite orbit control, and discloses a microsatellite orbit control method for a single-side single-axis SADA, and the method comprises the following steps: S1, obtaining corresponding satellite mass center positions when the single-side single-axis SADA rotates for different angles; s2, according to the position of the center of mass of the satellite, calculating a thrust vector deviation force arm, judging the attitude safety range during orbit control, and calculating the position with the longest orbit control time; and S3, calculating the satellite position and moment corresponding to the SADA rotation angle according to the relationship between the SADA rotation angle and the vector from the satellite to the sun.

    本发明属于卫星轨道控制技术领域,本发明公开了一种针对仅有单侧单轴SADA的微小卫星轨控方法,包括以下步骤:S1.获取单侧单轴SADA转动不同角度时对应的卫星质心位置;S2.根据所述卫星质心位置,计算推力矢量偏差力臂,判断轨控时姿态安全的范围并计算轨控时间最长的位置;S3.根据SADA转动角度与卫星到太阳矢量的关系,计算SADA转动角度对应的卫星位置和时刻。


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    Titel :

    Micro-satellite orbit control method for single-side single-axis SADA


    Weitere Titelangaben:

    一种针对仅有单侧单轴SADA的微小卫星轨控方法


    Beteiligte:
    LIU DONGCHEN (Autor:in) / QU YOUYANG (Autor:in) / REN HAO (Autor:in) / FAN LINDONG (Autor:in) / YI JIN (Autor:in) / DAI LU (Autor:in)

    Erscheinungsdatum :

    18.06.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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