The invention discloses a cubesat attitude control mode switching method, and particularly relates to the technical field of satellite attitude control, and the method comprises the following steps: after a satellite and a rocket are separated, attitude control is powered on, a pitch axis momentum wheel rotates, a satellite performs offset momentum angular rate damping, and a filter is started when an orbit is determined to be effective; performing bias momentum control when the filter converges and the attitude is captured, and switching to an angular rate damping mode when a fault occurs; and finally, switching an upper injection instruction to a zero momentum control mode, performing zero momentum control when the filter converges, and switching to an angular rate damping mode when a fault occurs. When a certain momentum wheel breaks down, the other three wheels form a bias momentum control or zero momentum control mode, and a set attitude control task is completed. Therefore, according to the attitude control mode switching method, limited hardware resources are fully utilized, mode switching logic is clear, software implementation is simple, and the reliability of a cubesat attitude control system can be effectively improved.

    本发明公开了一种立方星姿控模式切换方法,具体涉及卫星姿控技术领域,步骤如下:星箭分离后姿控上电,俯仰轴动量轮起旋,卫星进行偏置动量角速率阻尼,当判定轨道有效时开启滤波器;当滤波器收敛且姿态捕获时进行偏置动量控制,出现故障时切换至角速率阻尼模式;最后上注指令切换至零动量控制模式,当滤波器收敛时进行零动量控制,出现故障时切换至角速率阻尼模式。当某一动量轮故障时,另外三轮组成偏置动量控制或零动量控制模式,完成既定姿控任务。由此可知,上述姿控模式切换方法充分利用了有限的硬件资源,模式切换逻辑清晰,软件实现简单,可有效提高立方星姿态控制系统的可靠性。


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    Title :

    Cubesat attitude control mode switching method


    Additional title:

    一种立方星姿控模式切换方法


    Contributors:
    HU YUANDONG (author) / LIU BINGYUAN (author) / SUN JIE (author) / XU YI (author) / XIE HAODONG (author) / SHENG YIMING (author) / LU ZHENGLIANG (author)

    Publication date :

    2024-04-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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