The invention provides a spacecraft angular momentum offset high-dynamic attitude tracking control method, which comprises the following steps of: S1, calculating the maximum angular momentum required to be provided by a momentum wheel according to the maximum angular velocity required to be reached by aircraft attitude maneuver; s2, calculating the required offset angular momentum according to the angular momentum capability provided by the momentum wheel of the aircraft; s3, according to the angular momentum needing to be biased and information such as the installation layout and the mass center position of the thruster, the total pulse width duration of three-axis jet unloading is calculated; s4, attitude closed-loop stable control and thruster open-loop control are conducted through the momentum wheel, and air injection pulse width instructions are executed on the single shafts according to a certain pulse width and time interval; and S5, respectively calculating a feedforward control moment and a feedback control moment, generating a moment instruction for the control moment gyroscope, and carrying out high-angular-velocity attitude maneuver control. The angular momentum capability of the momentum wheel of the aircraft is fully utilized, and the control precision of the attitude control system is effectively improved.

    本发明提供一种空间飞行器角动量偏置的高动态姿态跟踪控制方法,其包含:步骤S1、根据飞行器姿态机动需要达到的最大角速度,计算动量轮所需要提供的最大角动量;步骤S2、根据飞行器的动量轮能够提供的角动量能力,计算所需要的偏置角动量;步骤S3、根据需要偏置的角动量和推力器的安装布局、质心位置等信息,分别计算三轴喷气卸载的脉宽总时长;步骤S4、利用动量轮进行姿态闭环稳定控制,推力器开环控制,分别对单轴按一定脉宽与时间间隔执行喷气脉宽指令;步骤S5、分别计算前馈控制力矩和反馈控制力矩,生成给控制力矩陀螺的力矩指令,进行大角速度姿态机动控制。其充分利用了飞行器动量轮的角动量能力,有效提高了姿态控制系统的控制精度。


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    Titel :

    High-dynamic attitude tracking control method for spacecraft angular momentum offset


    Weitere Titelangaben:

    一种空间飞行器角动量偏置的高动态姿态跟踪控制方法


    Beteiligte:
    GUO ZHENGYONG (Autor:in) / YIN JUNXIONG (Autor:in) / HUANG JINGMEI (Autor:in) / LIANG JUPING (Autor:in) / DAI WEIZONG (Autor:in) / LIU MINGYANG (Autor:in) / XU CHENLU (Autor:in) / ZHANG FENG (Autor:in)

    Erscheinungsdatum :

    2023-03-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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