A thruster control method for guaranteeing attitude stability and orbit control efficiency includes the steps that in each control period of a computer, attitude control jet required to be output by each thruster is calculated according to the current angle and angular velocity of a satellite, and orbit control jet required to be output is calculated according to the number of orbits required to be adjusted; then, respectively selecting the thrusters which need to be subjected to attitude control output and orbit control output at the current rhythm, and setting an attitude and orbit multiplexing mark; then an orbit control thruster combination containing the thruster with the attitude and orbit multiplexing mark is selected, and marks of'two times of air injection in one beat 'are set for all the thrusters in the combination; and carrying out two-time air injection pulse width output on the thruster with the mark of'two-time air injection is needed in one beat 'according to conditions.

    一种保障姿态稳定及轨道控制效率的推力器控制方法,在计算机每个控制周期内,首先根据卫星当前角度和角速度计算出每个推力器需要输出的姿态控制喷气,根据需要调整的轨道根数计算出需要输出的轨道控制喷气;然后,分别挑选出当前节拍即需要进行姿态控制输出和又需要进行轨道控制输出的推力器,并置出“姿轨复用”标志;然后挑选出包含已置出“姿轨复用”标志推力器所在的轨道控制推力器组合,并对组合内的所有推力器置出“一个节拍内需两次喷气”的标志;对置出“一个节拍内需两次喷气”标志的推力器分情况实施两次喷气脉宽输出。


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    Title :

    Thruster control method for guaranteeing attitude stability and orbit control efficiency


    Additional title:

    一种保障姿态稳定及轨道控制效率的推力器控制方法


    Contributors:
    WANG RUI (author) / XIANG KUN (author) / MENG QICHEN (author) / CHEN YINHE (author) / ZHANG HONGXING (author)

    Publication date :

    2025-01-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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