The invention relates to the technical field of aerospace, and discloses a micro-nano satellite attitude control method based on deterministic strategy gradient and PID, and the method comprises the following steps: obtaining the pitching theta, the rolling psi and the yaw angle # imgabs0 # of a satellite through a sensitive sensor; the required control moment is converted into the attitude angle speed # imgabs 1 #, the angles theta t and psi t of the satellite in the current state are obtained according to an attitude kinematics model, and the satellite attitude quaternion error qe is determined according to the difference of the satellite attitude angles determined by a sensitive sensor through # imgabs 2 #. According to the micro-nano satellite attitude control method based on the deterministic strategy gradient and the PID, a better control strategy can be learned by adopting a deterministic strategy gradient algorithm, and by combining the deterministic strategy gradient algorithm with the traditional PID, more accurate adjustment can be carried out for the complex attitude change of the micro-nano satellite, and attitude deviation is reduced.

    本发明涉及航空航天技术领域,公开了一种基于确定性策略梯度与PID的微纳卫星姿态控制方法,包括以下步骤:通过敏传感器获得卫星的俯仰θ、滚转ψ、偏航角#imgabs0#通过卫星姿态动力学模型,根据所需的控制力矩转化为姿态角角速度#imgabs1#根据姿态运动学模型,获得卫星在目前状态的角度θt,ψt,#imgabs2#通过敏传感器确定的卫星姿态角的差异确定卫星姿态四元数误差qe。该基于确定性策略梯度与PID的微纳卫星姿态控制方法,采用确定性策略梯度算法能够学习到更优的控制策略,与传统PID相结合,可以针对微纳卫星的复杂姿态变化进行更精准的调整,减少姿态偏差。


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    Title :

    Micro-nano satellite attitude control method based on deterministic strategy gradient and PID


    Additional title:

    一种基于确定性策略梯度与PID的微纳卫星姿态控制方法


    Contributors:
    KANG HUIFENG (author) / CHEN LIN (author) / CHEN XIANGQIU (author) / LIU JINGWANG (author) / XIA GUANGQING (author) / HU MIN (author) / LI ZONGGANG (author)

    Publication date :

    2025-01-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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