The invention discloses an attitude control method of a spin detection satellite, and belongs to the field of satellite attitude control. The method aims at solving the problems that complete attitude parameters are difficult to obtain in the satellite high-speed spinning process and the satellite attitude control precision is affected by disturbance torque. Comprising the following steps: establishing a satellite kinetic equation and converting into a state-space equation; designing two layers of linear cascade state observers, wherein the first layer of linear state observer is used for observing and obtaining a current angular velocity estimated value and a current disturbance variable estimated value of a satellite; the second-layer state observer observes the tracking error of the first-layer linear state observer based on the observation result of the first-layer linear state observer; calculating to obtain a satellite internal and external total disturbance torque estimated value according to the current disturbance variable estimated value and the tracking error thereof; a PD control law is designed by adopting attitude parameters representing the spin axis direction, and a control torque is calculated by compensating the estimated value of the total disturbance torque inside and outside the satellite and is used for satellite attitude control in the current period. The method is used for attitude control of the satellite.

    一种自旋探测卫星的姿态控制方法,属于卫星姿态控制领域。本发明针对卫星高速自旋过程中难以获得完整姿态参数以及存在干扰力矩影响卫星姿态控制精度的问题。包括:建立卫星动力学方程并转换为状态空间方程;设计两层线性级联状态观测器,其中第一层线性状态观测器用于观测获取卫星的当前角速度估计值和当前干扰量估计值;第二层状态观测器基于第一层线性状态观测器的观测结果观测第一层线性状态观测器的跟踪误差;再由当前干扰量估计值和其跟踪误差计算得到卫星内外总干扰力矩估计值;采用表征自旋轴方向的姿态参数设计PD控制律,并补偿卫星内外总干扰力矩估计值计算得到控制力矩,用于当前周期的卫星姿态控制。本发明方法用于卫星的姿态控制。


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    Titel :

    Attitude control method of spin detection satellite


    Weitere Titelangaben:

    自旋探测卫星的姿态控制方法


    Beteiligte:
    XI RUICHEN (Autor:in) / LIU ZAIHUA (Autor:in) / WEI CHAO (Autor:in) / WANG WEIJIAN (Autor:in) / WU FAN (Autor:in) / LE XINLONG (Autor:in)

    Erscheinungsdatum :

    2024-04-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS





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