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为了研究带重力梯度杆的充液卫星姿态动力学 ,利用带端质量的等效悬臂梁模型及液体晃动的等效力学模型 ,即一组球面摆和一个轴对称圆盘 ,建立了挠性充液耦合的卫星姿态动力学方程。根据某微小卫星的具体参数 ,利用多变量控制系统极点配置选取了 3个反作用飞轮的控制率 ,通过数值仿真计算 ,得到了刚柔耦合及挠性充液耦合卫星姿态角的变化规律。仿真结果表明 ,采用三轴反作用飞轮控制方法 ,并对挠性振动进行动态补偿 ,可以改善姿态控制精度 ;同时得到了液体晃动对姿态角精度的影响
In order to study the attitude dynamics of a liquid-filled satellite with a gravity-gradient rod, an equivalent cantilever beam model with equivalent end-masses and an equivalent mechanical model of liquid sloshing, a set of spherical pendulum and an axisymmetric disk, Liquid Coupled Satellite Attitude Dynamics Equation. According to the specific parameters of a tiny satellite, the control rate of three reaction flywheels is selected by the pole configuration of the multivariable control system. The variation of the attitude angles of the rigid-flexible coupling and the flexible liquid-filled coupling satellite is obtained by numerical simulation. The simulation results show that the three-axis reaction flywheel control method and the dynamic compensation of the flexible vibration can improve the accuracy of attitude control. At the same time, the influence of liquid sloshing on attitude angle accuracy is obtained