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建立了三轴稳定小卫星稳定工作模式下的动力学模型,在此基础上设计了用于其姿态稳定控制的线性二次高斯型(LQG)控制器。该控制器由Kalman滤波状态估计器和线性二次型最优调节器两部分组成,前者对卫星姿态信息进行滤波融合,在此基础上,后者进行反馈增益矩阵的最优化设计。由三轴正交反作用飞轮系统提供控制力矩,得到了卫星姿态稳定系统的状态空间仿真模型。仿真结果表明:设计的LQG控制器可以实现卫星姿态的精确确定和稳定控制,姿态确定精度相对于敏感器测量精度有较大提高;二次型调节器能够对卫星姿态小偏置量进行快速稳定,而且可以较好地抑制卫星稳定工作时受到的外界干扰。
The dynamic model of the stabilized three-axis small satellite is set up. On the basis of this, a linear quadratic Gaussian (LQG) controller is designed for its attitude stability control. The controller consists of a Kalman filter state estimator and a linear quadratic optimal regulator. The former filters and combines the satellite attitude information. On the basis of this, the latter optimizes the feedback gain matrix. The control torque is provided by the three-axis orthogonal reaction flywheel system, and the state space simulation model of the satellite attitude stabilization system is obtained. The simulation results show that the designed LQG controller can accurately determine and control the attitude of the satellite, and the accuracy of attitude determination is greatly improved compared with that of the sensor. The quadratic regulator can quickly stabilize the satellite attitude bias , But also can better restrain the interference caused by the stable operation of the satellite.