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摘要:
针对带转动挠性帆板航天器的动力学参数存在不确定性的问题，提出一种利用线性变参数理论(LPV)的鲁棒保性能姿态控制器设计方法。以太阳帆板转角作为变参数，建立挠性航天器姿态动力学LPV模型。考虑输入受限及输入信号变化率受限的约束，并将二次型控制指标上限最优化，通过线性矩阵不等式(LMI)方法求解得到随变参数调度的LPV状态反馈控制器，所求得的控制器能够在系统参数大范围变化的情况下保持鲁棒稳定性，并具备抗干扰能力。用数值方法进行仿真验证，并与定常鲁棒保性能控制器相比较，验证了所提出的LPV鲁棒保性能控制器的适应性与鲁棒性。
Abstract:The dynamic parameters of spacecraft with rotating flexible panels are uncertain. In view of this problem, a robust attitude controller design method based on linear parameter varying (LPV) theory was proposed. Firstly, the LPV model of attitude dynamics of flexible spacecraft was established by taking the angles of rotations of solar panels as the variable parameter. The limited input and rates of change of input signals were considered, and the quadratic control indicator limit was optimized. Based on the linear matrix inequality (LMI) method, An LPV state feedback controller with variable parameter scheduling was obtained. The obtained controller can maintain robust stability under the condition of a wide range of system parameters and has anti-interference ability. Finally, the simulation was verified by numerical method and compared with the steady robust controller. The adaptability and robustness of the proposed LPV robust controller were verified.
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图 4 算例1航天器的控制力矩变化率
Figure 4. Rates of change of control torques of spacecraft in condition 1
图 9 算例2航天器的控制力矩变化率
Figure 9. Rates of change of control torques of spacecraft in condition 2
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