航天器柔性太阳翼最优PPF主动振动抑制方法

针对采用可变速控制力矩陀螺(VSCMG)进行柔性太阳翼振动抑制问题，提出一种基于求解非光滑 H∞ 综合问题的最优参数正位置反馈(PPF)控制方法。首先，建立考虑VSCMG和柔性太阳翼耦合的振动模型，得到了线性化的约束陀螺柔性板动力学模型，基于同位控制思想推导了以角度陀螺为测量装置的约束陀螺柔性板全阶状态空间模型。针对被控对象特性，确定最优PPF控制器的结构构型和待优化参数。进而，通过对约束陀螺柔性板全阶状态空间模型进行降阶、修正和加权处理，将PPF控制器参数优化问题转化为在PPF控制器构型约束条件下的非光滑H∞综合问题，并应用一阶下降算法进行寻优求解，实现最优PPF控制器的设计。该方法能够实现对各阶陀螺模态的独立控制，在保证快速性和鲁棒性的前提下，实现最优PPF参数的稳定高效求解。仿真结果表明，所提出的最优PPF控制方法能够快速、鲁棒地实现航天器柔性太阳翼的主动振动抑制。

Active Vibration Suppression of Spacecraft’s Flexible Solar Panel with Optimal PPF Method

A novel optimal parameter positive position feedback (PPF) control method based on solving the nonsmooth H∞ synthesis problem is proposed to suppress the vibration of the spacecraft’s flexible solar panel with variable-speed control moment gyros (VSCMG). Firstly, a vibration model considering the coupling of VSCMG and the flexible solar panel is established as the linearized dynamic model of the constrained gyroelastic plate. Based on the idea of the collocated control, the full order state space model of the constrained gyroelastic plate with angle gyros as the measuring devices is derived. According to the characteristics of the controlled object, the structure and design parameters of the optimal PPF controller are determined. Then, by reducing, modifying and weighting the full order state space model of the constrained gyroelastic plate, the parameter optimization problem of the PPF controller is transformed into the nonsmooth H∞ synthesis problem under the constraint of the configuration of the PPF controller, and the optimizing process of the PPF controller’s parameters is realized by using the first-order descent algorithm. This method can realize the independent control of each gyro modes, and realize the stable and efficient optimization of the optimal PPF parameters on the premise of ensuring the performance and robustness. The simulation results show that the proposed optimal PPF control method can quickly and robustly achieve the vibration suppression of the spacecraft’s flexible solar panel.