Abstract: 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.

Key words: Flexible solar panel, Control moment gyro (VSCMG), Positive position feedback (PPF), Nonsmooth H∞ synthesis, Vibration suppression