Abstract：The flutter characteristics and the vibration suppression of a composite laminate in the supersonic flow are studied. The first-order piston theory is used to calculate the aerodynamic pressure in the supersonic flow field. The dynamic model of a piezoelectric composite laminate is deduced by using the classical laminate theory and the Hamilton's principle. The sliding observer is designed to reduce the observation overflow, and the Lyapunov method is used to prove the stability. The LQR controller is designed based on the observed state. The effects of geometric parameters and fiber angles on the flutter characteristics of piezoelectric composite laminates are studied. The impulse response of the laminated plate is solved by SIMULINK simulation to verify the effectiveness of the controller. The results show that reasonable planning of the geometric parameters and fiber angle of the laminated plate can improve the system flutter stability. The sliding mode observer can trace the original system more accurately and has good robustness. The LQR control can eliminate the flutter point of the laminate within a certain range, and also can effectively suppress the vibration of the piezoelectric composite laminate at the flutter boundary, with the increase of the Q matrix, and the vibration suppression effect is better. The LQR control effect is better with the thickness of the piezoelectric layer becomes larger.
2022, Vol. 43 
