## 1 Introduction  
Thin-walled structures with characteristics of lightweight, flexible, and low damping have been broadly applied in advanced aircraft. The increase of modern aircraft's flight velocity causes the aeroelastic behaviors of these structures to be a significant concern. When the external skin of aircraft is subjected to complex aerodynamic flow conditions, the aeroelastic self-excited oscillation, termed the aeroelastic flutter, occurs. The large amplitude vibration produced by an aeroelastic flutter may lead to catastrophic consequences for aircraft. Hence, analysis of the aeroelastic flutter of panels under supersonic flow is important in designing and optimation of the supersonic aircraft vehicles' external structures. Aeroelastic flutter analysis is an important research branch of aerodynamics and is getting much more concern. [PERSON] and [PERSON] [1] investigated the supersonic flutter features of functionally graded plates based on the finite element procedure. The effects of different parameters, such as thermal gradient on aspect ratios, damping, and boundary conditions on the flutter behaviors were analyzed by solving the complex eigenvalue problem. [PERSON] et al. [2,3] studied the aeroelastic and aero-thermoelastic flutter behaviors of the composite cylindrical panels and shells with viscoelastic layers under supersonic flows. Several types of damping treatments have been estimated and the results indicated that damping properties had important influences on the flutter boundaries of these sturctures. [PERSON] et al. [4; 5] investigated the nonlinear response and aeroelastic flutter of composite laminated plates and shells under the combined excitation of aerodynamic pressures and transverse excitation. [PERSON] et al. [6] studied the supersonic flutter of laminated composite plate concluding a viscoelastic mid-layer and examined the influences of viscoelastic damping and aerodynamic damping on the flutter boundary of the plate. [PERSON] and [PERSON] [7] numerically evaluated influences of the panel geometry, material parameters, boundary conditions, and airflow direction on the supersonic flutter characteristics and critical aerodynamic pressure of laminated composite cylindrical panels and plates. [PERSON] et al. [8] proposed a theoretical model to analyze the nonlinear aeroelastic and random vibration of composite panels with shape memory alloy subjected to the thermal-aero-acoustic excitations. Hence, flutter suppression became of particular interest and primary objective for aeroelastic investigation, considering its practical significance. Based on their proposed positive position feedback algorithm, [PERSON] et al. [9; 10] experimentally achieved an amplitude reduction of a free sandwich plate. [PERSON] et al. [11; 12] conducted theoretical and experimental investigations on the vibration control and performance of the aeroelastic stability of a rigid wing model attached with nonlinear energy sinks. Developing an adaptive output feedback controller, [PERSON] et al. [13] applied the control surface actuation of the leading edge and trailing edge to achieve the aeroelastic oscillation suppression of a nonlinear wing section. [PERSON] et al. [14] proposed a robust control algorithm to enhance the aeroelastic performance of the composite laminated cantilever plates in a hygothermal environment. [PERSON] et al. [15; 16] applied a robust control strategy to suppress flutter and reduce the vibration amplitudes of an aeroelastic flapped wing system subjected to a pulse excitation in a supersonic flow. Utilizing a proportional derivative feedback approach, [PERSON] and [PERSON] [17] investigated the active suppression of a nonlinear piezolaminated plate. Piezoelectric material is one kind of smart material that has been widely utilized in active vibration suppression. [PERSON] and [PERSON] [18] investigated the aeroelastic stability and vibration characteristics of a plate with piezoelectric material.