Abstract：This paper focus on the aerothermoelastic characteristics of composite laminated panels subjected to supersonic airflow, and implements macro fiber composite (MFC) materials for active flutter bound control. The aerodynamic pressure is calculated by utilizing supersonic piston theory, and the system's motion differential equations are established based on the assumed mode method and Hamilton's principle. The aerothermoelastic characteristics of the structural system are analyzed via the frequency domain method. The research examines the influences of ply angles and geometric parameters of the laminated panels on the variations in critical flutter aerodynamic pressure and critical buckling temperature. The proportional feedback control is designed to compute the flutter bounds under different gain coefficients. The results demonstrate that the laminated panel with ply angle of [90°/?90°/90°] exhibits the poorest aerothermoelastic stability for various aspect ratios. For larger ply angles, an increase in aspect ratio enhances the aerothermoelastic stability of the laminated panels. Moreover, the proportional feedback control method can significantly enhance the system's flutter bound, but the gain coefficients requires to be adjusted to ensure the stability and performance of the control system.
2024, Vol. 45 
