To study the aeroelastic instability of composite laminated panel under supersonic airflow, in order to analyze it by solving the generalized eigenvalue problem through aeroelastic properties. And generally by calculating the natural frequency of the laminated structure at different incoming flow speeds, the critical instability velocity of the laminated panel under the action of airflow is obtained, because the rigidity of the laminate structure decreases, resulting in structural instability. The structural parameters should be reasonably designed according to the mechanical environment of the composite panels to avoid structural instability problems under the action of airflow. Piston theory was originally developed by Lighthill, on the basis of the extension of Tsien’s hypersonic similitude by Hayes.