The plate structures are the basic elements in the flight vehicle， and they are exposed in severe environment during the cruise with aerodynamic， thermal and mechanical loads acted on them. In this paper， the first order deformation plate theory and supersonic piston theory were employed to formulate the energy functionals of the composite plate in supersonic airflow. The governing equations of the system were obtained by using the Hamilton’s principle， and the dynamic responses of the plate were computed by adopting the Newmark method and Newton iteration method. The influence of key parameters on the dynamic behaviors of the composite plate was discussed. Finally， the vibration control of the plate was carried out by using the nonlinear energy sink， and the results showed that the dynamic responses can be suppressed by the nonlinear energy sink.