Nonlinear static/dynamic behaviors of composite curved panels with piezoelectric patches in supersonic airflow

Abstract

The nonlinear aeroelastic static deflection and dynamic response of the composite curved panel with rectilinear- and curvilinear-fiber lay-up configurations under supersonic flow are investigated. The geometrical nonlinear effect of the composite curved panel is depicted by the Von-Karman strain and the aerodynamic load is incorporated through the nonlinear third-order piston theory. The Newton-Raphson method is employed to determine the static deflection of the composite curved panel and the four-order Runge-Kutta method is for the dynamic response, respectively. After examining the accuracy of the established mechanical model through numerical comparisons with existing literatures, the parametric studies focusing on panel curvature, high-order piston aerodynamic force, fiber angle orientation, temperature rise, locations and applied voltages of the piezoelectric patch on nonlinear static deformation and dynamic response are investigated. The results are deliberated in detail, and it is observed that the panel curvature and fiber angle orientation significantly affect the aeroelastic static deflection and dynamic response of the curved panel under thermal environment. Moreover, high-order aerodynamic force enlarges the static deflection and dynamic response of the curved panels with a large curvature whereas the impact of applied voltages of the piezoelectric patch will be weaker.