Aero-Thermo-Mechanical Characteristics of Shape Memory Alloy Hybrid Composite Panels With Geometric Imperfection

Abstract

A new nonlinear finite element model is presented for the static aero-thermal deflection of a shape memory alloy (SMA) hybrid composite panel with initial geometric imperfection and under the combined effect of thermal and aerodynamic loads. The nonlinear governing equations are obtained using Marguerre curved plate theory and the principle of virtual work. The effect of large deflection is included in the formulation through the von Karman nonlinear strain-displacement relations. To account for the temperature dependence of material properties, the thermal strain is stated as an integral quantity of the thermal expansion coefficient with respect to temperature. The aerodynamic pressure is modeled using the quasi-steady first-order piston theory. The Newton-Raphson iteration method is employed to obtain the nonlinear aero-thermal deflections, while an Eigen value problem is solved at each temperature and static aerodynamic load to predict the free vibration frequencies about the deflected equilibrium position. Finally, the nonlinear deflection and free vibration characteristics of a SMA hybrid composite panel are presented, illustrating the effect of SMA fiber embeddings, temperature rise, dynamic pressure, boundary conditions and an initial geometric imperfection on the panel response.