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.