The goal of this paper is to understand transient dynamics of an aero-structure under combined loading. In this study, a nonlinear finite element model of a representative panel is used to evaluate the effect of combined thermal and mechanical loading on nonlinear response with specific focus on severe aerodynamic heating and fluctuating pressure. This results in nonlinear response behavior including thermal buckling, snap-through and snap-buckling. A snap-through boundary is presented in the space of combined loading parameters. Relationship between the frequency of snap-through and loading magnitude is also discussed. Some observations are presented on transient behavior as well as the asymmetric response. It is demonstrated that boundary conditions can be utilized to enhance the design of such structural panels.
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