Future hypersonic vehicle will operate in an extreme environment, which involves extreme aerodynamic heating, fluctuating pressure and acoustic loading. Hypersonic vehicle must be reusable, lightweight and affordable in such environment. For hypersonic flight, the structure experiences complex aeroacoustic loads. The design of the structure depends on the ability to predict the response and the life of structure in extreme environment. This research presents a
detailed investigation of the interactions and interplay among these parameters as evidenced by the nonlinear (static and dynamic) response of the panel.
A representative panel was selected as part of a ramp skin panel on a blend wing body hypersonic vehicle concept. This project focuses on the nonlinear response of the skin panel under combined thermal and structural loading. Thermal buckling, snap-through, and snap-buckling behaviors have been investigated by using different structural boundary condition. The long term goal of this research includes capturing fluid structure interaction as well as
developing design curves for nonlinear response of the panel.