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With the raised performance of advanced aircraft, hypersonic vehicles are subjected to increasingly severe environment. Very severe elevated temperature and high intensity acoustic loads will cause the thin-walled structures of aircraft to respond in a strong nonlinear large deflection vibration, and leading to premature fatigue failure of the structure. According to the Von Karman large deflection theory, the large deflection governing equation of plate under thermo-acoustic loadings is obtained. The Galerkin method is employed to obtain the ordinary differential equation under modal coordinates and the stress expressed by modal displacement for the simply-supported plate and the clamped plate. The critical thermal buckling temperatures and modal frequencies of simply-supported plate and thin-walled cylindrical shell under thermal loads with linear temperature gradient, the dynamic responses of them under thermo-acoustic loads, are obtained using finite element numerical stimulation, The thermal-acoustic responses of simply-supported plate and thinwalled cylindrical shell with different combinations of thermal-acoustic loadings are obtained, including the random vibration in pre-buckled regime, snap-through motion between post-buckled equilibrium positions and nonlinear vibration around one post-buckled position.

Response Analysis of thin-walled Structure under Non-uniform temperature field and Acoustic Loads