No abstract

Hypersonic vehicles structures suffer complex combined loadings generally. For the thin-walled structures and thermal protection systems of the aircraft, high temperature and intensity acoustic loadings are the significant factors that leading to their break. The object of this paper is typical simply supported titanium alloy plate, the finite element method was adopted to calculate the critical thermal buckling temperature the ordinal coupling method and Newmark method were adopted to calculate the thermalacoustic dynamic response. Based on the FEM analysis, the power spectrum densities (PSD) of center point was presented. Research results show that the thermal buckling of the typical simply supported titanium alloy plate occurs easily because of the low critical thermal buckling temperature, dynamic response of the thermal buckled plate suffering acoustic loads performs strong nonlinear characteristics and complex forms of exercise.

surface structures of the vehicle suffer thermal loadings during the high speed flight. The thermal stress distribution of typical titanium alloy plate under thermal loadings is studied based on the assumption of uncoupled thermal-structural properties and nonlinear von Karman large-deflection strain-displacement relationship; the critical buckling temperature of simply supported titanium alloy plate is obtained through generalized eigenvalue analysis, and the change of the response characteristic before and after plate buckling is obtained by further analysis. The results show that, simply supported titanium alloy plate in uniform temperature field is prone to buckling because of the relatively low critical buckling temperature. The modal and frequency of the plate were changed before and after the buckling, structure shows more characteristics of higher order modes.