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摘要
In this work the dynamic thermoelastic response of a slab with finite thickness subjected to aerodynamic heating is investigated. The system of generalized governing equations with generalized initial and boundary conditions is solved by the method of finite integral transformation, and the analytic expressions of the transient temperature and dynamical stresses in the slab are obtained. The finite integral transformation method shows its advantage and convenience to deal with the complex boundary conditions of a dynamic thermoelastic problem. Moreover, by introducing the aerodynamic heating and taking into account a typical Mach number curve for hypersonic flight, the analytical solution is obtained to simulate the dynamic thermoelastic response of the slab in hypersonic flight environment. Calculations are carried out for zirconium diboride to obtain transient temperature and dynamical stresses induced by aerodynamic heating.
