Abstract
In the present paper, the aerothermoelastic behavior of Functionally Graded (FG) plates under supersonic airflow is investigated using Generalized Differential Quadrature Method (GDQM). The structural model is considered based on the classical plate theory and the von Karman strain-displacement relations are utilized to involve the nonlinear behavior of the plate. To consider the supersonic aerodynamic loads on the plate, the first order piston theory is applied. The material properties of the FG panel are assumed to be temperature independent and alter in the thickness direction according to a power law distribution. The temperature distribution on the surface of the plate is assumed to be constant and in the thickness direction is obtained by one-dimensional steady conductive heat transfer equation. The discretized governing equations via GDQM are solved by the fourth order Runge-Kutta method. Comparison of the obtained results with those available in literature confirms the accuracy and ability of the GDQM to perform the aerothermoelastic analysis of FG plates. Also, the effect of some important parameters such as Mach number, in-plane thermal load, plate aspect ratio and volume fraction index on the plate aerothermoelastic behavior is examined.
Highlights
The lifting surfaces and panels of space re-entry vehicles and high-speed aircrafts are exposed to combined effects of aerodynamic, thermodynamic, inertial, and elastic forces
To account for structural nonlinearity, von Karman's large detion plate theory was considered. They studied the effects of nonuniform temperature distribution, panel aspect ratio, and boundary conditions on the flutter behaviors of rectangular and triangular panels
This paper extends the application of the DQM to aerothermoelastic analysis of a flat plate in supersonic flow
Summary
The lifting surfaces and panels of space re-entry vehicles and high-speed aircrafts are exposed to combined effects of aerodynamic, thermodynamic, inertial, and elastic forces. To account for structural nonlinearity, von Karman's large detion plate theory was considered They studied the effects of nonuniform temperature distribution, panel aspect ratio, and boundary conditions on the flutter behaviors of rectangular and triangular panels. Praveen and Reddy (1998) investigated the static and dynamic response of functionally graded plates using a plate finite element that accounted for the effects of the transverse shear strains, rotary inertia and the moderately large rotations in the von Karman sense. Sohn and Kim (2009) studied the aerothermoelastic instability of FGM panels in supersonic flow and showed the effects of the volume fraction distributions, temperature changes, aerodynamic pressures and the boundary conditions on the panel flutter. The effects of some important parameters such as Mach number, in-plane thermal load, plate aspect ratio and volume fraction index on the plate aerothermoelastic behavior are investigated
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