AEROTHERMOELASTIC ANALYSIS OF FUNCTIONALLY GRADED PLATES USING GENERALIZED DIFFERENTIAL QUADRATURE METHOD

Abstract

IN THE PRESENT PAPER, THE AEROTHERMOELASTIC BEHAVIOR OF FUNTIOALLY 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 SUPEROIC AERODYNAIC LOADS ON THE PLATE, FIRST ORDER PISTON THEORY IS APPLIED. MATERIAL PROPERTIES OF THE FG PANEL ARE ASSUMED TO BE TEMPERATURE INDEPENENT AND ALTERED IN THE THICKNESS DIRECTION ACCORDING TO A POWER LAW DITRIBUTION. 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 OBTAIED RESULTS WITH THOSE AVAILABLE IN LITERATURE CONFIRMS THE ACCURACY AND ABILITY OF THE GDQM TO PERFORM AN 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 FRACTIN INDEX ON THE PLATE AEROTHERMOELASTIC BEHAVIOR IS EXAMINED.