Self-excited Vibration Characteristics of Cylindrical Composit Shell subject to Thermal Stresses in Supersonic Flow

초음속 유동에서 열응력을 받는 원통형 복합적층 쉘의 자려진동 특성

The supersonic flutter analysis of cylindrical composite panels subject to thermal stresses has been performed using layerwise nonlinear finite elements. The geometric nonlinear finite elements of cylindrical shells are formulated using hamilton's principle with von Karman strain-displacement relationship. Hans Krumhaar's modified supersonic piston theory is appled to calculate aerodynamic loads for the panel flutter analysis. The present results show that the critical dynamic pressure of cylindrical panels under compressive thermal stresses can be dramatically reduced. The margin of aerothermoelastic stability considering thermal and aerodynamic coupling should be verified in the structural design of launch vehicles and high speed aircrafts.