초음속 영역에서 복합적층 평판의 공력열탄성 해석

Abstract

Supersonic linear and nonlinear flutter characteristics are presented for laminated composite plates subject to thermal loads. The quasisteady first-order piston theory is used to model the supersonic aerodynamic forces. First order shear deformable plate theory (FSDT) considering von Karman displacement-strain relation is used to account for geometrically nonlinear structural behavior. The temperature distribution is assumed to be constant over the surface and a thermal gradient though the thickness is also assumed to be constant. The static deformation due to aerodynamic and thermal load is determined using Newton-Rhapson iteration method. The complex eigenvalue problem is solved to investigate the linear and nonlinear panel flutter phenomena and the Guyan Reduction method is used for the computational efficiency. The postbuckling and linear flutter analyses are performed and the effects of the lamination scheme, material type and boundary conditions are investigated. Nonlinear flutter characteristics for limit-cycle-oscillation are also obtained.