FEM BUCKLING BEHAVIOR STUDIES ON COMPOSITE PLATES WITH INITIAL IMPERFECTIONS

Abstract

In the paper, the buckling behavior analysis of a clamped, composite laminated quadratic plate under a uniaxial and shear in-plane loading is presented. The imperfection is considered as the initial deformation due to the manufacturing operations: cosine shape in both of the longitudinal and transverse direction. Usually, the initial deformation mode appears in the form of the fundamental mode of the buckling or vibration. The boundary conditions are considered as the usual condition of the structural composite ship panels. On the plate sides the loading is considered as an uniform pressure. Variation of the maximum transverse displacement versus the in-plane load (displacement controlled after nonlinear buckling analysis)or three cases. Maximum initial deformation magnitude is considered as a rate from the thickness, t, that The parametric calculus was done for various values of loading ratio.