Buckling behavior of Composite Plates with Circular Embedded Delaminations under In-Plane Compressive loading

Delamination is the most common failure modes in composite structures. Delamination on a flat composite structure under compressive in-plane loads can be causes local buckling on the delamination area, reduced stiffness and early failure. In this paper, buckling analysis of laminates with an embedded delamination has been studied by employing a finite element analysis. The modeling and calculations was done using FEM commercial software ANSYS. Also the effect of increasing the area of the delamination and the effect of fiber angle on the buckling load is investigated. Composite laminates with embedded circular delamination are studied that under compressive unidirectional and bidirectional plane loading are located. The results show that increasing the area of the delamination, buckling load of structural is reduced and buckling mode is changed. Specimen under unidirectional compressive loading, maximum buckling load is related to stacking sequence [±75]s . Buckling behavior of structures under tensile-compressive loads is entirely different and maximum buckling load is related to stacking sequence[±45]s.