Progressive Damage Analysis Of Composite Laminates

In the engineering field, especially in aviation and aerospace, the effectiveness of thestructure is concerned mostly, high strength and light quality of structural materials need todevelop. Because of fiber reinforced composites（FRC）with high strength-to-weight and highstiffness-to-weigh properties, FRC has a wide range of applications in the engineering field.But composite structure in the normal work condition frequently damage，such as Matrixcracking、Fiber fracture、Interfacial debonding and Delamination. In addition, these localdamage initiation and growth of composite structure will lead to the final failure. Therefore, amethod of effectively simulating partial damage initiation, expansion and accuratelypredicting the failure load of the structure with practical engineering significance is necessaryto put forward.In this paper, the progressive failure analysis method is used to simulate the process ofFRC failure. First, the two-dimensional model is used to simulate the failure process of FRC.Given a certain limitations of two-dimensional model, this paper puts forward three-dimensional progressive failure analysis model.This3d model can calculate the single plyplate internal force and the initial damage, the expansion and the strength of the final failurein the composite laminated plate,according to Shokrieh’s improved Hashin failure criteria tojudge the failure mode. The3d model considers the matrix failure, fiber failure andDelamination mode. This paper is based on the finite element software ABAQUS to completenumerical analysis,USDFLD subroutine compiled by FORTRAN is used to judge compositefailure mode according to properties of material degeneration. This model can effectivelysimulate the process and the mechanical response from initial to the final failure of compositelaminated structure under static loads including the damage initiation and growth. Incomparison with test results in the literature,the feasibility of model is verified,and theninvestigation on influence of the layer proportion and diameter of the hole has beenperformed by proposed model.