The Finite Element Analysis Of The Progressive Damage Of Composite Laminated Plates Based On ABAQUS

Composite materials are widely used in aerospace, automotive industry, energy engineering,wind power generation and shipbuilding industry, because of its excellent performanceincluding higher specific strength and modulus, being designable and identical material andstructure. However, composite materials often suffer the external loads in the actualproduction, usage and maintenance process. There are some damages within or between thelayers. These damages, including matrix cracking, fiber fracture and interlayer delamination,are invisible in the composite materials. As known, most damages caused by the weakinterlayer shear strength, the poor damage resistance or interlayer strength of laminated platematerial structure. And, the mechanical properties of composite material structure degenerateseriously and structure strength and service life reducing severely because of them,consequently leads to the potential safety hazard and the restriction of fiber reinforced resinmatrix composites application.Based on the Hashin failure criterion and cohesive, this paper used the large commercialfinite element analysis software ABAQUS/Explicit, established the finite element analysismodel for the progressive damage of composite laminated plate. Meanwhile, the needed basicparameters of the ABAQUS analysis are obtained, through testing the basis performance ofglass fiber reinforced epoxy resin composite laminates, Then, the model was optimized byconsidering the influence of grid density and element damage degradation parameters.In this paper, the initiatory and extensional process of intralayer failure and interlayerdelamination failure of the composite laminated plate under three point bending load wereobtained based on optimized finite element model. The studies showed that matrix tensile failure and matrix compression failure are the main failure modes in90°layer, fiber tensilefailure and fiber compression failure are the main failure modes in0°layer, matrix tensilefailure and fiber tensile failure are mainly concentrated in the lower position of the laminatedplate, but matrix compression failure and fiber compression failure are more serious in theupper position of the laminated plate than in the lower position. The matrix failure modeappears in laminated plate first, and then the fiber failure mode appears, but the fiber failuremode dominates the carrying capacity of the laminated plate. In terms of the delamination, itis facility to appear in the lower position of the laminated plate, and expand fast.