The Study On Delamination Growth In Composite Laminate Under Fatigue Load

With the expansion of application fields of composite material, research on compositemechanical properties has become one of the hottest research topics in aviation industry. Compositelaminate has been widely used in modern aircraft industry; however, the delamination in laminatedcomposite is unavoidable during the manufacture process, especially when structure withstands thealternating cycle fatigue loading, a progressive accumulation of damage will bring great safety troubleand can considerably reduce the safely service life of composite structure. Therefore, research onfatigue performance of composite laminates containing delamination damage should be carried out.In this paper, a numerical analysis model for problems of delamination growth damage oncomposite laminates with compressive loading was established based on3D nonlinear dynamic finiteelement analysis by using finite analysis software Abaqus, and took B-K standard based on the energyrelease rate as the criterion of delamination growth, the research on delamination propagationbehavior with static loading has been put forward. During the calculation of fatigue delaminationgrowth behavior, based on the residual strength model,3D-Hashin failure criteria was adopted tojudge the failure of model,and VUMAT user subroutine was introduced to reduce the stiffnessperformance of material, the delamination growth mechanism of composite laminates with initialone-dimensional and two-dimensional delamination damage under fatigue compression load wassimulated, a good agreement was obtained between numerical analysis and experiment results. At last,the effect of loading level, delamination size and stacking sequence on fatigue delamination growthbehavior was analyzed quantificationally.