Progressive Failure Analysis Of Composite Laminate Considering The Stress Of Z Direction

Fiber reinforced composite materials have been more and more widely uesed in aerospace field, because of its high strength and its high modulus. At first, the part of composite materails were hatch, fairing, stabilizer, etc. It was now also used on aerofoil and airframe which mainly bear loads. The thickness of the composite laminates develop from thin plate to medium plate or thick plate. For thick plate, the classical laminate theory(CLT) is not applicable. How to effectively predict the strength of the composite laminates and the damage process is very important.Strength analyses of composite components, which contains three steps: the stresses calculation, the failure criterion and the rigidity decay, was reviewed in this paper. By analyzing the characteristics and disadvantages of some commonly used method, the author decided use the three-dimensional laminated medium theory. The three-dimensional Hashin failure criterion is used to judge the laminate a layer or multilayer failure. The failure layer adopts Camanho stiffness reduction to update the stiffness. In this paper, the user material subroutine UMAT of the finite element software ABAQUS is used to write the material property program. The finite element model of various thickness laminates is established by using the material property program. Using the model, the author numerically analyzes kinds of thich composite components to predict the strength of the components under the static tensile loads, and the process of progressive failure. The conclusion of this paper establishes a good foundation for further predicting the strength of kinds of different layers thick composite components, and will be reference for deeply understanding its process of progressive failure. At the same time,the finite element model of this paper has been greatly simplified. It helps to improve the efficiency of numerical analysis.