Open Access

ARTICLE

A Ply-By-Ply Discretized 2D FEA Approach with the Integrated XFEM-CE Strategy for Predicting Multiple Failures in Laminated Composite Structures

Yana Wang^1,2,3,4, Ruodi Jia^1,5, Fengrui Liu^1,5,6,*

1 School of Astronautics, Beihang University, Beijing, 100191, China.
2 Aeronautical Material Testing Research Center, AECC Beijing Institute of Aeronautical Materials, Beijing, 100095, China.
3 Beijing Key Laboratory of Aeronautical Material Testing and Evaluation, Beijing, 100095, China.
4 Key Laboratory of Aeronautical Material Testing and Evaluation, Aero Engine Corporation of China, Beijing, 100095, China.
5 Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technologies, Minisitry of Education, Beihang University, Beijing, 100191, China.
6 State Key Laboratory for Strength and Vibration of Mechanical Structures, Xi’an Jiaotong University, Xi’an, 710049, China.

*Corresponding Author: Fengrui Liu. Email: .

Computer Modeling in Engineering & Sciences 2019, 120(1), 215-234. https://doi.org/10.32604/cmes.2019.06542

Abstract

Delamination and matrix cracking are two common failure mechanisms in composite structures, and are usually coupled with each other, leading to multiple failures pattern. This paper proposed a fast damage prediction methodology for composite laminated structures based on the ply-by-ply 2D (two dimensional) FE model of composite laminates in the transverse plane. The layer-wise 2D FE model was firstly used in conjunction with the integrated XFEM/CE strategy, which simulated the interface delamination with cohesive elements and the intra-ply matrix crack with XFEM (extended finite element method). To realize ply-by-ply 2D FE (finite element) modeling of composite laminates, two 2D material models were developed based on the plane stress assumption and plane strain assumption, respectively. A general crack propagation scheme was developed in the framework of the integrated XFEM-CE method. Adopting the 2D material model based on the plane strain assumption, a ply-by-ply discretized 2D FEA procedure was conducted for an out-of-plane composite Pi joint under the static tensile load. The predicted load-displacement response and damage evolution process showed good agreement with the experimental results, which verified the proposed approach.

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