Fatigue crack propagation in composite laminates by a novel approach based on the S-N diagrams

Conference paper (2019)

Authors

A. Raimondo Aerospace Structures & Computational Mechanics - Aerospace Engineering
C. Bisagni Aerospace Structures & Computational Mechanics - Aerospace Engineering
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Copyright: © 2019 A. Raimondo, C. Bisagni
Fatigue Delamination Cohesive Zone Model S-N Diagram
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Published Date

2019

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

This paper focuses on a novel numerical formulation based on cohesive elements and S-N diagram to simulate fatigue-driven delamination in composite laminates. The constitutive model adopts a two-parameters heuristic equation, which coefficients are evaluated using an idealization of the S-N diagram rather than the more commonly used Paris law. The approach is implemented in the finite element code ABAQUS and validated with analysis on Double Cantilever Beam specimen. The numerical outcomes are compared with experimental data taken from literature showing the capability of the model in predicting the crack growth rate. The model is then applied to evaluate the fatigue delamination growth in a specimen similar to the Double Cantilever Beam but with reinforcement plates which force the delamination front to change its shape during the propagation. The results compared with experimental data taken from literature show the effectiveness of the approach in predicting the load-displacement curve and the delamination front shape and position at different load cycles.