Cohesive analysis of a 3D benchmark for delamination growth under quasi-static and fatigue loading conditions

Journal article (2022)

Authors

A. Raimondo Aerospace Structures & Computational Mechanics - Aerospace Engineering
Carlos G. Dávila NASA Langley Research Center
C. Bisagni Aerospace Structures & Computational Mechanics - Aerospace Engineering
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Copyright: © 2022 A. Raimondo, Carlos G. Dávila, C. Bisagni
DOI: https://doi.org/10.1111/ffe.13712
Fatigue Delamination Cohesive zone model Paris law S-N diagram
More Info
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Published Date

2022

Language

English

Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

This paper evaluates the capabilities of the recently developed CF20 cohesive fatigue model, which can predict crack initiation as well as the rates of crack propagation by relying on intrinsic relationships between a stress-life diagram and its corresponding Paris law. The model is validated here using a partially reinforced double cantilever beam (R-DCB) benchmark proposed in literature. The two parameters needed for the CF20 cohesive fatigue model were obtained by performing preliminary analyses of a conventional DCB. The analysis results indicate that the CF20 cohesive fatigue model can accurately reproduce the complex evolution of the delamination observed in the R-DCB.