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. 2022 Nov 17;14(22):4985.
doi: 10.3390/polym14224985.

A Multiaxial Fatigue Damage Model Based on Constant Life Diagrams for Polymer Fiber-Reinforced Laminates

Aleksandr Elkin  1 , Viktor Gaibel  1 , Dmitry Dzhurinskiy  1 , Ivan Sergeichev  1
Affiliations

A Multiaxial Fatigue Damage Model Based on Constant Life Diagrams for Polymer Fiber-Reinforced Laminates

Aleksandr Elkin et al. Polymers (Basel). .

Abstract

In the last decade, fatigue damage models for fiber-reinforced polymer composites have been developed assuming the fracture energy equivalence hypothesis. These models are able to predict a fatigue life of composite laminates, but their identification requires a significant number of off-axial tests for various stress ratios. The present study proposes the stress ratio dependent model, which phenomenologically adopts a decrease in stiffness and residual strength of a unique ply according to experimental constant life diagrams. Hashin, Tsai-Hill, and the maximum stress failure criteria are utilized for damage initiation considering the residual strength of the ply. The obtained results indicate a sufficiency of using S-N curves for UD 0°, UD 45°, and UD 90° for identification of the model. The model was verified by S-N curves for UD 10°, UD 15°, and UD 30° and its applicability was demonstrated for prediction of a fatigue life of composite laminates with an arbitrary lay-up. The model is implemented into ABAQUS finite element software as a user subroutine.

Keywords: damage initiation; fatigue; fiber-reinforced polymer composites; finite element analysis; residual strength.

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Conflict of interest statement

The authors declare no conflict of interest.

Figures

Figure 1
Figure 1
Fatigue failure in multilayered FRPs: (a) Formation of cracks, i.e., damage accumulation; (b) Stiffness reduction for the described failure stages [14,15].
Figure 2
Figure 2
The CLD diagram illustration: A vertical axis—the alternate stress; A horizontal axis—the mean stress [21].
Figure 3
Figure 3
The FDM workflow.
Figure 4
Figure 4
Assumptions accepted: (a) Linear interpolation between S-N curves for a predefined R-ratios; (b) Proportional to stress stiffness reduction.
Figure 5
Figure 5
The samples geometry.
Figure 6
Figure 6
Approximated CLDs and S-N curves based on data [34] used in the FDM as lamina fatigue properties. S-N curves: (a) UD 0°, (c) UD 45°, (e) UD 90°. The CLDs: (b) UD 0°, (d) UD 45°, (f) UD 90°.
Figure 7
Figure 7
S-N curves used for verification of the FDM [29]: (a) UD 10°, (b) UD 15°, (c) UD 30°.
Figure 8
Figure 8
The finite element model for the FDM verification.
Figure 9
Figure 9
Comparison between experimental and predicted S-N curves of UD 10, 15, 30° for R = 0.1.
Figure 10
Figure 10
Comparison between experimental and predicted S-N curves of UD 10, 15, 30° for R = 10.
Figure 11
Figure 11
Comparison between experimental and predicted S-N curves of UD 10, 15, 30° for Rcrit (combined tension-compression mode).
See this image and copyright information in PMC

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