Nonlinear constant fatigue life diagrams for carbon/epoxy laminates at room temperature

Kawai, M.; Koizumi, Masatoshi

doi:10.1016/j.compositesa.2007.01.016

Cited by 107 publications

(109 citation statements)

References 19 publications

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“…For laminates exhibiting significantly higher tensile strength than compressive strength, e.g. unidirectional carbon/ epoxy laminates [8], the CLD is shifted towards the right, tension-dominated domain. For materials exhibiting higher compressive than tensile fatigue properties, e.g.…”

Section: Introductionmentioning

confidence: 99%

“…The main parameters that define a CLD are the cyclic mean stress, stress amplitude and number of fatigue cycles. The CLDs for composite materials are usually shifted towards the tension-or compression-dominated domain, reflecting the degree of anisotropy of the examined material [8][9][10][11][12][13][14]. For laminates exhibiting significantly higher tensile strength than compressive strength, e.g.…”

Section: Introductionmentioning

confidence: 99%

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Experimental investigation and modeling of mean load effect on fatigue behavior of adhesively-bonded pultruded GFRP joints

Sarfaraz

Vassilopoulos

Keller

2012

International Journal of Fatigue

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental investigation and modeling of mean load effect on fatigue behavior of adhesively-bonded pultruded GFRP joints

Sarfaraz

Vassilopoulos

Keller

2012

International Journal of Fatigue

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“…The S-N lines are sections parallel to the N axis and the CL lines are presented in the V m -V a plane and are valid for one number of cycles. In this study, constant amplitude fatigue data was generated for a carbon fiber composite and constant fatigue life (CFL) diagram [5][6][7] is constructed which could be used further for accurate prediction of fatigue life under any given VA load sequence.…”

Section: Introductionmentioning

confidence: 99%

Construction of constant fatigue life diagram for a carbon fiber composite

Thawre

Paretkar

Peshwe

et al. 2011

Trans Indian Inst Met

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Using the constant amplitude fatigue data at various stress ratios, the constant fatigue life (CFL) diagram was constructed for the CFC material which is useful in prediction of fatigue life under variable amplitude fatigue loads. A quasi-isotropic lay-up sequenced carbon fiber-epoxy composite (CFC) laminate was fabricated by resin infusion technique. The tensile and compression tests were carried out to determine the static strength of the material. About 175 mm long, constant rectangular cross-sectioned fatigue test specimens were cut and prepared from the laminate. The stress-controlled, constant-amplitude fatigue tests were conducted in a 100 kN servo-hydraulic test machine, at room temperature and in lab air atmosphere. All the fatigue tests were performed with a sinusoidal waveform and a frequency of 1-3 Hz. The fatigue tests were conducted at four different stress ratio, R = V min /V max , Viz., 0.7,0.5 (tension-tension), -1.0 (tension-compression), and 4.0 (compression-compression). Anti-buckling guide was employed during the fatigue tests which involved compressive load cycles . The CFL Diagrams are material specific with predictive capability for any designed levels from selective experimental data.

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“…For the Kawai CLD, the model can be implemented by applying only one critical S-N curve, which is its basic characteristic [31,32]. e critical S-N curve is defined as the experimentally determined S-N curve at R value, where R value is the ratio of USC to UTS for the examined material.…”

Section: Kawai Cld Modelmentioning

confidence: 99%

“…An alleged heteromorphic CLD was derived by Kawai, and the model was established by introducing the "critical" S-N curve concept [31,32]. e ratio of ultimate compression strength (UCS) to ultimate tensile strength (UTS) was treated as the R value of the critical S-N curve for the examined material.…”

Section: Constant Life Diagram Modelsmentioning

confidence: 99%

Effect of Mean Stress on the Fatigue Life Prediction of Notched Fiber‐Reinforced 2060 Al‐Li Alloy Laminates under Spectrum Loading

Meng

Xie

Wang

et al. 2018

Advances in Materials Science and Engineering

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is paper presents a study on the fatigue life prediction of notched fiber-reinforced 2060 Al-Li alloy laminates under spectrum loading by applying the constant life diagram. Firstly, a review on the state of the art of constant life diagram models for the life prediction of composite materials is given, which highlights the effect on the forecast accuracy. en, the fatigue life of notched fiber-reinforced Al-Li alloy laminates (2/1 laminates and 3/2 laminates) is tested under cyclic stress, which has different stress cycle characteristics (constant amplitude loading and Mini-Twist spectrum loading). e introduced models are successfully realized based on the available experimental data of examined laminates. In the case of Mini-Twist spectrum loading, the effect of the constant life diagram on the life prediction accuracy of examined laminates is studied based on the rainflow-counting method and Miner damage criteria. e results show that the simple Goodman model and piecewise linear model have certain advantages compared to other complex models for the life prediction of notched fiber metal laminates with different structures under MiniTwist loading. From the engineering perspective, the S-N curve prediction based on the piecewise linear model is most applicable and accurate among all the models.

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Nonlinear constant fatigue life diagrams for carbon/epoxy laminates at room temperature

Cited by 107 publications

References 19 publications

Experimental investigation and modeling of mean load effect on fatigue behavior of adhesively-bonded pultruded GFRP joints

Experimental investigation and modeling of mean load effect on fatigue behavior of adhesively-bonded pultruded GFRP joints

Construction of constant fatigue life diagram for a carbon fiber composite

Effect of Mean Stress on the Fatigue Life Prediction of Notched Fiber‐Reinforced 2060 Al‐Li Alloy Laminates under Spectrum Loading

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