A new approach to the cohesive zone model that includes thermal effects

Ibrahim, Ghalib R.; Albarbar, Alhussein

doi:10.1016/j.compositesb.2019.03.003

Cited by 17 publications

(13 citation statements)

References 14 publications

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“…The damage variable is determined based on an effective separation and given by the following linear softening expression 16 where δm is an effective relative displacement under mixed mode loading conditions and is defined as …”

Section: Present Proposed Methods Based On Strain Failure Criteriamentioning

confidence: 99%

“…< 1). The damage variable is determined based on an effective separation and given by the following linear softening expression 16 !…”

Section: Damage Evolution Lawmentioning

confidence: 99%

“…Following the early stage, or in the case of a high energy impact, the damaged area expands in all directions with increase in pressure loading, which causes the gap between the two delamination lobes to disappear. When the friction coefficient is equal to or greater than 0.5, the intact zone in the damage area can be captured for laminate [0 3 /90 3 ] s , see contour plots in Figures 15(b) and 16. The predicted delamination shapes of laminate [90 3 / 0 3 ] s for friction factors, 0.3, 0.5, 0.75 and 0.9 under three levels of impact energy, are shown in Figure 17.…”

Section: Impact Energy 1jmentioning

confidence: 99%

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Effect of friction and shear strength enhancement on delamination prediction

Hameed

Ibrahim

Albarbar

2020

Journal of Composite Materials

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This study considers the intra-laminar damage mode in composite structures and its effect on delamination prediction. The progressive damage models for matrix cracking and fibre failure in ABAQUS, based on Hashin's model, are only available for shell elements. The results presented here show that the predicted matrix cracking based on the damage model presently available in ABAQUS diverges from experimental results. A new model based on strain failure criteria, which can be used with both shell elements and 3D solid elements, has been developed. The effect of friction coefficient and enhancement factor on the delamination lobes within the delamination area was investigated, and it is shown that the intact zone can be captured in laminate [03/903]s and [903/03]s subjected to low-velocity impact, by using an enhancement factor of η = 0.75, and friction coefficient [Formula: see text], together with the new model proposed here.

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Section: Present Proposed Methods Based On Strain Failure Criteriamentioning

confidence: 99%

“…< 1). The damage variable is determined based on an effective separation and given by the following linear softening expression 16 !…”

Section: Damage Evolution Lawmentioning

confidence: 99%

Section: Impact Energy 1jmentioning

confidence: 99%

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Effect of friction and shear strength enhancement on delamination prediction

Hameed

Ibrahim

Albarbar

2020

Journal of Composite Materials

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“…The quadratic nominal stress criterion to predict the onset of delamination under mixed mode loading is one of the most frequently adopted failure criteria. 25 This criterion has been successfully utilized by many researchers e.g. Hameed et al, 26 Zou and Hameed, 27 Belnoue et al 17 and Kawashita and Hallett, 12 and is written as;…”

Section: Developed Fatigue Damage Degradationmentioning

confidence: 99%

Progressive failure mechanism of laminated composites under fatigue loading

Ibrahim

Albarbar

Brethee

2020

Journal of Composite Materials

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A cohesive zone model for delamination propagation in laminated composites under static and fatigue loading has been derived and validated with experimental data under different mode conditions. This study presents a new approach to quantify fatigue delamination degradation based on damage mechanics to evaluate the rate of fatigue damage ([Formula: see text]). The static damage evaluation and fatigue damage degradation are derived from damage surface concept. Both static and fatigue damage linked each other to establish fatigue crack growth formula in the laminated composites. A user-defined subroutine, UMAT, has been employed to develop and implement a damage model in ABAQUS. Two different specimens; a double cantilever beam and a single lap joint were used to investigate the effectiveness of the new method. The simulation results revealed that the developed model had good agreement with experimental data available in literature.

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“…A modified thermal inclusive cohesive zone model was applied and validated by Ibrahim and Albarbar [21] by comparing their model results with literature data on composite laminates ranging from the lowest temperatures of -100 • C to the highest of 150 • C. The thermal expansion coefficient and effect of temperature parameters based on the Helmholtz free energy equation were included in the damage evolution law of cohesive zone elements. Moreover, fracture energy varies with temperature based on the square of peak traction stresses and interface penalty stiffness were estimated from the literature.…”

Section: Introductionmentioning

confidence: 99%

Thermal Delamination Modelling and Evaluation of Aluminium–Glass Fibre-Reinforced Polymer Hybrid

et al. 2021

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This paper aims to propose a temperature-dependent cohesive model to predict the delamination of dissimilar metal–composite material hybrid under Mode-I and Mode-II delamination. Commercial nonlinear finite element (FE) code LS-DYNA was used to simulate the material and cohesive model of hybrid aluminium–glass fibre-reinforced polymer (GFRP) laminate. For an accurate representation of the Mode-I and Mode-II delamination between aluminium and GFRP laminates, cohesive zone modelling with bilinear traction separation law was implemented. Cohesive zone properties at different temperatures were obtained by applying trends of experimental results from double cantilever beam and end notched flexural tests. Results from experimental tests were compared with simulation results at 30, 70 and 110 °C to verify the validity of the model. Mode-I and Mode-II FE models compared to experimental tests show a good correlation of 5.73% and 7.26% discrepancy, respectively. Crack front stress distribution at 30 °C is characterised by a smooth gradual decrease in Mode-I stress from the centre to the edge of the specimen. At 70 °C, the entire crack front reaches the maximum Mode-I stress with the exception of much lower stress build-up at the specimen’s edge. On the other hand, the Mode-II stress increases progressively from the centre to the edge at 30 °C. At 70 °C, uniform low stress is built up along the crack front with the exception of significantly higher stress concentrated only at the free edge. At 110 °C, the stress distribution for both modes transforms back to the similar profile, as observed in the 30 °C case.

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A new approach to the cohesive zone model that includes thermal effects

Cited by 17 publications

References 14 publications

Effect of friction and shear strength enhancement on delamination prediction

Effect of friction and shear strength enhancement on delamination prediction

Progressive failure mechanism of laminated composites under fatigue loading

Thermal Delamination Modelling and Evaluation of Aluminium–Glass Fibre-Reinforced Polymer Hybrid

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