Prediction of the failure metal/composite bonded joints

Derewońko, A.

doi:10.1016/j.commatsci.2008.07.018

Cited by 14 publications

(5 citation statements)

References 5 publications

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“…Many researchers have been prompted by the significance of debonding failures in metal‐composite adhesive bonded joints to explore this type of deficiency by employing experimental, analytical, and numerical methods. Derwnko introduced a function for normal and frictional stresses of the interface in aluminum‐glass/epoxy composite adhesive joints. Using numerical and experimental approaches, Andre et al investigated the adhesive strength of steel‐CFRP structures in mode I, mode II, and mixed mode I/II.…”

Section: Introductionmentioning

confidence: 99%

Reliability analysis of metal‐composite adhesive joints under debonding modes I, II, and I/II using the results of experimental and FEM analyses

Delbariani-Nejad

Malakouti

Farrokhabadi

2019

Fatigue Fract Eng Mat Struct

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In the present study, the experimental and finite element (FE) analyses are first carried out to investigate the deboning behavior of metal‐composite adhesive joints under modes of I and mode II loading. To conduct an FE on the debonding propagation, cohesive zone method (CZM), as well as maximum nominal stress and energy criteria, is applied. In the reliability analysis, to achieve the probability of debonding growth (PODG), limit state functions are formulated based on the energy release rate. To that end, the first‐order reliability method (FORM), the second‐order reliability method (SORM), and the Monte Carlo simulation (MCS) are used to calculate the PODG. The effect of initial debonding length on the PODG in all mentioned modes is investigated. Results obtained from reliability analysis reveal that the random variables including the initial debonding length, width, and thickness are the most sensitive variables to ascertain the PODG.

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Section: Introductionmentioning

confidence: 99%

Reliability analysis of metal‐composite adhesive joints under debonding modes I, II, and I/II using the results of experimental and FEM analyses

Delbariani-Nejad

Malakouti

Farrokhabadi

2019

Fatigue Fract Eng Mat Struct

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“…The contact problem is modelled between composite layers and grips [3][4][5]. To perform contact analysis the penalty method was used [12].…”

Section: Fig 4 Overall Dimensions Of the Specimenmentioning

confidence: 99%

Carbon-Epoxy Composite Fatigue Strength – Experiment and Fem Numerical Estimation

Derewońko

Gieleta

2015

Journal of KONES. Powertrain and Transport

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The development of composite materials characterized by the constant amelioration of their mechanical properties (stiffness and strength) has widened their application for structural elements, mainly in aeronautical, naval and automobile industries. The possibility of tailoring the composite's properties appropriately to the applied load (by changing the direction of the fibre alignment and applying a corresponding matrix) results in the growing importance of the design process. The paper presents a numerical technique of determining the fatigue strength of the laminated carbon-epoxy composite. The experimental investigations were carried out to determine the complete set of the stiffness characteristics E ij , G ij , ij , the strength characteristics i,n , i,n. and the S-N fatigue curves. The static and fatigue numerical calculations were carried out for the material anisotropic model of the particular composite layers. Eight-node 3D finite elements with the composite's properties were used to develop the specimen's numerical model. The contact problem between the composite layers enabling the reflection of a mutual interaction was taken into account. The numerical investigation also included the state of effort analysis and the fatigue life assessment of the composite. The assessment of the composite's fatigue life was performed using the MSC.Fatigue code. The verification of models and numerical analysis was carried out for composite specimens made of the CE 8201-245-45/120 prepreg. The experimental verification confirmed that the places of the lowest fatigue life, found out in numerical analysis, are located in the area of the gauge part.

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“…[1][2][3][4] Several researchers have studied adhesive bonding between dissimilar materials focused in determination of the joint strength. The most commonly analyzed joint geometries are the single lap, [5][6][7] double lap, [8][9][10] scarf, [11][12][13][14] and tubular. [15][16][17] Adhesive bonded repair is a common application of adhesive joints involving bonding between dissimilar materials.…”

Section: Introductionmentioning

confidence: 99%

Fracture characterization of a bi‐material bonded aluminum/CFRP joints under mixed‐mode I + II loading

Moreira

Moura

Silva

et al. 2022

Fatigue Fract Eng Mat Struct

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Fracture characterization under mixed-mode I + II loading of bi-material bonded joints with aluminum-carbon fiber reinforced polymer (AL-CFRP) adherends was analyzed in this work. Five different and quite simple fracture tests were employed aiming to cover properly the complete mixed-mode I + II range and identifying a representative energy-based fracture criterion. A mode partitioning method lying on cohesive zone analysis was implemented, enabling the identification of strain energy mode I and mode II components for each type of test, which is relevant regarding the estimation of the energybased criterion defining the fracture envelope of these bi-material joints.

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Prediction of the failure metal/composite bonded joints

Cited by 14 publications

References 5 publications

Reliability analysis of metal‐composite adhesive joints under debonding modes I, II, and I/II using the results of experimental and FEM analyses

Reliability analysis of metal‐composite adhesive joints under debonding modes I, II, and I/II using the results of experimental and FEM analyses

Carbon-Epoxy Composite Fatigue Strength – Experiment and Fem Numerical Estimation

Fracture characterization of a bi‐material bonded aluminum/CFRP joints under mixed‐mode I + II loading

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