Initiation of free-edge delamination in composite laminates

Lagunegrand, L.; Lorriot, T.; Harry, R.; Wargnier, Hervé; Quenisset, J.M.

doi:10.1016/j.compscitech.2005.10.010

Cited by 66 publications

(32 citation statements)

References 25 publications

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“…The interlaminar normal stress is not presented in this subsection, due to the assumption of that interlaminar compressive stress is able to delay delamination. This assumption is in agreement with the view of Reference [41]. In addition, shear stress distributions play a significant role in determining the mechanical behavior of multi-direction laminates.…”

Section: Stress Distributions At Each Interface Around the Hole Edge supporting

confidence: 80%

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Evaluation of Interlaminar Stresses in Composite Laminates with a Bolt-Filled Hole Using a Linear Elastic Traction-Separation Description

et al. 2017

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Determination of the local interlaminar stress distribution in a laminate with a bolt-filled hole is helpful for optimal bolted joint design, due to the three-dimensional (3D) nature of the stress field near the bolt hole. A new interlaminar stress distribution phenomenon induced by the bolt-head and clamp-up load, which occurs in a filled-hole composite laminate, is investigated. In order to efficiently evaluate interlaminar stresses under the complex boundary condition, a calculation strategy that using zero-thickness cohesive interface element is presented and validated. The interface element is based on a linear elastic traction-separation description. It is found that the interlaminar stress concentrations occur at the hole edge, as well as the interior of the laminate near the periphery of the bolt head. In addition, the interlaminar stresses near the periphery of the bolt head increased with an increase in the clamp-up load, and the interlaminar normal and shear stresses are not at the same circular position. Therefore, the clamp-up load cannot improve the interlaminar stress distribution in the laminate near the periphery of the bolt head, although it can reduce the magnitude of the interlaminar shear stress at the hole edge. Thus, the interlaminar stress distribution phenomena may lead to delamination initiation in the laminate near the periphery of the bolt head, and should be considered in composite bolted joint design.

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Section: Stress Distributions At Each Interface Around the Hole Edge supporting

confidence: 80%

“…σ z is a negative value in the clamp-up region, in other words, σ z is interlaminar compressive stress. According to Reference [41], the compression interlaminar stress is able to delay the delamination initiation. 3.…”

Section: Interlaminar Stress Distributions In the Filled-hole Laminatmentioning

confidence: 99%

Evaluation of Interlaminar Stresses in Composite Laminates with a Bolt-Filled Hole Using a Linear Elastic Traction-Separation Description

et al. 2017

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“…The results indicate that the layup influences the load at crack initiation where the different ply orientations cause high interlaminar stresses to develop. Consequently, for the standard layups the delamination is more likely to occur at the 0/90 and the 0/45 interfaces than at 0/0 due to the Poisson's ratio mismatch effect and shearextension coupling coefficients [35,36]. The mismatch effects at adjacent plies, which have different orientations, produce high interlaminar normal and shear stresses.…”

Section: Resultsmentioning

confidence: 94%

Effects of scratch damage on progressive failure of laminated carbon fiber/epoxy composites

Shams

Elhajjar

2013

International Journal of Mechanical Sciences

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“…It is to be noted that a different situation may be found in others laminates. For example, a ð15 2 =90= À15 2 Þ s laminate exhibits a significant tensile normal stress r 33 and an interlaminar shear stress r 13 at the (15/90) interface (Lagunegrand et al, 2006).…”

Section: Laminate Modelmentioning

confidence: 99%

“…Within this paper, this variational approach was employed to evaluate the stress distribution within ðAE10Þ s and ðAE20Þ s laminates under tensile loading. The geometry and the mechanical properties of the (G947/M18) carbon/epoxy laminates tested by (Lagunegrand et al, 2006) were used as reported in Table 1. First, Fig.…”

Section: Laminate Modelmentioning

confidence: 99%

A twofold strength and toughness criterion for the onset of free-edge shear delamination in angle-ply laminates

Martín

Leguillon

Carrère

2010

International Journal of Solids and Structures

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a b s t r a c tFree edge delamination in composite structures results from very localised stress fields which induce a stress concentration promoting the nucleation of an interfacial crack. To predict such a delamination onset at the free edge of a ðAEhÞ s laminate in traction, use is made of a strength and toughness criterion which combines a stress condition with an energy analysis. A generalised plane strain model allows to determine the stress distribution near the free edge and the energy released by the nucleation of an interfacial crack. The results show that this approach can predict the delamination onset for ððAE10Þ s ; ðAE20Þ s Þ laminates provided the interfacial fracture energy and interlaminar shear strength are known. These characteristic values can be identified with the help of traction tests performed on samples with different thicknesses.

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Initiation of free-edge delamination in composite laminates

Cited by 66 publications

References 25 publications

Evaluation of Interlaminar Stresses in Composite Laminates with a Bolt-Filled Hole Using a Linear Elastic Traction-Separation Description

Evaluation of Interlaminar Stresses in Composite Laminates with a Bolt-Filled Hole Using a Linear Elastic Traction-Separation Description

Effects of scratch damage on progressive failure of laminated carbon fiber/epoxy composites

A twofold strength and toughness criterion for the onset of free-edge shear delamination in angle-ply laminates

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