Irreversible constitutive law for modeling the delamination process using interfacial surface discontinuities

Goyal, Vinay K.; Johnson, Eric R.; Dávila, Carlos G.

doi:10.1016/j.compstruct.2003.11.005

Cited by 125 publications

(52 citation statements)

References 13 publications

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“…The FEA is implemented on the high-performance computer and the main configurations are: Intel Xeon CPU with 16 processors (the main frequency of each processor is 2.4 GHz) and 8GB memory. Each calculation takes about 1 h. Figures 7,8,9,10 ,11,12,13,14,15,16 and 17 shows the damage evolution processes for the fiber and matrix for the [0°/90°] 4s and [0°/45°] 4s laminates with a 10 mm-diameter hole. In the numerical subroutine, the status variables SDV7 and SDV8 represent the damage variables d 1 and d 2 in Eq.…”

Section: Strain Localization Problem and Nonlocal Integral Theorymentioning

confidence: 99%

Finite Element Analysis of Progressive Failure and Strain Localization of Carbon Fiber/Epoxy Composite Laminates by ABAQUS

Liu

Yang

et al. 2014

Appl Compos Mater

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Interaction mechanism between the intralaminar damage and interlaminar delamination of composite laminates is always a challenging issue. It is important to consider the progressive failure and strain softening behaviors simultaneously during the damage modeling and numerical simulation of composites using FEA. This paper performs three-dimensional finite element analysis of the progressive failure and strain localization of composites using FEA. An intralaminar progressive failure model based on the strain components is proposed and the nonlinear cohesive model is used to predict the delamination growth. In particular, the nonlocal integral theory which introduces a length scale into the governing equations is used to regularize the strain localization problems of composite structures. Special finite element codes are developed using ABAQUS to predict the intralaminar and interlaminar damage evolution of composites simultaneously. The carbon fiber/epoxy composite laminates with a central hole demonstrates the developed theoretical models and numerical algorithm by discussing the effects of the mesh sizes and layups patterns. It is shown the strain localization problem can be well solved in the progressive failure analysis of composites when the energy dissipation due to the damage of the fiber, matrix and interface occurs at a relatively wide area.

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Section: Strain Localization Problem and Nonlocal Integral Theorymentioning

confidence: 99%

Finite Element Analysis of Progressive Failure and Strain Localization of Carbon Fiber/Epoxy Composite Laminates by ABAQUS

Liu

Yang

et al. 2014

Appl Compos Mater

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“…PAM-CRASH includes penalty based tied interface elements that allow inter-laminar damage to be modelled at prespecified ply interfaces. To model a laminated composite material with interfaces, a "stacked shell" modelling approach is used to model the laminate as a number of sublaminates with interfaces tying them together [11][12][13][14][15][16]. A schematic representation of this…”

Section: Cohesive Zone Interface Modelmentioning

confidence: 99%

Numerical Investigation of Dynamically Loaded Bolted Joints in Carbon Fibre Composite Structures

Pearce

Johnson

Thomson³

et al. 2009

Appl Compos Mater

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This paper presents quasi-static and dynamic modelling of bolted composite structures using the explicit finite element code PAM-CRASH. User controlled point link (PLINK) elements were investigated for modelling the bolted composite joints used in the structures. Simulation results were compared with quasi-static and dynamic structural testing reported previously. Two loading configurations were considered. It was shown that the PLINK element modelling approach agreed well with the experimental results for both loading configurations and for one case offered significant improvements over other simplified bolt modelling methods. A stacked shell modelling approach was used to model the interlaminar delamination damage present in the ball-loaded impact mode. The overall response of the structure was significantly improved by the addition of these energy absorbing interfaces.

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“…Der Operator P transformiert zwischen dem virtuellen Verschiebungssprung δ∆ und den global definierten virtuellen Verschiebungen δu + und δu − an der oberen und unteren Seite der Grenzfl¨ache [1].…”

Section: Grenzflächenelementunclassified

Delaminationsberechnung von Faserverbundstrukturen

Fiolka

Matzenmiller

2005

Proc Appl Math and Mech

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Irreversible constitutive law for modeling the delamination process using interfacial surface discontinuities

Cited by 125 publications

References 13 publications

Finite Element Analysis of Progressive Failure and Strain Localization of Carbon Fiber/Epoxy Composite Laminates by ABAQUS

Finite Element Analysis of Progressive Failure and Strain Localization of Carbon Fiber/Epoxy Composite Laminates by ABAQUS

Numerical Investigation of Dynamically Loaded Bolted Joints in Carbon Fibre Composite Structures

Delaminationsberechnung von Faserverbundstrukturen

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