A Progressive Damage Model for Mechanically Fastened Joints in Composite Laminates

Camanho, P.P.; Matthews, F.L.

doi:10.1177/002199839903302402

Cited by 478 publications

(267 citation statements)

References 56 publications

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“…Based on existing micromechanical analyses, [17][18][19], Camanho et al [20] have proposed the following reduction, used in this work:…”

Section: Effect Of Damage In the Elastic Propertiesmentioning

confidence: 99%

Numerical simulation of the crushing process of composite materials

Pinho¹,

Camanho²,

Moura³

2004

International Journal of Crashworthiness

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Components in composite materials are progressively replacing metals for crashworthy applications in the automotive, railway and aeronautical industries. The numerical simulation of the crushing process for composite structures is a recent research area. Due to the complex mechanical behaviour of advanced composites, the capability of the existing analytical and numerical models to predict the crushing behaviour of composite materials is still limited.A numerical model for the crushing simulation of fibre-reinforced composite materials is proposed in this work. The progression of the main cracks is modelled using * DEMEGI, Faculdade de Engenharia, Universidade do Porto, Portugal; currently at the De-

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“…Based on existing micromechanical analyses, [17][18][19], Camanho et al [20] have proposed the following reduction, used in this work:…”

Section: Effect Of Damage In the Elastic Propertiesmentioning

confidence: 99%

Numerical simulation of the crushing process of composite materials

Pinho¹,

Camanho²,

Moura³

2004

International Journal of Crashworthiness

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“…Failure criteria that consider out of plane stresses as Hashin [27] have been applied to predict bearing failure in double lap [4,9] and bolted single lap joints [28,29]. These studies have proved the influence of out of plane stresses on bearing strength, however there is a lack of studies that consider both out of plane stresses and non linear shear stress strain relationship.…”

Section: Introductionmentioning

confidence: 99%

On the prediction of bolted single-lap composite joints

Olmedo

Santiuste

2012

Composite Structures

156

103

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a b s t r a c tA new set of failure criteria to predict composite failure in single lap bolted joints is proposed. The pres ent failure criteria are an extension of Chang Lessard criteria considering a three dimensional stress field and including out of plane failure modes. The advantage with respect to other three dimensional failure criteria is the consideration of non linear shear stress strain relationship. The failure criteria were imple mented in a finite element model and validated through comparison with experiments in literature. Stresses were calculated by a non linear finite element model developed in ABAQUS/Standard which con siders material and geometric nonlinearities. A progressive damage model was implemented in a USDFLD subroutine. The model predicted the effect of secondary bending and tightening torque showing an excel lent agreement with experimental results. Moreover, results were compared with those reported in lit erature using Hashin failure criteria. In addition, a parametric study was carried out to analyse the influence of friction coefficient and tightening torque.

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“…The degradation equations are given in Reference [21]. Furthermore, in the finite element models, the material softening laws with Tsai-Wu failure criteria have been implemented using user defined subroutines USDFLD (User subroutine to redefine field variables at a material point) of Abaqus (Version 6.11, Dassault systemes simulia Corp, Providence, RI, USA, 2011).…”

Section: Failure and Softening Formulation For Fibermentioning

confidence: 99%

“…A 3D progressive failure model [21] is used to predict the final failure of composites tows. This failure model connects the material elastic properties with internal state variables that functions of the type of damage.…”

Section: Failure Model For Composites Towsmentioning

confidence: 99%

Estimation of Lamina Stiffness and Strength of Quadriaxial Non-Crimp Fabric Composites Based on Semi-Laminar Considerations

et al. 2016

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Quadriaxial non-crimp fabric (QNCF) composites are increasingly being used as primary structural materials in aircraft and automotive applications. Predicting the mechanical properties of QNCF lamina is more complicated compared with that of unidirectional (UD) composites, because of the knitting connection of different plies. In this study, to analyze the stiffness and strength of the QNCF composites, a novel modeling strategy for the meso-scale features is presented based on the semi-laminar assumption. Following the view of the mechanical properties of single composite lamina, the complex QNCF layer is decomposed into individual plies. Three different representative unit cells along fiber direction are selected to predict the mechanical performance of QNCF, including in-plane stiffness, damage initiation, and stiffness degradation. To validate the developed modeling strategy, the predictions are compared with existing experimental results, where a good agreement is presented on the prediction of in-plane stiffness and strength. Furthermore, the effect of in-plane fiber distortion, induced by the stitching yarn on the mechanical properties, is studied.

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A Progressive Damage Model for Mechanically Fastened Joints in Composite Laminates

Cited by 478 publications

References 56 publications

Numerical simulation of the crushing process of composite materials

Numerical simulation of the crushing process of composite materials

On the prediction of bolted single-lap composite joints

Estimation of Lamina Stiffness and Strength of Quadriaxial Non-Crimp Fabric Composites Based on Semi-Laminar Considerations

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