An overview of continuum damage models used to simulate intralaminar failure mechanisms in advanced composite materials

Forghani, Alireza; Shahbazi, Mehdi; Zobeiry, Navid; Poursartip, Anoush; Vaziri, Reza

doi:10.1016/b978-0-08-100332-9.00006-2

Cited by 16 publications

(9 citation statements)

References 81 publications

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“…It is worth mentioning that the presented global-local strategy is not restricted to the particular intralaminar failure criterion used and other criteria such as LaRC04 by Pinho et al [16] [20] and Kaddour et al [21]. Material degradation models are reviewed in [22] and more recently in [23]. However, the particular choice of the Linde criterion is explained by the aim to obtain reliable results at a relatively low computational costs with an accurate material model, but also with a reasonably simple model that is not excessively demanding in terms of material model parameters required.…”

Section: Detailed Methodology: Two-way Loose Coupling Approach Wmentioning

confidence: 99%

Progressive Failure Analysis Using Global-Local Coupling Including Intralaminar Failure and Debonding

et al. 2019

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Composite laminate stiffened panels are often used in aircraft fuselage design because of their favourable properties. To assess the failure load of these thin-walled structures and to exploit their reserves, a reliable simulation capability for their postbuckling behaviour is often necessary. To perform a realistic failure analysis and to accurately detect final collapse, material degradation should be considered. Global-local approaches are computationally efficient techniques to perform a progressive failure analysis and to examine localized damaged areas in detail. In this paper, a two-way coupling global-local approach is presented, including a combination of different damage modes, such as matrix cracking, fiber damage and skin-stringer debonding. An accurate exchange of information concerning the damage state between global and refined local models is performed. From the global to the local model, the displacements are transferred through a submodeling procedure. Afterwards, the degraded material properties obtained from the local model analysis are returned to the global model with a special mapping technique that accounts for the different mesh sizes at the two levels. The two-way coupling procedure is applied to the progressive failure analysis of a one-stringer composite panel loaded in compression. Finally, the numerical results of the procedure are compared with experimental results.

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Section: Detailed Methodology: Two-way Loose Coupling Approach Wmentioning

confidence: 99%

Progressive Failure Analysis Using Global-Local Coupling Including Intralaminar Failure and Debonding

et al. 2019

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“…The bibliography on distributed damage in composite laminates is extensive. 46,47 Among the multitude of damage models available, discrete damage mechanics (DDM) 48 is attractive for this study because, in addition to the usual elastic properties, it requires only two values of critical energy release rate (critical ERR), G Ic and G IIc , to predict both damage initiation and evolution due to transverse and in-plane shear stresses for general laminates subjected to general loads. 49 DDM is an objective (mesh independent) constitutive model, meaning that when implemented in FEM software, it does not require guessing of characteristic length L c in order to reduce mesh dependency.…”

Section: Discrete Damage Mechanicsmentioning

confidence: 99%

Damage initiation and evolution during monotonic cooling of laminated composites

Barbero

2018

Journal of Composite Materials

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The objective of this work is to develop a methodology to predict matrix damage initiation and evolution in laminated composites subjected to monotonic cooling using discrete damage mechanics and a careful characterization of the required temperature-dependent material properties. Since prediction of thermo-mechanical damage requires precise knowledge of the temperature-dependent properties of the material, back-calculation of fiber and matrix properties from different sources is included. The proposed methodology is flexible, in that it can be adapted to the availability of experimental data. A compilation of literature data is developed to estimate the properties of several fiber and matrix systems. Prediction of lamina and laminate temperature-dependent properties are compared with available data. Furthermore, temperature-dependent fracture toughness of four material systems are estimated from available crack density data. For the material systems studied, it is found that temperature-independent fracture toughness is satisfactory for prediction of damage initiation, evolution, and saturation.

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“…In recent years, more advanced progressive damage models, in which the application of failure criteria to predict damage initiation is associated with procedures for continuous degradation of material properties [22,23], have been increasingly employed to investigate the low-velocity impact behaviour of sandwich composites. A general strategy that has become frequently adopted to simulate damage in the composite skins involves the combined use of continuum damage mechanics (CDM) methods [24] to model in-ply matrix cracking and fibre fracture with cohesive elements [25] to represent cracks at locations known a priori, such as delaminations at interfaces between layers of different orientations. Energy-based procedures are generally incorporated in both CDM and cohesive models to introduce a gradual decrease of the elastic properties due to damage [22].…”

Section: Introductionmentioning

confidence: 99%

A Numerical and Experimental Investigation into the Impact Response of Sandwich Composites under Different Boundary Conditions

2022

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The paper reports the results of an experimental and numerical investigation into the effect of the support conditions on the low velocity impact behaviour of sandwich composite panels. Significant differences are observed experimentally between the structural and damage responses to impact of small-span and large-span sandwich panels. In particular, impact events on large-span panels generate lower peak forces, larger displacements and smaller damage sizes in comparison to small-span panels subjected to the same impact energy. The experimental results are employed to validate the capability of a finite element (FE) tool to simulate the impact behaviour of the sandwich panels for the different boundary conditions. The comparison of FE and experimental results shows that the model provides a good prediction of the structural response as well as of the extent and mechanisms of impact damage for both small-span and large-span lengths, thus demonstrating the potential of the FE tool for verification and design of sandwich components in real engineering applications.

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An overview of continuum damage models used to simulate intralaminar failure mechanisms in advanced composite materials

Cited by 16 publications

References 81 publications

Progressive Failure Analysis Using Global-Local Coupling Including Intralaminar Failure and Debonding

Progressive Failure Analysis Using Global-Local Coupling Including Intralaminar Failure and Debonding

Damage initiation and evolution during monotonic cooling of laminated composites

A Numerical and Experimental Investigation into the Impact Response of Sandwich Composites under Different Boundary Conditions

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