An investigation of matrix damage in composite laminates using continuum damage mechanics

Salavatian, M.; Smith, Lloyd

doi:10.1016/j.compstruct.2015.06.012

Cited by 16 publications

(4 citation statements)

References 15 publications

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“…where G d Ic , G d I Ic are the Mode I and II critical energy release rates of CZE, respectively after intralaminar damage, and D 1 , D 2 are the matrix damage variables at two intralaminar elements adjacent to a given CZE, which are given by Equation (5). This means that critical energy release rates of CZEs are not independent of matrix damage of the adjacent solid elements and vary with their damage variable, that is the CZEs are easily damaged with a high matrix damage level.…”

Section: Interaction Between Delamination and Intralaminar Failurementioning

confidence: 99%

“…The cohesive zone model (CZM) was recently used for simulating intralaminar failure [3,4], but the CZM approach has a shortcoming; it is difficult for CZM to describe arbitrary matrix cracks in composites. Continuous damage mechanics (CDM) of composite materials stands on its own as a mature field solidly having a variety of analytical and computational methodologies associated with it [5][6][7][8]. CDM theory was the first applied to study the creep rupture of materials [9], and the progressive damage failure analysis based on CDM has been widely employed to predict the damage initiation and evolution of composites.…”

Section: Introductionmentioning

confidence: 99%

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A Damage Model Reflecting the Interaction between Delamination and Intralaminar Crack for Failure Analysis of FRP Laminates

Yun¹,

Kwak²,

Wang

et al. 2019

Applied Sciences

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In this paper, a progressive damage model reflecting the interaction between delamination and intralaminar crack is developed to predict fracture behaviors and the ultimate load-bearing ability of the fiber-reinforced polymer laminates subject to quasi-static load. Initiation and evolution of intralaminar crack in composites are modeled using a continuum damage mechanics model, which has the capability to reliably predict the discrete crack direction by introducing the crack direction parameter while analyzing the multi-failure of FRP composites. Delamination is modeled using a cohesive zone method with the mixed bilinear law. When the continuum damage model and cohesive zone model are used together, the interactive behavior between multiple failure mechanisms such as delamination induced by matrix cracking often seen in the failure of composite laminates is not generally captured. Interaction between delamination and intralaminar crack in FRP composite structures is investigated in detail and reflected in a finite element analysis in order to eliminate the drawbacks of using both models together. Good agreements between numerical results and experimental data are obtained.

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Section: Interaction Between Delamination and Intralaminar Failurementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Damage Model Reflecting the Interaction between Delamination and Intralaminar Crack for Failure Analysis of FRP Laminates

Yun¹,

Kwak²,

Wang

et al. 2019

Applied Sciences

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“…Studies on the fracture mechanism made by impact damage and cracking have been conducted based on the micro/macro crack initiation and crack growth in the fiber and matrix of the composite. [3][4][5][6][7][8] However, because composites are inhomogeneous, and ply-stacked structures in general, it is common to have in-plane delamination and internal damage, which are difficult to detect and define as the standardized damage. As a result, statistical damage tolerance and probability analysis have been required.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Real world application of angular scan pulse-echo ultrasonic propagation imager for damage tolerance evaluation of full-scale composite fuselage

Lee

Seo

Hong

et al. 2019

Structural Health Monitoring

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Composite structures are assertively used for new airframe designs and manufacturing in military aircrafts because of superior strength-to-weight ratios and fatigue resistance. Because the composites have different fatigue failure characteristics compared with metals, it is necessary to develop different approaches for the composite fatigue design and testing. In this study, we propose an in situ damage evaluation technology with high spatial resolution during full-scale fatigue testing of composite aircraft structures. For real composite structure development considering composite fatigue characteristics, full-scale fatigue and damage tolerance tests of the composite fuselage structure were conducted to evaluate the structural characteristics. In the meantime, the laser ultrasonic nondestructive inspection method, called an angular scan pulse-echo ultrasonic propagation imager, which is fully noncontact, real-time, and portable to position it in between the complex test rigs, is used to observe in situ damage growth of the composite. Finally, the verification procedure assisted by the angular scan pulse-echo ultrasonic propagation imager assures no growth of the initial impact damages after lifetime operation and proves the damage tolerance capability of the developed composite fuselage structure.

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Silk Biocomposites: Structure and Chemistry

Morin

Pahlevan

Alam

2017

Handbook of Composites From Renewable Materials

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An investigation of matrix damage in composite laminates using continuum damage mechanics

Cited by 16 publications

References 15 publications

A Damage Model Reflecting the Interaction between Delamination and Intralaminar Crack for Failure Analysis of FRP Laminates

A Damage Model Reflecting the Interaction between Delamination and Intralaminar Crack for Failure Analysis of FRP Laminates

Real world application of angular scan pulse-echo ultrasonic propagation imager for damage tolerance evaluation of full-scale composite fuselage

Silk Biocomposites: Structure and Chemistry

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