Progressive Fatigue Damage Modeling of Composite Materials, Part I: Modeling

Shokrieh, M.M.; Lessard, Larry

doi:10.1106/ncnx-dxp1-jt6a-e49e

Cited by 93 publications

(185 citation statements)

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“…In the latter (older) approach, certain stiffness components of solid elements are reduced according to some formula when the element experiences a critical state of stress or strain. Good examples are in (Shokrieh and Lessard, 2000) and (Chang et al, 1991) and the literature cited therein. Micromechanical arguments can be used to specify both the critical condition and the reduction formulae, including statistical variance.…”

Section: Non-prescribed Crack Pathsmentioning

confidence: 98%

“…For in-plane failure, various material property degradation models have been proposed in an effort to describe the load redistribution associated with damage accumulation (Chang et al, 1991;Shokrieh and Lessard, 2000). Classical laminate theories are used to compute the in-plane stress state and then the stresses (or strains) are used to evaluate failure criteria for different possible failure mechanisms at material points of interest.…”

Section: Early Models Of Single and Multiple Damage Mechanismsmentioning

confidence: 99%

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Cohesive models for damage evolution in laminated composites

2005

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A trend in the last decade towards models in which nonlinear crack tip processes are represented explicitly, rather than being assigned to a point process at the crack tip (as in linear elastic fracture mechanics), is reviewed by a survey of the literature. A good compromise between computational efficiency and physical reality seems to be the cohesive zone formulation, which collapses the effect of the nonlinear crack process zone onto a surface of displacement discontinuity (generalized crack). Damage mechanisms that can be represented by cohesive models include delamination of plies, large splitting (shear) cracks within plies, multiple matrix cracking within plies, fiber rupture or microbuckling (kink band formation), friction acting between delaminated plies, process zones at crack tips representing crazing or other nonlinearity, and large scale bridging by through-thickness reinforcement or oblique crack-bridging fibers. The power of the technique is illustrated here for delamination and splitting cracks in laminates. A cohesive element is presented for simulating three-dimensional, modedependent process zones. An essential feature of the formulation is that the delamination crack shape can follow its natural evolution, according to the evolving mode conditions calculated within the simulation. But in numerical work, care must be taken that element sizes are defined consistently with the characteristic lengths of cohesive zones that are implied by the chosen cohesive laws. Qualitatively successful applications are reported to some practical problems in composite engineering, which cannot be adequately analyzed by conventional tools such as linear elastic fracture mechanics and the virtual crack closure technique. The simulations successfully reproduce experimentally measured crack shapes that have been reported in the literature over a decade ago, but have not been reproduced by prior models.

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Section: Non-prescribed Crack Pathsmentioning

confidence: 98%

Section: Early Models Of Single and Multiple Damage Mechanismsmentioning

confidence: 99%

Cohesive models for damage evolution in laminated composites

2005

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“…As mentioned by Adam et al [26], fatigue normalization model can be used for similar scientific phenomena. In a performed by Shokrieh [27] the following equation is developed for strength degradation of a unidirectional ply under fatigue loading condition: Physics of the problem in fatigue behavior of composites is very similar to SCC of composites. As it is seen from previous decades in different research, SCC phenomenon is named as static fatigue [16,[28][29][30][31][32][33].…”

Section: Scc Normalized Strength Degradation Modelmentioning

confidence: 99%

“…In current research, to express loss properties of the composites under stress corrosion, the model presented by Shokrieh [27] for fatigue of composites is employed and SCC normalized strength degradation model is presented. By replacing n (number of loading cycles) with t (stress corrosion exerting time), N F (number of cycles to failure) with T F (stress corrosion time to failure), and omitting log0.25, because of non-existence of such a term in a SCC phenomenon, in Eq.…”

Section: Scc Normalized Strength Degradation Modelmentioning

confidence: 99%

Stress Corrosion Cracking of Basalt/Epoxy Composites under Bending Loading

Shokrieh

Memar

2009

Appl Compos Mater

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The purpose of this research is to study the stress corrosion behavior of basalt/ epoxy composites under bending loading and submerged in 5% sulfuric acid corrosive medium. There are limited numbers of research in durability of fiber reinforced polymer composites. Moreover, studies on basalt fibers and its composites are very limited. In this research, mechanical property degradation of basalt/epoxy composites under bending loading and submerged in acidic corrosive medium is investigated. Three states of stress, equal to 30%, 50% and 70% of the ultimate strength of composites, are applied on samples. High stress states are applied to the samples to accelerate the testing procedure. Mechanical properties degradation consists of bending strength, bending modulus of elasticity and fracture energy of samples are examined. Also, a normalized strength degradation model for stress corrosion condition is presented. Finally, microscopic images of broken cross sections of samples are examined.

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“…Concerning the intralaminar damage, different failure criteria are available in literature for the individuation of the first ply failure load such as the Hashin's criteria [17,18] whose peculiar characteristic is that they allow distinguishing among different failure modes.…”

Section: Introductionmentioning

confidence: 99%

A Global/Local Finite Element Approach for Predicting Interlaminar and Intralaminar Damage Evolution in Composite Stiffened Panels Under Compressive Load

Pietropaoli

Riccio

2010

Appl Compos Mater

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This paper addresses the prediction of intralaminar and interlaminar damage onset and evolution in composite structures through the use of a finite element based procedure. This procedure joins methodologies whose credibility has been already assessed in literature such as the Virtual Crack Closure Technique (for delamination) and the ply discount approach (for matrix/fiber failures). In order to establish the reliability of the procedure developed, comparisons with literature experimental results on a stiffened panel with an embedded delamination are illustrated. The methodology proposed, implemented in ANSYS © as post-processing routines, is combined with a finite element model of the panel, built by adopting both shell and solid elements within the frame of an embedded global/local approach to connect differently modelled substructures.

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Progressive Fatigue Damage Modeling of Composite Materials, Part I: Modeling

Cited by 93 publications

References 0 publications

Cohesive models for damage evolution in laminated composites

Cohesive models for damage evolution in laminated composites

Stress Corrosion Cracking of Basalt/Epoxy Composites under Bending Loading

A Global/Local Finite Element Approach for Predicting Interlaminar and Intralaminar Damage Evolution in Composite Stiffened Panels Under Compressive Load

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