Multiscale finite element analysis of mode I delamination growth in a fabric composite

Yamanaka, Tadayoshi; Ghiasi, Hossein; Heidari-Rarani, M.; Lessard, Larry; Feret, Victor; Hubert, Pascal

doi:10.1016/j.compstruct.2015.07.094

Cited by 15 publications

(8 citation statements)

References 35 publications

(38 reference statements)

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“…Yamanaka [18] used the VCCT method for the numerical modeling of Mode-I interlaminar fracture in the doctoral thesis. Pereira and Morais [19] used the VCCT method to evaluate the Mode-I interlaminar fracture of carbon/epoxy multidirectional laminates.…”

Section: Vcctmentioning

confidence: 99%

Mode-I Interlaminar Fracture Modeling of DCB Composite Laminate using Finite Element Techniques

Sharma

Mali

Dixit

2023

Preprint

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The interlaminar fracture is the most common type of failure in polymeric textile composites because these composites are prone to delaminate under the influence of external loading. Depending on the type of deformation, the interlayer fracture can be Mode-I, Mode-II, Mode-III, and Mixed Mode-I/II type. In this research work, Mode-I interlaminar fracture modeling of carbon fiber reinforced polymer (CFRP) composite laminate is performed using a double cantilever beam (DCB) test specimen on ABAQUS software as a cost-effective numerical simulation approach. The finite element based fracture modeling techniques, virtual crack closure technique (VCCT), cohesive zone modeling (CZM), and extended finite element method (XFEM) were employed under the two-dimensional and three-dimensional interlayer crack propagation to evaluate the load-displacement responses. The interaction properties were applied between the top and bottom part of DCB specimen and the adhesive layer was modeled using the CZM approach. The numerically simulated responses were compared with the published experimental load-displacement responses and found to be in good agreement. All the fracture modeling approaches validate the experimental trend, however the three-dimensional XFEM technique was found to be the most suitable modeling approach for crack growth in adhesively bonded parts. The stress based criteria was used for crack initiation, whereas the energy based approach used for crack propagation in DCB laminate. The parametric study of various fracture parameters (cohesive strength, fracture energy, interfacial stiffness, laminate thickness, and pre-crack length) were also conducted to understand their effects on load-displacement responses of the Mode-I interlaminar fracture. The fracture modeling approaches were compared by considering the element type, shape, total elements, accuracy, run-time, increments, and convergence speed.

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Section: Vcctmentioning

confidence: 99%

Mode-I Interlaminar Fracture Modeling of DCB Composite Laminate using Finite Element Techniques

Sharma

Mali

Dixit

2023

Preprint

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“…Previous attempts to model delamination migration in multidirectional laminates were restricted to mesoscale models, using homogenised composite plies [15,16,17,18,19,20], and thus did not provide enough detail to capture microscale features such as the full migration history, including inititation and intralaminar propagation, the role of the different constituents (particularly the role of fibre-matrix interface), or the effect of ply thickness and orientation. Other studies have addressed interlaminar damage evolution of multidirectional reinforcements using mesoscale modelling approaches, but have not specifically addressed the delamination relocation issue [28,29].…”

Section: Introductionmentioning

confidence: 99%

Micromechanical analysis of interlaminar crack propagation between angled plies in mode I tests

Varandas

Arteiro

Catalanotti

et al. 2019

Composite Structures

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This paper presents a micromechanical finite element model to study interlaminar damage propagation and relocation, known as delamination migration, between angled plies, consisting of a double-ply θ/0 • Unit Cell (UC) in-between homogenised unidirectional 0 • plies. Random fibre distributions and appropriate constitutive models are used to model the different dissipative phenomena that occur at crack onset and propagation. Varying the upper ply fibres orientation, θ, and ply thickness, it is possible to assess their influence on the damage migration mechanism. Different features associated with delamination migration are analysed, such as the distribution of interlaminar shear stresses at the crack tip and the kink angles. When comparing the results of the micromechanical model with previously conducted experimental observations, similar trends are obtained. It is concluded that the computational framework is able to simulate mode I interlaminar damage propagation and delamination migration in multidirectional laminates, providing a sound tool to better understand the conditions behind interlaminar crack migration.

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“…Micro-scale models and multi-scale models describing the properties of composite materials have been sprung up recent years. In these models, the information about fibers, resin, interface, weaving details of the fabric and various kinds of defects were included [20,21,22,23,24]. In this paper, we aim to create a model to study the details about when a crack initiates and how it propagates without pre-cracks and the correlation of the laminate’s elastic properties to the cracks.…”

Section: Introductionmentioning

confidence: 99%

A Simplified Computational Strategy Focused on Resin Damage to Study Matrix Cracking of The Cross-Ply Laminates Under Uniaxial Tension Load

Sun

Wang

et al. 2019

Materials

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Transverse cracking is probably the first and most dominant mode of damage in composite materials. In this paper, transverse cracking of cross-ply [02/90n]s (n = 2,3,4) laminates under uniaxial tension load was studied by means of experimental and numerical methods. In the numerical simulations, a simplified computational strategy only focusing on the damage of the resin was proposed and the mechanical response of the cracking cross-ply laminates was studied by finite element analysis of multi-scale representative volume elements (RVEs). In the RVEs, the longitudinal 0° plies were represented by macro-scale, homogeneous, orthotropic elastic solids while the 90° plies were modeled by the discrete fibers and the surrounding matrix resin in micro-scale. Based on researching the critical longitudinal mechanical strain ε x which initiates the cracks, the in-situ transverse ply strength and the stiffness degradation of the transverse plies, the simplified computational strategy proposed was proven correct. In addition, the crack initiation is sensitive to residual stress. Higher process-induced residual stress levels are dangerous to laminates, leading to early crack initiation.

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Multiscale finite element analysis of mode I delamination growth in a fabric composite

Cited by 15 publications

References 35 publications

Mode-I Interlaminar Fracture Modeling of DCB Composite Laminate using Finite Element Techniques

Mode-I Interlaminar Fracture Modeling of DCB Composite Laminate using Finite Element Techniques

Micromechanical analysis of interlaminar crack propagation between angled plies in mode I tests

A Simplified Computational Strategy Focused on Resin Damage to Study Matrix Cracking of The Cross-Ply Laminates Under Uniaxial Tension Load

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