Delamination growth in composite laminates of variable stiffness

Yazdani, Saleh; Rust, Wilhelm; Wriggers, Peter

doi:10.1002/nme.5264

Cited by 14 publications

(3 citation statements)

References 32 publications

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“…Butler et al [27] applied the finite strip method to study the compression after impact (CAI) performance of delaminated VAT composite plates. Yazdani et al [28] utilized XFEM (Extended Finite Element Method) to analyze the delamination propagation of VAT composite laminates. To the best of the authors' knowledge, no research has been reported in which an attempt has been made to investigate the buckling behaviour of VAT composite plates with delaminations.…”

Section: Accepted Manuscriptmentioning

confidence: 99%

Buckling analysis of variable angle tow composite plates with a through-the-width or an embedded rectangular delamination

Chen

Nie

et al. 2018

International Journal of Solids and Structures

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Variable angle tow (VAT) composite laminates, in which fibre orientation varies spatially in-plane in a continuous fashion yet is piecewise constant through-thickness, have been made possible by advanced automated fibre placement technology. Such designs have shown considerable potential to improve the performance of lightweight composite structures. In the present study, an analytical model is developed to study the buckling behaviour of VAT composite plates with a through-the-width or an embedded rectangular delamination under compression loadings. The proposed model can accurately capture the global, local and mixed buckling response of delaminated VAT composite plates. Both free and constrained modes are assumed in the delamination buckling analysis. A constrained point approach is employed to analyze the buckling response when contact occurs between delaminated layers. The accuracy and reliability of this proposed delamination buckling model is validated by finite element analysis and with prior results. The influence of delamination size, position and varying fibre orientation angles on the buckling response of delaminated VAT compositeplates is studied by numerical examples. It is shown that the buckling loads decrease with an increase of the delamination size. The VAT laminates with an off-midplane delamination may lead to the delamination opening up, which further reduces the buckling loads. Finally, the mechanism of taking advantages of VAT laminates to improve the buckling performance of delaminated composite plates is thoroughly investigated in a parametric study. This study also shows that the residual buckling resistance of the delaminated composite plates can be significantly improved through using the VAT design concept.

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Section: Accepted Manuscriptmentioning

confidence: 99%

Buckling analysis of variable angle tow composite plates with a through-the-width or an embedded rectangular delamination

Chen

Nie

et al. 2018

International Journal of Solids and Structures

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“…the geometric equation g − = 0, the constitutive equation W − = 0, the equilibrium of higher order stress resultants (29) and the constraint (33). Thus, it holds…”

Section: Boundary Value Problem Weak Form and Linearizationsmentioning

confidence: 99%

“…26 The extended finite element method (XFEM) is enlarged for delamination problems in other works. [27][28][29][30][31] Delamination initiation analyses are often based on stress criteria. Especially, the interlaminar stresses as driving forces for this type of failure mode must be known.…”

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confidence: 99%

A shell element for the prediction of residual load‐carrying capacities due to delamination

Gruttmann

Knust

2019

Numerical Meth Engineering

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This paper deals with layered plates and shells subjected to static loading. The kinematic assumptions are extended by a jump function in dependence of a damage parameter. Additionally, an intermediate layer is arranged at any position of the laminate. This allows numerical simulation of onset and growth of delaminations. The equations of the boundary value problem include besides the equilibrium in terms of stress resultants, the local equilibrium in terms of stresses, the geometric field equations, the constitutive equations, and a constraint which enforces the correct shape of a superposed displacement field through the thickness as well as boundary conditions. The weak form of the boundary value problem and the associated finite element formulation for quadrilaterals is derived. The developed shell element possesses the usual 5 or 6 degrees of freedom at the nodes. This is an essential feature since standard geometrical boundary conditions can be applied and the elements are applicable to shell intersection problems. With the developed model, residual load-carrying capacities of layered shells due to delamination failure are computed. KEYWORDSdamage model, layered plates and shells, progressive delaminations, standard nodal degrees of freedom, thin intermediate layers INTRODUCTIONDelamination, or interfacial cracking between layers, is one of the most common types of damage in laminated fibre-reinforced composite structures. The reason is the relative weak interlaminar strength. Delamination as result of impact or manufacturing defect can cause a significant reduction of the load-carrying capacity of a structure. In general, the fracture process in high performance composite laminates is quite complex, involving not only delamination but also occurrence of transverse matrix cracking or fibre fracture in the layers. Stress gradients that occur near geometric discontinuities such as ply drop-offs, stiffener terminations, bonded and bolted joints, and access holes promote delamination initiation, trigger intraply damage mechanisms, and may cause a significant loss of structural integrity. Thus, a reliable prediction of different failure modes is essential. The delamination failure mode is particularly important for the structural integrity of composite structures because it is difficult to detect during inspection.The simulation of delamination using the finite element method is performed by means of the virtual crack closure technique, eg, in the works of Rybicki and Kanninen 1 and Krueger, 2 or using cohesive finite elements, eg, in other works. [3][4][5][6][7][8][9][10][11][12][13][14][15][16][17] Another approach is to use continuum damage models within the layers, eg, in the works of Simon et al, [18][19][20] or to introduce thin intermediate layers along with a damage model or an inelastic material model with softening, eg, in the works 132 of Allix and Ladevèze, 21 Wagner et al, 22 and Groh et al. 23 In the works of Remmers et al, 24,25 the kinematics of solid-like shell elements is enhanced to allow for...

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Modeling Fracture in Straight Fiber and Tow-Steered Fiber Laminated Composites—A Phase Field Approach

Hirshikesh

Annabattula

Natarajan

2021

Materials Horizons: From Nature to Nanomaterials

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Delamination growth in composite laminates of variable stiffness

Cited by 14 publications

References 32 publications

Buckling analysis of variable angle tow composite plates with a through-the-width or an embedded rectangular delamination

Buckling analysis of variable angle tow composite plates with a through-the-width or an embedded rectangular delamination

A shell element for the prediction of residual load‐carrying capacities due to delamination

Modeling Fracture in Straight Fiber and Tow-Steered Fiber Laminated Composites—A Phase Field Approach

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