A numerical study on compressive behavior of composite plates with multiple circular delaminations considering delamination propagation

Suemasu, Hiroshi; Sasaki, Wataru; Ishikawa, Takashi; Aoki, Yoshio

doi:10.1016/j.compscitech.2008.05.014

Cited by 61 publications

(39 citation statements)

References 17 publications

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“…The mechanism is well illustrated by the detailed results of finite-element simulations with simplified circular delaminations [25] and more realistic spiral patterns of delaminations linked by transverse cracks [26]. Propagation of damage under compressive loading was modelled using cohesive elements.…”

Section: (B) Effect Of Delamination On Residual Strengthmentioning

confidence: 99%

The role of delamination in failure of fibre-reinforced composites

Wisnom

2012

Phil. Trans. R. Soc. A.

228

119

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The mechanisms by which delamination contributes to the failure of fibre-reinforced composites are reviewed. Through-thickness failure owing to interlaminar stresses is considered first, and the effect of delamination in impact and compression after impact. The way in which in-plane failure can occur by delamination and matrix cracks joining up to produce a fracture surface without the need to break fibres is considered next. Examples of quasi-isotropic laminates loaded at different off-axis angles, and with different numbers and thicknesses of ply blocks show large differences in unnotched tensile strength controlled by delamination from the free edge. Similar mechanisms determine the strength of notched specimens and give rise to the hole size effect, whereby tensile strength increases with decreasing hole diameter owing to increased delamination and splitting. Open hole tension and over-height compact tension tests with constant inplane dimensions show a transition in failure mode with increasing ply block thickness from fibre-dominated fracture to complete delamination. In all these cases, the critical factor controlling strength is the relative propensity to delaminate.

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Section: (B) Effect Of Delamination On Residual Strengthmentioning

confidence: 99%

The role of delamination in failure of fibre-reinforced composites

Wisnom

2012

Phil. Trans. R. Soc. A.

228

119

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“…The result of Suemasu et al [25] was used for this validation. The laminate has dimensions 100 mm x 150 mm x 3.2 mm, boundary conditions are the same as shown in Eq.…”

Section: Details Of Cai Modelmentioning

confidence: 99%

“…For the matrix cracks it is more appropriate to use the cohesive contact formulation since zero thickness is required and the contact formulation is easier to insert into the model in this case. Cohesive law-based interface elements are used in the paper for delamination prediction, because they have a number of advantages over other modeling approaches, such as the capacity to investigate both initiation and growth of damage, incorporating both strength and fracture based criteria [22][23][24][25][26]. Another added advantage is that the use of interface elements does not require an assumption of initial damage size or propagation direction.…”

Section: Introductionmentioning

confidence: 99%

A numerical study on impact and compression after impact behaviour of variable angle tow laminates

Dang

Hallett

2013

Composite Structures

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Recent developments of variable angled tow (VAT) technology have indicated that variable stiffness composite laminates offer a strong potential for structural tailoring. However, the design complexity requires use of numerical analysis and novel techniques for this type of structural composites. This paper addresses the problem of the impact and compression after impact (CAI) behavior prediction of variable stiffness composite laminates with emphasis on the effect of the interaction between fibre orientations, matrix-cracks and delaminations. An explicit finite element analysis using bilinear cohesive law-based interface elements and cohesive contacts is employed for the investigation. Examples are presented to illustrate the effectiveness of the current models for predicting the extent of impact damage and subsequent compression strength. The current study has improved the understanding of interactions between matrix-cracks and delaminations to clarify open questions on delamination initiation and how matrix cracks and fibre orientations interact.

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“…In recent years, studies on CAI have largely focused on modelling the residual strength with analytical [2,3], semi-empirical [4], or finite elements [5][6][7][8][9][10] approaches, even though the physical mechanisms leading to the final rupture are still not well known today. Indeed, among the experimental studies, some focus on the influence of material properties on the evolution of the residual strength: fibre [8,11], resin [11][12][13], interface [14], stacking [15], transverse reinforcement like stitching [16,17] or Z-pinning [18], fabric instead of unidirectional tape [12,19], curing temperature [19].…”

Section: Introductionmentioning

confidence: 99%