Modeling Inter-Laminar Failure in Composite Structures: Illustration on an Industrial Case Study

Bruyneel, Michaël; Delsemme, Jean-Pierre; Jetteur, Philippe; Germain, F.

doi:10.1007/s10443-009-9083-9

Cited by 14 publications

(7 citation statements)

References 10 publications

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“…A lot of research has been accomplished on this topic [9,18,19,42,43,44,45] and many papers are related to the simulation of delaminations in a double cantilever beam test. But in many cases not all the different parameters are given in order to reproduce the same simulations using the same models and material parameters.…”

Section: Numerical Simulations On the Mode I -Dcbmentioning

confidence: 99%

Analysis of the Numerical and Geometrical Parameters Influencing the Simulation of Mode I and Mode II Delamination Growth in Unidirectional and Textile Composites

2014

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The reliability of composite structures depends, among other damage mechanisms, on their ability to withstand delaminations. In order to have a better understanding of the cohesive zone method technique for delamination simulations, a complete analysis of the multiple parameters influencing the results is necessary. In this paper the work is concentrated on the cohesive zone method using cohesive elements. First a summary of the theory of the cohesive zone method is given. A numerical investigation on the multiple parameters influencing the numerical simulation of the mode I and mode II delamination tests has been performed. The parameters such as the stabilization method, the output frequency, the friction and the computational efficiency have been taken into account. The results will be compared to an analytical solution obtained by linear elastic fracture mechanics. Additionally the numerical simulation results will be compared to the experimental results of a glass-fibre reinforced composite material for the mode I Double Cantilever Beam (DCB) and to a carbon fibre 5harness satin weave reinforced polyphenylene sulphide composite for the mode I DCB and mode II End Notched Flexure (ENF).

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Section: Numerical Simulations On the Mode I -Dcbmentioning

confidence: 99%

Analysis of the Numerical and Geometrical Parameters Influencing the Simulation of Mode I and Mode II Delamination Growth in Unidirectional and Textile Composites

2014

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“…The damage variable d, considering the failure state at the interface between plies, is related to the equivalent thermodynamic force Y with a function of the form g(Y). In SAMCEF, three different functions g(Y) are available [5], leading to three cohesive laws, i.e. exponential, bi-triangular and polynomial.…”

Section: Modeling Inter-laminar Damagementioning

confidence: 99%

Modeling and Simulating Progressive Failure in Composite Structures for Automotive Applications

Bruyneel

Jetteur

Delsemme

et al. 2014

SAE Technical Paper Series

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In this paper, it is explained how composite structures, made of continuous fibers embedded in a polymer matrix, are designed and analyzed in the aerospace industry. The strategy is based on the building block approach, in which the knowledge on the composite material and structure is built step by step from the coupon level up to the final full scale structure. Damage is then discussed, as it can't be ignored when composites are concerned. The approach available in the SAMCEF finite element code is then described. It is based on the continuum mechanics approach, and allows studying the progressive failure of composites in the plies and at their interface (so considering delamination). The material models are described, and their use is illustrated at the coupon level. The identification procedure for this damage models is also discussed. It is therefore shown how this information of the material behavior can be used at the upper stages of the building block approach and so applied to larger scale structures. It is advocated here that this approach can be used for the automotive applications, leading to a transfer of technology from aerospace to automotive.

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“…The literature survey of T-joints shows that filler region and flange tips are the critical locations for delamination/debond initiation. Two of the major initiation mechanisms observed in the literature are the debond of the filler/stringer interface [10,19,23] as shown in Figure 3 and the delamination of plies in the stringer laminate at the curved region [1,3,4,6] as shown in Figure 4. …”

Section: Critical Regions In T-joints For Delamination/debondmentioning

confidence: 99%

Delamination-Debond Behaviour of Composite T- Joints in Wind Turbine Blades

Gülaşık¹,

Çöker²

2014

J. Phys.: Conf. Ser.

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Abstract. Wind turbine industry utilizes composite materials in turbine blade structural designs because of their high strength/stiffness to weight ratio. T-joint is one of the design configurations of composite wind turbine blades. T-joints consist of a skin panel and a stiffener co-bonded or co-cured together with a filler material between them. T-joints are prone to delaminations between skin/stiffener plies and debonds between skin-stiffener-filler interfaces. In this study, delamination/debond behavior of a co-bonded composite T-joint is investigated under 0° pull load condition by 2D finite element method. Using Abaqus ® commercial FE software, zero-thickness cohesive elements are used to simulate delamination/debond in ply interfaces and bonding lines. Pulling load at 0° is applied and load-displacement behavior and failure scenario are observed. The failure sequence consists of debonding of filler/stringer interface during one load drop followed by a second drop in which the 2 nd filler/stringer debonds, filler/skin debonding and skin delamination leading to total loss of load carrying capacity. This type of failure initiation has been observed widely in the literature. When the debond strength is increased 30%, failure pattern is found to change in addition to increasing the load capacity by 200% before total loss of loading carrying capacity occurs. Failure initiation and propagation behavior, initial and max failure loads and stress fields are affected by the property change. In all cases mixed-mode crack tip loading is observed in the failure initiation and propagation stages. In this paper, the detailed delamination/debonding history in T-joints is predicted with cohesive elements for the first time.

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Modeling Inter-Laminar Failure in Composite Structures: Illustration on an Industrial Case Study

Cited by 14 publications

References 10 publications

Analysis of the Numerical and Geometrical Parameters Influencing the Simulation of Mode I and Mode II Delamination Growth in Unidirectional and Textile Composites

Analysis of the Numerical and Geometrical Parameters Influencing the Simulation of Mode I and Mode II Delamination Growth in Unidirectional and Textile Composites

Modeling and Simulating Progressive Failure in Composite Structures for Automotive Applications

Delamination-Debond Behaviour of Composite T- Joints in Wind Turbine Blades

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