Development of a finite-element analysis methodology for the propagation of delaminations in composite structures

Orifici, Adrian C.; Thomson, Rodney S.; Degenhardt, Richard; Bisagni, Chiara; Bayandor, Javid

doi:10.1007/s11029-007-0002-6

Cited by 35 publications

(30 citation statements)

References 16 publications

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“…The iterative approach was developed as it was found that a simple fail-release method led to violation of the assumption of self-similar growth. The prediction of interlaminar crack growth was validated using fracture mechanics characterisation specimens, including mode I double cantilever beam (DCB), 5 mode II end notched flexure, 6 mode III edge crack torsion, 1 and mode I-II mixed-mode bending (MMB). 6 From these specimens, the crack growth degradation model with the iterative propagation method was shown to be capable of accurately representing specimen behaviour under single and mixed-mode crack growth.…”

Section: Analysis Toolmentioning

confidence: 99%

An Analysis Tool for Design and Certification of Postbuckling Composite Aerospace Structures

Orifici

Thomson²,

Degenhardt

et al. 2010

Int. J. Str. Stab. Dyn.

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In aerospace, carbon fibre-reinforced polymer (CFRP) materials and postbuckling skin-stiffened structures are key technologies that have been used to improve structural efficiency. However, the application of composite postbuckling structures in aircraft has been limited as today's analysis tools cannot accurately predict structural collapse in compression. In this work, a finite element analysis tool for design and certification of aerospace structures is presented, which predicts collapse by taking the critical damage mechanisms into account. The tool incorporates a global-local analysis technique for predicting interlaminar damage initiation, and degradation models to capture the growth of a pre-existing interlaminar damage region, such as a delamination or skin-stiffener debond, and in-plane ply damage mechanisms such as fibre fracture and matrix cracking. The analysis tool has been applied to single-and multi-stiffener fuselage-representative composite panels, in both intact and pre-damaged configurations. This has been performed in a design context, in which panel configurations are selected based on their suitability for experimental testing, and in an analysis context for comparison with experimental results as representative of aircraft certification studies. For all cases, the tool was capable of accurately capturing the key damage mechanisms contributing to final structural collapse, and suitable for the design of next-generation composite aerospace structures. Analysis ToolThe finite element (FE) analysis tool developed was focused on predicting the collapse of stiffened composite structures in compression by capturing the effects of the critical damage mechanisms. The approach contains several aspects: predicting initiation of interlaminar damage in intact structures; capturing in-plane degradation; and, capturing the propagation of a pre-existing interlaminar damage region. The analysis tool was implemented into MSC.Marc v2005r3 (Marc) by a combination of user subroutines, and supported by utilities for pre-and post-processing within a user-friendly menu system developed in MSC.Patran. 1 This work was conducted as part of the European Commission Project COCOMAT, which focused on exploiting the large strength reserves of composite aerospace structures through a more accurate prediction of collapse. 2The approach for predicting the initiation of interlaminar damage in the skin-stiffener interface was based on a globallocal technique. In this technique, a global shell model of the full structure was used to determine the deformation field of the entire structure, which was then input as boundary conditions on a local three-dimensional (3D) brick model of a skin-stiffener interface. In the local model the strength-based "degenerated Tsai" criterion was monitored at all elements in order to predict the initiation of delamination or skin-stiffener separation. Failure was deemed to occur when the average of all integration point values in an element satisfied this criterion. By modifying the locat...

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Section: Analysis Toolmentioning

confidence: 99%

An Analysis Tool for Design and Certification of Postbuckling Composite Aerospace Structures

Orifici

Thomson²,

Degenhardt

et al. 2010

Int. J. Str. Stab. Dyn.

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“…The Virtual Crack Closure Technique (VCCT) is certainly the most popular method for computing the modes of the energy release rate (GI, GII, GIII) needed for estimating the onset of delamination [2][3][4][5][6]. A specific Virtual Crack Extension method (VCE), based on [12], is presented here as an alternative to VCCT.…”

Section: Solution Procedures For Assessing Damage Tolerance In Composmentioning

confidence: 99%

“…The most dangerous crack and the propagation load are then predicted according to criteria such as those given in equation (1), where GIc, GIIc and GIIIc are the fracture toughness for each mode. With this approach crack growth analysis remains difficult to simulate and recent references only propose specific solutions for simple 3D configurations with a single crack front [2][3][4][5][6]. …”

Section: Introductionmentioning

confidence: 99%

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

Bruyneel¹,

Delsemme²,

Jetteur³

et al. 2009

Appl Compos Mater

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This paper presents a solution procedure made available at an industrial level to study delamination in composites. Two approaches are presented. The first one is based on an original VCE (Virtual Crack Extension) method used to provide a quick estimate of the propagation load and the critical inter-laminar cracks, in a linear finite element analysis. The second approach relies on cohesive elements, and implies a non linear analysis. More general than the fracture mechanics (VCE) approach, the cohesive elements technique allows to provide the value of the maximum load that can be sustained by the structure, and to predict the residual strength and stiffness over the fracture process. Those two methods are first compared in a DCB test case to show that the results agree well with those from the literature or with the analytical solutions. Finally, a multidelaminated industrial test case is solved with both approaches.

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“…straight or circular/elliptical -2/35-when modelled by using orthogonal meshes with edges parallel or orthogonal to the delamination front). When the delamination growth is of concern, the VCCT can be used in conjunction with interface elements [5][6][7] or with a fail release approach [8][9][10] whose effect is that to simulate the growth process by releasing constraints between crack faces when the Strain Energy Release Rate level overcomes critical values (instantaneous propagation). However, during the propagation the delamination front may assume complex and non-smoothed shapes with corners.…”

Section: Introductionmentioning

confidence: 99%

“…Mabson et al [5] emphasized the tendency for corner nodes to accumulate energy in a Double Cantilever Beam specimen and than to be smoothed thus inducing to a misleading prediction of the shape of the delamination front. Orifici et al [8] analysed the delamination growth in an analogous specimen by using four different approaches and individuating the best correlation between numerical and experimental results in terms of growth rate when weight factors were introduced in VCCT formulae. These weight factors were not predetermined as in Ref.11 but computed taking into account the shape of the local crack front created when constraints are released.…”

Section: Introductionmentioning

confidence: 99%

Formulation and assessment of an enhanced finite element procedure for the analysis of delamination growth phenomena in composite structures

Pietropaoli

Riccio

2011

Composites Science and Technology

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To cite this version:Elisa Pietropaoli, Aniello Riccio. Formulation and assessment of an enhanced finite element procedure for the analysis of delamination growth phenomena in composite structures. Composites Science and Technology, Elsevier, 2011, 71 (6) This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting proof before it is published in its final form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain.-1/35-

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Development of a finite-element analysis methodology for the propagation of delaminations in composite structures

Cited by 35 publications

References 16 publications

An Analysis Tool for Design and Certification of Postbuckling Composite Aerospace Structures

An Analysis Tool for Design and Certification of Postbuckling Composite Aerospace Structures

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

Formulation and assessment of an enhanced finite element procedure for the analysis of delamination growth phenomena in composite structures

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