Predicting delamination and debonding in modern aerospace composite structures

Davies, G. A. O.; Hitchings, D.; Ankersen, J.

doi:10.1016/j.compscitech.2004.12.043

Cited by 99 publications

(50 citation statements)

References 7 publications

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“…T-piece specimens have been paid a high degree of attention in the study of behavior of aerospace composite structures because they are representative of features in key aerospace structures such as composite vanes in aero engines and T and I stiffeners and beams such as stringers [1,2]. Study of the failure mechanisms in T-piece specimens and prediction of their damage resistant capability is fundamental for the design of such composite components.…”

Section: Introductionmentioning

confidence: 99%

Prediction of delamination in braided composite T-piece specimens

Chen

Ravey

Hallett

et al. 2009

Composites Science and Technology

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Abstract:This paper presents an approach to predict the delamination of braided composite Tpiece specimen using cohesive models. As part of an investigation on simulation of delamination in T-piece specimens, cohesive elements from ABAQUS were employed in forming a cohesive model to study the progressive delamination. Predictions given by the model of single delamination together with experimental results are presented.These results suggest that prediction of progressive delamination using cohesive models is feasible. Finally this paper proposes future work for precise prediction of delamination of braided composite T-piece specimens.2

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Section: Introductionmentioning

confidence: 99%

Prediction of delamination in braided composite T-piece specimens

Chen

Ravey

Hallett

et al. 2009

Composites Science and Technology

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“…According to Davies [12], delamination in the plate's mid-plane will propagate in mode II, at a critical force given by:…”

Section: Delaminationmentioning

confidence: 99%

Development of fibre-metal laminates for improved impact performance

Morinière

Alderliesten

Benedictus

2012

Eur. Phys. J. Spec. Top.

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Abstract. An analytical and experimental investigation into the low-velocity behaviour of GLARE Fibre-Metal Laminates (FMLs) has been performed. A quasi-static approach was developed to estimate the perforation energy absorbed between the constituents of GLARE. The analysis considered contact area increase during perforation and strain rate effect on material properties. Particular attention was paid to the effect of ply-angle orientation and aluminium position. Predicted maximum impact force, maximum displacement, and perforation energy related to impact velocity were within 10% of test results. Stacking composite plies oriented along the diagonal of the plate with more than 2 aluminium layers leads to a more impact resistant FML. The generic nature of the developed methodology can support the optimization of high-performance FML concepts.

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“…However, a full exploitation of the advantages offered by these materials (low weight, excellent strength, stiffness, energy absorption and fatigue properties) requires an accurate modeling of local damage rise and growth in service, due to the inability of sandwiches to yield and dissipate a large amount of energy via plasticity, as thoroughly discussed in the book by Daniel and Ishai [1] and in the recent papers by Davies et al [2] and de Freitas et al [3].…”

Section: Introductionmentioning

confidence: 99%

Indentation of Sandwiches Using a Refined Zig-Zag Model and a Mesoscale Damage Model

Icardi¹,

Sola²

2014

ujme

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An accurate and cost effective zig-zag plate model with variable kinematics and fixed degrees of freedom recently developed by the authors, which a priori fulfills the stress and displacement continuity requirements, is applied to study indentation of sandwiches with honeycomb/foam core. The variable elastic properties of the core during crushing are evaluated apart and once at a time through a 3D finite element analysis. Shell elements with elastic-plastic isotropic properties are adopted to discretize honeycomb cores and faces, instead solid elements with nonlinear material behavior are used for foam cores. To keep low the computational burden, the structural response is computed in closed form by the zig-zag model using these elastic properties. The damage analysis is carried out through a mesoscale model that determines the degraded properties of failed regions in a physically consistent way. A good agreement with experiments taken from the literature being shown, the present simulation procedure with a low computational effort is proven to be an efficient alternative to the ones currently employed.

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Predicting delamination and debonding in modern aerospace composite structures

Cited by 99 publications

References 7 publications

Prediction of delamination in braided composite T-piece specimens

Prediction of delamination in braided composite T-piece specimens

Development of fibre-metal laminates for improved impact performance

Indentation of Sandwiches Using a Refined Zig-Zag Model and a Mesoscale Damage Model

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