Progressive fracture of laminated composite stiffened plate

Gotsis, Pascalis K.; Chamis, Christos C.; David, Constantine; Abdi, Frank

doi:10.1016/j.tafmec.2009.04.008

Cited by 7 publications

(2 citation statements)

References 7 publications

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“…During the analysis on the strength of the wing-box, it is usually assumed that the adhesive condition between the wing-box skin and the rib as well as spar is intact. Namely, the interface is strong enough to resist any damage in the test [6,7]. However, interface debonding occurs easily under the in-plane compression or shear load in the wind tunnel test, for the adhesive area between spar flange and skin is too small.…”

Section: Introductionmentioning

confidence: 99%

Effect of Interfacial Debonding on the Strength of Composite Structure-Similarity Scale Model for the Wing-Box

Sun

Yang

Yan

et al. 2015

International Journal of Aerospace Engineering

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Based on the wing-box structure, a model was established to analyze the strength of the scale model for the composite wing. Firstly, different failure criteria were set to determine damage onset of the components. The continuum damage variables were adopted in the stiffness degradation rule. Secondly, the interface elements were placed along the interface between the beam flange and the skin to investigate the effects of bonding strength on the ultimate load-carrying capacity of the wing-box. The failure modes of the wing-box structure were studied by using the nonlinear finite element method. The effect of flange’s width on the strength of wing-box was discussed based on the prediction method. The results indicated that the ultimate load-carrying capacity varied distinctly with the change of flange’s width. However, the bonding strength had limited effect on the model strength as the flange’s width increases to the critical value. The research methods and results of the study can serve as reference for the strength analysis on the scale model of composite wing as well as the determination of principles adopted in the design of the scale model for wing spar.

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Section: Introductionmentioning

confidence: 99%

Effect of Interfacial Debonding on the Strength of Composite Structure-Similarity Scale Model for the Wing-Box

Sun

Yang

Yan

et al. 2015

International Journal of Aerospace Engineering

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“…Newman [3] and Seshadri [4] used the Structural Analysis of General Shells (STAGS) finite-element shell code and the critical crack-tip-opening angle (CTOA) fracture criterion on stiffened , un-stiffened panels and wide panels residual strength analyses. Gotsis [5] performed computational simulation to S-Glass/epoxy [0/90/±45]S laminated reinforced fibers composite stiffened plate, subjected to thermo-mechanical loads, predicted the damage progression, fracture thought the thickness and propagation to final fracture of the structure. Lauterbach [6] used an analysis tool to investigate fuselage representative carbon fibre-reinforced multi-stiffener panel under compressive loading, predicting interlaminar damage initiation and degradation models for capturing interlaminar damage growth as well as in-plane damage mechanisms.…”

Section: Introductionmentioning

confidence: 99%

Progressive Failure Study of Discrete-Source Damage in Stiffened Composite Panels

Jia

Jiao

2011

AMR

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In this paper experimental and FEA methods were used to study the damage propagation and failure properties of stiffened composite panels with discrete-source damage. The influence of discrete-source damage on residual strength of the composite panel was also investigated. The research results indicated that notched composite panel was suitable to simulate the damage property of stiffened composite panel with discrete-source damage. It has showed that there is high strain concentration at the notch end. And break-through of the stringer can make the load path changed. Based on different failure criteria, FEA method with progressive failure procedure was used to simulate the damage progression and failure procedure of the notched stiffened composite panel effectively. The analytical result was in good correspondence with the experimental data.

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An extended layerwise/solid-element method of stiffened composite plates with delaminations and transverse crack

Lü

Yang

et al. 2017

Int J Mech Mater Des

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Progressive fracture of laminated composite stiffened plate

Cited by 7 publications

References 7 publications

Effect of Interfacial Debonding on the Strength of Composite Structure-Similarity Scale Model for the Wing-Box

Effect of Interfacial Debonding on the Strength of Composite Structure-Similarity Scale Model for the Wing-Box

Progressive Failure Study of Discrete-Source Damage in Stiffened Composite Panels

An extended layerwise/solid-element method of stiffened composite plates with delaminations and transverse crack

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