Predicting the ultimate load of a CFRP wingbox

Michael Koundouros; Brian G. Falzon; Costas Soutis; Steven J. Lord

doi:10.1016/j.compositesa.2004.01.016

Predicting the ultimate load of a CFRP wingbox

Michael Koundouros, Brian G. Falzon, Costas Soutis, Steven J. Lord

Research output: Contribution to journal › Article › peer-review

Abstract

The finite element method in conjunction with the Soutis-Fleck model is used to predict the residual strength after impact of a carbon-fibre reinforced plastic wingbox subjected to a cantilever type loading. The maximum stress failure criterion further validates the Soutis-Fleck model predictions. The Soutis-Fleck model predicts that the wingbox fails at a tip load of 99.2kN, approximately 5.5% less than the experimental observation. © 2004 Elsevier Ltd. All rights reserved.

Original language	English
Pages (from-to)	895-903
Number of pages	8
Journal	Composites Part A: Applied Science and Manufacturing
Volume	35
Issue number	7-8
DOIs	https://doi.org/10.1016/j.compositesa.2004.01.016
Publication status	Published - Jul 2004

Keywords

B. Fracture toughness
B. Stress concentrations
C. Damage mechanics
C. Finite element analysis (FEA)

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10.1016/j.compositesa.2004.01.016

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title = "Predicting the ultimate load of a CFRP wingbox",

abstract = "The finite element method in conjunction with the Soutis-Fleck model is used to predict the residual strength after impact of a carbon-fibre reinforced plastic wingbox subjected to a cantilever type loading. The maximum stress failure criterion further validates the Soutis-Fleck model predictions. The Soutis-Fleck model predicts that the wingbox fails at a tip load of 99.2kN, approximately 5.5% less than the experimental observation. {\textcopyright} 2004 Elsevier Ltd. All rights reserved.",

keywords = "B. Fracture toughness, B. Stress concentrations, C. Damage mechanics, C. Finite element analysis (FEA)",

author = "Michael Koundouros and Falzon, {Brian G.} and Costas Soutis and Lord, {Steven J.}",

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T1 - Predicting the ultimate load of a CFRP wingbox

AU - Koundouros, Michael

AU - Falzon, Brian G.

AU - Soutis, Costas

AU - Lord, Steven J.

PY - 2004/7

Y1 - 2004/7

N2 - The finite element method in conjunction with the Soutis-Fleck model is used to predict the residual strength after impact of a carbon-fibre reinforced plastic wingbox subjected to a cantilever type loading. The maximum stress failure criterion further validates the Soutis-Fleck model predictions. The Soutis-Fleck model predicts that the wingbox fails at a tip load of 99.2kN, approximately 5.5% less than the experimental observation. © 2004 Elsevier Ltd. All rights reserved.

AB - The finite element method in conjunction with the Soutis-Fleck model is used to predict the residual strength after impact of a carbon-fibre reinforced plastic wingbox subjected to a cantilever type loading. The maximum stress failure criterion further validates the Soutis-Fleck model predictions. The Soutis-Fleck model predicts that the wingbox fails at a tip load of 99.2kN, approximately 5.5% less than the experimental observation. © 2004 Elsevier Ltd. All rights reserved.

KW - B. Fracture toughness

KW - B. Stress concentrations

KW - C. Damage mechanics

KW - C. Finite element analysis (FEA)

U2 - 10.1016/j.compositesa.2004.01.016

DO - 10.1016/j.compositesa.2004.01.016

M3 - Article

SN - 1878-5840

VL - 35

SP - 895

EP - 903

JO - Composites Part A: Applied Science and Manufacturing

JF - Composites Part A: Applied Science and Manufacturing

IS - 7-8

ER -

Predicting the ultimate load of a CFRP wingbox

Abstract

Keywords

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