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

Imperial College London

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

2 Citations (Scopus)

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.

Original language	English
Pages (from-to)	895-903
Number of pages	9
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 - 2004
Externally published	Yes

Keywords

B. Fracture toughness B. Stress concentrations C. Damage mechanics C. Finite element analysis (FEA) Approximation theory Failure (mechanical) Finite element method Fracture toughness Mathematical models Stress concentration Structural loads Damage mechanics Wingbox structure Carbon fiber reinforced plastics

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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.",

keywords = "B. Fracture toughness B. Stress concentrations C. Damage mechanics C. Finite element analysis (FEA) Approximation theory Failure (mechanical) Finite element method Fracture toughness Mathematical models Stress concentration Structural loads Damage mechanics Wingbox structure Carbon fiber reinforced plastics",

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year = "2004",

doi = "10.1016/j.compositesa.2004.01.016",

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volume = "35",

pages = "895--903",

journal = "Composites. Part A, Applied Science and Manufacturing",

issn = "1359-835X",

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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

Y1 - 2004

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.

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.

KW - B. Fracture toughness B. Stress concentrations C. Damage mechanics C. Finite element analysis (FEA) Approximation theory Failure (mechanical) Finite element method Fracture toughness Mathematical models Stress concentration Structural loads Damage mechani

U2 - 10.1016/j.compositesa.2004.01.016

DO - 10.1016/j.compositesa.2004.01.016

M3 - Article

SN - 1359-835X

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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