Postbucking behaviour of a blade-stiffened composite panel loaded in uniaxial compression

Brian G Falzon; KA Stevens; Glyn AO Davies

doi:10.1016/S1359-835X(99)00085-8

Postbucking behaviour of a blade-stiffened composite panel loaded in uniaxial compression

Brian G Falzon, KA Stevens, Glyn AO Davies

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

120 Citations (Scopus)

Abstract

The postbuckling behaviour of a panel with blade-stiffeners incorporating tapered flanges was experimentally investigated. A new failure mechanism was identified for this particular type of stiffener. Failure was initiated by mid-plane delamination at the free edge of the postbuckled stiffener web at a node-line. This was consistent with an interlaminar shear stress failure and was calculated from strain gauge measurements using an approximate analysis based on lamination theory and incorporating edge effects. The critical shear stress was found to agree well with the shear strength obtained from a three-point bending test of the web laminate.

Original language	English
Pages (from-to)	459-468
Number of pages	10
Journal	Compos Part A Appl Sci Manuf
Volume	31
Issue number	5
DOIs	https://doi.org/10.1016/S1359-835X(99)00085-8
Publication status	Published - 2000
Externally published	Yes

Keywords

Bending (deformation) Buckling Calculations Delamination Epoxy resins Failure analysis Laminating Materials testing Shear stress Stiffness Strain gages Interlaminar shear stress Stiffened composite panel Three point bending test Carbon fiber reinforced plastics

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10.1016/S1359-835X(99)00085-8

Cite this

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title = "Postbucking behaviour of a blade-stiffened composite panel loaded in uniaxial compression",

abstract = "The postbuckling behaviour of a panel with blade-stiffeners incorporating tapered flanges was experimentally investigated. A new failure mechanism was identified for this particular type of stiffener. Failure was initiated by mid-plane delamination at the free edge of the postbuckled stiffener web at a node-line. This was consistent with an interlaminar shear stress failure and was calculated from strain gauge measurements using an approximate analysis based on lamination theory and incorporating edge effects. The critical shear stress was found to agree well with the shear strength obtained from a three-point bending test of the web laminate.",

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AU - Falzon, Brian G

AU - Stevens, KA

AU - Davies, Glyn AO

PY - 2000

Y1 - 2000

N2 - The postbuckling behaviour of a panel with blade-stiffeners incorporating tapered flanges was experimentally investigated. A new failure mechanism was identified for this particular type of stiffener. Failure was initiated by mid-plane delamination at the free edge of the postbuckled stiffener web at a node-line. This was consistent with an interlaminar shear stress failure and was calculated from strain gauge measurements using an approximate analysis based on lamination theory and incorporating edge effects. The critical shear stress was found to agree well with the shear strength obtained from a three-point bending test of the web laminate.

AB - The postbuckling behaviour of a panel with blade-stiffeners incorporating tapered flanges was experimentally investigated. A new failure mechanism was identified for this particular type of stiffener. Failure was initiated by mid-plane delamination at the free edge of the postbuckled stiffener web at a node-line. This was consistent with an interlaminar shear stress failure and was calculated from strain gauge measurements using an approximate analysis based on lamination theory and incorporating edge effects. The critical shear stress was found to agree well with the shear strength obtained from a three-point bending test of the web laminate.

KW - Bending (deformation) Buckling Calculations Delamination Epoxy resins Failure analysis Laminating Materials testing Shear stress Stiffness Strain gages Interlaminar shear stress Stiffened composite panel Three point bending test Carbon fiber reinforced pl

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DO - 10.1016/S1359-835X(99)00085-8

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Postbucking behaviour of a blade-stiffened composite panel loaded in uniaxial compression

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Keywords

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