Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels

Brian G Falzon; Grant P Steven

doi:10.2514/6.1995-1458

Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels

Brian G Falzon
, Grant P Steven

Research output: Chapter in Book / Conference Paper › Conference Paper › peer-review

Abstract

The results of a combined experimental and numerical study of hat-stiffened co-cured carbon-fibre composite panels loaded in uniaxial compression are presented. All panels consisted of two integrated stiffeners separated by an eight-ply thick skin bay of lay-up [±45/0/90]s. The effects of a 100 mm circular cutout in the skin was also investigated. The ultimate strength of all panels was governed by the load carrying capacity of the stiffeners. A change in the skin's buckling mode-shape was also observed for all panels loaded deep in the postbuckling region. The strains induced at the interior free-edge were not found to be critical. Non-linear finite element results correlated well with the prebuckling and initial postbuckling strain and displacements results obtained by experiment.

Original language	English
Title of host publication	AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum
Place of Publication	Proceedings of the 36th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and AIAA/ASME Adaptive Structures Forum. Part 1 (of 5); New Orleans, LA, USA; ; 10 April 1995 through 13 April 1995; Code 43152
Number of pages	9
DOIs	https://doi.org/10.2514/6.1995-1458
Publication status	Published - 1995

Bibliographical note

AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum
New Orleans, LA, USA
10 - 13 April 1995

Keywords

Buckling Carbon fiber reinforced plastics Composite structures Compression testing Finite element method Mathematical models Stiffness Strength of materials Structural loads Structural panels Carbon fiber composite panels Load carrying capacity Stiffeners Uniaxial compression Structural analysis

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10.2514/6.1995-1458

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Falzon, Brian G ; Steven, Grant P. / Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels. AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum . Proceedings of the 36th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and AIAA/ASME Adaptive Structures Forum. Part 1 (of 5); New Orleans, LA, USA; ; 10 April 1995 through 13 April 1995; Code 43152, 1995.

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title = "Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels",

abstract = "The results of a combined experimental and numerical study of hat-stiffened co-cured carbon-fibre composite panels loaded in uniaxial compression are presented. All panels consisted of two integrated stiffeners separated by an eight-ply thick skin bay of lay-up [±45/0/90]s. The effects of a 100 mm circular cutout in the skin was also investigated. The ultimate strength of all panels was governed by the load carrying capacity of the stiffeners. A change in the skin's buckling mode-shape was also observed for all panels loaded deep in the postbuckling region. The strains induced at the interior free-edge were not found to be critical. Non-linear finite element results correlated well with the prebuckling and initial postbuckling strain and displacements results obtained by experiment.",

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author = "Falzon, \{Brian G\} and Steven, \{Grant P\}",

note = "AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum New Orleans, LA, USA 10 - 13 April 1995",

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doi = "10.2514/6.1995-1458",

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Falzon, BG & Steven, GP 1995, Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels. in AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum ., AIAA 1995-1458, Proceedings of the 36th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and AIAA/ASME Adaptive Structures Forum. Part 1 (of 5); New Orleans, LA, USA; ; 10 April 1995 through 13 April 1995; Code 43152. https://doi.org/10.2514/6.1995-1458

Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels. / Falzon, Brian G; Steven, Grant P.
AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum . Proceedings of the 36th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and AIAA/ASME Adaptive Structures Forum. Part 1 (of 5); New Orleans, LA, USA; ; 10 April 1995 through 13 April 1995; Code 43152, 1995. AIAA 1995-1458.

Research output: Chapter in Book / Conference Paper › Conference Paper › peer-review

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AU - Falzon, Brian G

AU - Steven, Grant P

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N2 - The results of a combined experimental and numerical study of hat-stiffened co-cured carbon-fibre composite panels loaded in uniaxial compression are presented. All panels consisted of two integrated stiffeners separated by an eight-ply thick skin bay of lay-up [±45/0/90]s. The effects of a 100 mm circular cutout in the skin was also investigated. The ultimate strength of all panels was governed by the load carrying capacity of the stiffeners. A change in the skin's buckling mode-shape was also observed for all panels loaded deep in the postbuckling region. The strains induced at the interior free-edge were not found to be critical. Non-linear finite element results correlated well with the prebuckling and initial postbuckling strain and displacements results obtained by experiment.

AB - The results of a combined experimental and numerical study of hat-stiffened co-cured carbon-fibre composite panels loaded in uniaxial compression are presented. All panels consisted of two integrated stiffeners separated by an eight-ply thick skin bay of lay-up [±45/0/90]s. The effects of a 100 mm circular cutout in the skin was also investigated. The ultimate strength of all panels was governed by the load carrying capacity of the stiffeners. A change in the skin's buckling mode-shape was also observed for all panels loaded deep in the postbuckling region. The strains induced at the interior free-edge were not found to be critical. Non-linear finite element results correlated well with the prebuckling and initial postbuckling strain and displacements results obtained by experiment.

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BT - AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum

CY - Proceedings of the 36th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and AIAA/ASME Adaptive Structures Forum. Part 1 (of 5); New Orleans, LA, USA; ; 10 April 1995 through 13 April 1995; Code 43152

ER -

Falzon BG, Steven GP. Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels. In AIAA/ASME/ASCE/AHS/ASC 36th Structures, Structural Dynamics and Materials Conference and AIAA/ASME Adaptive Structures Forum . Proceedings of the 36th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and AIAA/ASME Adaptive Structures Forum. Part 1 (of 5); New Orleans, LA, USA; ; 10 April 1995 through 13 April 1995; Code 43152. 1995. AIAA 1995-1458 doi: 10.2514/6.1995-1458

Postbuckling behaviour of hat-stiffened thin-skinned carbon-fibre composite panels

Abstract

Bibliographical note

Keywords

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