Numerical simulation of fatigue failure in carbon fibre reinforced aluminium alloy laminates
Numerical simulation of fatigue failure in carbon fibre reinforced aluminium alloy laminates
Hybrid laminates typically consist of alternate layers of fibre reinforced plastic and aluminium alloy. Developed for fatigue critical aerospace applications i.e. fuselage and lower wing skins, the hybrid laminates are orthotropic materials with lower density and higher strength compared to the alloy monolith. A remote sensing system reliant upon fibre optic technology has been developed to monitor the strain field encountered across composite laminae. This fibre optic system has been applied initially to the problem of characterising delamination zone development about a fatigue crack initiated at a through thickness fastener hole. Delamination measurements obtained using an in-situ ultrasonic C-scanner have been utilised in numerical simulations of the fatigue failure process and the data compared with measured strain profiles.
1-85312-683-7
Wessex Institute of Technology
Austin, T.S.P.
97c7f52a-2535-4fde-b3dc-2150e81ca30f
Singh, M.M.
2fd46335-d898-4bfc-945a-75f3c8e575fd
Gregson, P.J.
ddc3b65d-18fb-4c11-9fa1-feb7e9cbe9fe
Dakin, J.P.
04891b9b-5fb5-4245-879e-9e7361adf904
Powell, P.M.
2fda759a-bb1b-4451-9713-e36535feb341
1999
Austin, T.S.P.
97c7f52a-2535-4fde-b3dc-2150e81ca30f
Singh, M.M.
2fd46335-d898-4bfc-945a-75f3c8e575fd
Gregson, P.J.
ddc3b65d-18fb-4c11-9fa1-feb7e9cbe9fe
Dakin, J.P.
04891b9b-5fb5-4245-879e-9e7361adf904
Powell, P.M.
2fda759a-bb1b-4451-9713-e36535feb341
Austin, T.S.P., Singh, M.M., Gregson, P.J., Dakin, J.P. and Powell, P.M.
(1999)
Numerical simulation of fatigue failure in carbon fibre reinforced aluminium alloy laminates.
Brebbia, C.A.
(ed.)
In Computational Methods in Experimental Measurements IX.
vol. 22,
Wessex Institute of Technology.
10 pp
.
(doi:10.2495/CMEM990061).
Record type:
Conference or Workshop Item
(Paper)
Abstract
Hybrid laminates typically consist of alternate layers of fibre reinforced plastic and aluminium alloy. Developed for fatigue critical aerospace applications i.e. fuselage and lower wing skins, the hybrid laminates are orthotropic materials with lower density and higher strength compared to the alloy monolith. A remote sensing system reliant upon fibre optic technology has been developed to monitor the strain field encountered across composite laminae. This fibre optic system has been applied initially to the problem of characterising delamination zone development about a fatigue crack initiated at a through thickness fastener hole. Delamination measurements obtained using an in-situ ultrasonic C-scanner have been utilised in numerical simulations of the fatigue failure process and the data compared with measured strain profiles.
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Published date: 1999
Venue - Dates:
Computational Methods and Experimental Measurements, Sorrento, Italy, 1999-04-27 - 1999-04-29
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Local EPrints ID: 76553
URI: http://eprints.soton.ac.uk/id/eprint/76553
ISBN: 1-85312-683-7
PURE UUID: d65d6ffc-013b-4dac-b10d-5a5067dc6fe5
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Date deposited: 11 Mar 2010
Last modified: 13 Mar 2024 23:19
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Contributors
Author:
T.S.P. Austin
Author:
M.M. Singh
Author:
P.J. Gregson
Author:
J.P. Dakin
Author:
P.M. Powell
Editor:
C.A. Brebbia
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