The fatigue damage mechanics of notched carbon fibre/PEEK laminates
The fatigue damage mechanics of notched carbon fibre/PEEK laminates
A model is presented for the strength, post-fatigue residual strength and damage propagation in notched, cross-ply carbon fibre/polyetheretherketone (PEEK) laminates. Fracture mechanics principles are used to predict quasi-static damage growth, and the application of a Paris law permits extension to fatigue damage. Strength is predicted by applying a failure criterion based on the tensile stress distribution in the 0° plies, as modified by damage (either quasi-static or fatigue). The volume dependence of strength is included by using a simple Weibull distribution. The parameters of the model are determined from independent experiments. Good agreement with experimental results is obtained. Comparisons are made with previous results from carbon fibre/epoxy laminates. The behaviour of the carbon fibre/PEEK is similar, although the extent of delamination and matrix cracking is reduced owing to the higher inherent toughness of the matrix.
composite materials, fatigue, fatigue strength, residual strength, damage propagation, modelling, notched cross-ply laminates, carbon fibres, epoxy matrix, PEEK matrix
305-311
Spearing, S.M.
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
Beaumont, P.W.R.
985e59e0-5e69-4091-b7ae-68a4bc7c34ad
Kortschot, M.T.
b6fda6a2-a697-4596-a08b-ce2b5f4d6ba8
1992
Spearing, S.M.
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
Beaumont, P.W.R.
985e59e0-5e69-4091-b7ae-68a4bc7c34ad
Kortschot, M.T.
b6fda6a2-a697-4596-a08b-ce2b5f4d6ba8
Spearing, S.M., Beaumont, P.W.R. and Kortschot, M.T.
(1992)
The fatigue damage mechanics of notched carbon fibre/PEEK laminates.
Composites Part A: Applied Science and Manufacturing, 23 (5), .
(doi:10.1016/0010-4361(92)90329-S).
Abstract
A model is presented for the strength, post-fatigue residual strength and damage propagation in notched, cross-ply carbon fibre/polyetheretherketone (PEEK) laminates. Fracture mechanics principles are used to predict quasi-static damage growth, and the application of a Paris law permits extension to fatigue damage. Strength is predicted by applying a failure criterion based on the tensile stress distribution in the 0° plies, as modified by damage (either quasi-static or fatigue). The volume dependence of strength is included by using a simple Weibull distribution. The parameters of the model are determined from independent experiments. Good agreement with experimental results is obtained. Comparisons are made with previous results from carbon fibre/epoxy laminates. The behaviour of the carbon fibre/PEEK is similar, although the extent of delamination and matrix cracking is reduced owing to the higher inherent toughness of the matrix.
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Published date: 1992
Keywords:
composite materials, fatigue, fatigue strength, residual strength, damage propagation, modelling, notched cross-ply laminates, carbon fibres, epoxy matrix, PEEK matrix
Identifiers
Local EPrints ID: 22770
URI: http://eprints.soton.ac.uk/id/eprint/22770
ISSN: 1359-835X
PURE UUID: ad425fcd-3b8e-4813-b77a-3f50b21da46b
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Date deposited: 30 Jan 2007
Last modified: 16 Mar 2024 03:37
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Contributors
Author:
P.W.R. Beaumont
Author:
M.T. Kortschot
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