Fatigue damage mechanics of composite materials III: prediction of post-fatigue strength
Fatigue damage mechanics of composite materials III: prediction of post-fatigue strength
A damage-based model for post-fatigue notch strength is presented. The model is an extension of a method developed previously to predict the notch strength of laminated composites. A simple finite element representation of the notch tip damage zone is used to obtain the localized damage-modified stress distribution. A uniaxial tensile stress failure criterion is applied to the 0° plies from which the laminate strength is evaluated. In conjunction with the fatigue damage growth law described in Part II, residual strength is calculated as a function of the applied loading conditions, specimen geometry and lay-up for (90/0)s, (90/0)2s and (902/02)s T300/914C carbon-fibre/epoxy laminates subjected to tension-tension fatigue cycling.
predicting post-fatigue strength, finite element analysis
299-307
Spearing, S.M.
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
Beaumont, P.W.R.
985e59e0-5e69-4091-b7ae-68a4bc7c34ad
1992
Spearing, S.M.
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
Beaumont, P.W.R.
985e59e0-5e69-4091-b7ae-68a4bc7c34ad
Spearing, S.M. and Beaumont, P.W.R.
(1992)
Fatigue damage mechanics of composite materials III: prediction of post-fatigue strength.
Composites Science and Technology, 44 (4), .
(doi:10.1016/0266-3538(92)90067-D).
Abstract
A damage-based model for post-fatigue notch strength is presented. The model is an extension of a method developed previously to predict the notch strength of laminated composites. A simple finite element representation of the notch tip damage zone is used to obtain the localized damage-modified stress distribution. A uniaxial tensile stress failure criterion is applied to the 0° plies from which the laminate strength is evaluated. In conjunction with the fatigue damage growth law described in Part II, residual strength is calculated as a function of the applied loading conditions, specimen geometry and lay-up for (90/0)s, (90/0)2s and (902/02)s T300/914C carbon-fibre/epoxy laminates subjected to tension-tension fatigue cycling.
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Published date: 1992
Keywords:
predicting post-fatigue strength, finite element analysis
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Local EPrints ID: 22854
URI: http://eprints.soton.ac.uk/id/eprint/22854
ISSN: 0266-3538
PURE UUID: 321c5ca3-2511-46b1-b208-76c0c63ea1c2
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Date deposited: 30 Jan 2007
Last modified: 16 Mar 2024 03:37
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Author:
P.W.R. Beaumont
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