Investigation into skin stiffener debonding of top-hat stiffened composite structures
Investigation into skin stiffener debonding of top-hat stiffened composite structures
Top-hat stiffened plates provide an efficient structure for engineering applications. During service debonding between the stiffener and the plate is often observed and parametric studies of open section stiffeners have shown that debond size and location have a significant effect on the damage mode of the panel. However, these studies do not consider the interaction of failure modes and do not assess the ultimate failure of the structure. In this paper top-hat stiffened composite structures are assessed considering debond damage between the stiffener and plate. A non-linear finite element model is used to perform a parametric study on the effect of both damage and the panel’s geometry on the failure modes, ultimate strength and its damage tolerance. Results show that top-hat stiffened panels exhibit a trend between ultimate strength and the debond size with crack initiation not necessarily propagating. Geometric imperfections accelerate buckling but can provide an arrest point for crack propagation.
damage tolerance, delamination, stiffened structures, progressive damage
1168-1181
Yetman, J.E.
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Sobey, A.J.
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Blake, J.I.R.
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Shenoi, R.A.
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Yetman, J.E.
dfb6dc92-c9ce-4cae-bab3-998fdd7e537b
Sobey, A.J.
e850606f-aa79-4c99-8682-2cfffda3cd28
Blake, J.I.R.
6afa420d-0936-4acc-861b-36885406c891
Shenoi, R.A.
a37b4e0a-06f1-425f-966d-71e6fa299960
Yetman, J.E., Sobey, A.J., Blake, J.I.R. and Shenoi, R.A.
(2015)
Investigation into skin stiffener debonding of top-hat stiffened composite structures.
Composite Structures, 132, .
(doi:10.1016/j.compstruct.2015.06.061).
Abstract
Top-hat stiffened plates provide an efficient structure for engineering applications. During service debonding between the stiffener and the plate is often observed and parametric studies of open section stiffeners have shown that debond size and location have a significant effect on the damage mode of the panel. However, these studies do not consider the interaction of failure modes and do not assess the ultimate failure of the structure. In this paper top-hat stiffened composite structures are assessed considering debond damage between the stiffener and plate. A non-linear finite element model is used to perform a parametric study on the effect of both damage and the panel’s geometry on the failure modes, ultimate strength and its damage tolerance. Results show that top-hat stiffened panels exhibit a trend between ultimate strength and the debond size with crack initiation not necessarily propagating. Geometric imperfections accelerate buckling but can provide an arrest point for crack propagation.
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Yetman_Investigation.pdf
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e-pub ahead of print date: 4 July 2015
Keywords:
damage tolerance, delamination, stiffened structures, progressive damage
Organisations:
Fluid Structure Interactions Group
Identifiers
Local EPrints ID: 378956
URI: http://eprints.soton.ac.uk/id/eprint/378956
ISSN: 0263-8223
PURE UUID: 7378003a-8991-44c2-b238-d05f734377a0
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Date deposited: 15 Jul 2015 13:26
Last modified: 15 Mar 2024 03:28
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Author:
J.E. Yetman
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