Delamination growth from facesheet seams in cross-ply titanium/graphite hybrid laminates
Delamination growth from facesheet seams in cross-ply titanium/graphite hybrid laminates
A test program was conducted to study the fatigue delamination behavior of titanium/graphite hybrid laminates (TiGr) with seams in the titanium face sheets. Tension fatigue experiments were conducted at ?18°C, 21°C (room temperature), 93°C, and at 177°C on cross-ply, [Ti/0/90/02]s, titanium/graphite hybrid laminates (TiGr). The delamination growth rate obeyed a power-law function of the applied strain energy release rate range. The prefactor on the power-law function showed a strong dependence on temperature. In addition, experiments were performed on laminates with ±30° plies. The primary damage mode in this lay-up was edge delamination of the interior plies. Analysis of the [Ti/0/90/±?]s family of laminates indicated that for angles greater than 10°, edge delamination would be the dominant damage mode in coupon specimens.
fiber metal laminates (FML), delamination, strain energy release rate, fatigue, temperature
261-269
Burianek, Dennis A.
6dd8b685-86ee-493d-8992-709fb7a5a6e7
Spearing, S. Mark
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
2001
Burianek, Dennis A.
6dd8b685-86ee-493d-8992-709fb7a5a6e7
Spearing, S. Mark
9e56a7b3-e0e8-47b1-a6b4-db676ed3c17a
Burianek, Dennis A. and Spearing, S. Mark
(2001)
Delamination growth from facesheet seams in cross-ply titanium/graphite hybrid laminates.
Composites Science and Technology, 61 (2), .
(doi:10.1016/S0266-3538(00)00206-2).
Abstract
A test program was conducted to study the fatigue delamination behavior of titanium/graphite hybrid laminates (TiGr) with seams in the titanium face sheets. Tension fatigue experiments were conducted at ?18°C, 21°C (room temperature), 93°C, and at 177°C on cross-ply, [Ti/0/90/02]s, titanium/graphite hybrid laminates (TiGr). The delamination growth rate obeyed a power-law function of the applied strain energy release rate range. The prefactor on the power-law function showed a strong dependence on temperature. In addition, experiments were performed on laminates with ±30° plies. The primary damage mode in this lay-up was edge delamination of the interior plies. Analysis of the [Ti/0/90/±?]s family of laminates indicated that for angles greater than 10°, edge delamination would be the dominant damage mode in coupon specimens.
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Published date: 2001
Keywords:
fiber metal laminates (FML), delamination, strain energy release rate, fatigue, temperature
Identifiers
Local EPrints ID: 23085
URI: http://eprints.soton.ac.uk/id/eprint/23085
ISSN: 0266-3538
PURE UUID: d7f0d652-323a-4c2a-b41a-ffe0673acd6a
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Date deposited: 10 Mar 2006
Last modified: 16 Mar 2024 03:37
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Author:
Dennis A. Burianek
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