An investigation into the damage development and residual strengths of open-hole specimens in fatigue
An extensive experimental program was carried out to investigate and understand the sequence of damage development throughout the life of open-hole composite laminates loaded in tension–tension fatigue. Quasi-isotropic carbon/epoxy laminates, with stacking sequence [452/902/−452/02]S, [45/90/−45/0]2...
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Published in | Composites. Part A, Applied science and manufacturing Vol. 69; pp. 266 - 278 |
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Main Authors | , |
Format | Journal Article |
Language | English |
Published |
Elsevier Ltd
01.02.2015
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Subjects | |
Online Access | Get full text |
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Summary: | An extensive experimental program was carried out to investigate and understand the sequence of damage development throughout the life of open-hole composite laminates loaded in tension–tension fatigue. Quasi-isotropic carbon/epoxy laminates, with stacking sequence [452/902/−452/02]S, [45/90/−45/0]2S and [45/90/−45/0]4S were examined. These were selected on the basis that under quasi-static loading the [452/902/−452/02]S configuration exhibited a delamination dominated mode of failure whilst the [45/90/−45/0]2S and [45/90/−45/0]4S configurations showed a fibre dominated failure mode, previously described as “pull-out” and “brittle” respectively. Specimens were fatigue loaded to 1×106 cycles or catastrophic failure, which ever occurred first. A number of tests were interrupted at various points as the stiffness dropped with increasing cycles, which were inspected using X-ray computed tomography (CT) scanning. A static residual strength program was carried out for run-out specimens of each configuration. |
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Bibliography: | ObjectType-Article-1 SourceType-Scholarly Journals-1 ObjectType-Feature-2 content type line 23 |
ISSN: | 1359-835X 1878-5840 |
DOI: | 10.1016/j.compositesa.2014.11.013 |