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Static and high-rate loading of single and multi-bolt carbon-epoxy aircraft fuselage joints
Date
2013
Abstract
Single-lap shear behaviour of carbon epoxy composite bolted aircraft fuselage joints at quasi-static and dynamic (5 m/s and 10 m/s) loading speeds is studied experimentally. Single and multi-bolt joints with countersunk fasteners were tested. The initial joint failure mode was bearing, while final failure was either due to fastener pull-through or fastener fracture at a thread. Much less hole bearing damage, and hence energy absorption, occurred when the fastener(s) fractured at a thread, which occurred most frequently in thick joints and in quasi-static tests. Fastener failure thus requires special consideration in designing crashworthy fastened composite structures; if it can be delayed, energy absorption is greater. A correlation between energy absorption in multi-bolt and single-bolt joint tests indicates potential to downsize future test programmes. Tapering a thin fuselage panel layup to a thicker layup at the countersunk hole proved highly effective in achieving satisfactory joint strength and energy absorption.
Supervisor
Description
peer-reviewed
Publisher
Elsevier
Citation
Composities Part A: Applied Science and Manufacturing;53, pp. 97-108
Files
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Egan_2013_static.pdf
Adobe PDF, 1.78 MB
ULRR Identifiers
Funding code
Funding Information
European Research Council (ERC)