Journal
COMPOSITE STRUCTURES
Volume 106, Issue -, Pages 882-889Publisher
ELSEVIER SCI LTD
DOI: 10.1016/j.compstruct.2013.05.033
Keywords
Carbon fibre/epoxy; Damage; Fatigue; Open hole
Categories
Funding
- Engineering and Physical Sciences Research Council (EPSRC) [EP/G036772/1]
- EPSRC [EP/F028431/1, EP/F007906/1]
- Engineering and Physical Sciences Research Council [EP/F028431/1, EP/F007906/1] Funding Source: researchfish
- EPSRC [EP/F007906/1, EP/F028431/1] Funding Source: UKRI
Ask authors/readers for more resources
An extensive experimental program has been carried out to investigate and understand the sequence of damage development throughout the life of open-hole quasi-isotropic IM7/8552 carbon-fibre/epoxy laminates loaded in tension-tension fatigue. Samples were initially quasi-statically loaded to failure to determine an average strength, sigma(UTS). Specimens were then cyclically loaded at 5 Hz at various amplitudes to 1 x 10(+6) cycles or to failure (15% loss of stiffness), which ever occurred first. Interrupted fatigue tests were carried out with peak amplitude at 60% of the ultimate static load (60% severity) in order to determine the 3D sequence of damage events using X-ray Computed Tomography (CT). Matrix cracking at the surface ply and initiation of matrix cracks in the subsequent plies lead to delaminations that progress through the thickness, and ultimately to the propagation of delamination at the -45/0 interface all the way back towards the end tabs. The log (number of cycles to failure) decreased linearly as the maximum fatigue stress level increased. (C) 2013 Elsevier Ltd. All rights reserved.
Authors
I am an author on this paper
Click your name to claim this paper and add it to your profile.
Reviews
Recommended
No Data Available