Ply-interleaving technique for joining hybrid carbon/glass fibre composite materials

Ahamed, J, Joosten, M, Callus, P, John, S and Wang, C 2016, 'Ply-interleaving technique for joining hybrid carbon/glass fibre composite materials', Composites Part A: Applied Science and Manufacturing, vol. 84, pp. 134-146.

Document type: Journal Article
Collection: Journal Articles

Title Ply-interleaving technique for joining hybrid carbon/glass fibre composite materials
Author(s) Ahamed, J
Joosten, M
Callus, P
John, S
Wang, C
Year 2016
Journal name Composites Part A: Applied Science and Manufacturing
Volume number 84
Start page 134
End page 146
Total pages 13
Publisher Elsevier Ltd
Abstract Efficiently joining materials with dissimilar mechanical and thermal properties is fundamental to the development of strong and lightweight load-bearing hybrid structures particularly for aerospace applications. This paper presents a ply-interleaving technique for joining dissimilar composite materials. The load-carrying capacity of such a joint depends strongly on several design parameters such as the distance between ply terminations, the spatial distribution of ply terminations, and the stiffness and coefficients of thermal expansion of the composites. The effects of these factors on the strength of quasi-isotropic hybrid carbon/glass fibre composite are investigated using combined experimental, analytical and computational methods. Through fractographic analyses significant insights are gained into the failure mechanism of the hybrid joints, which are then used to aid the development of predictive models using analytical and high fidelity computational methods. To characterise the interaction between transverse matrix cracking and delamination, continuum damage mechanics model and cohesive zone model are employed. The predictions are found to correlate well with experimental data. These modelling tools pave the way for optimising hybrid joint concepts, which will enable the structural integration of dielectric windows required for multifunctional load-bearing antenna aircraft structures.
Subject Aerospace Engineering not elsewhere classified
Keyword(s) A. Hybrid
B. Strength
E. Joint
DOI - identifier 10.1016/j.compositesa.2016.01.010
Copyright notice © 2016 Elsevier Ltd. All rights reserved.
ISSN 1359-835X
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Citation counts: TR Web of Science Citation Count  Cited 10 times in Thomson Reuters Web of Science Article | Citations
Scopus Citation Count Cited 3 times in Scopus Article | Citations
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