Abstract
It has been experimentally shown [1-5] the possibility to obtain with hybrid (bolted/bonded) joining technology higher static failure load and a longer fatigue life than the corresponding bolted or bonded joints by using a suitable adhesive. This paper aims at comprehensively showing, by both a simplified analytical approach and an accurate three-dimensional finite element analysis that the application of hybrid (bolted/bonded) joining technology instead of the classical bolted technology allows for a possible improvement of fatigue life. A simplified theoretical analysis is presented to understand the mechanical behaviour of such joints and to provide possible elastic mechanical properties of a suitable adhesive. Then, an accurate three-dimensional Finite Element model is developed to demonstrate the possible benefit on fatigue life. © Springer Science+Business Media B.V. 2009.
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CITATION STYLE
Paroissien, E., Ngoc, C. T. H., Bhugaloo, H., & Ducher, D. (2009). Improving the fatigue life of aeronautical single-lap bolted joints thanks to the hybrid (bolted/bonded) joining technology. In ICAF 2009, Bridging the Gap Between Theory and Operational Practice - Proceedings of the 25th Symposium of the International Committee on Aeronautical Fatigue (pp. 475–492). Kluwer Academic Publishers. https://doi.org/10.1007/978-90-481-2746-7_27
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