Summary
Repairs using bonded composites have numerous advantages over mechanically fastened repairs. Adhesive bonding does not result in stress concentrations due to additional fastener holes. Composites are readily formed into complex shapes, permitting the repair of irregular components. In service damage monitoring is possible, with the appropriate fibre matrix system, by direct inspection through the repair using eddy current methods or by thermal emission measurements. This paper presents a bonded repair for fuselage lap joints containing multi-site damage. The effectiveness of this repair is confirmed by the results of a laboratory test program.
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References
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© 1991 Springer-Verlag Berlin, Heidelberg
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Jones, R., Bridgford, N., Wallace, G., Molent, L. (1991). Bonded Repair of Multi-Site Damage. In: Atluri, S.N., Sampath, S.G., Tong, P. (eds) Structural Integrity of Aging Airplanes. Springer Series in Computational Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-84364-8_14
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DOI: https://doi.org/10.1007/978-3-642-84364-8_14
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-84366-2
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