Abstract
A test campaign has been performed to investigate the design of fuselage stiffened panels with different metallic skin concepts (monolithic vs. Metal Laminates), stringer materials and local reinforcements from aluminum, titanium and glass-fiber. Observations were made on the crack growth retardation mechanisms. Bonded doublers and selective reinforcements confirmed to be outstanding tools to improve the damage tolerance properties of structural elements with a minor weight increase. © Springer Science+Business Media B.V. 2009.
Cite
CITATION STYLE
Meneghin, I., Pacchione, M., & Vermeer, P. (2009). Investigation on the design of bonded structures for increased damage tolerance. In ICAF 2009, Bridging the Gap Between Theory and Operational Practice - Proceedings of the 25th Symposium of the International Committee on Aeronautical Fatigue (pp. 427–447). Kluwer Academic Publishers. https://doi.org/10.1007/978-90-481-2746-7_25
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