Abstract
This paper presents the results of analytical and test study on fracture behaviour of aluminium alloys applied in lower and upper wing surfaces and in fuselage skin. Characteristics of static strength, fatigue, residual strength and crack growth had been studied. Fatigue and crack growth had been analysed at cyclic loads and at standardized quasi-random load spectra. Fatigue life had been analyzed basing on linear hypothesis of damage accumulation. Crack growth was calculated using linear as well as retardation\acceleration models. Comparison of fracture behaviour of different aluminium alloys had been carried out. © Springer Science+Business Media B.V. 2009.
Cite
CITATION STYLE
Nesterenko, B., I.nesterenko, G., & N.basov, V. (2009). Fracture behaviour of skin materials of civil airplane structures. In ICAF 2009, Bridging the Gap Between Theory and Operational Practice - Proceedings of the 25th Symposium of the International Committee on Aeronautical Fatigue (pp. 661–683). Kluwer Academic Publishers. https://doi.org/10.1007/978-90-481-2746-7_38
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