Abstract
The research goal of the present study was to develop and validate a tool for reliable analysis of fatigue crack growth following initiation from several small surface flaws that grow and coalesce when subjected to service loading. Both analytical and experimental methods were applied in a case study of an isolated detail of an F-18 Hornet bulkhead structure selected for this purpose. The experimental part consisted of integral I-type beams, designed to closely simulate a critical part of an F-18 Hornet fuselage bulkhead, which were subjected to actual inflight bending and tension loads in the critical section. The variable amplitude spectrum used in the tests was created based on the operational load measurement results of the F-18 Hornet of the Finnish Air Force. © Springer Science+Business Media B.V. 2009.
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CITATION STYLE
Andersson, B., Blom, A. F., Falk, U., Wang, G. S., Koski, K., Siljander, A., … Lahtinen, R. (2009). A case study of multiple-site fatigue crack growth in the F-18 hornet bulkhead. In ICAF 2009, Bridging the Gap Between Theory and Operational Practice - Proceedings of the 25th Symposium of the International Committee on Aeronautical Fatigue (pp. 707–741). Kluwer Academic Publishers. https://doi.org/10.1007/978-90-481-2746-7_40
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