This paper presents the modelling and testing of the effects of exfoliation corrosion on the structural integrity of an aluminium 7075-T651 wing upper skin. Finite element and fatigue strength analyses were carried out to quantify the impact of exfoliation corrosion and grind-out repairs at fastener holes on a wing upper skin under a fighter aircraft spectrum loading. The analytical models were compared and validated by test results. The tests were performed on 27 fatigue coupons in a pristine, naturally and artificially corroded and grinded condition. The models provide an engineering tool for quick assessment of the effects of exfoliation corrosion damage on wing upper skins as well as guidance on possible grind-out repair actions.
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Uebersax, A., Huber, C., Renaud, G., Liao, M. (2009). Structural Integrity Of A Wing Upper Skin With Exfoliation Corrosion. In: Bos, M.J. (eds) ICAF 2009, Bridging the Gap between Theory and Operational Practice. Springer, Dordrecht. https://doi.org/10.1007/978-90-481-2746-7_15
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DOI: https://doi.org/10.1007/978-90-481-2746-7_15
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