| DOI | Trouver le DOI : https://doi.org/10.1016/j.ijfatigue.2006.07.003 |
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| Auteur | Rechercher : Liao, M.1; Rechercher : Renaud, G.1; Rechercher : Bellinger, N. C.1 |
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| Affiliation | - Conseil national de recherches du Canada. Institut de recherche aérospatiale du CNRC
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| Format | Texte, Article |
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| Sujet | aircraft; aluminum alloys; computer simulation; corrosion; fractography; nondestructive examination; exfoliation corrosion; life prediction; prior corrosion and fatigue; fatigue of materials |
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| Résumé | This paper presents the results of testing and modeling studies on the remaining fatigue life of aircraft wing skins containing natural exfoliation corrosion. Dogbone specimens were manufactured from 7075-T6511 upper wing panels containing natural exfoliation. The maximum depth of the exfoliation damage was determined by an ultrasonic non-destructive inspection (NDI). Fatigue tests were carried out under fully reversed constant amplitude loading (R = -1.0), and fractographic analyses were performed to examine the cracking mechanisms in the exfoliation region. Based on the test findings, a simplified fatigue model was developed to estimate the remaining fatigue life of the corroded specimens. In this model, the exfoliation damage was assumed as a surface crack with a depth that was presumably available from an NDI or grindout database. The comparison indicates that the simplified model gave a good estimation for the remaining fatigue life of the naturally exfoliated specimens. |
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| Date de publication | 2006-09-12 |
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| Dans | |
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| Langue | anglais |
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| Publications évaluées par des pairs | Oui |
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| Numéro NPARC | 21275956 |
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| Exporter la notice | Exporter en format RIS |
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| Signaler une correction | Signaler une correction (s'ouvre dans un nouvel onglet) |
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| Identificateur de l’enregistrement | 0103d838-bae4-4f19-9e0a-33ae2be829a2 |
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| Enregistrement créé | 2015-08-21 |
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| Enregistrement modifié | 2020-04-22 |
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