| DOI | Resolve DOI: https://doi.org/10.1016/j.ijfatigue.2006.07.003 |
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| Author | Search for: Liao, M.1; Search for: Renaud, G.1; Search for: Bellinger, N. C.1 |
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| Affiliation | - National Research Council of Canada. NRC Institute for Aerospace Research
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| Format | Text, Article |
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| Subject | aircraft; aluminum alloys; computer simulation; corrosion; fractography; nondestructive examination; exfoliation corrosion; life prediction; prior corrosion and fatigue; fatigue of materials |
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| Abstract | 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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| Publication date | 2006-09-12 |
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| In | |
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| Language | English |
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| Peer reviewed | Yes |
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| NPARC number | 21275956 |
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| Export citation | Export as RIS |
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| Report a correction | Report a correction (opens in a new tab) |
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| Record identifier | 0103d838-bae4-4f19-9e0a-33ae2be829a2 |
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| Record created | 2015-08-21 |
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| Record modified | 2020-04-22 |
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