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.
Fatigue modeling for aircraft structures containing natural exfoliation corrosion
International Journal of Fatigue ; 29 , 4 ; 677-686
2007
10 Seiten, 26 Quellen
Article (Journal)
English
Aluminiumlegierung , Amplitudenabhängigkeit , Ermüdungslebensdauer , Flügel , Fraktographie , Korrosion , Lebensdauervorhersage , Luftfahrzeug , mathematisches Modell , Modellmethode , Oberflächenriss , Rechnersimulation , Schichtkorrosion , Theorie-Experiment-Vergleich , Tragfläche (Aerodynamik) , Ultraschallprüfung , Werkstoffdatenbank , zerstörungsfreie Prüfung
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