DGLR-Publikationsdatenbank - Detailansicht
Titel:
The Use of GLARE Fiber Metal Laminate Patches in the Damage Tolerant Riveted Repair of Aluminum Fuselage Structures
Autor(en):
R. Fredell, M.E. Herrschap, J. Schijve, B. van Wimersma
Zusammenfassung:
Riveted repairs to pressurized aluminum alloy fuselage structures are common sources of fatigue "hot spots". Typical repair practices involve relatively thick aluminum sheets riveted in place over corrosion thinning or incidental damage. Often in repair, design consideration is given to static residual strength, while fatigue concerns are generally slighted because the original structure is considered much older than the repair. However, as the average age of large transport aircraft continues to increase, repairs can suffer fatigue damage and present increased inspection requirements to operators.
Veranstaltung:
5th International Conference on Structural Airworthiness of New and Aging Aircraft, Hamburg, 1993
Medientyp:
Conference Poster
Sprache:
englisch
Format:
21,0 x 29,7 cm, 21 Seiten
Veröffentlicht:
DGLR-Bericht, 1993, 1993-02, 5th International Conference on Structural Airworthiness of New and Aging Aircraft - Proceedings; S.279-299; 1993; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn
Preis:
NA
ISBN:
ISSN:
Kommentar:
Klassifikation:
Stichworte zum Inhalt:
structural fatigue
Verfügbarkeit:
Bestellbar
Veröffentlicht:
1993
Dieses Dokument ist Teil einer übergeordneten Publikation037:
5th International Conference on Structural Airworthiness of New and Aging Aircraft - Proceedings