The concept of repairing cracked aluminum aircraft structures with composite patches was investigated both analytically and experimentally. Coupon tests provided basic mechanical properties of composite patches manufactured using a repair procedure. A new surface treatment for bonding patches was developed and optimized. The damage repair process was substantiated by elements and beam testing. Crack growth predictions were made using analytical stress intensity factors for the patched structure, and excellent correlation was obtained between observed and predicted values. Patches were very effective in reducing the crack growth rate. Cracks of patched element specimens which propagated to failure during random spectrum fatigue loading survived without failure for much longer lifetimes (approx. 3.5 times) under all tested environmental conditions. The process was then substantiated by repairing and testing a defective beam element.
Repair of cracked aluminum aircraft structure with graphite/epoxy patches
Reparatur von gerissenen Aluminiumkonstruktionen in Flugzeugen mit Flecken aus graphitverstärktem Epoxidharz
1993
8 Seiten, 7 Bilder, 1 Tabelle, 3 Quellen
Conference paper
English
Reparatur , Aluminium , Flugzeugbau , mechanische Festigkeit , carbonfaserverstärkter Kunststoff , Materialbruch , praktische Untersuchung , Rissgeschwindigkeit , Rissausbreitung , Rissstillstand , Wechsellast (mechanisch) , Lebensdauer , Flugzeug , Luftfahrtindustrie , Festigkeit , faserverstärkter Kunststoff , Kohlenstoffaser , experimentelle Untersuchung , Geschwindigkeit , Schwingbeanspruchung , zyklische Belastung
Analysis of Cracked Aluminum Plates Repaired with Bonded Composite Patches
Online Contents | 1996
|Analysis of Cracked Aluminum Plates Repaired With Bonded Composite Patches
British Library Conference Proceedings | 1995
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