A. Pourkamali Anaraki*, G. H. Payganeh, F. Ashena Ghasemi, A. Fallah
World Academy of Science, Engineering and Technology, UAE, January 29-30, 2012.
Repairing of the cracks by fiber metal laminates (FMLs) was first done by some aeronautical laboratories in early 1970s. In this study, experimental investigations were done on the effect of repairing the center-cracked aluminum plates using the FML patches. The repairing processes were conducted to characterize the response of the repaired structures to tensile tests. The composite patches were made of one aluminum layer and two woven glassepoxy composite layers. Three different crack lengths in three crack angles and different patch lay-ups were examined. It was observed for the lengthen cracks, the effect of increasing the crack angle on ultimate tensile load in the structure was increase. It was indicated that the situation of metal layer in the FML patches had an important effect on the tensile response of the tested specimens. It was found when the aluminum layer is farther, the ultimate tensile load has the highest amount.
Crack; Composite patch repair; Fiber metal laminate (FML); Patch lay-up; Repair surface; Ultimate load.