Fiber metal laminates (FMLs) are widely used in aerospace industries nowadays. Repairing
of the cracks in these advanced materials 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
glass-epoxy composite layers. Three different crack lengths in three crack angles and
different patch lay-ups were examined. It was observed that no matter what the crack
length was, the more the crack angle is larger, the more ultimate tensile strength of the
structure became. It was also indicated that the patch lay-up had an important effect on
the tensile response of the repaired specimens. When the aluminum layer of the patches was
farther from the repair zone, the ultimate tensile strength reached to its maximum value.