Abstract
Bonded composite patches have been used for two decades to extend the lives of fatigue-damaged F-16, F-111, B-1B, C-141B, and many other aircraft. One of the key features of the technology is extremely slow crack growth under the bonded repair. Researchers have performed hundreds of experiments on repaired cracked panels, and have reported near-constant crack growth rates for a variety of relatively thin sheet (t < 3 mm or 0.125 inch) configurations and constant amplitude load cases. Constant crack growth rates rely on the existence of a constant crack tip cyclic stress intensity factor, Δ K, underneath the patch.
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