This paper presents an investigation on the effectiveness of crack growthretarders bonded to integral metallic structures. The study was performed byboth numerical modelling and experimental tests. It focuses on aluminium alloypanels reinforced by bonded straps made of carbon-epoxy, glass-epoxy compositematerials or a titanium alloy. The goal was to develop a fail-safe design forintegrally stiffened skin-stringer panels applicable to aircraft wingstructures. The modelling strategy and finite element models are presented anddiscussed. The requirements that the models should meet are also discussed. Thestudy has focused on establishing the extent of crack retarder benefits, interms of fatigue crack growth life improvement, by numerical simulation andexperimental tests of various crack retarders. The results of predicted fatiguecrack growth retardation have been validated by tests of laboratory samples.This study concludes that by bonding discrete straps to an integral structure,the fatigue crack growth life can be significantly improved.
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