The effects of disbonds on the stress intensity factor of aluminium panels repaired using composite materials

Modeling of a cracked and repaired Al 2024T3 aircraft plate: effect of the composite patch shape on the repair performance

“…Whatever the applied stress intensities, the repair becomes more and more effective and efficient with the use of the wider patch. This behaviour was observed by Dajmel Ouinas [16] and al, Mahadesh Kumar and al. [13] and confirmed by Ramji and al.…”

Experimental and numerical analysis of bonded composite patch repair in aluminum alloy 7075 T6

“…Denney and Mall [11] conducted a series of experiments to investigate the effects of disband location and size on the fatigue response of cracked thin aluminum panels repaired with bonded composite patches [12]. Bachir Bouiadjra et al [13], Ouinas et al [14] and Amiri et al [15] studied the effect of the adhesive disband on the amplification of the stress concentrations at the notch root and the stress intensity factor at the crack tip. They concluded that the stress intensity factor increases significantly if there is an adhesive disband over the crack region.…”

Comparison between composite and metallic patches for repairing aircraft structures of aluminum alloy 7075 T6

“…They showed that this rigidity was highly improved by the presence of the Boron/Epoxy patch repair or reinforcement. Ouinas et al [3] made a comparison between the Boron/epoxy and Graphite/Epoxy for repairing aircraft structures. They reported that the reduction of the stress intensity factor at the crack tip is more significant for Boron/epoxy patch; In addition; the thermal residual stresses due to the adhesive curing are less significant.…”

“…Nevertheless, the cured graphite fibers composites are very abrasive and require diamonds tipped tools for cutting or machining. Several experimental and numerical researches were performed to analyze the performance of bonded composite repairs [2][3][4][5][6]. Clemczyk et Belason [2] analyzed the effect of boron/epoxy patches on the rigidity of the aircraft metallic structures.…”