Abstract
Composite patch repairing technique of damaged structure has a substantial potential in aircraft maintenance and crack repair in Aluminium alloy. In this work unidirectional Carbon Fiber Reinforced Polymer (CFRP) patch separation from Aluminium alloy surface is studied through interfacial shear stress point of view whereas earlier studies focused their attention on fracture toughness parameters like stress intensity factor (K) and J-integral. These studies elaborated the importance of patch shape, size and material on fracture toughness. To study interfacial shear stress inclined crack is made in Aluminium alloy sheet and CFRP patch is applied by epoxy adhesives. When the repaired Aluminium alloy model is simulated in Abaqus the numerical solution showed reduction in the J-integral but in actual experiments patches tend to delaminate from the leading edge and the crack face. It is observed that out of plane shear stresses 23 play an important role in delaminating the patch from the Aluminium alloy surface. To suppress the delamination by reducing interfacial shear stress, ply thickness is varied by suggested ply drop technique. Design of experiment is conducted for optimum sequence of CFRP ply. Three configurations show reduced interfacial shear stress. This is validated by testing the specimen on universal testing machine.
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