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- W2275804892 abstract "Integrally stiffened carbon fibre composite structures, which are representative for dominantly shear and compression loaded skins of a forward fuselage of a modern fighter aircraft have been repaired by bolted aluminum elements. The design criteria for the repairs and the carbon fibre skin are described. The repaired panels have been tested for static and residual strength after spectrum fatigue loading; the maximum fatigue loads did exceed buckling load of the individual panels. It can be shown that the goal of recovering the ultimate design strength of the structure is achieved for both static and residual strength. The failure loads do not change significantly after spectrum fatigue testing. Repairing monolithic composite structures with bolted aluminum elements is therefore a viable option within the large variety of methods for composite repairs. This method is especially applicable in a field repair situation because standard aluminum elements, tools and equipment can be used." @default.
- W2275804892 created "2016-06-24" @default.
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- W2275804892 date "1991-01-01" @default.
- W2275804892 modified "2023-09-24" @default.
- W2275804892 title "Rapid Repair of Integrally Stiffened Carbon Fibre Composite Structures by Bolted Aluminum Elements" @default.
- W2275804892 hasPublicationYear "1991" @default.
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