Abstract
Fibre-metal laminates are an attractive alternative for monolithic aluminium alloys in primary aircraft structures. The fatigue crack initiation behaviour and fatigue crack growth behaviour of laminates in joints under realistic loading conditions are superior to those of aluminum alloys. The damage tolerance of GLARE structures is significantly better than that of aluminiu alloys. The superior behaviour of laminates can be translated into weight savings in aircraft structures, combined with cost savings in production. However, fibre-metal laminates could be the only option from a safety standpoint for large parts of the new generation of large aircraft. A new design philosophy based on an increased level of safety compared with today's standards (focusing on fire resistance and improved damage tolerance and inspectability) might require the use of laminates.
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