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The fibre metal laminates offer significant improvements over traditional materials for aircraft structures. The prime drivers of their development are weight reduction and improved damage tolerance characteristics, but it turns out that they have additional benefits which become more and
more important for today's designers, e.g. cost reduction and improved safety. The combination of aspects typical of each constituent materials in one material is an extraordinary achievement. This work concerns the analysis of the in-plane shear strength of Hybrid Titanium Composite Laminate developed for high temperature in aeronautical and space applications. The Hybrid Titanium Composite laminate (HTCL) keeps the mechanical advantages of existing hybrid composite laminates such as ARALL and GLARE while extends their applications to harsh environments. HTCL has proven to possess exceptional strength and fatigue resistance. Hybrid composite laminates, consisting of layers of Titanium grade 2 and Titanium grade 5 foils bonded together with fibre-reinforced composite plies and with carbon + PEEK plies, have been utilised in the “Single Lap Shear” tests for the analyses of the bond strength. Special attention has been paid to surface treatments, which appear critical in Titanium bonding: both a mechanical one such as plasma spray and a chemical one such as chromic acid anodisation, have been tested on HTCL laminate in order to verify mechanical performances of the interface. As expected, different results have been acheived for the two treatments: in particular plasma spray denoted good resistance but lower ductility compared to ionic anodisation.