Flexural behavior of CFRP-aluminum fuselage frames with bolted splice joints

Abstract Few work concerned on the flexural strength of carbon fiber reinforced plastic (CFRP)-aluminum fuselage frames with bolted splice joints used in aeronautical industry. To provide help for design CFRP aircraft strcutures, this paper investigated behavior CFRP-aluminum experimentally. Firstly, were fabricated mid-span joints. The comprised: or unreinforced aluminum plates to frames. bolt diameters 4.76mm and 6.35mm. Then, effects plate dimeter through four-point bending test. It has been shown that introduction improves structural load capacity. However, increasing diameter lowers This jointed structure is a representative part rear fuselage, experimental results will be commonly instructive joining applications.