Considering the fact that the foundation data for a new X850 ± IM190 carbon/epoxy material system adopted in commercial aircraft industry are extremely scarce in the literature, an in-plane, static tensile experiment was carried out to investigate the bearing performance of double-lap, single-bolt joints in X850 ± IM190 carbon fiber-reinforced polymer (CFRP) composites. The effects of ply ratio, 0° layers’ combination percentage, bolt diameter, and curing method were considered. Then, special attention was paid to determine the design parameters of X850 ± IM190 CFRP bolted joints, such as tensile strength of un-notched laminate and stress concentration relief factor. Based on these design parameters, an efficient semianalytical approach was established to obtain the ultimate bearing strength of the joints. The failure prediction exhibited excellent agreement with the experimental data. These results will play an important role in design and strength evaluation of X850 ± IM190 CFRP bolted joints.

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