A Numerical and Experimental Study of Carbon Fibre Riveted Splice Joints

This paper investigates the maximum stress in the riveted splice joint of an aircraft wing due to tensile loading. Riveted joints are used in aircraft assembly because of their reliability as well as high strength. Research is based on previous work done on riveted splice joints in aeroplane fuselage which is attached to the skin of the airship. The analysis considers the strength of splice joints used in aerofoils consisting of two stringers and one splice which are connected to each other by means of aluminium rivets to form a single cover butt joint. This aluminium riveted carbon fibre structure is analysed using experimental tests and these results are validated using numerical simulations. The stress analysis of the splice joint is carried out to compute the stress under tensile load as well as to determine the mode of a failure. Refining of the numerical model was also undertaken to produce accurate results closer to that of the experimental findings