ABSTRACT
Chapter 5 brings out the effects of loading on the performance of the functionally graded adhesively bonded assembly. These tee joint structures are extensively used in fuselage bulkhead-to-skin, rib-to-skin, spar-to-skin and longer on-to-skin interfaces. T-stiffeners are also widely used in aircraft wings to prevent buckling during wing loading. The behavior and performance of the tee joint structure must be known to designers to ensure the joint reliability and structural integrity. The structure having tee joint is expected to be subjected to tensile, compressive, bending, or combination during the service conditions. Stress analysis of these loading conditions is of utmost importance for a tee joint designer. Design and analysis of tee joint structure become a challenge for the designer/researcher when functionally graded adhesive materials and laminated fiber-reinforced polymeric (FRP) composites are used. The performances and behavior of adhesively bonded double supported tee joint subjected to a general loading, including bending were presented in this chapter. Three-dimensional geometrically nonlinear finite element simulations have been carried out to evaluate the stresses at different surfaces under different loading conditions. Subsequently, a coupled stress failure criterion has been employed to evaluate the failure indices to predict damage onset location for the tee joint structure under general loading conditions. A series of numerical simulations have been performed to indicate the effect of functionally graded adhesive with varied modulus ratios on the out-of-plane stresses induced in the joint structure.
