Abstract
Traditionally, the adhesive layer in adhesively bonded joints is simplified as having constant shear and peel stresses across the thickness. In this study, it is modeled as a separate 3D elastic body without the uniform stress assumption. The stress state in an adhesively bonded fiber-reinforced composite tubular joint subjected to a torsional load is theoretically analyzed. A finite difference method is utilized to solve the system of equilibrium equations. The solution is validated by comparison with data found in the literature. The effects of fiber orientation, composite laminate stacking sequence, overlap length, adhesive layer thickness, and adhesive stiffness on the shear and peel stress distribution are evaluated and presented. The results show that all the six stress components are present and they vary considerably across the adhesive layer thickness; 3D analysis is desired, especially for general laminated composite adherends.
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