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Adhesively Bonded Carbon-Titanium Joints Under In-plane and Bending Loads

size: 9pt;">The goal of this research is to optimize the design of single-lap joints made by joining composite material to metals. The single-lap joint under both out-of-plane load and tensile load was examined. It is observed that designing a joint for one size: 9pt;">kind of load is not always satisfactory because for other load cases, different stresses size: 9pt;">would govern the design. Local stress peaks were investigated in order to find ways size: 9pt;">to decrease these peaks. An approach for optimizing the joint was chosen so the size: 9pt;">stress peaks at each end could be minimized (peel, axial and shear stress). By tapering the titanium adherend inside and outside, the stress distribution in the adhesive size: 9pt;">can be significantly changed at the tapered end and all three important stresses that size: 9pt;">governed the design (peel, axial and shear stress) are decreased for a joint under tension and out-of-plane load. For dissimilar adherends, the numerically largest stresses size: 9pt;">always occur in the adhesive at the edge of the overlap adjacent to the adherend with size: 9pt;">the lower value of flexural stiffness and the relative difference in these peaks is a function of the relative flexural stiffness of two adherends. Using an outer bead of adhesive decreases the stress peak at composite edge. Thus, two methods are used to
size: 9pt;">reduce adhesive stresses: tapering and addition of adhesive beads. Having completed a finite element stress analysis, the results are used to predict the strength of a size: 9pt;">given joint.

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