Abstract
This article presents the finite element analysis of a bolted composite/metal hybrid panel assembly subjected to uniform pressure loading. The structure consists of four EG/VE stiffened panels joined together by a hybrid connection configuration. A simplified modeling approach is presented, where effective section properties of the hybrid joint regions are computed according to the behavior of each section. The modeling approach is verified with available experimental data, and the global panel deflections as well as the strains within the bulk of the panels are in good agreement with the test results. Parametric studies are presented to quantify the influence of the geometry of the joint constituents on the global response of the hybrid assembly. The model response is most sensitive to changes in the steel component geometries, while the composite laminate geometry has a modest localized effect at the joint region. This approach is useful for global modeling of hybrid joints in large-scale structures, where extensive detailing of the joint region is unfeasible.
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