繊維強化樹脂/金属積層板のピン継手の界面応力に及ぼす材料定数と塑性の効果

概要

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Fiber metal laminates (FML) are composites laminated by fiber reinforced plastics (FRP) and aluminum alloy. GLARE, one of the FML laminated by Glass Fiber Reinforced Plastics and aluminum alloy, has been applied to an upper fuselage panel in an Airbus A380. The precise stress distribution of the out of plane components has not been discussed around the contact hole boundary, though several papers applied the three dimensional (3D) finite element method (FEM) to GLARE for delamination failure analysis. This paper applies 3D-FEM to a GLARE pin joint and obtains the characteristic stresses near the contact region. Effects of material properties and plasticity on the distribution and magnitude of stresses are discussed together with previous results of Carbon FML obtained by the present authors. It was found that within the practical range of material properties and loading stroke, their effects on the stress distribution are small and that the magnitude depends on them. A model that relates the out of plane normal stress σ ZZ with the longitudinal stiffness of FRP is presented, which explains well the several numerical results.
Research Institute for Applied Mechanics, Kyushu Universityの論文