Journal of the Japan Society for Composite Materials

The present paper shows the solution procedure for obtaining the laminate configurations corresponding to the in-plane and/or out-of-plane lamination parameters for the symmetric balanced laminates. The solution procedure is shown for both cases of the infinite number of plies and the finite number of plies. As a numerical example of the present method, a particular class of laminate configurations which is isotropic with respect to the stiffness characteristics is presented.

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This paper describes a stress analysis method based on the finite element method for adhesive bonded joints whose adherends have apparent laminate structure as well as the fiber cloth reinforced composites. The former analysis method for adhesive bonded joints whose adherends are isotropic and homogeneous materials was developed to the present method. For the analysis, the reinforcement layer impregnated with matrix is considered as a one-dimensional plate having the equivalent stiffness. In order to examine this method, a three point bending test of a model joint was conducted and the test result was compared with the calculated one. A good agreement was obtained. Some calculations were conducted for the joints subjected to tensile shear loading. The calculated result reveals the typical failure modes of the FRP single joints. Namely, it is found that relatively large inter-laminar stress concentrations are occurred in the first matrix layer as well as the adhesive layer. This might be one of reasons for the interlaminar delamination failure of the FRP joints. The first reinforcement layer also has a large normal stress concentration parallel to the loading direction of the joint at the lap end. It might cause the tensile failure of adherends prior to the final joint failure. The effect of tapering at the lap end on reduction of the stress concentration was also discussed.

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