軸圧縮荷重を受ける繊維強化ハイブリッド複合材料平板の最適設計 : アスペクト比が1より小さい場合(<小特集>強化プラスチック)

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In recent years high-modulus fibers such as boron and graphite have been widely used in many aerospace applications in the forms of hybrid composites along with glass or Kevlar fibers. In this paper presented is an analytical method useful for designing optimum hybrid plates subject to a given compressive load. It is assumed that the hybrid plate is symmetric and consists of two surface layers and a core, and that the ply material for the surface has high performance and is expensive, while the ply material for the core has low performance and is inexpensive. The object of the design problem is to minimize the cost of the hybrid plates, which corresponds to the maximization of the core thick-ness ratio. The proposed method is based on the flexural lamination parameter diagram of hybrid composites. The feasible design region where the constraint on the buckling load is satisfied becomes smaller as the core thickness ratio increases, and the region finally reduces to a point. The optimum solution can be obtained under this condition. The optimum fiber orientation in both the surface and the core and the optimum core thickness ratio can be obtained easily by using the proposed method. It is found that neither the optimum fiber orientation of the surface nor that of the core is affected by the elastic constants or the fiber orientation of the other material. This means that the optimization of hybrid composites can be done by the independent optimizations of each component materials.
1987-03-15

軸圧縮荷重を受ける繊維強化ハイブリッド複合材料平板の最適設計 : アスペクト比が1より小さい場合(<小特集>強化プラスチック)

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