著者

小林 繁夫 長島 利夫

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.34, no.389, pp.332-339, 1986-06-05 (Released:2009-05-25)

参考文献数

10

被引用文献数

1 1

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Three subjects are studied for the vibration characteristics of laminated graphite-epoxy cylindrical shell. Firstly the eigen-value problem is exactly solved to obtain the natural frequency of layered composite cylindrical shell by use of Flugge type vibration equation. In the case of two layer crossply and angle-ply laminates the coupling effect decreases the fundamental natural frequency about 20%. For four layer antisymmetric cross-ply and angle-ply, the natural frequency is close to the one of the thickness-wise homogeneous cylindrical shell. However in the case of symmetric four layer crossply the lamination constitution unexpectedly affects the fundamental natural frequency. The natural frequency is explicitly obtained using Donnell type vibration equation of orthotropic cylindrical shell for the S2 boundary condition and the influence of lamination constitution is clarified. The optimum lamination constitutions for the highest fundamental natural frequency are disclosed. It is shown that the quasi-isotropic lamination is not optimal. The influence of lamination constitution on the nonlinear property of resonance curve for the fundamental natural frequency of the shell is analytically studied. It is concluded that the nonlinear property is softening for all laminations and the degree of the softening is stronger in the order of the circumferential layer alone, the ±45° angle-ply, the cross-ply, the quasi-isotropic and the axial alone.