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190 ALEKSANDR KORJAKIN ET AL. Figure 9. Modal loss factors of the sandwich cylindrical panel for modes 1 – 1–1 – 4. Vibration and Damping Analysis of a Composite Sandwich Conical Shell A three-layered composite conical shell has been considered. The shell has two variants of boundary conditions: clamped-clamped and simply supported-simply supported from both sides. The following geometric characteristics are presented: the thickness of outer layers h t = 0.0005 m and core h c = 0.004, 0.005, 0.006, ..., 0.012 m, the radius of the cone at its small end R = 0.27 m, the semi-vertex angle β = 7.0°, the meridional length of the cone L = 0.84 m, Figure 6. The layers are with the following properties of material: outer from glass epoxy E t = 25.0 GPa, ν t = 0.20, p t = 2800 kg/m 3 and inner from aluminium honeycomb E1 c =0.529 GPa, E2 c c c = 0.226 GPa, ν 12 = ν 23 = 0.2, ρ c = 36.80 kg/m 3 . The loss factor was assumed zero (η t = 0) for outer layers and η c = 0.4 for the core. The results for the natural frequencies and modal loss factors of sandwich conical shell with different core thickness obtained by using finite element CLW54 are presented in Figures 10 and 11 for clamped-clamped and Figures 12 and 13 for simply supported boundary conditions. Vibration and Damping Analysis of Composite Sandwich Spherical Shell A three-layered composite spherical shell has been considered. The shell is
Free Damped Vibrations of Sandwich Shells of Revolution 191 Figure 10. Natural frequencies of the sandwich conical shell (clamped-clamped). Figure 11. Modal loss factors of the sandwich conical shell (clamped-clamped). Figure 12. Natural frequencies of the sandwich simply supported conical shell.
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