面内力を受ける複合材補強平板の固有振動の簡易解析法

概要

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As a recent trend, composite materials are used in many parts of structural components for the newly developed aircraft and launch vehicles. The main structures of aerospace vehicles are semi-monocoque construction, which are composed of skins, stringers and frames. The composites are used as laminated stiffened panels for the wings and fuselages. During the service of aircraft and launch vehicles, their outer surface such as wing, fuselage and engine covers are exposed to severe acoustic environment due to their engine exhaust noise. Therefore, it is important to consider vibration characteristics in the structural design of airframes. This paper describes a simple analysis method of free vibration of rectangular plates and stiffened plates. This method can deal with isotropic and anisotropic plates with several boundary conditions under in-plane stress. The accuracy of the analysis of this method was verified by comparing with theoretical analysis and finite element method (FEM) using NASTRAN. The natural frequencies obtained by the present analysis are within the allowable error bounds of those by detail analysis method. Consequently, this method was designed to be an effective calculation tool for the vibration analysis in the early phase of airframe design. As an example, this paper describes analysis result of the relation between in-plane stress level and natural frequencies of a laminated composite plate.
2009-04-25