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- W2030059524 abstract "Forced vibrations of a cylindrical panel freely supported in contour, with regular orthogonal system of stiffeners (typical of aircraft fuselage structure) are investigated. The connection of all three components of displacement of the skin and of discrete stiffeners as well as of the respective elastic and inertial forces and moments are taken into account in the case of excitation by normal and tangential forces. This connection can be described correctly at joint application of the recreptance method and the method of space-harmonics. The task of forced vibrations is solved directly except the procedure of solving the task in terms of eigen-values. Some illustrative examples of the aircraft fuselage panel by a concentric harmonic force are presented. They demonstrate a high efficiency of applying this combined method. Potential possibilities of using this combined method for solving the tasks related to vibrations of a framed skin modeling the aircraft fuselage section and to the sound field in the volume bounded by it are considered." @default.
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- W2030059524 date "2008-05-01" @default.
- W2030059524 modified "2023-09-27" @default.
- W2030059524 title "Forced vibrations of a cylindric panel with regular orthogonal system of stiffeners" @default.
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- W2030059524 doi "https://doi.org/10.1121/1.2933763" @default.
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