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- W4239554270 abstract "This paper considers the response of thin elastic plates to sinusoidal acoustic excitation. A theoretical method for obtaining the dynamic deflection and stress in the nonlinear region is given. The theory is compared with test results and shows rather good agreement with these tests. The application of the theory to the design of panels to withstand acoustic fatigue is discussed in the latter part of the paper. The basic assumption involved in the theory is that the panel behaves like a nonlinear spring with a restoring force of F = C1w+C2w3, where F is the restoring force, C1, and C2 are constants which depend upon the physical characteristics of the panel, and w is the deflection of the center of the panel. The constants C1, and C2 are found from the static large deflection curves obtained either theoretically (S. Way, Proceedings Fifth International Congress of Applied Mechanics, Cambridge, Massachusetts, 1938) or experimentally. The amplification factors for the resonant response of the plate are obtained by combining these static large deflection curves with the nonlinear vibration analysis as given in “Nonlinear Vibrations,” by J. J. Stoker, Interscience Publishers, Inc., 1950. Experiments were conducted on aluminum panels, some containing Z stiffeners. The panels were excited by a horn and strains were picked up by use of SR-4 strain gages. Square panels up to length of side/thickness = 120 exhibited nonlinear behavior under sound pressure of 150 db. The magnification factors calculated by use of linear theory were approximately five times those actually experienced, while those calculated by use of the nonlinear theory presented in this paper were of the same order of magnitude as those obtained in the experiments." @default.
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- W4239554270 date "1957-01-01" @default.
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- W4239554270 title "Nonlinear Response of Aircraft Panels to Acoustic Noise" @default.
- W4239554270 doi "https://doi.org/10.1121/1.1918451" @default.
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