Theory Of Elastic Oscillations

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Space Station Systems

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ISBN : UOM:39015023293965
Genre : Space stations
File Size : 66.62 MB
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Category: Space stations

Large Amplitude Oscillations Of Elastic Rods

Author : Kevin William MacEwen
ISBN : CORNELL:31924081457123
Genre :
File Size : 48.9 MB
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We consider several problems involving large amplitude periodic motions of rods. In each case we study the stability of these systems as a parameter is varied. We then investigate the existence of large amplitude motions which accompany a change in stability.
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Journal Of Rheology

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ISBN : MINN:31951D003193697
Genre : Rheology
File Size : 52.80 MB
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Category: Rheology

Proceedings

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ISBN : PSU:000012142545
Genre : Medical electronics
File Size : 22.14 MB
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Category: Medical electronics

Mathematical Reviews

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ISBN : UOM:39015049327961
Genre : Mathematics
File Size : 74.33 MB
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Category: Mathematics

Nonlinear Oscillations Of Elastic Panels In A Supersonic Nonviscous Airstream

Author : Stanford University. Department of Aeronautics and Astronautics
ISBN : STANFORD:36105046320342
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File Size : 53.91 MB
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A variational analysis is presented for the problem of a panel under the influence of both random excitation (turbulent boundary layer) and aerodynamic loading. Geometric nonlinear effects in the panel are taken into account, and a (Rayleigh-Ritz) modal approximation is used to represent the spatial variation of the displacements. The supercritical (beyond linear flutter boundaries) limit-cycle amplitude and frequency are determined by assuming a Fourier-series representation for the modal amplitudes, thereby reducing the problem to solving a set of nonlinear algebraic equations. The aerodynamic loads resulting from the panel deformation are approximated by linear piston theory. Random excitation in the form of a pressure with known spatial and temporal correlations is then introduced. The forced response is calculated with the aid of Fourier-transform techniques and a method of equivalent linearization at flow conditions below and above the stability boundary for classical panel flutter. The effect of random excitation on the supercritical response is reduced to a study of coupled nonhomogeneous Mathieu equations. The solution of these equations is determined approximately using the digital computer. The determination of the amplitude of response and the frequency of oscillation provides the necessary information for a fatigue analysis. (Author).
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