CHARACTERIZING THE DYNAMIC RESPONSE OF A THERMALLY LOADED, ACOUSTICALLY EXCITED PLATE
In this work the dynamic response is considered of a homogeneous, fully clamped rectangular plate subject to spatially uniform thermal loads and narrow-band acoustic excitation. In both the pre-and post-buckled regimes, the small amplitude, linear response is confirmed. However, the primary focus is...
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| Published in | Journal of sound and vibration Vol. 196; no. 5; pp. 635 - 658 |
|---|---|
| Main Authors | , , |
| Format | Journal Article |
| Language | English |
| Published |
London
Elsevier Ltd
10.10.1996
Elsevier |
| Subjects | |
| Online Access | Get full text |
| ISSN | 0022-460X 1095-8568 |
| DOI | 10.1006/jsvi.1996.0506 |
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| Abstract | In this work the dynamic response is considered of a homogeneous, fully clamped rectangular plate subject to spatially uniform thermal loads and narrow-band acoustic excitation. In both the pre-and post-buckled regimes, the small amplitude, linear response is confirmed. However, the primary focus is on the large amplitude, non-linear, snap-through response, because of the obvious implications for fatigue in aircraft components.
A theoretical model is developed which uses nine spatial modes and incorporates initial imperfections and non-ideal boundary conditions. Because of the higher order nature of this model, it is inherently more complicated than a one-mode buckled beam equation (Duffing's equation). An experimental system was developed to complement the theoretical results, and also to measure certain system parameters for the model which are not available theoretically.
Several analysis techniques are used to characterize the response. These include time series, power spectra and autocorrelation functions. In addition, the fractal dimension and Lyapunov exponents for the response are computed to address the issue of spatial dimension and temporal complexity (chaos), respectively. Comparisons between theory and experiment are made and show considerable agreement. However, these comparisons also serve to point out difficulties in computing the fractal dimension and Lyapunov exponents from experimental data. |
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| AbstractList | In this work the dynamic response is considered of a homogeneous, fully clamped rectangular plate subject to spatially uniform thermal loads and narrow-band acoustic excitation. In both the pre-and post-buckled regimes, the small amplitude, linear response is confirmed. However, the primary focus is on the large amplitude, non-linear, snap-through response, because of the obvious implications for fatigue in aircraft components.
A theoretical model is developed which uses nine spatial modes and incorporates initial imperfections and non-ideal boundary conditions. Because of the higher order nature of this model, it is inherently more complicated than a one-mode buckled beam equation (Duffing's equation). An experimental system was developed to complement the theoretical results, and also to measure certain system parameters for the model which are not available theoretically.
Several analysis techniques are used to characterize the response. These include time series, power spectra and autocorrelation functions. In addition, the fractal dimension and Lyapunov exponents for the response are computed to address the issue of spatial dimension and temporal complexity (chaos), respectively. Comparisons between theory and experiment are made and show considerable agreement. However, these comparisons also serve to point out difficulties in computing the fractal dimension and Lyapunov exponents from experimental data. |
| Author | Murphy, K.D. Rizzi, S.A. Virgin, L.N. |
| Author_xml | – sequence: 1 givenname: K.D. surname: Murphy fullname: Murphy, K.D. organization: Department of Engineering Mechanics, University of Nebraska, Lincoln, NE 68588-0347, U.S.A – sequence: 2 givenname: L.N. surname: Virgin fullname: Virgin, L.N. organization: Department of Mechanical Engineering, Duke University, Durham, NC 27708-0300, U.S.A – sequence: 3 givenname: S.A. surname: Rizzi fullname: Rizzi, S.A. organization: NASA Langley Research Center, Structural Acoustics Branch, Hampton, VA 23681-0001, U.S.A |
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| Keywords | Dynamic response Acoustic wave Fatigue Dynamic loads Numerical method Thermal load Experimental study Narrow band Fractal Dynamic stability Testing equipment Rectangular plate Non linear effect Aircraft |
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| SubjectTerms | Acoustics Exact sciences and technology Fundamental areas of phenomenology (including applications) Physics Solid mechanics Structural acoustics and vibration Structural and continuum mechanics Vibration, mechanical wave, dynamic stability (aeroelasticity, vibration control...) Vibrations and mechanical waves |
| Title | CHARACTERIZING THE DYNAMIC RESPONSE OF A THERMALLY LOADED, ACOUSTICALLY EXCITED PLATE |
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