The dynamic response of an aircraft panel forced at resonance and off-resonance by plane acoustic waves at normal incidence is investigated experimentally and numerically. Linear, nonlinear (period doubling), and chaotic responses are obtained by increasing the sound pressure level of the excitation. The response time history is sensitive to the input level and to the frequency of excitation. The change in response behavior is due to a change in input conditions, triggered either naturally or by modulation of the bandwidth of the incident waves. Off-resonance bifurcation is diffused and difficult to maintain; thus the panel response drifts into a linear behavior. The acoustic pressure emanated by the panel is either linear or nonlinear as is the vibration response. The nonlinear effects accumulate during the propagation with distance. Results are also obtained on the control of the panel response using damping tape on an aluminum panel and a graphite epoxy panel having the same size and weight. Good agreement is obtained betwen the experimental and numerical results.
Nonlinear vibration and radiation from a panel with transition to chaos
AIAA Journal ; 30 , 11
1992-11-01
Sonstige
Keine Angabe
Englisch
Nonlinear Vibration and Radiation from a Panel with Transition to Chaos Induced by Acoustic Waves
British Library Conference Proceedings | 1992
|Chaos in nonlinear dynamic systems: helicopter vibration mechanisms
Tema Archiv | 2007
|Study on the chaos anti-control technology in nonlinear vibration isolation system
Online Contents | 2008
|Forward Motion Effects on Jet Noise, Panel Vibration, and Radiation
Online Contents | 1996
|