The noise and vibration in an aircraft cabin during cruise conditions is primarily caused by external flow excitations from the turbulent boundary layer (TBL). The TBL causes the fuselage panels on the aircraft to vibrate. These vibrations radiate sound energy in the form of noise. It is of interest to be able to predict the response of these panels to different excitations using an analytical model, so that expensive wind tunnel and flight tests can be minimized when doing noise research. Two existing analytical models were modified to account for different excitations: one with simply supported boundary conditions and the other with arbitrary boundary conditions. These models were programmed and validated against experimental data, obtained by the authors, for a thin rectangular panel with boundary conditions between simply supported and clamped conditions. The goal of this research is to use the models to conduct optimization studies, experimentally simulate the resulting vibration response on a panel subjected to TBL pressure fluctuations and to use a piezo-electric patch as a means of experimentally simulating the same panel response from a TBL excitation. It is shown that the modified analytical models accurately predict the panel response for a point force excitation, for a TBL excitation, and for an oscillating piezoelectric patch excitation.

Additional Metadata
Keywords Aeroacoustics, Analytical model, Power spectral density, Structural acoustics, Turbulent boundary layer
Journal Canadian Acoustics - Acoustique Canadienne
Citation
Sonnenberg, S.A.J. (Steven A. J.), Rocha, J, Misol, M. (Malte), & Rose, M. (Michael). (2018). Experimental validation of an acceleration power spectral density aircraft panel model given different excitations. Canadian Acoustics - Acoustique Canadienne, 46(2), 19–30.