A Wavenumber Approach for the Response of Aircraft Sidewalls to Random Pressure Fluctuations

摘要

Under cruise conditions, aircraft fuselages are exposed to high-level fluctuating pressures mainly due to aerodynamic turbulence and jet noise. In order to analyse the resulting sound transmission through aircraft sidewalls, simulations have been carried out to predict the response of a fuselage panel for two types of random pressure field, namely a diffuse acoustic field and a turbulent boundary layer excitation. An analytical model is first presented for determining the vibro-acoustic response of an aircraft panel to a large class of random excitations in the wavenumber domain. From the simulations, several trends have been pointed out: (ⅰ) both resonant and non resonant modes contribute to the panel response over a broad frequency range, below the acoustic coincidence frequency for a diffuse field excitation, and over the hydrodynamic coincidence area for a turbulent excitation; (ⅱ) the panel structural modes are more efficiently excited with a diffuse acoustic field than with turbulent wall-pressure fluctuations.