Objective

To identiy vibration patterns on the fuselage surface and sound pressure level distribution in the cabin of an aricraft.

Test Procedure

1. A 60-microphone circular array was used to sweep along the length of the aircraft cabin and capture acoustic pressure data close to the fuselage surface.
2. A 60-microphone radial sector array was used to rotate and cover the end caps of the fuselage and capture acoustic pressure data.
3. Acoustic pressure data was acquired on several patches to cover the whole length of the cabin.
4. Acoustic pressure, normal acoustic intensity and surface velocity were reconstructed on the fuselage surface.

Results

The following images shows the vibration pattern of the fuselage surface and the sound pressure level distribution in the cabin volume.