Using dynamic absorbers for reducing the vibration and the interior noise of an aircraft’s fuselage is studied. In this paper, the fuselage is modeled as a circular panel connected to a plate. The fuselage’s floor effect is considered herein via including the plate in the model. The source caused the vibration and the interior noise is a set of external pressures to the fuselage. Several dynamic absorbers are then attached to the fuselage for vibration and noise control. The dynamic response of the fuselage and its interior sound pressure are analytically formulated. From the numerical results, the absorbers are found to be effective in decreasing the vibration of the fuselage and the resultant interior acoustic pressure. Some general guidelines on absorber design are also suggested in the conclusions.

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