Piezoelectric Actuator Configuration Optimization for Active Structural Acoustic Control in Aircraft NASA Langley Research Center

Format:

Conference/Event

Author/Creator:

Gibbs, Gary P., author.

Conference Name:

General, Corporate & Regional Aviation Meeting & Exposition (1997-04-29 : Wichita, Kansas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1997

Summary:

This paper has presented a technique for the determination of an optimal configuration of fuselage mounted piezoelectric actuators for active structural acoustic control of interior noise in aircraft. The technique has demonstrated much potential in preliminary experiments where actuators were configured to couple into the first principal component of the acoustically coupled fuselage vibration. In this test, average reductions of 6 dB at the error microphones and 4 dB at five auxiliary microphones were observed for a pure tone disturbance at the left forward engine pylon of a business jet. This disturbance was used to simulate an oscillating force due to engine unbalance

Notes:

Vendor supplied data

Publisher Number:

971461

Access Restriction:

Restricted for use by site license