Piezoelectric Actuator Configuration Optimization for Active Structural Acoustic Control in Aircraft

Document Number: 971461

Date Published: May 1997

Author(s):
Dr Gary P Gibbs - Nasa Langley Res Ctr
C Fuller - Nasa Langley Res Ctr
S Paxton - Nasa Langley Res Ctr

Abstract:
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.

File Size: 903K
Product Status: In Stock

See other papers presented at General, Corporate & Regional Aviation Meeting & Exposition, April 1997, Wichita, KS, USA, Session: Noise

Purchase more technical papers and save! With TechSelect, you decide what SAE Technical Papers you need, when you need them, and how much you want to pay. Learn more >