Piezoelectric Actuator Configuration Optimization for Active Structural Acoustic Control in Aircraft 971461
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.
Citation: Gibbs, G., Fuller, C., and Paxton, S., "Piezoelectric Actuator Configuration Optimization for Active Structural Acoustic Control in Aircraft," SAE Technical Paper 971461, 1997, https://doi.org/10.4271/971461. Download Citation
Author(s):
Gary P. Gibbs, Chris R. Fuller, Scott Paxton
Affiliated:
NASA Langley Research Center, Virginia Polytechnic Institute and State Univ.
Pages: 7
Event:
General, Corporate & Regional Aviation Meeting & Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Interior noise
Aircraft
Sensors and actuators
Fuselages
Acoustics
Vibration
Optimization
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