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Evaluation of piezoceramic actuators for control of aircraft interior noiseResults of an experiment to evaluate piezoceramic actuators as the control actuator for active control of interior noise in a large-scale fuselage model are presented. Control was demonstrated for tonal excitation using a time domain least mean squares algorithm. A maximum of four actuator channels and six error signals were used. The actuators were employed for control of noise at frequencies where interior cavity modes were the dominant response and for driven acoustic responses where a structure resonance was dominant. Global reductions of 9 to 12 dB were obtained for the cases examined. The most effective configuration of skin-mounted actuators was found to be a pure in-plane forcing function as opposed to a bending excitation. The frame-mounted actuators were found to be equally effective as the skin-mounted actuators. However, both configurations resulted in local regions of unacceptably high vibration response in the structure.
Document ID
19930035189
Document Type
Conference Paper
Authors
Silcox, Richard J. (NASA Langley Research Center Hampton, VA, United States)
Lefebvre, Sylvie (Virginia Polytechnic Inst. and State Univ. Blacksburg, United States)
Metcalf, Vern L. (U.S. Army, Aviation Systems Command, Hampton VA, United States)
Beyer, Todd B. (NASA Langley Research Center Hampton, VA, United States)
Fuller, Chris R. (Virginia Polytechnic Inst. and State Univ. Blacksburg, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: DGLR(AIAA Aeroacoustics Conference, 14th, Aachen, Germany, May 11-14, 1992, Proceedings. Vol. 2 (A93-19126 05-71)
Subject Category
ACOUSTICS
Distribution Limits
Public
Copyright
Other