Active control of interior noise in model aircraft fuselages using piezoceramic actuatorsActive control of interior noise in model aircraft fuselages using piezoceramic actuators is experimentally studied. The actuators are bonded directly to the structure and error information is taken from up to two microphones located in the interior acoustic field. The results demonstrate that global attenuation of the order of 10 to 15 dB of interior noise can be achieved with piezoceramic actuators, irrespective of whether the shell system is vibrating at an acoustic or structural resonant frequency. The work also proves that active control using vibration (moment) inputs works well when a floor simulating that of an aircraft is installed in the model. This result suggests that the technique will be successful in controlling interior noise in realistic aircraft structures.
Document ID
19910027815
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fuller, C. R. (Virginia Polytechnic Institute and State University Blacksburg, United States)
Hansen, C. H. (Adelaide, University Australia)
Silcox, R. J. (NASA Langley Research Center Hampton, VA, United States)
Snyder, S. D. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)