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System Identification and Active Control of Interior Noise in a Business Aircraft
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English
Abstract
This work primarily consists of two main parts. First a series of acoustic system identification experiments of the interior space of a business aircraft were performed. The system was subjected to both a structural based excitation (at the left forward engine mount), and an acoustic based excitation (speaker mounted in cockpit). Sound pressure was measured at over 3000 points in the cabin over a frequency range of 0-400 Hz. Data was reduced to produce 3-D acoustic plots at single frequency bins and 2-D dispersion diagrams (wavenumber vs. frequency). Secondly, preliminary experiments on controlling interior noise using small patch type piezoceramic actuators bonded to the fuselage were investigated. The results demonstrate that the piezoceramic patch actuators have enough control authority for this application. In addition, for the dominant noise case of a cabin resonance, reasonable sound reductions with only four control inputs were measured throughout the cabin space except at one location. Results at the off-resonance case show reduced control performance. Important non-linear behavior, most likely due to curving the flat piezoceramic actuators on attachment was identified.
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Citation
Gibbs, G., Mahnken, B., and Fuller, C., "System Identification and Active Control of Interior Noise in a Business Aircraft," SAE Technical Paper 951178, 1995, https://doi.org/10.4271/951178.Also In
References
- “Experiments on reduction of propeller induced interior noise by active control of cylinder vibration,” Fuller C. R. Jones J. D. Journal of Sound and Vibration 112 2 389 395 1987
- “Active control of interior noise in model aircraft fuselage using piezoceramic actuators,” Fuller C. R. Snyder S. D. Hausen C. H. Silcox R. J. AIAA Paper 90-3922 1990
- “Evaluation of piezoceramic actuators for control of aircraft interior noise,” Silcox R. J. Lefebvre S. Metcalf V. L. Beyer T. B. Fuller C. R. AIAA Paper 92-02-091 1992
- “Full-scale demonstration tests of cabin noise reduction using active vibration control,” Simpson M. A. Luong T. M. Fuller C. R. Jones J. D. AIAA Paper 89-1074 1989
- “Aircraft cabin noise reduction tests using active structural acoustic control,” Mathur G. Tran B. AIAA Paper 93-4437 1993
- “Using Non-modal Method for System Identification,” Cessna Year One Annual Report Li W. X. Mitchell L. D. Department of Mechanical Engineering Blacksburg, VA
- “Spatial Domain Techniques for Modal Analysis Using A Laser Doppler Velocimeter,” Arruda J. R. F. Sun F. Mitchell L. D. Proceedings of IMAC 10 February 3 7 1992 San Diego, CA 656 664
- “A multiple error LMS algorithm and its application to the active control of sound and vibration,” Elliott S. J. Stothers I. M. Nelson P. A. IEEE Transaction on Acoustics, Speech and Signal Processing ASSP-35 1423 1434 1987
- “Optimal placement of piezoelectric actuators and polyvinylidene fluoride sensors in active structural acoustic control approaches,” Clark R. L. Fuller C. R. Journal of the Acoustical Society of America 92 3 1521 1533 1992
- “Optimization of actuator arrays for aircraft interior noise control,” Cabell R. H. Lester H. C. Mathur G. P. Tran B. N. AIAA Paper 93-4447 1993