The objective of this project was to develop a speaker-based active control system capable of dissipating reverberant acoustic energy within the fuselage of a typical business jet aircraft. A ground-based fuselage was utilized as the test-bed for the work conducted in this project. Typical aircraft fuselage trim was installed to more accurately reflect the acoustic properties of a flight-ready aircraft. Speaker locations were selected based upon the acoustic modal characteristics of the fuselage and practical considerations concerning available space in the walls of the trim. Preliminary control experiments involving single-input, single-output, feedback loops resulted in a very localized zone of quiet which yielded no global effects. Multi-input, multi-output feedback control with a distributed array of eight pairs of transducers weighted (spatially) to emphasize energy dissipation of select acoustic modes resulted in as much as 6 dB of global attenuation at acoustic resonances corresponding to the secon...
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