R.J. Silcox, S. Levebvre, V.L. Metcalf, T.B. Beyer, C.R. Fuller

An experiment has been conducted to evaluate piezoceramic actuators as the control actuator for active control of interior noise in a large scale fuselage model. These experiments were conducted in the anechoic room of the Acoustics Research Laboratory on a composite model of a commuter class aircraft. 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 used 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. Frame mounted and skin mounted piezoceramic actuators were used. 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 equally effective as the skin mounted actuators. However, both configurations resulted in local regions of unacceptably high vibration response in the structure.

DGLR/AIAA 14th Aeroacoustics Conference, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1992, 1992-03, DGLR/AIAA 14th Aeroacoustics Conference - Proceedings; S.542-551; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

actuators, aeroacoustics, piezoelectric ceramics

Bibliothek

1992