L. Lecce, A. Concilio, S.F. Del Gatto

In this paper the results of an ongoing research on the noise and vibration control inside an aircraft cabin, with active control systems using piezoelectric sensors and actuators, are presented. Available analytical models, able to predict the piezoelectric actuators action upon simple structural elements, have been extended to typical structures of the fuselage, like panels and frames. Then, some numerical models (FEM) have been developed where it has been possible to treat with the vibration and vibroacoustic phenomena of the complete structure-control system. Experimental results are reported, in order to validate the numerical and analytical models and to obtain an evaluation of the capability of this approach. The results are encouraging and show an increasing interest for the development of such systems.

Workshop on Smart Material Systems and Structures, 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

DGLR-Bericht, 1991, 1991-09, Workshop on Smart Material Systems and Structures - Proceedings; S.84-94; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

structural design

Bestellbar

1991