Abstract:

Active structural acoustic control (ASAC) research has previously concentrated on flat plates with attached piezoelectric sensoriactuators. Application of this ASAC research to aircraft interior noise requires the consideration of the curvature of the fuselage panels in the dynamic modeling. This paper investigates the effects of curvature on the dynamics of fuselage panels. A state variable model of a simply supported curved panel with attached piezoelectric sensoriactuators is developed for ASAC applications. The model is verified by comparison to previous work on curved panels and flat plates. Further, the model is validated by experimental data obtained from a simply supported curved panel test structure. [Research supported by NASA Langley Research Center under Grant No. NCC 1 250.]