Modeling of a helicopter fuselage panel with active vibration control

Abstract

In this study, modeling of a helicopter fuselage panel with active vibration control is carried out. In order to represent the helicopter body shell, a cabin panel clamped from four edges is designed. Piezoelectric patches are attached on the body according to the literature. The dynamic characteristics of the structure are obtained by finite element based modal analysis and exporting of state space matrices. The numerical model of the cabin panel is characterized with regard to active vibration control loop. Vibration data obtained from the helicopter operational tests is applied as a distortion. Positive position feedback (PPF) which is collocated controller design is implemented on the system and system performance is verified by evaluating the strain responses at the controlled points. Active vibration control studies are carried out in simulation. The results show that the designed system can decrease the vibration at desired level. © 2016 ACM.