Smart double panel with decentralised active damping units for the control of sound transmission

Abstract

This thesis presents a comprehensive study of a smart aircraft double panel for active vibroacoustic control. The control of the double panel vibration is implemented using Multi-Input-Multi-Output (MIMO) decentralised velocity feedback loops. The loops are applied via an array of electrodynamic force actuators and collocated velocity sensors. The actuators are located in an air cavity between the two panels such that they can react against the two panels. Two velocity sensors per actuator are used. Either sensor is located at the source and radiating panel footprint of an actuator. The error velocity is formed by subtracting weighted sensor outputs. In the introductory part of the thesis a survey of aircraft interior noise is given, and stateof- the-art passive and active noise control methods are presented. In Chapter two the mathematical model for the theoretical analysis of the smart double panel is formulated and a parametric study of passive sound transmission is performed using the mathematical model. In Chapter three the performance of decentralised feedback control systems using absolute and relative velocity is analysed theoretically. In Chapter four the stability and performance of decentralised feedback control systems using reactive actuators driven with weighted velocity error signals is analysed theoretically. In Chapter five the stability of decentralised feedback control systems using weighted velocity error signals and electrodynamic reactive actuators is analysed experimentally. In Chapter six the performance of decentralised feedback control systems using weighted velocity error signals and reactive actuators is analysed experimentally.

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