Cabin noise level during cruise is one of the most important variable impacting aircrafts passenger comfort and one of the most difficult to control. The most important noise path to aircrafts cabin is through fuselage panels. Through their vibration in fact both aerodynamic noise and structure born noise are transmitted inside the cabin. A possible solution for reducing fuselage panel vibration is to pad the panels with damping materials, on the other hand this choice result in a significant weight increase which is unacceptable by aircraft manufacturer because of the impact in operational costs and pollution due to the increase in fuel consumption. In this paper the design and experimental testing of a vibration reduction system based on Active Constrained Layer Damping technique is presented. This technique improves the damping efficiency of standard viscoelastic materials by using piezoelectric plate actuators. The viscoelastic material is layered between the panel and actuator, a sensor senses the vibration of the panel and a control system processes this signal to drive the actuator in order to maximize the damping capability of the viscoelastic material. This treatment is patched at selected locations to reduce weight. In this paper the development of a small scale demonstrator on a carbon fibre composite plate coupon is described. The finding of the coupon test has been used to design a larger demonstrator which will be tested in spring-summer 2009.


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    Title :

    Design and testing of an active constrained layer damping demonstrator for aircraft's cabin noise reduction


    Additional title:

    Design und Prüfung eines aktiven, eingespannten Schichtdämpfungs-Demonstrationsmodells für die Geräuschreduzierung in Flugzeugkabinen


    Contributors:


    Publication date :

    2009


    Size :

    10 Seiten, 14 Bilder, 1 Tabelle, 7 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English






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