To overcome high interior noise levels due to tonal propeller-induced vibrations of the aircraft structure is a major challenge for turboprop aircraft, such as Airbus A 400M. One approach for effective interior noise reduction is the reduction of fuselage vibrations by vibration absorbers. In the case of variable propeller speed, these vibration absorbers have to be tuned according to the change of the blade passage frequency and its harmonics. From several possibilities to design an adaptive system, a tuneable vibration absorber (TVA) system based on the emerging piezoelectric technology is presented in this paper. The core element of the force generator amenable to direct electrical control are piezoceramic elements embedded into a GFRP leaf spring. Depending on the control law and the system configuration a tuneable vibration absorber and an actuator for active vibration and noise control is obtained. For the Piezo-TVA system considered, leaf-spring absorbers are designed for a fundamental BPF at 87.3 Hz as well as its first harmonics. Absorber prototypes are manufactured and control laws formulated, simulated and implemented into a dSPACE system. The system is tested on a real size aircraft fuselage panel (main dimensions similar to A320) installed into a transmission loss test suite where the panel is acoustically excited. A vibration reduction performance of up to 40 dB and a noise reduction performance of up to 13 dB are demonstrated. Moreover, a multi-mode operation of the TVA system is presented as well as its high flexibility required for optimum system configuration during flight tests. The system presented is extremely beneficial with respect to guaranteed performance, high flexibility and a minimum weight realization. The proposed Piezo-TVA technology permits direct electrical control without any mechanical friction and wear. As a result, the frequency tuning can be realized with high precision.


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    Titel :

    Tuneable vibration absorber system for aircraft


    Weitere Titelangaben:

    Abstimmbares Vibrationsdämpfungssystem für Flugzeuge


    Beteiligte:


    Erscheinungsdatum :

    2006


    Format / Umfang :

    5 Seiten, 4 Bilder, 2 Tabellen, 9 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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