This paper formulates a new control methodology for vibration reduction at the rotor hub by controlling trailing edge flaps. The novelty of the proposed methodology lies in its ability to control each rotor blade separately and optimally taking into account blade-to-blade dissimilarities, while using exclusively fixed frame measurements. The controller is formulated in the time domain, and adaptively generates in real time individual control inputs to the trailing edge flaps to achieve vibration reduction. Numerical simulations using a hingeless rotor model show that the controller generates control inputs to each blade, taking blade dissimilarities into account, and successfully minimizes vertical hub vibrations.


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    Titel :

    Trailing edge flap control methodology for vibration reduction of helicopter with dissimilar blades


    Beteiligte:
    Roget, B. (Autor:in) / Chopra, I. (Autor:in) / Gessow, A. (Autor:in)


    Erscheinungsdatum :

    2001


    Format / Umfang :

    11 Seiten, 9 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





    AIAA-2001-1433 Trailing Edge Flap Control Methodology for Vibration Reduction of Helicopter with Dissimilar Blades

    Roget, B. / Chopra, I. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2001


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