The aeroservoelastic behaviour of a thin rectangular wing with a controllable trailing edge flap is investigated. A rather high aspect ratio motivates a numerical model based on linear beam theory for the structural dynamics and strip theory for the unsteady aerodynamic loads. Experimental flutter testing shows good agreement with the numerical stability analysis, and the impact of the trailing edge flap on the dynamics is verified by open-loop testing. The problem of stabilizing the wing utilizing the trailing edge flap is posed, and the design of a fixed-structure feedback controller is performed using numerical optimization. The problem of maximizing closed-loop modal damping with constraints on actuator performance is solved for a sequence of flow speeds and the obtained controller is synthesized using gain scheduling. The fairly large predicted increase in critical speed is experimentally verified with satisfactory accuracy.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Active wing flutter suppression using a trailing edge flap


    Weitere Titelangaben:

    Aktive Unterdrückung der Flatterschwingungen von Tragflächen durch Betätigung einer an der Hinterkante angebrachten Ablenkklappe


    Beteiligte:
    Borglund, D. (Autor:in) / Kuttenkeuler, J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2002


    Format / Umfang :

    24 Seiten, 12 Bilder, 4 Tabellen, 28 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Flutter Suppression Using Micro-Trailing Edge Effectors

    Bieniawski, S. / Kroo, I. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2003


    Flutter Suppression Using Micro-Trailing Edge Effectors

    Bieniawski, Stefan / Kroo, Ilan | AIAA | 2003


    DISTRIBUTED TRAILING EDGE WING FLAP SYSTEMS

    HUYNH NEAL V | Europäisches Patentamt | 2022

    Freier Zugriff