Results of work done on active controls on the modified YF-17 flutter model are summarized. The basic derivation of a suitable control law is discussed. It is shown that discrepencies found between analysis and wind tunnel tests originate from the lack of proper implementation of the desired control law. Program capabilities are described.


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    Titel :

    Active Controls for Flutter Suppression and Gust Alleviation in Supersonic Aircraft


    Beteiligte:
    E. Nissim (Autor:in)

    Erscheinungsdatum :

    1980


    Format / Umfang :

    269 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch