The U.S. Navy and NASA are currently involved in the design and development of an unsymmetric-skew-wing aircraft capable of 65 deg wing sweep and flight at Mach 1.6. A generic skew-wing aircraft model was developed for 45 deg wing skew at a flight condition of Mach 0.70 and 3048 m altitude. At this flight condition the aircraft has a wing flutter mode. An active implementable control law was developed using the linear quadratic Gaussian design technique. A method of modal residualization was used to reduce the order of the controller used for flutter suppression.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Aeroelastic control of oblique-wing aircraft


    Beteiligte:
    Burken, J. J. (Autor:in) / Gilyard, G. B. (Autor:in) / Alag, G. S. (Autor:in)

    Erscheinungsdatum :

    1986-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Aeroelastic Control of Oblique-Wing Aircraft

    J. J. Burken / G. S. Alag / G. B. Gilyard | NTIS | 1986


    Aeroelastic control of oblique-wing aircraft

    Burken, J. J. / Alag, G. S. / Gilyard, G. B. | NTRS | 1986


    Aeroelastic Stability Characteristics of an Oblique-Wing Aircraft

    J. B. Crittenden / T. A. Weishaar / E. H. Johnson et al. | AIAA | 1978


    Aeroelastic stability characteristics of an oblique wing aircraft

    CRITTENDEN, J. / WEISSHAAR, T. / JOHNSON, E. et al. | AIAA | 1977


    Aeroelastic stability characteristics of an oblique wing aircraft

    Crittenden, J. B. / Weisshaar, T. A. / Johnson, E. H. et al. | NTRS | 1977