Active flutter suppression control laws were designed, implemented, and tested on an aeroelastically-scaled wind tunnel model in the NASA Langley Transonic Dynamics Tunnel. One of the control laws was successful in stabilizing the model while the dynamic pressure was increased to 24 percent greater than the measured open-loop flutter boundary. Other accomplishments included the design, implementation, and successful operation of a one-of-a-kind digital controller, the design and use of two simulation methods to support the project, and the development and successful use of a methodology for on-line controller performance evaluation.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel model


    Beteiligte:

    Kongress:

    AIAA 31st Structures, Structural Dynamics, and Materials Conference ; 1990 ; Long Beach, CA, United States


    Erscheinungsdatum :

    1990-03-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel model

    Perry, Boyd, III / Mukhopadhyay, Vivek / Hoadley, Sherwood Tiffany et al. | NTRS | 1990


    Digital-flutter-suppression-system investigations for the active flexible wing wind-tunnel model

    PERRY, III, BOYD / MUKHOPADHYAY, VIVEK / HOADLEY, SHERWOOD et al. | AIAA | 1990