A theoretical study is presented on the application of the Individual-Blade-Control concept to helicopter attitude stabilization. The design of a system controlling blade flapping dynamics, and related testing of the system on a model rotor in the wind tunnel, is described. The control inputs considered are blade pitch changes proportional to blade flapping acceleration, velocity, and displacement. The effect of such a system on helicopter rotor damping-in-pitch, and angle-of-attack stability is then evaluated. It is shown that helicopter attitude stabilization is achieved, with a corresponding improvement in flying qualities.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Helicopter attitude stabilization using individual-blade-control


    Beteiligte:
    Ham, N. D. (Autor:in)

    Erscheinungsdatum :

    01.08.1984


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Helicopter Individual-Blade-Control: Promising Technology for the Future Helicopter

    Ham, N. D. / American Helicopter Society; Northeast Region | British Library Conference Proceedings | 1995


    Helicopter Individual-Blade-Control: Promising Technology for the Future Helicopter

    Ham, N. D. / American Helicopter Society; Northeast Region | British Library Conference Proceedings | 1995