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.


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    Title :

    Helicopter attitude stabilization using individual-blade-control


    Contributors:
    Ham, N. D. (author)

    Publication date :

    1984-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    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