Two-bladed teetering rotors with elastic flapping hinge restraint are shown to be suitable for zero-g flight. The alternating moment component introduced into the fuselage by the hinge spring can be balanced about the aircraft center of gravity by alternating hub shears. Such shears can be produced in proper magnitude, frequency, and phase by additional underslinging of the hub and by judicious choice of the location of the first inplane cantilevered natural frequency. Trends of theoretical results agree with test results from a small scale model and a modified OH-58A helicopter.


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    Title :

    Hub moment springs on two-bladed teetering rotors


    Contributors:
    Sonneborn, W. (author) / Yen, J. (author)


    Publication date :

    1974-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Hub moment springs on two-bladed teetering rotors

    Sonneborn, W. / Yen, J. | Tema Archive | 1974


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