CONSIDER a single rotor helicopter disturbed from the hovering condition as in FIG. 16. It has acquired a small forward velocity V ft./sec. and a nose-up angular velocity of q rads./sec. For simplicity we consider the centre of gravity of the fuselage to be on the shaft axis, since its actual position can be shown to have a negligible effect in hovering. Resolving moments about the centre of gravity, the important terms are


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    Title :

    Helicopter Longitudinal Stability


    Subtitle :

    Some Contributions to Existing Theory


    Contributors:
    Payne, P.R. (author)

    Published in:

    Publication date :

    1957-06-01


    Size :

    6 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



    Helicopter Longitudinal Stability

    Payne, P.R. | Emerald Group Publishing | 1957


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