Under normal operating flight procedures, a helicopter main rotor revolves at a strictly controlled speed. The centrifugal forces generated keep balance with the aerodynamic loads with the result that the rotor blade motion, in particular the blade flapping, is maintained under control. To reach the normal rotational speeds the rotor must of course pass through lower speeds, both during acceleration and deceleration, and during these periods the blades can fall prey to the phenomenon of blade sailing. With this, not inconsiderable aerodynamic loads can be generated when the helicopter is operating in high winds and with the reduced centrifugal forces because of the lower rotor speeds, the blade flapping motion can build up to dangerously large deflections.


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    Titel :

    Theoretical and Experimental Investigation into the Rotor Blade Aeroelastic Behaviour of a Shipborne Helicopter During Rotor Engagement and Braking


    Beteiligte:
    S. J. Newman (Autor:in)

    Erscheinungsdatum :

    1995


    Format / Umfang :

    10 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    A Theoretical and Experimental Investigation into the Rotor Blade Aeroelastic Behaviour of a Shipborne Helicopter during Rotor Engagement and Braking

    Newman, S. J. / Advisory Group for Aerospace Research and Development / Fluid Dynamics Panel | British Library Conference Proceedings | 1995





    Helicopter aeroelastic analysis with spatially uncertain rotor blade properties

    Murugan, Senthil / Chowdhury, R. / Adhikari, S. et al. | Elsevier | 2011