A 5.5-foot-diameter, soft-in-plane, hingeless-rotor system was tested on a gimbal which allowed the helicopter rigid-body pitch and roll motions. Coupled rotor/airframe aeroelastic stability boundaries were explored and the modal damping ratios were measured. The time histories were correlated with analysis with excellent agreement. The effects of forward speed and some rotor design parameters on the coupled rotor/airframe stability were explored both by model and analysis. Some physical insights into the coupled stability phenomenon are suggested.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Rotor aeroelastic stability coupled with helicopter body motion


    Contributors:
    Miao, W. L. (author) / Huber, H. B. (author)


    Publication date :

    1974-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :