This paper describes how the combination of a carefully tailored flapping flexure with a small amount of forward blade sweep can result in a composite/bearingless rotor that has the inherent capability to eliminate rotor moments caused by gusts, speed and angle of attack changes, and gyroscopic rotor moments due to vehicle angular velocity. This feature allows the rotor itself to be used as a very large attitude gyro, thus eliminating the need for electronic SAS systems. Forward blade sweep creates a negative spring effect that cancels out the positive torsional spring rate of the flexure, thus tuning the feathering frequency to near 1P and minimizing cyclic control forces. This eliminates the need for power boost. Included are the author's experiences with wind tunnel model, rotor whirl, and flight testing of this type of rotor.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    The auto-trim rotor stability system


    Additional title:

    Das Autotrimm-Rotorstabilitätssystem


    Contributors:

    Published in:

    Publication date :

    1997


    Size :

    12 Seiten, 12 Bilder, 5 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    The Auto-Trim Rotor Stability System

    Hanson, T. / American Helicopter Society | British Library Conference Proceedings | 1997


    Rotor Trim by a Neural Model-Predictive Auto-Pilot

    Bottasso, C. L. / Riviello, L. / American Helicopter Society | British Library Conference Proceedings | 2006


    Anodized aluminum auto trim

    Cochran, W.C. / Englehart, E.T. / George, D.J. | Engineering Index Backfile | 1960


    A theoretical and experimental investigation of hingeless-rotor stability and trim

    Subramanian, S. / Goankar, G.H. / Maier, T.H. | Tema Archive | 1997


    TRIM-STAB-Aerospace vehicle trim and stability

    Barnes, R. E. / Kuchta, B. J. | NTRS | 1977