The results of a design study to define and analyze a hydrofluidic flight control system for helicopters, incorporating pilot relief modes, are presented. The system defined provides the pilot with stability augmentation in three axes, over the total aircraft flight envelope, and with pitch and roll attitude hold, heading hold, and altitude hold over the normal range of cruise airspeeds. To obtain a relatively simple, low-cost system, control panel switching, electrical display gyros for attitude and heading signals, and series servoactuators for both stability augmentation and outer-loop modes are used. The study results indicate that a simple hydrofluidic flight control system which will provide significant relief for the pilot can be mechanized. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Advanced Hydrofluidic Stabilization System


    Contributors:
    M. E. Ebsen (author) / J. O. Hedeen (author)

    Publication date :

    1972


    Size :

    149 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Hydrofluidic Servoactuator Development

    H. C. Kent / J. R. Sjolund | NTIS | 1973


    Hydrofluidic Flight Controls

    Posingies, W. M. | SAE Technical Papers | 1970


    Evolution of the hydrofluidic liquid SAS

    EVANS, RICHARD A. / FOSDICK, G.W. | Emerald Group Publishing | 1972