The report describes the design and flight tests of a hydrofluidic yaw stability augmentation system (SAS) for an OH-58A helicopter. The design objective was to improve stability characteristics in yaw for all flight conditions from hover to 120 kn. The yaw SAS, which initially featured only high-passed yaw rate feedback, was installed in an OH-58A helicopter and flight tested in 1972. Performance at forward flight speeds was satisfactory; but at hover, yaw rates were excessive. The system was then modified to add a straight-through yaw rate feedback term. Flight tests of this configuration were conducted from October-December 1973. Results were satisfactory. (Author)


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    Title :

    Yaw Axis Stability Augmentation System Flight Test Report


    Contributors:
    H. Ogren (author) / D. Sotanski (author) / L. Genaw (author)

    Publication date :

    1974


    Size :

    111 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English