The semi-constrained attitude control tests are described of the flying test bed developed for the purpose of studying the problems associated with hovering as well as vertical takeoff and landing operations of VTOL aircraft. The FTB without landing gears was installed to a link mechanism which was designed to constrain the three linear movements, but to allow the three angular displacements. The attitude angles were constrained within + or - - 7.5 in roll, + or - 7.5 in pitch and + or 20 in yaw. The maximum angles and angular velocities which were recorded in the attitude control tests are as follows: 5, 4.1/S in roll and 4, 3.4/S in pitch for the remote control; 5.5, 6.3/S in roll, 4.5, 3.8/S in pitch and 10, 2.6/S in yaw for the pilot control. The attitude control tests showed that the attitude control system including the automatic stabilization equipment (ASE) provided good stability and control characteristics 9which are comparable to current helicopters and that the cancellation of engine gyroscopic moment by the ASE was satisfactory. The left yawing pedal effectiveness was better than that of right pedal because of engine rotation and of constrained reaction. Operating the ASE about the mechanically constrained axis caused to excite the FTB structural vibration. (Author)


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    Title :

    Semi-Constrained Attitude Control Tests of Flying Test Bed for VTOL Aircraft


    Contributors:
    N. Takizawa (author) / T. Ogawa (author) / Y. Tanabe (author) / A. Shibuya (author) / H. Fujieda (author)

    Publication date :

    1975


    Size :

    55 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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