The present invention provides an aircraft ejection seat having two gimballed rocket motors which may be attached either below or behind the seat. A control circuit causes the gimballed rocket motors to rotate in response to pitch and yaw command signals. A pitch command signal alone causes both gimballed rocket motors to have identical angular displacements so that the thrust vectors from the gimballed rocket motors are always parallel. A yaw command signal, either alone or combined with a pitch command signal, causes the gimballed rocket motors to have different angular displacements; and the non-parallel thrust vectors cause a torque about the yaw axis of the ejection seat. The gimballed rocket motors are moved by servo-controlled hydraulic actuators connected between the rocket motor housings and the frame of the ejection seat. A yaw rate signal is processed by a computer to determine the yaw angle of the seat. Yaw rate and yaw angle signals are combined by a summer to produce a negative yaw feedback signal which is connected to the input of the control system.


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    Titel :

    Ejection Seat with Pitch, Roll and Yaw Control


    Beteiligte:
    W. J. Stone (Autor:in) / L. P. Thomas (Autor:in)

    Erscheinungsdatum :

    1979


    Format / Umfang :

    12 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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