An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.


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    Title :

    OPTIMIZED PITCH AND ROLL CONTROL APPARATUS FOR AN AIRCRAFT


    Contributors:

    Publication date :

    2018-01-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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