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.
OPTIMIZED PITCH AND ROLL CONTROL APPARATUS FOR AN AIRCRAFT
OPTIMIERTE NICK- UND ROLLBEWEGUNGSSTEUERUNGSVORRICHTUNG FÜR EIN FLUGZEUG
APPAREIL DE RÉGLAGE DE TANGAGE ET DE ROULIS OPTIMISÉ POUR UN AVION
2020-01-01
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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