An aircraft hybrid flight control system comprising a manual control element (C), a mechanical transmission (11) interposed between the manual control element (C) and a control surface (S), an electromechanical actuator (12; 101) and a coupling unit (16; 28, 42; 108, 111) configured to connect selectively the control surface (S) to the mechanical transmission (11) in a manual control mode and to the electromechanical actuator (12; 101) in a fly-by-wire control mode; the coupling unit (16; 28, 42; 108, 111) is configured to maintain the mechanical transmission (11) in a condition of substantial continuity with said control surface (S) even in fly-by-wire mode, but for a freedom of relative motion of pre-set amplitude.


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    Title :

    AIRCRAFT HYBRID FLIGHT CONTROL SYSTEM


    Additional title:

    HYBRIDES FLUGZEUGFLUGSTEUERUNGSSYSTEM
    SYSTÈME DE COMMANDE DE VOL HYBRIDE D'AÉRONEF


    Contributors:

    Publication date :

    2018-07-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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