The invention relates to an engine control device comprising a first control channel (V1) and a second control channel (V2), each control channel comprising a first sensor (CAV1, CAV2) and a second sensor (CBV2, CBV2), each configured to provide, respectively, a first measurement (A) and a second measurement (B) to each channel, each of the channels having an active or passive state defining an active channel (V1) or a passive channel (V2), the active channel (V1) being designed to control at least one actuator (ACT) of the engine while the passive channel (V2) is designed to take over for the active channel if the latter fails.


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    Title :

    PROCÉDÉ DE COMMANDE D'UN MOTEUR D'UN AÉRONEF COMMANDÉ PAR UN DISPOSITIF DE COMMANDE COMPRENANT DEUX VOIES DE COMMANDE REDONDÉES


    Additional title:

    METHOD FOR CONTROLLING AN AIRCRAFT ENGINE CONTROLLED BY A DEVICE COMPRISING TWO REDUNDANT CONTROL CHANNELS
    VERFAHREN ZUR STEUERUNG EINES VON EINER STEUERVORRICHTUNG GESTEUERTEN FLUGZEUGMOTORS MIT ZWEI REDUNDANTEN STEUERKANÄLEN



    Publication date :

    2025-06-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G05B Steuer- oder Regelsysteme allgemein , CONTROL OR REGULATING SYSTEMS IN GENERAL



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