An engine and propeller control system (EPECS) of an aircraft includes a propeller with a plurality of blades coupled to an aircraft engine. Each of the blades are coupled to an actuator configured to adjust the blades between a first pitch to produce forward thrust and a second pitch to produce reverse thrust. The EPECS further includes a controller configured to control the actuator to invoke the second pitch in response to receiving a reverse thrust command signal. The controller is configured to alert that the reverse thrust command signal is generated prior to landing the aircraft.


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    Titel :

    DISENGAGEMENT FOR REVERSE PROPELLER PROTECTION


    Beteiligte:
    GHATTAS ANDREW (Autor:in)

    Erscheinungsdatum :

    12.06.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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