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.


    Access

    Download


    Export, share and cite



    Title :

    DISENGAGEMENT FOR REVERSE PROPELLER PROTECTION


    Contributors:

    Publication date :

    2025-06-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    DISENGAGEMENT FOR REVERSE PROPELLER PROTECTION

    GHATTAS ANDREW | European Patent Office | 2025

    Free access

    Propeller thrust reverse

    Roosenboom, Eric W.M. / Schröder, Andreas | Tema Archive | 2007


    Reverse stop folding propeller

    HE JUN / DU XINYANG / LI SHENGJUN et al. | European Patent Office | 2023

    Free access

    Coaxial reverse propeller helicopter

    LUO JUN | European Patent Office | 2021

    Free access

    DISENGAGEMENT DEVICE

    NASHIKO TADAHIRO / HITOMI ATSUSHI | European Patent Office | 2017

    Free access