The redundancy control device includes three controllers that output status signals, a majority voting circuit to which a first voltage or a second voltage is supplied as an output signal through an output line of each controller, a switch provided in each output line, a voltage supply unit provided for each output line to supply the second voltage to the output line when the first voltage is lost, a latch circuit provided for each output line to latch the second voltage when the second voltage is supplied thereto and continue to output the second voltage, a comparison circuit provided for each controller to output a comparison signal based on a comparison of the status signals, and a switch control unit provided for each switch to outputs a switch signal to the switch in response to the comparison signal from the comparison circuit.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Redundancy control device for aircraft


    Beteiligte:
    JINNO TAKAYUKI (Autor:in) / OGAWA TAKASHI (Autor:in)

    Erscheinungsdatum :

    2023-01-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    H03K PULSE TECHNIQUE , Impulstechnik / B64C AEROPLANES , Flugzeuge



    REDUNDANCY CONTROL DEVICE FOR AIRCRAFT

    JINNO TAKAYUKI / OGAWA TAKASHI | Europäisches Patentamt | 2024

    Freier Zugriff

    REDUNDANCY CONTROL DEVICE FOR AIRCRAFT

    JINNO TAKAYUKI / OGAWA TAKASHI | Europäisches Patentamt | 2021

    Freier Zugriff