The redundancy control device (350, 450) includes three controllers (11, 12, 13) that output status signals (N1, N2, N3), a majority voting circuit (70) to which a first voltage or a second voltage is supplied as an output signal (T) through an output line (91, 92, 93) of each controller, a switch (41, 42, 43) provided in each output line, a voltage supply unit (51, 52, 53) provided for each output line to supply the second voltage to the output line when the first voltage is lost, a latch circuit (61, 62, 63) 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 (31, 32, 33) provided for each controller to output a comparison signal (C) based on a comparison of the status signals, and a switch control unit (81, 82, 83) provided for each switch to outputs a switch signal (K) to the switch in response to the comparison signal from the comparison circuit.


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    Title :

    REDUNDANCY CONTROL DEVICE FOR AIRCRAFT


    Additional title:

    REDUNDANZSTEUERUNGSVORRICHTUNG FÜR FLUGZEUGE
    DISPOSITIF DE COMMANDE DE REDONDANCE POUR AÉRONEF


    Contributors:

    Publication date :

    2024-02-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    H02P CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS , Steuern oder Regeln von elektrischen Motoren, elektrischen Generatoren, dynamoelektrischen Umformern / B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / B64C AEROPLANES , Flugzeuge / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



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