A flight control system (100, 200) for a flight control surface (102) includes a first actuator control electronics (ACE) (202), a second ACE (204), a third ACE (206), a first remote electronics unit (REU) (208), and a second REU (210). The first ACE (202) is configured to generate a first control signal for the flight control surface (102). The second ACE (204) is configured to generate a second control signal for the flight control surface (102). The third ACE (206) is configured to generate a third control signal for the flight control surface (102). The first REU (208) is coupled to the first ACE (202) and the second ACE (204), and configured to operate, based on the first control signal and the second control signal, an actuator (216, 220) coupled to the flight control surface (102). The second REU (210) is coupled to the second ACE (204) and the third ACE (206), and configured to operate, based on the second control signal and the third control signal, the actuator (216, 220).


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    Titel :

    REDUNDANT FLIGHT CONTROL SYSTEM AND METHOD OF USE


    Weitere Titelangaben:

    REDUNDANTES FLUGSTEUERUNGSSYSTEM UND VERFAHREN ZUR VERWENDUNG
    SYSTÈME DE COMMANDE DE VOL REDONDANT ET PROCÉDÉ D'UTILISATION


    Beteiligte:

    Erscheinungsdatum :

    2020-06-03


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen



    FLIGHT CONTROL SYSTEM WITH DUAL REDUNDANT LIDAR

    HUMPHREY IAN P | Europäisches Patentamt | 2017

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