An electric brake system architecture for an aircraft with two or more electrical braking subsystems (301,303) including brake system controls (306,338) configured to communicate pilot pedal commands to electric brake actuator controllers (308,310,340,342) that apply or release brakes in wheel groups (312,324,344,356). The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system (300) further includes remote data consolidators (314,318,328,330,346,348,360,362) to collect and transmit wheel data to brake system controls (306,338) through a digital data communication bus (333,365). The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.


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    Titel :

    Aircraft electrical brake control system architecture


    Weitere Titelangaben:

    Systemarchitektur einer elektrischen Flugzeugbremssteuerung
    Architecture de système d'un commande de freinage électrique pour avion


    Beteiligte:
    GRIFFITH TODD T (Autor:in) / YAMAMOTO DAVID T (Autor:in) / NGUYEN TU-LUC H (Autor:in) / GODO ERIK L (Autor:in)

    Erscheinungsdatum :

    2017-03-29


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B60T Bremsanlagen für Fahrzeuge oder Teile davon , VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF



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