An aircraft hydraulic braking system 100 with at least one hydraulic accumulator 150,250 which is the sole source of pressurised hydraulic fluid in the braking system for operating a brake actuator 15a-15d. The system is controlled by precluding accumulator charging during flight and causing partial accumulator discharge to operate the brake actuator during flight or during landing. Preferably, the system has at least one inlet 140 for recharging the accumulator with hydraulic fluid. The system may be free of any charging hydraulic fluid source, or may have a reservoir 120 of hydraulic fluid for charging between flights using a pump. Also claimed is a system with two self-contained braking systems (fig.1,100a,100b). A first hydraulic braking system has a first supply of hydraulic fluid and is configured to brake a first aircraft wheel (fig.1,11a); a second hydraulic braking system has a different supply of hydraulic fluid, and is configured to brake a second aircraft wheel (fig.1,11b); and where there is no fluid connection between the two braking systems.


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    Titel :

    Aircraft hydraulic braking system and method of controlling same


    Beteiligte:
    ALEXANDER HAYES (Autor:in) / YASSER IBRAHIM (Autor:in) / MARICA PALITTA (Autor:in) / ROMAIN SIEGEL (Autor:in)

    Erscheinungsdatum :

    12.04.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B60T Bremsanlagen für Fahrzeuge oder Teile davon , VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF



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