A hydraulic system (100) for an aircraft having an engine (108) and an auxiliary power unit (122) includes a first hydraulic subsystem (102) including a first hydraulic pump (106) and a first set of hydraulic-powered components (112, 114, 116) in fluid communication with the first hydraulic pump (106). The first hydraulic pump (106) is powered by the engine (108) to pump shared hydraulic fluid to the first set of hydraulic-powered components (112, 114, 116). The hydraulic system (100) includes a second hydraulic subsystem (104) including a second hydraulic pump (120) and a second set of hydraulic-powered components (126, 128, 130) in fluid communication with the second hydraulic pump (120). The second hydraulic pump (120) is powered by the auxiliary power unit (122) to pump the shared hydraulic fluid to the second set of hydraulic-powered components (126, 128, 130). A shared return line subsystem (134) and reservoir (136) is in fluid communication with the first and second hydraulic subsystems (102, 104) to return the shared hydraulic fluid to the first and second hydraulic pumps (106, 120).


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    Title :

    AIRCRAFT HYDRAULIC SYSTEMS HAVING SHARED COMPONENTS


    Additional title:

    FLUGZEUGHYDRAULIKSYSTEME MIT GEMEINSAM GENUTZTEN KOMPONENTEN
    SYSTÈMES HYDRAULIQUES D'AÉRONEF POSSÉDANT DES COMPOSANTS PARTAGÉS



    Publication date :

    2019-01-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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