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).
AIRCRAFT HYDRAULIC SYSTEMS HAVING SHARED COMPONENTS
FLUGZEUGHYDRAULIKSYSTEME MIT GEMEINSAM GENUTZTEN KOMPONENTEN
SYSTÈMES HYDRAULIQUES D'AÉRONEF POSSÉDANT DES COMPOSANTS PARTAGÉS
2019-01-30
Patent
Elektronische Ressource
Englisch
GERMAN AIRCRAFT and HYDRAULIC SYSTEMS Their Components
SAE Technical Papers | 1946
|Hydraulic control systems and methods for components of an aircraft
Europäisches Patentamt | 2022
|TIBKAT | 1987
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