A pump unit installed inside a wing (102) includes a backup hydraulic pump (20) that can supply pressure oil to an actuator (104) when a loss or reduction occurs in the function of an aircraft central hydraulic power source (105) and an electric motor that drives the pump. A wing structure (102) portion forming the surface structure of the wing is provided with an inlet port and an exhaust port that are formed therethrough. The inlet port is provided so as to be opened and closed by an inlet port opening/closing portion, and the exhaust port is provided so as to be opened and closed by an exhaust port opening/closing portion.
Hydraulic apparatus for aircraft actuators
Hydraulikvorrichtung für Flugzeugbetätiger
Appareil hydraulique pour actionneurs d'avion
28.11.2018
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
CRYOGENIC TANK FOR AN AIRCRAFT WITH HYDRAULIC ACTUATORS
Europäisches Patentamt | 2025
|Emerald Group Publishing | 2001
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SAE Technical Papers | 2002