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
2018-11-28
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
ACTUATORS: AIRCRAFT FLIGHT CONTROLS, POWER OPERATED, HYDRAULIC, GENERAL SPECIFICATION FOR
SAE Technical Papers | 1991
Emerald Group Publishing | 2001
Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For
SAE Technical Papers | 2002