A pump unit (12) installed inside a wing (100), and a panel body (11) constituting part of a wing structure portion forming a surface structure of the wing (100) are provided. The pump unit (12) includes a backup hydraulic pump (13) that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor (14) that drives this pump. Except for at least the panel body, the wing structure portion is formed from fiber reinforced plastics. The panel body (11) is formed of a metallic material.
Hydraulic apparatus for aircraft actuators
Hydraulikvorrichtung für Flugzeugbetätiger
Appareil hydraulique pour actionneurs d'avion
2018-10-10
Patent
Electronic Resource
English
ACTUATORS: AIRCRAFT FLIGHT CONTROLS, POWER OPERATED, HYDRAULIC, GENERAL SPECIFICATION FOR
SAE Technical Papers | 1991
Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For
SAE Technical Papers | 2002
ACTUATORS: AIRCRAFT FLIGHT CONTROLS, POWER OPERATED, HYDRAULIC, GENERAL SPECIFICATION FOR
SAE Technical Papers | 1993