When a loss or degradation in the function of one of a first aircraft central hydraulic power source (104) and a second aircraft central hydraulic power source (105) occurs, a controller performs a control so as to operate the other backup hydraulic pump, out of a first backup hydraulic pump (18a) and a second backup hydraulic pump (18b), which is connected downstream of the other hydraulic power source, which is the other of the first and second aircraft central hydraulic power sources. Oil flowing through the other backup hydraulic pump is cooled by an oil cooler of the other hydraulic power source by operation of the other backup hydraulic pump in a state where the other hydraulic power source is being operated.
Aircraft actuator hydraulic system
Flugzeughydraulikantriebssystem
Système hydraulique d'actionneur d'avion
2018-10-03
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |