An aircraft hydraulic actuation system for retracting an aircraft landing gear. The actuation system includes a supply line arranged to carry hydraulic fluid pressurized by a pump, a return line arranged to return hydraulic fluid to a reservoir, and a hydraulic actuator 128. In a first mode of operation, a first chamber 130 of the actuator 128 is supplied with pressurized hydraulic fluid from the supply line such that a piston 134 is moved in a first direction so as to move a load such as a landing gear. In a second mode of operation, the first chamber 130 is taken out of fluid communication with the supply line and a second chamber 132 is in fluid communication with the return line, such that the piston 134 is able to be moved under the influence of the load, for example when the landing gear extends under gravity.
HYDRAULIC ACTUATION SYSTEM FOR AN AIRCRAFT
HYDRAULIKBETÄTIGUNGSSYSTEM FÜR EIN FLUGZEUG
SYSTÈME D'ACTIONNEMENT HYDRAULIQUE POUR UN AÉRONEF
2022-06-01
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Hydraulic servo actuation system and method for aircraft
European Patent Office | 2024
|