An aircraft hydraulic actuation system comprises a supply line carrying hydraulic fluid pressurised by a pump, a return line returning hydraulic fluid to a reservoir, and a hydraulic actuator 128. In a first operation mode (figure 8a) a first chamber 130 (230, figure 9) of the actuator is supplied with pressurised hydraulic fluid from the supply line and piston 134 (234) is moved in a first direction, moving a load (e.g. door or landing gear). In a second operation mode (figure 8b) the first chamber is taken out of fluid communication with the supply line, a second chamber 132 (232, figure 9) is in fluid communication with the return line and the piston is moved under the load (e.g. landing gear extends under gravity). Preferably, a hydraulic fluid flow path 144 (244) having a flow restrictor 146 (246) (e.g. orifice, through hole 244 or valve) is provided between the chambers.
Hydraulic actuation system for an aircraft
2021-03-03
Patent
Electronic Resource
English
Aircraft hydraulic actuation system with chambers for hydraulic fluid
European Patent Office | 2025
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