Method and electro-hydraulic system for controlling the retractable landing gear of an aircraft, landing gear and aircraft

Abstract

The present invention relates to an electro-hydraulic control system (1) for the landing gear (2) of an aircraft, said landing gear (2) comprising a plurality of retractable landing gears (21, 22), each equipped with at least one wheel (25, 26). Said system (1) comprises two braking devices (11, 12) for braking said wheel (25, 26) of two landing gears (21, 22), a displacement device (13, 14, 15) per landing gear for moving a landing gear (21, 22) relative to a housing of said aircraft, and two hydraulic power units (16, 17), hydraulically connected to said displacement devices (13, 14, 15) and to at least one of said braking devices (11, 12).Each hydraulic power unit (16, 17) comprises a reservoir (161, 171) containing a fluid, a pump (162, 172) driven by an electric pump motor (163, 173), and a distributor (164, 174) configured to distribute said fluid to at least one braking device (11, 12) and to said displacement devices (13, 14, 15), by means of braking (165, 175), deployment (166, 176), retraction (168, 178), and discharge (167, 169, 177, 179) valves. Abbreviated figure: Figure 1.