HELICOPTER HYDRAULIC SYSTEM Russian patent published in 2020 - IPC B64C13/42 B64C27/64 

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, particularly, to hydraulic systems with active redundancy. Proposed system comprises hydraulic tank (1) with insulated tanks (2, 3) communicated via pipelines with two-chamber steering drives (19). Their chambers (20, 21) are isolated from each other. Reservoir (3) of hydraulic tank (1) is connected by means of the first hydraulic system with chambers (20), and tank (2) of hydraulic tank (1) is connected by means of the second hydraulic system with chambers (21). At that, each of hydraulic systems contains gear pump (5) connected to gears of main reduction gear and equipped with pump unloading device (6), check valve (7), passing valve (8), electrohydraulic crane (9), on-board discharge valve (10), on-board suction valve (11), two hydraulic accumulators (12), pressure sensor (13), two filters (15) connected by means of sleeves (24) and pipelines (25). Pressure collectors (16, 16') and drain manifolds (17, 17') are connected to chambers (20, 21) of steering drives (19) by means of hoses (18).

EFFECT: higher reliability of autopilot operation and increased safety of flights.

5 cl, 1 dwg