FIELD: aircraft engineering.
SUBSTANCE: proposed system comprises hydraulic pump, filter, hydraulic shock damper, hydraulic accumulator, check valve, hydraulic pressure control valve and connecting lines. Hydraulic pressure control valve is controlled by working fluid temperature controller. Hydraulic pump suction chamber is communicated via pipe with filter with the line of fuel feed to engines. Hydraulic pump suction chamber is communicated via hydraulic shock damper valve and pipe parallel with hydraulic accumulator and working chambers of actuators. Drain chambers of actuators are communicated via working fluid drain line with hydraulic pressure control valve inlet. One outlet of hydraulic pressure control valve is connected with pipeline with hydraulic pump suction chamber while another outlet is communicated via check valve with the line of fuel feed to engines.
EFFECT: decreased eight, required fluid temperature conditions in hydraulic system.
2 cl, 1 dwg
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