FIELD: machine building.
SUBSTANCE: proposed drive relates to control system servo drives and can be used as a high-reliability hydroelectric actuator in aircraft control systems. Proposed drive may be operated as both usual pneumoelectric drive with hydraulic cylinder piston velocity throttle control and as self-contained drive supplied from aircraft electric power system. In the first case, mode selection valve connects hydraulic control valve to power hydraulic cylinder. In the second case, pump with DC motor-controlled delivery is connected thereto via slide valve of reverse with larger area of working openings controlled by linear motor.
EFFECT: expanded performances.
2 cl, 2 dwg
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