FIELD: machine building.
SUBSTANCE: proposed servo drive is intended for aircraft electrohydraulic automatic control systems. It comprises the 1st adding operating amplifier with its output connected to the input of the 1st correcting device, its output being connected to the electronic limiting unit input. The said electronic limiting unit out is connected to one of the inputs of the 2nd adding operating amplifier, its 2nd input being connected to the output of 2nd electronic correcting device. The input of the latter is connected to the output of matching hardware with its output connected to control winding of electro mechanic converter. The latter has its armature is articulated with hydraulic control valve moving element. The said hydraulic control valve communicates with the inlet and discharge hydraulic lines and, via two hydraulic lines, with the hydraulic cylinder working chambers. The hydraulic cylinder rod is articulated with the feed back transducer movable member. The said feed back transducer is connected to the matching hardware.
EFFECT: simpler design.
1 dwg
