FIELD: pilotless aircraft.
SUBSTANCE: invention relates to electrohydraulic servo actuators of displacement-throttle governing and it is designed for use as actuator mechanism for shifting control surfaces of aircraft by electric control signals. Hydraulic supply sources, drive electric motor and at least three actuators are constructionally and functionally united into common unit, being rigidly coupled by common housing. Independently moving output links of actuators are arranged opposite to each other on peripheral zones of common housing with equal radius-vector distance from central axis. Hydromechanical lock of each actuator is made in form of spring-loaded differential piston with axial outer projection installed in bores of common housing for axial displacement and forming of control space communicating with pressure channel of its remote controlled source of command pressure to provide quick response and independent operation.
EFFECT: improved reliability of operation.
2 cl, 3 dwg
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Authors
Dates
2005-10-20—Published
2003-12-19—Filed