FIELD: aeronautical engineering.
SUBSTANCE: proposed system has control members in each control channel kinematically connected with position sensor and electrically connected with electronic computer which is connected in its turn with onboard information monitoring system whose analog output is connected with electric remote control actuators. Flight parameter sensor outputs are connected to electron computer. Control member position sensor in each control channel and electronic computer are provided with at least double redundancy in digital and analog parts with function of shaping and processing the signals in all redundant channels.
EFFECT: enhanced reliability of control and safety of flight.
1 dwg
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