AIRCRAFT CONTROL SYSTEM Russian patent published in 2013 - IPC B64C13/00 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Proposed system ups the horizontal flight performances owing to using aircraft longitudinal stability evaluation and flight stability variation compensation unit. It allows eliminating retention of transient processes characteristic of integral systems in aircraft nose heaviness and overload and angle of attack overshoots at bow heaviness. Added is the bank integral control unit to ensure preset conformity between bank stick deflection and bank angular speed. This allows accurate limitation of bank rate at maximum deflections of said stick. To decrab aircraft at stall phenomena originating at high angles of attack and in transonic zones bank disturbance compensation unit is used. Aircraft yaw stability and controllability are improved by using yaw integral control unit. This ensures accurate conformity in statics between pedal deflection and slip angle, limitation of slip angle at maximum pedal deflection and compensation of yaw moments originating at high angles of attack or at asymmetric configuration of aircraft with suspensions.

EFFECT: better characteristics of stability and controllability.

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