HELICOPTER YAW CONTROL SYSTEM Russian patent published in 2025 - IPC B64C27/82 B64C15/14 

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, particularly, to rotor thrust and yaw control systems. Helicopter yaw control system includes air intakes located on the helicopter fuselage under the rotor, an air channel, an electric motor located in the fuselage tail part, a two-stage compressor, a tail channel, a flap and controlled nozzles. Air collectors are made with possibility of supply of air sucked from atmosphere through air channel to two-stage compressor connected to electric motor, and then to controlled nozzles located in tail channel, which is controlled by means of shutter. Air flow between nozzles is distributed in ratio of 0.7 to 0.3 at cruising flight mode or at ratio of 0.55 to 0.45 at turning.

EFFECT: control of nozzles directly from electric motor with preservation of power of main engine and rotor.

1 cl, 2 dwg