FIELD: aviation.
SUBSTANCE: invention relates to the field of aviation, in particular to the design of the helicopter, performed on single-rotor scheme with no tail rotor. Compensator reluctance torque of the rotor is in the form of a series of aerodynamic stabilizers disposed vertically in the region of rotation of the rotor and rotatable by means of the control wiring and longitudinal joints. Installed on the fuselage of the helicopter longitudinal joints associated with the transverse compensator wings and tail fins, which are interconnected aerodynamic grille of intersecting vertical stripes flute profile, the concave side oriented towards the rotation of the main rotor of the helicopter. Directional control pedal and the lever step-associated gas via the wiring of the automatic hydraulic cylinders with the body and wings of the transverse strut rods.
EFFECT: achieved weight reduction and vibration design of the helicopter, improving the reliability of management and more efficient use of engine power to create lift rotor.
2 cl, 2 dwg
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