FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering. In compliance with each version, helicopter comprises airframe consisting of the cab and engine with drive shaft, two opposite rotors, aerodynamic control system and landing hardware. In compliance with the first version, helicopter is furnished with wings, longitudinal arch girder and rotors synchronous rotation reduction gearbox. Said cab and engine are jointed together by the base of wings and longitudinal arch girder so that horizontal rotational planes of rotors intersect above airframe at zero to 60 degrees. Control system comprises rudder, wing and fin ailerons, as well as turning lobes. In compliance with the second version, helicopter comprises top arch and lateral tandem wings, as well as rotors coaxial shafts counter rotation gearbox. Control system comprises rudder fin and aerodynamic control surface and two turning lobes. Horizontal rotational planes of rotors intersect above coaxial drive shaft at zero to 60 degrees, said shaft being provided with CV-joint.
EFFECT: increased range and speed of horizontal flight.
6 cl, 7 dwg
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