FIELD: aviation.
SUBSTANCE: light double-rotor helicopter comprises a fuselage with a tail beam, lift rotors, a stabilizing yaw control system. Lift rotors are located in one plane and are interconnected kinematically. At that, the coefficient of lift rotors solidity constitutes 25÷30%. Lift rotors blades are made with a small elongation making a value from 5 to 7 units. Yaw control stabilizers are located behind the helicopter center of gravity along the fuselage sides in the peripheral zone of the front lift rotor rotation.
EFFECT: there is achieved a higher efficiency of load ratio at reduced power consumption of power plant and considerably reduced fuel consumption.
1 cl, 4 dwg
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