FIELD: transport.
SUBSTANCE: invention relates to production of helicopters. Multirotor helicopter comprises fuselage, frames, undercarriage, power plant, transmission, rotors and rotor control system. Engine torque is transmitted to four rotors via three differential gears. Central differential output shafts make lateral differential gear input shafts top transmit torque via bevel gearing to shafts of rotors. Helicopter rotor comprises hub with blades fitted thereat. Said hub is composed of two engaged jaw half-couplings. One of said half-couplings comprises disc and has dead joint with the shaft of rotors while another one runs free in circle through the angle equal to maximum in-flight pitch of rotor plus autorotation pitch. Rotor blades are articulated with said hub and coupled by links with hub disc with dead joint with the shaft of rotors whereon fitted is pitch and bank angle control rotor.
EFFECT: simplified control higher efficiency.
4 cl, 6 dwg
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