FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering, particularly, to helicopters with one lift rotor. The proposed short helicopter comprises a lift rotor and lift rotor reactive moment compensation mechanism. The disk of lift rotor rotation is crossed by compensating rotor/rotors rotation disk/disks. The gear ratio between the disks, representing the lift rotor RPM-to-compensating rotor RPM ratio satisfies ratio that follows, i.e. 
where, A is the gear ratio, N is the number of blades of lift rotor, n is the number of blades of the compensating rotor/rotors, C is an integer. The tail rotor rotation disk can be located at an angle to the helicopter a longitudinal vertical plane. The helicopter can have more than two compensating rotors on each side.
EFFECT: shortened helicopter tail boom.
7 cl, 7 dwg
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