FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to hydrid helicopters. Helicopter 1 comprises fuselage 2, surface 3 generating aerodynamic lift, tail plane surfaces 30, 35, 40, and integral drive system. Said rive system is made up of mechanical linkage 15 between radius R rotor 10 with pitch and blade cyclic pitch control system, at least, one rotor 6 with common blade control, and, at least, one gas turbine engine 5 to drive said mechanical linkage 15. Rotor 10 is continuously driven by gas turbine engine 5 irrespective of helicopter flight stage. Rotor rpm (Ω) equals first rpm (Ω1) before first flight speed (V1) of helicopter 1 decreasing gradually in using linear dependence as function of flight speed along flight path. Factor of proportionality of engine output rpm, rotor rpm and linkage rpm is constant.
EFFECT: reduced weight, higher efficiency.
17 cl, 4 dwg
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