FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to hybrid helicopters. Hybrid helicopter 1 comprises fuselage 2, surface 3 to generate lift, stabiliser surfaces 30, 35, 40, and integral drive system. The latter is composed of mechanical connection system 15 arranged between rotor 10 of radius R with control over blades collective pitch and control over rotor blades cyclic pitch by, at least, one propeller 6 with control over collective pitch of air screw blades, and, at least, one gas turbine engine to drive said mechanical system. Output rpm of said engine 6, said air screw 6, said rotor 10 and said mechanical connection system 15 varies mutually proportionally with invariable proportionality constant at all flight conditions. Rotor generates lift required for takeoff, landing, hovering and vertical flight, and portion of lift for horizontal flight.
EFFECT: improved design.
21 cl, 4 dwg
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