FIELD: aircraft engineering.
SUBSTANCE: helicopter comprises fuselage, rotor, antitorque rotor with controlled common and cyclic pitch, power plant, transmission elements and control system. Antitorque rotor shaft is set at constant angle in helicopter horizontal plane of 50-70 degrees relative to helicopter lengthwise axis. Common and cyclic pitch control mechanism is composed of swash plate with one-channel control with ring deflection through angle that increases or decreases propulsive component of antitorque rotor thrust vector. Control method comprises setting of rotor at constant angle in helicopter horizontal plane of 50-70 degrees relative to helicopter horizontal axis. Antitorque rotor cyclic pitch is controlled by swash plate in one channel by deflection of its ring in both directions relative to antitorque rotor shaft axis corresponding to thrust vector turn through not over 10 degrees.
EFFECT: simplified changeover from hovering to horizontal flight.
4 cl, 4 dwg
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