FIELD: transport.
SUBSTANCE: proposed mechanical system consists of gyro and control blades incorporated with assemblies that serve to control the helicopter multi-blade rotor cyclic pitch. Aforesaid gyro is arranged on the rotor shaft and runs at r.p.m. of the rotor. The gyro represents a ring with two rods attached thereto and furnished with weights locked thereon, and damping and control vanes. The axis of blades crosses the gyro ring and swinging point. Aforesaid control vanes are arranged to vary blade angle, when running on the shaft driven by the tie-rods coupled either directly, or via the system of cranks with swashplate.
EFFECT: reduced structure weight.
2 dwg
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