FIELD: aircraft manufacture. SUBSTANCE: system of control of collective and cyclic pitch of rotor flexible blade of combination flying vehicle has unit for control of blade root angle mounted on drum and blade tip stabilization unit which has centrifugal weight with stabilizer secured on it. Secured on stabilizer is servoflap connected with arm of three-arm crank by means of rod. Secured on second arm of crank is centrifugal control weight. Third arm of crank is connected by means of rope with piston which is coaxial to feathering hinge secured inside drum of blade winding. Piston is linked with arm of crank through connecting rod; second arm of crank is linked inside drum with rear (according to rotation) part of external body of feathering hinge through L-shaped crank; swivel unit for securing the blade root is mounted in body of feathering hinge. Blade root control unit has blade carrier with threaded end portion which is secured on external body of feathering hinge. Lever of this carrier is connected with swash- plate by means of rod. Locking unit is arranged inside the carrier body. EFFECT: reduction of load exerted on rod of swash- plate, providing the control system with flapping compensator, relief of blade root from torsion stresses, reduction of overall dimensions and mass of system and enhanced thrust characteristics of rotor. 3 dwg
