FIELD: aviation.
SUBSTANCE: invention relates to aircraft engineering, in particular to devices for controlling the change in the instantaneous value of the bearing strength of rotor blades. Helicopter rotor blade comprises a flap with a piezoelectric drive and a transmission mechanism incorporated in the blade housing comprising a lever and a pull rod connected to the flap and an automatic control system. Flap is made in the form of a trim plate located outside the aerodynamic profile in the rear part of the blade. Width of the trimmer plate is not more than 10 % of the blade chord. Trimmer plate is fixed with the possibility of deviation in both sides from the blade profile. Transmission mechanism lever is straight, and the pull rod is perpendicular to the longitudinal axis of the blade.
EFFECT: increased speed, accuracy and clarity of the system are provided.
6 cl, 10 dwg
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