FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering, particularly, to helicopter rotors cyclic pitch change devices. Helicopter rotor blade with deflecting rear edge comprises flap, drive and movement transmission system built in blade case containing tie-rods. Drive is made piezoelectric and includes automatic control system. Movement transmission device is located in blade front part and comprises flap stroke increase lever, made with bending with angle α = 22°-25°, and tie-rods lie perpendicular to blade longitudinal axis.
EFFECT: higher lifting force, reduction of periodic loads on blade from its azimuthal interaction with aerodynamic flow and, consequently, reduced helicopter vibration in general.
1 cl, 11 dwg
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