FIELD: aviation.
SUBSTANCE: invention relates to aircraft flight control means. Aerodynamic rudder consists of front and rear turning links with maximum turning angle of front link, smaller than maximum angle of rotation of rear link relative to not deflected position. Front and rear links can turn relative to one common axis, which is located on 25-30 % of chord of rudder at not deflected links.
EFFECT: invention is aimed at reduction of total rudder hinge moment, reduced capacity of power drive and reduced weight of rudder turning mechanism.
1 cl, 1 dwg
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