FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, namely, to one-rotor-helicopter tail rotors. Tail rotor hydraulic drive comprises constant-output hydraulic motor (n) driving rotor (r), variable-delivery hydraulic pump (p) driven by helicopter rotor shaft (t), control lever (h) to vary volume delivery of hydraulic pump, and hydraulic lines (c) between pump (p) and motor (n). Tail rotor consists of three constant-pitch hingeless blades. Control lever (h) is connected with helicopter cabin control pedals (f). Tail rotor direction and thrust are varies by adjusting rotor rpm and direction by means of control lever (h) on varying fluid speed and reversing fluid flow through hydraulic motor (n). Hydraulic system comprises also drain tubes (i), oil tank (k), oil filter (o), radiator (e) and loading pump (g). In engine failure, tail rotor is driven by autorotation with control components active.
EFFECT: simplified design, higher reliability.
6 cl, 1 dwg
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