FIELD: aircraft control. SUBSTANCE: facility includes singledegree-of-freedom gyro in the form of transmitter of angular velocity, power supply source and pointer-type angle indicator. Output of transmitter is coupled via amplifier and functional converter to indicator. Amplifier comes in the form of multiplying element to which input signal proportional to flying speed is fed. Functional converter realizes dependence of turning angle of aircraft on flying speed and angular speed of turn. Power supply source has D C voltage-to-A C three-phase voltage converter, element testing presence and correctness of phase alternation and relay. EFFECT: prolonged service life and increased functional reliability of facility, reduced mass and dimension characteristics, raised accuracy of measurement of turning angle of aircraft independent of inclination angle of indicator. 2 cl, 6 dwg
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