JET PROJECTILE ATTITUDE STABILIZATION SYSTEM

military equipment, in particular, flight vehicle control systems. SUBSTANCE: the system has an angular deviation sensor with a sensing element with a permanent magnet, drive, signal and reference windings, gas-dynamic actuator with supersonic nozzles, signal conversion unit, whose inputs are connected to the signal and reference windings, and the output - to the gas-dynamic actuator. The angular deviation sensor in the system is additionally provided with the second reference winding shifted by 90 degrees relative to the first reference winding and connected to the additional input of the signal conversion unit, the sensing element of the angular deviation sensor is made in the form of a spherical float and positioned in a spherical chamber mechanically linked with the drive, the spherical chamber is filled with liquid having a viscosity within 0.0022 to 0.04 sq.cm/S. Bushings are fastened on the projectile body coaxially with the nozzles in a spaced relation between the nozzle outside diameter and the bushing inside diameter, and the angle of setting of nozzle axes relative to the reference windings is determined by formula: = ωtau+arctgKCÐC, where - angle of setting of nozzle axes relative to the reference windings, ω - rate of projectile spin, tau - time lag of the gas-dynamic actuator, Kccc-cross coupling coefficient of the angular deviation sensor. EFFECT: enhanced accuracy of projectile stabilization due to reduced system dynamic errors. 2 dwg