GYROSCOPIC INSTRUMENT Russian patent published in 2000 - IPC

FIELD: rocketry, in particular, gyroscopic instruments of small- sized spin-stabilized guided missiles, used, for example, as a missile bearing pick-off at movement in trajectory. SUBSTANCE: the instrument has a rotor in a gimbal suspension, acceleration engine located in a separate chamber of the body and having a profiled output shaft aligned with the rotor, thread lead bush on the output shaft and an edge joint in the form of a groove and tongue. Positioned on the outer surface of the lead bush is a bearing in a race through which the lead bush relative to the body is pressed by a spring towards the acceleration engine. The hole in the lead bush on the opposite side of the acceleration engine is made threaded, and an annular cylindrical collar with a radial tongue is made in its periphery, they are conjugate respectively to the central hole and groove on the edge of the rotor bearing support. The rotor axle is made with a threaded section, with its smooth end it is installed in the hole of the lead bush and combined with it by a threaded joint. A bulge is made on the lateral wall of the rotor support groove at its edge towards the sense of rotation of the acceleration engine and motion of the tongue. A limiting ring is positioned on the body in alignment with the rotor with coverage of the lead bush. In another modification the rotor axle is installed in a hole of the lead bush, installed between the bearing race and the body is a stop kinematically linked with the rotary lever and pyrotechnical pusher, a limiting ring is positioned on the body in alignment with the rotor with a coverage of the lead bush. EFFECT: enhanced reliability and accuracy. 2 cl, 7 dwg