GYROSCOPIC INSTRUMENT

摘要

FIELD: instrumentation. SUBSTANCE: gyroscopic instrument is designed for use on small-sized guided rockets having bank spinning in the capacity of sensor of angle of bearing of rocket moving along trajectory. It includes case with circular flange for its anchoring. Rotor is placed in gimbal suspension. Boosting engine is fitted with gas nozzles, powder charge and electric igniter. Boosting engine is manufactured in the form of reaction turbine. Powder charge and electric igniter are located in chamber of reaction turbine, gas nozzles are made tangential on rim of reaction turbine. Turbine is positioned in space of case isolated from rotor and is linked with rotor via hole in wall of space uniaxial to rotor with the use of split coupling having gas sealing. Gas release passages are made in case behind plane of circular flange to anchor it on side opposite to rotor. Circular screen is placed uniaxially to reaction turbine with embracing of tangential nozzles. Arresting device including nut screwed on pin of reaction turbine is mounted on external surface of wall of space opposite to rotor. Current lead contacts of electric igniter are located on nut. Design of instrument ensures decrease of value of drift of rotor axis thanks to increase of its rotation speed and diminished heat and mechanical effect of boosting engine on rotor. EFFECT: increased accuracy of measurement of angles of bearing thanks to decreased values of drift of rotor axis owing to its increased rotational speed and diminished heat and mechanical effect of powder boosting engine on rotor. 2 dwge