| 摘要 |
FIELD: astronautics.SUBSTANCE: invention relates to space engineering, particularly intended at low-mass satellites. Cylindrical cases of terminals of heating elements and needle-type thermocouples are made in the form of flat bracket. Sensitive elements of needle-type thermocouples are arranged in cavity of micromotor on nozzle side. Swirler is composed of the cavity formed by surfaces of helical spring, located in the gap between cylindrical barrel with gas line and chamber of micromotor and contact with chamber inner surface and external smooth surface of cylindrical barrel and directing gas flow in to the nozzle. At micromotor end part at the point of output terminals of heating elements and on the side of the nozzle at its outlet thermocouples cavities for application of heat-resistant sealing compound are made. At the inlet of swirler cavity at chamber side surface of micromotor inlet branch pipe is made connected with pipeline of gasified fuel.EFFECT: invention provides higher specific thrust pulse at 12-15 % due to reduction of mass of micromotor on 14-18 %, shorter time for repair and its cost, high quality of sealing composition and air-tightness of micromotor.1 cl, 9 dwg |
