CHAMBER OF LIQUID ROCKET ENGINE (LRE) WITH GAS-DYNAMIC METHOD FOR CONTROL OF THRUST VECTOR AND NOZZLE OF CARBON-CARBON COMPOSITE MATERIAL (CCCM)

摘要

FIELD: rocket science.;SUBSTANCE: invention relates to rocket engines, in which gas-dynamic control of a thrust vector is used. A chamber of a liquid rocket engine (hereinafter – LRE) with a gas-dynamic method for control of a thrust vector and a nozzle is proposed, containing a cooled supersonic part with sectors for supply of a working medium to injection, located above it, a non-cooled section of carbon-carbon composite material (hereinafter – CCCM), inlet and outlet cooler collectors, and sectors for supply of the working medium. According to the invention, in the chamber, sectors with holes for supply of the working medium to injection are located in the area of an output part of the cooled nozzle, at a place of connection to the nozzle of CCCM, and holes of injection are made in the area of thickening of ribs alternately located with ribs without thickening, and they, together with an annular groove, provide flowing of a coolant of the output part of the nozzle and the place of connection to the nozzle, channels of the cooler of the nozzle part in the area of location of injection sectors, and have, between injection sectors, common inlet and outlet collectors.;EFFECT: invention provides an increase in the efficiency of gas-dynamic control of a thrust vector, as well as improvement of energy-weight characteristics of an engine.;2 cl, 5 dwg