FIELD: rocketry.
SUBSTANCE: invention relates to perfected design of rocket engine. Proposed rocket engine has combustion chamber, nozzle with smooth wall and combustion chamber and nozzle matting section. Said mating section has cooling duct including coolant manifold made of copper-free material. In design version intended for high heat transfer level, mating section is provided with additional manifold made on copper based material. According to proposed method of assembling of combustion chamber, mating section is formed by its fitting manifold on mandrel with group of holes made in manifold into which frames made of solder are installed, and then set of assembly tubes is fitted in, tubes being connected with manifold by soldering in furnace.
EFFECT: possibility of use of tubular chamber of rocket engine with regenerative cooling with any smooth-wall nozzle.
16 cl, 8 dwg
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