FIELD: engines and pumps.
SUBSTANCE: rocket engine comprises combustion chamber and pyrotechnic has generator grains. One set of said grains generates gaseous, vaporous or slurry propellant while another set generates oxidiser. Propellant of oxidiser is directed into combustion chamber cooling jacket for its cooling, or two components are directed into different compartments of said jacket. In compliance with another version, rocket engine makes a pipe with combustion chamber made at its one end and with end face made at opposite end. Said pipe is divided by transverse baffle with lengthwise pipe extending to combustion chamber or cooling jacket.
EFFECT: lower temperature at engine housing walls.
5 cl, 3 dwg
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