FIELD: rocket engines.
SUBSTANCE: proposed rocket engine contains combustion chamber whose working part is designed for combustion of propellant and oxidizer and is connected by neck with converging nozzle for exhaust of gases formed at combustion. Oxidizer is fed to working part from end opposite to neck. Working part is enclosed in porous surface layer made of thermally cross-linked composite material into which propellant is fed from outer side opposite to working part. Part of propellant is fed to working part through porous surface layer. Part of propellant getting into working part through porous surface layer is used to supply engine. Part of propellant non-passing through porous surface layer is directed to neck for cooling the neck.
EFFECT: provision of rocket engine of simple design and small weight with small number of parts and easy to manufacture.
12 cl, 13 dwg
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