FIELD: rocket science.
SUBSTANCE: invention relates to rocket science and concerns a structure of a rocket engine operating on bulk solid fuel. A heat protection mechanism of a rocket engine chamber contains a set of shielding heat-protection tapes located near walls in a working chamber of the engine and rewound by a tape-extending mechanism located on a cut of a nozzle, while tapes are introduced to the engine chamber through the cut of the nozzle, pass along a nozzle wall to a bottom of a combustion chamber, where guiding rollers are installed, and further pass to the specified tape-extending mechanism.
EFFECT: invention provides reduction in power used for rewinding of a tape, as well as increase in the reliability of operation of a heat protection mechanism.
1 cl, 3 dwg
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