FIELD: rocket technology.
SUBSTANCE: invention relates to rocket technology and is intended for use in rockets. A solid propellant rocket engine (SPRE) contains a housing, a nozzle cuff, a nozzle with a heat-shielding coating, and an insert of the critical section of the nozzle. According to the invention, the heat-shielding coating of the subsonic part of the nozzle is made in a section limited by a cross-section passing through the end of the nozzle cuff, 0.35…0.45 L long, with a thickening, and the thickness of the heat-shielding coating in this section is 1.4…1.8 of the thickness heat-shielding coating in a section spaced from the nozzle cuff at a distance of 0.75 L, where L is the distance from the end of the nozzle cuff to the end of the heat-shielding coating at the liner in the critical section.
EFFECT: invention provides increased reliability of solid propellant rocket engine operation with a charge of highly metallized fuels with a high content of condensed phase in combustion products.
1 cl, 1 dwg
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