FIELD: rocket technology.
SUBSTANCE: present invention relates to the field of rocket technology, mainly to systems such as unguided aircraft missiles (UAM), multiple launch rocket systems (MLRS), launch stages of anti-aircraft guided missiles (AAGM), etc. The use of the proposed technical solution will reduce the complexity of manufacturing and its cost, the total weight of the rocket engine and the rocket as a whole, increase the reliability and accuracy of the flight path and master mass production. The proposed design includes the rocket engine body itself, a nozzle block with attachment points of the tail, made in one piece with a heat-protective coating applied to the inner surface. Moreover, the entire structure is made of a thin-walled aluminum-based alloy pipe, and the heat-protective coating is made of an aluminum oxide anode film, the thickness is up to 60 microns, the ratio of the walls of the housing and the nozzle block is 5:1.
EFFECT: use of the proposed technical solution will reduce the complexity of manufacturing and its cost, the total weight of the rocket engine.
1 cl, 2 dwg
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