FIELD: engines and pumps.
SUBSTANCE: proposed rocket engine comprises housing made from composite material with front and rear flanges, front cover, charge with through channel jointed with said housing and nozzle with its section sunken in housing. Armor is applied on through channel surface representing a collar partially adjoining thermal protection applied on shell ring arranged around nozzle sunken section. Housing comprises sealing frame while outer surface of said sunken section is provided with obturator assembly jointed therewith in minimum radius area. Sealing frame is jointed with rear flange by ring arranged around sunken section. Nozzle attachment assembly is arranged on rear flange outer face side. Aforesaid collar fits shell ring thermal protection via anti-adhesive sublayer. Minimum positive allowance is made between collar and nozzle section extending into housing inner space and over said minimum positive allowance.
EFFECT: reduced weight, simplified design and production.
4 cl, 2 dwg
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