FIELD: rocketry.
SUBSTANCE: proposed of rocket engine contains cooled part, load-bearing ring and nozzle head made of composite material. Load-bearing ring is installed on cooled part from side of nozzle exit section, being connected with cooled part of nozzle through sealed joint made in form of lock with steps and gasket placed between steps. Load-bearing ring is fastened on cooling part by means of clamps connected with ring by bolts and engaging by one end with step of load-bearing ring and by other end, with thrust groove of nozzle cooled part.
EFFECT: possibility of using nozzle in engines with different dimensional and mass and thrust characteristics.
6 dwg
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