FIELD: rocket technology.
SUBSTANCE: invention relates to rocket technology and is intended for use in rockets. The body of the missile part contains the launch (7) and sustainer (1) combustion chambers with shells (2) and (6), the diaphragm (3) with axial (9) and peripheral (5) gas ducts with membranes and a nozzle. The area of the flow section of the axial gas pipeline is not less than 0.1 of the total area of the flow section of the gas pipelines. The thickness of the heat-shielding coating of the surfaces of the peripheral gas ducts facing the shells (2) and (6) of the combustion chambers is 1.5…3.0 of the thickness of the heat-shielding coating of the side and inner surfaces of the peripheral gas ducts.
EFFECT: increased stability of characteristics and reliability of operation.
1 cl, 1 dwg
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