FIELD: engines and pumps.
SUBSTANCE: invention relates to rocketry and can be used in designing and producing solid propellant rocket engines, gas generators and solid propellant independent charges. Proposed engine comprises combustion chamber with nozzle unit, independent solid propellant charge and igniter. Nozzle unit is furnished with seal plug. Solid propellant charge represents a cylindrical monoblock with armored front face and side surface adjoining said front face. Igniter is arranged nearby rear unrestricted charge face. The side of aforesaid face features through channels arranged at an angle to charge lengthwise axis, channels outlets being located nearby extremity of the charge side armor.
EFFECT: reduced maximum pressure in starting operation, higher reliability, reduced weight.
5 dwg
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RU2438033C1 |
