FIELD: rocketry; space vehicle jet control systems and power plant liquid gas generators. SUBSTANCE: proposed liquid rocket engine has propellant thermal decomposition chamber accommodating engine starting heater made in form of hollow cup with perforated walls and bottom pointed to nozzle inside which rod swirler is installed. Open end of cup is connected to chamber housing and place of its joint with engine nozzle. Heater is wound onto cup with clearance between turns, and additional electric heater is wound, with clearance between turns, on inner surface of chamber side wall. If hollow cylinder is used, heater is wound onto wall of hollow cylinder. Hollow perforated cylinder installed additionally provides enlargement of range of used monopropellants at higher thrust and increase of consumption intensity of engine decomposition chamber. EFFECT: provision of high dynamic and mass-energy characteristics of engine. 4 cl, 3 dwg
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