FIELD: rocketry.
SUBSTANCE: proposed ramjet engine contains air intake, generator with propellant combustion chamber with fuel unit and exit nozzle. Propellant carrying sections with nozzles for efflux of propellant jets from inner spaces of sections into inner space of combustion chamber are installed in combustion chamber and connected to control unit. Nozzles in each propellant carrying section are distributed over perimeter of combustion chamber, and their axes are pointed at angle of 90°>β>0° to axis of combustion chamber. Propellant charges differing in chemical composition and aggregative state are arranged in different propellant carrying sections. One or several propellant carrying sections are installed in narrowing (subsonic) part of engine exit nozzle.
EFFECT: improved mixing of propellant components providing complete combustion of propellant, improved stability of burning process in combustion chamber of ramjet engine.
3 cl, 5 dwg
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