FIELD: machine building.
SUBSTANCE: invention relates to aircraft and space-rocket equipment and can be used for creation of aerospace system of horizontal launch or for creation of aircraft, which will be able to perform short-term flight with hypersonic speed. Combined aircraft engine comprises supersonic controlled air intake, which ends with subsonic expanding diffuser, compressor, oxidative gas generator for increasing gas temperature, rotating compressor to turbine and combustion chamber with self-regulated nozzle made cooled. Turbine has the possibility of flow rate control. Between air intake and compressor mixer is installed, made with possibility to mix liquid nitrogen tetraoxide to air flow at flight speed corresponding to Mach number 3<Mn<6.
EFFECT: use of the invention allows reducing weight of the propulsion unit and simplifying its design.
1 cl, 1 dwg, 1 tbl
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