FIELD: rocketry. SUBSTANCE: according to proposed method, self-igniting components of fuel are delivered tangentially into corresponding coaxial vortex chambers of bipropellant centrifugal injector, and cylindrical sheets are formed changing into conical ones at mixing, igniting and burning in combustion chamber. Inner sheet is in contact with outer sheet in zone of transition of cylindrical part of sheet into conical one. Difference of semi-angles of components spray cones does not exceed 15°. EFFECT: improved efficiency of fuel component mixing and burning process, provision of reliable heat protection of walls of mixing head fire bottom, combustion chamber and injector, increased specific thrust pulse of liquid propellant thruster. 2 cl, 4 dwg
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