TWO-REGIME ROCKET ENGINE Russian patent published in 1997 - IPC

FIELD: rocket engineering. SUBSTANCE: inside the housing are combustion chambers of starting and cruise regimes. Between the chambers is a baffle provided with igniting and inlet openings. In the end face of the engine is a nozzle unit with Laval nozzles of starting regime and at least one Laval nozzle of cruise regime. There is a pipe line inside the engine. One end of the pipe line is connected with the combustion chamber of cruise regime through the outlet opening in the baffle. The inner diameter of the pipe line is equal or exceeds the outer maximum diameter of the opening of the converging portion of the Laval nozzle. EFFECT: enhanced efficiency. 1 dwg