LAYOUT OF CRUISE MULTI-CHAMBER PROPULSION PLANT OF TWO-STAGE LAUNCHER WITH COMPOSITE NOZZLE CLUSTER Russian patent published in 2017 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the sphere of space engineering. Package of cruise multi-chamber propulsion plant of two-stage launcher with composite nozzle cluster comprises a rocket pods of a first and second stages, they are connected and operate under parallel circuit, a cooling chamber of liquid-fuel rocket engines (LFRE) of first stage located around shortened central body common for both chambers of a plug-in nozzle, and a combustion chamber of second stage located in internal cavity of this shortened central body near their common round disk-shaped nozzle, connected by detachable assemblies of power link with detachable rocket pods of stages. The shortened central body of plug-in nozzle of the propulsion plant of the first stage and disk-shape nozzle of the propulsion plant of the second stage are made in form of single nozzles cluster coaxial with longitudinal axis of the rocket pods of the first banbd second stages. The cooled chambers of LFRE of the first stage of launcher have de Laval nozzles of preliminary expansion with round minimum cross-section and rectangular output cross-section, inclination relatively to the nozzle axis, and assembled to single ring package with rigid connection of side output edges of adjacent preliminary de Laval nozzles of preliminary expansion, and central body of the plug-in nozzle starts from bottom, close to axis of package of output edges of these nozzles. Planes of output cross-sections of nozzles of preliminary expansion are located perpendicularly to the longitudinal axis of the shortened central body. Fired surface of uncooled shortened central body made out of composite material is profiled ads continuation of the cooled fired surface of the nozzle of preliminary expansion.

EFFECT: invention ensures increasing of the having average flight energy specific propulsion burn of the multi-chamber propulsion plants of the first and second stages of the launcher and decreasing of bottom resistance of these stages.

3 cl, 8 dwg