LIQUID ROCKET ENGINE WITH DEFLECTOR SECTORS AT THE NOZZLE EXIT Russian patent published in 2017 - IPC F02K9/97 F02K9/80 

FIELD: engine devices and pumps.

SUBSTANCE: invention relates to rocket engines in which various control elements located at the nozzle exit or inside of it are used to control the thrust vector in flight. The LRE contains a chamber with cooled supersonic nozzle part, actuators and a frame, four sectors with a spherical outer surface are installed on the outer surface of the cooled supersonic nozzle part, with center on the chamber axis and side walls connecting the spherical surfaces of the sectors with the outer surface of the supersonic nozzle part, on which the deflector parts made of carbon-carbon composite material (CCCM) are installed, whose outer and inner surfaces, equidistant to sectors outer surface, are fixed to spherical sectors using shaped brackets disposed on either side of deflector parts and having inner surfaces, equidistant relative to the external surfaces of the deflector, having a gap between each other for mounting the bracket, placed on the outer surface of deflector parts. All equidistant surfaces of spherical sectors, parts of the deflector and brackets have a graphite coating.

EFFECT: increasing the efficiency, resource of work and reception of greater value of lateral driving effort and reducing the effort on actuators.

3 dwg