LIQUID ROCKET ENGINE WITH A NOZZLE OF CARBON-CARBON COMPOSITE MATERIAL (CCCM) Russian patent published in 2018 - IPC F02K9/90 F02K9/80 

FIELD: motors and pumps.

SUBSTANCE: invention relates to the thrust vector control of liquid rocket engines (LRE). LRE contains a chamber with a cooled supersonic part of a nozzle, an uncooled nozzle of a carbon-carbon composite material interconnected by a detachable joint, steering assemblies and a frame, in accordance with the invention, on the cooled part of the nozzle and the uncooled nozzle there are made round-shaped beads and having equidistant surfaces with a graphite coating, between which in two mutually perpendicular-disposed planes four round-shaped deflectors of carbon-carbon composite material are installed, the internal and external surfaces of which are identical in shape to the surfaces of the beads with the axis of rotation, located on the axis of the cooled part of the nozzle, and with the end surface of the deflector, which is a continuation of the profiled surface of the nozzle when they are in their original position.

EFFECT: invention provides a reduction in the weight of the structure, increase the efficiency of control and reduction in the effort on the steering units.

1 cl, 5 dwg