LIQUID-PROPELLANT ROCKET ENGINE WITH DEFLECTOR INSIDE NOZZLE Russian patent published in 2019 - IPC F02K9/90 

FIELD: rocket equipment.

SUBSTANCE: invention relates to control of thrust vector of rocket engines. Liquid-propellant engine comprising fuel line, chamber with cooled supersonic part of nozzle, uncooled nozzle from carbon-carbon composite material, connected to each other by means of detachable connection, steering units and a frame on a cooled part and an uncooled nozzle of a round-shaped collars, having equidistant surfaces with a graphite coating, between which four round-form deflectors of carbon-carbon composite material are installed, inner and outer surfaces of which are identical in shape to surfaces of collars, with axis of rotation located perpendicular to axis of cooled part of nozzle, and with an end surface of the deflector, which is a continuation of the shaped surface of the nozzle when they are in the initial position, according to the invention, in the area of the joint of the cooled supersonic part of the nozzle with parts of the deflector on the cooled part, there are four manifolds, which cavity is connected to chamber gas chamber by means of row of holes directed to deflector parts, and manifold inlet branch pipes are connected with engine fuel main line.

EFFECT: invention provides higher reliability of the deflector design and longer life.

1 cl, 2 dwg