LIQUID-PROPELLANT ROCKET ENGINE WITH CONTROLLED VECTOR OF THRUST Russian patent published in 2019 - IPC F02K9/80 F02K9/66 

FIELD: missiles.

SUBSTANCE: invention relates to rocket engineering. Liquid-propellant engine with controlled thrust vector, comprising a chamber nozzle swinging along main stabilization planes and a gimbal assembly with trunnions in orthogonal planes between traverses and a frame and mounted between the cardan assembly and the outer housing of the nozzle of the chamber in the region of the nozzle minimum section with a split band with trunnions, installed end parts on ends of the annular collars of the nozzle housing to minimum downstream of gases in the nozzle and after the minimum cross-section, wherein between detachable band and chamber housing and aligned therewith are installed conical bushes, oriented by minimum diameters first – to input, and second – to output from minimum nozzle cross-section, wherein minimum diameters fixed on nozzle case ends, and maximum first – on band on side of inlet part of nozzle, and second – on band on side of outlet part of nozzle, wherein in cone walls of bushings there are through radial slots, which form lugs, installed last in slots of bushings without mutual contact lugs.

EFFECT: invention provides higher reliability for liquid rocket engines of large thrusts, reduced radial dimensions of liquid-propellant engine, sealing of engine arrangement and due to this reduction of engine weight.

1 cl, 8 dwg