METHOD FOR COMPLETION OF LIQUID-PROPELLANT ENGINE WITH AFTERBURNING WITH CONTROLLED VECTOR OF THRUST Russian patent published in 2019 - IPC F02K9/66 F02K9/80 

FIELD: rocket equipment.

SUBSTANCE: invention relates to rocket engineering, and more specifically to methods for assembling liquid-propellant rocket engines with afterburning with controlled thrust vector. Method of assembling liquid-propellant engine with afterburning with controlled thrust vector, comprising operations of chamber housing assembly made of cylindrical part, convergent and divergent sections of nozzle, with cardan installed along periphery of joint of tapering section of nozzle with expanding beam, and then with trunnions and frame of liquid-propellant rocket engine, wherein cardan installation is performed before operation of connection of cases of convergent and divergent part of nozzle, cardan is separated by means of technological devices with the possibility of fixation from longitudinal and transverse displacements of it during operations of assembling of bodies of convergent and divergent sections of nozzle, two cases of convergent and divergent part of nozzle are connected, for example, by welding, and installation of cardan in trunnions of chambers and in trunnions of traverses, assembly of crossarms with frame is performed after complete cycle of chamber manufacturing.

EFFECT: invention provides for reduction of radial dimensions and weight of engine due to possibility of making cardan in form of solid monolithic block by means of volumetric forming without connectors of power perimeter part and trunnions.

1 cl, 13 dwg