LIQUID-PROPELLANT ROCKET ENGINE WITH AFTERBURNING WITH CONTROLLED VECTOR OF THRUST Russian patent published in 2020 - IPC F02K9/62 F02K9/66 

FIELD: rocket equipment.

SUBSTANCE: invention relates to rocket engineering, in which creation of liquid-propellant rocket engines with minimum possible weight, longitudinal and radial dimensions is always actual, especially for liquid-propellant rocket engines of upper stages of carrier rockets, more specifically, to liquid-propellant engine with afterburning with controlled thrust vector. Said task of invention is achieved by the fact that in it between support lower part of frame and fixed housing of flexible pipeline with displacement towards chamber nozzle along longitudinal axis of chamber and at distance from longitudinal axis and from fixed housing of flexible pipeline and at distance to longitudinal axis from support points of frame of mating face in parallel to mating face there is a closed frame, connected on one side by rods at points with second fixed housing of flexible pipeline, and on the other side – rods with support part of missile in vicinity of mating face.

EFFECT: invention reduces lengthwise dimensions of liquid-propellant engine with afterburning of generator gas with controlled thrust vector and reduces its weight.

1 cl, 11 dwg