SOLID PROPELLANT ROCKET ENGINE WITH VARIABLE THRUST VECTOR DIRECTION AND NOZZLE PLUG Russian patent published in 2019 - IPC F02K9/80 F02K9/97 

FIELD: engine building.

SUBSTANCE: solid-propellant rocket engine with variable traction vector in direction consists of power heat-insulated housing and central body, which form annular nozzle contour in outlet part, channel charge of solid fuel, attached to power heat-insulated housing, igniting device and nozzle plug, displacement drive located in central body. Part of central body extends beyond cutout of outer contour of annular nozzle. Power heat-insulated housing is equipped with additional internal power heat-insulated shell, which is continuation of central body located in inner cavity of channel charge of solid fuel and connected to rear bottom of power heat-insulated housing by sealing resilient hinge and mechanism of angular movement drive relative to central axis. Another invention of the group relates to a nozzle plug made in form of a sealing element. Sealing element is made in the form of toroidal elastic chamber filled with gas under pressure, installed in subsonic part of annular nozzle and connected by links in form of rods with several segments adjoining supersonic part of annular nozzle and uniformly located along its perimeter.

EFFECT: group of inventions allows reducing thrust losses, as well as reliability and stability of mode output at engine start-up.

7 cl, 4 dwg