ROCKET Russian patent published in 2004 - IPC

FIELD: rocketry, applicable in short-range rocket complexes.

SUBSTANCE: the nozzle exit section of the main zero-stage engine has a cylindrical guide, installed in which is the primary thruster. The separation chamber is made in the form of an isolated cavity positioned inside the combustion chamber of the primary zero-stage thruster. This cavity is connected by means of the nozzles to a space formed by the walls of the nozzle of the main zero-stage engine and the zero-stage thruster. A sleeve with a blind bottom is installed inside the separation chamber. The powder charge is placed around the sleeve and made in the form of cylindrical tubes resting on the radial lugs on the sleeve outer surface made near the end facing the nozzles. An igniter is positioned inside the sleeve, and a delayed-action beam igniter is placed in the body opposite the igniter. The body outer surface and the sleeve walls form an annular exhaust-gas duct.

EFFECT: enhanced reliability of rocket functioning due to the enhanced accuracy of its ejection in the field of view of the control system with optical communication channels.

3 dwg