PROPULSION SYSTEM Russian patent published in 2019 - IPC F02K9/30 F02K9/97 

FIELD: rocket equipment.

SUBSTANCE: invention relates to rocket engineering and can be used in propulsion systems operating on solid fuel and autonomous onboard power sources. Propulsion system comprises chamber with nozzle bosses, in holes of which there are inserts with nozzles, screen, powder charge and igniter. Inserts are made composite – in the form of a holder placed along the axis of each sleeve of the bushing with a nozzle, the length of which is less than the length of the holder. On the bushing on the side of the chamber there is a flange, and the bushing itself is installed with axial and radial gaps relative to the holder and is fixed to it with a heat-shielding material. Heat-shielding material is applied on the inner surface of the holder along its entire length, and the supercritical part of the nozzle of the insert is partially made in the bushing, and partially in the heat-shielding material. Inserts are installed in combustion chamber with thrust in its inner surface and fixed by means of shield from heat-shielding material attached to chamber walls and external surface of inserts. Inner surface of the cartridge behind the point of contact with the chamber has a lowering.

EFFECT: higher reliability of propulsion unit while maintaining minimum weight of its design.

8 cl, 3 dwg