DUAL-CHAMBER SOLID PROPELLANT ROCKET ENGINE (SPRE) Russian patent published in 2023 - IPC F02K9/28 

FIELD: rocket technology.

SUBSTANCE: invention relates to rocket technology, namely, rocket propulsion systems having two or more fuel charges, with the outflow of gases resulting from combustion through a common nozzle. Two-chamber solid-propellant rocket engine, consisting of a body, front, intermediate and rear bottoms with heat-shielding coatings, a nozzle, an igniter, a retractable mechanism, a starting charge of fuel, a sustainer charge of fuel, consisting of movable and fixed parts, there is a central hole in the intermediate bottom, closed by a cover with a heat-shielding coating, in the fixed part of the sustainer fuel charge there is an armored channel along its surface, inside which the movable part of the sustainer fuel charge is installed, adjoining its rear end to the cover with a heat-shielding coating, and the front - to the front end cap and retractable with the help of retractable mechanism by means of a system of pins and stops towards the nozzle, the cylindrical surface of the moving part of the main fuel charge is covered with an armor coating, which is an elastic sleeve with an edge bent at an angle of 180 degrees from the side of the rear end, to which the cables are attached, stretched to the front end cover through a system of rigging blocks and attached to the front bottom. The initiation of the igniter of the main fuel charge occurs by means of a piezoelectric element triggered by the mutual movement of the intermediate bottom and the cover with heat-shielding coatings or by closing electrical contacts when the moving part of the main fuel charge is extended.

EFFECT: invention provides tactical flexibility for the use of an aircraft with a solid propellant rocket engine over a wide range of altitudes, distances to the target and maneuvers.

3 cl, 2 dwg