SOLID-PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2011 - IPC F02K9/28 F02K9/32 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises combustion chamber, nozzle with recessed part and heat protection coat, and charge secured with combustion chamber and made up of two parts separated by web. Smaller part of said charge is arranged above recessed nozzle section and made from low-temperature charge while larger part is made from high-temperature fuel. In compliance with one version, cylinder thrusting against web and rear bottom is arranged between recessed section of nozzle and low-temperature charge, and aligned with said nozzle. Cylinder side surface has holes with their axes perpendicular to nozzle axis. Total area of said holes is selected subject to maintenance of low-temperature fuel consumption in the range of 2-3% of high-temperature fuel consumption. In compliance with second version, cylinder is made from thermally degradable and ablated material. In compliance with third version, said web is arranged on nozzle recessed section, while through holes are made on cylindrical surface of said recessed section along circumference, with their axes inclined to nozzle axis at angle smaller than 90°.

EFFECT: reliable and stable heat protection of rocket engine nozzle, lower weight.

3 cl, 3 dwg