SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2011 - IPC F02K9/32 F02K9/95 

FIELD: engines and pumps.

SUBSTANCE: solid-propellant rocket engine includes chamber with nozzle, front bottom, solid-propellant charge from bundle of cartridges, which is attached to the front bottom, priming composition in perforated metal tube, which is attached to the bottom, and nozzle closure. In perforated metal tube on the side of the front bottom there is perforated section throughout the length of not more than the half of the tube length, after which a pin with diameter of 0.1 to 0.3 of inner diameter of the tube is installed perpendicular to tube axis. Perforation holes are covered with cover from gas-permeable material, which is fixed on outer surface of the tube. Shell with pyrotechnic tracer agent arranged inside it, which protrudes beyond the end of cartridge bundle, is installed on the tube on the nozzle side. Nozzle closure is made from flexible material in the form of membrane with disc-shaped flanging, central boss with a hole and annular groove. Flanging of the closure is fixed in the connector made in supercritical part of the nozzle, and its groove is made on the side of the nozzle bell.

EFFECT: invention allows increasing energy characteristics of rocket engine and safety of its use.

3 cl, 2 dwg