SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2004 - IPC

Abstract RU 2239082 C2

FIELD: rocketry.

SUBSTANCE: proposed solid-propellant rocket engine has combustion chamber with inserted powder charge and nozzle assembly, bottom and nozzle diaphragms and bottom space with channel to let out gas from bottom space. If nozzle number is even, channel to let out gas from bottom space is made in form of tubes directly connecting bottom space with each second nozzle. If nozzle number is odd, channel to let out gas from bottom space is made in form of tubes directly connecting bottom space with each nozzle, outer diameter of tubes being less than diameter of nozzle critical section, thus forming ring passage cross section.

EFFECT: improved efficiency of holding of inserted powder charge in combustion chamber.

3 dwg

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RU 2 239 082 C2

Authors

Bol'Shakov A.N.

Krejer K.V.

Khudjakov V.I.

Dates

2004-10-27Published

2002-12-26Filed