SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2007 - IPC F02K9/95 

FIELD: rocketry.

SUBSTANCE: invention can be used in designing solid-propellant rocket engines with high propellant loading ratio, particularly, with blind channel. Proposed solid-propellant rocket engine has charge with central channel connected with body and burning end face, nozzle assembly and igniter. The latter is arranged in zone of mating of burning end face and channel of charge. Ignition consists of housing in form of tubular ring with perforation filled up with pyrotechnical compound. Perforation is made in form of holes arranged over circumference with axis common with axis of engine and pointed inside charge channel, and holes pointed to zone of mating of burning end face and change channel.

EFFECT: improved energy producing characteristics and provision of quick and stable coming to conditions with high propellant loading ratio owing to simultaneous ignition of charge over entire burning surface.

3 cl, 5 dwg