SOLID-PROPELLANT LAUNCHING ROCKET ENGINE Russian patent published in 2008 - IPC F02K9/10 

FIELD: engines and pumps.

SUBSTANCE: solid-propellant launching rocket engine incorporates an annular combustion chamber with a nozzle unit, an igniter and multi-grain charge made up of all-round burning grains representing equal-diameter channel cylinders buried one into another, the grains axes being arranged on circular arc. The distance between the channel cylinder axes and circular arc diameter the said grain axes are located on, are defined by ratios protected by this invention. Cavities between the grains adjoining the outer and/or inner annular chamber outline accommodate additional small caliber grains. The said small-caliber grains are made in the form of channel and/or channelless cylinders of all-round burning, or in the form of channel cylinders armoured over the outer surface.

EFFECT: higher efficiency of launching engine thanks to optimum filling of its combustion chamber with fuel.

3 cl, 9 dwg, 1 tbl