STAROVERV'S ROCKET ENGINE-9 (VERSIONS) Russian patent published in 2015 - IPC F02K9/08 F02K9/42 F02K99/00 

FIELD: engines and pumps.

SUBSTANCE: claimed rocket engine comprises the combustion chamber whereto fed is the pressurized mix of borane and hydrazine, or the solution or borane emulsion in the liquid hydrazine. The components are fed at the following ratio: diborane - 46.33±10 wt %, hydrazine - 53.67.2±10 wt %. Additionally, 0.0001-1 wt % of the bulk of reacting substances of fine coal, and/or soot, and/or graphite, and/of methane are fed into said combustion chamber. In compliance with the second version, the rocket engine comprises the combustion chamber or the body with nozzle running on liquid or solid propellant. Besides, the exhaust gas of the engine running on diborane, or tetraborane and hydrazine are fed additionally to the combustion chamber or to the body.

EFFECT: higher specific thrust pulse.

4 cl