STAROVERV'S ROCKET ENGINE-2 (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 mix of borane and ammonia, or the solution or borane solution in the liquid ammonia. The components are fed at the following ratio: diborane - 44.8±10 wt %, ammonia - 55.2±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 ammonia are fed additionally to the combustion chamber or to the body.

EFFECT: higher specific thrust pulse.

4 cl