STAROVEROV ROCKET ENGINE (VERSIONS) Russian patent published in 2016 - IPC F02K9/08 F02K9/42 F02K99/00 

FIELD: engines.

SUBSTANCE: rocket engine comprises combustion chamber, wherein combustion chamber is supplied with borane, or silane, or phosphine, or germane, or other hydrides, having positive formation enthalpy from simple substances, or their mixture at temperature, enabling self-maintaining pattern of said substances thermal decomposition reaction due to exothermal reaction heat. In another embodiment, rocket engine comprises combustion chamber or housing with nozzle, operating on liquid or solid rocket fuel. At that, into combustion chamber or solid propellant rocket housing in addition to redox fuel additionally supplied are diborane, tetraboran or methane in amount of 1:1 to fuel, or solid rocket fuel composition additionally contains beryllium boron hydride, in amount exceeding oxidizer oxidizing capabilities by 10 %.

EFFECT: higher specific impulse of rocket engine.

6 cl