STAROVEROV'S ROCKET PROPELLANT - 15 (VERSIONS) Russian patent published in 2014 - IPC F02K9/00 C06B47/02 C06B47/10 C06B27/00 C10L1/10 C10L1/12 

FIELD: engines and pumps.

SUBSTANCE: rocket propellant comprises fuel and oxidiser. Rocket propellant features the following composition at the following ratio of components in wt %: beryllium borane - 34.63±10, ammonia dinitramide - 55.50±10, beryllium hydride - 9.87±5, or beryllium borane - 23.78±10, ammonia dinitramide - 76.22±10, or lithium borane - 35.85±10, ammonia dinitramide - 51.06±10, lithium hydride - 13.09±5, or aluminium borane - 23.66±10, ammonia dinitramide - 57.76±10, aluminium hydride - 18.58±5, or decaborane - 39.64±10, ammonia dinitramide - 60.36±10. Other versions are produced using the reaction with ammonia (wt %): beryllium borane - 44.61±10, ammonia dinitramide - 35.75±10, ammonia - 19.63±5. All said reactions can be realised with the help of the other oxidiser, that is, nitrogen hexaoxide, N₃O₆.

EFFECT: emission of pure hydrogen solely.

11 cl