N2O4/Aerozine-50

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SE-9-3 / SE-9-5 Credit - Boeing / Rocketdyne Oxidizer: N2O4. Oxidizer Density: 1.450 g/cc. Oxidizer Freezing Point: -11 deg C. Oxidizer Boiling Point: 21 deg C. Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Nitrogen tetroxide consists principally of the tetroxide in equilibrium with a small amount of nitrogen dioxide (NO2). The purified grade contains less than 0.1 per cent water. Nitrogen tetroxide (N2O4) has a characteristic reddish-brown colour in both liquid and gaseous phases. The solid tetroxide is colorless. N2O4 has an irritating, unpleasant acid-like odour. N2O4 is a very reactive, toxic oxidiser. It is non-flammable with air; however, it will inflame combustible materials. It is not sensitive to mechanical shock, heat, or detonation. Nitrogen dioxide is made by the catalytic oxidation of ammonia; steam is used as a diluent to reduce the combustion temperature. Most of the water is condensed out, and the gases are further cooled; the nitric oxide is oxidised to nitrogen dioxide, and the remainder of the water is removed as nitric acid. The gas is essentially pure nitrogen tetroxide, which is condensed in a brine-cooled liquefier. 1959 production amounted to 60,000 tonnes per year. In carload lots of one-ton cylinders, the price was $ 0.15 per kg. By 1990 NASA was paying $ 6.00 per kg due to environmental regulations. Fuel: Aerozine-50. Fuel Density: 0.903 g/cc. Fuel Freezing Point: -7 deg C. Fuel Boiling Point: 70 deg C. Fuel Comments: A 50-50 mixture of hydrazine and UDMH developed for use in the Titan 2 missile. Copied in one Russian missile but otherwise straight UDMH used more commonly. Higher boiling point than UDMH. Engines Using N2O4/Aerozine-50 Motor Thrust(vac) kN Thrust(sl) kN Isp sec Isp (sl) sec Designed for Status P-7   222.310   234     LR87-11 AJ23-138   1,008.310     First Stages   LR87-9   956.100     First Stages   Expansion-Deflection 10k   44.463         Expansion-Deflection 50k   222.326         SE-9-3 0.107   295       SE-9-5 0.196   300       RM-100T 0.441   296       AJ10-131 9.800           RS-18 15.563   310       Astris 23.300 19.600 310 260 Upper Stages   AJ10-138 35.600   311   Upper Stages Out of production TR-201 41.900   301   Upper Stages   AJ10-118K 43.400   321   Upper Stages   SE-10 46.670   305       LE-3 53.340   285       AJ10-137 97.500   312   Upper Stages Out of Production RD-280 117.600   350   Upper Stages Study 1961 Ares 440.000   370   First Stages Development 1968. LR91-7 444.800 225.200 316 160 Upper Stages Study 1961 LR91-5 444.800   315   Upper Stages Out of Production LR91-9 448.605   316   Upper Stages Out of Production LR91-11 467.000 232.700 316 160 Upper Stages Out of production LR87-7 1,086.100 946.700 296 258 First Stages Study 1961 LR87-5 1,096.800 956.500 297 259 First Stages Out of Production LR87-11 1,218.800 968.400 302 250 First Stages Out of production LR87+ 1,634.400 1,439.200 293 258 First Stages Study 1965 Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted.