N2O4/MMH
Aestus
Credit - Boeing / Rocketdyne
Propellant Formulation: N2O4/MMH. Optimum Oxidiser to Fuel Ratio: 2.16. Temperature of Combustion: 3,385 deg K. Density: 1.20 g/cc. Isp (sl): 288. Isp (vac): 336.
Oxidiser: N2O4. Oxidiser Density: 1.450 g/cc. Oxidiser Freezing Point: -11 deg C. Oxidiser 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: MMH. Fuel Density: 0.880 g/cc. Fuel Freezing Point: -52 deg C. Fuel Boiling Point: 87 deg C.

Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. Monomethylhydrazine (MMH) is 95+ per cent pure, while the normally expected impurities are methylamine and water. MMH is a clear, water-white hygroscopic liquid which tends to turn yellow upon exposure to air. MMH is a toxic, volatile liquid which will react with carbon dioxide and oxygen. MMH has the typical sharp ammoniacal or fishy odour of amines. It is completely miscible in all proportions with hydrazine, water, and low molecular-weight alcohols. MMH is not sensitive to impact or friction; it is more stable than hydrazine on mild heating and similar to hydrazine in sensitivity to catalytic oxidation.

Monomethylhydrazine may be produced by a modified Raschig process; methylamine is substituted for ammonia in the reaction with chloramine. In general, substituted hydrazines may be prepared by the reaction of an alkylsulfate or halide with hydrazine. In 1959 the price for MMH was $ 15 per kg. It was projected that this would be reduced to $ 2.00 per kg in mass production. By 1990 NASA was actually paying $ 17.00 per kg due to stringent environmental protection regulations. By 2006 this had skyrocketed to $170.00 per kg.


Engines Using N2O4/MMH
Engine
engineslink
Thrust(vac)
kN
Thrust(sl)
kN
Isp
sec
Isp (sea level)
sec
Designed for Status
TIROC 0.001   303   Satellites  
Aerojet 2 0.002   265   Upper Stages In Production
RS-45 0.004   300      
RM-1-1 0.004   245      
RM-1-2 0.004   238      
RS-43 0.020   284      
RM-05 0.020   238      
Aerojet 21 0.021   285   Upper Stages In Production
MRE-5/Compton Observatory 0.025   240   Upper Stages In Production
KEW-1 0.029   266      
R-6C 0.033   290   Upper Stages In Production
Aerojet 62 0.062   287   Upper Stages In Production
RS-1403 0.078   230      
RS-1402 0.098   259      
SE-6 0.107   277      
SE-7-25 0.107   277      
RM-25-1 0.107   300      
RM-25 0.107   286      
R-1E 0.110   280   Upper Stages In Production
RESA-2 0.215          
KEW-2 0.215   275      
SE-7-1 0.313   274      
SE-7-85 0.372   295      
SE-8 0.411   274      
KEW-3 0.441   283      
RS-42 0.441   305      
RM-100A 0.441   301      
SE-7-100 0.441   296      
Aerojet 445 0.445   309   Upper Stages In Production
HiPAT 0.445   323   Upper Stages In Production
R-4D 0.490   312   Upper Stages Study 1985
OMV Variable Thrust Engine 0.578       Upper Stages In Production
DMT-600 MMH 0.600   306   Upper Stages In Production
R-42 0.890   303   Upper Stages In Production
RS-2101C 1.333   294      
RS-2101A 1.333   287      
RS-14 1.392   315      
RS-32 1.392   288      
KEW-4 2.216   235      
RS-28 2.667   220      
R-40A 3.870   306   Upper Stages In Production
R-40B 4.000   293   Upper Stages In Production
RM-900 4.001   309      
LR-101-NA-7 5.148   251      
PSLV-4 7.000   308   Upper Stages  
RESA-5 7.109   280      
RS-51 11.552   315      
RS-34 11.700   308      
RS-41 11.960   320      
Transtar 16.700   328   Upper Stages Development completed 1987
XLR-132 16.700   340   Upper Stages Out of Production
General Technology 17.779   295      
Liberty-2 17.800 11.900 300 200 Upper Stages Development ended 1988
Press Fed 17.800   300   Upper Stages Design concept 1960's
ATE 20.000   347   Upper Stages Developed 1990's
RS-23 26.670   313      
OME 26.700   316   First Stages Study 1972
L7 27.400   320   Upper Stages In Production
Aestus 29.000   324   Upper stages In production
RS-72 55.400   340      
RS-36 55.600   281      
Aestus-2 60.000       Upper stages Production
RD-0242M 98.100   336   Upper Stages Design concept 1998-
RD-0242M1 98.100   343   Upper Stages Design concept 1998-
 
 
 
 
 
 
 
 
 

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 - 2007 except where otherwise noted.

 
Encyclopedia Astronautica
topic index
0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z