Lox/LCH4

Oxidiser: LOX. Oxidiser Density: 1.140 g/cc. Oxidiser Freezing Point: -219 deg C. Oxidiser Boiling Point: -183 deg C.

Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquid oxygen, as normally supplied, is of 99.5 percent purity and is covered in the United States by Military Specification MIL-P-25508. High purity liquid oxygen has a light blue colour and is transparent. It has no characteristic odour. Liquid oxygen does not burn, but will support combustion vigorously. The liquid is stable; however, mixtures of fuel and liquid oxygen are shock-sensitive. Gaseous oxygen can form mixtures with fuel vapours that can be exploded by static electricity, electric spark, or flame. Liquid oxygen is obtained from air by fractional distillation. The 1959 United. States production of high-purity oxygen was estimated at nearly 2 million tonnes. The cost of liquid oxygen, at that time, ex-works, was $ 0.04 per kg. By the 1980's NASA was paying $ 0.08 per kg.


Fuel: LCH4. Fuel Density: 0.424 g/cc. Fuel Freezing Point: -184 deg C. Fuel Boiling Point: -162 deg C.

Liquid methane has been proposed as a propellant by the Russians.


Engines Using Lox/LCH4
Engine
engineslink
Thrust(vac)
kN
Thrust(sl)
kN
Isp
sec
Isp (sea level)
sec
Designed for Status
RD-0129           Developed 1990s
RD-184     322   Upper Stages Developed 1996-on
Orbitec Methane Engine 0.133       Upper Stages Developed 2005-
OPI Methane Engine 0.445       Upper Stages Developed 2001-
RD-183 9.800   360   Upper Stages Developed 1996-
RD-160 19.600   381   Upper Stages Developed 1993-
RD-169 167.000   351 309 First Stages Design concept 1990's
RD-185 179.000   378   Upper Stages Developed 1996-
RD-167 353.000   379   Upper Stages Design concept 1990's
RD-0234-CH 442.000   343 310 Upper Stages Developed 1996-
RD-0256-Methane 836.000   353   Upper Stages Design concept 1996-
RD-190 1,000.000   351 309 First Stages Developed 1996-
RD-0120-CH 1,576.000   363   First Stages Design concept 1990's
RD-0120M-CH 1,720.000   372   First Stages Design concept 1990's
RD-192.2 1,942.000   354 325 Upper Stages Developed 1996-on
RD-192.3 2,089.000   341 311 Upper Stages Developed 1996-on
RD-192S 2,128.000   372   Upper Stages Developed 1996-on
RD-192 2,138.000   356 330 Upper Stages Developed 1996-
 
 
 
 
 
 
 
 
 

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