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astronautix.com Lox/LCH4





Oxidiser: LOX. Oxidiser Density: 1.14 g/cc. Oxidiser Freezing Point: -219.00 deg C. Oxidiser Boiling Point: -183.00 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: 0.42 g/cc. Fuel Freezing Point: -184.00 deg C. Fuel Boiling Point: -162.00 deg C. Fuel.Comments: Liquid methane has been proposed as a propellant by the Russians.
Engines Using Lox/LCH4

Eng-engineslink Thrust(vac)-kgf Thrust(vac)-kN Isp-sec Isp (sea level)-sec Designed for Status
RD-183 999 9.80 360   Upper Stages Developed 1996-
RD-160 2,000 19.60 381   Upper Stages Developed 1993-
RD-169 17,000 167.00 351 309 First Stages Design concept 1990's
RD-185 18,250 179.00 378   Upper Stages Developed 1996-
RD-167 36,000 353.00 379   Upper Stages Design concept 1990's
RD-0234-CH 45,000 442.00 343 310 Upper Stages Developed 1996-
RD-0256-Methane 85,248 836.00 353   Upper Stages Design concept 1996-
RD-182 92,000 902.00 353 316 First Stages Developed 1994-
RD-190 101,972 1,000.00 351 309 First Stages Developed 1996-
RD-0120-CH 160,707 1,576.00 363   First Stages Design concept 1990's
RD-0120M-CH 175,391 1,720.00 372   First Stages Design concept 1990's
RD-192.2 198,000 1,942.00 354 325 Upper Stages Developed 1996-on
RD-192.3 213,000 2,089.00 341 311 Upper Stages Developed 1996-on
RD-192S 217,000 2,128.00 372   Upper Stages Developed 1996-on
RD-192 218,015 2,138.00 356 330 Upper Stages Developed 1996-


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Last update 3 May 2001.
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© Mark Wade, 2001 .