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-
|
|
|
|
|
|
|
|
|