This page no longer updated from 31 October 2001. Latest version can be found at Lox/Kerosene/LH2

RD-701 -

Credit: © Mark Wade. 10,913 bytes. 139 x 200 pixels.

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.

Engines Using Lox/Kerosene/LH2

Eng-engineslink Thrust(vac)-kgf Thrust(vac)-kN Isp-sec Isp (sea level)-sec Designed for Status
RD-0120TD 134,297 1,317.00 419 295 Upper Stages Developed 1990's
RD-0750 175,391 1,720.00 451   Upper Stages Developed 1997-
RD-704 200,480 1,966.00 407 356 Upper Stages Developed 1990's
RD-701 408,200 4,003.00 415 330 First Stages Hardware

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