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RD-0410 NTP Engine
RD-0410 NTP Engine - RD-0410 Nuclear Thermal Engine

Credit: © Dietrich Haeseler. 25,183 bytes. 159 x 327 pixels.

Oxidiser: Nuclear.

Nuclear thermal engines use the heat of a nuclear reactor to heat a propellant. Although early Russian designs used ammonia or alcohol as propellant, the ideal working fluid is the liquid form of the lightest element, hydrogen. Nuclear engines would have twice the performance of conventional chemical rocket engines. Although successfully tested in both Russia and America, they have never been flown due primarily to environmental and safety concerns.

Fuel: LH2. Fuel Density: 0.07 g/cc. Fuel Freezing Point: -259.00 deg C. Fuel Boiling Point: -253.00 deg C.

Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today.

In Russia hydrogen fuelled upper stages were designed and developed by the mid-1970's, but the Russians never seem to have found the extra performance to be worth the extra cost. Europe and China developed liquid oxygen/liquid hydrogen engines for upper stages of the Ariane and Long March launch vehicles.

The equilibrium composition of liquid hydrogen is 99.79 per cent parahydrogen and 0.21 per cent orthohydrogen. The boiling point of this composition is -253 deg C. Liquid hydrogen is transparent and without a characteristic odour. Gaseous hydrogen is colourless. Hydrogen is not toxic but is an extremely flammable material. The flammable limits of gaseous hydrogen in air are 4.0 to 75 volume percent.

Hydrogen is produced from by-product hydrogen from petroleum refining and the partial oxidation of fuel oil. The gaseous hydrogen is purified to 99.999+ per cent, and then liquefied in the presence of paramagnetic metallic oxides. The metallic oxides catalyse the ortho-para transformation of freshly liquefied hydrogen. Freshly liquefied hydrogen which has not been catalysed consists of a 3:1 ortho-para mixture and cannot be stored for any length of time because of the exothermic heat of conversion. The delivered cost of liquid hydrogen in 1960 was approximately $ 2.60 per kg. Large-scale production was expected to reduce the cost to $ 1.00 per kg. In the 1980's NASA was actually paying $ 3.60 per kg.

Engines Using Nuclear/LH2

Eng-engineslink Thrust(vac)-kgf Thrust(vac)-kN Isp-sec Isp (sea level)-sec Designed for Status
RD-0410 3,600 35.30 910   Upper Stages Developed 1965-94
RD-410 7,000 68.00     Upper Stages Developed 1960s
YaERD-2200 8,300 81.00     Upper Stages Developed 1962-69
YaRD Type A 18,000 177.00 900   Upper Stages Study 1963
YaRD Type AF 20,000 196.00 950   Upper Stages Study 1963
Nerva 27,206 266.00 800   Upper Stages Developed 1960's
Nerva NTR 34,000 333.40 925   Upper Stages Design concept 1980's
YaRD Type V 40,000 392.00 900   Upper Stages Study 1963
YaRD Type V-B 40,000 392.00 900   Upper Stages Study 1963
RD-0411 40,000 392.00 900   Upper Stages Design concept 1965-94
Timberwind 45 45,000 441.30 1,000 890 Upper Stages Developed -1990
Timberwind 75 75,000 735.50 1,000 890 Upper Stages Developed -1990
Nerva 2 88,451 867.40 825 380 Upper Stages Developed 1950-74
RD-600 200,000 1,960.00 2,000   Upper Stages Developed 1962-70
Timberwind 250 250,000 2,451.60 1,000 780 Upper Stages Developed -1990
Nuclear 12 Gw 295,000 2,892.00 830   Upper Stages Study, Ehricke, 1960
Nuclear 14 Gw 340,000 3,334.00 830   Upper Stages Study, Ehricke, 1960
NERVA 1mlbf 914,000 8,963.00 850   Upper Stages Study 1963

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