Notional nuclear/lh2 rocket engine. 8963 kN. DAC Helios, DAC Helios ISI studies 1963. Isp=850s.
Status: Study 1963.
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Thrust: 8,963.00 kN (2,014,962 lbf).
Specific impulse: 850 s.
Burn time: 392 s.
Associated Launch Vehicles
DAC Helios ISI American nuclear-powered orbital launch vehicle. As the basic design, but featuring an Improved Specific Impulse chemical stage that used many engines feeding into single large nozzle. More...
DAC Helios American nuclear-powered orbital launch vehicle. Douglas/Bono 1963 concept for a chemical-boosted / nuclear upper stage launch vehicle, designed as alternatives to the Convair/Ehricke Helios. The baseline version used a nuclear, recoverable upper stage boosted above the atmosphere by a minimum chemical stage. More...
Nuclear/LH2 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 for space applications is the liquid form of the lightest element, hydrogen. Nuclear engines would have twice the performance of conventional chemical rocket engines. Although successfully ground-tested in both Russia and America, they have never been flown due primarily to environmental and safety concerns. 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. More...
DAC Helios-2 Nuclear/LH2 propellant rocket stage. Loaded/empty mass 1,070,000/214,000 kg. Thrust 17,926.00 kN. Vacuum specific impulse 850 seconds. More...
DAC Helios ISI-2 Nuclear/LH2 propellant rocket stage. Loaded/empty mass 1,070,000/214,000 kg. Thrust 17,926.00 kN. Vacuum specific impulse 850 seconds. More...
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