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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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PERIGEE PROPULSION FOR ORBITAL LAUNCH OF NUCLEAR ROCKETS
Perigee propulsion for orbital launch of nuclear rockets
NUCLEAR PROPULSION. STATE OF THE ART - 1962
Nuclear propulsion progress - kiwi-b reactor, propellant and engine development, rift project, and nerva engine
Coaxial flow gaseous nuclear reactor concept
Coaxial flow gaseous fission reactor concept
Applications of low-power nuclear rockets
Velocity requirements of low power missions, and performance attainable with nuclear rockets
Fast and moderated low-power, lightweight reactors for nuclear rocket propulsion
Properties of high temperature materials for nuclear rocket reactor application - reactor concepts for low power lightweight nuclear power plant
Nuclear rockets for unmanned missions
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Gas-Core Reactor Work at NASA/Lewis
Gas core reactor, discussing application of fissionable gas to heat hydrogen propellant in nuclear rocket reactor
Nuclear rockets for interplanetary propulsion
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Fast and moderated reactors and applications of low-power nuclear rockets
Fast and moderated nuclear reactors, and feasibility of low-power lightweight reactors for nuclear rocket engine applications
Very high burnup vapor transport fuel pin concept for long life nuclear reactors
Very high burnup vapor transport fuel pin concept for long life nuclear reactors
Fast and moderated reactors and applications of low-power nuclear rockets.
Fast and thermal reactors for nuclear rockets noting high temperature materials requirements, performance and low power
Will the nuclear-powered aircraft be safe?
Safety of nuclear powered aircraft, discussing radiation protection, shock prevention in case of accidents, reactor shielding, etc
Fuel element concept for long life high power nuclear reactors
Nuclear reactor fuel elements have burnups that are an order of magnitude higher than can currently be achieved by conventional design practice. Elements have greater time integrated power producing capacity per unit volume. Element design concept capitalizes on known design principles and observed behavior of nuclear fuel.
Nuclear-Rocket Propulsion
The three basic types of nuclear power-plants (solid, liquid, and gas core) are compared on the bases of performance potential and the status of current technology. The solid-core systems are expected to have impulses in the range of 850 seconds, any thrust level (as long as it is greater than 10,000 pounds (44,480 newtons)), and thrust-to-engine-weight ratios of 2 to 20 pounds per pound (19.7 to 197 newtons per kilogram). There is negligible or no fuel loss from the solid-core system. The solid-core system, of course, has had the most work done on it. Large-scale tests have been performed on a breadboard engine that has produced specific impulses greater than 700 seconds at thrust levels of about 50,000 pounds (222,000 newtons). The liquid-core reactor would be interesting in the specific impulse range of 1200 to 1500 seconds. Again, any thrust level can be obtained depending on how big or small the reactor is made. The thrust-to-engine weight ratio for these systems would be in the range of 1 to 10. The discouraging feature of the liquid-core system is the high fuel-loss ratio anticipated. Values of 0.01 to 0.1 pound (0.00454 to 0.0454 kilograms) or uranium loss per pound (0.454 kilograms) of hydrogen are expected, if impulses in the range of 1200 to 1500 seconds are desired. The gas-core reactor shows specific impulses in the range of 1500 to 2500 seconds. The thrust levels should be at least as high as the weight so that the thrust-to-weight ratio does not go below 1. Because the engine weight is not expected to be under 100,000 pounds (444,800 newtons), thrust levels higher than 100,000 pounds (448,000 newtons) are of interest. The thrust-to-engine weights, in that case, would run from 1 to 20 pounds per pound (9.8 to 19.7 kilograms). Gas-core reactors tend to be very large, and can have high thrust-to-weight ratios. As in the case of the liquid-core system, the fuel loss that will be attendant with gas cores as envisioned today will be rather high. The loss rates will be 0.01 to 0.1 pound of uranium (0.00454 to 0.0454 kilograms) for each pound (0.454 kilograms) of hydrogen.