Synthesis, thermal conductivity, and hydrogen compatibility of a high melt point solid solution uranium carbide, (U0.2Zr0.8)C
Not Available
11 NUCLEAR FUEL CYCLE AND FUEL MATERIALS↗
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Results for “Nuclear propulsion”
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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Fluid-phase helium: Shock-compression experiments, quantum molecular dynamics simulations, and development of an equation of state
Helium (He) plays a critical role in numerous areas ranging from the study of celestial objects like brown dwarfs and gas giants to modern-day technologies like nuclear energy and rocket propulsion. For many of these applications, it is essential to have a reliable equation of state (EOS) for He that yields an accurate representation of its thermodynamic behavior. To help constrain and develop such EOS models, we have performed a series of shock-compression experiments on cryogenic liquid He to pressures exceeding 100 GPa using a magnetically accelerated flyer plate on Sandia National Laboratories' Z-machine. We have also performed quantum molecular dynamics simulations that are consistent with our shock measurements. None of the previously available EOSs agree with our experimental and simulation results, motivating the development of a fluid-phase He EOS that we present in this study. Here, we show that our EOS yields good agreement with published data that span temperatures and pressures encountered across a diverse array of applications.
75 CONDENSED MATTER PHYSICS, SUPERCONDUCTIVITY AND↗
Kiwi-TNT Simulation Model [Slides]
The Kiwi-TNT Test (Toonerville Trolley) was performed on January 12, 1965. LANL has the objective: "LANL will develop a defensible methodology for establishing the maximum number of fissions for postulated inadvertent criticality events. The methodology may include several methods, such as hand calculations, sophisticated modeling, and the use of historical data.” The historic test, Kiwi TNT, posed a starting point for predictive simulations to determine the number of fissions and excursion understanding. This presentation gives results of that effort.
73 NUCLEAR PHYSICS AND RADIATION PHYSICS↗
A NUCLEAR-ELECTRIC SPACEBUS FOR PLANETARY LANDING MISSIONS
Nuclear-electric spacebus for planetary landing missions
SPACECRAFT↗
THE NASA NUCLEAR ELECTRIC POWER PROGRAM
The aim of the NASA nuclear electric power program is to provide long-lived reliable nuclear power sources in the range from tens of watts to tens of megawatts for advanced missions. The work is conducted in corporation with the U.S. Atomic Energy Commission which is developing isotope power sources and the reactor for the SNAP-8 project. Isotopes are considered for missions requiring up to several hundred watts of power. SNAP-8 will provide about 35 to 60 kilowatts for missions requiring tens of kilowatts and lifetimes of about one year. SNAP-8 has been redesigned to emphasize reliability and performance. This decision permits many components to operate at lower, more nearly state-of-the -art temperatures at the sacrifice of greater cooling requirements and increased weight. Beyond SNAP-8, an extensive applied research program has been conducted since 1959 to provide the technology required for the sound development of light weight nuclear electric systems in the megawatt range for lifetimes of up to several years. The work is accomplished in university, industrial and government laboratories.
SPACECRAFT POWER SUPPLY↗
THE NASA NUCLEAR ELECTRIC POWER PROGRAM
Description of nasa nuclear electric power program with special emphasis on power supplies in the surveyor program and the snap 8 project
SPACECRAFT POWER SUPPLY↗
Temperature-control engineering of a nuclear- electric spacecraft
Temperature control engineering of nuclear- electric spacecraft
NUCLEAR-ELECTRIC PROPULSION↗
Development of electrical switchgear for space nuclear electrical systems quarterly progress report no. 3, jun. 4 - sep. 4, 1965
Design, development, and testing of ground prototype ac circuit breakers and dc engine contactors for space nuclear electric system
CIRCUIT BREAKER↗
Preliminary investigations to determine nuclear-electric spacecraft configurations for high-energy missions.
Nuclear-electric spacecraft configurations for Jupiter mission discussing radiation shielding, heat rejection radiator, spacecraft structure, etc
HEAT REJECTION DEVICE↗
Trends in earth-planetary space transportation systems.
Space transportation systems for Moon exploration and beyond noting nuclear, nuclear pulse and electric propulsion
PROPULSION SYSTEM↗
Research Summary No. 36-9
Nuclear physics, materials science, propulsion, telecommunication, guidance, and systems analysis
Source record↗
Frontiers in propulsion research: Laser, matter-antimatter, excited helium, energy exchange thermonuclear fusion
Concepts are described that presently appear to have the potential for propulsion applications in the post-1990 era of space technology. The studies are still in progress, and only the current status of investigation is presented. The topics for possible propulsion application are lasers, nuclear fusion, matter-antimatter annihilation, electronically excited helium, energy exchange through the interaction of various fields, laser propagation, and thermonuclear fusion technology.
Papailiou, D. D.↗
Elliptic integral solutions to a class of space flight optimization problems
This paper is initially concerned with the minimum-time, exoatmospheric flight of a rocket with constant thrust acceleration magnitude, as in the cases of nuclear and solar electric propulsion. Gravitational acceleration is assumed to be a constant scalar multiple of the radius vector, plus a correction term which is a given function of time. The solution to the state equations is obtained in terms of elliptic integrals. A method is presented for the solution of the two-point boundary-condition problem associated with orbital transfer. At most, the latter method requires iteration upon final time, angle of injection, and two other parameters which are bounded. An example problem is provided which involves a rocket with very low thrust and a spiraling trajectory of many revolutions, but an altitude change of only several hundred miles above the earth. Finally, the original elliptic integral solution is extended to a larger class of low and intermediate thrust problems with constant thrust magnitude, mass decreasing with time, and an inverse square gravitational force.
Andrus, J. F.↗
To the solar foci
Earlier authors showed that the sun is likely to act as a lens for gravitational radiation, with focui in the outer solar system. They suggested that missions to these foci have the potential of directly measuring the density structure of the sun. Other applications include gravitational wave astronomy and tests of general relativity. This idea is reexamined, concentrating on the engineering aspects of focal missions; primarily spacecraft design and performance. Other topics studied include solar optics, gravitational wave detectors, navigation, and the design of missions for different purposes. Specifically, it is shown that shuttle launched chemical rockets have a substantial capability for reaching some foci; and that all can be reached with large payloads using nuclear isotope-electric propulsion.
Sonnabend, D.↗
Efficiency optimization of a thermionic converter array
Intensive study of the outer planets of the solar system requires the use of nuclear power for electric propulsion of spacecraft. Among the power conversion devices being considered for this application are thermionic converters. This paper presents the results of computer modeling of thermionic converters to identify the major design variables and select an optimum size for each of the thermionic converters for the power conversion system under consideration. Among the variables investigated were electrical and thermal losses in electrodes, leads and heat chokes. Those elements which minimized the electrical losses tended to increase thermal losses and system weight. Overall mechanical design and relative positioning of components also had impacts on converter efficiency and the power subsystem weight. Numerical calculations were made using the computer heat transfer code SINDA coupled with electrical loss parameters. The results of the computations are presented in this paper.
Kuo, Y. S.↗
Lunar bases - A post-Apollo evaluation
It is presently noted that the moon furnishes a stable and radio-quiet platform for astronomy and space physics, as well as a source for such materials resources as Si, Al, Fe, O, Mg, and Ti, and a base for low cost interplanetary exploration. Attention is given to a vehicle designated the 'Lunar Geochemical Orbiter', and it is recommended that the prospective NASA Space Station's structural modules be designed for lunar as well as orbital use. Further, design studies should be initiated for a manned orbital transfer vehicle (whose propulsion system may be nuclear).
Lowman, P. D., Jr.↗
Design of a fast crew transfer vehicle to Mars
A final report is made on the trajectory and vehicle requirements for a fast crew transfer vehicle to Mars which will complete an Earth to Mars (and Mars to Earth) transfer in 150 days and will have a stay time at Mars of 40 days. This vehicle will maximize the crew's effectiveness on Mars by minimizing detrimental physiological effects such as bone demineralization and loss of muscle tone caused by long period exposure to zero gravity and radiation from cosmic rays and solar flares. The crew transfer vehicle discussed will complete the second half of a Split Mission to Mars. In the Split Mission, a slow, unmanned cargo vehicle, nicknamed the Barge, is sent to Mars ahead of the crew vehicle. Once the Barge is in orbit around Mars, the fast crew vehicle will be launched to rendezvous with the Barge in Mars orbit. The vehicle presented is designed to carry six astronauts for a mission duration of one year. The vehicle uses a chemical propulsion system and a nuclear power system. Four crew modules, similar to the proposed Space Station Common Modules, are used to house the crew and support equipment during the mission. The final design also includes a command module that is shielded to protect the crew during radiation events.
Source record↗
Ion Thruster Development at NASA Lewis Research Center
Recent ion propulsion technology efforts at NASA's Lewis Research Center including development of kW-class xenon ion thrusters, high power xenon and krypton ion thrusters, and power processors are reviewed. Thruster physical characteristics, performance data, life projections, and power processor component technology are summarized. The ion propulsion technology program is structured to address a broad set of mission applications from satellite stationkeeping and repositioning to primary propulsion using solar or nuclear power systems.
Sovey, James S.↗