Comparison of Closed- and Open-Cycle Systems
Nuclear light bulb engine and coaxial flow, gaseous core reactor rocket
F C Schwenk↗
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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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Experiments on the containment of simulated fuel in unheated and heated vortexes
Simulated-fuel containment characteristics in heated and unheated vortex flows for nuclear light bulb engines
Arthur E. Mensing↗
Calculations of the spectral emission from the fuel region of a nuclear light bulb reactor
Heavy-atom model parameter change, seed gas addition, and reflective end-wall effects on nuclear light bulb engine calculations of fuel region radiation emission spectra
Krascella, N. L.↗
Development of a high intensity RF radiant energy source for simulating the thermal environment of the nuclear light bulb reactor
Radio frequency induction heating plasma generator design and fiber optic scanner for simulation of nuclear light bulb engines
Roman, W. C.↗
Initial experiments to investigate condensation of flowing metal-vapor/heated-gas mixtures in a duct
Iodine/air and zinc/argon condensation tests of flowing metal-vapor/heated-gas mixtures in ducts for cavity exhaust port design of nuclear light bulb engines
Bauer, H. E.↗
Optical transmittance of fused silica during irradiation processes.
The level of irradiation-induced optical absorption and the resulting heat deposition in the transparent fused-silica wall of a nuclear light bulb engine during normal operation are investigated by means of a series of related experiments using available radiation sources, each of which simulates some aspect of the radiation flux or dose of the engine. A comparison of the results obtained in electron and reactor experiments indicates that the generation of optical absorption is due to ionizing effects and that neutron-caused displacement effects do not contribute significantly to optical absorption. The implications of these and other results obtained are discussed.
Palma, G. E.↗
Optical transmittance of fused silica at elevated temperatures during high energy electron bombardment.
An experimental determination of the optical transmission of Corning 7940 UV and Suprasil I fused silica has been made. The LeRC dynamitron provided the equivalent ionizing radiation and high temperature that the transparent gas divider of an operating nuclear light bulb engine would experience. The irradiation induced absorption was measured at 2150 A, 2700 A, and 4500 A. The length of the irradiations were sufficient so that an equilibrium between radiation induced coloration and high temperature annealing was reached. The experimental results indicate a significant optical absorption, particularly at the shorter wavelength, which would make the use of fused silica in this concept questionable.
Smith, A. B.↗
Space power - Emerging opportunities
NASA programs directed towards the development of technologies to meet the cost-effective energy needs of future space missions are described. Consideration is given to the space photovoltaic program, which was developed along two paths: one leading to high-performance ultralight weight solar arrays, the other to high output arrays. The space power materials and energy storage technology are discussed, together with the developmental aspects of an advanced solar dynamic power system and its subsystems. Special attention is given to the Nasa SP-100 Advanced Technology Project and the free-piston Stirling engine technology for nuclear power application.
Brandhorst, H. W.↗
Electromagnetic powered vehicles (EMPV) for Mars exploration
Special attention has been given to manned missions to the Moon and Mars not only for exploration, but to establish permanent manned outposts. In order to fulfill such ambitious plans, it is necessary to establish technology bases in the areas of transportation, robotics, life support, and power generation. In the latter area, major progress has been made in solar dynamics, photovoltaics, heat cycle engines, thermionics, and nuclear space power generation. At the level of the present technology, massive structures are required for power generation, cooling, and shielding. The great mass of these systems will hinder a manned mission from obtaining a reasonable mobility over a planetary surface. For planetary exploration, small wheeled vehicles driven by batteries or fuel cells have been proposed, although other types such as solar or nuclear powered could potentially be used.
Christian, Jose L., Jr.↗
Heat transfer analysis of fuel assemblies in a heterogeneous gas core nuclear rocket
Heat transfer problems of a heterogeneous gaseous core nuclear rocket were studied. The reactor core consists of 1.5-m long hexagonal fuel assemblies filled with pressurized uranium tetrafluoride (UF4) gas. The fuel gas temperature ranges from 3500 to 7000 K at a nominal operating condition of 40 atm. Each fuel assembly has seven coolant tubes, through which hydrogen propellant flows. The propellant temperature is not constrained by the fuel temperature but by the maximum temperature of the graphite coolant tube. For a core achieving a fission power density of 1000 MW/cu m, the propellant core exit temperature can be as high as 3200 K. The physical size of a 1250 MW gaseous core nuclear rocket is comparable with that of a NERVA-type solid core nuclear rocket. The engine can deliver a specific impulse of 1020 seconds and a thrust of 330 kN.
Watanabe, Yoichi↗
Report of the Nuclear Propulsion Mission Analysis, Figures of Merit Subpanel: Quantifiable figures of merit for nuclear thermal propulsion
The results of an inquiry by the Nuclear Propulsion Mission Analysis, Figures of Merit subpanel are given. The subpanel was tasked to consider the question of what are the appropriate and quantifiable parameters to be used in the definition of an overall figure of merit (FoM) for Mars transportation system (MTS) nuclear thermal rocket engines (NTR). Such a characterization is needed to resolve the NTR engine design trades by a logical and orderly means, and to provide a meaningful method for comparison of the various NTR engine concepts. The subpanel was specifically tasked to identify the quantifiable engine parameters which would be the most significant engine factors affecting an overall FoM for a MTS and was not tasked with determining 'acceptable' or 'recommended' values for the identified parameters. In addition, the subpanel was asked not to define an overall FoM for a MTS. Thus, the selection of a specific approach, applicable weighting factors, to any interrelationships, for establishing an overall numerical FoM were considered beyond the scope of the subpanel inquiry.
Haynes, Davy A.↗
NTRE extended life feasibility assessment
Results of a feasibility analysis of a long life, reusable nuclear thermal rocket engine are presented in text and graph form. Two engine/reactor concepts are addressed: the Particle Bed Reactor (PBR) design and the Commonwealth of Independent States (CIS) concept. Engine design, integration, reliability, and safety are addressed by various members of the NTRE team from Aerojet Propulsion Division, Energopool (Russia), and Babcock & Wilcox.
Source record↗
New Mars vehicle concepts
The paper briefly reviews the evolution of the Mars vehicle design concepts from 1952 to 1990, and the currently understood requirements, constraints, and options for manned Mars missions in the early decades of the 21st century. The most up-to-date integrated Mars vehicle concepts for crew-carrying transfer and excursion vehicles are presented together with the Mars descent-ascent mission phases. Particular attention is given to a reusable transfer ship, which is a modular vehicle launched to earth orbit on six 185 t-class boosters and assembled there robotically; it uses dual nuclear-thermal rocket engines and liquid hydrogen propellant. The lander concept is capable of supporting many kinds of surface missions anywhere on Mars.
Sherwood, Brent↗
SSTAC/ARTS Review of the Draft Integrated Technology Plan (ITP). Volume 2: Propulsion Systems
The topics addressed are: (1) space propulsion technology program overview; (2) space propulsion technology program fact sheet; (3) low thrust propulsion; (4) advanced propulsion concepts; (5) high-thrust chemical propulsion; (6) cryogenic fluid management; (7) NASA CSTI earth-to-orbit propulsion; (8) advanced main combustion chamber program; (9) earth-to-orbit propulsion turbomachinery; (10) transportation technology; (11) space chemical engines technology; (12) nuclear propulsion; (13) spacecraft on-board propulsion; and (14) low-cost commercial transport.
Source record↗
A review of nuclear thermal propulsion carbide fuel corrosion and key issues
Corrosion (mass loss) of carbide nuclear fuels due to their exposure to hot hydrogen in nuclear thermal propulsion engine systems greatly impacts the performance, thrust-to-weight and life of such systems. This report provides an overview of key issues and processes associated with the corrosion of carbide materials. Additionally, past pertinent development reactor test observations, as well as related experimental work and analysis modeling efforts are reviewed. At the conclusion, recommendations are presented, which provide the foundation for future corrosion modeling and verification efforts.
Pelaccio, Dennis G.↗
Propulsion Options For Interstellar Exploration
NASA is considering missions to explore near-interstellar space (40 - 250 Astronomical Units) early in the next decade as the first step toward a vigorous interstellar exploration program. A key enabling technology for such an ambitious science and exploration effort is a propulsion system capable of providing fast trip times, yet which has low enough mass to allow for the use of inexpensive launch vehicles. Advanced propulsion technologies that might support the First interstellar precursor mission by the end of the first decade of the new millennium include solar sails and nuclear electric propulsion. Solar sails and electric propulsion are two technology areas that may hold promise for the next generation of interstellar precursor missions as well - perhaps a thousand astronomical units traveled in a professional lifetime. Future missions to far beyond the Heliosphere will require the development of propulsion technologies that are only at the conceptual stage today. For years, the scientific community has been interested in solar sail and electric propulsion technologies to support robotic exploration of the solar system. Progress in thin-film materials fabrication and handling, and advancement in technologies that may enable the deployment of large sails in space are only now maturing to the point where ambitious interstellar precursor missions using sails can be considered. Xenon ion propulsion is now being demonstrated for planetary exploration by the Deep Space 1 mission. The primary issues for the adaptation of electric propulsion to interstellar precursor applications include the development of low specific mass nuclear power systems, engine lifetime, and high power operation. Recent studies of interstellar precursor mission scenarios that use these propulsion systems will be described, and the range of application of each technology will be explored.
Johnson, Les↗
Robust Joining and Assembly Technologies for Ceramic Matrix Composites: Technical Challenges and Opportunities
Fiber reinforced ceramic matrix composites are under active consideration for use in a wide variety of high temperature applications within the aeronautics, energy, process, and nuclear industries. The engineering designs require fabrication and manufacturing of complex shaped parts. In many instances, it is more economical to build up complex shapes by Joining simple geometrical shapes. Thus, joining and attachment have been recognized as enabling technologies for successful utilization of ceramic components in various demanding applications. In this presentation, various challenges and opportunities in design, fabrication, and testing of high temperature joints in ceramic matrix composites will be presented. Various joint design philosophies and design issues in joining of composites will be discussed along with an affordable, robust ceramic joining technology (ARCJoinT). A wide variety of ceramic composites, in different shapes and sizes, have been joined using this technology. Microstructure and mechanical properties of joints will be reported. Current status of various ceramic joining technologies and future prospects for their applications will also be discussed.
Mrityunjay, Singh↗
Ion Thruster Power Levels Extended by a Factor of 10
In response to two NASA Office of Space Science initiatives, the NASA Glenn Research Center is now developing a 7-kW-class xenon ion thruster system for near-term solar-powered spacecraft and a 25-kW ion engine for nuclear-electric spacecraft. The 7-kW ion thruster and power processor can be throttled down to 1 kW and are applicable to 25-kW flagship missions to the outer planets, asteroids, and comets. This propulsion system was scaled up from the 2.5-kW ion thruster and power processor that was developed successfully by Glenn, Boeing, the Jet Propulsion Laboratory (JPL), and Spectrum Astro for the Deep Space 1 spacecraft. The 7-kW ion thruster system is being developed under NASA's Evolutionary Xenon Thruster (NEXT) project, which includes partners from JPL, Aerojet, Boeing, the University of Michigan, and Colorado State University.
Patterson, Michael J.↗