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  • 1
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    Comparison of closed and open cycle systems (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Nuclear light bulb engine and coaxial flow, gaseous core reactor rocket
    Keywords: NUCLEAR ENGINEERING
    Type: FLORIDA UNIV. RES. ON URANIUM PLASMAS AND THEIR TECHNOL. APPL. 1971; P 3-11
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Propulsion for space - The nuclear rocket. (1967)
    In:  Other Sources
    Details
    Publication Date: 2011-08-11
    Description: Ground technology program for nuclear rocket development, discussing NERVA and KIWI programs
    Keywords: NUCLEAR ENGINEERING
    Type: TRW SPACE LOG
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Space Nuclear Propulsion Systems and Applications (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The basic principles of the operation of a nuclear rocket engine are reviewed along with a summary of the early history. In addition, the technology status in the nuclear rocket program for development of the flight-rated NERVA engine is described, and applications for this 75,000-pound thrust engine and the results of nuclear stage studies are presented. Advanced research and supporting technology activities in the nuclear rocket program are also summarized.
    Keywords: NUCLEAR ENGINEERING
    Type: NASA, Washington Proc. of the Natl. Symp. on Nat. and Manmade Radiation in Space; p 2-12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    NASA SBIR abstracts of 1990 phase 1 projects (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The research objectives of the 280 projects placed under contract in the National Aeronautics and Space Administration (NASA) 1990 Small Business Innovation Research (SBIR) Phase 1 program are described. The basic document consists of edited, non-proprietary abstracts of the winning proposals submitted by small businesses in response to NASA's 1990 SBIR Phase 1 Program Solicitation. The abstracts are presented under the 15 technical topics within which Phase 1 proposals were solicited. Each project was assigned a sequential identifying number from 001 to 280, in order of its appearance in the body of the report. The document also includes Appendixes to provide additional information about the SBIR program and permit cross-reference in the 1990 Phase 1 projects by company name, location by state, principal investigator, NASA field center responsible for management of each project, and NASA contract number.
    Keywords: ADMINISTRATION AND MANAGEMENT
    Type: NASA-TM-108145 , NASA-SBIR-PC-90 , NAS 1.15:108145
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Design Analysis of a Subsonic Nuclear Powered Logistic Airplane with Helium-Colled Reactor (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Subsonic nuclear powered logistic airplane with helium-cooled reactor
    Keywords: GENERAL
    Type: NASA-TM-X-28
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Considerations of nuclear power and propulsion. (1967)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Nuclear power and propulsion systems for space applications, discussing present and future technologies
    Keywords: NUCLEAR ENGINEERING
    Type: AAS PAPER 67-132
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Gaseous fuel reactors for power systems (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: The Los Alamos Scientific Laboratory is participating in a NASA-sponsored program to demonstrate the feasibility of a gaseous uranium fueled reactor. The work is aimed at acquiring experimental and theoretical information for the design of a prototype plasma core reactor which will test heat removal by optical radiation. The basic goal of this work is for space applications, however, other NASA-sponsored work suggests several attractive applications to help meet earth-bound energy needs. Such potential benefits are: small critical mass, on-site fuel processing, high fuel burnup, low fission fragment inventory in reactor core, high temperature for process heat, optical radiation for photochemistry and space power transmission, and high temperature for advanced propulsion systems.
    Keywords: NUCLEAR AND HIGH-ENERGY PHYSICS
    Type: Intersociety Energy Conversion Engineering Conference; Aug 20, 1978 - Aug 25, 1978; San Diego, CA
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    NASA TECHNICAL REPORTS
  • 8
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    Gaseous fuel nuclear reactor research (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Gaseous-fuel nuclear reactors are described; their distinguishing feature is the use of fissile fuels in a gaseous or plasma state, thereby breaking the barrier of temperature imposed by solid-fuel elements. This property creates a reactor heat source that may be able to heat the propellant of a rocket engine to 10,000 or 20,000 K. At this temperature level, gas-core reactors would provide the breakthrough in propulsion needed to open the entire solar system to manned and unmanned spacecraft. The possibility of fuel recycling makes possible efficiencies of up to 65% and nuclear safety at reduced cost, as well as high-thrust propulsion capabilities with specific impulse up to 5000 sec.
    Keywords: NUCLEAR AND HIGH-ENERGY PHYSICS
    Type: Energy - Engineering - Environment; Seventh Annual Frontiers of Power Technology Conference, Stillwater; Oct 09, 1974 - Oct 10, 1974; Stillwater, OK
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    NASA TECHNICAL REPORTS
  • 9
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    Physics and potentials of fissioning plasmas for space power and propulsion (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Fissioning uranium plasmas are the nuclear fuel in conceptual high-temperature gaseous-core reactors for advanced rocket propulsion in space. A gaseous-core nuclear rocket would be a thermal reactor in which an enriched uranium plasma at about 10,000 K is confined in a reflector-moderator cavity where it is nuclear critical and transfers its fission power to a confining propellant flow for the production of thrust at a specific impulse up to 5000 sec. With a thrust-to-engine weight ratio approaching unity, the gaseous-core nuclear rocket could provide for propulsion capabilities needed for manned missions to the nearby planets and for economical cislunar ferry services. Fueled with enriched uranium hexafluoride and operated at temperatures lower than needed for propulsion, the gaseous-core reactor scheme also offers significant benefits in applications for space and terrestrial power. They include high-efficiency power generation at low specific mass, the burnup of certain fission products and actinides, the breeding of U-233 from thorium with short doubling times, and improved convenience of fuel handling and processing in the gaseous phase.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica; 3; July-Aug
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    NASA TECHNICAL REPORTS
  • 10
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    Gaseous fuel reactor systems for aerospace applications (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: Research on the gaseous fuel nuclear rocket concept continues under the programs of the U.S. National Aeronautics and Space Administration (NASA) Office for Aeronautics and Space Technology and now includes work related to power applications in space and on earth. In a cavity reactor test series, initial experiments confirmed the low critical mass determined from reactor physics calculations. Recent work with flowing UF6 fuel indicates stable operation at increased power levels. Preliminary design and experimental verification of test hardware for high-temperature experiments have been accomplished. Research on energy extraction from fissioning gases has resulted in lasers energized by fission fragments. Combined experimental results and studies indicate that gaseous-fuel reactor systems have significant potential for providing nuclear fission power in space and on earth.
    Keywords: NUCLEAR AND HIGH-ENERGY PHYSICS
    Type: AIAA PAPER 77-513 , Conference on the Future of Aerospace Power Systems; Mar 01, 1977 - Mar 03, 1977; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
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