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  • 1
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    Nuclear safety considerations in the conceptual design of a fast reactor for space electric power and propulsion (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Some nuclear safety aspects of a 3.2 mWt heat pipe cooled fast reactor with out-of-core thermionic converters are discussed. Safety related characteristics of the design including a thin layer of B4C surrounding the core, the use of heat pipes and BeO reflector assembly, the elimination of fuel element bowing, etc., are highlighted. Potential supercriticality hazards and countermeasures are considered. Impacts of some safety guidelines of space transportation system are also briefly discussed, since the currently developing space shuttle would be used as the primary launch vehicle for the nuclear electric propulsion spacecraft.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 77-492 , 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
  • 2
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    Nuclear thermionic power system for spacecraft (1976)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Mission studies have shown that nuclear electric propulsion is necessary for providing the needed propulsion system for detailed outer planet exploration. The study is centered around thermionic conversion based on an out-of-core approach employing heat pipes to thermally couple the nuclear reactor with the thermionic converters. Emphasis is on a parametric study to size a 500 kWe thermionic power conversion system suitable for a single shuttle launch. It is shown that out-of-core thermionic conversion results in a large L/D system that produces minimum weight. This evolving thermionic technology is compatible with developing insulator technology allowing operation at temperatures compatible with both molybdenum and insulators while retaining a sufficiently high heat rejection temperature to minimize radiator size and weight.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Conference on Intersociety Energy Conversion Engineering; Sep 12, 1976 - Sep 17, 1976; State Line, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Nuclear power source for electric propulsion (1979)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A low specific weight (20 to 40 Kg/Kwe), long life (6 to 10 year), 100 to 400 KWe nuclear electric propulsion (NEP) system can deliver 2,000 to 10,000 Kg payloads for intensive study of our solar system. The nuclear power source is about 80% of the NEP system mass, thus the NASA program is focused on developing the power source technology. Because of the long life requirements, direct thermal to electric energy conversion technology (thermionic and thermoelectric) is being pursued. In order to meet the low specific weight it is necessary to develop a 10 to 15% conversion module with a 875 K minimum heat rejection temperature and a 1675 K maximum input temperature. The thermoionic converter is about 9% efficient at these temperatures. The thermoelectric converter is limited to a 1300 K input temperature. So, the thermionic program is focused on improving the efficiency while the thermoelectric program is focused on increasing the temperature.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-2088 , International Electric Propulsion Conference; Oct 30, 1979 - Nov 01, 1979; Princeton, NJ
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    An improved thermionic power conversion system for space propulsion (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A concept of an out-of-core thermionic nuclear electric power conversion system for 400 Kwe power level is being investigated for space propulsion applications. Two key features distinguish the power system design from previous thermionic power conversion concepts. First, the thermionic converters are located outside a nuclear reactor with a neutron shield inserted to reduce the radiation level on the thermionic converter matrix. Second, multiple liquid-metal heat pipes are used exclusively for both thermal power transport (from the nuclear reactor to the thermionic converters) and waste heat removal (from the thermionic converters to the space radiator); no mechanical or electromagnetic pumps are involved. The system characteristics are are compared to those of the in-core thermionic reactor system concept. In many aspects, the system characteristics, including specific weight, lifetime, dynamics control and safety features are found to be more desirable than those of the in-core system concept.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Intersociety Energy Conversion Engineering Conference; Aug 20, 1978 - Aug 25, 1978; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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