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  • 1
    Electronic Resource
    Electronic Resource
    Two-step laser-assisted ionization of sodium in a hydrogen-oxygen-argon flame (1981)
    s.l. : American Chemical Society
    Analytical chemistry 53 (1981), S. 1275-1279 
    Details
    ISSN: 1520-6882
    Source: ACS Legacy Archives
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1021/ac00231a031
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Development of arcjet and ion propulsion for spacecraft stationkeeping (1993)
    Elsevier
    Details
    Publication Date: 1993-07-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    Electric propulsion: An evolutionary technology (1993)
    Elsevier
    Details
    Publication Date: 1993-09-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 4
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    Electric propulsion - An evolutionary technology (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 29; 9; p. 651-665.
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Extended life and performance test of a low-power arcjet (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 4; p. 444-452.
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    NASA spacecraft propulsion activities (1997)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The NASA's activities in the development of spacecraft propulsion systems are reviewed, with emphasis on program directions and recent progress made in this domain. The recent trends towards the use of smaller spacecraft and launch vehicles call for new onboard propulsion systems. The NASA's efforts are conducted within the framework of the onboard propulsion program. The research and development work carried out in relation to the different propulsion system technologies are considered: electromagnetic systems; electrostatic systems; electrothermal systems; bipropellant systems; and monopropellant systems.
    Keywords: Spacecraft Propulsion and Power
    Type: ; 35-44
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Electric propulsion: An evolutionary technology (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The NASA Lewis Research Center (LeRC) conducts and directs an electric propulsion research and technology program aimed at providing high-performance electric propulsion system options for a broad range of near and far-term missions. This evolutionary program emphasizes the development of propulsion systems for three classes of missions: (1) near term auxiliary propulsion applications such as North-South Stationkeeping for next generation communications satellites and orbit maintainence for orbiting platforms such as Space Station Freedom; (2) advanced solar electric propulsion and SP-100-class nuclear electric propulsion for Earth-space orbit transfer and robotic planetary missions; and (3) very high power systems to support major space missions including the Space Exploration Initiative. To cover widely disparate mission requirements, the LeRC program includes research on electrothermal, electrostatic, and electromagnetic systems. This paper provides an overview of the LeRC program with a focus on recent progress.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 29; 9; p. 651-665
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Arcjet Nozzle Area Ratio Effects (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An experimental investigation was conducted to determine the effect of nozzle area ratio on the operating characteristics and performance of a low power dc arcjet thruster. Conical thoriated tungsten nozzle inserts were tested in a modular laboratory arcjet thruster run on hydrogen/nitrogen mixtures simulating the decomposition products of hydrazine. The converging and diverging sides of the inserts had half angles of 30 and 20 degrees, respectively, similar to a flight type unit currently under development. The length of the diverging side was varied to change the area ratio. The nozzle inserts were run over a wide range of specific power. Current, voltage, mass flow rate, and thrust were monitored to provide accurate comparisons between tests. While small differences in performance were observed between the two nozzle inserts, it was determined that for each nozzle insert, arcjet performance improved with increasing nozzle area ratio to the highest area ratio tested and that the losses become very pronounced for area ratios below 50. These trends are somewhat different than those obtained in previous experimental and analytical studies of low Re number nozzles. It appears that arcjet performance can be enhanced via area ratio optimization.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1990 JANNAF Propulsion Meeting, Volume 2; p 407-416
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Arcjet Cathode Phenomena (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Cathode tips made from a number of different materials were tested in a modular arcjet thruster in order to examine cathode phenomena. Periodic disassembly and examination, along with the data collected during testing, indicated that all of the tungsten-based materials behaved similarly despite the fact that in one of these samples the percentage of thorium oxide was doubled and another was 25 percent rhenium. The mass loss rate from a 2 percent thoriated rhenium cathode was found to be an order of magnitude greater than that observed using 2 percent thoriated tungsten. Detailed analysis of one of these cathode tips showed that the molten crater contained pure tungsten to a depth of about 150 microns. Problems with thermal stress cracking were encountered in the testing of a hafnium carbide tip. Post test analysis showed that the active area of the tip had chemically reacted with the propellant. A 100 hour continuous test was run at about 1 kW. Post test analysis revealed no dendrite formation, such as observed in a 30 kW arcjet lifetest, near the cathode crater. The cathodes from both this test and a previously run 1000 hour cycled test displayed nearly identical arc craters. Data and calculations indicate that the mass losses observed in testing can be explained by evaporation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 349-366
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Arcjet Nozzle Design Impacts (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The effect of nozzle configuration on the operating characteristics of a low power dc arcjet thruster was determined. A conical nozzle with a 30 deg converging angle, a 20 deg diverging angle, and an area ratio of 225 served as the baseline case. Variations on the geometry included bell-shaped contours both up and downstream, and a downstream trumpet-shaped contour. The nozzles were operated over a range of specific power near that anticipated for on-orbit operation. Mass flow rate, thrust, current, and voltage were monitored to provide accurate comparisons between nozzles. The upstream contour was found to have minimal effect on arcjet operation. It was determined that the contour of the divergent section of the nozzle, that serves as the anode, was very important in determining the location of arc attachment, and thus had a significant impact on arcjet performance. The conical nozzle was judged to have the optimal current/voltage characteristics and produced the best performance of the nozzles tested.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 367-380
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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