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  • 1
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    Tritiated thymidine incorporation does not measure DNA synthesis in ribavirin-treated human cells (1981)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 1981-05-01
    Description: When the incorporation of tritiated thymidine into acid insoluble material was measured, ribavirin appeared to be a potent inhibitor of DNA synthesis in KB cells and human lymphocytes. Inhibition was nearly 100-fold less, however, when DNA synthesis was measured by incorporation of phosphorus-32-labeled phosphate or by DNA fluorescence. The potent inhibition detected by incorporation of tritiated thymidine into DNA actually was the result of a potent effect on the labeling of deoxythymidine triphosphate, not on the synthesis of DNA.〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Drach, J C -- Thomas, M A -- Barnett, J W -- Smith, S H -- Shipman, C Jr -- DE 02731/DE/NIDCR NIH HHS/ -- New York, N.Y. -- Science. 1981 May 1;212(4494):549-51.〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/7209549" target="_blank"〉PubMed〈/a〉
    Keywords: Cells, Cultured ; DNA/*biosynthesis ; DNA Replication/*drug effects ; Humans ; Lymphocytes/metabolism ; Phosphates/metabolism ; Ribavirin/*pharmacology ; Ribonucleosides/*pharmacology ; Thymidine/*metabolism ; Thymine Nucleotides/biosynthesis
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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  • 2
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    Leukocyte migration inhibition assay of tumor immunity in patients with cervical squamous cell carcinoma (1979)
    Wiley
    Details
    Publication Date: 1979-06-01
    Print ISSN: 0008-543X
    Electronic ISSN: 1097-0142
    Topics: Biology , Medicine
    Published by Wiley on behalf of American Cancer Society.
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    PAPER CURRENT
  • 3
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    Onset phenomena in MPD thrusters (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental study has clarified some aspects of MPD thruster onset phenomena. The steep increase in terminal voltage that occurs as the onset current is approached may have different causes, depending on the propellant injection geometry. For propellant injection at the cathode radius, terminal voltage increase corresponds to a growing anode fall voltage; for injection at a larger radius, the increase is related to the back emf in the near-cathode plasma. The formation of the onset current pattern within the arc has been mapped experimentally as the thruster responds to an input current step which rises from below onset to the onset value. The appearance of terminal voltage hash at onset correlates with the extension into the exhaust region of a significant fraction of the arc current.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 85-2038
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    MPD thruster operation with stepped current input (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Experimental study of the response of a quasi-steady MPD thruster to an incremental increase or decrease in current illuminates the processes by which the discharge adjusts to changes in its operating level. For changes well below the onset condition, the thruster maintains quasi-steady operation throughout. Changes imposed near onset produce transition periods of non-quasi-steady operation. The duration of the transient appears to be determined by magnetic field diffusion in the portion of the discharge downstream of the thrust chamber.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: International Electric Propulsion Conference; May 28, 1984 - May 31, 1984; Tokyo; Japan
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The 30-kW ammonia arcjet technology (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The technical results are summarized of a 30 kW class ammonia propellant arcjet technology program. Evaluation of previous arcjet thruster performance, including materials analysis of used thruster components, led to the design of an arcjet with improved performance and thermal characteristics. Tests of the new engine demonstrated that engine performance is relatively insensitive to cathode tip geometry. Other data suggested a maximum sustainable arc length for a given thruster configuration, beyond which the arc may reconfigure in a destructive manner. A flow controller calibration error was identified. This error caused previously reported values of specific impulse and thrust efficiency to be 20 percent higher than the real values. Corrected arcjet performance data are given. Duration tests of 413 and 252 hours, and several tests 100 hours in duration, were performed. The cathode tip erosion rate increased with increasing arc current. Elimination of power source ripple did not affect cathode tip whisker growth. Results of arcjet modeling, diagnostic development and mission analyses are also discussed. The 30 kW ammonia arcjet may now be considered ready for development for a flight demonstration, but widespread application of 30 kW class arcjet will require improved efficiency and lifetime.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-186850 , NAS 1.26:186850 , JPL-PUBL-90-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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