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  • SPACECRAFT PROPULSION AND POWER  (3)
  • Antifungal Agents  (1)
  • 1975-1979  (4)
  • 1
    Electronic Resource
    Electronic Resource
    Determination of the minimal inhibitory concentration of Amphotericin B and Miconazole for 21 strains of Aspergillus (1978)
    Springer
    Mycopathologia 64 (1978), S. 147-151 
    Details
    ISSN: 1573-0832
    Keywords: Amphotericin B ; Antifungal Agents ; Aspergillus ; Aspergillosis
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology , Medicine
    Notes: Abstract The susceptibility of 21 strains ofAspergillus (11 ofA. fumigatus, 8 ofA. niger, and 2 ofA. flavus) isolated from human pathologic specimens to Amphotericin B and Miconazole has been comparatively studied. Determination of the minimal inhibitory concentration of both drugs in a liquid medium showed a noticeably variability for the different strains. The values obtained for Amphotericin B varied between 0.25μg/ml (2 strains) and 1.25μg/ml (5 strains) after 48 hours, and between 1.25μg/ml (1 strain) and 50μg/ml (1 strain) after 10 days. For Miconazole the results varied between 0.1μg/ml (1 strain) and 25μg/ml (1 strain) after 48 hours of incubation, and between 0.5μg/ml (5 strains) and 〉 100μg/ml after 10 days. The variability of these results indicates the usefulness of carrying ourin vitro sensitivity studies whenever it is possible.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00576365
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Unknown
    Linear rocket engines for advanced space transportation systems (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The linear rocket engine is shown to be a viable candidate propulsion system for post-Space Shuttle single-stage-to-orbit systems. The linear engine system has been developed and fired demonstrating high performance and long life with firing durations exceeding 500 seconds. The application of the split or dual combustor to the linear engine permits the uses of two different propellant combinations in a single engine system. The split combustor possesses the advantages of the two position extendible bell nozzle in a fixed nozzle configuration. Engine power cycles and applications to typical vehicles are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1251
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Linear aerospike engine (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A description is presented of a dual-fuel modular split-combustor linear aerospike engine concept. The considered engine represents an approach to an integrated engine for a reusable single-stage-to-orbit (SSTO) vehicle. The engine burns two fuels (hydrogen and a hydrocarbon) with oxygen in separate combustors. Combustion gases expand on a linear aerospike nozzle. An engine preliminary design is discussed. Attention is given to the evaluation process for selecting the optimum number of modules or divisions of the engine, aspects of cooling and power cycle balance, and details of engine operation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 77-968 , Propulsion Conference; Jul 11, 1977 - Jul 13, 1977; Orlando, FL; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Orbital transfer vehicle advanced expander cycle engine point design study (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed computer model of the expander cycle engine system steady-state operation was developed. Payload performance data for the expander cycle engine for 100K pounds and 65K pounds Space Shuttle missions were examined to establish peak payload thrusts. It was found that peak payload for the 100K pound gross weight single engine case occurred at nearly 15,000 pounds thrust for both engine mixture ratios of 6:1 and 7:1. Peak payload at engine mixture ratio of 6:1 was 4 percent greater than at 7:1 mixture ratio. The two engine configuration peak paYloads occurred at engine thrust below 7,500 pounds (extrapolated) and were lower than single engine payloads. For the 65K pound gross weight mission, peak payloads for the single engine configuration occurred at nearly 10,000 pounds for both mixture ratios. Mixture ratio of 7:1 payloads were 5 percent lower than 6:1 payloads. Two engine configuration payloads occurred at engine thrusts considerably below 10K pounds.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161318 , ASR79-109 , BMPR-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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