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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (6)
  • Clostridium botulinum
  • GEOPHYSICS
  • 1990-1994  (5)
  • 1985-1989  (3)
  • 1
    Electronic Resource
    Electronic Resource
    Genetic interrelationships of proteolyticClostridium botulinum types A, B, and F and other members of theClostridium botulinum complex as revealed by small-subunit rRNA gene sequences (1993)
    Springer
    Antonie van Leeuwenhoek 64 (1993), S. 273-283 
    Details
    ISSN: 1572-9699
    Keywords: 16S rRNA ; Clostridium botulinum ; phylogeny ; taxonomy
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology
    Notes: Abstract The phylogenetic interrelationships of members of theClostridium botulinum complex of species was investigated by direct sequencing of their 16S rRNA genes. Comparative analysis of the 16S rRNA sequences demonstrated the presence of four phylogenetically distinct lineages corresponding to: i) proteolyticC. botulinum types A, B, and F, andC. sporogenes, ii) saccharolytic types B, E and F, iii) types C and D andC. novyi type A, and iv) type G andC. subterminale. The phylogenetic groupings obtained from the 16S rRNA were in complete agreement with the four divisions recognised within the ‘species complex’ on the basis of phenotypic criteria.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00873087
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Space station (1986)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Space Station is being defined as a multi-purpose facility with emphasis in the following areas: scientific and technology research laboratory; permanent observatory; spacecraft servicing facility; construction and assembly facility; manufacturing facility; transportation node; and staging base for future space endeavors. The Station complex, in its initial operating capability configuration, includes a continuously habitable manned element, a polar orbiting unmanned platform, and a second unmanned platform co-orbiting with the manned element. All elements are dependent on the Space Transportation System (STS) for initial placement on-orbit and for subsequent logistical services. The manned element will be designed for long duration operations with systems maintainable on-orbit and operationally autonomous from ground control. A major feature of the Station will be its adaptability to evolutionary technology upgrades; and the Space Station, as a system, is to be designed for maximum ease of use by its users.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Lunar and Planetary Inst. IN Trajectory Determination and Collection of Micrometeoroids on the Space Station; p 83-84
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Active vehicle charging measurements in sounding rocket and space shuttle orbiter environments at Low Earth Orbit (LEO) altitude (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It was concluded that for electron beam emission up to 100mA, vehicle charging is not a significant problem with the Space Shuttle Orbiter. Similarly, sounding rocket payloads have no serious charging problems up to this level of beam current, provided that the maximum amount of the rocket skin is available to collect ionospheric electrons from the LEO altitude range. However, sounding rockets are marginal in their collecting area capability and other effects may occur to balance the beam current when operated at lower altitudes during the night.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, The Aerospace Environment at High Altitudes and its Implications for Spacecraft Charging and Communications; 16 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Recent observations of high voltage spacecraft-environment interaction at LEO altitudes using sounding rockets (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The paper addresses the subject of the interaction of positively and negatively charged bodies with the terrestrial ionosphere at low earth orbit altitudes. Data from two recent sounding rocket flights are used to establish that the current collected by exposed conductors biassed positively at up to 45kV relative to the ionospheric plasma generally follow predictions which account for strong control of electron flow by the geomagnetic field. If the biased structure is in the vicinity of disturbing influences such as an emitted charged particle beam, or locally enhanced gas pressure, then large deviations from the space-charge-limited return currents occur.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 90-0635
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    IR excitation of contaminant water by oxygen for the space shuttle at low Earth orbit altitude (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: As the water outgas of a space shuttle passes through the rarefied atmosphere at orbital altitude, collisions occur between the gases with sufficient energy to excite infrared-active water molecules to various vibrational and rotational states. An infrared contaminant model (IR model) has been developed to study the shuttle-induced excitation and emission of water molecules outgassed from the space shuttle. The focus of the first application of the model is translation-to-vibration (T-V) energy transfer since estimates suggest that this process should dominate the production of vibrationally excited H2O under typical low Earth orbit conditions. Using the velocity and position distribution functions of interacting neutral gases obtained from a neutral gases interaction model, the spatial distributions of excitation and IR radiation from contaminant water are computed, and typical results are presented. Infrared spectral data (450 - 2500/cm), measured by the Cryogenic Infrared Radiance Instrumentation for Shuttle (CIRRIS-1A) sensor on STS-39 (April 28 to May 6, 1991) at an altitude near 265 km, are used to test model predictions. The dependence of the radiant emission structure and brightness on outgassing rates and altitudes is discussed. The time history of the contaminant water outgassing rate is inferred for STS-39, and it is compared with the mass-spectrometer-based results for STS-4 (June 26 to July 4, 1982). Also, estimates of H2O column density at mission elapsed time (MET) 50 hours are compared for missions STS-2, STS-3, STS-4, and STS-39.
    Keywords: GEOPHYSICS
    Type: Journal of Geophysical Research (ISSN 0148-0227); 99; A10; p. 19,585-19,596
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Recent experimental measurements of space platform charging at LEO altitudes (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The paper discusses some of the results of vehicle electrical potential from recent sounding rocket experiments involving charging of a space platform by both electron beam emission and by the application of differential bias between elements of the platform. Conclusions are presented that are applicable to the experimental parameters of the CHARGE-2 and SPEAR-1 payloads. The currents collected by HV biased collectors in the sphere show strong magnetic limiting and are close to the values predicted by Parker and Murphy (1967). No volume breakdown was observed above 100 km altitude by exposing voltages up to 45 kV to the ionosphere in the SPEAR-1 payload. The release of gas at flow rates typical of ACS systems can provide sufficient plasma to electronically neutralize space platforms biased at either positive or negative potentials.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advances in Space Research (ISSN 0273-1177); 12; 12 D
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    TSS-1 - Orbiter current and voltage experiments (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Although the deployment distance of the TSS-1 tethered satellite was only about 1 percent of nominal, experiments to study the current collection and vehicle charging effects at low voltages were performed. We present measurements of Orbiter charging resulting from electron beam emission from the Orbiter, currents in the TSS system with and without electron beam emissions, and the effects of Orbiter thrusters on charging and currents. Generally, charging induced by beam emission was limited to a few volts, though during times with low ambient plasma density the Orbiter was charged up to 80 V. Thrusters are seen to enhance Orbiter charging during beam emission, and reduce ion current collection at other times.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 93-0702 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 10 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Plasma parameters in the near wake of the Space Shuttle (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Results are presented from a Spherical Retarding Potential Analyzer and a spherical Langmuir Probe which were flown on the Spacelab-2 mission of the Space Shuttle Orbiter in August 1985. The probes were mounted in such a position that for certain Orbiter orientations, the wake edge formed by the starboard payload bay sill swept across the probes at a roll rate of once per orbit about an inertially stabilized pointing direction. Profiles of O(+) number density and electron number density across the wake edge showed that the charge particle number densities declined into the wake at a faster rate than that predicted by theoretical models. At angles of more than 10 deg into the wake from its geometric edge, two electron populations are found, with different mean random energies and electrical potentials. One of these populations is suggested to be the result of selective filtering of the high energy tails of the ambient ionospheric population, the other, a result of photoemission from the payload bay surfaces.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Geophysical Research Letters (ISSN 0094-8276); 14; 359-362
    Format: text
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    NASA TECHNICAL REPORTS
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