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  • 1
    ISSN: 1744-313X
    Source: Blackwell Publishing Journal Backfiles 1879-2005
    Topics: Biology , Medicine
    Notes: Mouse strains differ widely in their natural killer(NK)-cell activity. In the (A X B6) X A backcross, high reactivity was linked to H-2b, although non-H-2-linked genes were also demonstrated (Petranyi et al., 1975). Harmon et al. (1977) demonstrated an H-2Dd-associated reactivity gene (1977). In the present study, we have tested eleven B10 congenic strains for NK activity. The H-2Dd strains B10.A, B10.T(6R), B10.S(7R), B10.HTT and B10.D2 were more highly reactive than B10, B10.S, B10.G, B10.A(2R) and B10.BR, which do not carry the d allele at the H-2D locus. While this confirms the H-2Dd association of a reactivity gene, an exception was found in the B10.A(5R) strain that was low reactive in spite of the fact that it carries H-2Dd. This suggests the possibility that the H-2Dd-associated gene is outside H-2, to the right of Tla.The AKR.H-2b congenic line had the same low activity as the AKR.H-2k strain; both were much lower than B6. This suggests either one of two possibilities: the H-2b-linked reactivity gene is relatively distant from the H-2 complex, although localized on chromosome 17 or alternatively, if localized within or in the close neighbourhood of H-2, it requires non-H-2 genes for full expression.Previously, we have shown that the B6 X DBA/2 F1 hybrid was more highly reactive than either one of its two parental strains (Klein et al., 1978). A similar complementation effect is described in the present paper for the B10.D2 congenic strain. The high reactivity of this line can be due to the combined effect of an H-2b-linked gene from DBA/2 and the non-H-2 background of B10 or, alternatively, the former, together with an H-2b-linked gene from B6 that lies well outside outside the H-2 locus itself.
    Type of Medium: Electronic Resource
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  • 2
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    In:  Other Sources
    Publication Date: 2018-12-01
    Description: The system integration issues associated with the design of Rovers for Mars ground surface operations are addressed in this paper. Requirements are established for both long distance traverse between geology sites and for geologic survey operations. To satisfy these mission requirements, a semi-autonomous vehicle design has been proposed and its performance capabilities are assessed. Furthermore, the mobility, power consumption, coordination and control (maneuverability), and reliability issues associated with the design of mobility systems to permit vehicle traverse over rugged terrain are examined and the direction of future work required to address these issues is outlined.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: AIAA PAPER 86-1198
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  • 3
    Publication Date: 2013-08-31
    Description: Halon 1301 which is a halocarbon fire extinguishing agent (CBrF3) used by the U.S. Army for vehicle fire suppression is discussed. Halon 1301 is discharged under nitrogen pressure, and the Halon-nitrogen mixture is a two phase, two component mixture that obeys compressible fluid laws and exhibits choking effects. A computer model was developed to analyze the discharge of Halon and nitrogen from a storage bottle through pipes and nozzles. The model agrees well with data from Halon 1301 discharge tests. The discharge time depends mainly on nozzle area and pipe volume, for given initial conditions. Graphs were developed for estimating discharge times. A nozzle employing multiple concentric converging/diverging nozzles was developed which gave hemispherical coverage.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-CR-174271 , JPL-PUBL-84-62 , NAS 1.26:174271
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  • 4
    Publication Date: 2016-03-08
    Keywords: AEROSPACE MEDICINE
    Type: Life Sci. Publ., Vol. 1; 2 p
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  • 5
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    In:  CASI
    Publication Date: 2016-06-07
    Description: Recent NASA and DOD mission models have indicated future needs for orbital cryogenic storage and supply systems. Two thermal control systems which show the greatest promise for improving propellant storage life were evaluated. One system was an open cycle thermodynamic vent type with a refrigeration system for partial hydrogen reliquefaction located at the LH2 tank and a vapor cooled shield for integrated and non-integrated tank designs to reduce boiloff. The other was a closed system with direct refrigeration at the LH2 tank. A reversed Brayton cycle unit was baselined for the propellant processor. It is concluded that: (1) reliquefaction systems are not attractive for minimizing propellant boiloff; (2) open cycle systems may not be economically attractive for long term storage; (3) a number of refrigeration systems are available to assist in the long term storage of cryogenic propellants; and (4) shields can significantly improve the performance of mechanical coolers.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA. Lewis Research Center OTV Propulsion Issues; p 165-177
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  • 6
    Publication Date: 2017-10-02
    Description: Inertial fusion can be used to power spacecraft within the solar system and beyond. Such spacecraft have the potential for short-duration manned-mission performance exceeding other technologies. We are conducting a study to assess the systems aspects of inertial fusion as applied to such missions, based on the conceptual engine design of Hyde (1983) we describe the required systems for an entirely new spacecraft design called VISTA that is based on the use of DT fuel. We give preliminary design details for the power conversion and power conditioning systems for manned missions to Mars of total duration of about 100 days. Specific mission performance results will be published elsewhere, after the study has been completed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: CONF-870102-29-REV-1 , DE87-014342 , NASA-TM-89661 , NAS 1.15:89661 , UCRL-95275-REV-1
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  • 7
    Publication Date: 2017-08-09
    Description: This study was performed to investigate gas formation and gas saturation conditions related to acoustic turbidity in shallow (∼40 m deep) marine basins. The Arkona Basin, Baltic Sea, with its organic-rich fine-grained surface sediment provides an ideal “Natural Laboratory” to characterise free gas using seismic, geoacoustic, and geochemical methods. The area of acoustic turbidity covers about 1500 km2 of the central Arkona Basin, corresponding to areas where organic-rich post-glacial sediments exceed 4–6 m in thickness. The highest concentration of pore water methane (7660 μmol L−1), found in areas of high acoustic turbidity, was near the calculated lower limit of methane solubility for the measured in situ temperature, salinity, and pressure. Pore water methane concentration decreased to near 4 μmol L−1 in areas outside of the zone of high acoustic turbidity. Stable carbon (−70.7‰ to −92.3‰ PDB) and hydrogen (−124‰ to −185‰ SMOW) isotope values of methane indicate that methane is predominantly formed by microbial CO2 reduction in Arkona Basin surface sediments and rules out significant contributions of other sources.
    Type: Article , PeerReviewed
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  • 8
    Publication Date: 2005-04-13
    Description: This presentation will outline a proposed mission for the Jupiter Icy Moons Orbiter (JIMO). The mission outlined will concentrate on an examination of Europa. Some of the primary science goals for the JIMO mission are: 1) to answer broad science questions, 2) improved knowledge of Jovian system; specifically, lunar geological and geophysical properties, 3) chemical composition of Jovian lunar surfaces and subterranean matter, and 4) the search for life. In order to address these issues, the experiment proposed here will deploy orbiting, surface, and subterranean science platforms.
    Keywords: Lunar and Planetary Science and Exploration
    Type: Forum on Concepts and Approaches for Jupiter Icy Moons Orbiter; 30; LPI-Contrib-1163
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  • 9
    Publication Date: 2011-08-16
    Description: An electron microscope examination was carried out on the lungs of 11 pocket mice (Perognathus longimembris) that breathed oxygen at 10 psi or 12 psi partial pressure over a period of 7 d, at the end of which time they were decompressed to sea-level O2 pressure, either suddenly or in 30, 60, or 90 min. Vesiculation was noted in the endothelium of the alveolar-capillary wall in most of the animals and, occasionally, blebbing. Some mitochrondria were swollen in a few of the animals. Alveolar exudate was, in general, sparse. Compared with the lungs of other rodents, the lungs of pocket mice appeared relatively resistant to the toxic effects of oxygen. This conclusion needs, however, to be tempered by the fact that 5% N2 was used in the tests reported here. Nonetheless, the results suggest that the oxygen pressures anticipated on the flight of Apollo XVII should be well tolerated by the pocket mice.
    Keywords: LIFE SCIENCES (GENERAL)
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  • 10
    Publication Date: 2011-08-19
    Description: This paper addresses issues that should receive further examination in the near-term as concept selection for development of a U.S. space reactor power system is approached. The issues include: the economics, practicality and system reliability associated with transfer of nuclear spacecraft from low earth shuttle orbits to operational orbits, via chemical propulsion versus nuclear electric propulsion; possible astronaut supervised reactor and nuclear electric propulsion startup in low altitude Shuttle orbit; potential deployment methods for nuclear powered spacecraft from Shuttle; the general public safety of low altitude startup and nuclear safe and disposal orbits; the question of preferred reactor power level; and the question of frozen versus molten alkali metal coolant during launch and deployment. These issues must be considered now because they impact the SP-100 concept selection, power level selection, weight and size limits, use of deployable radiators, reliability requirements, and economics, as well as the degree of need for and the urgency of developing space reactor power systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
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