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  • 1
    Publication Date: 2015-04-21
    Description: Insulinomas cause neuroglycopenic symptoms, permanent neurological damage and even death. Current available therapies cannot satisfactorily treat malignant insulinomas and some benign insulinomas. The promising phototherapeutic results and harmless side effects of hypericin in some cancer treatments prompted us to explore possible antigrowth activity of photoactivated hypericin against RINm5F insulinoma cells and underlying mechanisms. We now show that detectable and maximal internalization of hypericin in RINm5F insulinoma cells occurred in 20 and 60 min, respectively. Hypericin was considerably associated with the plasma membrane, appreciably localized in the subplasma membrane region and substantially accumulated in the cytoplasm. Photoactivated hypericin decreased the viability of RINm5F insulinoma cells due to its antiproliferative and apoptotic actions. Photoactivation of hypericin inhibited cell proliferation reflected by decreased expression of the proliferation marker Ki-67 and cell-cycle arrest in the G0/G1 phase. The antiproliferative effect resulted from downregulation of phosphorylation of JNK and ERK. Photoactivated hypericin triggered apoptosis through activation of caspase-3 and caspase-9 and elevation of the Bax-to-Bcl-2 ratio.The findings lay a solid foundation for implementation of hypericin-mediated photodynamic therapy in treatment of insulinomas.
    Print ISSN: 0144-8463
    Electronic ISSN: 1573-4935
    Topics: Biology , Chemistry and Pharmacology
    Published by Portland Press
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  • 2
    ISSN: 0168-583X
    Source: Elsevier Journal Backfiles on ScienceDirect 1907 - 2002
    Topics: Physics
    Type of Medium: Electronic Resource
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  • 3
    Publication Date: 2019-01-25
    Description: Uranium-containing materials, refractory metals and alloys, discussing interface interaction, thermionic properties and parameters of vacuum electron emission stability
    Keywords: NUCLEAR ENGINEERING
    Format: text
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  • 4
    Publication Date: 2018-12-01
    Description: The dimensions of aerobrakes and associated heat shields are calculated as a fraction of the vehicle mass required for a high-velocity manned Mars entry. The entry speed and deceleration limit are assumed to be 8.6 km/sec and 5 earth g, respectively, to consider vehicles with low lift-drag ratio (L/D) and ballistic coefficients of 100 and 200 kg/sq m, as well as a vehicle with a medium L/D and a ballistic coefficient of 375 kg/sq m. The aerobrake mass plus the heat shield divided by an optimized, blunt-shaped vehicle's total mass is 15 and 13 percent for ballistic coefficients of 100 and 200 kg/sq m, respectively. For a winged vehicle the mass fraction is 17 percent because the higher ballistic coefficient requires more thermal protection to account for the greater temperatures generated. It is concluded that aerobraking is more efficient than propulsive braking because the mass fraction for a propulsive system would be 4 or 5 times greater than those calculated for aerobraking.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 91-1344
    Format: text
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  • 5
    Publication Date: 2011-08-24
    Description: Analytic expressions have been derived for estimating the nonablating laminar and turbulent boundary-layer convective heating rates on inclined flat surfaces for the Martian atmosphere in thermochemical equilibrium. The equations are valid in the speed and altitude regime where aerobraking would occur at Mars. Comparisons with limited experimental measurements and calculations for CO2 (the Martian atmosphere is 95.6 percent CO2) yielded reasonably good agreement, especially for the ratios of heating rates in CO2 to those in air at the same conditions. In the aerobraking speed regime, the laminar flat surface boundary layer heating rates are 15-25 percent greater at Mars than in air. The differences between the turbulent heating rates are even more pronounced. The turbulent heating rates can be over 50 percent greater at Mars than in air at the same flight conditions.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 30; 2; p. 164-169.
    Format: text
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  • 6
    Publication Date: 2013-08-31
    Description: The space shuttle orbiter experiments program is responsible for collecting flight data to extend the research and technology base for future aerospace vehicle design. The infrared imagery of shuttle (IRIS), catalytic surface effects, and tile gap heating experiments sponsored by Ames Research Center are part of this program. The software required to process the flight data which support these experiments is described. In addition, data analysis techniques, developed in support of the IRIS experiment, are discussed. Using the flight data base, the techniques provide information useful in analyzing and correcting problems with the experiment, and in interpreting the IRIS image obtained during the entry of the third shuttle mission.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: A-9289 , NASA-TM-84345 , NAS 1.15:84345
    Format: application/pdf
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  • 7
    Publication Date: 2013-08-31
    Description: An efficient method for detecting carbon fibers collected on a stick tape monitor was developed. The fibers were released from a simulated crash fire situation containing carbon fiber composite material. The method utilized the ability of the fiber to initiate a spark across a set of alternately biased high voltage electrodes to electronically count the number of fiber fragments collected on the tape. It was found that the spark, which contains high energy and is of very short duration, is capable of partially damaging or consuming the fiber fragments. It also creates a mechanical disturbance which ejects the fiber from the grid. Both characteristics were helpful in establishing a single discharge pulse for each fiber segment.
    Keywords: ENVIRONMENT POLLUTION
    Type: NASA-CR-163747 , JPL-PUB-80-55
    Format: application/pdf
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  • 8
    Publication Date: 2016-03-09
    Description: An apparatus and method for destructively removing particles from a flowing gas containing the particles is described. In the specific embodiments disclosed the apparatus is adapted to remove carbon particles from diesel engine exhaust products. The exhaust products are directed to a predetermined location where they are rapidly vaporized and combine with oxygen in the exhaust products to form carbon dioxide. Vaporization in one embodiment is effected by a discharge grid located within an exhaust conduit, the grid being chosen so that alternate conductors defining the grid are spaced apart a distance approximately 125 times the mean diameter of the particles to be removed. A voltage differential of approximately 690 volts is applied across adjacent conductors.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: application/pdf
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  • 9
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    In:  CASI
    Publication Date: 2016-03-08
    Description: Apparatus for generating a substantially oscillation-free seismic signal for use in underwater petroleum exploration, including a bag with walls that are flexible but substantially inelastic, and a pressured gas supply for rapidly expanding the bag to its fully expanded condition is described. The inelasticity of the bag permits the application of high pressure gas to rapidly expand it to full size, without requiring a venting mechanism to decrease the pressure as the bag approaches a predetermined size to avoid breaking of the bag.
    Keywords: GEOPHYSICS
    Format: application/pdf
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  • 10
    Publication Date: 2014-09-12
    Description: Thermionic reactor power systems are discussed with respect to their suitability for space missions. The technology status of thermionic emitters and sheath insulator assemblies is described along with testing of the thermionic fuel elements.
    Keywords: NUCLEAR AND HIGH-ENERGY PHYSICS
    Type: NASA. Lewis Research Center Space Power; p 157-169
    Format: text
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