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  • SPACECRAFT PROPULSION AND POWER  (3)
  • decatenation  (1)
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  • 1
    ISSN: 0730-2312
    Keywords: DNase II ; decatenation ; in situ nuclear matrix ; mitotic chromosomes ; VP-16 ; RNP ; Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Chemistry and Pharmacology , Medicine
    Notes: Topo IIα is considered an important constituent of the nuclear matrix, serving as a fastener of DNA loops to the underlying filamentous scaffolding network. To further define a mechanism of drug resistance to topo II poisons, we studied the quantity of topo IIα associated with the nuclear matrix in drug-resistant SMR16 and parental cells in the presence and absence of VP-16. Nuclear matrices were prepared from nuclei isolated in EDTA buffer, followed by nuclease digestion with DNase II in the absence of RNase treatment and extraction with 2 M NaCl. Whole-mount spreading of residual structures permits, by means of isoform-specific antibody and colloidal-gold secondary antibodies, an estimate of the amount of topo IIα in individual nuclear matrices. There are significant variations in topo IIα amounts between individual nuclear matrices due to the cell cycle distribution. The parental cell line contained eight to ten times more nuclear matrix-associated topo IIα than the resistant cell line matrices. Nuclear matrix-associated topo IIα from wild-type and resistant cell lines correlated well with the immunofluorescent staining of the enzyme in nuclei of intact cells. The amount of DNA associated with residual nuclear structures was five times greater in the resistant cell line. This quantity of DNA was not proportional to the quantity of topo IIα in the same matrix; in fact they were inversely related. In situ whole-mount nuclear matrix preparations were obtained from cells grown on grids and confirmed the results from labeling of isolated residual structures. J. Cell. Biochem. 67:112-130, 1997. © 1997 Wiley-Liss, Inc.
    Additional Material: 8 Ill.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2019-06-28
    Description: The Hybrid Plume Plasma Rocket (HPPR) is a high power electric propulsion concept which is being developed at the MIT Plasma Fusion Center. This paper presents a theoretical overview of the concept as well as the results and conclusions of an independent study which has been conducted to identify and categorize those technologies which require significant development before the HPPR can be considered a viable electric propulsion device. It has been determined that the technologies which require the most development are high power radio-frequency and microwave generation for space applications and the associated power processing units, low mass superconducting magnets, a reliable, long duration, multi-megawatt space nuclear power source, and long term storage of liquid hydrogen propellant. In addition to this, a mission analysis of a one-way transfer from low earth orbit (LEO) to Mars indicates that a constant acceleration thrust profile, which can be obtained using the HPPR, results in faster trip times and greater payload capacities than those afforded by more conventional constant thrust profiles.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-2599
    Format: text
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  • 3
    Publication Date: 2019-07-13
    Description: Results are reported from preliminary tests to evaluate the high power microwave electrothermal thruster concept, which employs a free-floating plasma discharge maintained by applied CW microwave power to heat a propellant gas flow. Stable plasmas have been created and maintained in He, N2, and H2 as propellants in both the TM(sub 011) and TM(sub 012) modes at discharge pressures from 10 Pa to 69 kPa. Vortical inflow of the propellant gas was observed to cause the formation of on-axis 'spike' plasmas. Operation in the spike plasma condition yields maximum power absorption with minimum wall heating and maximum propellant-heating efficiency; plasmas of the three propellant gases were investigated in the spike condition in an open channel to a maximum applied power level of 11.2 kW (in N2). Microwave power coupling efficiencies of over 90 percent were routinely obtained at absorbed power levels up to 2 kW. Magnetic nozzle effects were investigated with a superconducting solenoid Al magnet applying a high magnetic field to the plasmas in, and exiting from, the discharge tube.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 93-2106 , ; 18 p.|AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States
    Format: text
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  • 4
    Publication Date: 2019-07-13
    Description: Results are reported from preliminary tests to evaluate the high power microwave electrothermal thruster (MET) concept, which employs a free-floating plasma discharge maintained by applied CW microwave power to heat a propellant gas flow. Stable plasmas have been created and maintained in helium (He), nitrogen (N2), and hydrogen (H2) as propellants in both the TM(sub 011) and TM(sub 012) modes at discharge pressures from 10 Pa to 69 kPa. Reproducible starting conditions of pressure and power have been documented for all the plasmas. Vortical inflow of the propellant gas was observed to cause the formation of on-axis 'spike' plasmas. The formation and unformation conditions of these plasmas were studied. Operation in the spike plasma condition enables maximum power absorption with minimum wall heating and offers maximum efficiency in heating the propellant gas. In the spike condition, plasmas of the three propellant gases were investigated in an open channel configuration to a maximum applied power level of 11.2 kW (in N2). Microwave power coupling efficiencies of over 90 percent were routinely obtained at absorbed power levels up to 2 kW. Magnetic nozzle effects were investigated with a superconducting solenoid Al magnet applying a high magnetic field to the plasmas in and exiting from the discharge tube.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-106207 , E-7917 , NAS 1.15:106207 , AIAA PAPER 93-2106 , Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States
    Format: application/pdf
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