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  • FTIR  (1)
  • SPACECRAFT PROPULSION AND POWER  (1)
  • 1
    Electronic Resource
    Electronic Resource
    Springer
    International journal of thermophysics 11 (1990), S. 119-132 
    ISSN: 1572-9567
    Keywords: entrainer ; FTIR ; hydrogen bonding ; supercritical
    Source: Springer Online Journal Archives 1860-2000
    Topics: Physics
    Notes: Abstract In chemical separation processes such as supercritical extraction the use of an entrainer cosolvent can dramatically improve selectivity and yield. Ideally, in an extraction process, an entrainer cosolvent should complex with only the desired solute, pulling it from the feed. But not all cosolvents are entrainers, and a cosolvent that is effective in one application may not be effective in others. Often, competing hydrogen bonding interactions limit the effectiveness of an entrainer cosolvent. In this paper FTIR spectroscopy is used to study hydrogen bonding competition in solute/solvent/entrainer cosolvent mixtures. The extent of hydrogen bonding is determined from analysis of hydrogen-bonded and non-hydrogen-bonded infrared absorption peaks. Since these peaks overlap, curvefitting and Fourier self-deconvolution techniques are used to resolve them. Concentrations of monomeric and hydrogen-bonded species are modeled using the associated perturbed anisotropic chain theory (APACT). Using APACT it is shown that the equilibrium constant, derived from activities, can be written as the product of a temperature-dependent term and the ratio of concentrations: K=(RT) vIIC i vi . This gives a statistical mechanical basis for the empirical observation that for hydrogen-bonding equilibria, the ratio of concentrations is approximately equal to the ratio of activities.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2019-07-13
    Description: Thermal control concepts for the square and the heliogyro solar sail designs under consideration for a Halley's Comet rendezvous mission are presented. The mission, involving a 1982 launch, navigation to a 0.25-AU cranking orbit about the sun in order to develop a retrograde orbit, and rendezvous with the comet in 1986, would subject surfaces of the sail vehicle to solar constant values ranging from 16 to 0.1. A highly reflective coating to produce propulsive force is needed for one surface of the sail, while the other surface requires a highly emittive coating. The problem of maintaining the sail wrinkle-free is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-885 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
    Format: text
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