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  • PROPELLANTS AND FUELS  (2)
  • Chemistry  (1)
  • 1980-1984  (3)
  • 1
    Electronic Resource
    Electronic Resource
    Chichester [u.a.] : Wiley-Blackwell
    Surface and Interface Analysis 3 (1981), S. 110-117 
    ISSN: 0142-2421
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Physics
    Notes: The corrosion behaviour of orthopaedic metal implants was studied in an animal experiment in which 30 rabbits had stainless steel plates implanted after a varization osteotomy of the tibiae of their hind legs for one year. ESCA was used for the investigation of the surfaces of the inplants. The removed plates were covered by an easily destroyable 3-5 nm thick oxidic layer which contained Cr(III), Fe(II), Fe(III), Mo(VI) and Mo(IV), but no Ni. This passive layer (and possibly also the nearest metal layer below it) is strongly enriched in Cr. Additionally, corrosion experiments with radioactivated implants in Ringer's solution demonstrated that the passivation of the stainless steel is accompanied by marked selective solution of the steel constituents. The observed solubilities (Co 〉 Ni 〉 Fe 〉 Mo 〉 Cr) are inversely correlated with the abundance of the respective element in the passive layer. The trace element composition of the tissues was measured by instrumental neutron activation analysis. It turned out that the actual burdening of the tissues surrounding the implants by corrosion products is exhibited by strong enrichments of the elements Cr, Fe, Co, Ni and Mo relative to their normal concentrations. While Cr, Co, Ni and Mo are abundant in fairly constant ratios in the contact tissues, the excess of Fe is influenced by biological regulation mechanisms. The extent to which the distribution patterns of steel-specific elements in animal (and human) tissues can be explained by the dissolution of the steel during the passivation process is discussed.
    Additional Material: 6 Ill.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2019-06-28
    Description: A program to evaluate liquid oxygen and various hydrocarbon fuel as low cost alternative propellants suitable for future space transportation system applications is discussed. The emphasis of the program is directed toward low earth orbit maneuvering engine and reaction control engine systems. The feasibility of regeneratively cooling an orbit maneuvering thruster was analytically determined over a range of operating conditions from 100 to 1000 psia chamber pressure and 1000 to 10,000-1bF thrust, and specific design points were analyzed in detail for propane, methane, RP-1, ammonia, and ethanol; similar design point studies were performed for a filmcooled reaction control thruster. Heat transfer characteristics of propate were experimentally evaluated in heated tube tests. Forced convection heat transfer coefficients were determined over the range of fluid conditions encompassed by 450 to 1800 psia, -250 to +250 F, and 50 to 150 ft/sec, with wall temperatures from ambient to 1200 F. Seventy-seven hot firing tests were conducted with LOX/propane and LOC/ethanol, for a total duration of nearly 1400 seconds, using both heat sink and water-cooled calorimetric chambers.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA-CR-171713 , NAS 1.26:171713 , REPT-15958-MA-129T-003F-VOL-1
    Format: application/pdf
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  • 3
    Publication Date: 2019-06-28
    Description: An evaluation liquid oxygen (LOX) and various hydrocarbon fuels as low cost alternative propellants suitable for future space transportation system applications was done. The emphasis was directed toward low earth orbit maneuvering engine and reaction control engine systems. The feasibility of regeneratively cooling an orbit maneuvering thruster was analytically determined over a range of operating conditions from 100 to 1000 psia chamber pressure and 1000 to 10,000-1bF thrust, and specific design points were analyzed in detail for propane, methane, RP-1, ammonia, and ethanol; similar design point studies were performed for a film-cooled reaction control thruster. Heat transfer characteristics of propane were experimentally evaluated in heated tube tests. Forced convection heat transfer coefficients were determined. Seventy-seven hot firing tests were conducted with LOX/propane and LOX/ethanol, for a total duration of nearly 1400 seconds, using both heat sink and water-cooled calorimetric chambers. Combustion performance and stability and gas-side heat transfer characteristics were evaluated.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA-CR-171712 , NAS 1.26:171712 , REPT-15958-T-1548-262T-0045
    Format: application/pdf
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