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  • 1
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    Mercury: reusable metadata management, data discovery and access system (2010)
    Springer
    Details
    Publication Date: 2010-05-18
    Print ISSN: 1865-0473
    Electronic ISSN: 1865-0481
    Topics: Geosciences , Computer Science
    Published by Springer
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    PAPER CURRENT
  • 2
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    Data sharing and retrieval using OAI-PMH (2010)
    Springer
    Details
    Publication Date: 2010-10-28
    Print ISSN: 1865-0473
    Electronic ISSN: 1865-0481
    Topics: Geosciences , Computer Science
    Published by Springer
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    PAPER CURRENT
  • 3
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    Catalytic ignition of hydrogen/oxygen (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An experimental program was conducted to evaluate the catalytic ignition of gaseous hydrogen and oxygen. Shell 405 granular catalyst and a unique monolithic sponge catalyst were tested. Mixture ratio, mass flow rate, propellant inlet temperature, and back pressure were varied parametrically in testing to determine the operational limits of a catalytic igniter. The test results showed that the gaseous hydrogen/oxygen propellant combination can be ignited catalytically using Shell 405 catalyst over a wide range of mixture ratios, mass flow rates, and propellant injection temperatures. These operating conditions must be optimized to ensure reliable ignition for an extended period of time. The results of the experimental program and the established operational limits for a catalytic igniter using both the granular and monolithic catalysts are presented. The capabilities of a facility constructed to conduct the igniter testing and the advantages of a catalytic igniter over other ignition systems for gaseous hydrogen and oxygen are also discussed.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: NASA, Marshall Space Flight Center, Advanced Earth-to-Orbit Propulsion Technology 1988, Volume 1; p 231-248
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    An evaluation of metallized propellants based on vehicle performance (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analytical study was conducted to determine the improvements in vehicle performance possible by burning metals with conventional liquid bipropellants. These metallized propellants theoretically offer higher specific impulse, increased propellant density and improved vehicle performance compared with conventional liquid bipropellants. Metals considered were beryllium, lithium, aluminum and iron. Liquid bipropellants were H2/O2, N2H4/N2O4, RP-1/O2 and H2/F2. A mission with a delta V = 4267.2 m/sec (14,000 ft/sec) and vehicle with propellant volume fixed at 56.63 cu m (2000 cu ft) and dry mass fixed at 2761.6 kg (6000 lb) was used, roughly representing the transfer of a chemically propelled upper-stage vehicle from a low-Earth orbit to a geosynchronous orbit. The results of thermochemical calculations and mission analysis calculations for bipropellants metallized with beryllium, lithium, aluminum and iron are presented. Technology issues pertinent to metallized propellants are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100104 , E-3639 , NAS 1.15:100104 , AIAA PAPER 87-1773
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Catalytic ignition of hydrogen and oxygen propellants (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental program was conducted to evaluate the catalytic ignition of gaseous hydrogen and oxygen propellants. Shell 405 granular catalyst and a monolithic sponge catalyst were tested. Mixture ratio, mass flow rate, propellant temperature, and back pressure were varied parametrically in testing to determine the operational limits of the catalytic igniter. The test results show that the gaseous hydrogen and oxygen propellant combination can be ignited catalytically using Shell 405 catalyst over a wide range of mixture ratios, mass flow rates, and propellant injection temperatures. These operating conditions must be optimized to ensure reliable ignition for an extended period of time. A cyclic life of nearly 2000, 2 sec pulses at nominal operating conditions was demonstrated with the catalytic igniter. The results of the experimental program and the established operational limits for a catalytic igniter using the Shell 405 catalysts are presented.
    Keywords: PROPELLANTS AND FUELS
    Type: AIAA PAPER 88-3300
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Catalytic ignition of hydrogen and oxygen propellants (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental program was conducted to evaluate the catalytic ignition of gaseous hydrogen and oxygen propellants. Shell 405 granular catalyst and a monolithic sponge catalyst were tested. Mixture ratio, mass flow rate, propellant temperature, and back pressure were varied parametrically in testing to determine the operational limits of the catalytic igniter. The test results show that the gaseous hydrogen and oxygen propellant combination can be ignited catalytically using Shell 405 catalyst over a wide range of mixture ratios, mass flow rates, and propellant injection temperatures. These operating conditions must be optimized to ensure reliable ignition for an extended period of time. A cyclic life of nearly 2000, 2 sec pulses at nominal operating conditions was demonstrated with the catalytic igniter. The results of the experimental program and the established operational limits for a catalytic igniter using the Shell 405 catalyst are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100957 , E-4104 , NAS 1.15:100957 , AIAA PAPER 88-3300
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A premixed hydrogen/oxygen catalytic igniter (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The catalytic ignition of hydrogen and oxygen propellants was studied using a premixing hydrogen/oxygen injector. The premixed injector was designed to eliminate problems associated with catalytic ignition caused by poor propellant mixing in the catalyst bed. Mixture ratio, mass flow rate, and propellant inlet temperature were varied parametrically in testing, and a pulse mode life test of the igniter was conducted. The results of the tests showed that the premixed injector eliminated flame flashback in the reactor and increased the life of the igniter significantly. The results of the experimental program and a comparison with data collected in a previous program are given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-2302
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    An evaluation of metallized propellants based on vehicle performance (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An analytical study was conducted to determine the improvements in vehicle performance possible by burning metals with conventional liquid bipropellants. These metallized propellants theoretically offer higher specific impulse, increased propellant density and improved vehicle performance compared with conventional liquid bipropellants. Metals considered were beryllium, lithium, aluminum and iron. Liquid bipropellants were H2/O2, N2H4/N2O4, RP-1/O2 and H2/F2. A mission with a delta V = 4267.2 m/sec (14,000 ft/sec) and vehicle with propellant volume fixed at 56.63 cu m (2000 cu ft) and dry mass fixed at 2761.6 kg (6000 lb) was used, roughly representing the transfer of a chemically propelled upper-stage vehicle from a low-Earth orbit to a geosynchronous orbit. The results of thermochemical calculations and mission analysis calculations for bipropellants metallized with beryllium, lithium, aluminum and iron are presented. Technology issues pertinent to metallized propellants are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-1773
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Flow visualization of a rocket injector spray using gelled propellant simulants (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A study was conducted at NASA-Lewis to compare the atomization characteristics of gelled and nongelled propellant simulants. A gelled propellant simulant composed of water, sodium hydroxide, and an acrylic acid polymer resin (as the gelling agent) was used to simulate the viscosity of an aluminum/PR-1 metallized fuel gel. Water was used as a comparison fluid to isolate the rheological effects of the water-gel and to simulate nongelled RP-1. The water-gel was injected through the central orifice of a triplet injector element and the central post of a coaxial injector element. Nitrogen gas flowed through the outer orifices of the triplet injector element and through the annulus of the coaxial injector element and atomized the gelled and nongelled liquids. Photographs of the water-gel spray patterns at different operating conditions were compared with images obtained using water and nitrogen. A laser light was used for illumination of the sprays. The results of the testing showed that the water sprays produced a finer and more uniform atomization than the water-gel sprays. Rheological analysis of the water-gel showed poor atomization caused by high viscosity of water-gel delaying the transition to turbulence.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2198
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    A Heated Tube Facility for Rocket Coolant Channel Research (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The capabilities of a heated tube facility used for testing rocket engine coolant channels at the NASA Lewis Research Center are presented. The facility uses high current, low voltage power supplies to resistively heat a test section to outer wall temperatures as high as 730 C (1350 F). Liquid or gaseous nitrogen, gaseous helium, or combustible liquids can be used as the test section coolant. The test section is enclosed in a vacuum chamber to minimize heat loss to the surrounding system. Test section geometry, size, and material; coolant properties; and heating levels can be varied to generate heat transfer and coolant performance data bases.
    Keywords: Ground Support Systems and Facilities (Space)
    Type: NASA-TM-106968 , E-9725 , NAS 1.15:106968 , AIAA Paper 95-2936 , 31st Joint Propulsion Conference and Exhibit; Jul 10, 1995 - Jul 12, 1995; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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