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  • 1
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    Space station propulsion test bed: A complete system (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A test bed was fabricated to demonstrate hydrogen/oxygen propulsion technology readiness for the Initial Operating Capabilities (IOC) space station application and for use as a means to test evolving technology for the growth station. The test bed, its function, and plans for future testing are discussed.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: Johns Hopkins Univ., The 1986 JANNAF Propulsion Meeting, Volume 1; p 533-538
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Space Station propulsion test bed - A complete system (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A test bed was fabricated under NASA/MSFC (Marshall Space Flight Center) Contract NAS8-36418 to demonstrate hydrogen/oxygen propulsion technology readiness for the Initial Operating Conditions Space Station application and for use as a means to test evolving technology for the growth station. This paper describes the test bed and its function.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: AIAA PAPER 86-1402
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Space station propulsion test bed (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A test bed was fabricated to demonstrate hydrogen/oxygen propulsion technology readiness for the intital operating configuration (IOC) space station application. The test bed propulsion module and computer control system were delivered in December 1985, but activation was delayed until mid-1986 while the propulsion system baseline for the station was reexamined. A new baseline was selected with hydrogen/oxygen thruster modules supplied with gas produced by electrolysis of waste water from the space shuttle and space station. As a result, an electrolysis module was designed, fabricated, and added to the test bed to provide an end-to-end simulation of the baseline system. Subsequent testing of the test bed propulsion and electrolysis modules provided an end-to-end demonstration of the complete space station propulsion system, including thruster hot firings using the oxygen and hydrogen generated from electrolysis of water. Complete autonomous control and operation of all test bed components by the microprocessor control system designed and delivered during the program was demonstrated. The technical readiness of the system is now firmly established.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183615 , NAS 1.26:183615 , RI/RD89-104
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Space Station propulsion system test bed (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The test bed to study H2/O2 propulsion technology for the Space Station is discussed. The test bed consists of propellant accumulators, valving, instrumentation, and controls configured in a 9-ft cube. A water electrolysis module was added to simulate the baseline propulsion system configuration. The activation of the test bed is described, and results are presented from tests of the system, including verification of the control system, thruster tests, electrolysis system testing, and acceptance test, oxidizer system, and fuel system blowdowns.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: IAF PAPER 88-241
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    25-LBF GO2/GH2 space station thruster (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Multiple 25-lbf oxygen/gaseous hydrogen thruster assemblies for the Space Station propulsion application were designed and fabricated by Rocketdyne and endurance tested at the NASA/Marshall Space Flight Center. The thrusters incorporate a regeneratively cooled thrust chamber with a nozzle area ratio of 30, a 12-element coaxial injector, an ignition system, and close-coupled propellant valves. The various thruster configurations comprised of mating different injectors and thrust chambers. Over 2 million lbf-sec of impulse was demonstrated at mixture ratios from 3 to 8.4 at vacuum conditions. A thruster was subjected to over 10,000 pulses during which minimum impulse bits of less than 0.5 lb/sec were repeatedly and reliably demonstrated. A total operating time of 25.6 hr was accumulated on the thruster assemblies with one 6.1-hr. continuous firing duration. The thrusters operated between a thrust range of 11.2 and 36.6 lbf. The test results indicate that all major technology issues for long-life gaseous oxygen/gaseous hydrogen thrusters for the Space Station application have been resolved.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 88-2793
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Space Station propulsion system test bed and control system testing results (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The test bed fabricated to demonstrate hydrogen/oxygen propulsion technology readiness for the IOC Space Station application is described and test results are presented. The reliability and safety of the O2/H2 system was demonstrated with blowdowns and thruster firings. The flexibility of the system was demonstrated through the addition of an electrolysis supply module.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: AIAA PAPER 87-1858
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Space station propulsion technology: Space station propulsion system test bed test plan (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Testing of the hydrogen/oxygen Space Station Propulsion System will demonstrate the technology readiness for the IOC application. To facilitate early demonstration of this technology and to allow demonstration of maturing technology, this testing will be performed with the components installed on a test bed which simulated the Space Station Structure. The test plan contains a description of the test bed, test objective, instrumentation plan, and controls plan. Each of these is discussed in detail.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179201 , NAS 1.26:179201
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Space station propulsion technology (1987)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objectives of this program are to provide a demonstration of hydrogen/oxygen propulsion technology readiness for the initial operational capability (IOC) space station application, specifically gaseous hydrogen/oxygen and warm hydrogen thruster concepts, and to establish a means for evolving from the IOC space station propulsion system (SSPS) to that required to support and interface with advanced station functions. These objectives were met by analytical studies and by furnishing a propulsion test bed to the Marshall Space Flight Center for testing.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179260 , NAS 1.26:179260
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Space station propulsion technology (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The progress on the Space Station Propulsion Technology Program is described. The objectives are to provide a demonstration of hydrogen/oxygen propulsion technology readiness for the Initial Operating Capability (IOC) space station application, specifically gaseous hydrogen/oxygen and warm hydrogen thruster concepts, and to establish a means for evolving from the IOC space station propulsion to that required to support and interface with advanced station functions. The evaluation of concepts was completed. The accumulator module of the test bed was completed and, with the microprocessor controller, delivered to NASA-MSFC. An oxygen/hydrogen thruster was modified for use with the test bed and successfully tested at mixture ratios from 4:1 to 8:1.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-178897 , NAS 1.26:178897 , RI/RD86-226 , REPT-0737P-105- , 1-Apr
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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