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  • Other Sources  (4)
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  • 1
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    Long life monopropellant hydrazine thruster evaluation for Space Station Freedom application (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In support of propulsion system thruster development activity for Space Station Freedom (SSF), NASA Johnson Space Center (JSC) is conducting a hydrazine thruster technology demonstration program. The goal of this program is to identify impulse life capability of state-of-the-art long life hydrazine thrusters nominally rated for 50 pounds thrust at 300 psia supply pressure. The SSF propulsion system requirement for impulse life of this thruster class is 1.5 million pound-seconds, corresponding to a throughput of approximately 6400 pounds of propellant, with a high performance (234 pound-seconds per propellant pound). Long life thrusters were procured from Hamilton Standard, The Marquardt Company, and Rocket Research Company. Testing has initiated on the thruster designs to identify life while simulating expected thruster firing duty cycles and durations for SSF using monopropellant grade hydrazine. This paper presents a review of the SSF propulsion system and requirements as applicable to hydrazine thrusters, the three long life thruster designs procured by JSC and the resultant acceptance test data for each thruster, and the JSC test plan and facility.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-2041
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Examination of the evolutionary growth requirement of the U.S. Space Station Freedom propulsion system (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A trade study, performed to examine different propulsion systems into which the modular hydrazine system may evolve after the completion of the assembly phase, is discussed and results of this study are presented. Propulsion system options include: the modular hydrazine system, a modified hydrazine system, hypergolic bipropellant systems, an oxygen-hydrogen system, hypergolic bipropellant/hydrazine hybrid systems, and the oxygen-hydrogen/hydrazine hybrid system. Trade study criteria and methodology are reviewed. Water availability and growth and nongrowth configurations are discussed. Recommendations are made on the type of Space Station propulsion system that should be developed for long-term operations at minimal life cycle cost. It is suggested that, due to growth of the station shown in the assembly complete configuration, the oxygen-hydrogen propulsion system should be further developed so that related technology will be mature by assembly complete.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AIAA PAPER 90-2734
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Design, operation, and critical issues of the U.S. Space Station Freedom propulsion system (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The U.S. Space Station Freedom Manned Base (SSFMB) propulsion system is a gaseous hydrogen/oxygen-based system for primary reboost, attitude control, and station contingencies using electrolyzed water as a propellant. A secondary propulsion reboost system employs multipropellant resistojets which utilize the various waste gases generated during normal station operations. The hydrogen/oxygen propulsion system is comprised of several modules which contain thrusters, propellant storage tanks, regulation subsystems, water electrolysis units, electronic controls, and fluid plumbing. The resistojet system is comprised of one module containing the resistojets, regulators, electronic controls, and fluid plumbing. The waste gas propellant storage takes place in the Fluid Management System.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-2611
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A modular propulsion system required for Space Station assembly (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The U.S. Space Station Freedom Manned Base will be assembled on-orbit over the course of several years and multiple Space Shuttle flights. This paper discusses the assembly sequence evolution and its effects on the propulsion system. Relevant descriptions and parameters are given for the gaseous propellant storage, thruster quantity and orientation, and resistojet module. Specific assembly sequences are described and their most important characteristics are compared.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-2613
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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