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  • 1
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    Space storable propellant performance demonstration. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Specific impulse deliverable performance of space storable propellant combination fluorine-oxygen/ methane and oxygen difluoride/diborane
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 69-505 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, PROPULSION JOINT SPECIALIST CONFERENCE; Jun 09, 1969 - Jun 13, 1969; COLORADO SPRINGS, COLO.
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Hydrogen-oxygen space shuttle ACPS thruster technology review (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The generation of technology for injectors, cooled thrust chambers, valves, and ignition systems is discussed. The thrusters are designed to meet a unique and stringent set of requirements, including: long life for 100 mission reuses, high performance, light weight, ability to provide long duration firings as well as small impulse bits, ability to operate over wide ranges of propellant inlet conditions and to withstand reentry heating. The program has included evaluation of thrusters designed for ambient temperature and cold gaseous propellants at the vehicle interface.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-68146 , E-7171 , Propulsion Joint Specialists Conf.; Nov 29, 1972 - Dec 01, 1972; New Orleans; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Demonstration of a pulsing liquid hydrogen/liquid oxygen thruster (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The development of an injector/thruster concept capable of pulsing a liquid hydrogen/liquid oxygen attitude control propulsion system thruster over thrust and chamber-pressure ranges of 625 to 1250 lbF and 250 to 500 psia, respectively, is discussed. It is shown how continuing search for a simple light-weight, high-performance reaction control system concept led to successful operation tests at cryogenic propellant temperatures (150 and 45 degrees Rankine for oxygen and hydrogen, respectively). The analytical and experimental phases of the liquid/liquid thruster technology efforts are examined.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1244 , Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Demonstration of a pulsing liquid hydrogen/liquid oxygen thruster (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Successful operation of a pulsing liquid hydrogen/liquid oxygen attitude control propulsion system thruster (1250 lb sub f) at cryogenic inlet conditions while maintaining high specific impulse and low impulse bit capability was demonstrated. Significant technical advances and departures from conventional injector design practices were necessary in order to achieve an operable thruster. These advancements were achieved through extensive analyses of heat transfer and injector manifold priming that established the baseline feasibility for an actual hardware design. The primary subject of this paper is the result of experimental evaluation of the 45 R hydrogen inlet temperature injector concept. The test matrix consisted of 66 hot firing tests in a heat sink thrust chamber.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71444 , E-7703 , Propulsion Joint Specialist Conf.; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Hydrogen-oxygen Space Shuttle ACPS thruster technology review. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A comprehensive program has provided the technology groundwork for the use of hydrogen-oxygen propellants in the Space Shuttle Attitude Control Propulsion System (ACPS) thrustors. This work has concentrated on generation of technology for injectors, cooled thrust chambers, valves, and ignition systems. The thrustors are designed to meet a unique and stringent set of requirements, including: long life for 100 mission reuses, high performance, light weight, ability to provide long duration firings as well as small impulse bits, ability to operate over wide ranges of propellant inlet conditions and to withstand reentry heating. The program has included evaluation of thrustors designed for ambient temperature and cold gaseous propellants at the vehicle interface.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 72-1158 , Joint Propulsion Specialist Conference; Nov 29, 1972 - Dec 01, 1972; New Orleans, LA; US
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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