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  • 1
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    Cryogenic propellant management architectures to support the Space Exploration Initiative (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The initial results of a current study to develop fuel system architectures to support the lunar requirements of the Space Exploration Initiative (SEI) are reported. The study includes the development and assessment of propellant management facility concepts, supporting infrastructure, operations analysis, and identification of impact on current programs, including Space Station Freedom, Earth-to-Orbit vehicles, and the Space Transfer Vehicle. The cryogenic propellant management architectures are evaluated using criteria that have been defined to provide for minimum subjective assessment and effective data reliability.
    Keywords: PROPELLANTS AND FUELS
    Type: AIAA PAPER 90-3713
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Main tank injection pressurization program (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer program predicts performance of fluorine-hydrogen main tank injection pressurization system for full range of liquid-hydrogen-fueled space vehicles. Analytical model includes provisions for heat transfer, injectant jet penetration, and ullage gas mixing. Analysis predicts GF2 usage, ullage gas and tank wall temperatures, and LH2 evaporation.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LEW-11368
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Vehicle-scale investigation of a fluorine-hydrogen main tank injection pressurization system Final report, 1 Jul. 1969 - 31 Jul. 1970 (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Vehicle-scale analysis of fluorine-hydrogen main tank injection pressurization system
    Keywords: SPACE VEHICLES
    Type: NASA-CR-72756 , MDC-G0805
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Hypergolicity of F2-H2 and reaction product freezing under main tank injection pressurization conditions Interim report, 30 Jun. 1966 - 30 Jul. 1967 (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effects of physical, and chemical variables on hypergolicity of cryogenic fluorine-hydrogen propellants
    Keywords: PROPELLANTS
    Type: NASA-CR-72253 , DAC-60975
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Feasibility study for a Cryogenic On-Orbit Liquid Depot-Storage, Acquisition and Transfer (COLD-SAT) satellite (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This feasibility study presents the conceptual design of a spacecraft for performing a series of cryogenic fluid management flight experiments. This spacecraft, the Cryogenic On-Orbit Liquid Depot-Storage, Acquisition, and Transfer (COLD-SAT) satellite, will use liquid hydrogen as the test fluid, be launched on a Delta expendable launch vehicle, and conduct a series of experiments over a two to three month period. These experiments will investigate the physics of subcritical cryogens in the low gravity space environment to characterize their behavior and to correlate the data with analytical and numerical models of in-space cryogenic fluid management systems. Primary technologies addressed by COLD-SAT are: (1) pressure control; (2) chilldown; (3) no-vent fill; (4) liquid acquisition device fill; (5) pressurization; (6) low-g fill and drain; (7) liquid acquisition device expulsion; (8) line chilldown; (9) thermodynamic state control; and (10) fluid dumping.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-185248 , NAS 1.26:185248
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Feasibility study for the Cryogenic Orbital Nitrogen Experiment (CONE) (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An improved understanding of low gravity subcritical cryogenic fluid behavior is critical for the continued development of space based systems. Although early experimental programs provided some fundamental understanding of zero gravity cryogenic fluid behavior, more extensive flight data are required to design space based cryogenic liquid storage and transfer systems with confidence. As NASA's mission concepts evolve, the demand for optimized in-space cryogenic systems is increasing. Cryogenic Orbital Nitrogen Experiment (CONE) is an attached shuttle payload experiment designed to address major technological issues associated with on-orbit storage and supply of cryogenic liquids. During its 7 day mission, CONE will conduct experiments and technology demonstrations in active and passive pressure control, stratification and mixing, liquid delivery and expulsion efficiency, and pressurant bottle recharge. These experiments, conducted with liquid nitrogen as the test fluid, will substantially extend the existing low gravity fluid data base and will provide future system designers with vital performance data from an orbital environment.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-187231 , NAS 1.26:187231
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    An investigation of fluorine-hydrogen main tank injection pressurization. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Fluorine injectors for main tank injection of space vehicle liquid hydrogen tank, including study of hypergolicity and reaction product freezing
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 69-528 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, PROPULSION JOINT SPECIALIST CONFERENCE; Jun 09, 1969 - Jun 13, 1969; COLORADO SPRINGS, COLO.
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Solar Thermal Upper Stage Liquid Hydrogen Pressure Control Testing and Analytical Modeling (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The demonstration of a unique liquid hydrogen (LH2) storage and feed system concept for solar thermal upper stage was cooperatively accomplished by a Boeing/NASA Marshall Space Flight Center team. The strategy was to balance thermodynamic venting with the engine thrusting timeline during a representative 30-day mission, thereby, assuring no vent losses. Using a 2 cubic m (71 cubic ft) LH2 tank, proof-of-concept testing consisted of an engineering checkout followed by a 30-day mission simulation. The data were used to anchor a combination of standard analyses and computational fluid dynamics (CFD) modeling. Dependence on orbital testing has been incrementally reduced as CFD codes, combined with standard modeling, continue to be challenged with test data such as this.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TP-2012-217469 , M-1345
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Design and evaluation of thermodynamic vent/screen baffle cryogenic storage system (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A comprehensive analytical program was performed to compare an integrated thermodynamic vent/screen baffle orbital cryogenic propellant storage and transfer system with other concepts. The screen systems were found to be 20% to 29% lighter in weight than a propulsively accelerated Tug-scale LH2/LO2 resupply module. The screen systems were compared with small-scale supercritical storage systems for the space shuttle fuel cell reactant and life support system fluid supply and were lighter by up to 556 kg (1225 lb) for the extended 30-day mission. When compared with high-pressure gas storage for the spacelab atmosphere supply, the screen system saved 79% of the inert system weight for the 30-day mission. An experimental program found that heat flux rates up to 9,450 watts/sq m (3,000 Btu/hr-sq ft) degraded the LH2 bubble point performance of eight screens by a maximum of 12.5%. No effects of helium pressurant, screen material, or LH2 superheat were observed.
    Keywords: ENGINEERING (GENERAL)
    Type: NASA-CR-134810 , MDC-G5979
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Developments in low-gravity cryogenic propellant acquisition and thermal control systems (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Development programs are described for two low-gravity cryogenic propellant acquisition systems: a full-screen liner system, and a refillable start-tank. First, based on experimental LH2 screen flow data, the fluid-dynamic characteristics of an integrated screen/thermodynamic vent system were analyzed for a design compared to 17.5 cu fg supercritical life-support systems, and for a Tug orbital LH2/LQ2 resupply system. Second, the analysis, design, fabrication, and test of a 10 cu ft, annular-screen start-tank with a wall-mounted thermodynamic vent was performed. The test program demonstrated that the system expelled LH2 against 1-g and performed properly over a range of conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 74-1155 , MDAC-WD-2461 , American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference; Oct 21, 1974 - Oct 23, 1974; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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