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  • 1
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    NASA Lewis Research Center low-gravity fluid management technology program (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A history of the Lewis Research Center in space fluid management technology program is presented. Current programs which include numerical modeling of fluid systems, heat exchanger/radiator concept studies, and the design of the Cryogenic Fluid Management Facility are discussed. Recent analytical and experimental activities performed to support the Shuttle/Centaur development activity are highlighted.
    Keywords: SPACE TRANSPORTATION
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    NASA TECHNICAL REPORTS
  • 2
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    An experimental investigation of boiling in normal and zero gravity. (1967)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Zero gravity effects on boiling from flat horizontal surface for various subcoolings, fluid properties and heat transfer rates
    Keywords: THERMODYNAMICS AND COMBUSTION
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    NASA TECHNICAL REPORTS
  • 3
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    Effects of subcooling and gravity level on boiling in the discrete bubble region (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Subcooling and gravity level effects investigated for water boiling at low heat flux from flat horizontal surface
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-3449
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Discharge rate of cryogens in microgravity - What ground based experimentation cannot resolve (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The discharge of cryogenic vapor and liquid from tanks to a vacuum is examined and the effects of the mass quality, length/diameter ratio, supply tank transient and gravitational environment are discussed. Existing model results and normal gravity experiments are presented which indicate that the homogeneous equilibrium model provides an accurate description of two-phase critical flow for a number of conditions likely to be encountered in practical microgravity systems. Nonequilibrium effects are shown to produce flow rates greater than homogeneous equilibrium model predictions for long tubes with low inlet pressure and short tubes with high inlet pressure.
    Keywords: ENGINEERING (GENERAL)
    Type: AIAA PAPER 91-3545
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Transient cryogenic liquid discharge in normal and micro-gravity (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Transient discharge of liquid cryogens from partially filled tanks under microgravity is considered. The discharge is made to a low-pressure site through a straight tube. The ultimate objective of the study is to predict the transient mass flow rate. In addition, the pressure history in the tank is of interest, since the pressure falls below the triple point toward the end of the dump, causing solidification in the tank and/or the discharge line. As first steps, experiments have been performed in normal gravity and attempts are made to predict the transient rate and pressure history under this condition. Experiments are performed with liquid nitrogen dumped to sites with pressures below the triple point. Homogeneous equilibrium and nonequilibrium two-phase critical flow models are compared to the experimental results. Equilibrium and nonequilibrium tank pressure history models are also compared to experimental data.
    Keywords: PROPELLANTS AND FUELS
    Type: AIAA PAPER 91-0486
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    NASA TECHNICAL REPORTS
  • 6
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    Effect of subcooling on the on-orbit pressurization rate of cryogenic propellant tankage (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The SOLA-ECLIPSE code is being developed to enable prediction of the behavior of cryogenic propellants in spacecraft tankage. A brief description of the formulations used for modeling heat transfer and for determining thermodynamic state is presented. Code performance is verified through comparison to experimental data for the self-pressurization of scale model liquid hydrogen tanks. SOLA-ECLIPSE is used to examine the effect of initial subcooling of the liquid phase on the self-pressurization rate of an on-orbit full scale liquid hydrogen tank typical for a chemical propulsion Orbital Transfer Vehicle. The computational predictions show that even small amounts of subcooling will significantly decrease the self-pressurization rate. Further, if the cooling is provided by a Thermodynamic Vent System, it is concluded that small levels of subcooling will maximize propellant conservation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 86-1253
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Technology requirements to be addressed by the NASA Lewis Research Center Cryogenic Fluid Management Facility program (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The NASA Lewis Research Center is responsible for the planning and execution of a scientific program which will provide advance in space cryogenic fluid management technology. A number of future space missions were identified that require or could benefit from this technology. These fluid management technology needs were prioritized and a shuttle attached reuseable test bed, the cryogenic fluid management facility (CFMF), is being designed to provide the experimental data necessary for the technology development effort.
    Keywords: ENGINEERING (GENERAL)
    Type: AIAA PAPER 85-1229
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    NASA TECHNICAL REPORTS
  • 8
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    Temperature fields due to jet induced mixing in a typical OTV tank (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Eclipse Code is being developed as a general tool for analysis of cryogenic propellant behavior in spacecraft tankage. The focus of the work being reported is on prediction of temperature fields due to introduction of a cold jet along the centerline of a typical Orbit Transfer Vehicle tank. A brief description of the formulations used for modeling heat transfer and turbulent flow is presented. Code performance is verified through comparison to experimental data for mixing in small scale tanks. An unexpected difficulty in computing long duration flows is reviewed. Preliminary results for a partially filled full scale tank are obtained by approximating the free surface by a spherical solid boundary.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2017
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Effect of baffles on inflow patterns in spherical containers during weightlessness (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation of isothermal liquid inflow patterns in a spherical container during weightlessness was conducted in a 2.2-Second Zero-Gravity Facility. The test liquids employed exhibited an essentially zero-degree static contact angle on the surface of the container. Qualitative results are presented for both baffled and unbaffled containers describing the uniformity of tank wall wetting and the liquid loss through two symmetrically located vents.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-2670 , E-7085
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Centaur propellant acquisition system (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The desirability of replacing the hydrogen peroxide settling system of the Centaur D-1S with a capillary acquisition system was evaluated. A comprehensive screening was performed to select the most promising capillary device fluid acquisition, thermal conditioning, and fabrication techniques. Refillable start baskets and bypass feed start tanks were selected for detailed design. Critical analysis areas were settling and refilling, start sequence development with an initially dry boost pump, and cooling the fluid delivered to the boost pump to provide the necessary net positive suction head (NPSH). Design drawings were prepared for start basket and start tank concepts for both the liquid oxygen and liquid hydrogen tanks. System comparisons indicated that the start baskets using wicking flow for thermal conditioning, and thermal subcooling for providing boost pump NPSH, are the most desirable systems for future Centaur acquisition system development.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-1194
    Format: text
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    NASA TECHNICAL REPORTS
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