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  • 1
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    Capillary acquisition devices for high-performance vehicles: Executive summary (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technology areas critical to the development of cryogenic capillary devices were studied. Passive cooling of capillary devices was investigated with an analytical and experimental study of wicking flow. Capillary device refilling with settled fluid was studied using an analytical and experimental program that resulted in successful correlation of a versatile computer program with test data. The program was used to predict Centaur D-1S LO2 and LH2 start basket refilling. Comparisons were made between the baseline Centaur D-1S propellant feed system and feed system alternatives including systems using capillary devices. The preferred concepts from the Centaur D-1S study were examined for APOTV and POTV vehicles for delivery and round trip transfer of payloads between LEO and GEO. Mission profiles were determined to provide propellant usage timelines and the payload partials were defined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-159658 , GDC-CRAD-80-003
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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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
  • 3
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    Fluid management systems technology summaries (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A summarization and categorization of the pertinent literature associated with fluid management systems technology having potential application to in-orbit fluid transfer and/or associated storage are presented. A literature search was conducted to obtain pertinent documents for review. Reports determined to be of primary significance were summarized in the following manner: (1) report identification, (2) objective(s) of the work, (3) description of pertinent work performed, (4) major results, and (5) comments of the reviewer. Pertinent figures are presented on a single facing page separate from the text. Specific areas covered are: fluid line dynamics and thermodynamics, low-g mass gauging, other instrumentation, stratification/pressurization, low-g vent systems, fluid mixing refrigeration and reliquefaction, and low-g interface control and liquid acquisition systems. Reports which were reviewed and not summarized, along with reasons for not summarizing, are also listed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-134748 , CASD-NAS-74-068
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Centaur Propellant Thermal Conditioning Study (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wicking investigation revealed that passive thermal conditioning was feasible and provided considerable weight advantage over active systems using throttled vent fluid in a Centaur D-1s launch vehicle. Experimental wicking correlations were obtained using empirical revisions to the analytical flow model. Thermal subcoolers were evaluated parametrically as a function of tank pressure and NPSP. Results showed that the RL10 category I engine was the best candidate for boost pump replacement and the option showing the lowest weight penalty employed passively cooled acquisition devices, thermal subcoolers, dry ducts between burns and pumping of subcooler coolant back into the tank. A mixing correlation was identified for sizing the thermodynamic vent system mixer. Worst case mixing requirements were determined by surveying Centaur D-1T, D-1S, IUS, and space tug vehicles. Vent system sizing was based upon worst case requirements. Thermodynamic vent system/mixer weights were determined for each vehicle.
    Keywords: PROPELLANTS AND FUELS
    Type: NASA-CR-135032 , CASD-NAS-76-026
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Capillary device refilling (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An analytical and experimental study was conducted dealing with refilling start baskets (capillary devices) with settled fluid. A computer program was written to include dynamic pressure, screen wicking, multiple-screen barriers, standpipe screens, variable vehicle mass for computing vehicle acceleration, and calculation of tank outflow rate and vapor pullthrough height. An experimental apparatus was fabricated and tested to provide data for correlation with the analytical model; the test program was conducted in normal gravity using a scale-model capillary device and ethanol as the test fluid. The test data correlated with the analytical model; the model is a versatile and apparently accurate tool for predicting start basket refilling under actual mission conditions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 80-1095 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Centaur propellant acquisition system study (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A study was performed to determine the desirability of replacing the hydrogen peroxide settling system on the Centaur D-1S with a capillary acquisition system. 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 in order to provide necessary net position suction head (NPSH). Design drawings were prepared for the start basket and start tank concepts for both LO2 and LH2 tanks. System comparisons indicated that the start baskets using wicking for thermal conditioning, and thermal subcooling for boost pump NPSH, are the most desirable systems for future development.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-134811 , CASD-NAS-75-023
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Centaur propellant thermal conditioning system (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An upgraded Centaur capability was studied by investigating three main areas: (1) Analytical and experimental investigation of promising capillary pumping concepts for passive cooling of cryogenic capillary acquisition devices resulted in selection, test, and empirical correlation of four wicking configurations. Only plate/screen-screen/plate and plate/screen-plate/screen configurations would function successfully under worst-case Centaur D-1S conditions. Weight estimates were developed for the passively cooled configurations and comparisons were made of passive and actively cooled capillary devices. (2) Thermal subcoolers for replacing pressurization and boost pump systems for three engine candidates and three Centaur D-1S missions were evaluated for several feed system configurations. Analysis included both transient and steady-state operation. Weight comparisons were made among feed system alternatives. (3) Existing experimental mixing studies to destroy thermal stratification were evaluated to determine the best mixing correlation to fit all available data. The correlation was then used to modify a computer program to size thermodynamic vent systems for Shuttle-based Centaur derivatives.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 77-851 , Propulsion Conference; Jul 11, 1977 - Jul 13, 1977; Orlando, FL; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Cryogenic zero-gravity prototype vent system (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design, fabrication, and tests of prototype cryogenic zero-gravity heat exchanger vent system
    Keywords: SPACE VEHICLES
    Type: NASA-CR-98079 , GDC-DDB67-006
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Filling of orbital fluid management systems (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was performed with three objectives: (1) analyze fluid management system fill under orbital conditions; (2) determine what experimentation is needed; and (3) develop an experimental program. The fluid management system was a 1.06m (41.7 in) diameter pressure vessel with screen channel device. Analyses were conducted using liquid hydrogen and N2O4. The influence of helium and autogenous pressurization systems was considered. Analyses showed that fluid management system fill will be more difficult with a cryogen than with an earth storable. The key to a successful fill with cryogens is in devising techniques for filling without vent liquid, and removing trapped vapor from the screen device at tank fill completion. This will be accomplished with prechill, fill, and vapor condensation processes. Refill will require a vent and purge process, to dilute the residual helium, prior to introducing liquid. Neither prechill, chill, nor purge processes will be required for earth storables.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-159404 , CASD-NAS-78-010
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Low-G fluid behavior technology summaries (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This report presents a summarization and categorization of the pertinent literature associated with low-g fluid behavior technology. Initially a literature search was conducted to obtain pertinent documents for review. Reports determined to be of primary significance are summarized in detail. Each summary, where applicable, consists of; (1) report identification, (2) objective(s) of the work, (3) description of pertinent work performed, (4) major results, and (5) comments of the reviewer (GD/C). Pertinent figures are presented on a single facing page separate from the text. Specific areas covered are; interface configuration, interface stability, natural frequency and damping, liquid reorientation, bubbles and droplets, fluid inflow, fluid outflow, convection, boiling and condensation heat transfer, venting effects, and fluid properties. Reports which were reviewed and not summarized, along with reasons for not summarizing, are also listed. Cryogenic thermal control and fluid management systems technology are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-134746 , CASD-NAS-74-066
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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