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  • Spacecraft Propulsion and Power  (12)
  • tannic acid  (2)
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  • 1
    Electronic Resource
    Electronic Resource
    The effects of chronic tannic acid intake on prairie vole (Microtus ochrogaster) reproduction (1993)
    Springer
    Journal of chemical ecology 19 (1993), S. 1577-1585 
    Details
    ISSN: 1573-1561
    Keywords: Tannins ; tannic acid ; polyphenolics ; plant defense ; microtines ; Microtus ochrogaster ; reproduction ; resting metabolic rate ; digestibility reduction ; energetics ; growth rates
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology , Chemistry and Pharmacology
    Notes: Abstract The hypothesis was tested that the reproductive performance of voles would be reduced when fed diets containing tannins either because of increased metabolic rates, decreased intake, or decreased digestive efficiency. We fed a ration containing 4% tannic acid (TA) (dry mass basis) to 24 pair of prairie voles (Microtus ochrogaster) and compared reproductive performance (litter size, birth weights, body mass of the young until weaning, and mass changes in the dams) to that of 24 pair of prairie vole fed a control ration. We also compared the intake rates, digestive efficiency, and metabolic rates [as measured by Vo2 consumption (cm3/hr)] of dams and young fed both rations. Voles consuming 4% TA diets produced litters of similar size and mass as did voles fed the control ration. Furthermore, the mass of the young of dams fed the tannic acid ration were similar to the young of dams consuming the control ration through day 19 postpartum. However, dams consuming the tannic acid ration lost mass throughout lactation while the control dams maintained mass. Because the Vo2 rates of both treated and control dams and litters were similar, we conclude increased metabolic costs were not the reason for the observed mass loss but, rather, reduced digestive efficiency, reduced intake of digestible dry mass, and apparent digestible nitrogen.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00984898
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    Paper (German National Licenses)
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  • 2
    Electronic Resource
    Electronic Resource
    Tannic acid inhibition of amino acid and sugar absorption by mouse and vole intestine: Tests following acute and subchronic exposure (1992)
    Springer
    Journal of chemical ecology 18 (1992), S. 719-736 
    Details
    ISSN: 1573-1561
    Keywords: Dietary tannins ; tannic acid ; digestion ; absorption ; small intestine ; brush border membrane ; unstirred layer ; mucus ; Microtus, Mus.
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology , Chemistry and Pharmacology
    Notes: Abstract The acute effects of tannin (tannic acid; TA) on nutrient absorption were studied by measuring sugar and amino acid uptake across the brash border (luminal membrane) of intact intestine in the presence and absence of TA. Incubation of tissue for 4–9 min in TA solution (1 mg/ml) caused a reduction in passive influx ofl-glucose in voles and mice and a reduction in carrier-mediated influx ofd-glucose and total influx ofl-proline in mice, but not voles. In subchronic experiments, mice and voles were fed for 7–14 days a diet with 4% TA, but there was no significant effect on intestinal brush border uptake ofl-glucose,d-glucose, orl-proline (or three other amino acids tested in voles). In a synthesis of our study with others in the literature, three inferences are made from the patterns of effects across solutes, time scales of exposure, and species. First, the transport inhibitory effects following acute exposure are probably mediated by two processes: increased resistance to passive flux across an effective unstirred layer juxtaposed to the brush border membrane, perhaps due to tannin-mucin binding, and reduced Na+-coupled nutrient uptake across the intestinal brush border. Second, there is a species sensitivity difference in TA's effect on the second process. Third, the negative effects observed at the acute time scale in vitro do not necessarily occur in animals eating TA subchronically because little TA reaches the luminal membrane, or if it does its effects are quickly reversed when the tissue is removed and washed with solution free of TA.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00994610
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  • 3
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    IHPRPT Steering Committee Meeting - NASA Spacecraft Propulsion Update (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: The activities and status of NASA Spacecraft Propulsion is presented including recent accomplishments.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN11245 , IHPRPT Steering Committee Meeting; 18 Sept. 2013; Edwards Air Force Base, California; United States
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  • 4
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    Forced Convection Boiling and Critical Heat Flux of Ethanol in Electrically Heated Tube Tests (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Electrically heated tube tests were conducted to characterize the critical heat flux (transition from nucleate to film boiling) of subcritical ethanol flowing at conditions relevant to the design of a regeneratively cooled rocket engine thrust chamber. The coolant was SDA-3C alcohol (95% ethyl alcohol, 5% isopropyl alcohol by weight), and tests were conducted over the following ranges of conditions: pressure from 144 to 703 psia, flow velocities from 9.7 to 77 ft/s, coolant subcooling from 33 to 362 F, and critical heat fluxes up to 8.7 BTU/in(exp 2)/sec. For the data taken near 200 psia, critical heat flux was correlated as a function of the product of velocity and fluid subcooling to within +/- 20%. For data taken at higher pressures, an additional pressure term is needed to correlate the critical heat flux. It was also shown that at the higher test pressures and/or flow rates, exceeding the critical heat flux did not result in wall burnout. This result may significantly increase the engine heat flux design envelope for higher pressure conditions.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1998-206612 , E-11032 , NAS 1.15:206612 , AIAA Paper 98-1055 , Aerospace Sciences Meeting and Exhibit; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
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  • 5
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    Technology Area Roadmap for In-Space Propulsion Technologies (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The exponential increase of launch system size.and cost.with delta-V makes missions that require large total impulse cost prohibitive. Led by NASA fs Marshall Space Flight Center, a team from government, industry, and academia has developed a flight demonstration mission concept of an integrated electrodynamic (ED) tethered satellite system called PROPEL: \Propulsion using Electrodynamics.. The PROPEL Mission is focused on demonstrating a versatile configuration of an ED tether to overcome the limitations of the rocket equation, enable new classes of missions currently unaffordable or infeasible, and significantly advance the Technology Readiness Level (TRL) to an operational level. We are also focused on establishing a far deeper understanding of critical processes and technologies to be able to scale and improve tether systems in the future. Here, we provide an overview of the proposed PROPEL mission. One of the critical processes for efficient ED tether operation is the ability to inject current to and collect current from the ionosphere. Because the PROPEL mission is planned to have both boost and deboost capability using a single tether, the tether current must be capable of flowing in both directions and at levels well over 1 A. Given the greater mobility of electrons over that of ions, this generally requires that both ends of the ED tether system can both collect and emit electrons. For example, hollow cathode plasma contactors (HCPCs) generally are viewed as state-of-the-art and high TRL devices; however, for ED tether applications important questions remain of how efficiently they can operate as both electron collectors and emitters. Other technologies will be highlighted that are being investigated as possible alternatives to the HCPC such as Solex that generates a plasma cloud from a solid material (Teflon) and electron emission (only) technologies such as cold-cathode electron field emission or photo-electron beam generation (PEBG) techniques
    Keywords: Spacecraft Propulsion and Power
    Type: M12-1836 , M12-1798 , Global Space Exploration Conference; May 22, 2012 - May 24, 2012; Washinton, DC; United States
    Format: application/pdf
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  • 6
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    Roadmap for In-Space Propulsion Technology (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA has created a roadmap for the development of advanced in-space propulsion technologies for the NASA Office of the Chief Technologist (OCT). This roadmap was drafted by a team of subject matter experts from within the Agency and then independently evaluated, integrated and prioritized by a National Research Council (NRC) panel. The roadmap describes a portfolio of in-space propulsion technologies that could meet future space science and exploration needs, and shows their traceability to potential future missions. Mission applications range from small satellites and robotic deep space exploration to space stations and human missions to Mars. Development of technologies within the area of in-space propulsion will result in technical solutions with improvements in thrust, specific impulse (Isp), power, specific mass (or specific power), volume, system mass, system complexity, operational complexity, commonality with other spacecraft systems, manufacturability, durability, and of course, cost. These types of improvements will yield decreased transit times, increased payload mass, safer spacecraft, and decreased costs. In some instances, development of technologies within this area will result in mission-enabling breakthroughs that will revolutionize space exploration. There is no single propulsion technology that will benefit all missions or mission types. The requirements for in-space propulsion vary widely according to their intended application. This paper provides an updated summary of the In-Space Propulsion Systems technology area roadmap incorporating the recommendations of the NRC.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2012-217641 , E-18195 , E-18195-1 , Space Propulsion 2012; May 07, 2012 - May 10, 2012; Bordeaux; France
    Format: application/pdf
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  • 7
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    Cryogenic Propellant Storage and Transfer (CPST) Tour Stop (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: No abstract available
    Keywords: Spacecraft Propulsion and Power
    Type: E-664451
    Format: application/pdf
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  • 8
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    Technology Area Roadmap for In Space Propulsion Technologies (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This roadmap describes a portfolio of in-space propulsion technologies that can meet future space science and exploration needs.
    Keywords: Spacecraft Propulsion and Power
    Type: M11-0738 , 7th Symposium on Realistic Near-Term Advanced Scientific Space Missions; Jul 11, 2011 - Jul 14, 2011; Aosta; Italy
    Format: application/pdf
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  • 9
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    Performance of the Spacecraft Propulsion Research Facility During Altitude Firing Tests of the Delta 3 Upper Stage (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Spacecraft Propulsion Research Facility at the NASA Lewis Research Center's Plum Brook Station was reactivated in order to conduct flight simulation ground tests of the Delta 3 cryogenic upper stage. The tests were a cooperative effort between The Boeing Company, Pratt and Whitney, and NASA. They included demonstration of tanking and detanking of liquid hydrogen, liquid oxygen and helium pressurant gas as well as 12 engine firings simulating first, second, and third burns at altitude conditions. A key to the success of these tests was the performance of the primary facility systems and their interfaces with the vehicle. These systems included the structural support of the vehicle, propellant supplies, data acquisition, facility control systems, and the altitude exhaust system. While the facility connections to the vehicle umbilical panel simulated the performance of the launch pad systems, additional purge and electrical connections were also required which were unique to ground testing of the vehicle. The altitude exhaust system permitted an approximate simulation of the boost-phase pressure profile by rapidly pumping the test chamber from 13 psia to 0.5 psia as well as maintaining altitude conditions during extended steady-state firings. The performance of the steam driven ejector exhaust system has been correlated with variations in cooling water temperature during these tests. This correlation and comparisons to limited data available from Centaur tests conducted in the facility from 1969-1971 provided insight into optimizing the operation of the exhaust system for future tests. Overall, the facility proved to be robust and flexible for vehicle space simulation engine firings and enabled all test objectives to be successfully completed within the planned schedule.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1998-208477 , E-11247 , NAS 1.15:208477 , AIAA Paper 98-4010 , Propulsion; Jul 12, 1998 - Jul 15, 1998; Cleveland, OH; United States
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  • 10
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    Cryogenic Fluid Management Technologies for Advanced Green Propulsion Systems (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In support of the Exploration Vision for returning to the Moon and beyond, NASA and its partners are developing and testing critical cryogenic fluid propellant technologies that will meet the need for high performance propellants on long-term missions. Reliable knowledge of low-gravity cryogenic fluid management behavior is lacking and yet is critical in the areas of tank thermal and pressure control, fluid acquisition, mass gauging, and fluid transfer. Such knowledge can significantly reduce or even eliminate tank fluid boil-off losses for long term missions, reduce propellant launch mass and required on-orbit margins, and simplify vehicle operations. The Propulsion and Cryogenic Advanced Development (PCAD) Project is performing experimental and analytical evaluation of several areas within Cryogenic Fluid Management (CFM) to enable NASA's Exploration Vision. This paper discusses the status of the PCAD CFM technology focus areas relative to the anticipated CFM requirements to enable execution of the Vision for Space Exploration.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2007-214810 , AIAA Paper-2007-343 , 45th AIAA Aerospace Sciences Meeting and Exhibit; Jan 08, 2007 - Jan 11, 2007; Reno, NV; United States
    Format: application/pdf
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