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  • 1
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    Anthelmintic activity of albendazole against liver flukes, tapeworms, lung and gastrointestinal roundworms (1976)
    Springer
    Details
    Publication Date: 1976-06-01
    Print ISSN: 0014-4754
    Topics: Biology , Medicine
    Published by Springer
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    PAPER CURRENT
  • 2
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    Condensation heat transfer in a microgravity environment (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 2; 82-84
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Condensation heat transfer in a microgravity environment (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In the present treatment of the condensation heat transfer process in a microgravity environment, two mechanisms for condensate removal are analyzed in light of two problems: (1) film condensation on a flat, porous plate, with condensate being removed by wall suction; and (2) the analytical prediction of the heat transfer coefficient of condensing annular flows, where the condensate film is driven by vapor shear. Both suction and vapor shear can effectively drain the condensate, ensuring continuous operation in microgravity.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 86-0068
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Development of a prototype automated on-orbit contact heat exchanger (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An automated contact heat exchanger is being developed for use aboard the manned Space Station, serving as an interface heat exchanger between the pressurized module internal thermal buses and the central external thermal bus. The concept makes use of an array of flattened, thin-walled, flexible tubes that expand or contract to make or break the thermal connection as the internal pressure changes. Because of its simplicity, it permits on-orbit assembly by the remote manipulator system, thus eliminating the need for expensive EVA to make connections. A design methodology based on stress and thermal analyses has been developed and used to perform trade-offs between performance and cost, and to optimize design parameters. Simple verification tests have been performed to confirm the stress analysis model. Two conceptual variants of the contact heat exchanger are described, each designed for a 25 kW total heat load and a minimum uniform heat flux of 2.15 W/sq cm.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-1269
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Shuttle-launch triangular space station (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A triangular space station deployable in orbit is described. The framework is comprized of three trusses, formed of a pair of generally planar faces consistine of foldable struts. The struts expand and lock into rigid structural engagement forming a repetition of equilater triangles and nonfolding diagonal struts interconnecting the two faces. The struts are joined together by node fittings. The framework can be packaged into a size and configuration transportable by a space shuttle. When deployed, the framework provides a large work/construction area and ample planar surface area for solar panels and thermal radiators. A plurity of modules are secured to the framework and then joined by tunnels to make an interconnected modular display. Thruster units for the space station orientation and altitude maintenance are provided.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A steerable radiator for spacecraft application (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Future large space structures such as the Space Station will have high dissipation and long life requirements which dictate the requirements for steerable radiators. Several rotary coupling concepts were considered to accomplish heat transport across the steerable radiator system's rotating interface. Rotary fluid couplings were chosen over rotary contact couplings or flexible lines because of low temperature gradients and operational flexibility. A rotary fluid coupling has been designed for use on initial operating capability (IOC) and growth Space Station. Its internal seals have been demonstrated to a 10 year life with minimal (0.055 lbm NH3/year) leakage between internal passages. Materials compatibility tests have been conducted to demonstrate compatibility with ammonia. A seal leakage management system has been designed to: (1) monitor pressures between the internal seals, (2) remove leakage, and (3) store the leakage fluid in a reservoir.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-1298
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Heat Rejection Working Group Synopsis (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: Heat rejection system requirements of specific mission types (space station, planetary exploration, commercial, very high power, and military missions) are discussed. Heat pipe radiators, weight and volume reduction, stable coatings, and working fluids are addressed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 309-316
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal Management Technology Status (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: The thermal control requirements of a large space station are considered. Motivations for advanced thermal technology are discussed. Two test programs, designed to evaluate the analytical and theoretical basis from which thermal technology directions are determined, are described.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Lewis Research Center Space Power; p 189-203
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Structural and preliminary thermal performance testing of a pressure activated contact heat exchanger (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A contact heat exchanger concept is being developed for use onboard Space Station as an interface device between external thermal bus and pressurized modules. The concept relies on mechanical contact activated by the fluid pressure inside thin-walled tubes. Structural testings were carried out to confirm the technology feasibility of using such thin-walled tubes. The test results also verified the linear elastic stress analysis which was used to predict the tube mechanical behaviors. A preliminary thermal testing was also performed with liquid Freon-11 flowing inside tubes and heat being supplied by electrical heating from the bottom of the contact heat exchanger baseplate. The test results showed excellent agreement of test data with analytical prediction for all thermal resistances except for the two-phase flow characteristics. Testing with two-phase flow inside tubes will, however, be performed on the NASA-JSC test bed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 87-1540
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Development of a prototype two-phase thermal bus system for Space Station (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the basic elements of a pumped two-phase ammonia thermal control system designed for microgravity environments, the development of the concept into a Space Station flight design, and design details of the prototype to be ground-tested in the Johnson Space Center (JSC) Thermal Test Bed. The basic system concept is one of forced-flow heat transport through interface heat exchangers with anhydrous ammonia being pumped by a device expressly designed for two-phase fluid management in reduced gravity. Control of saturation conditions, and thus system interface temperatures, is accomplished with a single central pressure regulating valve. Flow control and liquid inventory are controlled by passive, nonelectromechanical devices. Use of these simple control elements results in minimal computer controls and high system reliability. Building on the basic system concept, a brief overview of a potential Space Station flight design is given. Primary verification of the system concept will involve testing at JSC of a 25-kW ground test article currently in fabrication.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 87-1628
    Format: text
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    NASA TECHNICAL REPORTS
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