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  • Other Sources  (9)
  • 1
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    Space heat rejection radiatiors: Meteoroid/debris consideration (1985)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The effect of the meteoroid/space debris environment on the design and evolution of spacecraft waste heat rejection radiator systems is discussed. Active radiator systems; i.e., systems in which waste heat is collected from the various heat sources within a spacecraft and delivered to the radiator system by a heat transport loop are emphasized. The heat is distributed over the radiator area and thus rejected to space. Present and future systems are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Orbital Debris; p 295-298
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal control - Heat buses will operate like a public utility (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Active thermal control for the NASA space station concept requires long life heat rejection, highly versatile thermal transport, and efficient system integration. By a significant margin, the heat radiator will be the largest and most exposed portion of the space station thermal system. Transport requirements encompass the collection and movement of thermal energy from the space station's heat sources to the radiator heat sink at required temperature levels. In a decentralized thermal system, each space station module would collect and reject all of the waste heat generated, thereby requiring no module interconnections. This scheme does not, however, allow waste heat from one module to be used by another. In a centralized system, heat must be transported across module boundaries. A high capacity monogroove heat pipe has been developed to simplify space radiators design and operation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 21; Mar. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Development of an Advanced Trapezoidal Axially Grooved (ATAG) heat pipe (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper discusses the breadboard development of an Advanced Trapezoidal Axially Grooved (ATAG) heat pipe, which will satisfy space constructible radiator heat rejection requirements for large space power systems. The ATAG heat pipe development program includes a technology demonstration of Space Station heat load and temperature requirements through the design, fabrication, and testing of breadboard and preprototype units. A parametric analysis was conducted to determine trapezoidal groove geometries that could meet the transport performance goal and could be fabricated by available extrusion technology for a diameter chosen to be compatible with an existing development test unit of a cylindrical, pressure-actuated contact heat exchanger. Performance test results for the breadboard heat pipes are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-1342
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Space Station thermal management system development status and plans (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The manned Space Station, as currently designed, contains a baseline thermal management system (TMS) which uses components and subsystems never before employed in manned spacecraft. The basis for the technology used in the TMS design is the result of a long-term TMS Technology Development Plan which was initiated in 1979. Rankin and Marshall (1983) have discussed the history and progress of that plan from its beginnings to early 1983. The present paper is concerned with the status of activities conducted at the NASA Lyndon B. Johnson Space Center (JSC) under this plan since 1983, taking into account also a summary of activities planned for the next several years.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 851350
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Honeycomb panel heat pipe development for space radiators (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An assessment of the honeycomb panel heat pipe concept as a moderate temperature range, low-mass, highly efficient radiator fin for the NASA Space Station is presented, based on test results for a thin-wall (0.46 mm) all-welded stainless steel sample with core depth of 63.5 mm and a hexagonal-cell size of 127.7 mm. The 0.61 x 3.05 m test segment, operating with methanol as a working fluid, exhibited a maximum heat transfer rate of 600 W at 50 C and was isothermal to within + or - 2 C almost entirely throughout the surface. Tilt testing, which comprised relocation of the heater along one edge of the panel, resulted in maximum power levels of 70 and 50 W at panel elevations of 12.7 and 25.4 mm, respectively. As-designed panel performance is predicted to be from 500 to 1000 W over the range of operating temperatures; better performance is predicted for an open-channel design.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 85-0978
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Integration and flight demonstration of a high-capacity monogroove heat-pipe radiator (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The cancellation of the TDRS-B satellite as the payload for the eighth Space Shuttle mission provided a unique opportunity to demonstrate on-orbit operation of the high-capacity monogroove heat pipe used in the space constructible radiator subsystem. In less than 4 months, a flight experiment was conceived, designed, fabricated, tested, integrated with a payload carrier, installed in the Orbiter Challenger payload bay, and successfully operated in flight. Still color photographs and direct crew visual observation of color changes in a pattern of temperature-sensitive liquid-crystal tapes provided the temperature data necessary to verify successful on-orbit startup and orbital transient response of the heat pipe when subjected to a heat load from its attached electrical heaters. This successful on-orbit demonstration verified analytical design tools and provided confidence in the use of high-capacity heat pipes for future space applications. The flight experiment hardware and the integration and test activities that led to the flight are described, and the actual flight results are compared to analytical performance predictions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 84-1716
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Orbiter radiator panel solar focusing test (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Test data are presented which define the area around the Orbiter radiator panels for which the solar reflections are concentrated to one-sun or more. The concave shape of the panels and their specular silver/Teflon coating causes focusing of the reflected solar energy which could have adverse heating effects on equipment or astronaut extravehicular activity (EVA) in the vicinity of the radiator panels. A room ambient test method was utilized with a one-tenth scale model of the radiator panels.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 831125
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal management system technology development for space station applications (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A short discussion of the history to date of the NASA thermal management system technology development program is presented, and the current status of several ongoing studies and hardware demonstration tasks is reported. One element of technology that is required for long-life, high-power orbital platforms/stations that is being developed is heat rejection and a space-constructable radiator system. Aspects of this project include high-efficiency fin concepts, a heat pipe quick-disconnect device, high-capacity heat pipes, and an alternate interface heat exchanger design. In the area of heat acquisition and transport, developments in a pumped two-phase transport loop, a capillary pumped transport loop using the concept of thermal utility are reported. An example of a thermal management system concept is provided.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 831097
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Heat rejection development requirements for orbital power systems (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Long-term orbital applications in which large amounts of electrical power are generated and utilized will require waste heat rejection beyond the capabilities of existing radiator systems. Therefore, it will be necessary to develop a new concept for large orbital energy systems. This paper presents a discussion of the primary factors to be considered in the design and development of a large orbital power module heat rejection system. Specific design requirements are defined based on these factors, and a review of supporting technology in the advanced space radiator area is presented. A proposed development approach and a candidate baseline heat rejection system are then identified and discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Intersociety Energy Conversion Engineering Conference; Aug 05, 1979 - Aug 10, 1979; Boston, MA
    Format: text
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