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  • 1
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    Challenges in the development of the orbiter radiator system (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Major technical challenges which were met in the design and development of the Space Shuttle Orbiter Radiator System are discussed. This system rejects up to 30 kW of waste heat from eight individual radiators having a combined surface area of 175 sq m. The radiators, which are deployable, are mounted on the inside of the payload bay doors for protection from aerodynamic heating during ascent and re-entry. While in orbit the payload bay doors are opened to expose the radiators for operation. An R21 coolant loop accumulates waste heat from various components in the Orbiter and delivers the heat to the radiators for rejection to space. Specific challenges included high acoustically induced loads during lift-off, severe radiating area constraints, demanding heat load control requirements, and long life goals. Details of major design and analysis efforts are discussed. The success of the developed hardware in satisfying mission objectives showed how well the design challenge was met.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Space Shuttle Tech. Conf., Pt. 1; p 480-489
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal vacuum performance testing of the Space Shuttle Orbiter radiator system (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A space shuttle orbiter system thermal vacuum performance test was conducted at NASA-Johnson Space Center in Chamber A of the space environment simulation laboratory. The test of objective was to verify the radiator system heat rejection performance capability utilizing two development and two flight radiator panels comprising one of the two Orbiter Freon-21 coolant loops. Radiator performance over the range of expected flight conditions was as predicted, and there was no degradation of performance after extended vacuum exposure.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: The 11th Space simulation Conf.; p 305-317
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Parallel operation of aerospace static inverters. (1965)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: Parallel operation of aerospace static inverters with load division effected by locking each inverter in-phase and automatic voltage control
    Keywords: AUXILIARY SYSTEMS
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Study of Thermal Control Systems for orbiting power systems (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thermal control system designs were evaluated for the 25 kW power system. Factors considered include long operating life, high reliability, and meteoroid hazards to the space radiator. Based on a cost advantage, the bumpered pumped fluid radiator is recommended for the initial 25 kW power system and intermediate versions up to 50 kW. For advanced power systems with heat rejection rates above 50 kW the lower weight of the advanced heat pipe radiator offsets the higher cost and this design is recommended. The power system payloads heat rejection allocations studies show that a centralized heat rejection system is the most weight and cost effective approach. The thermal interface between the power system and the payloads was addressed and a concept for a contact heat exchanger that eliminates fluid transfer between the power system and the payloads was developed. Finally, a preliminary design of the thermal control system, with emphasis on the radiator and radiator deployment mechanism, is presented.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-CR-161751 , REPT-2-53020/IR-52666
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Orbiter radiator panel solar focusing test (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A test was conducted to determine the solar reflections from the Orbiter radiator panels. A one-tenth scale model of the forward and mid-forward radiator panels in the deployed position was utilized in the test. Test data was obtained to define the reflected one-sun envelope for the embossed silver/Teflon radiator coating. The effects of the double contour on the forward radiator panels were included in the test. Solar concentrations of 2 suns were measured and the one-sun envelope was found to extend approximately 86 inches above the radiator panel. A limited amount of test data was also obtained for the radiator panels with the smooth silver/Teflon coating to support the planned EVA on the Orbiter STS-5 flight. Reflected solar flux concentrations as high as 8 suns were observed with the smooth coating and the one-sun envelope was determined to extend 195 inches above the panel. It is recommended that additional testing be conducted to define the reflected solar environment beyond the one-sun boundary.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-167784 , NAS 1.26:167784 , V-2-53200/2R-53333
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Development of a contact heat exchanger for a constructable radiator system (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A development program for a contact heat exchanger to be used to transfer heat from a spacecraft coolant loop to a heat pipe radiator is described. The contact heat exchanger provides for a connectable/disconnectable joint which allows for on-orbit assembly of the radiator system and replacement or exchange of radiator panels for repair and maintenance. The contact heat exchanger does not require the transfer of fluid across the joint; the spacecraft coolant loop remains contained in an all welded system with no static or dynamic fluid seals. The contact interface is also "dry' with no conductive grease or interstitial material required.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-171730 , NAS 1.26:171730 , REPT-2-53200/3R-53490
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Shuttle active thermal control system development testing. Volume 4, Book 2: Modular radiator system test data (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N74-34343.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-140271 , TI69-28-VOL-4-BK-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Shuttle active thermal control system development testing. Volume 4, Book 1: Modular radiator system test data (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A three-week test of a modular radiator system was conducted and plots of all key data recorded during the three-week test are presented.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-140270 , TI69-28-VOL-4-BK-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Shuttle active thermal control system development testing. Volume 2: Modular radiator system tests (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were designed to investigate the validity of the "modular" approach to space radiator system design for space shuttle and future applications by gathering performance data on various systems comprised of different numbers of identical panels, subject to nominal and extreme heat loads and environments. Both one-sided and two-sided radiation was tested, and engineering data was gathered on simulated low a/e coatings and system response to changes in outlet temperature control point. The results of the testing showed system stability throughout nominal orbital transients, unrealistically skewed environments, freeze-thaw transients, and rapid changes in outlet temperature control point. Various alternative panel plumbing arrangements were tested with no significant changes in performance being observed. With the MRS panels arranged to represent the shuttle baseline system, a maximum heat rejection of 76,600 Btu/hr was obtained in segmented tests under the expected worst case design environments. Testing of an alternate smaller two-sided radiation configuration yielded a maximum heat rejection of 52,931 Btu/hr under the maximum design environments.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-140268 , T169-28-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Shuttle active thermal control system development testing. Volume 1: Overall summary (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A summary is given of a series of thermal vacuum tests designed to support the development of the orbiter active thermal control system (ATCS) and included testing of a wide heat load range modular radiator system (MRS) configured to the March 1973 orbiter baseline system, a candidate weight reducing radiator/water cooling system, and a smaller radiator system with a high performance radiator coating. The tests verified the performance of the baseline system and obtained detailed design information for application of a wide heat load range modular radiator system to the orbiter. The two candidate ATCS weight reducing designs have undergone extensive concept verification testing and their system operating characteristics have been determined in sufficient detail for application to the orbiter. Design information has been obtained for an integrated radiator/water cooling system that provides for vehicle heat rejection as well as water management of the excess fuel cell water. Processing techniques have been developed and verified for the application of a high performance thermal control coating to large radiator areas subjected to a temperature range of -280 F to +160 F.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-140267 , T169-28-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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