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  • 1
    Publication Date: 2019-08-28
    Description: An open loop heat pipe radiator comprises a radiator tube and a free-piston. The radiator tube has a first end, a second end, and a tube wall, and the tube wall has an inner surface and an outer surface. The free-piston is enclosed within the radiator tube and is capable of movement within the radiator tube between the first and second ends. The free-piston defines a first space between the free-piston, the first end, and the tube wall, and further defines a second space between the free-piston, the second end, and the tube wall. A gaseous-state working fluid, which was evaporated to remove waste heat, alternately enters the first and second spaces, and the free-piston wipes condensed working fluid from the inner surface of the tube wall as the free-piston alternately moves between the first and second ends. The condensed working fluid is then pumped back to the heat source.
    Keywords: Fluid Mechanics and Thermodynamics
    Format: application/pdf
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  • 2
    Publication Date: 2019-07-13
    Description: The Hyper-X (X-43A) program is a flight experiment to demonstrate scramjet performance and operability under controlled powered free-flight conditions at Mach 7 and 10. The Mach 7 flight was successfully completed on March 27, 2004. Thermocouple instrumentation in the hot structures (nose, horizontal tail, and vertical tail) recorded the flight thermal response of these components. Preflight thermal analysis was performed for design and risk assessment purposes. This paper will present a comparison of the preflight thermal analysis and the recorded flight data.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Paper 109-A0016 , Fifteenth Annual Thermal and Fluids Analysis Workshop; Aug 29, 2004 - Sep 03, 2004; Pasadena, CA; United States
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  • 3
    Publication Date: 2019-07-10
    Description: The heat pipe code LERCHP has been revised, corrected, and extended. New features include provisions for pipes with curvature and bends in "G" fields. Heat pipe limits are examined in detail and limit envelopes are shown for some sodium and lithium-filled heat pipes. Refluxing heat pipes and gas-loaded or variable conductance heat pipes were not considered.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/TM-2000-209807 , E-12113 , NAS 1.15:209807
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  • 4
    Publication Date: 2019-07-13
    Description: A spacecraft's thermal protection system (TPS) is required to survive the harsh environment experienced during reentry. Accurate thermal modeling of the TPS is required to since uncertainties in the thermal response result in higher design margins and an increase in mass. The Radiant Heat Test Facility (RHTF) located at the NASA Johnson Space Center (JSC) replicates the reentry temperatures and pressures on system level full scale TPS test models for the validation of thermal math models. Reusable TPS, i.e. tile or reinforced carbon-carbon (RCC), have been the primary materials tested in the past. However, current capsule designs for MPCV and commercial programs have required the use of an ablator TPS. The RHTF has successfully completed a pathfinder program on avcoat ablator material to demonstrate the feasibility of ablator testing. The test results and corresponding ablation analysis results are presented in this paper.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: JSC-CN-39835 , AIAA Aerospace Sciences Meeting; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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