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  • 1
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    Application of an optical data link in an airborne scanning system (1982)
    American Institute of Physics
    Details
    Publication Date: 1982-08-01
    Print ISSN: 0034-6748
    Electronic ISSN: 1089-7623
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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    Microcomputer‐controlled furnace for obtaining dynamic thermogravimetric measurements (1984)
    American Institute of Physics
    Details
    Publication Date: 1984-08-01
    Print ISSN: 0034-6748
    Electronic ISSN: 1089-7623
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 3
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    Ablation of carbonaceous materials in a hydrogen-helium arcjet flow (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Keywords: NONMETALLIC MATERIALS
    Type: AIAA Journal (ISSN 0001-1452); 22; 1491-149
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Ablation of carbonaceous materials in a hydrogen-helium arc-jet flow (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The stagnation-point ablation rates of a graphite, a carbon-carbon composite, and four carbon-phenolic materials are measured in an arc-jet wind tunnel with a 50 percent hydrogen-50 percent helium mixture as the test gas. Flow environments are determined through measurements of static and impact pressures, heat-transfer rates to a calorimeter, and radiation spectra, and through numerical calculation of the flow through the wind tunnel, spectra, and heat-transfer rates. The environments so determined are: impact pressure approximately equal to 3 atm, Mach number approximately equal to 2.1, convective heat-transfer rate approximately equal to 14 kW/sq cm, and radiative heat-transfer rate approximately equal to 7 kW/sq cm in the absence of ablation. Ablation rates are determined from the measured rates of mass loss and recession of the ablation specimens. Compared with the predicted ablation rates obtained by running RASLE and CMA codes, the measured rates are higher by about 15 percent for all tested materials.
    Keywords: NONMETALLIC MATERIALS
    Type: AIAA PAPER 83-1561
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Supporting flight data analysis for Space Shuttle Orbiter Experiments at NASA Ames Research Center (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Space Shuttle Orbiter Experiments program in responsible for collecting flight data to extend the research and technology base for future aerospace vehicle design. The Infrared Imagery of Shuttle (IRIS), Catalytic Surface Effects, and Tile Gap Heating experiments sponsored by Ames Research Center are part of this program. The paper describes the software required to process the flight data which support these experiments. In addition, data analysis techniques, developed in support of the IRIS experiment, are discussed. Using the flight data base, the techniques have provided information useful in analyzing and correcting problems with the experiment, and in interpreting the IRIS image obtained during the entry of the third Shuttle mission.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 83-1532
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Ablation of carbonaceous materials in a hydrogen-helium arc-jet flow (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stagnation-point ablation rates of a graphite, a carbon-carbon composite, and four carbon-phenolic materials are measured in an arc-jet wind tunnel with a 50% hydrogen-50% helium mixture as the test gas. Flow environments are determined through measurements of static and impact pressures, heat-transfer rates to a calorimeter, and radiation spectra, and through numerical calculation of the flow through the wind tunnel, spectra, and heat-transfer rates. The environments so determined are: impact pressure approx. 3 atm, Mach number approx. 2.1, convective heat-transfer rate approx. 14 kw/sq cm, and radiative heat-transfer rate approx. 7 kw/sq cm in the absence of ablation. Ablation rates are determined from the measured rates of mass loss and recession of the ablation specimens. Compared with the predicted ablation rates obtained by running RASLE and CMA codes, the measured rates are higher by about 15% for all tested materials.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-84346 , A-9286 , NAS 1.15:84346
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Aerothermodynamic environment and thermal protection for a Titan aerocapture vehicle (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents thermal protection system (TPS) requirements for a potential Titan aerocapture vehicle. Shock-layer solutions are obtained for a nominal trajectory through the current Titan model atmosphere. Fully laminar and fully turbulent solutions are presented along the blunted fore-cone in the windward symmetry plane of a bent-biconic vehicle. Using these solutions to define the aerothermodynamic environment, transient material-response solutions are obtained for a Galileo-type TPS with a carbon-phenolic ablator heat shield. Shock-layer results indicate that turbulent flow is the more realistic flow condition. They also show that the lengthy aerocapture heating pulse is dominated by convective heating. The TPS results show that the required insulation thickness is uniformly about 4 cm along the fore-cone because of the long heat-soak period. The total heat-shield thickness is 6.4 cm at the stagnation point, and 4.7 cm near the end of the fore-cone. These TPS requirements are greater than those presented in a previous Titan aerocapture study.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1714
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Forebody and base region real-gas flow in severe planetary entry by a factored implicit numerical method. I - Computational fluid dynamics (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new code for the simulation of full (forebody and base region) flowfields about bluff bodies in the hypersonic regime of severe planetary entry is described. The present 'maximally conservative, maximally differenced' formulation of the unsteady compressible Navier-Stokes equations for 2-D axisymmetric 3-D flow is contrasted for stability with previous formulations of Viviand, Kutler, et al, and Thomas and Lombard. Discrete metric relations peculiar to the axisymmetric finite volume formulation are presented along with a general discussion of their relations to and consequences of failure to close computational cells. A computational mesh of curvilinear coordinate topology singular in the flow regime is presented that permits aligned capturing of the major physical features of the complex flowfield.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-0065 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Supporting flight data analysis for Space Shuttle Orbiter experiments at NASA Ames Research Center (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The space shuttle orbiter experiments program is responsible for collecting flight data to extend the research and technology base for future aerospace vehicle design. The infrared imagery of shuttle (IRIS), catalytic surface effects, and tile gap heating experiments sponsored by Ames Research Center are part of this program. The software required to process the flight data which support these experiments is described. In addition, data analysis techniques, developed in support of the IRIS experiment, are discussed. Using the flight data base, the techniques provide information useful in analyzing and correcting problems with the experiment, and in interpreting the IRIS image obtained during the entry of the third shuttle mission.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-84345 , A-9289 , NAS 1.15:84345
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Galileo Probe forebody thermal protection (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Material response solutions for the forebody heat shield on the candidate 310-kg Galileo Probe are presented. A charring material ablation analysis predicts thermochemical surface recession, insulation thickness, and total required heat shield mass. Benchmark shock layer solutions provide the imposed entry heating environments on the ablating surface. Heat shield sizing results are given for a nominal entry into modeled nominal and cool-heavy Jovian atmospheres, and for two heat-shield property models. The nominally designed heat shield requires a mass of at least 126 kg and would require an additional 13 kg to survive entry into the less probable cool-heavy atmosphere. The material-property model with a 30% surface reflectance reduces these mass requirements by as much as 16%.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 81-1073 , Thermophysics Conference; Jun 23, 1981 - Jun 25, 1981; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
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