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  • 1
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    Thermal stability of ceramic coated thermal protection materials in a simulated high-speed earth entry (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The dimensional stability of ceramic coated thermal protection materials developed for use on advanced entry vehicles is evaluated. Dimensional stability of these ceramic materials were studied as a function of temperature and pressure during exposure to simulated atmospheric entry in an arc-jet facility.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Ceramic Engineering and Science Proceedings (ISSN 0196-6219); 9; 1199-120
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal response of integral multicomponent composites to a high-energy aerothermodynamic heating environment with surface temperature to 1800 K (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Laminated composite insulations developed for potential use on advanced spacecraft operating between GEO and LEO were tested in an aerothermodynamic environment simulating an AOTV aerobraking maneuver (altitude 82.3 km and velocity = 9.0 km/s). Comparisons are discussed between these data and predictions of in-depth temperature response using dynamical thermal conductivity values to 2000 K.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Ceramic Engineering and Science Proceedings (ISSN 0196-6219); 8; 613-625
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  • 3
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    Surface Catalysis and Characterization of Proposed Candidate TPS for Access-to-Space Vehicles (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Surface properties have been obtained on several classes of thermal protection systems (TPS) using data from both side-arm-reactor and arc-jet facilities. Thermochemical stability, optical properties, and coefficients for atom recombination were determined for candidate TPS proposed for single-stage-to-orbit vehicles. The systems included rigid fibrous insulations, blankets, reinforced carbon carbon, and metals. Test techniques, theories used to define arc-jet and side-arm-reactor flow, and material surface properties are described. Total hemispherical emittance and atom recombination coefficients for each candidate TPS are summarized in the form of polynomial and Arrhenius expressions.
    Keywords: Space Transportation
    Type: NASA-TM-112206 , NAS 1.15:112206 , A-976955
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Surface Catalytic Efficiency of Advanced Carbon Carbon Candidate Thermal Protection Materials for SSTO Vehicles (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The catalytic efficiency (atom recombination coefficients) for advanced ceramic thermal protection systems was calculated using arc-jet data. Coefficients for both oxygen and nitrogen atom recombination on the surfaces of these systems were obtained to temperatures of 1650 K. Optical and chemical stability of the candidate systems to the high energy hypersonic flow was also demonstrated during these tests.
    Keywords: Chemistry and Materials (General)
    Type: NASA-TM-110383 , A-961133 , NAS 1.15:110383
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  • 5
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    Effect of non-equilibrium flow chemistry and surface catalysis on surface heating to AFE (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effect of nonequilibrium flow chemistry on the surface temperature distribution over the forebody heat shield on the Aeroassisted Flight Experiment (AFE) vehicle was investigated using a reacting boundary-layer code. Computations were performed by using boundary-layer-edge properties determined from global iterations between the boundary-layer code and flow field solutions from a viscous shock layer (VSL) and a full Navier-Stokes solution. Surface temperature distribution over the AFE heat shield was calculated for two flight conditions during a nominal AFE trajectory. This study indicates that the surface temperature distribution is sensitive to the nonequilibrium chemistry in the shock layer. Heating distributions over the AFE forebody calculated using nonequilibrium edge properties were similar to values calculated using the VSL program.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1373
    Format: text
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  • 6
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    Effect of surface catalysis on heating to ceramic coated thermal protection systems for transatmospheric vehicles (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the effect of surface catalysis on the heat transfer rate to the heat shield of a typical Transatmospheric Vehicle (TAV) during ascent and atmospheric entry. Surface kinetics and optical properties obtained from arc-jet tests on candidate thermal protection systems (coated metals) were used in a reacting boundary layer code to estimate the heating distribution along the surface of a TAV. Thermochemical stability of the coatings is described in terms of reduction in emittance and loss of opacifiers from the coatings during the arc-jet tests.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 88-2706
    Format: text
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  • 7
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    Wall catalysis experiment on AFE (1988)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This paper describes the wall catalysis experiment which is planned as part of the Aeroassist Flight experiments (AFE) that will be flown from the Space Shuttle Orbiter in late 1993. Research on candidate high-catalytic efficiency overcoats for the experiment conducted in an arc-jet air stream are discussed. The temperature distribution over the AFE heat shield is also predicted using a reacting boundary layer solution that includes surface kinetics and optical properties determined from these tests.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: AIAA PAPER 88-2674
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  • 8
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    Nitrogen recombination on high-temperature reusable surface insulation and the analysis of its effect on surface catalysis (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The energy transfer catalytic recombination coefficients for nitrogen and oxygen on a borosilicate glass are determined in nitrogen and air hypersonic arc jet streams. These data, obtained from a reacting boundary-layer analysis with first-order surface reaction kinetics, compare well with earlier results from a Goulard frozen boundary-layer model up to 1600 K. The apparent surface recombination rates increase up to 1600 K, then begin to decrease. To illustrate the effects of temperature and nitrogen dissociation on energy transfer to the glass, a diffusional heat-flux is calculated using the present results from 1450 K up to 1850 K. This diffusional heat-flux is the contribution to the total heating rate by atom recombination, and is used to compare the present results with coefficients from three previous studies.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: AIAA PAPER 87-1637
    Format: text
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  • 9
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    Reusable Surface Insulation Tile Thermal Protection Materials: Past, Present and the Future (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Silica (LI-900) Reusable Surface Insulation (RSI) tile have been used on the majority of the Shuttle since its initial flight. Its overall performance with Reaction Cured Glass (RCG) coating applied will be reviewed. Improvements in insulations, Fibrous Refractory Composite Insulation (FRCI-12) and Alumina Enhanced Thermal Barrier (AETB-8) and coatings/surface treatments such as Toughened Uni-Piece Fibrous Insulation (TUFI) have been developed and successfully applied. The performance of these enhancements on the Shuttle Orbiters over the past few years along with the next version of tile materials, High Efficiency Tantalum-based Ceramic (HETC) with even broader applicability will also be discussed.
    Keywords: Nonmetallic Materials
    Type: 105th Annual Meeting and Exposition of the American Ceramic Society; Apr 27, 2003 - Apr 30, 2003; Nashville, TN; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Thermal Protection System Evaluation Using Arc-jet Flows: Flight Simulation or Research Tool? (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The arc-jet has been used to evaluate thermal protection systems (TPS) and materials for the past forty years. Systems that have been studied in this environmerd include ablators, active, and passive TPS concepts designed for vehicles entering planetary and Earth atmospheres. The question of whether arc-jet flow can simulate a flight environment or is it a research tool that provides an aero-thermodynamic heating environment to obtain critical material properties will be addressed. Stagnation point tests in arc-jets are commonly used to obtain material properties such as mass loss rates, thermal chemical stability data, optical properties, and surface catalytic efficiency. These properties are required in computational fluid dynamic codes to accurately predict the performance of a TPS during flight. Special facilities have been developed at NASA Ames Research Center to approximate the flow environment over the mid-fuselage and body flap regions of proposed space-planes type vehicles. This paper compares flow environments generated in flight over a vehicle with those created over an arc-jet test articles in terms of scale, chemistry, and fluid dynamic properties. Flight experiments are essential in order to validate the material properties obtained from arc-jet tests and used to predict flight performance of any TPS being considered for use on a vehicle entering the Earth atmosphere at hypersonic speed.
    Keywords: Nonmetallic Materials
    Type: 105th Annual Meeting and Exposition of the American Ceramic Society; 27-30 Apr. 203; Nashville, TN; United States
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