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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (3)
  • 1980-1984  (3)
  • 1
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    Effects of nonequilibrium and surface catalysis on Shuttle heat transfer - A review (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: It is pointed out that the Space Shuttle Orbiter is a hypersonic glide reentry vehicle which spends much of its entry time at relatively tenuous altitudes in which chemical nonequilibrium predominates in the shock layer. On the windward side, dissociation nonequilibrium exists in the inviscid layer and recombination nonequilibrium exists in the boundary layer. The present investigation is concerned with an evaluation of various flowfield predictions, taking into account a comparison of equilibrium and nonequilibrium flowfields coupled with reacting axisymmetric analog boundary-layer solutions and the results of viscous-shock-layer solutions with flight temperature/heat-flux measurements near the windward centerline for the Shuttle flights STS-2, STS-3, and STS-5.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1485
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    An AOTV aeroheating and thermal protection study (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The aerothermodynamics and thermal protection of aerobraking orbital transfer vehicles are studied with a view toward design methodology and technology requirements. A particular class of geometries is investigated: the ellipsoidally blunted raked-off elliptic cone. Discussed are the influence of various geometrical parameters on the trajectory and the heat flux as well as heating prediction methods ranging from an engineering correlation formula to computational solutions of the Navier-Stokes equations. Finite-rate catalytic thermal protection materials and gas radiation are considered. Estimates of the specific mass of possible thermal protection systems indicate that support structure is a large contributor to the aerobrake mass as compared with the thermal protection insulation itself. Sizing curves are included which enable the designer to estimate the size aerobrake required from heating considerations for different mass vehicles having aerobrakes of several specific masses.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-1710
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Space Shuttle laminar heating with finite-rate catalytic recombination (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Temperature-dependent catalytic recombination coefficients are used to calculate the heat flux to the Space Shuttle Orbiter. With variable entropy boundary-layer edge properties obtained from a reacting inviscid flow-field calculation, the reacting boundary-layer equations are solved along the forward 50 percent of the windward centerline using the boundary-layer integral matrix procedure. The results are compared with fully catalytic and noncatalytic reacting solutions, with equilibrium solutions, and with the Orbiter-design heating rates. The fully catalytic heat fluxes are about equal to the equilibrium predictions; whereas, the finite catalytic results are about 12 to 27 percent lower than the fully catalytic results (approaching the noncatalytic results downstream) and as much as 30 to 50 percent lower than design predictions away from the nose area.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-1144 , Thermophysics Conference; Jun 23, 1981 - Jun 25, 1981; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
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