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  • 1
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    The Parameters of Simple Excess Semiconductors (1951)
    Institute of Physics
    Details
    Publication Date: 1951-05-01
    Print ISSN: 0370-1298
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 2
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    On the possibility of Earth reentry simulation of shallow angle Jupiter entry (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Possible Earth reentry simulation of shallow-angle (3 to 30 deg) Jupiter entry was investigated in terms of four parameters of the bow shock layer ahead of a blunt vehicle: peak (equilibrium) temperature, peak pressure, peak inward radiative flux, and time-integrated radiative flux. It is shown that simulation ranging from fair to good can be achieved. Reentry is easiest (lowest Earth reentry speed) at steep Earth reentry, in the Earth entry speed range of 15 to 22 km/sec, for both the Jupiter nominal and cool atmospheres. Increased Earth speed is required, generally, for increasing Jupiter entry angle, and for increasing temperature, radiative flux, time-integrated flux and pressure, in that order.
    Keywords: SPACE VEHICLES
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 19-29
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Measurement of density and temperature in a hypersonic turbulent boundary layer using the electron beam fluorescence technique (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Mean density and temperature fluctuations were measured across the turbulent, cooled-wall boundary layer in a continuous hypersonic (Mach 9.4) wind tunnel in air, using the nitrogen fluorescence excited by a 50 kV electron beam. Data were taken at three values of the tunnel stagnation pressure, the corresponding free stream densities being equivalent to 1.2, 4.0, and 7.4 torr at room temperature, and the boundary layer thicknesses about 4.0, 4.5, and 6.0 inches. The mean temperature and density profiles were similar to those previously determined in the same facility by conventional probes (static and pitot pressure, total temperature). A static pressure variation of about 50% across the boundary layer was found, the shape of the variation changing somewhat for the three stagnation pressure levels. The quadrupole model for rotational temperature spectra gave closer agreement with the free stream isentropic level (approximately 44 K) than the dipole model.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-119169 , USC-53-4514-8152
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Improved electron-beam probe for hypersonic flows (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Probe uses differentially-pumped drift tube to connect high and low pressure regions thereby allowing higher gas densities to be studied. System uses higher beam voltages (50 kV) and currents (1 mA delivered to gas), and extends boundary layer penetration up to 15.2 cm, and test duration to one hour.
    Keywords: MECHANICS
    Type: NPO-13793 , NASA Tech Briefs (ISSN 0145-319X); 3; 2; P. 261
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Thin film gauge (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A thin film gauge for use in measuring distributed convective heat transfer rates occurring along given surfaces, is described. The gauge is particularly suited to measuring test surfaces in the air stream of a wind tunnel. The gauge is characterized by a plurality of painted platinum leads extend across the surface of a substrate; a pair of leads on the surface is adapted to deliver an electric current at a constant amperage through a selected thermally active area. Leads are also coupled at opposite sides of the thermally active area for detecting induced voltage drops occurring in the area so that the active length of the gauge is defined between voltage output leads. Changes in heat transfer to the thermally active area are isolated and determined by detecting induces changes in voltage drop.
    Keywords: GENERAL
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Spacecraft microbial burden reduction due to atmospheric entry heating - Jupiter. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An effort has been underway at Jet Propulsion Laboratory to develop the tools necessary to predict temperature histories for a typical spacecraft during inadvertent entry. In order that the results have general applicability, parametric analyses are performed. The thermal response of the spacecraft components and debris resulting from disintegration is determined. The temperature histories of small particles and composite materials, such as thermal blankets and an antenna, are given special attention. Guidelines are given to indicate the types of components and debris most likely to contain viable organisms, which could contaminate the lower layers of the Jovian atmosphere.
    Keywords: BIOTECHNOLOGY
    Type: Plenary Meeting on The near ultraviolet spectrum of early type stars obtained with S 59; May 23, 1973 - Jun 05, 1973; Konstanz; Germany
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Atmospheric braking to circularize an elliptical Venus orbit (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The use of atmospheric drag to circularize an elliptical spacecraft orbit at Venus is analyzed parametrically for the Venus Orbital Imaging Radar Mission (VOIR) in 1983. Navigation, maneuver, and guidance requirements are discussed for the decay of a 24-hr orbit to a close circular orbit in about 30-60 days. A prototype 'Aerobrake' is described which is approximately 5 m in diameter and 25 kg in mass and which replaces a chemical retroengine of about 1300 kg in mass (delta V = 2.5 km/s) by a 700 kg in-orbit mass. The aerobrake, a light deployable Inconel sheet, shields the spacecraft from the flow and radiates the aerodynamic heating.
    Keywords: ASTRODYNAMICS
    Type: Astrodynamics Specialist Conference; Sept. 7-9, 1977; Jackson Hole, WY; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Thermophysical and system integration considerations in aerobraking design (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aerobraking concept for decelerating spacecraft into low-energy orbits is summarized. Data and comparisons are given for aerobraking approaches to Venus, Earth, Mars, and Titan. Calculations are based on adaption of a craft similar to the Venus Orbiting Imaging Radar vehicle to an aerobraking configuration. Special attention is given to integration of the aerobraking parts into the system and protection of the craft from heat loads due to the aerobraking maneuvers.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1492 , Thermophysics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Solar probe mission status (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The penetration of coronal regions by a solar probe employing planetary gravity-assist trajectories to attain perihelia of only a few solar radii will allow unique in situ experiments to be conducted. The trajectory design options will fundamentally impact solar probe spacecraft design criteria. The aerogravity-assist method, which requires the bending of a trajectory in the vicinity of a planet by passing through a portion of its atmosphere will yield large changes in direction and velocity. This option would in the case of a solar probe mission involve the use of either the earth or Venus as a target for a specially aerodynamically configured 'waverider' spacecraft with L/D of the order of 10.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AAS PAPER 89-212 , AAS/NASA Intl. Symposium on Orbital Mechanics and Mission Design; Apr 24, 1989 - Apr 27, 1989; Greenbelt, MD; United States
    Format: text
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    NASA TECHNICAL REPORTS
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