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  • 1
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    Spectral characteristics of Shuttle glow (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The glowing cloud near the ram surfaces of the Space Shuttle was observed with a hand-held, intensified spectrograph operated by the astronauts from the aft-flight-deck of the Space Shuttle. The spectral measurements were made between 400 and 800 nm with a resolution of 3 nm. Analysis of the spectral response of the instrument and the transmission of the Shuttle window was performed on orbit using earth-airglow OH Meinel bands. This analysis resulted in a correction of the Shuttle glow intensity in the spectral region between 700 and 800 nm. The data presented in this report is in better agreement with laboratory measurements of the NO2 continuum.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Geophysical Research Letters (ISSN 0094-8276); 19; 12, J
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  • 2
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    Spectrographic observation at wavelengths near 630 nm of the interaction between the atmosphere and the Space Shuttle exhaust (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The interaction between the Space Shuttle exhaust and the ambient atmosphere was studied using spectra in the wavelength region near 630 nm, obtained from the Air Force Maui Optical Station were the temporal, spatial, and spectral distribution of the emission in this region was recorded. The results show that, when the Space Shuttle exhaust gases interact with the atmosphere in the ram direction, an intense long-lasting emission is generated at 630 nm due to O(1D - 3P). A substantial amount of O(1D) is swept back onto the orbiter. Two processes responsible for the formation of O(1D) are proposed.
    Keywords: GEOPHYSICS
    Type: Journal of Geophysical Research (ISSN 0148-0227); 97; A12; p. 19,501-19,508.
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  • 3
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    The current status and future upgrade of the PDS at the Royal Greenwich Observatory (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Various aspects of the performance of the PDS 1010A microdensitometer are described. The primary points in an upgrade propsal for the unit are outlined. Photometric instabilities in the PDS are mentioned.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Astron. Microdensitometry Conf.; p 129-134
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  • 4
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    Prediction of spacecraft potentials at geosynchronous orbit (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Two relatively straightforward techniques are outlined for determining spacecraft potentials in the limit of a 'thick sheath' surrounding the spacecraft. A statistical model of the various features of the geosynchronous environment based on ATS-5 and ATS-6 data and an analytic model capable of detailed simulation of the low energy geosynchronous environment are also discussed. The results from these two environmental models are then combined with the charging models in order to provide estimates of the relationships between the geomagnetic index and spacecraft potential. The results are compared with actual potential measurements from ATS-5 and ATS-6.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 104-118
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  • 5
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    O(1)S 557.7nm and O(1)D 630 nm emissions in shuttle thruster plumes (1995)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Radiation resulting from interaction between the effluent cloud of a space shuttle thruster and the ambient atmosphere was observed with a spectograph aboard the shutttle. The spectral measurements were made between 400 and 800 nm with a resolutoion of 3 nm. The primary emissions are identified as NO2, HNO, O(1)D, and O(1)S. These are the first observations od O(1)S emission in the shuttle plume. These data are compared with the previous measurements, and possible excitation mechanisms are discussed. The results are also compared with a Monte Carlo simulation of thruster plume-atmosphere interaction radiation.
    Keywords: GEOPHYSICS
    Type: Journal of Geophysical Research (ISSN 0148-0227); 100; A4; p. 5819-5825
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  • 6
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    Visible light emission excited by interaction of Space Shuttle exhaust with the atmosphere (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Ground-based video photography of firings of Space Shuttle Primary Reaction Control System (PRCS) engines show optical emissions extending nearly 4 km form the vehicle after steady state is reached. The total intensity and spatial distribution of these emissions depend on the angle between the spacecraft velocity vector and the engine exhaust axis. Candidate sources for this radiation are reviewed and the conclusion is reached that it is most likely due to vibrationally excited OH, formed by the reaction of fast ambient O atoms and H2O molecules in the exhaust.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Geophysical Research Letters (ISSN 0094-8276); 17; 2205-220
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  • 7
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    Photometric analysis of a space shuttle water venting (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Presented here is a preliminary interpretation of a recent experiment conducted on Space Shuttle Discovery (Mission STS 29) in which a stream of liquid supply water was vented into space at twilight. The data consist of video images of the sunlight-scattering water/ice particle cloud that formed, taken by visible light-sensitive intensified cameras both onboard the spacecraft and at the AMOS ground station near the trajectory's nadir. This experiment was undertaken to study the phenomenology of water columns injected into the low-Earth orbital environment, and to provide information about the lifetime of ice particles that may recontact Space Shuttle orbits later. The findings about the composition of the cloud have relevance to ionospheric plasma depletion experiments and to the dynamics of the interaction of orbiting spacecraft with the environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Lyndon B. Johnson Space Center, Fourth Annual Workshop on Space Operations Applications and Research (SOAR 90); p 676-680
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  • 8
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    Interactions measurement payload for Shuttle (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Interactions Measurement Payload for Shuttle (IMPS) consisted of engineering experiments to determine the effects of the space environment on projected Air Force space systems. Measurements by IMPS on a polar-orbit Shuttle flight will lead to detailed knowledge of the interaction of the low-altitude polar-auroral environment on materials, equipment and technologies to be used in future large, high-power space systems. The results from the IMPS measurements will provide direct input to MIL-STD design guidelines and test standards that properly account for space-environment effects.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Environ. Interactions Technol., 1983; p 609-618
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  • 9
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    Origin of the Shuttle glow (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: On a recent Shuttle mission four gases, NO, CO2, Xe, and Ne were released for a plasma experiment. Unintentionally, enough gas was scattered onto the surfaces of the Shuttle tail that when NO was released a much more intense version of Shuttle glow was observed. The other gases did not affect the normal Shuttle glow. Under normal conditions the adsorbed NO that causes the glow probably come either from the ambient atmosphere or from reactions in exhaust gases from the Shuttle thrusters.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Nature (ISSN 0028-0836); 354; 48-50
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  • 10
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    Proceedings of the Spacecraft Charging Technology Conference: Executive Summary (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Aerospace environments are reviewed in reference to spacecraft charging. Modelling, a theoretical scheme which can be used to describe the structure of the sheath around the spacecraft and to calculate the charging currents within, is discussed. Materials characterization is considered for experimental determination of the behavior of typical spacecraft materials when exposed to simulated geomagnetic substorm conditions. Materials development is also examined for controlling and minimizing spacecraft charging or at least for distributing the charge in an equipotential manner, using electrical conductive surfaces for materials exposed to space environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Res. Center Proc. of the Spacecraft Charging Technol. Conf.; p 9-20
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