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  • 1
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    Emissivity physics (1966)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Space environment effects on emissivity and optical absorption of thermal control surfaces
    Keywords: THERMODYNAMICS AND COMBUSTION
    Format: text
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  • 2
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    The Shuttle induced background - Gaseous constituents (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The gaseous environment around the Shuttle was evaluated by several instruments flown on many Shuttle flights. The major contaminant turned out to be water vapor. The rear thrusters are a major transitory source of water, N2 and/or CO, and possibly NO. Since effluent fluxes are scattered from the atmosphere into instrument faces, the angle of attack is an important variable in the flux levels.
    Keywords: SPACE TRANSPORTATION
    Type: Advances in Space Research (ISSN 0273-1177); 7; 5, 19
    Format: text
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  • 3
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    Fluorescence measurements of the thermal control experiments coatings on LDEF S0069 and A0114 (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Fluorescence measurements were made on the thermal control coatings from the Long Duration Experiment Facility (LDEF) S0069, Thermal Control Surfaces Experiment (TCSE); and the A0114, Interaction of Atomic Oxygen with Material Surfaces in Low Earth orbit. Fluorescence was observed in two types of thermal control coatings and is attributed to pigments or binders. In addition, fluorescence measurement on the silver Teflon from the front cover of TCSE led to confirmation of damage (cracking) to the metal layers during application.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA. Langley Research Center, LDEF: 69 Months in Space. Part 3: Second Post-Retrieval Symposium; p 1111-1123
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  • 4
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    Mass spectrometer (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The quadrupole Mass Spectrometer of the Induced Environment Contamination Monitor (IECM) operates in the range from 2 to 150 amu. It is pointed out that the Mass Spectrometer on STS-2 performed very well. It was found that the column density of H2O effluent from the Shuttle reached a maximum of 1 x 10 to the 13th per sq cm at 7 hr, 30 min and decreased by a factor of 7.5 during the subsequent 40 hrs. The count rate response of H2O could be correlated with mission-related events, taking into account the dumping of supply water, the operation of the Flash Evaporator System, and the firing of a primary reaction control system engine.
    Keywords: SPACE TRANSPORTATION
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  • 5
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    Results of apparent atomic oxygen reactions on Ag, C, and Os exposed during the Shuttle STS-4 orbits (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Films selected for anticipated reaction with atomic oxygen, namely carbon, silver, and osmium, were exposed during the Shuttle STS-4 mission. A silver film within 5 nm of 225 nm thick was converted to a transparent blue-green interference film within 5 nm of 355 nm thick. Both carbon and osmium films 10-30 nm thick apparently formed volatile oxides and disappeared, except where well shielded. A calculated total of approximately 7 x 10 to the 19th oxygen atoms per sq cm struck the surfaces, which could have removed on the order of 3 microns of material if only 10 percent reacted. The absence of apparent effects on adjacent thin and thick gold films is offered as evidence that sputtering is not responsible.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: Geophysical Research Letters (ISSN 0094-8276); 10; July 198
    Format: text
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  • 6
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    Space Station surface deposition monitoring (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Quartz crystal microbalance sensors are recommended to verify and monitor surface deposition on the early transverse boom as well as the later dual-keel Space Station configurations. Performance and placement of these sensors are discussed and compared to imposed maximum mass deposition rate requirements at the science instrument and critical power locations. Additional measurements are suggested to gain further knowledge on properties of the deposited material.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Space Station Induced Monitoring; p 51-57
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  • 7
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    Space station particulate contamination environment (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The origin of particulate contamination on the Space Station will mostly be from pre-launch operations. The adherence and subsequent release of these particles during space flight are discussed. Particle size, release velocity, and release direction are important in determining particle behavior in the vicinity of the vehicle. The particulate environment at the principal science instrument locations is compared to the space shuttle bay environment. Recommendations for possibly decreasing the particulate contamination are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Langley Research Center, A Study of Space Station Contamination Effects; p 71-77
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  • 8
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    Thermophysics research at MSFC (1968)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Thermophysics research review at Marshall Space Flight Center
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: RES. ACHIEVEMENTS REV., VOL. 2 1968 (SEE N69-18059 07-34)
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  • 9
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    STS-1 mission contamination evaluation approach (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The space transportation system 1 mission will be the first opportunity to assess the induced environment of the orbiter payload bay region. Two tools were developed to aid in this assessment. The shuttle payload contamination evaluation computer program was developed to provide an analytical tool for prediction of the induced molecular contamination environment of the space shuttle orbiter during its onorbit operations. An induced environment contamination monitor was constructed and tested to measure the space shuttle orbiter contamination environment inside the payload bay during ascent and descent and inside and outside the payload bay during the onorbit phase. Measurements are to be performed during the four orbital flight test series. Measurements planned for the first flight are described and predicted environmental data are discussed. The results indicate that the expected data are within the measurement range of the induced environment contamination monitor instruments evaluated, and therefore it is expected that useful contamination environmental data will be available after the first flight.
    Keywords: SPACE TRANSPORTATION
    Type: The 11th Space Simulation Conf.; p 201-215
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  • 10
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    Induced environment contamination monitor ascent/entry, optical and deposition measurements (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The induced environment contamination monitor is described. Optical and deposition measurements for ascent and descent are presented.
    Keywords: SPACE TRANSPORTATION
    Type: Systematics General Corp. The Shuttle Environ. Workshop; 15 p
    Format: application/pdf
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