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  • INSTRUMENTATION AND PHOTOGRAPHY  (1)
  • Quality Assurance and Reliability  (1)
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  • 1
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    Stratospheric spectroscopy with the far-infrared spectrometer (FIRS-2) - Overview and recent results (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The Smithsonian Astrophysical Observatory's program of balloon-borne stratospheric spectroscopic measurements is described, including instrumentation, recent scientific results, and future plans. The design and operation of the FIRS-2 far-infrared spectrometer is discussed. The current status of our efforts to recover mixing-ratio profiles with about 1 percent precision is presented. Representative recent results are shown giving mixing-ratio profiles from 20 to 50 km, selected from the suite HOCl, HCl, HF, NO2, N2O, HNO3, OH, HO2, H2O2, H2O (and isotopes), O2 (and isotopes), O3 (and isotopes), and CO2 (and isotopes). The utility of O2 and CO2 spectral lines for information on view angle or temperature and pressure is discussed. Future plans are mentioned, including the use of FIRS-2 on a balloon platform for UARS correlative measurements, the use of FIRS-2 on the NASA DC-8 platform for polar measurements, and the potential benefits of a FIRS instrument on a Shuttle platform.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: In: Remote sensing of atmospheric chemistry; Proceedings of the Meeting, Orlando, FL, Apr. 1-3, 1991 (A93-31376 11-35); p. 298-307.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Development of Detectability Limits for On-Orbit Inspection of Space Shuttle Wing Leading Edge (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: At the conclusion of the Columbia Accident Investigation, one of the recommendations of the Columbia Accident Investigation Board (CAIB) was that NASA develop and implement an inspection plan for the Reinforced Carbon-Carbon (RCC) system components of the Space Shuttle. To address these issues, a group of scientists and engineers at NASA Langley Research Center proposed the use of an IR camera to inspect the RCC. Any crack in an RCC panel changes the thermal resistance of the material in the direction perpendicular to the crack. The change in thermal resistance can be made visible by introducing a heat flow across the crack and using an IR camera to image the resulting surface temperature distribution. The temperature difference across the crack depends on the change in the thermal resistance, the length of the crack, the local thermal gradient, and the rate of radiation exchange with the environment. This paper describes how the authors derived the minimum thermal gradient detectability limits for a through crack in an RCC panel. This paper will also show, through the use of a transient, 3-dimensional, finite element model, that these minimum gradients naturally exist on-orbit. The results from the finite element model confirm that there are sufficient thermal gradient to detect a crack on 96% of the RCC leading edge.
    Keywords: Quality Assurance and Reliability
    Type: SPIE Defense and Security Symposium 2005; Mar 28, 2005 - Apr 01, 2005; Orlando, FL; United States
    Format: text
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    NASA TECHNICAL REPORTS
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