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  • 1
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    Decoupling of heat generated from ejected and non-ejected contents of 18650-format lithium-ion cells using statistical methods (2019)
    Elsevier
    Details
    Publication Date: 2019-03-01
    Print ISSN: 0378-7753
    Electronic ISSN: 1873-2755
    Topics: Electrical Engineering, Measurement and Control Technology
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Evaluation of Oxygen Interactions with Materials 3: Mission and induced environments (1995)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Evaluation of Oxygen Interactions with Materials 3 (EOIM-3) flight experiment was developed to obtain benchmark atomic oxygen/material reactivity data. The experiment was conducted during Space Shuttle mission 46 (STS-46), which flew July 31 to August 7, 1992. Quantitative interpretation of the materials reactivity measurements requires a complete and accurate definition of the space environment exposure, including the thermal history of the payload, the solar ultraviolet exposure, the atomic oxygen fluence, and any spacecraft outgassing contamination effects. The thermal history of the payload was measured using twelve thermocouple sensors placed behind selected samples and on the EOIM-3 payload structure. The solar ultraviolet exposure history of the EOIM-3 payload was determined by analysis of the as-flown orbit and vehicle attitude combined with daily average solar ultraviolet and vacuum ultraviolet (UV/VUV) fluxes. The atomic oxygen fluence was assessed in three different ways. First, the O-atom fluence was calculated using a program that incorporates the MSIS-86 atmospheric model, the as-flown Space Shuttle trajectory, and solar activity parameters. Second, the oxygen atom fluence was estimated directly from Kapton film erosion. Third, ambient oxygen atom measurements were made using the quadrupole mass spectrometer on the EOIM-3 payload. Our best estimate of the oxygen atom fluence as of this writing is 2.3 +/- 0.3 x 10(exp 20) atoms/sq cm. Finally, results of post-flight X-ray photoelectron spectroscopy (XPS) surface analyses of selected samples indicate low levels of contamination on the payload surface.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: NASA. Langley Research Center, LDEF: 69 Months in Space. Third Post-Retrieval Symposium, Part 3; p 903-916
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Heavy-lift vehicle-launched Space Station method and apparatus (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Methods and apparatus are provided for a single heavy-lift launch to place a complete, operational space station on-orbit. A payload including the space station takes the place of a shuttle orbiter using the launch vehicle of the shuttle orbiter. The payload includes a forward shroud, a core module, a propulsion module, and a transition module between the core module and the propulsion module. The essential subsystems are preintegrated and verified on Earth. The core module provides means for attaching international modules with minimum impact to the overall design. The space station includes six control moment gyros for selectably operating in either LVLH (local-vertical local-horizontal) or SI (solar inertial) flight modes.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Method for the calculation of spacecraft umbra and penumbra shadow terminator points (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method for calculating orbital shadow terminator points is presented. The current method employs the use of an iterative process which is used for an accurate determination of shadow points. This calculation methodology is required since orbital perturbation effects can introduce large errors when a spacecraft orbits a planet in a high altitude and/or highly elliptical orbit. To compensate for the required iteration methodology, all reference frame change definitions and calculations are performed with quaternions. Quaternion algebra significantly reduces the computational time required for the accurate determination of shadow terminator points.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-TP-3547 , S-800 , NAS 1.60:3547
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Spacecraft Crew Cabin Condensation Control (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A report discusses a new technique to prevent condensation on the cabin walls of manned spacecraft exposed to the cold environment of space, as such condensation could lead to free water in the cabin. This could facilitate the growth of mold and bacteria, and could lead to oxidation and weakening of the cabin wall. This condensation control technique employs a passive method that uses spacecraft waste heat as the primary wallheating mechanism. A network of heat pipes is bonded to the crew cabin pressure vessel, as well as the pipes to each other, in order to provide for efficient heat transfer to the cabin walls and from one heat pipe to another. When properly sized, the heat-pipe network can maintain the crew cabin walls at a nearly uniform temperature. It can also accept and distribute spacecraft waste heat to maintain the pressure vessel above dew point.
    Keywords: Man/System Technology and Life Support
    Type: MSC-24526-1 , NASA Tech Briefs, April 2013; 35
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Improvements to Wire Bundle Thermal Modeling for Ampacity Determination (2017)
    In:  CASI
    Details
    Publication Date: 2019-08-03
    Description: Abstract - Determining current carrying capacity (ampacity) of wire bundles in aerospace vehicles is critical not only to safety but also to efficient design. Published standards provide guidance on determining wire bundle ampacity but offer little flexibility for configurations where wire bundles of mixed gauges and currents are employed with various external insulation jacket surface properties. Thermal modeling has been employed in an attempt to develop techniques to assist in ampacity determination for these complex configurations. An earlier tool allowed analysis of wire bundle configurations but was constrained to configurations comprised of less than 50 elements. Additionally, for vacuum analyses, configurations with very low emittance external jackets suffered from numerical instability in the solution. A new thermal modeler is presented allowing for larger configurations and is not constrained by low bundle jacket surface infrared emittance calculations. Formulation of key internal radiation and interface conductance parameters is discussed including the effects of temperature and ambient air pressure on wire-to-wire thermal conductance. Test cases comparing model-predicted ampacity and that calculated from standards documents are presented.
    Keywords: Electronics and Electrical Engineering
    Type: NF1676L-27588 , Journal of Fluid Flow, Heat and Mass Transfer (JFFHMT) (ISSN 2368-6111); 4; 47-53
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Status and Preliminary Results for the Large Format Fractional Thermal Runaway Calorimeter (L-FTRC) (2019)
    In:  CASI
    Details
    Publication Date: 2019-11-27
    Description: Final document is attached. Status and preliminary results for the development of a large format fractional thermal runaway calorimeter (L-FTRC) capable of measuring the total energy release and fractional energy release for Li-ion cells that have greater than 100 Ah capacities.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-E-DAA-TN75665 , NASA Aerospace Battery Workshop; Nov 19, 2019 - Nov 21, 2019; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Space Shuttle Debris Impact Tool Assessment Using the Modern Design of Experiments (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Complex computer codes are used to estimate thermal and structural reentry loads on the Shuttle Orbiter induced by ice and foam debris impact during ascent. Such debris can create cavities in the Shuttle Thermal Protection System. The sizes and shapes of these cavities are approximated to accommodate a code limitation that requires simple "shoebox" geometries to describe the cavities -- rectangular areas and planar walls that are at constant angles with respect to vertical. These approximations induce uncertainty in the code results. The Modern Design of Experiments (MDOE) has recently been applied to develop a series of resource-minimal computational experiments designed to generate low-order polynomial graduating functions to approximate the more complex underlying codes. These polynomial functions were then used to propagate cavity geometry errors to estimate the uncertainty they induce in the reentry load calculations performed by the underlying code. This paper describes a methodological study focused on evaluating the application of MDOE to future operational codes in a rapid and low-cost way to assess the effects of cavity geometry uncertainty.
    Keywords: Space Transportation and Safety
    Type: AIAA Paper 2007-0550 , 45th AIAA Aerospace Sciences Meeting and Exhibit; Jan 08, 2007 - Jan 11, 2007; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A Physics-Based Temperature Stabilization Criterion for Thermal Testing (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft testing specifications differ greatly in the criteria they specify for stability in thermal balance tests. Some specify a required temperature stabilization rate (the change in temperature per unit time, dT/dt), some specify that the final steady-state temperature be approached to within a specified difference, delta T , and some specify a combination of the two. The particular values for temperature stabilization rate and final temperature difference also vary greatly between specification documents. A one-size-fits-all temperature stabilization rate requirement does not yield consistent results for all test configurations because of differences in thermal mass and heat transfer to the environment. Applying a steady-state temperature difference requirement is problematic because the final test temperature is not accurately known a priori, especially for powered configurations. In the present work, a simplified, lumped-mass analysis has been used to explore the applicability of these criteria. A new, user-friendly, physics-based approach is developed that allows the thermal engineer to determine when an acceptable level of temperature stabilization has been achieved. The stabilization criterion can be predicted pre-test but must be refined during test to allow verification that the defined level of temperature stabilization has been achieved.
    Keywords: Spacecraft Design, Testing and Performance
    Type: LF99-8634 , 25th Aerospace Testing Seminar; Oct 13, 2009 - Oct 15, 2009; Manhattan Beach, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Re-Architecting the NASA Wire Derating Approach for Space Flight Applications (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Mr. Steve Rickman, NASA Technical Fellow for Passive Thermal, proposed a pathfinder study to develop an apparatus for wire and wire bundle thermal testing to measure their performance, and to support development of thermal analytical models. Development of such capability would enable wire and wire bundle amperage capacity. The goal of this study was to assess the feasibility of developing physics-based and regression thermal models of single wires and wire bundles. This report contains the outcome of the NESC assessment.
    Keywords: Space Transportation and Safety
    Type: NASA/TM?2018-220114 , NESC-RP-17-01264 , NF1676L-31824 , L-20978
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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