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  • 1
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    Seismogenesis and Earthquake Forecasting: The Frank Evison Volume I (2010)
    Basel, Boston, Berlin : Birkhäuser
    Details
    Description / Table of Contents: This special issue of Pure and Applied Geophysics is one of two volumes containing an augmented collection of papers originating from the Evison Symposium on Seismogenesis and Earthquake Forecasting held in Wellington, New Zealand, in February 2008. The volumes honor Frank Evison's interest in earthquake generation and forecasting. A biography of Frank Evison and a list of his publications is included, as well as review papers and new research papers in the field. The volume includes papers related to Frank's most abiding interest of precursory earthquake swarms. The research contributions cover a range of current forecasting methods such as the Epidemic-Type Aftershock model, the Every Earthquake a precursor According to Scale model, Pattern Informatics, Reverse Tracing of Precursors, stochastic models of elastic rebound, and methods for handling multiple precursors. The methods considered employ a variety of statistical approaches to using previous seismicity to forecast future earthquakes, including regional and global earthquake likelihood models and alarm-type forecasts. The forecast time-frames of interest range from the short time-frame associated with clustering of aftershocks to the long time-frame associated with recurrence of major earthquakes. A recurring theme is the assessment of forecasting performance, whether by likelihood scores, skill scores, error diagrams, or relative operating characteristic tests. The volume will be useful to students and professional researchers who are interested in the earthquake preparation process and in converting that understanding into forecasts of earthquake occurrence.
    Pages: Online-Ressource (250 Seiten)
    ISBN: 9783034604970
    URL: http://link.springer.com/journal/24/167/6/
    Language: English
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    E-BOOK
  • 2
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    Seismogenesis and Earthquake Forecasting: The Frank Evison Volume II (2010)
    Basel, Boston, Berlin : Birkhäuser
    Details
    Description / Table of Contents: This special issue of Pure and Applied Geophysics is the second of two volumes containing an augmented collection of papers originating from the Evison Symposium on Seismogenesis and Earthquake Forecasting held in Wellington, New Zealand, in February 2008. The volumes honor Frank Evison's interest in earthquake generation and forecasting. This volume includes descriptions of earthquake forecasting test centers through the Collaboratory for the Study of Earthquake Predictability (CSEP) program and the first results from the Regional Earthquake Likelihood Model (RELM) experiment in California. Other papers discuss methods of testing predictions, in particular by the use of error diagrams. There is discussion of prediction methodologies using seismicity, including an application of the statistical technique of Hidden Markov Models to identify changes in seismicity and a new technique for identifying precursory quiescence. Several papers employ other data besides seismicity, such as geologically determined faults, calculations of stress changes via Coulomb stress modeling, tomographically determined velocity structure, groundwater, crustal deformation, and comparisons of real earthquakes to synthetic seismicity determined from hypothesized earthquake physics. One paper focuses on the prediction of human casualties in the event that a large earthquake occurs anywhere on the globe. The volume will be useful to students and professional researchers who are interested in the earthquake preparation process and in converting that understanding into forecasts of earthquake occurrence.
    Pages: Online-Ressource (274 Seiten)
    ISBN: 9783034604994
    URL: http://link.springer.com/journal/24/167/8/
    Language: English
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    E-BOOK
  • 3
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    Behavior of aircraft antiskid braking systems on dry and wet runway surfaces: Hydromechanically controlled system (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The investigation utilized one main gear wheel, brake, and tire assembly of a McDonnell Douglas DC-9 series 10 airplane. The landing-gear strut was replaced by a dynamometer. During maximum braking, average braking behavior indexes based upon brake pressure, brake torque, and drag-force friction coefficient developed by the antiskid system were generally higher on dry surfaces than on wet surfaces. The three braking behavior indexes gave similar results but should not be used interchangeably as a measure of the braking of this antiskid sytem. During the transition from a dry to a flooded surface under heavy braking, the wheel entered into a deep skid but the antiskid system reacted quickly by reducing brake pressure and performed normally during the remainder of the run on the flooded surface. The brake-pressure recovery following transition from a flooded to a dry surface was shown to be a function of the antiskid modulating orifice.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1877 , L-14549
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Behavior of aircraft antiskid braking systems on dry and wet runway surfaces. A slip-velocity-controlled, pressure-bias-modulated system (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The braking and cornering response of a slip velocity controlled, pressure bias modulated aircraft antiskid braking system is investigated. The investigation, conducted on dry and wet runway surfaces, utilized one main gear wheel, brake, and tire assembly of a McDonnell Douglas DC 9 series 10 airplane. The landing gear strut was replaced by a dynamometer. The parameters, which were varied, included the carriage speed, tire loading, yaw angle, tire tread condition, brake system operating pressure, and runway wetness conditions. The effects of each of these parameters on the behavior of the skid control system is presented. Comparisons between data obtained with the skid control system and data obtained from single cycle braking tests without antiskid protection are examined.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1051 , L-11760
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Aircraft tire behavior during high-speed operations in soil (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation to determine aircraft tire behavior and operating problems in soil of different characteristics was conducted at the Langley landing-loads track with a 29 x 110.0-10, 8-ply-rating, type 3 tire. Four clay test beds of different moisture content and one sand test bed were used to explore the effects on axle drag loads developed during operation at different tire inflation pressures in free rolling, locked-wheel braking, and yawed (cornering) modes, all at forward speeds up to 95 knots. The test results indicated a complicated drag-load--velocity relationship, with a peak in the drag-load curve occurring near 40 knots for most test conditions. The magnitude of this peak was found to vary with tire inflation pressure and soil character and, in certain cases, might prove large enough to make take-off hazardous.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6813 , L-7641
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A transformation method for deriving from a photograph, position and heading of a vehicle in a plane (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Equations have been derived that transform perspectively viewed planar surface coordinates, as seen in a photograph, into coordinates of the original plane surface. These transformation equations are developed in terms of nine geometric variables that define the photographic setup and are redefined in terms of eight parameters. The parameters are then treated as independent quantities that fully characterize the transformation and are expressed directly in terms of the four corner coordinates of a reference rectangle in the object plane and their coordinates as seen in a photograph. Vehicle position is determined by transforming the perspectively viewed coordinate position of a representative vehicle target into runway coordinates. Vehicle heading is determined from the runway coordinates of two vehicle target points. When the targets are elevated above the plane of the reference grid, the computation of the heading angle is unaffected; however, the computation of the target position may require adjustment of two parameters. Methods are given for adjusting the parameters for elevation and an example is included for both nonelevated and elevated target conditions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TN-D-8201 , L-10411
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Design, fabrication and acoustic tests of a 36 inch (0.914 meter) statorless turbotip fan (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The LF336/E is a 36 inch (0.914 meter) diameter fan designed to operate in a rotor-alone configuration. Design features required for modification of the existing LF336/A rotor-stator fan into the LF336/E statorless fan configuration are discussed. Tests of the statorless fan identified an aerodynamic performance deficiency due to inaccurate accounting of the fan exit swirl during the aerodynamic design. This performance deficiency, related to fan exit static pressure levels, produced about a 20 percent thrust loss. A study was then conducted for further evaluation of the fan exit flow fields typical of statorless fan systems. This study showed that through proper selection of fan design variables such as pressure ratio, radius ratio, and swirl distributions, performance of a statorless fan configuration could be improved with levels of thrust approaching the conventional rotor-stator fan system. Acoustic measurements were taken for the statorless fan system at both GE and NASA, and when compared to other lift fan systems, showed noise levels comparable to the quietest lift fan configuration which included rotor-stator spacing and acoustic treatment. The statorless fan system was also used to determine effects of rotor leading edge serrations on noise generations. A cascade test program identified the serration geometry based on minimum pressure losses, wake turbulence levels and noise generations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2597 , R74AEG334
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Planar equations of rollout motion for an aircraft with free or steerable landing gears (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Equations were derived for an aircraft in a three-point attitude. Transient tire forces were simulated by delaying the application of forces derived from steady-state considerations. Predicted rollout trajectories were similar to those measured in tests of a small-scale landing-gear model equipped with pneumatic tires (where a laterally sloping runway was used to simulate a crosswind), both with and without nose-wheel steering.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1984 , L-11689 , NAS 1.60:1984
    Format: application/pdf
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  • 9
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    Dynamics of aircraft antiskid braking systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computer study was performed to assess the accuracy of three brake pressure-torque mathematical models. The investigation utilized one main gear wheel, brake, and tire assembly of a McDonnell Douglas DC-9 series 10 airplane. The investigation indicates that the performance of aircraft antiskid braking systems is strongly influenced by tire characteristics, dynamic response of the antiskid control valve, and pressure-torque response of the brake. The computer study employed an average torque error criterion to assess the accuracy of the models. The results indicate that a variable nonlinear spring with hysteresis memory function models the pressure-torque response of the brake more accurately than currently used models.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1959 , L-14788
    Format: application/pdf
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  • 10
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    Development of explosive welding techniques for fabrication of regeneratively cooled thrust chambers for large rocket engine requirements Final report, 28 Jun. 1967 - 15 Sep. 1970 (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Explosive welding techniques in fabricating regeneratively cooled thrust chambers for large rocket engine requirements including ultrasonic inspection, metallography, and burst testing
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-72878
    Format: application/pdf
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