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  • 1
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    The tsunami induced by the 2003 Zemmouri earthquake (Ms-2dWus0 = 6.9, Algeria): modelling and results (2006)
    In:  Geophysical Journal International, Tokyo, Pergamon Press, vol. 166, no. 1, pp. 213-226, pp. 8043
    Details
    Publication Date: 2006
    Keywords: Tsunami(s) ; Earthquake ; Modelling ; Source parameters ; Crank-Nicolson ; numerical ; schema ; with ; a ; finite ; difference ; method ; and ; the ; Okada ; elastic ; dislocation ; theory ; for ; the ; fault ; rupture ; GJI ; Hebert ; Finite difference method ; Dislocation ; Mediterranean ; Sea, ; propagation ; modelling, ; T ; waves ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Global Positioning System ; run-up ; Site amplification
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Analysis of UAS DAA Surveillance in Fast-Time Simulations without DAA Mitigation (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: Realization of the expected proliferation of Unmanned Aircraft System (UAS) operations in the National Airspace System (NAS) depends on the development and validation of performance standards for UAS Detect and Avoid (DAA) Systems. The RTCA Special Committee 228 is charged with leading the development of draft Minimum Operational Performance Standards (MOPS) for UAS DAA Systems. NASA, as a participating member of RTCA SC-228 is committed to supporting the development and validation of draft requirements for DAA surveillance system performance. A recent study conducted using NASA's ACES (Airspace Concept Evaluation System) simulation capability begins to address questions surrounding the development of draft MOPS for DAA surveillance systems. ACES simulations were conducted to study the performance of sensor systems proposed by the SC-228 DAA Surveillance sub-group. Analysis included but was not limited to: 1) number of intruders (both IFR and VFR) detected by all sensors as a function of UAS flight time, 2) number of intruders (both IFR and VFR) detected by radar alone as a function of UAS flight time, and 3) number of VFR intruders detected by all sensors as a function of UAS flight time. The results will be used by SC-228 to inform decisions about the surveillance standards of UAS DAA systems and future requirements development and validation efforts.
    Keywords: Air Transportation and Safety
    Type: ARC-E-DAA-TN27427 , RTCA SC-228 DAA Surveillance Subgroup Meeting; Oct 22, 2015; Moffett Field, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Analysis of UAS DAA Alerting in Fast-Time Simulations without DAA Mitigation (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: Realization of the expected proliferation of Unmanned Aircraft System (UAS) operations in the National Airspace System (NAS) depends on the development and validation of performance standards for UAS Detect and Avoid (DAA) Systems. The RTCA Special Committee 228 is charged with leading the development of draft Minimum Operational Performance Standards (MOPS) for UAS DAA Systems. NASA, as a participating member of RTCA SC-228 is committed to supporting the development and validation of draft requirements for DAA alerting system performance. A recent study conducted using NASA's ACES (Airspace Concept Evaluation System) simulation capability begins to address questions surrounding the development of draft MOPS for DAA alerting systems. ACES simulations were conducted to study the performance of alerting systems proposed by the SC-228 DAA Alerting sub-group. Analysis included but was not limited to: 1) correct alert (and timeliness), 2) false alert (and severity and duration), 3) missed alert, and 4) probability of an alert type at the time of loss of well clear. The performance of DAA alerting systems when using intent vs. dead-reckoning for UAS ownship trajectories was also compared. The results will be used by SC-228 to inform decisions about the surveillance standards of UAS DAA systems and future requirements development and validation efforts.
    Keywords: Behavioral Sciences; Research and Support Facilities (Air); Air Transportation and Safety; Avionics and Aircraft Instrumentation
    Type: ARC-E-DAA-TN27428 , RTCA SC-228 DAA Surveillance Subgroup; Oct 22, 2015; Moffett Field, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Retrieval of Ocean Subsurface Particulate Backscattering Coefficient from Space-Borne CALIOP Lidar Measurement (2016)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new approach has been proposed to determine ocean subsurface particulate backscattering coefficient bbp from CALIOP 30deg off-nadir lidar measurements. The new method also provides estimates of the particle volume scattering function at the 180deg scattering angle. The CALIOP based layer-integrated lidar backscatter and particulate backscattering coefficients are compared with the results obtained from MODIS ocean color measurements. The comparison analysis shows that ocean subsurface lidar backscatter and particulate backscattering coefficient bbp can be accurately obtained from CALIOP lidar measurements, thereby supporting the use of space-borne lidar measurements for ocean subsurface studies.
    Keywords: Earth Resources and Remote Sensing; Oceanography
    Type: NF1676L-25398 , Journal of Optics Express (e-ISSN 1094-4087); 24; 25; 29001-29008
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Assessment of Satellite-Derived Surface Reflectances by NASA's CAR Airborne Radiometer over Railroad Valley, Nevada (2017)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: CAR (Cloud Absorption Radiometer) is a multi-angular and multi-spectral airborne radiometer instrument, whose radiometric and geometric characteristics are well calibrated and adjusted before and after each flight campaign. CAR was built by NASA (National Aeronautics and Space Administration) in 1984. On 16 May 2008, a CAR flight campaign took place over the well-known calibration and validation site of Railroad Valley in Nevada (38.504 deg N, 115.692 deg W).The campaign coincided with the overpasses of several key EO (Earth Observation) satellites such as Landsat-7, Envisat and Terra. Thus, there are nearly simultaneous measurements from these satellites and the CAR airborne sensor over the same calibration site. The CAR spectral bands are close to those of most EO satellites. CAR has the ability to cover the whole range of azimuth view angles and a variety of zenith angles depending on altitude and, as a consequence, the biases seen between satellite and CAR measurements due to both unmatched spectral bands and unmatched angles can be significantly reduced. A comparison is presented here between CARs land surface reflectance (BRF or Bidirectional Reflectance Factor) with those derived from Terra/MODIS (MOD09 and MAIAC), Terra/MISR, Envisat/MERIS and Landsat-7. In this study, we utilized CAR data from low altitude flights (approx. 180 m above the surface) in order to minimize the effects of the atmosphere on these measurements and then obtain a valuable ground-truth data set of surface reflectance. Furthermore, this study shows that differences between measurements caused by surface heterogeneity can be tolerated, thanks to the high homogeneity of the study site on the one hand, and on the other hand, to the spatial sampling and the large number of CAR samples. These results demonstrate that satellite BRF measurements over this site are in good agreement with CAR with variable biases across different spectral bands. This is most likely due to residual aerosol effects in the EO derived reflectances.
    Keywords: Earth Resources and Remote Sensing
    Type: GSFC-E-DAA-TN45201 , Remote Sensing (e-ISSN 2072-4292); 9; 6; 562
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Round Trip Review Process Improvement (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-04
    Description: No abstract available
    Keywords: Computer Programming and Software
    Type: M19-7744 , RAM/ Defense Acquisition University Society of Reliability Engineers; Nov 13, 2019 - Nov 14, 2019; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Repurposing Traceability (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-04
    Description: No abstract available
    Keywords: Social and Information Sciences (General)
    Type: M19-7743 , RAM XII Training Summit; Nov 13, 2019 - Nov 14, 2019; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Deep Space Network Antenna Logic Controller (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The Antenna Logic Controller (ALC) software controls and monitors the motion control equipment of the 4,000-metric-ton structure of the Deep Space Network 70-meter antenna. This program coordinates the control of 42 hydraulic pumps, while monitoring several interlocks for personnel and equipment safety. Remote operation of the ALC runs via the Antenna Monitor & Control (AMC) computer, which orchestrates the tracking functions of the entire antenna. This software provides a graphical user interface for local control, monitoring, and identification of faults as well as, at a high level, providing for the digital control of the axis brakes so that the servo of the AMC may control the motion of the antenna. Specific functions of the ALC also include routines for startup in cold weather, controlled shutdown for both normal and fault situations, and pump switching on failure. The increased monitoring, the ability to trend key performance characteristics, the improved fault detection and recovery, the centralization of all control at a single panel, and the simplification of the user interface have all reduced the required workforce to run 70-meter antennas. The ALC also increases the antenna availability by reducing the time required to start up the antenna, to diagnose faults, and by providing additional insight into the performance of key parameters that aid in preventive maintenance to avoid key element failure. The ALC User Display (AUD) is a graphical user interface with hierarchical display structure, which provides high-level status information to the operation of the ALC, as well as detailed information for virtually all aspects of the ALC via drill-down displays. The operational status of an item, be it a function or assembly, is shown in the higher-level display. By pressing the item on the display screen, a new screen opens to show more detail of the function/assembly. Navigation tools and the map button allow immediate access to all screens.
    Keywords: Man/System Technology and Life Support
    Type: NPO-44341 , NASA Tech Briefs, September 2007; 48-49
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Second Generation Prototype Design and Testing for a High Altitude Venus Balloon (2008)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the development of a second generation prototype balloon intended for flight in the upper atmosphere of Venus. The design of this new prototype incorporates lessons learned from the construction and testing of the first generation prototype, including finite element analyses of the balloon stresses and deformations, measured leak performance after handling and packaging, permeability and optical property measurements on material samples, and sulfuric acid testing. An improved design for the second generation prototype was formulated based on these results, although the spherical shape and 5.5 m diameter size were retained. The resulting balloon has a volume of 87 cubic meters and is capable of carrying a 45 kg payload at a 55 km altitude at Venus. The design and fabrication of the new prototype is described, along with test data for inflation and leakage performance.
    Keywords: Spacecraft Design, Testing and Performance; Lunar and Planetary Science and Exploration
    Type: Scientific Assembly of the Committee on Space Research and Associated Events (COSPAR 2008); Jul 13, 2008 - Jul 20, 2008; Montreal; Canada
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Balloon for Long-Duration, High-Altitude Flight at Venus (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A document describes a 5.5-m-diameter, helium-filled balloon designed for carrying a scientific payload having a mass of 44 kg for at least six days at an altitude of about 55 km in the atmosphere of Venus. The requirement for floating at nearly constant altitude dictates the choice of a mass-efficient spherical super-pressure balloon that tracks a constant atmospheric density. Therefore, the balloon is of a conventional spherical super-pressure type, except that it is made of materials chosen to minimize solar radiant heating and withstand the corrosive sulfuric acid aerosol of the Venusian atmosphere. The shell consists of 16 gores of a multilayer composite material. The outer layer, made of polytetrafluoroethylene, protects against sulfuric acid aerosol. Next is an aluminum layer that reflects sunlight to minimize heating, followed by an aluminized polyethylene terephthalate layer that resists permeation by helium, followed by an aromatic polyester fabric that imparts strength to withstand deployment forces and steady super-pressure. A polyurethane coat on the inner surface of the fabric facilitates sealing at gore-to-gore seams. End fittings and seals, and a tether connecting the end fittings to a gondola, are all made of sulfuric-acid-resistant materials.
    Keywords: Man/System Technology and Life Support
    Type: NPO-43852 , NASA Tech Briefs, April 2007; 29
    Format: application/pdf
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