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  • 1
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    Experimental evaluation of candidate graphical microburst alert displays (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The topics addressed are: (1) experimental evaluation of candidate graphical microburst displays; (2) microburst detection and alerting; (3) previous part-task simulator experiment-comparison of presentation modes; (4) presentation mode comparison-results; (5) advantages of graphical mode of presentation; (6) graphical microburst alert experiment-objectives; and graphical microburst alert experiment-overview; and (7) candidate display design.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, Airborne Wind Shear Detection and Warning Systems. Fourth Combined Manufacturers' and Technologists' Conference, Part 2; p 879-904
    Format: application/pdf
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  • 2
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    Evaluation of iconic versus F-map microburst displays (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Previous studies have shown graphical presentation methods of hazardous wind shear to be superior to textual or audible warnings alone. Positional information and the strength of the hazard were observed to be and were cited by pilots as the most important factors in a display. In this experiment the use of the three different graphical presentations of hazardous wind shear are examined. Airborne predictive detectors of wind shear enable the dissemination of varying levels of information. The effectiveness of iconic and mapping display modes of different complexities are addressed through simulation and analysis. Different positional and time-varying situations are presented in a 'part-task' Boeing 767 simulator using data from actual microburst events. Experienced airline pilots fly approach profiles using both iconic and F-map wind shear alerting displays. Microburst accompanied each event is also shown to the pilot. Mapping display types are expected to be found exceptionally efficient at conveying location comparison information while iconic displays simplify the threat recognition process. Preliminary results from the simulator study are presented. Recommendations concerning the suitability of multilevel iconic and mapping displays are made. Situational problems with current display prototypes are also addressed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, Airborne Windshear Detection and Warning Systems. Fifth and Final Combined Manufacturers' and Technologists' Conference, Part 1; p 287-305
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  • 3
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    An investigation of air transportation technology at the Massachusetts Institute of Technology: 1993-1994 (1995)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: There are two completed projects and two continuing research activities under the sponsorship of the FAA/NASA Joint University Program as the 1993-94 period ends. There were a number of publications during the year which are referenced in this report. A brief summary of the continuing research projects is provided. The completed projects were (1) Analysis of Aircraft Surface Motion at Boston Logan International Airport and (2) A State of the Art Review and Critical Analysis of World Jet Transport Safety and Aviation Fire Safety. The active research projects are (1) ASLOTS - An Interactive Adaptive System for Automated Approach Spacing of Aircraft and (2) Alerting in Automated and Datalink Capable Cockpits.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, FAA(NASA Joint University Program for Air Transportation Research:1993-1994; p 3-15
    Format: text
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  • 4
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    Cockpit display of hazardous wind shear information (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Information on cockpit display of wind shear information is given in viewgraph form. Based on the current status of windshear sensors and candidate data dissemination systems, the near-term capabilities for windshear avoidance will most likely include: (1) Ground-based detection: TDWR (Terminal Doppler Weather Radar), LLWAS (Low-Level Windshear Alert System), Automated PIREPS; (2) Ground-Air datalinks: Air traffic control voice channels, Mode-S digital datalink, ACARS alphanumeric datalink. The possible datapaths for integration of these systems are illustrated in a diagram. In the future, airborne windshear detection systems such as lidars, passive IR detectors, or airborne Doppler radars may also become available. Possible future datalinks include satellite downlink and specialized en route weather channels.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA, Langley Research Center, Joint University Program for Air Transportation Research, 1988-1989; p 17-34
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  • 5
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    Experimental methodologies to support aircraft icing analysis (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The experimental methodologies are illustrated by graphs, charts and line drawings. Typical ultrasonic echo signals for dry and wet ice growth, ice accretion rates for various tunnel configurations, the experimental configuration for flight tests of the ultrasonic measuring system and heat balance models used to predict ice growth are among the topics that are illustrated and briefly discussed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA, Langley Research Center, Joint University Program for Air Transportation Research, 1985; p 7-25
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  • 6
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    Measurement of ice accretion using ultrasonic pulse echo techniques (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Many figures are given to illustrate the measurement of ice deposition using ultrasonic pulse echo techniques. The basic concept is to measure the thickness of the ice by relating the pulse echo time to the speed of sound. The measurements are made in an icing research tunnel (IRT), where echo patterns are videotaped during icing exposures under a variety of conditions. Typical echo patterns for different types of ice are illustrated. A table summarizing the icing rates measured in the IRT, along with the presence or absence of surface water is also given.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center Joint University Program for Air Transportation Research, 1984; p 25-41
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  • 7
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    A data fusion algorithm for multi-sensor microburst hazard assessment (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A recursive model-based data fusion algorithm for multi-sensor microburst hazard assessment is described. An analytical microburst model is used to approximate the actual windfield, and a set of 'best' model parameters are estimated from measured winds. The winds corresponding to the best parameter set can then be used to compute alerting factors such as microburst position, extent, and intensity. The estimation algorithm is based on an iterated extended Kalman filter which uses the microburst model parameters as state variables. Microburst state dynamic and process noise parameters are chosen based on measured microburst statistics. The estimation method is applied to data from a time-varying computational simulation of a historical microburst event to demonstrate its capabilities and limitations. Selection of filter parameters and initial conditions is discussed. Computational requirements and datalink bandwidth considerations are also addressed.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA. Langley Research Center, FAA(NASA Joint University Program for Air Transportation Research, 1992-1993; p 17-28
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  • 8
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    Experimental investigation of passive infrared ice detection for helicopter applications (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A technique is proposed to remotely detect rotor icing on helicopters. Using passive infrared (IR) thermometry it is possible to detect the warming caused by latent heat released as supercooled water freezes. During icing, the ice accretion region on the blade leading edge will be warmer than the uniced trailing edge resulting in a chordwise temperature profile characteristic of icing. Preliminary tests were conducted on a static model in the NASA Icing Research Tunnel for a variety of wet (glaze) and dry (rime) ice conditions. The characteristic chordwise temperature profiles were observed with an IR thermal video system and confirmed with thermocouple measurements. A prototype detector system was built consisting of a single point IR pyrometer, and experiments were run on a small scale rotor model. Again the characteristic chordwise temperature profiles were observed during icing, and the IR system was able to remotely detect icing. Based on the static and subscale rotor tests the passive IR technique is promising for rotor ice detection.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 91-0667
    Format: text
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  • 9
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    The influence of ice accretion physics on the forecasting of aircraft icing conditions (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The physics which control aircraft ice accretion are reviewed in the context of identifying and forecasting hazardous icing conditions. The severity of aircraft icing is found to be extremely sensitive to temperature, liquid water content and droplet size distribution particularly near the transition between rime and mixed icing. The difficulty in measurement and the variability of these factors with altitude, position and time coupled with variable aircraft sensitivity make forecasting and identifying icing conditions difficult. Automated Pilot Reports (PIREPS) are suggested as one mechanism for improving the data base necessary to forecast icing conditions.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA, Langley Research Center, Joint University Program for Air Transportation Research, 1988-1989; p 63-67
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  • 10
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    A passive infrared ice detection technique for helicopter applications (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique has been developed, and successfully tested, to detect icing remotely on helicopter rotor blades. Using passive infrared (IR) thermometry it is possible to detect the warming caused by latent heat released as supercooled water freezes. During icing, the ice accretion region on the leading edge of the blade is found to be warmer than the uniced trailing edge resulting in a chordwise temperature profile characteristic of icing. Preliminary tests, using an IR Thermal video system, were conducted on a static model in the NASA Icing Research Tunnel (IRT) for a variety of wet (glaze) and dry (rime) ice conditions. A prototype detector system was built consisting of a single point IR pyrometer, and experiments were run on a small scale rotor model. Using this prototype detector, the characteristic chordwise temperature profiles were again observed for a range of icing conditions. Several signal processing methods were investigated, to allow automatic recognition of the icing signature. Additionally, several implementation issues were considered. Based on both the static and subscale rotor tests, where ice was successfully detected, the passive IR technique appears to be promising for rotor ice detection.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-CR-193187 , NAS 1.26:193187 , ASL-91-4
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