Optimal trajectories for the aeroassisted flight experiment. Part 4: Data, tables, and graphs

NASA Technical Reports Server (NTRS)

Miele, A.; Wang, T.; Lee, W. Y.; Wang, H.; Wu, G. D.

1989-01-01

The determination of optimal trajectories for the aeroassisted flight experiment (AFE) is discussed. Data, tables, and graphs relative to the following transfers are presented: (IA) indirect ascent to a 178 NM perigee via a 197 NM apogee; and (DA) direct ascent to a 178 NM apogee. For both transfers, two cases are investigated: (1) the bank angle is continuously variable; and (2) the trajectory is divided into segments along which the bank angle is constant. For case (2), the following subcases are studied: two segments, three segments, four segments, and five segments; because the time duration of each segment is optimized, the above subcases involve four, six, eight, and ten parameters, respectively. Presented here are systematic data on a total of ten optimal trajectories (OT), five for Transfer IA and five for Transfer DA. For comparison purposes and only for Transfer IA, a five-segment reference trajectory RT is also considered.

Reliability growth modeling analysis of the space shuttle main engines based upon the Weibull process

NASA Technical Reports Server (NTRS)

Wheeler, J. T.

1990-01-01

The Weibull process, identified as the inhomogeneous Poisson process with the Weibull intensity function, is used to model the reliability growth assessment of the space shuttle main engine test and flight failure data. Additional tables of percentage-point probabilities for several different values of the confidence coefficient have been generated for setting (1-alpha)100-percent two sided confidence interval estimates on the mean time between failures. The tabled data pertain to two cases: (1) time-terminated testing, and (2) failure-terminated testing. The critical values of the three test statistics, namely Cramer-von Mises, Kolmogorov-Smirnov, and chi-square, were calculated and tabled for use in the goodness of fit tests for the engine reliability data. Numerical results are presented for five different groupings of the engine data that reflect the actual response to the failures.

jsc2014e049625

NASA Image and Video Library

2014-05-21

11-57-29-2: At the Cosmonaut Hotel crew quarters in Baikonur, Kazakhstan, Expedition 40/41 Flight Engineer Alexander Gerst of the European Space Agency takes a turn on a tilt table May 21 as he tests his vestibular system during pre-launch medical tests. Gerst, Soyuz Commander Max Suraev of the Russian Federal Space Agency (Roscosmos) and Flight Engineer Reid Wiseman of NASA will launch on May 29, Kazakh time, on the Soyuz TMA-13M spacecraft from the Baikonur Cosmodrome for a 5 ½ month mission on the International Space Station. NASA/Victor Zelentsov

A New Baseline for Chronic Fatigue: Why Measuring Flight Time Is the Wrong Approach

DTIC Science & Technology

2013-04-01

crew is shown to report fully or nearly fully effective for the following sortie despite their harrowing schedule. (Table 3) Flyawake Results...Journal of Psychology, July 1948: 13. Svan, Jennifer H. "Air Force Changes Deployments Lengths for Some 42,000 Airmen." Stars and Stripes, September 16

Potential problems relative to TDRS/IUS tilt table elevation with failed VRCS

NASA Technical Reports Server (NTRS)

Bell, J.

1980-01-01

Operational concerns and preliminary solution alternatives related to elevating the inertial upper stage/tracking and data relay satellite (IUS/TDRS) with a failed orbiter vernier reaction control system (VRCS) are presented. Problems arise from the combination of TDRS thermal constraints and tilt table constraints (the primary reaction control system (PRCS) cannot be used to hold attitude while the tilt table is being elevated), and the problems are compounded by the minimum PRCS attitude deadband. The potential solution options are affected by the launch window, flight profile, crew procedures, vehicle capability and constraints, and flight rules.

A Flight Control Approach for Small Reentry Vehicles

NASA Technical Reports Server (NTRS)

Bevacqoa, Tim; Adams, Tony; Zhu. J. Jim; Rao, P. Prabhakara

2004-01-01

Flight control of small crew return vehicles during atmospheric reentry will be an important technology in any human space flight mission undertaken in the future. The control system presented in this paper is applicable to small crew return vehicles in which reaction control system (RCS) thrusters are the only actuators available for attitude control. The control system consists of two modules: (i) the attitude controller using the trajectory linearization control (TLC) technique, and (ii) the reaction control system (RCS) control allocation module using a dynamic table-lookup technique. This paper describes the design and implementation of the TLC attitude control and the dynamic table-lookup RCS control allocation for nonimal flight along with design verification test results.

Environmental Impact Analysis Process. Draft Environmental Impact Statement, Winnersville Weapons Range, Lanier and Lowndes Counties, Georgia

DTIC Science & Technology

1985-07-01

proposed range . 54 Table 4.4. HUD site acceptability standards ... ........... .. 55 Table 4.5. Predicted pollutant emissions for flight activties...Current flight operations from Moody contribute particulatmatter, carbon monoxide, hydrocarbons, oxides of nitrogen, and oxides of sulfur to the...regional pollution levels, but because of the amounts emitted and the altitudes at which they typically occur, these emissions have only minor impact on

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms August 21, 1946 to August 22, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1946-01-01

Tables I and II of this report summarize the gust and draft velocity data for thunderstorm flights 25 and 26 of August 21, 1946 and August 22, 1946, respectively. These dta were evaluated from records of NACA instruments installed in P-61C airplanes and are of the type presented in reference 1 for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient air temperature during thunderstorm surveys. These data were read from motion-picture records of the instrument and include all cases in which variations in the instrument indications were noted during the present flights.

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes Within Thunderstorms August 14, 1946 to August 15, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1947-01-01

Tables I and II of the present paper summarize the gust and draft velocity data for thunderstorm-flights 21 and 22 of August 14, 1946 and August 15, 1946, respectively. These data were evaluated from records of NACA airspeed-altitude and acceleration recorders installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient-air temperature during thunderstorm surveys. These data were read from photo-observer records and include all cases in which variations of the instrument indications were noted for the present flights.

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: September 5, 1946 to September 10, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1947-01-01

Tables I and II of this report summarize the gust and draft velocity data for thunderstorm flights 31, 32, and 33 of September 5, 1946, September 6, 1946, and September 10, 1946, respectively. These data were evaluated from records of NACA instruments installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient air temperature during thunderstorm surveys. These data were read from motion-picture records of the instrument and include all cases in which variations in the instrument indications were noted for the present flights.

Environmental Impact Analysis Process. Draft Environmental Impact Statement, Winnersville Weapons Range, Lanier and Lowndes Counties, Georgia

DTIC Science & Technology

1985-07-01

pollutant emissions for flight activities over the proposed range (grams of pollutant per sortie)a Carbon Unburned Oxides of Particulates Oxides Aircraft...Table 4.4. HUD site acceptability standards ... ........... .. 55 Table 4.5. Predicted pollutant emissions for flight activties over the proposed range...matter, carbon monoxide, hydrocarbons, oxides of nitrogen, and oxides of sulfur to the regional pollution levels, but because of the amounts emitted and

A Cost Prediction Model for Electronic Systems Flight Test Costs.

DTIC Science & Technology

1983-09-01

development. It was found that a significant cost estimating relationship (CER) exists between costs and the characteristics of the flight test design. Using...University In Partial Fulfillment of the Requirements for the Degree of Master of Science in Systems Management By C ., Thomas 3. DuPre’, BS Accession...SYSTEMS MANAGEMENT DATE: 28 September 1983 COMMITTEE CHA. ICEAfER it TABLE OF CONTENTS Page LIST OF TABLES ......................... vi LIST OF FIGURES

The Department of Defense: Reducing Its Reliance on Fossil-Based Aviation Fuel - Issues for Congress

DTIC Science & Technology

2007-06-15

19 Figure 2. KC-135 Winglet Flight Tests at Dryden Flight Research Center . . . . 23 List of Tables Table 1...involving two or more opposing forces using rules, data, and procedures designed to depict an actual or assumed real life situation.” 19 Winglets , for...applying winglets to DOD aircraft. See page 24 of this report for further information. reflect the DOD’s true fuel costs, masks energy efficiency

14 CFR 103.23 - Flight visibility and cloud clearance requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight visibility and cloud clearance... Flight visibility and cloud clearance requirements. No person may operate an ultralight vehicle when the flight visibility or distance from clouds is less than that in the table found below. All operations in...

14 CFR 103.23 - Flight visibility and cloud clearance requirements.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Flight visibility and cloud clearance... Flight visibility and cloud clearance requirements. No person may operate an ultralight vehicle when the flight visibility or distance from clouds is less than that in the table found below. All operations in...

14 CFR 103.23 - Flight visibility and cloud clearance requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Flight visibility and cloud clearance... Flight visibility and cloud clearance requirements. No person may operate an ultralight vehicle when the flight visibility or distance from clouds is less than that in the table found below. All operations in...

14 CFR 103.23 - Flight visibility and cloud clearance requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Flight visibility and cloud clearance... Flight visibility and cloud clearance requirements. No person may operate an ultralight vehicle when the flight visibility or distance from clouds is less than that in the table found below. All operations in...

14 CFR 103.23 - Flight visibility and cloud clearance requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight visibility and cloud clearance... Flight visibility and cloud clearance requirements. No person may operate an ultralight vehicle when the flight visibility or distance from clouds is less than that in the table found below. All operations in...

Quality Attributes for Mission Flight Software: A Reference for Architects

NASA Technical Reports Server (NTRS)

Wilmot, Jonathan; Fesq, Lorraine; Dvorak, Dan

2016-01-01

In the international standards for architecture descriptions in systems and software engineering (ISO/IEC/IEEE 42010), "concern" is a primary concept that often manifests itself in relation to the quality attributes or "ilities" that a system is expected to exhibit - qualities such as reliability, security and modifiability. One of the main uses of an architecture description is to serve as a basis for analyzing how well the architecture achieves its quality attributes, and that requires architects to be as precise as possible about what they mean in claiming, for example, that an architecture supports "modifiability." This paper describes a table, generated by NASA's Software Architecture Review Board, which lists fourteen key quality attributes, identifies different important aspects of each quality attribute and considers each aspect in terms of requirements, rationale, evidence, and tactics to achieve the aspect. This quality attribute table is intended to serve as a guide to software architects, software developers, and software architecture reviewers in the domain of mission-critical real-time embedded systems, such as space mission flight software.

First Spacelab flight - A status report of the joint ESA/NASA mission

NASA Technical Reports Server (NTRS)

Craft, H. G., Jr.; Sanfourche, J.-P.

1978-01-01

A general overview of the first Spacelab flight is presented and a table is given listing the payload composition. An accommodation study is presented with emphasis on the configuration, mass status, timeline, and experiment interface specifications. Also considered are flight and ground operations, safety factors, and payload specialists training for the first flight.

14 CFR 61.411 - What aeronautical experience must I have to apply for a flight instructor certificate with a...

Code of Federal Regulations, 2010 CFR

2010-01-01

... apply for a flight instructor certificate with a sport pilot rating? 61.411 Section 61.411 Aeronautics... CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS Flight Instructors With a Sport Pilot Rating... sport pilot rating? Use the following table to determine the experience you must have for each aircraft...

14 CFR 61.411 - What aeronautical experience must I have to apply for a flight instructor certificate with a...

Code of Federal Regulations, 2011 CFR

2011-01-01

... apply for a flight instructor certificate with a sport pilot rating? 61.411 Section 61.411 Aeronautics... CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS Flight Instructors With a Sport Pilot Rating... sport pilot rating? Use the following table to determine the experience you must have for each aircraft...

Influence of Individual Experience and Flight Strips on Air Traffic Controller Memory/Situational Awareness

DTIC Science & Technology

1993-06-01

Aircraft 21 3-4 Mean Proportion Correct: Last Command Issued 22 3-5 Mean Proportion Correct: Last Altitude Change Issued 23 LIST OF TABLES Table Page 2-1...record altitude changes on strips. The same pattern of results was obtained. Participants with lower video-game experience showed poorer memory for...altitude changes than did those with higher experience, particularly when note- writing was not allowed. Flight strips may have been helpful to the group

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 24, 1946 to August 6, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, Harold B.

1947-01-01

The results obtained from gust and draft velocity measurements within thunderstorms for the period July 24, 1946 to August 6, 1946 at Orlando, Florida are presented herein. These data are summarized in tables I and II and are of the type presented in reference 1 for previous flights. In two thunderstorm traverses, indications of ambient-air temperature were obtained from photo-observer records. These data are summarized in table III.

Compatibility Flight Profile and Internal Environment Characterization for the RASCAL Pod. Project: Senior RASCAL

DTIC Science & Technology

2008-12-01

pod at increasing angles of attack. An overall vertical acceleration maximum of 7.5 g RMS occurred while in a transonic wind-up turn at 15,000 ft and...landings, level accelerations, and specific maneuver blocks of varying sideslip, load factor, and angle of attack (AOA). The flight conditions...0g 10s maximum Angle of Attack (deg) ±1 ±1 16 Table A1: Data Bands and Tolerances for the Vibroacoustic Tests Table A2 summarizes the conditions

Neck Muscle Fatigue Resulting from Prolonged Wear of Weighted Helmets

DTIC Science & Technology

2008-06-01

23 LIST OF TABLES Table 1. Subject Anthropometry ...prior to any testing (Protocol F-WR-2005-0023-H). Table 1. Subject Anthropometry Males Females Group Range Mean SD Range Mean SD...Three sizes (M, L, XL ) of the HGU-55/P flight helmet were modified to simulate either a currently operational or “in-development” helmet mounted

14 CFR 1214.107 - Postponement.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.107...) A customer postponing the flight of a payload will pay a postponement fee to NASA. The fee will be computed as a percentage of the customer's Shuttle standard flight price and will be based on the table...

14 CFR 1214.107 - Postponement.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.107...) A customer postponing the flight of a payload will pay a postponement fee to NASA. The fee will be computed as a percentage of the customer's Shuttle standard flight price and will be based on the table...

14 CFR 1214.107 - Postponement.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.107...) A customer postponing the flight of a payload will pay a postponement fee to NASA. The fee will be computed as a percentage of the customer's Shuttle standard flight price and will be based on the table...

14 CFR 1214.107 - Postponement.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.107...) A customer postponing the flight of a payload will pay a postponement fee to NASA. The fee will be computed as a percentage of the customer's Shuttle standard flight price and will be based on the table...

14 CFR § 1214.108 - Termination.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Provisions Regarding Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214... standard services to NASA. (1) The termination fee for dedicated flights will be computed as a percentage of the Shuttle standard flight price and will be based on the table below. Months before scheduled...

Lightning swept-stroke attachment patterns and flight conditions for storm hazards 1981

NASA Technical Reports Server (NTRS)

Fisher, B. D.

1984-01-01

As part of the NASA Langley Research Center Storm Hazards Program, 111 thunderstorm penetrations were made in 1981 with an F-106B airplane in order to record direct-strike lightning data and the associated flight conditions. Ground-based weather radar measurements in conjunction with these penetrations were made by NOAA National Severe Storms Laboratory in Oklahoma and by NASA Wallops Flight Facility in Virginia. In 1981, the airplane received 10 direct lightning strikes; in addition, lightning transient data were recorded from 22 nearby flashes. Following each flight, the airplane was thoroughly inspected for evidence of lightning attachment, and the individual lightning attachment points were plotted on isometric projections of the airplane to identify swept-flash patterns. This report shows the strike attachment patterns that were found, and tabulates the flight conditions at the time of each lightning event. Finally, this paper contains a table in which the data in this report are cross-referenced with the previously published electromagnetic waveform data recorded onboard the airplane.

Estimating Bird / Aircraft Collision Probabilities and Risk Utilizing Spatial Poisson Processes

DTIC Science & Technology

2012-06-10

Operations (1995-2011) ........................................... 2 Table 2 DeVault Top 15 Relative Hazard Score...dedicated bird radar (Dokter, et al. 2011). The WRS-88D is used in the Avian Hazard Advisory System which is described later in this paper. Advisory...Avian Hazard Advisory System (AHAS) is an online, near real-time, geographic information system (GIS) used for bird strike risk flight planning across

Space shuttle on-orbit flight control software requirements, preliminary version

NASA Technical Reports Server (NTRS)

1975-01-01

Software modules associated with various flight control functions for the space shuttle orbiter are described. Data flow, interface requirements, initialization requirements and module sequencing requirements are considered. Block diagrams and tables are included.

Food table on ISS

NASA Image and Video Library

2015-04-08

ISS043E091650 (04/08/2015) --- A view of the food table located in the Russian Zvezda service module on the International Space Station taken by Expedition 43 Flight Engineer Scott Kelly. Assorted food, drink and condiment packets are visible. Kelly tweeted this image along with the comment: ""Looks messy, but it's functional. Our #food table on the @space station. What's for breakfast? #YearInSpace".

STS-1 low-speed ground navigation console procedures

NASA Technical Reports Server (NTRS)

Weaver, J.

1980-01-01

The space Transportation System 1 Flight onorbit mission phase is broken into three distinct subphases; those subphases being the rev 1 through rev 6 contigency reentry opportunities, the general onorbit time period, and the rev 34 to the postdeorbit Guam pass inclusive. The necessary information to ensure that sufficient data tables are accummulated in real time to support the postmission off line ancillary data analysis studies designed to support postmission ancillary data generation and investigation of mission related anomalies is given.

Self-Contained Avionics Sensing and Flight Control System for Small Unmanned Aerial Vehicle

NASA Technical Reports Server (NTRS)

Ingham, John C. (Inventor); Shams, Qamar A. (Inventor); Logan, Michael J. (Inventor); Fox, Robert L. (Inventor); Fox, legal representative, Melanie L. (Inventor); Kuhn, III, Theodore R. (Inventor); Babel, III, Walter C. (Inventor); Fox, legal representative, Christopher L. (Inventor); Adams, James K. (Inventor); Laughter, Sean A. (Inventor)

2011-01-01

A self-contained avionics sensing and flight control system is provided for an unmanned aerial vehicle (UAV). The system includes sensors for sensing flight control parameters and surveillance parameters, and a Global Positioning System (GPS) receiver. Flight control parameters and location signals are processed to generate flight control signals. A Field Programmable Gate Array (FPGA) is configured to provide a look-up table storing sets of values with each set being associated with a servo mechanism mounted on the UAV and with each value in each set indicating a unique duty cycle for the servo mechanism associated therewith. Each value in each set is further indexed to a bit position indicative of a unique percentage of a maximum duty cycle for the servo mechanism associated therewith. The FPGA is further configured to provide a plurality of pulse width modulation (PWM) generators coupled to the look-up table. Each PWM generator is associated with and adapted to be coupled to one of the servo mechanisms.

78 FR 25523 - Acceptance of Noise Exposure Map Notice for Oakland County International Airport, Pontiac, Michigan

Federal Register 2010, 2011, 2012, 2013, 2014

2013-05-01

... Utilization, Table D5, Runway Utilization By Category of Aircraft; Figure D3, INM Flight Tracks, West Flow, Figure D4, INM Flight Tracks, East Flow. The Future NEM is located in Figure D6, Future Noise Exposure... Assumptions for Future Conditions, 2021. The Flight Tracks depicted in Figure D3, INM Flight Tracks, West Flow...

14 CFR Appendix C to Part 63 - Flight Engineer Training Course Requirements

Code of Federal Regulations, 2010 CFR

2010-01-01

... looseleaf binder to include a table of contents. If an applicant desires approval of both a ground school course and a flight school course, they must be combined in one looseleaf binder that includes a separate... include additional subjects in the ground course curriculum, such as international law, flight hygiene, or...

77 FR 50759 - Noise Exposure Map Notice, Orlando Sanford International Airport, Sanford, FL

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-22

...; Table 13: 2009 and 2016 Local Runway Use Percentages; Figure 1: East Flow Flight Tracks; Figure 2: West Flow Flight Tracks; Figure 3: Local Flight Tracks; Figure 4: Existing Land Use; Figure 5: 2011 NEM... inseparable from the ultimate land use control and planning responsibilities of local government. These local...

18. NBS SUIT LAB. OVERALL VIEW. ALL WORK TABLES WITH ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

18. NBS SUIT LAB. OVERALL VIEW. ALL WORK TABLES WITH MISCELLANEOUS SUIT COMPONENTS AND SUPPLIES. TERRY WEST TO LEFT, AND PAUL DUMBACHER TO RIGHT. - Marshall Space Flight Center, Neutral Buoyancy Simulator Facility, Rideout Road, Huntsville, Madison County, AL

LANDSAT-2 and LANDSAT-3 flight evaluation report, 23 April to 23 July 1979

NASA Technical Reports Server (NTRS)

1979-01-01

The performance of satellite subsystems and the response of in-orbit payload systems are summarized. Graphs and tables show the values of the various parameters of these systems. A spacecraft orbit reference table is included.

Analysis of structural dynamic data from Skylab. Volume 2: Skylab analytical and test model data

NASA Technical Reports Server (NTRS)

Demchak, L.; Harcrow, H.

1976-01-01

The orbital configuration test modal data, analytical test correlation modal data, and analytical flight configuration modal data are presented. Tables showing the generalized mass contributions (GMCs) for each of the thirty tests modes are given along with the two dimensional mode shape plots and tables of GMCs for the test correlated analytical modes. The two dimensional mode shape plots for the analytical modes and uncoupled and coupled modes of the orbital flight configuration at three development phases of the model are included.

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms: August 23, 1946 to September 4, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1946-01-01

This report presents the results obtained from gust and draft velocity measurements within thunderstorms for the period August 23, 1946 to September 4, 1946 at Orlando, Florida. These data are summarized in tables I end II and are of the type presented in reference 1 for previous flights. In several of the surveys, indications of ambient air temperature were obtained from photo-observer records. These data are summarized in table III.

Characterization of mustard seeds and paste by DART ionization with time-of-flight mass spectrometry.

PubMed

Prchalová, Jana; Kovařík, František; Ševčík, Rudolf; Čížková, Helena; Rajchl, Aleš

2014-09-01

Direct analysis in real time (DART) is a novel technique with great potential for rapid screening analysis. The DART ionization method coupled with high-resolution time-of-flight mass spectrometry (TOF-MS) has been used for characterization of mustard seeds and table mustard. The possibility to use DART to analyse glucosinolates was confirmed on determination of sinalbin (4-hydroxybenzyl glucosinolate). The DART-TOF-MS method was optimized and validated. A set of samples of mustard seeds and mustard products was analyzed. High-performance liquid chromatography and DART-TOF-MS were used to determine glucosinolates in mustard seeds and compared. The correlation equation between these methods was DART = 0.797*HPLC + 6.987, R(2)  = 0.972. The DART technique seems to be a suitable method for evaluation of the quality of mustard seeds and mustard products. Copyright © 2014 John Wiley & Sons, Ltd.

Towards new paradigms for the treatment of hypobaric decompression sickness.

PubMed

Dart, T S; Butler, W

1998-04-01

Altitude induced (hypobaric) decompression sickness (DCS) has long been treated with ground level oxygen and U.S. Navy Treatment Tables 5 and 6. These treatment tables originate from surface excursion diving and, when implemented, require significant resource allocation. Although they are effective treatment regimens, these tables were not developed for treating hypobaric DCS which has an etiology similar to saturation diving DCS. In this review, different treatment options for hypobaric DCS are presented. These options include more aggressive use of ground level oxygen and treatment tables using a maximum pressure of 2 atmospheres (ATA). Specific attention is given to USAF Table VIII, an experimental hypobaric DCS treatment-table, and space suit overpressurization treatment. This paradigm shift for DCS treatment is based on a projected increase in hypobaric DCS treatment from exposure to low pressure during several operational conditions: cruise flight in the next generation aircraft (e.g., F-22); high altitude, unpressurized flight by special operations forces; and the extraordinary amount of extravehicular activity (EVA) required to construct the international space station. Anticipating the need to treat DCS encountered during these and other activities, it is proposed that 2 ATA or less hyperbaric oxygen (HBO) treatment conjoined with new collapsible chamber technology can be used to address these issues in a safe and cost effective fashion.

Development and Implementation of Software for Visualizing and Editing Multidimensional Flight Simulation Input Data

NASA Technical Reports Server (NTRS)

Whelan, Todd Michael

1996-01-01

In a real-time or batch mode simulation that is designed to model aircraft dynamics over a wide range of flight conditions, a table look- up scheme is implemented to determine the forces and moments on the vehicle based upon the values of parameters such as angle of attack, altitude, Mach number, and control surface deflections. Simulation Aerodynamic Variable Interface (SAVI) is a graphical user interface to the flight simulation input data, designed to operate on workstations that support X Windows. The purpose of the application is to provide two and three dimensional visualization of the data, to allow an intuitive sense of the data set. SAVI also allows the user to manipulate the data, either to conduct an interactive study of the influence of changes on the vehicle dynamics, or to make revisions to data set based on new information such as flight test. This paper discusses the reasons for developing the application, provides an overview of its capabilities, and outlines the software architecture and operating environment.

STS-26 crewmembers participate in bench review at offsite Boeing Bldg

NASA Technical Reports Server (NTRS)

1988-01-01

STS-26 Discovery, Orbiter Vehicle (OV) 103, crewmembers participate in bench review at the offsite Boeing Building. Commander Frederick H. Hauck reviews a checklist of necessary supplies with Flight Equipment Processing engineer Laura E. Duvall. Pilot Richard O. Covey makes notations on checklist in background. Hygiene supplies (razors, deodorants, brushes, combs, etc.) are displayed on table behind Hauck. Photograph was taken by Keith Meyers of the NEW YORK TIMES.

Flight Model Discharge System.

DTIC Science & Technology

1987-04-01

will immediately remove the charge from the front surface of the dielectric and return it to ground. The 2-hour time constant network will then reset the...ATDP programs. NEWT5 permits the digitized input of board and component position data, while ATDP automates certain phases of input and output table...format. 8.5 RESULTS The system-level results are presented as curves of AR (normalized radiator area) versus THOT and as curves of Q (heater

HD-SAO-DM cross index

NASA Technical Reports Server (NTRS)

Nagy, T. A.; Mead, J.

1978-01-01

A table of correspondence SAO-HD-DM-GC was prepared by Morin (1973). The machine-readable version of this cross identification was obtained from the Centre de Donnees Stellaires (Strasbourg, France). The table was sorted at the Goddard Space Flight Center by HD number and all blank HD number records were removed to produce the HD-SAO-DM table presented. There were 258997 entries in the original table; there are 180411 entries after removing the blank HD records. The Boss General Catalogue (GC) numbers were retained on the machine-readable version after the sort.

Conversion from Engineering Units to Telemetry Counts on Dryden Flight Simulators

NASA Technical Reports Server (NTRS)

Fantini, Jay A.

1998-01-01

Dryden real-time flight simulators encompass the simulation of pulse code modulation (PCM) telemetry signals. This paper presents a new method whereby the calibration polynomial (from first to sixth order), representing the conversion from counts to engineering units (EU), is numerically inverted in real time. The result is less than one-count error for valid EU inputs. The Newton-Raphson method is used to numerically invert the polynomial. A reverse linear interpolation between the EU limits is used to obtain an initial value for the desired telemetry count. The method presented here is not new. What is new is how classical numerical techniques are optimized to take advantage of modem computer power to perform the desired calculations in real time. This technique makes the method simple to understand and implement. There are no interpolation tables to store in memory as in traditional methods. The NASA F-15 simulation converts and transmits over 1000 parameters at 80 times/sec. This paper presents algorithm development, FORTRAN code, and performance results.

Adding EUNIS and VAULT rocket data to the VSO with Modern Perl frameworks

NASA Astrophysics Data System (ADS)

Mansky, Edmund

2017-08-01

A new Perl code is described, that uses the modern Object-oriented Moose framework, to add EUNIS and VAULT rocket data to the Virtual Solar Observatory website. The code permits the easy fixing of FITS header fields in the case where some FITS fields that are required are missing from the original data files. The code makes novel use of the Moose extensions “before” and “after” to build in dependencies so that database creation of tables occurs before the loading of data, and that the validation of file-dependent tables occurs after the loading is completed. Also described is the computation and loading of the deferred FITS field CHECKSUM into the database following the loading and validation of the file-dependent tables. The loading of the EUNIS 2006 and 2007 flight data, and the VAULT 2.0 flight data is described in detail as illustrative examples.

Origin of Marshall Space Flight Center (MSFC)

NASA Image and Video Library

1959-08-11

In this picture, negotiations are under way between officials of the Army Ballistic Missile Agency (ABMA) and the National Aeronautics and Space Administration (NASA) on August 11, 1959. Seated at the table with his back to the camera, is Dr. T. Keith Glernan, NASA Administrator. At the head of the table is Major General John Barclay, Commander of ABMA and at the right side of the table are Colonel John G. Zierdt of ABMA and Dr. von Braun.

Numerical solution of Space Shuttle Orbiter flow field including real gas effects

NASA Technical Reports Server (NTRS)

Prabhu, D. K.; Tannehill, J. C.

1984-01-01

The hypersonic, laminar flow around the Space Shuttle Orbiter has been computed for both an ideal gas (gamma = 1.2) and equilibrium air using a real-gas, parabolized Navier-Stokes code. This code employs a generalized coordinate transformation; hence, it places no restrictions on the orientation of the solution surfaces. The initial solution in the nose region was computed using a 3-D, real-gas, time-dependent Navier-Stokes code. The thermodynamic and transport properties of equilibrium air were obtained from either approximate curve fits or a table look-up procedure. Numerical results are presented for flight conditions corresponding to the STS-3 trajectory. The computed surface pressures and convective heating rates are compared with data from the STS-3 flight.

14 CFR Appendix F to Part 91 - Helicopter Flight Recorder Specifications

Code of Federal Regulations, 2014 CFR

2014-01-01

.... Engine Torque Maximum Range ±5% 1 1%2. Flight Control Hydraulic Pressure Primary (Discrete) High/Low 1... greater 1 1 kt. Altitude −1,000 ft. to 20,000 ft. pressure altitude ±100 to ±700 ft. (see Table 1, TSO C51...

14 CFR Appendix F to Part 91 - Helicopter Flight Recorder Specifications

Code of Federal Regulations, 2013 CFR

2013-01-01

.... Engine Torque Maximum Range ±5% 1 1%2. Flight Control Hydraulic Pressure Primary (Discrete) High/Low 1... greater 1 1 kt. Altitude −1,000 ft. to 20,000 ft. pressure altitude ±100 to ±700 ft. (see Table 1, TSO C51...

New Approaches to Motion Cuing in Flight Simulators

DTIC Science & Technology

1991-09-01

iv Table of Contents 1.0 Introduction ............................. .......... ...... 1 1.1 The Problem of Motion Cuing in Flight Simulation...the Report ................ ................... 7 2.0 A Conceptual Model of Pilot Control .......... ............ 9 2.1 Introduction ...33 3.4 Task Analysis ................ ...................... .. 34 3.4.1 Introduction ................ ...................... 34 3.4.2 Discussion

20. NBS SUIT LAB. TABLE WITH MISCELLANEOUS SUIT PARTS AND ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

20. NBS SUIT LAB. TABLE WITH MISCELLANEOUS SUIT PARTS AND TERRY WEST, A SPACE SUIT ASSEMBLY TECHNICIAN LOGGING SUIT PART DATA. PARTS ON THE TABLE ARE A HARD UPPER TORSO (HUT) (REAR LEFT), FULL HELMET (FRONT LEFT), TWO HELMETS WITHOUT PROTECTIVE VISORS, A PAIR OF GLOVES, AND A BACKPACK WITHOUT VOLUMETRIC COVER (REAR RIGHT). THE BACKPACK ATTACHES TO THE HUT TO MAKE-UP THE UPPER TORSO COMPONENTS OF THE SUIT. - Marshall Space Flight Center, Neutral Buoyancy Simulator Facility, Rideout Road, Huntsville, Madison County, AL

Toward Real Time Neural Net Flight Controllers

NASA Technical Reports Server (NTRS)

Jorgensen, C. C.; Mah, R. W.; Ross, J.; Lu, Henry, Jr. (Technical Monitor)

1994-01-01

NASA Ames Research Center has an ongoing program in neural network control technology targeted toward real time flight demonstrations using a modified F-15 which permits direct inner loop control of actuators, rapid switching between alternative control designs, and substitutable processors. An important part of this program is the ACTIVE flight project which is examining the feasibility of using neural networks in the design, control, and system identification of new aircraft prototypes. This paper discusses two research applications initiated with this objective in mind: utilization of neural networks for wind tunnel aircraft model identification and rapid learning algorithms for on line reconfiguration and control. The first application involves the identification of aerodynamic flight characteristics from analysis of wind tunnel test data. This identification is important in the early stages of aircraft design because complete specification of control architecture's may not be possible even though concept models at varying scales are available for aerodynamic wind tunnel testing. Testing of this type is often a long and expensive process involving measurement of aircraft lift, drag, and moment of inertia at varying angles of attack and control surface configurations. This information in turn can be used in the design of the flight control systems by applying the derived lookup tables to generate piece wise linearized controllers. Thus, reduced costs in tunnel test times and the rapid transfer of wind tunnel insights into prototype controllers becomes an important factor in more efficient generation and testing of new flight systems. NASA Ames Research Center is successfully applying modular neural networks as one way of anticipating small scale aircraft model performances prior to testing, thus reducing the number of in tunnel test hours and potentially, the number of intermediate scaled models required for estimation of surface flow effects.

Interface Supports Lightweight Subsystem Routing for Flight Applications

NASA Technical Reports Server (NTRS)

Lux, James P.; Block, Gary L.; Ahmad, Mohammad; Whitaker, William D.; Dillon, James W.

2010-01-01

A wireless avionics interface exploits the constrained nature of data networks in flight systems to use a lightweight routing method. This simplified routing means that a processor is not required, and the logic can be implemented as an intellectual property (IP) core in a field-programmable gate array (FPGA). The FPGA can be shared with the flight subsystem application. In addition, the router is aware of redundant subsystems, and can be configured to provide hot standby support as part of the interface. This simplifies implementation of flight applications requiring hot stand - by support. When a valid inbound packet is received from the network, the destination node address is inspected to determine whether the packet is to be processed by this node. Each node has routing tables for the next neighbor node to guide the packet to the destination node. If it is to be processed, the final packet destination is inspected to determine whether the packet is to be forwarded to another node, or routed locally. If the packet is local, it is sent to an Applications Data Interface (ADI), which is attached to a local flight application. Under this scheme, an interface can support many applications in a subsystem supporting a high level of subsystem integration. If the packet is to be forwarded to another node, it is sent to the outbound packet router. The outbound packet router receives packets from an ADI or a packet to be forwarded. It then uses a lookup table to determine the next destination for the packet. Upon detecting a remote subsystem failure, the routing table can be updated to autonomously bypass the failed subsystem.

14 CFR 91.125 - ATC light signals.

Code of Federal Regulations, 2014 CFR

2014-01-01

... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Flight Rules General § 91.125 ATC light signals. ATC light signals have the meaning shown in the following table: Color and type of signal Meaning... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false ATC light signals. 91.125 Section 91.125...

14 CFR Appendix E to Part 417 - Flight Termination System Testing and Analysis

Code of Federal Regulations, 2012 CFR

2012-01-01

... contains requirements for tests and analyses that apply to all flight termination systems and the... termination system components that satisfy the requirements of this appendix. (b) Component tests and analyses. A component must satisfy each test or analysis required by any table of this appendix to demonstrate...

14 CFR Appendix E to Part 417 - Flight Termination System Testing and Analysis

Code of Federal Regulations, 2010 CFR

2010-01-01

... contains requirements for tests and analyses that apply to all flight termination systems and the... termination system components that satisfy the requirements of this appendix. (b) Component tests and analyses. A component must satisfy each test or analysis required by any table of this appendix to demonstrate...

14 CFR Appendix E to Part 417 - Flight Termination System Testing and Analysis

Code of Federal Regulations, 2013 CFR

2013-01-01

... contains requirements for tests and analyses that apply to all flight termination systems and the... termination system components that satisfy the requirements of this appendix. (b) Component tests and analyses. A component must satisfy each test or analysis required by any table of this appendix to demonstrate...

14 CFR Appendix E to Part 417 - Flight Termination System Testing and Analysis

Code of Federal Regulations, 2014 CFR

2014-01-01

... contains requirements for tests and analyses that apply to all flight termination systems and the... termination system components that satisfy the requirements of this appendix. (b) Component tests and analyses. A component must satisfy each test or analysis required by any table of this appendix to demonstrate...

14 CFR Appendix E to Part 417 - Flight Termination System Testing and Analysis

Code of Federal Regulations, 2011 CFR

2011-01-01

... contains requirements for tests and analyses that apply to all flight termination systems and the... termination system components that satisfy the requirements of this appendix. (b) Component tests and analyses. A component must satisfy each test or analysis required by any table of this appendix to demonstrate...

Pilots and Flight Engineers. Aviation Careers Series.

ERIC Educational Resources Information Center

Zaharevitz, Walter

This booklet, one in a series on aviation careers, outlines the variety of careers available for airplane pilots and flight engineers. The first part of the booklet provides general information about careers for pilots and summarizes the information in a table. In the main part of the booklet, the following 11 job categories are outlined: flight…

14 CFR 91.125 - ATC light signals.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false ATC light signals. 91.125 Section 91.125... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Flight Rules General § 91.125 ATC light signals. ATC light signals have the meaning shown in the following table: Color and type of signal Meaning...

14 CFR 91.125 - ATC light signals.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false ATC light signals. 91.125 Section 91.125... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Flight Rules General § 91.125 ATC light signals. ATC light signals have the meaning shown in the following table: Color and type of signal Meaning...

14 CFR 91.125 - ATC light signals.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false ATC light signals. 91.125 Section 91.125... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Flight Rules General § 91.125 ATC light signals. ATC light signals have the meaning shown in the following table: Color and type of signal Meaning...

14 CFR 91.125 - ATC light signals.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false ATC light signals. 91.125 Section 91.125... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Flight Rules General § 91.125 ATC light signals. ATC light signals have the meaning shown in the following table: Color and type of signal Meaning...

Stability and Control. Volume 2. Stability and Control Flight Test Theory

DTIC Science & Technology

1974-07-01

e we have 2 mx , . mx , mx n am e + bme + ce = 0 or (am2 + bm + c)emx = 0 (1.21) mx , n Since e ? 0...1.97) (1.98) Substituting 2 mt , , mt , mt n am e + bme + ce =0 (1.99) and emt (am2 + bm + c) =0 (1.100) led us to assert that 1.98 would...derive Laplace transforms each time we use them. Extensive tables of transforms exist in most advanced mathe- matics and control system textbooks . We

Tile-Based Fisher-Ratio Software for Improved Feature Selection Analysis of Comprehensive Two-Dimensional Gas Chromatography Time-of-Flight Mass Spectrometry Data

DOE Office of Scientific and Technical Information (OSTI.GOV)

Marney, Luke C.; Siegler, William C.; Parsons, Brendon A.

Two-dimensional (2D) gas chromatography coupled with time-of-flight mass spectrometry (GC × GC – TOFMS) is a highly capable instrumental platform that produces complex and information-rich multi-dimensional chemical data. The complex data can be overwhelming, especially when many samples (of various sample classes) are analyzed with multiple injections for each sample. Thus, the data must be analyzed in such a way to extract the most meaningful information. The pixel-based and peak table-based algorithmic use of Fisher ratios has been used successfully in the past to reduce the multi-dimensional data down to those chemical compounds that are changing between classes relative tomore » those that are not (i.e., chemical feature selection). We report on the initial development of a computationally fast novel tile-based Fisher-ratio software that addresses challenges due to 2D retention time misalignment without explicitly aligning the data, which is a problem for both pixel-based and peak table- based methods. Concurrently, the tile-based Fisher-ratio software maximizes the sensitivity contrast of true positives against a background of potential false positives and noise. To study this software, eight compounds, plus one internal standard, were spiked into diesel at various concentrations. The tile-based F-ratio software was able to discover all spiked analytes, within the complex diesel sample matrix with thousands of potential false positives, in each possible concentration comparison, even at the lowest absolute spiked analyte concentration ratio of 1.06.« less

Ablation, Thermal Response, and Chemistry Program for Analysis of Thermal Protection Systems

NASA Technical Reports Server (NTRS)

Milos, Frank S.; Chen, Yih-Kanq

2010-01-01

In previous work, the authors documented the Multicomponent Ablation Thermochemistry (MAT) and Fully Implicit Ablation and Thermal response (FIAT) programs. In this work, key features from MAT and FIAT were combined to create the new Fully Implicit Ablation, Thermal response, and Chemistry (FIATC) program. FIATC is fully compatible with FIAT (version 2.5) but has expanded capabilities to compute the multispecies surface chemistry and ablation rate as part of the surface energy balance. This new methodology eliminates B' tables, provides blown species fractions as a function of time, and enables calculations that would otherwise be impractical (e.g. 4+ dimensional tables) such as pyrolysis and ablation with kinetic rates or unequal diffusion coefficients. Equations and solution procedures are presented, then representative calculations of equilibrium and finite-rate ablation in flight and ground-test environments are discussed.

Development of an expert system for analysis of Shuttle atmospheric revitalization and pressure control subsystem anomalies

NASA Technical Reports Server (NTRS)

Lafuse, Sharon A.

1991-01-01

The paper describes the Shuttle Leak Management Expert System (SLMES), a preprototype expert system developed to enable the ECLSS subsystem manager to analyze subsystem anomalies and to formulate flight procedures based on flight data. The SLMES combines the rule-based expert system technology with the traditional FORTRAN-based software into an integrated system. SLMES analyzes the data using rules, and, when it detects a problem that requires simulation, it sets up the input for the FORTRAN-based simulation program ARPCS2AT2, which predicts the cabin total pressure and composition as a function of time. The program simulates the pressure control system, the crew oxygen masks, the airlock repress/depress valves, and the leakage. When the simulation has completed, other SLMES rules are triggered to examine the results of simulation contrary to flight data and to suggest methods for correcting the problem. Results are then presented in form of graphs and tables.

The 1973 NASA payload model: Space opportunities 1973 - 1991. [characteristics of payloads and requirements of user community

NASA Technical Reports Server (NTRS)

1973-01-01

The tables of schedules and descriptions which portray the 1973 NASA Payload Model are presented. The schedules cover all NASA programs and the anticipated requirements of the user community, not including the Department of Defense, for the 1973 to 1991 period. The descriptions give an indication of what the payload is expected to accomplish, its characteristics, and where it is going. The payload flight schedules shown for each of the discipline areas indicate the time frame in which individual payloads will be launched, serviced, or retrieved. These do not necessarily constitute shuttle flights, however, since more than one payload can be flown on a single shuttle flight depending on size, weight, orbital destination, and the suitability of combining them. The weight, dimension, and destination data represent approximations of the payload characteristics as estimated by the Program Offices. Payload codes are provided for easy correlation between the schedules and descriptions of the Payload Model and subsequent documentation which may reference this model.

F-111C Flight Data Reduction and Analysis Procedures

DTIC Science & Technology

1990-12-01

BPHI NO 24 BTHE YES 25 BPSI NO 26 BH YES 27 LVEL NO 28 LBET NO 29 LALP YES 30 LPHI NO 31 LTHE NO 32 LPSI NO 33 LH NO 34 TABLE 2 INPUTS I Ax YES 2 Av NO...03 * 51 IJ Appendix G - A priori Data from Six Degree of Free- dom Flight Dynamic Model The six degree of freedom flight dynamic mathematical model of...Estimated Mathematical mode response - > of aircraft !Gauss- Maximum " Newton --- likelihood 4,computational cost Salgorithm function Maximum

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms August 17, 1946 to August 19, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1947-01-01

Results obtained from gust and draft velocity measurements within thunderstorms for the period August 17, 1946 to August 19, 1946 at Orlando, Florida are presented herein. These data are summarized in tables I and II and are of the type presented in reference 1 for previous flights. Inspection of photo-observer records taken on the present flights indicated that mo ambient-air temperature data were obtained.

KC-46A Formal Training Unit (FTU) and First Main Operating Base (MOB 1) Beddown EIS. Volume 1

DTIC Science & Technology

2014-03-01

jamaicensis), northern harrier (Circus cyaneus), great horned owl (Bubo virginianus), ring -necked pheasant (Phasianus colchicus), and a variety of...vary from flight to flight based on winds and other factors, so flight procedures could be louder or quieter than the SEL values listed in Table 4-3...Suspend all soil disturbance activities when winds exceed 25 miles per hour or when visible dust plumes emanate from the site and stabilize all

Post-Hurricane Ivan coastal oblique aerial photographs collected from Crawfordville, Florida, to Petit Bois Island, Mississippi, September 17, 2004

USGS Publications Warehouse

Morgan, Karen L.M.; Krohn, M. Dennis; Peterson, Russell D.; Thompson, Philip R.; Subino, Janice A.

2015-01-01

Table 1 provides detailed information about the GPS location, image name, date, and time for each of the 3,381 photographs taken, along with links to each photograph. The photographs are organized into segments, also referred to as contact sheets, and represent approximately 5 minutes of flight time. In addition to the photographs, a Google Earth Keyhole Markup Language (KML) file is provided, which can be used to view the images by clicking on the marker and then clicking on either the thumbnail or the link above the thumbnail. The KML files were created using the photographic navigation files.

The Capabilities of the upgraded MIPP experiment with respect to Hypernuclear physics

DOE Office of Scientific and Technical Information (OSTI.GOV)

Raja, Rajendran

2012-01-01

We describe the state of analysis of the MIPP experiment, its plans to upgrade the experiment and the impact such an upgraded experiment will have on hypernuclear physics. The upgraded MIPP experiment is designed to measure the properties of strong interaction spectra form beams {pi}{sup {+-}}, K{sup {+-}}, and p{sup {+-}}, for momenta ranging from 1 GeV/c to 120 GeV/c. The layout of the apparatus in the data taken so far can be seen in Figure 1. The centerpiece of the experiment is the time projection chamber, which is followed by the time of flight counter, a multi-cell Cerenkov detectormore » and the RICH detector. The TPC can identify charged particles with momenta less than 1 GeV/c using dE/dx, the time of flight will identify particles below approximately 2 GeV/c, the multi-cell Cerenkov detector is operational from 2.5 GeV/c to 14 GeV/c and the RICH detector can identify particles up to 120 GeVc. Following this is an EM and hadronic calorimeter capable of detecting forward going neutrons and photons. The experiment has been busy analyzing its data taken on various nuclei and beam conditions. The table 2 shows the data taken by MIPP I to date. We have almost complete acceptance in the forward hemisphere in the lab using the TPC. The reconstruction capabilities of the TPC can be seen in Figure 3. The particle identification capabilities of the TPC can be seen in Figure 4. The time of flight system provides further measurement of the particles with momenta less than 2 GeV/c. Figure 5 shows the time of flight data where a kaon peak is clearly visible.« less

Demonstration of the Dynamic Flowgraph Methodology using the Titan 2 Space Launch Vehicle Digital Flight Control System

NASA Technical Reports Server (NTRS)

Yau, M.; Guarro, S.; Apostolakis, G.

1993-01-01

Dynamic Flowgraph Methodology (DFM) is a new approach developed to integrate the modeling and analysis of the hardware and software components of an embedded system. The objective is to complement the traditional approaches which generally follow the philosophy of separating out the hardware and software portions of the assurance analysis. In this paper, the DFM approach is demonstrated using the Titan 2 Space Launch Vehicle Digital Flight Control System. The hardware and software portions of this embedded system are modeled in an integrated framework. In addition, the time dependent behavior and the switching logic can be captured by this DFM model. In the modeling process, it is found that constructing decision tables for software subroutines is very time consuming. A possible solution is suggested. This approach makes use of a well-known numerical method, the Newton-Raphson method, to solve the equations implemented in the subroutines in reverse. Convergence can be achieved in a few steps.

Progress on automated data analysis algorithms for ultrasonic inspection of composites

NASA Astrophysics Data System (ADS)

Aldrin, John C.; Forsyth, David S.; Welter, John T.

2015-03-01

Progress is presented on the development and demonstration of automated data analysis (ADA) software to address the burden in interpreting ultrasonic inspection data for large composite structures. The automated data analysis algorithm is presented in detail, which follows standard procedures for analyzing signals for time-of-flight indications and backwall amplitude dropout. New algorithms have been implemented to reliably identify indications in time-of-flight images near the front and back walls of composite panels. Adaptive call criteria have also been applied to address sensitivity to variation in backwall signal level, panel thickness variation, and internal signal noise. ADA processing results are presented for a variety of test specimens that include inserted materials and discontinuities produced under poor manufacturing conditions. Software tools have been developed to support both ADA algorithm design and certification, producing a statistical evaluation of indication results and false calls using a matching process with predefined truth tables. Parametric studies were performed to evaluate detection and false call results with respect to varying algorithm settings.

Human Space Flight

NASA Technical Reports Server (NTRS)

Woolford, Barbara; Mount, Frances

2004-01-01

The first human space flight, in the early 1960s, was aimed primarily at determining whether humans could indeed survive and function in micro-gravity. Would eating and sleeping be possible? What mental and physical tasks could be performed? Subsequent programs increased the complexity of the tasks the crew performed. Table 1 summarizes the history of U.S. space flight, showing the projects, their dates, crew sizes, and mission durations. With over forty years of experience with human space flight, the emphasis now is on how to design space vehicles, habitats, and missions to produce the greatest returns to human knowledge. What are the roles of the humans in space flight in low earth orbit, on the moon, and in exploring Mars?

Expedition 10 Preflight

NASA Image and Video Library

2004-10-07

Expedition 10 Commander Leroy Chiao undergoes physical testing on a mechanized tilt table at crew quarters in Baikonur, Kazakhstan, Friday, October 8, 2004, in preparation for launch with Flight Engineer and Soyuz Commander Salizhan Sharipov and Russian Space Forces Agency cosmonaut Yuri Shargin to the International Space Station on October 14. The tilt table is used to condition the crewmembers' cardiovascular system against the effects of weightlessness once on orbit. Photo Credit: (NASA/Bill Ingalls)

Expedition 10 Preflight

NASA Image and Video Library

2004-10-07

Expedition 10 Commander Leroy Chiao, left, and Russian Space Forces cosmonaut Yuri Shargin undergo physical testing on a mechanized tilt table at their crew quarters in Baikonur, Kazakhstan, Friday, October 8, 2004, in preparation for launch with Flight Engineer and Soyuz Commander Salizhan Sharipov to the International Space Station on October 14. The tilt table is used to condition the crewmembers' cardiovascular system against the effects of weightlessness once in orbit. Photo Credit: (NASA/Bill Ingalls)

Simulation of Aircraft Sortie Generation Under an Autonomic Logistics System

DTIC Science & Technology

2016-12-01

56 Design of Experiment...Figure 8. Pre -flight Operations ......................................................................................... 40 Figure 9. Sortie...Critical Factors and Their Associated Levels ................................................... 57 xiii Table 18. Design of Experiment

Development and evaluation of a prototype in-flight instrument flight rules (IFR) procedures trainer

NASA Technical Reports Server (NTRS)

Aaron, J. B., Jr.; Morris, G. G.

1981-01-01

An in-flight instrument flight rules (IFR) procedures trainer capable of providing simulated indications of instrument flight in a typical general aviation aircraft independent of ground based navigation aids was developed. The IFR navaid related instruments and circuits from an ATC 610J table top simulator were installed in a Cessna 172 aircraft and connected to its electrical power and pitot static systems. The benefits expected from this hybridization concept include increased safety by reducing the number of general aviation aircraft conducting IFR training flights in congested terminal areas, and reduced fuel use and instruction costs by lessening the need to fly to and from navaid equipped airports and by increased efficiency of the required in-flight training. Technical feasibility was demonstrated and the operational feasibility of the concept was evaluated. Results indicated that the in-flight simulator is an effective training device for teaching IFR procedural skills.

Predictability of Pilot Performance from Simulated to Real Flight in the UH-60 (Black Hawk) Helicopter

DTIC Science & Technology

2008-02-01

keratectomy ( PRK ) and laser in-situ keratomileusis ( LASIK ) procedures to determine compatibility, safety, and efficacy of these procedures for rated Army...performance data. Table B- 1. Simulator and aircraft mean flight performance. LASIK PRK Simulator Aircraft Simulator Aircraft Pre-op 60.81 (2.65) 56.41...12 7. Aircraft vs . Simulator scatter plot, hover turn maneuvers

Vitamin D metabolites and bioactive parathyroid hormone levels during Spacelab 2

NASA Technical Reports Server (NTRS)

Morey-Holton, Emily R.; Schnoes, Heinrich K.; Deluca, Hector F.; Phelps, Mary E.; Klein, Robert F.

1988-01-01

The effect of an 8-day space flight (Spacelab mission 2) on plasma levels of the vitamin D and parathyroid hormones is investigated experimentally in four crew members. The results are presented in tables and graphs and briefly characterized. Parathyroid hormone levels remained normal throughout the flight, whereas vitamin D hormone levels increased significantly on day 1 but returned to normal by day 7.

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 22, 1946 to July 23, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1947-01-01

The results obtained from measurements of gust and draft velocities within thunderstorms for the period July 22, 1946 to July 23, 1946 at Orlando, Florida, are presented herein. These data are summarized in tables I and II, respectively, and are of the type presented in reference 1 for previous flights. Inspection of photo-observer records for the flights indicated that no data on ambient air temperature variations within thunderstorms were obtained.

Automated Testing Experience of the Linear Aerospike SR-71 Experiment (LASRE) Controller

NASA Technical Reports Server (NTRS)

Larson, Richard R.

1999-01-01

System controllers must be fail-safe, low cost, flexible to software changes, able to output health and status words, and permit rapid retest qualification. The system controller designed and tested for the aerospike engine program was an attempt to meet these requirements. This paper describes (1) the aerospike controller design, (2) the automated simulation testing techniques, and (3) the real time monitoring data visualization structure. Controller cost was minimized by design of a single-string system that used an off-the-shelf 486 central processing unit (CPU). A linked-list architecture, with states (nodes) defined in a user-friendly state table, accomplished software changes to the controller. Proven to be fail-safe, this system reported the abort cause and automatically reverted to a safe condition for any first failure. A real time simulation and test system automated the software checkout and retest requirements. A program requirement to decode all abort causes in real time during all ground and flight tests assured the safety of flight decisions and the proper execution of mission rules. The design also included health and status words, and provided a real time analysis interpretation for all health and status data.

Enhancements on the Convex Programming Based Powered Descent Guidance Algorithm for Mars Landing

NASA Technical Reports Server (NTRS)

Acikmese, Behcet; Blackmore, Lars; Scharf, Daniel P.; Wolf, Aron

2008-01-01

In this paper, we present enhancements on the powered descent guidance algorithm developed for Mars pinpoint landing. The guidance algorithm solves the powered descent minimum fuel trajectory optimization problem via a direct numerical method. Our main contribution is to formulate the trajectory optimization problem, which has nonconvex control constraints, as a finite dimensional convex optimization problem, specifically as a finite dimensional second order cone programming (SOCP) problem. SOCP is a subclass of convex programming, and there are efficient SOCP solvers with deterministic convergence properties. Hence, the resulting guidance algorithm can potentially be implemented onboard a spacecraft for real-time applications. Particularly, this paper discusses the algorithmic improvements obtained by: (i) Using an efficient approach to choose the optimal time-of-flight; (ii) Using a computationally inexpensive way to detect the feasibility/ infeasibility of the problem due to the thrust-to-weight constraint; (iii) Incorporating the rotation rate of the planet into the problem formulation; (iv) Developing additional constraints on the position and velocity to guarantee no-subsurface flight between the time samples of the temporal discretization; (v) Developing a fuel-limited targeting algorithm; (vi) Initial result on developing an onboard table lookup method to obtain almost fuel optimal solutions in real-time.

Orbital flight test shuttle external tank aerothermal flight evaluation, volume 1

NASA Technical Reports Server (NTRS)

Praharaj, Sarat C.; Engel, Carl D.; Warmbrod, John D.

1986-01-01

This 3-volume report discusses the evaluation of aerothermal flight measurements made on the orbital flight test Space Shuttle External Tanks (ETs). Six ETs were instrumented to measure various quantities during flight; including heat transfer, pressure, and structural temperature. The flight data was reduced and analyzed against math models established from an extensive wind tunnel data base and empirical heat-transfer relationships. This analysis has supported the validity of the current aeroheating methodology and existing data base; and, has also identified some problem areas which require methodology modifications. This is Volume 1, an Executive Summary. Volume 2 contains Appendices A (Aerothermal Comparisons) and B (Flight Derived h sub 1/h sub u vs. M sub inf. Plots), and Volume 3 contains Appendix C (Comparison of Interference Factors among OFT Flight, Prediction and 1H-97A Data), Appendix D (Freestream Stanton Number and Reynolds Number Correlation for Flight and Tunnel Data), and Appendix E (Flight-Derived h sub i/h sub u Tables).

Orbital flight test shuttle external tank aerothermal flight evaluation, volume 3

NASA Technical Reports Server (NTRS)

Praharaj, Sarat C.; Engel, Carl D.; Warmbrod, John D.

1986-01-01

This 3-volume report discusses the evaluation of aerothermal flight measurements made on the orbital flight test Space Shuttle External Tanks (ETs). Six ETs were instrumented to measure various quantities during flight; including heat transfer, pressure, and structural temperature. The flight data was reduced and analyzed against math models established from an extensive wind tunnel data base and empirical heat-transfer relationships. This analysis has supported the validity of the current aeroheating methodology and existing data base; and, has also identified some problem areas which require methodology modifications. Volume 1 is the Executive Summary. Volume 2 contains Appendix A (Aerothermal Comparisons), and Appendix B (Flight-Derived h sub 1/h sub u vs. M sub inf. Plots). This is Volume 3, containing Appendix C (Comparison of Interference Factors between OFT Flight, Prediction and 1H-97A Data), Appendix D (Freestream Stanton Number and Reynolds Number Correlation for Flight and Tunnel Data), and Appendix E (Flight-Derived h sub i/h sub u Tables).

Orbital flight test shuttle external tank aerothermal flight evaluation, volume 2

NASA Technical Reports Server (NTRS)

Praharaj, Sarat C.; Engel, Carl D.; Warmbrod, John D.

1986-01-01

This 3-volume report discusses the evaluation of aerothermal flight measurements made on the orbital flight test Space Shuttle External Tanks (ETs). Six ETs were instrumented to measure various quantities during flight; including heat transfer, pressure, and structural temperature. The flight data was reduced and analyzed against math models established from an extensive wind tunnel data base and empirical heat-transfer relationships. This analysis has supported the validity of the current aeroheating methodology and existing data base; and, has also identified some problem areas which require methodology modifications. Volume 1 is the Executive Summary. This is volume 2, containing Appendix A (Aerothermal Comparisons), and Appendix B (Flight-Derived h sub i/h sub u vs. M sub inf. Plots). Volume 3 contains Appendix C (Comparison of Interference Factors between OFT Flight, Prediction and 1H-97A Data), Appendix D (Freestream Stanton Number and Reynolds Number Correlation for Flight and Tunnel Data), and Appendix E (Flight-Derived h sub i/h sub u Tables).

Satellite services system analysis study. Volume 4: Service equipment concepts

NASA Technical Reports Server (NTRS)

1981-01-01

Payload deployment equipment is discussed, including payload separation, retention structures, the remote manipulator system, tilt tables, the payload installation and deployment aid, the handling and positioning aid, and spin tables. Close proximity retrieval, and on-orbit servicing equipment is discussed. Backup and contingency equipment is also discussed. Delivery and retrieval of high-energy payloads are considered. Earth return equipment, the aft flight deck, optional, and advanced equipment are also discussed.

THE BUREAU OF AERONAUTICS RESEARCH AND DEVELOPMENT PROGRAM FOR WATER-BASED AIRCRAFT,

DTIC Science & Technology

WATER BASED AIRCRAFT, BUDGETS), RESEARCH MANAGEMENT, FLIGHT TESTING, WIND TUNNEL MODELS, TABLES(DATA), AIRCRAFT, TEST VEHICLES, HYDRODYNAMICS, PIERS, FLOATING DOCKS, LOADS(FORCES), WATER , STABILITY, SPRAYS, NAVAL AIRCRAFT.

Operational Problems Associated with Head-Up Displays during Instrument Flight.

DTIC Science & Technology

1980-10-01

Force project engineers were Major Michael F. Rundle and Mr. William L. Welde . 41 4 TABLE OF CONTENTS Page ABBREVIATIONS...of Automotive Engineers SETP Society of Experimental Test Pilots SI Solid Instruments SNPL Syndicat National des Pilotes des Lignes (French ALPA) TACAN...Factors Relevent to Jet Upsets ," Lessons with Emphasis on Flight Mechanics from Operating Experience, Incidents, and Accidents, AGARD CP-76, 1971 153 J

A Framework for Optimal Control Allocation with Structural Load Constraints

NASA Technical Reports Server (NTRS)

Frost, Susan A.; Taylor, Brian R.; Jutte, Christine V.; Burken, John J.; Trinh, Khanh V.; Bodson, Marc

2010-01-01

Conventional aircraft generally employ mixing algorithms or lookup tables to determine control surface deflections needed to achieve moments commanded by the flight control system. Control allocation is the problem of converting desired moments into control effector commands. Next generation aircraft may have many multipurpose, redundant control surfaces, adding considerable complexity to the control allocation problem. These issues can be addressed with optimal control allocation. Most optimal control allocation algorithms have control surface position and rate constraints. However, these constraints are insufficient to ensure that the aircraft's structural load limits will not be exceeded by commanded surface deflections. In this paper, a framework is proposed to enable a flight control system with optimal control allocation to incorporate real-time structural load feedback and structural load constraints. A proof of concept simulation that demonstrates the framework in a simulation of a generic transport aircraft is presented.

Analysis of Wallops Flight Test Data Through an Automated COTS System

NASA Technical Reports Server (NTRS)

Blackstock, Dexter Lee; Theobalds, Andre B.

2005-01-01

During the summer of 2004 NASA Langley Research Center flight tested a Synthetic Vision System (SVS) at the Reno/Tahoe International Airport (RNO) and the Wallops Flight Facility (WAL). The SVS included a Runway Incursion Prevention System (RIPS) to improve pilot situational awareness while operating near and on the airport surface. The flight tests consisted of air and ground operations to evaluate and validate the performance of the system. This paper describes the flight test and emphasizes how positioning data was collected, post processed and analyzed through the use of a COTS-derived software system. The system that was developed to analyze the data was constructed within the MATLAB(TM) environment. The software was modified to read the data, perform several if-then scenarios and produce the relevant graphs, figures and tables.

Computer Program Development Specification for IDAMST Operational Flight Programs. Addendum 1. Executive Software.

DTIC Science & Technology

1976-11-01

system. b. Read different program configurations to reconfigure the software during flight. c. Write Digital Integrated Test System (DITS) results...associated witn > inor C):l.e Event must be Unlatched. The sole difference between a Latched ana an lnratcrec Condition is that upon the Scheduling...Table. Furthermore, the block of pointers for one Minor Cycle may be wholly contained witnir the Diock of ocinters for a different Minor Cycle. For

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes Within Thunderstorms September 17, 1946 to September 18, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1947-01-01

The results obtained from measurements of gust velocities, draft velocities, and ambient-air temperature within thunderstorms for the period September 17, 1946 to September 18, 1946 at Orlando, Fla. are presented herein. These data are summarized in tables I, II, and III, respectively, and are of the type presented in reference 1 for previous flights.

Guide for Airborne Infrared Roof Moisture Surveys

DTIC Science & Technology

1978-01-01

larger), but it takes more flight lines (and more film ) to cover an area at low altitudes than it does at higher altitudes. 13. Flight-line spacing...normally provided in rolls as negatives or trans- parent positives. For ease of interpretation, the film should be cut into strips representing...interpretation. Items other than a light table that are helpful include a large magnifying glass and a pocket stereoscope (such as those used to intepret

Ocular Problems of the Aging Military Aviator

DTIC Science & Technology

2000-08-01

disposition. This might be grounding, further treatment , a waiver to return to flight status or change in flight status. (1) TABLE 2. DIAGNOSES AND...advancements in medicine and science since 1959, when Uveitis iritis 3 The Age 60 (2) rule came into being, had any effect on Optic neuritis/ischemnic...glaucoma with visual a diagnosis of glaucoma was a reason for commencing field defects 1 drug treatment of the disease. This was usually with Trauma

Update of the Bisphosphonate ISS Flight Experiment

NASA Technical Reports Server (NTRS)

LeBlanc, Adrian; Matsumoto, Toshio; Jones, Jeffrey; Shapiro, Jay; Lang, Thomas; Shackelford, Linda; Smith, Scott M.; Evans, Harlan; Spector, Elisabeth; Ploutz-Snyder, Robert;

Reliability Estimating Procedures for Electric and Thermochemical Propulsion Systems. Volume 2

DTIC Science & Technology

1977-02-01

final form. For some components, the parameters are calculated from design factors (e.g., design life) that must be input when requested. Each component...Components Components are regarded as statis- tically identical if they are drawn from the same production lot because the initial and sub- sequent...table yields b 0.0023 The - factors are obtained from Tables 2.2.4-1 through 2.2.4-5: Factor Value rE Space, flight 1 JANTXV quality 0.5 7A Small signal

Rotorcraft Flight Simulation Computer Program C81 with DATAMAP interface. Volume I. User’s Manual

DTIC Science & Technology

1981-10-01

any one of the RWAS tables to simulate the defined effect of that input, care must be exercised to assure that the table used is based on the correct... IMPROVED MANEUVER AUTOPILOT HAVE BEEN INSTALLED IN AGAPBO. A NEW LISTING OF THE CONTENTS OF THE ANALYTICAL DATA BASE WILL BE GENERATED DURING THE WEEK...of the program (Reference 1) has been improved by providing the cap- ability to generate Postprocessing Data Blocks containing selected variables

The IRAS radiation environment

NASA Technical Reports Server (NTRS)

Stassinopoulos, E. G.

1978-01-01

Orbital flux integration for three selected mission altitudes and geographic instantaneous flux-mapping for nominal flight-path altitude were used to determine the external charged particle radiation predicted for the Infrared Astronomy Satellite. A current field model was used for magnetic field definitions for three nominal circular trajectories and for the geographic mapping positions. Innovative analysis features introduced include (1) positional fluxes as a function of time and energy for the most severe pass through the South Atlantic Anomaly; (2) total positional doses as a function of time and shield thickness; (3) comparison mapping fluxes for ratios of positional intensities to orbit integrated averages; and (4) statistical exposure-time history of a trajectory as a function of energy indicating, in percent of total mission duration, the time intervals over which the instantaneous fluxes would exceed the orbit integrated averages. Results are presented in tables and graphs.

The DaveMLTranslator: An Interface for DAVE-ML Aerodynamic Models

NASA Technical Reports Server (NTRS)

Hill, Melissa A.; Jackson, E. Bruce

2007-01-01

It can take weeks or months to incorporate a new aerodynamic model into a vehicle simulation and validate the performance of the model. The Dynamic Aerospace Vehicle Exchange Markup Language (DAVE-ML) has been proposed as a means to reduce the time required to accomplish this task by defining a standard format for typical components of a flight dynamic model. The purpose of this paper is to describe an object-oriented C++ implementation of a class that interfaces a vehicle subsystem model specified in DAVE-ML and a vehicle simulation. Using the DaveMLTranslator class, aerodynamic or other subsystem models can be automatically imported and verified at run-time, significantly reducing the elapsed time between receipt of a DAVE-ML model and its integration into a simulation environment. The translator performs variable initializations, data table lookups, and mathematical calculations for the aerodynamic build-up, and executes any embedded static check-cases for verification. The implementation is efficient, enabling real-time execution. Simple interface code for the model inputs and outputs is the only requirement to integrate the DaveMLTranslator as a vehicle aerodynamic model. The translator makes use of existing table-lookup utilities from the Langley Standard Real-Time Simulation in C++ (LaSRS++). The design and operation of the translator class is described and comparisons with existing, conventional, C++ aerodynamic models of the same vehicle are given.

Wind shear modeling for aircraft hazard definition

NASA Technical Reports Server (NTRS)

Frost, W.; Camp, D. W.; Wang, S. T.

1978-01-01

Mathematical models of wind profiles were developed for use in fast time and manned flight simulation studies aimed at defining and eliminating these wind shear hazards. A set of wind profiles and associated wind shear characteristics for stable and neutral boundary layers, thunderstorms, and frontal winds potentially encounterable by aircraft in the terminal area are given. Engineering models of wind shear for direct hazard analysis are presented in mathematical formulae, graphs, tables, and computer lookup routines. The wind profile data utilized to establish the models are described as to location, how obtained, time of observation and number of data points up to 500 m. Recommendations, engineering interpretations and guidelines for use of the data are given and the range of applicability of the wind shear models is described.

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms. IV - July 19, 1946 to July 20, 1946 at Orlando, Florida. Part 4; July 19, 1946 to July 20, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, H. B.

1946-01-01

Summaries of the gust and draft velocities evaluated from acceleration and airspeed-altitude records taken by NACA instruments installed n P-61c airplanes participating in thunderstorm flights 12 and 13 of July 19, 1946, and July 20, 1946, respectively, are presented in tables I and II herein. These data are of the type presented in reference 1 for previous flights. Inspection of the motion picture records of the pilots' instrument panels for the present flights indicated that the milliameter connected to equipment for measuring ambient air temperature read zero throughout all traverses.

Official portrait of Astronaut Ronald E. McNair

NASA Technical Reports Server (NTRS)

1985-01-01

Official portrait of Astronaut Ronald E. McNair. McNair is in the blue shuttle flight suit, standing in front of a table which holds a model of the Space Shuttle. An American flag is visible behind him.

Astronaut James A. McDivitt has blood pressure checked during preflight exam.

NASA Technical Reports Server (NTRS)

1965-01-01

S65-19524 (1 June 1965) --- Dr. Charles A. Berry, Chief of Center Medical Programs, Manned Spacecraft Center (MSC), Houston, prepares to check the blood pressure of astronaut James A. McDivitt, command pilot for the Gemini-Titan 4 space flight. McDivitt is on the tilt table at the Aero Medical Area, Merritt Island, where he and Astronaut Edward H. White II, GT-4 pilot, underwent pre-flight physicals in preparation for the 4-day, 62 revolution space flight. The two astronauts were declared in top physical condition. In the background is Dr. Gordon Benson, NASA physician at Cape Kennedy.

An Evaluation of Performance-Based Tests Designed to Improve Naval Aviation Selection.

DTIC Science & Technology

1991-08-01

Qualification Test AQT/FAR 8z Flight Aptitude Rating 3 Complex Visual CVT Information Processing 3 Risk RISK 3 Absolute Difference ADHT & Horizontal...01329* .01852 1077 6 CVT .03752* .05064 557 3 ADHT .03432* .03289 499 8 RISK .03369* .05028 337 2 MB .01814 .02479 544 5 PMT/DLT .00987 .01037 641 7 *p...to differences in age, sex, accession source, college major, prior flight hours, or intelligence. From Table 2 we see that the CVT, ADHT , and the RISK

Apollo-Soyuz pamphlet no. 1: The flight

NASA Technical Reports Server (NTRS)

Page, L. W.; From, T. P.

1977-01-01

The goals of the Apollo-Soyuz Test Project are described in this first in a series of nine pamphlets designed as a curriculum supplement for teachers, supervisors, curriculum specialists, and textbook writers as well as for the general public. Aspects of the space flight covered include descriptions of the astronaut-cosmonaut meeting and of the spacecraft and landing module; spacecraft launch; control, and rendezvous; crew work schedule; and telemetry. Experiments performed are listed in tables, and their major results are summarized.

Analysis of sleep on Shuttle missions

NASA Technical Reports Server (NTRS)

Santy, Patricia A.; Kapanka, Heidi; Davis, Jeffrey R.; Stewart, Donald F.

1988-01-01

The sleep patterns of 58 Space Shuttle crew members are analyzed statistically on the basis of debriefing forms filled out within 3 days postflight. The data are compiled in a table, and photographs of typical sleep conditions on the Shuttle are provided. It is found that sleep disruption is relatively common on Shuttle missions, especially on the first and last days. Sleep medication was used by 19.4 percent of crew on single-shift flights and 50 percent of crew on dual-shift flights.

GPM Solar Array Gravity Negated Deployment Testing

NASA Technical Reports Server (NTRS)

Penn, Jonathan; Johnson, Chris; Lewis, Jesse; Dear, Trevin; Stewart, Alphonso

2014-01-01

NASA Goddard Space Flight Center (GSFC) successfully developed a g-negation support system for use on the solar arrays of the Global Precipitation Measurement (GPM) Satellite. This system provides full deployment capability at the subsystem and observatory levels. In addition, the system provides capability for deployed configuration first mode frequency verification testing. The system consists of air pads, a support structure, an air supply, and support tables. The g-negation support system was used to support all deployment activities for flight solar array deployment testing.

Nickelzinc Batteries for RPV Applications.

DTIC Science & Technology

1981-06-01

batteries used in the BQM-34A target drones are: 1) The secondary nickel-zinc system is able to provide superior Amp-Hr capacity with respect to volume as...7) MAR-5013 Flight Test batteries, have been constructed and shipped to Tyndall AFB for testing in the BQM- 34A remotely piloted target drone . The...ditioning.The seventh battery was lost on a flight mission when the target drone was shot down. Refer to Table 16 for a summary of battery history prior

Object oriented design (OOD) in real-time hardware-in-the-loop (HWIL) simulations

NASA Astrophysics Data System (ADS)

Morris, Joe; Richard, Henri; Lowman, Alan; Youngren, Rob

2006-05-01

Using Object Oriented Design (OOD) concepts in AMRDEC's Hardware-in-the Loop (HWIL) real-time simulations allows the user to interchange parts of the simulation to meet test requirements. A large-scale three-spectral band simulator connected via a high speed reflective memory ring for time-critical data transfers to PC controllers connected by non real-time Ethernet protocols is used to separate software objects from logical entities close to their respective controlled hardware. Each standalone object does its own dynamic initialization, real-time processing, and end of run processing; therefore it can be easily maintained and updated. A Resource Allocation Program (RAP) is also utilized along with a device table to allocate, organize, and document the communication protocol between the software and hardware components. A GUI display program lists all allocations and deallocations of HWIL memory and hardware resources. This interactive program is also used to clean up defunct allocations of dead processes. Three examples are presented using the OOD and RAP concepts. The first is the control of an ACUTRONICS built three-axis flight table using the same control for calibration and real-time functions. The second is the transportability of a six-degree-of-freedom (6-DOF) simulation from an Onyx residence to a Linux-PC. The third is the replacement of the 6-DOF simulation with a replay program to drive the facility with archived run data for demonstration or analysis purposes.

Overseas trip report, CV 990 underflight mission. [Norwegian Sea, Greenland ice sheet, and Alaska

NASA Technical Reports Server (NTRS)

Gloersen, P.; Crawford, J.; Hardis, L.

1980-01-01

The scanning microwave radiometer-7 simulator, the ocean temperature scanner, and an imaging scatterometer/altimeter operating at 14 GHz were carried onboard the NASA CV-990 over open oceans, sea ice, and continental ice sheets to gather surface truth information. Data flights were conducted over the Norwegian Sea to map the ocean polar front south and west of Bear Island and to transect several Nimbus-7 footprints in a rectangular pattern parallel to the northern shoreline of Norway. Additional flights were conducted to obtain correlative data on the cryosphere parameters and characteristics of the Greenland ice sheet, and study the frozen lakes near Barrow. The weather conditions and flight path way points for each of the nineteen flights are presented in tables and maps.

The Knowledge Level of United States Air Force Flight Nurses Regarding the Injuries of Conventional Warfare Casualties

DTIC Science & Technology

1989-01-01

d) lack of supplies; (e) sexual harassment; ( f ) problems with some professional relatiouships; (g) survivor guilt; and (h) threat to life. After...Demographic Profile of the Subjects Characteristics Samplea f (t) Sx Male 26(28) Female 66(72) Age 25-29 10(11) 30-34 37(40) 35-39 30(33) 40-44 11(12) 45+ 4(4...20 3(3) 21-24 2(2) Note. Only 90 of 92 reported. (table continues) 44 Table I (continued) Characteristics Samplea f (e) Area of Clinical Practice

An Experimental Study of the Driving Mechanism and Control of the Unsteady Shock Induced Turbulent Separation in a Mach 5 Compression Corner Flow.

DTIC Science & Technology

1992-01-01

vili Table of Contents Section Page List of Tables xiii List of Figures xiv Nomenclature xxii 1 Introduction 1 1.1 Motivation 1 1.2 Objective of...Introduction 1.1 Motivation The mid-1980’s saw a renewed interest in hypersonic flight. Motivated by the achievements of the American Space Transportation... measuments made downstrem of the compreson corner. 4.2.2 VITA Technique Another approach to event detection was applied to the fluctuating pitot

Plenary Round Table: The Main Challenges of Space Propulsion Industry for the Coming Ten Years

NASA Technical Reports Server (NTRS)

Wood, Byron K.; Hopson, George (Technical Monitor)

2002-01-01

This viewgraph presentation provides limited information on the Space Shuttle Main Engine. Topics covered include reusability levels for individual parts, the relation between the number of certification tests and average risk factor for first flights.

Ozone Contamination in Aircraft Cabins: Appendix B: Overview papers. Ozone destruction techniques

NASA Technical Reports Server (NTRS)

Wilder, R.

1979-01-01

Ozone filter test program and ozone instrumentation are presented. Tables on the flight tests, samll scale lab tests, and full scale lab tests were reviewed. Design verification, flammability, vibration, accelerated contamination, life cycle, and cabin air quality are described.

Visitors Center Exhibits

NASA Technical Reports Server (NTRS)

1997-01-01

A child enjoys building his own LEGO model at a play table which was included in the exhibit 'Travel in Space' World Show. The exhibit consisted of 21 displays designed to teach children about flight and space travel from the Wright brothers to future generations of space vehicles.

Expedition 11 Preflight

NASA Image and Video Library

2005-04-10

Expedition 11 Flight Engineer John Phillips takes part in a tilt table test, Monday, April 11, 2005, in Baikonur, Kazakhstan as technicians collect pre-launch data on the state of his equilibrium prior to the April 15 launch to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

Expedition 19 Crew Training

NASA Image and Video Library

2009-03-20

Expedition 19 Commander Gennady I. Padalka, left, and Flight Engineer Michael R. Barratt listen to their mp3 players as a medical doctor looks on during the tilt table training at the Cosmonaut Hotel, Saturday, March 21, 2009 in Baikonur, Kazakhstan.(Photo Credit: NASA/Bill Ingalls)

Quad-rotor flight path energy optimization

NASA Astrophysics Data System (ADS)

Kemper, Edward

Quad-Rotor unmanned areal vehicles (UAVs) have been a popular area of research and development in the last decade, especially with the advent of affordable microcontrollers like the MSP 430 and the Raspberry Pi. Path-Energy Optimization is an area that is well developed for linear systems. In this thesis, this idea of path-energy optimization is extended to the nonlinear model of the Quad-rotor UAV. The classical optimization technique is adapted to the nonlinear model that is derived for the problem at hand, coming up with a set of partial differential equations and boundary value conditions to solve these equations. Then, different techniques to implement energy optimization algorithms are tested using simulations in Python. First, a purely nonlinear approach is used. This method is shown to be computationally intensive, with no practical solution available in a reasonable amount of time. Second, heuristic techniques to minimize the energy of the flight path are tested, using Ziegler-Nichols' proportional integral derivative (PID) controller tuning technique. Finally, a brute force look-up table based PID controller is used. Simulation results of the heuristic method show that both reliable control of the system and path-energy optimization are achieved in a reasonable amount of time.

Evaluation of Gust and Draft Velocities from Flights of P-61c Airplanes within Thunderstorms. II - July 9, 1946 to July 11, 1946 at Orlando, Florida. II; July 9, 1946 to July 11, 1946 at Orlando, Florida

NASA Technical Reports Server (NTRS)

Tolefson, Harold B.

1946-01-01

The results obtained from an evaluation for gust and draft velocities of acceleration and airspeed-altitude records taken by NACA recording instruments installed in P-61c airplanes participating in thunderstorm flights 6, 7, and 8 of July 9, 1946, July 10, 1946, and July 11, 1946, respectively, are presented herein. These data are summarized in tables I and II. In accordance with a recent discussion with a member of the U.S. Weather Bureau staff, the tabulated results for the present flight include in addition to data of the type presented in reference 1, the initial heading of the airplane for each traverse, the pressure altitude at the start of each traverse in increments of 500 feet, and the gust gradient distance when it could be evaluated. The cloud entry and exit times for the present data were taken from motion-picture records of the pilot's instrument panels whenever such records were available while the length fo the traverses in seconds and feet was taken from the airspeed-altitude records. In many cases, however, poor agreement is indicated between the duration of the cloud traverses as obtained from the motion-picture records and from the airspeed-altitude records. This result is believed to be due to camera stoppages, inaccurate spring mechanisms of the clocks, and loss of motion-picture record in exposure or development. With reference to the evaluation of gust data, the nominal threshold was about 2 feet per second. In making gust counts to this threshold, some gusts below that threshold have been included due to limitations of the procedure used. Thus, it will be noted that in some instances gust counts are given in table I although now corresponding gust velocities are listed.

LANDSAT-1 and LANDSAT-2 flight evaluation report, 23 April - 23 July 1976

NASA Technical Reports Server (NTRS)

1976-01-01

LANDSAT 1 and 2 operations were described, giving detailed charts and tables of their performances since 1972. Orbital parameters, attitude control subsystem, telemetry subsystem, orbit adjust subsystem, and magnetic moment compensating assembly were some of the main parameters discussed.

Voss with coffee and snack in Service Module

NASA Image and Video Library

2001-04-12

ISS002-E-5532 (12 April 2001) --- Astronaut James S. Voss, Expedition Two flight engineer, has a coffee and a snack at the table in the Zvezda / Service Module of the International Space Station (ISS). This image was recorded with a digital still camera.

Patient-Reported Dyspnea Correlates Poorly with Aerobic Exercise Capacity Measured During Cardiopulmonary Exercise Testing.

PubMed

Gaspard, Dany; Kass, Jonathan; Akers, Stephen; Hunter, Krystal; Pratter, Melvin

2017-10-01

Patient-reported dyspnea plays a central role in assessing cardiopulmonary disease. There is little evidence, however, that dyspnea correlates with objective exercise capacity measurements. If the correlation is poor, dyspnea as a proxy for objective assessment may be misleading. To compare patient's perception of dyspnea with maximum oxygen uptake (MaxVO2) during cardiopulmonary exercise testing (CPET). Fifty patients undergoing CPET for dyspnea evaluation were studied prospectively. Dyspnea assessment was measured by a metabolic equivalent of task (METs) table, Mahler Dyspnea Index, Borg Index, number of blocks walked, and flights of stairs climbed before stopping due to dyspnea. These descriptors were compared to MaxVO2. MaxVO2 showed low correlation with METs table (r = 0.388, p = 0.005) and no correlation with Mahler Index (r = 0.24, p = 0.093), Borg Index (r = -0.017, p = 0.905), number of blocks walked (r = 0.266, p = 0.077) or flights of stairs climbed (r = 0.188, p = 0.217). When adjusted for weight (maxVO2/kg), there was significant correlation between MaxVO2 and METs table (r = 0.711, p < 0.001), moderate correlation with blocks walked (r = 0.614, p < 0.001), and low correlation with Mahler Index (r = 0.488 p = 0.001), Borg Index (r = -0.333 p = 0.036), and flights of stairs (r = 0.457 p = 0.004). Subgroup analysis showed worse correlation when patients with normal CPET were excluded (12/50 excluded). Patients with BMI < 30 had no correlation between Max VO2 and the assessment methods, while patients with BMI > 30 had moderate correlation between MaxVO2 and METs table (r = 0.568, p = 0.002). Patient-reported dyspnea correlates poorly with MaxVO2 and fails to predict exercise capacity. Reliance on reported dyspnea may result in suboptimal categorization of cardiopulmonary disease severity.

Occupant Injury Severity and Accident Causes in Helicopter Emergency Medical Services (1983-2014).

PubMed

Boyd, Douglas D; Macchiarella, Nickolas D

2016-01-01

Helicopter emergency medical services (HEMS) transport critically ill patients to/between emergency care facilities and operate in a hazardous environment: the destination site is often encumbered with obstacles, difficult to visualize at night, and lack instrument approaches for degraded visibility. The study objectives were to determine 1) HEMS accident rates and causes; 2) occupant injury severity profiles; and 3) whether accident aircraft were certified to the more stringent crashworthiness standards implemented two decades ago. The National Transportation Safety Board (NTSB) aviation accident database was used to identify HEMS mishaps for the years spanning 1983-2014. Contingency tables (Pearson Chi-square or Fisher's exact test) were used to determine differences in proportions. A generalized linear model (Poisson distribution) was used to determine if accident rates differed over time. While the HEMS accident rate decreased by 71% across the study period, the fraction of fatal accidents (36-50%) and the injury severity profiles were unchanged. None of the accident aircraft fully satisfied the current crashworthiness standards. Failure to clear obstacles and visual-to-instrument flight, the most frequent accident causes (37 and 26%, respectively), showed a downward trend, whereas accidents ascribed to aircraft malfunction showed an upward trend over time. HEMS operators should consider updating their fleet to the current, more stringent crashworthiness standards in an attempt to reduce injury severity. Additionally, toward further mitigating accidents ascribed to inadvertent visual-to-instrument conditions, HEMS aircraft should be avionics-equipped for instrument flight rules flight.

OPALS: A COTS-based Tech Demo of Optical Communications

NASA Technical Reports Server (NTRS)

Oaida, Bogdan

2012-01-01

I. Objective: Deliver video from ISS to optical ground terminal via an optical communications link. a) JPL Phaeton/Early Career Hire (ECH) training project. b) Implemented as Class-D payload. c) Downlink at approx.30Mb/s. II. Flight System a) Optical Head Beacon Acquisition Camera. Downlink Transmitter. 2-axis Gimbal. b) Sealed Container Laser Avionics Power distribution Digital I/O board III. Implementation: a) Ground Station - Optical Communications Telescope Laboratory at Table Mountain Facility b) Flight System mounted to ISS FRAM as standard I/F. Attached externally on Express Logistics Carrier.

The rhesus monkey (Macaca mulatta) as a flight candidate

NASA Technical Reports Server (NTRS)

Debourne, M. N. G.; Bourne, G. H.; Mcclure, H. M.

1977-01-01

The intelligence and ruggedness of rhesus monkeys, as well as the abundance of normative data on their anatomy, physiology, and biochemistry, and the availability of captive bred animals qualify them for selection as candidates for orbital flight and weightlessness studies. Baseline data discussed include: physical characteristics, auditory thresholds, visual accuity, blood, serological taxomony, immunogenetics, cytogenics, circadian rhythms, respiration, cardiovascular values, corticosteroid response to charr restraint, microscopy of tissues, pathology, nutrition, and learning skills. Results from various tests used to establish the baseline data are presented in tables.

Algorithm for constructing the programmed motion of a bounding vehicle for the flight phase

NASA Technical Reports Server (NTRS)

Lapshin, V. V.

1979-01-01

The construction of the programmed motion of a multileg bounding vehicle in the flight was studied. An algorithm is given for solving the boundary value problem for constructing this programmed motion. If the motion is shown to be symmetrical, a simplified use of the algorithm can be applied. A method is proposed for nonimpact of the legs during lift-off of the vehicle, and for softness at touchdown. Tables are utilized to construct this programmed motion over a broad set of standard motion conditions.

Report on a Visit to the U.S.A. during January 1982 Relating to the Effect of Turbulence and Other Meteorological Hazards on Aircraft Flight

DTIC Science & Technology

1982-08-01

experienced nearly the same wind shear problems as arose with the accident at JFK airport . The measurements are probably quite significant for Australia as...is between -4 and +4. (The accident at JFK airport occurred with a - +4). Roland produced z table showing that as a increased over the positive range...Eastern Airlines accident at JFK airport . He also mentioned that NSSL had a contract with MIT to use a flight simulator with a simulated convective wind

An instrument for spatial conductivity measurements of high Tc superconducting (HTSC) materials

NASA Technical Reports Server (NTRS)

Vansant, T.

1991-01-01

High T(sub c) Superconducting (HTSC) thin films are suggested for use in a number of aerospace applications such as an IR bolometer and as electromagnetic shielding. As part of its flight assurance role, the Materials Branch of the Goddard Space Flight Center has initiated development of an instrument capable of measuring variations in conductivity for flat samples using an eddy current testing device and an X-Y positioning table. This instrument was used to examine bulk HTSC samples. System changes that would enable characterization of thin film materials are discussed.

STS-4 post flight crew debriefing in JSC conference room

NASA Technical Reports Server (NTRS)

1982-01-01

STS-4 Commander Ken Mattingly and Pilot Henry Hartsfield discuss mission events with astronauts and administrators during a post flight crew debriefing held in a JSC conference room. Seated around the conference table clockwise (from lower left) are astronaut William B. Lenoir, Hartsfield, Mattingly, astronaut Robert F. Overmyer, astronaut S. David Griggs, astronaut Karol J. Bobko, astronaut John W. Young, administrator George W. Abbey, and astronaut Vance D. Brand. On the perimeter of the room are astronaut George D. Nelson (left) and astronaut Francis (Dick) Scobee (right).

Flight Test Techniques. Proceedings of the Flight Mechanics Panel Symposium Held in Lisbon, Portugal on 2-5 April 1984

DTIC Science & Technology

1984-07-01

results are caused only by the individual aerodynamic cleanliness. A table in thr lower part of this figure gives a, frst impression of the surface quality ...for the Tornado which will be the firso, iarc-iaft in operational service in t•• .. , SGersany and Italy to be so equipped. -nen considering the...and must be tested to the limits of their capability before being released to Service . The. final lesson is that when a high risk trial is undertaken

Causal Factors and Adverse Conditions of Aviation Accidents and Incidents Related to Integrated Resilient Aircraft Control

NASA Technical Reports Server (NTRS)

Reveley, Mary S.; Briggs, Jeffrey L.; Evans, Joni K.; Sandifer, Carl E.; Jones, Sharon Monica

2010-01-01

The causal factors of accidents from the National Transportation Safety Board (NTSB) database and incidents from the Federal Aviation Administration (FAA) database associated with loss of control (LOC) were examined for four types of operations (i.e., Federal Aviation Regulation Part 121, Part 135 Scheduled, Part 135 Nonscheduled, and Part 91) for the years 1988 to 2004. In-flight LOC is a serious aviation problem. Well over half of the LOC accidents included at least one fatality (80 percent in Part 121), and roughly half of all aviation fatalities in the studied time period occurred in conjunction with LOC. An adverse events table was updated to provide focus to the technology validation strategy of the Integrated Resilient Aircraft Control (IRAC) Project. The table contains three types of adverse conditions: failure, damage, and upset. Thirteen different adverse condition subtypes were gleaned from the Aviation Safety Reporting System (ASRS), the FAA Accident and Incident database, and the NTSB database. The severity and frequency of the damage conditions, initial test conditions, and milestones references are also provided.

STS-34 Atlantis, OV-104, crew eats preflight breakfast at KSC O and C Bldg

NASA Technical Reports Server (NTRS)

1989-01-01

STS-34 crewmembers, wearing mission t-shirts, eat preflight breakfast at Kennedy Space Center (KSC) Operations and Checkout (O and C) Building before boarding Atlantis, Orbiter Vehicle (OV) 104. Sitting around table (left to right) are Commmander Donald E. Williams, Mission Specialist (MS) Franklin R. Chang-Diaz, MS Shannon W. Lucid, MS Ellen S. Baker, and Pilot Michael J. McCulley. A jack-o-lantern (pumpkin) carved with the STS-34 mission insignia is in the center of the table decorated with a mission baseball cap and sitting atop a flight jacket.

Flying After Conducting an Aircraft Excessive Cabin Leakage Test.

PubMed

Houston, Stephen; Wilkinson, Elizabeth

2016-09-01

Aviation medical specialists should be aware that commercial airline aircraft engineers may undertake a 'dive equivalent' operation while conducting maintenance activities on the ground. We present a worked example of an occupational risk assessment to determine a minimum safe preflight surface interval (PFSI) for an engineer before flying home to base after conducting an Excessive Cabin Leakage Test (ECLT) on an unserviceable aircraft overseas. We use published dive tables to determine the minimum safe PFSI. The estimated maximum depth acquired during the procedure varies between 10 and 20 fsw and the typical estimated bottom time varies between 26 and 53 min for the aircraft types operated by the airline. Published dive tables suggest that no minimum PFSI is required for such a dive profile. Diving tables suggest that no minimum PFSI is required for the typical ECLT dive profile within the airline; however, having conducted a risk assessment, which considered peak altitude exposure during commercial flight, the worst-case scenario test dive profile, the variability of interindividual inert gas retention, and our existing policy among other occupational groups within the airline, we advised that, in the absence of a bespoke assessment of the particular circumstances on the day, the minimum PFSI after conducting ECLT should be 24 h. Houston S, Wilkinson E. Flying after conducting an aircraft excessive cabin leakage test. Aerosp Med Hum Perform. 2016; 87(9):816-820.

Flight effects on the aerodynamic and acoustic characteristics of inverted profile coannular nozzles, volume 3. [supersonic cruise aircraft research wind tunnel tests

NASA Technical Reports Server (NTRS)

Kozlowski, H.; Packman, A. B.

1978-01-01

Acoustic data from tests of the 0.75 area ratio coannular nozzle with ejector and the 1.2 area ratio coannular are presented in tables. Aerodynamic data acquired for the four test configurations are included.

An overview of the essential differences and similarities of system identification techniques

NASA Technical Reports Server (NTRS)

Mehra, Raman K.

1991-01-01

Information is given in the form of outlines, graphs, tables and charts. Topics include system identification, Bayesian statistical decision theory, Maximum Likelihood Estimation, identification methods, structural mode identification using a stochastic realization algorithm, and identification results regarding membrane simulations and X-29 flutter flight test data.

Mobility Research for Future Vehicles: A Methodology to Create a Unified Trade-Off Environment for Advanced Aerospace Vehicle

DTIC Science & Technology

2016-11-15

First, a performance sweep of blade loading and advance ratio is run in RCAS to obtain the rotor induced and profile power required during flight...Figure 19 Wide Chord Blade ....................................................................................................................... 27...26 Table 3 Wide Chord Blade NDARC Parameters

Analysis of multispectral scanner (MSS) and Thematic Mapper (TM) performance (pre-launch and post-launch)

NASA Technical Reports Server (NTRS)

Barker, J. L.

1983-01-01

Tables and graphs show the results of the spectral, radiometric, and geometric characterization of LANDSAT 4 sensors associated with imagery and of the imagery associated with sensors and processing. Specifications for the various parameters are compared with the photoflight and flight values.

Military Manpower Training Report for FY 1976.

ERIC Educational Resources Information Center

Office of the Assistant Secretary of Defense for Manpower and Reserve Affairs (DOD), Washington, DC.

The document presents anticipated needs and costs for training military personnel in FY 1976, based on national security objectives. Training loads for each of the following categories are presented with supporting tables: (1) recruit training, (2) officer acquisition training, (3) specialized skill training, (4) flight training programs, and (5)…

Checking Flight Rules with TraceContract: Application of a Scala DSL for Trace Analysis

NASA Technical Reports Server (NTRS)

Barringer, Howard; Havelund, Klaus; Morris, Robert A.

2011-01-01

Typically during the design and development of a NASA space mission, rules and constraints are identified to help reduce reasons for failure during operations. These flight rules are usually captured in a set of indexed tables, containing rule descriptions, rationales for the rules, and other information. Flight rules can be part of manual operations procedures carried out by humans. However, they can also be automated, and either implemented as on-board monitors, or as ground based monitors that are part of a ground data system. In the case of automated flight rules, one considerable expense to be addressed for any mission is the extensive process by which system engineers express flight rules in prose, software developers translate these requirements into code, and then both experts verify that the resulting application is correct. This paper explores the potential benefits of using an internal Scala DSL for general trace analysis, named TRACECONTRACT, to write executable specifications of flight rules. TRACECONTRACT can generally be applied to analysis of for example log files or for monitoring executing systems online.

ADF/ADC Web Tools for Browsing and Visualizing Astronomical Catalogs and NASA Astrophysics Mission Metadata

NASA Astrophysics Data System (ADS)

Shaya, E.; Kargatis, V.; Blackwell, J.; Borne, K.; White, R. A.; Cheung, C.

1998-05-01

Several new web based services have been introduced this year by the Astrophysics Data Facility (ADF) at the NASA Goddard Space Flight Center. IMPReSS is a graphical interface to astrophysics databases that presents the user with the footprints of observations of space-based missions. It also aids astronomers in retrieving these data by sending requests to distributed data archives. The VIEWER is a reader of ADC astronomical catalogs and journal tables that allows subsetting of catalogs by column choices and range selection and provides database-like search capability within each table. With it, the user can easily find the table data most appropriate for their purposes and then download either the subset table or the original table. CATSEYE is a tool that plots output tables from the VIEWER (and soon AMASE), making exploring the datasets fast and easy. Having completed the basic functionality of these systems, we are enhancing the site to provide advanced functionality. These will include: market basket storage of tables and records of VIEWER output for IMPReSS and AstroBrowse queries, non-HTML table responses to AstroBrowse type queries, general column arithmetic, modularity to allow entrance into the sequence of web pages at any point, histogram plots, navigable maps, and overplotting of catalog objects on mission footprint maps. When completed, the ADF/ADC web facilities will provide astronomical tabled data and mission retrieval information in several hyperlinked environments geared for users at any level, from the school student to the typical astronomer to the expert datamining tools at state-of-the-art data centers.

Flight Test Series 3: Flight Test Report

NASA Technical Reports Server (NTRS)

Marston, Mike; Sternberg, Daniel; Valkov, Steffi

2015-01-01

This document is a flight test report from the Operational perspective for Flight Test Series 3, a subpart of the Unmanned Aircraft System (UAS) Integration in the National Airspace System (NAS) project. Flight Test Series 3 testing began on June 15, 2015, and concluded on August 12, 2015. Participants included NASA Ames Research Center, NASA Armstrong Flight Research Center, NASA Glenn Research Center, NASA Langley Research center, General Atomics Aeronautical Systems, Inc., and Honeywell. Key stakeholders analyzed their System Under Test (SUT) in two distinct configurations. Configuration 1, known as Pairwise Encounters, was subdivided into two parts: 1a, involving a low-speed UAS ownship and intruder(s), and 1b, involving a high-speed surrogate ownship and intruder. Configuration 2, known as Full Mission, involved a surrogate ownship, live intruder(s), and integrated virtual traffic. Table 1 is a summary of flights for each configuration, with data collection flights highlighted in green. Section 2 and 3 of this report give an in-depth description of the flight test period, aircraft involved, flight crew, and mission team. Overall, Flight Test 3 gathered excellent data for each SUT. We attribute this successful outcome in large part from the experience that was acquired from the ACAS Xu SS flight test flown in December 2014. Configuration 1 was a tremendous success, thanks to the training, member participation, integration/testing, and in-depth analysis of the flight points. Although Configuration 2 flights were cancelled after 3 data collection flights due to various problems, the lessons learned from this will help the UAS in the NAS project move forward successfully in future flight phases.

Drift Rates of Three Micro-g LaCoste Turnkey Airborne Gravity Systems (TAGS) Used for the GRAV-D Project

NASA Astrophysics Data System (ADS)

Preaux, S. A.; Crump, B.; Damiani, T.

2015-12-01

The Gravity for the Redefinition of the American Vertical Datum (GRAV-D) project of NOAA's National Geodetic Survey has been collecting airborne gravity data since 2008 using 3 TAGS gravimeters, S-137, S-160 and S-161 (Table 1). The 38 surveys contain 1697 gravimeter calibration readings taken when the aircraft is parked on the ground before and after each flight, called still readings. This dataset is uniquely suited to examine the drift characteristics of these instruments. This study is broken into 3 parts: re-computation of individual still reading values; examination of drift rates during flights and surveys; and examination of long term drift rates. Re-computation of still readings was accomplished by isolating the least-noisy 10-minute segment of gravity data while the aircraft was parked and the beam unclamped. This automated method worked in most cases, but a small number of readings required further examination. This method improved the consistency of pre- and post-flight still readings as compared to those recorded in the field. Preliminary results indicate that the drift rate for these 3 instruments during a typical survey period is both small (95% smaller than 0.35 mGal/day) and linear. The average drift rate during a survey is -0.11 mGal/day with a standard deviation of 0.12 mGal/day (Figure 1). Still readings for most surveys were well represented by a linear trend, but a small number have curvature or discontinuities. The nature and cause of this non-linearity will be investigated. Early results show a long term linear drift rate for these 3 gravimeters between 0.01 and 0.04 mGal/day. There also appears to be significant non-linear variability. Comparing the 1.5-2 year time series of still readings from S-160 and S-161 with the 7.5 year time series for S-137, indicates that data from more than two years are needed to accurately characterize the long-term behavior. Instrumentation and processing causes for this non-linearity will be explored. Table1. Number of surveys and still reading and duration of use for each Gravimeter Meter # of surveys # still readings Duration of use S-137 27 1205 7.5 years S-160 4 288 1.5 years S-161 7 204 2 years

Summary of shuttle data processing and aerodynamic performance comparisons for the first 11 flights

NASA Technical Reports Server (NTRS)

Findlay, J. T.; Kelly, G. M.; Heck, M. L.; Mcconnell, J. G.

1984-01-01

NASA Space Shuttle aerodynamic and aerothermodynamic research is but one part of the most comprehensive end-to-end flight test program ever undertaken considering: the extensive pre-flight experimental data base development; the multitude of spacecraft and remote measurements taken during entry flight; the complexity of the Orbiter aerodynamic configuration; the variety of flight conditions available across the entire speed regime; and the efforts devoted to flight data reduction throughout the aerospace community. Shuttle entry flights provide a wealth of research quality data, in essence a veritable flying wind tunnel, for use by researchers to verify and improve the operational capability of the Orbiter and provide data for evaluations of experimental facilities as well as computational methods. This final report merely summarizes the major activities conducted by the AMA, Inc. under NASA Contract NAS1-16087 as part of that interesting research. Investigators desiring more detailed information can refer to the glossary of AMA publications attached herein as Appendix A. Section I provides background discussion of software and methodology development to enable Best Estimate Trajectory (BET) generation. Actual products generated are summarized in Section II as tables which completely describe the post-flight products available from the first three-year Shuttle flight history. Summary results are presented in Section III, with longitudinal performance comparisons included as Appendices for each of the flights.

Selected Lessons Learned in Space Shuttle Orbiter Propulsion and Power Subsystems

NASA Technical Reports Server (NTRS)

Hernandez, Francisco J.; Martinez, Hugo; Ryan, Abigail; Westover, Shayne; Davies, Frank

2011-01-01

Over its 30 years of space flight history, plus the nearly 10 years of design, development test and evaluation, the Space Shuttle Orbiter is full of lessons learned in all of its numerous and complex subsystems. In the current paper, only selected lessons learned in the areas of the Orbiter propulsion and power subsystems will be described. The particular Orbiter subsystems include: Auxiliary Power Unit (APU), Hydraulics and Water Spray Boiler (WSB), Mechanical Flight Controls, Main Propulsion System (MPS), Fuel Cells and Power Reactant and Storage Devices (PRSD), Orbital Maneuvering System (OMS), Reaction Control System (RCS), Electrical Power Distribution (EPDC), electrical wiring and pyrotechnics. Given the complexity and extensive history of each of these subsystems, and the limited scope of this paper, it is impossible to include most of the lessons learned; instead the attempt will be to present a selected few or key lessons, in the judgment of the authors. Each subsystem is presented separate, beginning with an overview of the hardware and their function, a short description of a few historical problems and their lessons, followed by a more comprehensive table listing of the major subsystem problems and lessons. These tables serve as a quick reference for lessons learned in each subsystem. In addition, this paper will establish common lessons across subsystems as well as concentrate on those lessons which are deemed to have the highest applicability to future space flight programs.

Solder Joint Health Monitoring Testbed

NASA Technical Reports Server (NTRS)

Delaney, Michael M.; Flynn, James; Browder, Mark

2009-01-01

A method of monitoring the health of selected solder joints, called SJ-BIST, has been developed by Ridgetop Group Inc. under a Small Business Innovative Research (SBIR) contract. The primary goal of this research program is to test and validate this method in a flight environment using realistically seeded faults in selected solder joints. An additional objective is to gather environmental data for future development of physics-based and data-driven prognostics algorithms. A test board is being designed using a Xilinx FPGA. These boards will be tested both in flight and on the ground using a shaker table and an altitude chamber.

Aeroacoustics of Flight Vehicles: Theory and Practice. Volume 1: Noise Sources

NASA Technical Reports Server (NTRS)

Hubbard, Harvey H. (Editor)

1991-01-01

Methodology recommended to evaluate aeroacoustic related problems is provided, and approaches to their solutions are suggested without extensive tables, nomographs, and derivations. Orientation is toward flight vehicles and emphasis is on underlying physical concepts. Theoretical, experimental, and applied aspects are covered, including the main formulations and comparisons of theory and experiment. The topics covered include: propeller and propfan noise, rotor noise, turbomachinery noise, jet noise classical theory and experiments, noise from turbulent shear flows, jet noise generated by large-scale coherent motion, airframe noise, propulsive lift noise, combustion and core noise, and sonic booms.

Interim-Night Integrated Goggle Head Tracking System (I-Nights). Volume 1. Ground Test Summary

DTIC Science & Technology

1992-08-01

A/WDP _ DATE: I COORDINATION: NWC 04_______ DATE: 7914401 COORDINATION: USD/ YAGO DATE:9 4/ APPROVED BY: ESD/YAff-1DST j T [!1! / 624 TABLE OF CONTENTS...B/U YAGO ) Voltmeter 1 NWC Voltage Standard 1 NWC (CAL Lab) Soldering Iron 1 NWC O-Scope 1 NWC LPU-9D Life Preserver/ Surv. Vest 1 YAGO G-Suit (Large...1 YAGO Large Flight Boots 1 YAGO Ex-Large Flight Suit 1 YAGO ADAM #12 (Large) I Holloman ADAM I-NIGHTS Liners 3 (1 per vendor) AAMRL/BBM 5% Hybrid

Overview and Status of the Laser Communication Relay Demonstration

NASA Technical Reports Server (NTRS)

Luzhanskiy, E.; Edwards, B.; Israel, D.; Cornwell, D.; Staren, J.; Cummings, N.; Roberts, T.; Patschke, R.

2016-01-01

NASA is presently developing first all optical high data rate satellite relay system, LCRD. To be flown on commercial geosynchronous satellite, it will communicate at DPSK and PPM modulation formats up to 1.244 Gbps. LCRD flight payload is being developed by NASA's Goddard Space Flight Center. The two ground stations, one on Table Mountain in CA, developed by NASA's Jet Propulsion Laboratory and another on Hawaiian island will enable bi-directional relay operation and ground sites diversity experiments. In this paper we will report on the current state of LCRD system development, planned operational scenarios and expected system performance.

New in-flight calibration adjustment of the Nimbus 6 and 7 earth radiation budget wide field of view radiometers

NASA Technical Reports Server (NTRS)

Kyle, H. L.; House, F. B.; Ardanuy, P. E.; Jacobowitz, H.; Maschhoff, R. H.; Hickey, J. R.

1984-01-01

In-flight calibration adjustments are developed to process data obtained from the wide-field-of-view channels of Nimbus-6 and Nimbus-7 after the failure of the Nimbus-7 longwave scanner on June 22, 1980. The sensor characteristics are investigated; the satellite environment is examined in detail; and algorithms are constructed to correct for long-term sensor-response changes, on/off-cycle thermal transients, and filter-dome absorption of longwave radiation. Data and results are presented in graphs and tables, including comparisons of the old and new algorithms.

KSC00pp1847

NASA Image and Video Library

2000-12-07

KENNEDY SPACE CENTER, FLA. -- As part of In-Flight Maintenance training, members of the STS-107 crew check out one of the Biotube experiments that will be part of their research mission. From left (in uniform) are Payload Specialist Ilan Ramon of Israel, Mission Specialists David M. Brown and Kalpana Chawla, Pilot William C. “Willie” McCool (crouching behind the table), Commander Rick D. Husband, and Mission Specialist Laurel Clark. STS-107 will carry the SPACEHAB Double Module in its first research flight into space and a broad collection of experiments ranging from material science to life science. It is scheduled to launch July 19, 2001

KSC-00pp1847

NASA Image and Video Library

2000-12-07

KENNEDY SPACE CENTER, FLA. -- As part of In-Flight Maintenance training, members of the STS-107 crew check out one of the Biotube experiments that will be part of their research mission. From left (in uniform) are Payload Specialist Ilan Ramon of Israel, Mission Specialists David M. Brown and Kalpana Chawla, Pilot William C. “Willie” McCool (crouching behind the table), Commander Rick D. Husband, and Mission Specialist Laurel Clark. STS-107 will carry the SPACEHAB Double Module in its first research flight into space and a broad collection of experiments ranging from material science to life science. It is scheduled to launch July 19, 2001

Airborne and Ground-Based Measurements Using a High-Performance Raman Lidar. Part 2; Ground Based

NASA Technical Reports Server (NTRS)

Whiteman, David N.; Cadirola, Martin; Venable, Demetrius; Connell, Rasheen; Rush, Kurt; Leblanc, Thierry; McDermid, Stuart

2009-01-01

The same RASL hardware as described in part I was installed in a ground-based mobile trailer and used in a water vapor lidar intercomparison campaign, hosted at Table Mountain, CA, under the auspices of the Network for the Detection of Atmospheric Composition Change (NDACC). The converted RASL hardware demonstrated high sensitivity to lower stratospheric water vapor indicating that profiling water vapor at those altitudes with sufficient accuracy to monitor climate change is possible. The measurements from Table Mountain also were used to explain the reason, and correct , for sub-optimal airborne aerosol extinction performance during the flight campaign.

Encyclopedia: Satellites and Sounding Rockets, August 1959 - December 1969

NASA Technical Reports Server (NTRS)

1970-01-01

Major space missions utilizing satellites or sounding rockets managed by the NASA Goddard Space Flight Center between August 1959 and December 1969 were documented. The information was presented in the following form: (1) description of each satellite project where Goddard was responsible for the spacecraft or the successful launch or both, with data such as launch characteristics, objectives, etc.; (2) description of each Goddard sounding rocket project, with the following data: sounding rocket type, vehicle number, experimental affiliation, and type of experiment; (3) brief description of current sounding rockets and launch vehicles; (4) table of tracking and data acquisition stations. Summary tables are also provided.

Test Record of Flight Tests Using Alcohol-to-Jet/JP-8 Blended Fuel

DTIC Science & Technology

2015-09-01

Fuel Pump Corrosion ……………………………………………………………….... 14, 15 2. Pre-Test Coke (carbon) Buildup on Swirl Cups in T55-GA-714A Engines …………………. 16 3...Post-Test Coke (carbon) Buildup on Swirl Cups in T55-GA-714A Engines ………………... 18 5 LIST OF TABLES Table Title Page 1...significant coke (carbon) buildup on the fuel nozzles and swirl cups was observed. The combustor section inspection criteria stipulates that any

32 CFR Table 1 to Part 855 - Purpose of Use/Verification/Approval Authority/Fees

Code of Federal Regulations, 2011 CFR

2011-07-01

... change of station, etc.) or for private, non revenue flights Social security number in block 1 on DD Form... of a uniformed service member Identification card (DD Form 1173) number or social security number... Form 1173) number or social security number, identification card expiration date, sponsor's retirement...

32 CFR Table 1 to Part 855 - Purpose of Use/Verification/Approval Authority/Fees

Code of Federal Regulations, 2013 CFR

2013-07-01

... change of station, etc.) or for private, non revenue flights Social security number in block 1 on DD Form... of a uniformed service member Identification card (DD Form 1173) number or social security number... Form 1173) number or social security number, identification card expiration date, sponsor's retirement...

The Effects of Subthreshold Visual Cues on Flight Performance in the NUH-60FS Black Hawk Research Simulator

DTIC Science & Technology

2011-08-01

influenced your opinion of subthreshold priming/ subliminal messaging...17 10. After completing this experiment, do you have a positive or negative view of subthreshold priming/ subliminal ...0%) Table 9. Has participating in this experiment influenced your opinion of subthreshold priming/ subliminal messaging? Yes No Other

Development of Autonomous Unmanned Aerial Vehicle Platform: Modeling, Simulating, and Flight Testing

DTIC Science & Technology

2006-03-01

Eppler 193 Airfoil .............................................................. 58 Figure 18. Rascal Airfoil vs. Eppler 205 Airfoil ...53 Table 14. E193 Airfoil Data at Re = 204,200 ................................................................... 61 ...two hours. According to the manufacturer, the Rascal uses an airfoil married from two Eppler airfoils . The top airfoil is an Eppler 193, while the

75 FR 10552 - Noise Exposure Map Notice for Chandler Municipal Airport, Chandler, AZ

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-08

... shown in Table 6.6. Flight tracks for the existing and the five-year Noise Exposure Maps are found in... from the ultimate land use control and planning responsibilities of local government. These local... those public agencies and planning agencies with which consultation is required under section 47503 of...

Flight effects on the aerodynamic and acoustic characteristics of inverted profile coannular nozzles, volume 2. [supersonic cruise aircraft research wind tunnel tests

NASA Technical Reports Server (NTRS)

Kozlowski, H.; Packman, A. B.

1978-01-01

Data from the acoustic tests of the convergent reference nozzle and the 0.75 area ratio coannular nozzle are presented in tables. Data processing routines used to scale the acoustic data and to correct the data for atmospheric attenuation are included.

Changes in muscles accompanying non-weight-bearing and weightlessness

NASA Technical Reports Server (NTRS)

Tischler, M. E.; Henriksen, E. J.; Jaspers, S. R.; Jacob, S.; Kirby, C.

1989-01-01

Results of hindlimb suspension and space flight experiments with rats examine the effects of weightlessness simulation, weightlessness, and delay in postflight recovery of animals. Parameters examined were body mass, protein balance, amino acid metabolism, glucose and glycogen metabolism, and hormone levels. Tables show metabolic responses to unweighting of the soleus muscle.

Patient positioning in radiotherapy based on surface imaging using time of flight cameras

DOE Office of Scientific and Technical Information (OSTI.GOV)

Gilles, M., E-mail: marlene.gilles@univ-brest.fr

2016-08-15

Purpose: To evaluate the patient positioning accuracy in radiotherapy using a stereo-time of flight (ToF)-camera system. Methods: A system using two ToF cameras was used to scan the surface of the patients in order to position them daily on the treatment couch. The obtained point clouds were registered to (a) detect translations applied to the table (intrafraction motion) and (b) predict the displacement to be applied in order to place the patient in its reference position (interfraction motion). The measures provided by this system were compared to the effectively applied translations. The authors analyzed 150 fractions including lung, pelvis/prostate, andmore » head and neck cancer patients. Results: The authors obtained small absolute errors for displacement detection: 0.8 ± 0.7, 0.8 ± 0.7, and 0.7 ± 0.6 mm along the vertical, longitudinal, and lateral axes, respectively, and 0.8 ± 0.7 mm for the total norm displacement. Lung cancer patients presented the largest errors with a respective mean of 1.1 ± 0.9, 0.9 ± 0.9, and 0.8 ± 0.7 mm. Conclusions: The proposed stereo-ToF system allows for sufficient accuracy and faster patient repositioning in radiotherapy. Its capability to track the complete patient surface in real time could allow, in the future, not only for an accurate positioning but also a real time tracking of any patient intrafraction motion (translation, involuntary, and breathing).« less

Patient positioning in radiotherapy based on surface imaging using time of flight cameras.

PubMed

Gilles, M; Fayad, H; Miglierini, P; Clement, J F; Scheib, S; Cozzi, L; Bert, J; Boussion, N; Schick, U; Pradier, O; Visvikis, D

2016-08-01

To evaluate the patient positioning accuracy in radiotherapy using a stereo-time of flight (ToF)-camera system. A system using two ToF cameras was used to scan the surface of the patients in order to position them daily on the treatment couch. The obtained point clouds were registered to (a) detect translations applied to the table (intrafraction motion) and (b) predict the displacement to be applied in order to place the patient in its reference position (interfraction motion). The measures provided by this system were compared to the effectively applied translations. The authors analyzed 150 fractions including lung, pelvis/prostate, and head and neck cancer patients. The authors obtained small absolute errors for displacement detection: 0.8 ± 0.7, 0.8 ± 0.7, and 0.7 ± 0.6 mm along the vertical, longitudinal, and lateral axes, respectively, and 0.8 ± 0.7 mm for the total norm displacement. Lung cancer patients presented the largest errors with a respective mean of 1.1 ± 0.9, 0.9 ± 0.9, and 0.8 ± 0.7 mm. The proposed stereo-ToF system allows for sufficient accuracy and faster patient repositioning in radiotherapy. Its capability to track the complete patient surface in real time could allow, in the future, not only for an accurate positioning but also a real time tracking of any patient intrafraction motion (translation, involuntary, and breathing).

Laser Tracker Utilization Methodology in Measuring Truth Trajectories for INS Testing on 6 Degree of Freedom Table at the Marshall Space Flight Center's Contact Dynamics Simulation Laboratory with Lessons Learned

NASA Technical Reports Server (NTRS)

Leggett, Jared O.; Bryant, Thomas C.; Cowen, Charles T.; Clifton, Billy W.

2018-01-01

When performing Inertial Navigation System (INS) testing at the Marshall Space Flight Center's (MSFC) Contact Dynamics Simulation Laboratory (CDSL) early in 2017, a Leica Geosystems AT901 Laser Tracker system (LLT) measured the twist & sway trajectories as generated by the 6 Degree Of Freedom (6DOF) Table in the CDSL. These LLT measured trajectories were used in the INS software model validation effort. Several challenges were identified and overcome during the preparation for the INS testing, as well as numerous lessons learned. These challenges included determining the position and attitude of the LLT with respect to an INS-shared coordinate frame using surveyed monument locations in the CDSL and the accompanying mathematical transformation, accurately measuring the spatial relationship between the INS and a 6DOF tracking probe due to lack of INS visibility from the LLT location, obtaining the data from the LLT during a test, determining how to process the results for comparison with INS data in time and frequency domains, and using a sensitivity analysis of the results to verify the quality of the results. While many of these challenges were identified and overcome before or during testing, a significant lesson on test set-up was not learned until later in the data analysis process. It was found that a combination of trajectory-dependent gimbal locking and environmental noise introduced non-negligible noise in the angular measurements of the LLT that spanned the evaluated frequency spectrum. The lessons learned in this experiment may be useful for others performing INS testing in similar testing facilities.

Expedition 11 Preflight

NASA Image and Video Library

2005-04-10

European Space Agency astronaut Roberto Vittori, of Italy, left, and Expedition 11 Commander Sergei Krikalev participate in tilt table tests, Sunday, April 10, 2005, so technicians can collect pre-launch data on the state of their equilibrium prior to the April 15 launch to the International Space Station with Flight Engineer John Phillips in Baikonur, Kazakhstan. Photo Credit: (NASA/Bill Ingalls)

A Comparative Study of Soviet versus Western Helicopters. Part 1. General Comparison of Designs

DTIC Science & Technology

1983-03-01

kid in hover and in forward flight may be considerably different. Consequently, the validity of using the hovering point in conjunction with the two...coefficients computed for two porn -weight values, using data from Fig. .. 17. ,:.:. assumed a being correct, and is shown in Table 5.5 with the corresponding

Teacher is Space participant Christa McAuliffe during suite/hygiene briefing

NASA Technical Reports Server (NTRS)

1985-01-01

Teacher is Space participant Christa McAuliffe is briefed on her suit and on personal hygiene equipment to be used on the STS 51-L mission. She is standing in front of a table with several of the items to be used on the flight, including one can labeled DIAL and one can labeled BAN.

32 CFR Table 1 to Part 855 - Purpose of Use/Verification/Approval Authority/Fees

Code of Federal Regulations, 2014 CFR

2014-07-01

... change of station, etc.) or for private, non revenue flights Social security number in block 1 on DD Form... other available aircraft for official Government business travel Supervisor's endorsement in block 4 of... be listed in block 4 of the DD Form 2401. An official government document, such as an SF 1169, US...

32 CFR Table 1 to Part 855 - Purpose of Use/Verification/Approval Authority/Fees

Code of Federal Regulations, 2012 CFR

2012-07-01

... change of station, etc.) or for private, non revenue flights Social security number in block 1 on DD Form... other available aircraft for official Government business travel Supervisor's endorsement in block 4 of... be listed in block 4 of the DD Form 2401. An official government document, such as an SF 1169, US...

32 CFR Table 1 to Part 855 - Purpose of Use/Verification/Approval Authority/Fees

Code of Federal Regulations, 2010 CFR

2010-07-01

... change of station, etc.) or for private, non revenue flights Social security number in block 1 on DD Form... other available aircraft for official Government business travel Supervisor's endorsement in block 4 of... be listed in block 4 of the DD Form 2401. An official government document, such as an SF 1169, US...

14 CFR Appendix C to Part 135 - Helicopter Flight Recorder Specifications

Code of Federal Regulations, 2011 CFR

2011-01-01

.... (see Table 1, TSO C51-a) 1 25 to 150 ft. Magnetic heading 360° ±5° 1 1°. Vertical acceleration −3g to +6g ±0.2g in addition to ±0.3g maximum datum 4 (or 1 per second where peaks, ref. to 1g are recorded...

SDO FlatSat Facility

NASA Technical Reports Server (NTRS)

Amason, David L.

2008-01-01

The goal of the Solar Dynamics Observatory (SDO) is to understand and, ideally, predict the solar variations that influence life and society. It's instruments will measure the properties of the Sun and will take hifh definition images of the Sun every few seconds, all day every day. The FlatSat is a high fidelity electrical and functional representation of the SDO spacecraft bus. It is a high fidelity test bed for Integration & Test (I & T), flight software, and flight operations. For I & T purposes FlatSat will be a driver to development and dry run electrical integration procedures, STOL test procedures, page displays, and the command and telemetry database. FlatSat will also serve as a platform for flight software acceptance and systems testing for the flight software system component including the spacecraft main processors, power supply electronics, attitude control electronic, gimbal control electrons and the S-band communications card. FlatSat will also benefit the flight operations team through post-launch flight software code and table update development and verification and verification of new and updated flight operations products. This document highlights the benefits of FlatSat; describes the building of FlatSat; provides FlatSat facility requirements, access roles and responsibilities; and, and discusses FlatSat mechanical and electrical integration and functional testing.

The STS-98 crew gathers for snack before launch

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- The STS-98 crew gathers around a table for a snack before getting ready for launch on Space Shuttle Atlantis. Seated left to right are Mission Specialist Thomas Jones, Pilot Mark Polansky, Commander Ken Cockrell and Mission Specialists Marsha Ivins and Robert Curbeam. STS-98 is the seventh construction flight to the International Space Station. Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle'''s robotic arm. Three spacewalks, by Curbeam and Jones, are required to complete the planned construction work during the 11-day mission. Launch is targeted for 6:11 p.m. EST and the planned landing at KSC Feb. 18 about 1:39 p.m. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA'''s Space Shuttle program.

Airborne Turbulence Detection System Certification Tool Set

NASA Technical Reports Server (NTRS)

Hamilton, David W.; Proctor, Fred H.

2006-01-01

A methodology and a corresponding set of simulation tools for testing and evaluating turbulence detection sensors has been presented. The tool set is available to industry and the FAA for certification of radar based airborne turbulence detection systems. The tool set consists of simulated data sets representing convectively induced turbulence, an airborne radar simulation system, hazard tables to convert the radar observable to an aircraft load, documentation, a hazard metric "truth" algorithm, and criteria for scoring the predictions. Analysis indicates that flight test data supports spatial buffers for scoring detections. Also, flight data and demonstrations with the tool set suggest the need for a magnitude buffer.

KSC-2009-4333

NASA Image and Video Library

2009-07-30

CAPE CANAVERAL, Fla. – Norman R. Augustine, retired chairman and CEO of Lockheed Martin Corp., is seated at the conference table for the Augustine Commission, meeting in Cocoa Beach, Fla. At the request of the Office of Science and Technology Policy, NASA established the Review of U.S. Human Space Flight Plans Committee, known as the Augustine Commission. Chaired by Augustine, the committee is conducting an independent review of ongoing U.S. human spaceflight plans and programs, as well as alternatives, to ensure the nation is pursuing the best trajectory for the future of human space flight - one that is safe, innovative, affordable, and sustainable. Photo credit: NASA/Jim Grossmann

Investigation of remote sensing to detect near-surface groundwater on irrigated lands

NASA Technical Reports Server (NTRS)

Ryland, D. W.; Schmer, F. A.; Moore, D. G.

1975-01-01

The application of remote sensing techniques was studied for detecting areas with high water tables in irrigated agricultural lands. Aerial data were collected by the LANDSAT-1 satellite and aircraft over the Kansas/Bostwick Irrigation District in Republic and Jewell Counties, Kansas. LANDSAT-1 data for May 12 and August 10, 1973, and aircraft flights (midday and predawn) on August 10 and 11, 1973, and June 25 and 26, 1974, were obtained. Surface and water table contour maps and active observation well hydrographs were obtained from the Bureau of Reclamation for use in the analysis. Results of the study reveal that LANDSAT-1 data (May MSS band 6 and August MSS band 7) correlate significantly (0.01 level) with water table depth for 144 active observation wells located throughout the Kansas/Bostwick Irrigation District. However, a map of water table depths of less than 1.83 meters prepared from the LANDSAT-1 data did not compare favorably with a map of seeped lands of less than 1.22 m (4 feet) to the water table. Field evaluation of the map is necessary for a complete analysis. Analysis of three fields on a within or single-field basis for the 1973 LANDSAT-1 data also showed significant correlation results.

Mortality From Neurodegenerative Diseases in a Cohort of US Flight Attendants

PubMed Central

Pinkerton, Lynne E.; Hein, Misty J.; Grajewski, Barbara; Kamel, Freya

2016-01-01

Background Concern exists about the potential chronic neurological effects among aircrew of exposure to chemical contaminants from engine oil in aircraft cabin air. We evaluated mortality from neurodegenerative diseases among 11,311 former US flight attendants. Methods Vital status was ascertained through 2007, and life table analyses were conducted to obtain standardized mortality ratios (SMRs). Results Amyotrophic lateral sclerosis (ALS) mortality was over twice as high in the cohort as in the US general population, based on nine observed ALS deaths. There was no clear pattern in risk when SMRs for ALS were stratified by exposure duration. Mortality from other neurodegenerative diseases was not elevated. Conclusions Our findings are limited due to small numbers of observed deaths and reliance on mortality data, but suggest that flight attendants may have an increased risk of ALS. Additional research is needed. PMID:27184412

Hydra Rendezvous and Docking Sensor

NASA Technical Reports Server (NTRS)

Roe, Fred; Carrington, Connie

2007-01-01

The U.S. technology to support a CEV AR&D activity is mature and was developed by NASA and supporting industry during an extensive research and development program conducted during the 1990's and early 2000 time frame at the Marshall Space Flight Center. Development and demonstration of a rendezvous/docking sensor was identified early in the AR&D Program as the critical enabling technology that allows automated proxinity operations and docking. A first generation rendezvous/docking sensor, the Video Guidance Sensor (VGS) was developed and successfully flown on STS 87 and again on STS 95, proving the concept of a video-based sensor. Advances in both video and signal processing technologies and the lessons learned from the two successful flight experiments provided a baseline for the development of a new generation of video based rendezvous/docking sensor. The Advanced Video Guidance Sensor (AVGS) has greatly increased performance and additional capability for longer-range operation. A Demonstration Automatic Rendezvous Technology (DART) flight experiment was flown in April 2005 using AVGS as the primary proximity operations sensor. Because of the absence of a docking mechanism on the target satellite, this mission did not demonstrate the ability of the sensor to coltrold ocking. Mission results indicate that the rendezvous sensor operated successfully in "spot mode" (2 km acquisition of the target, bearing data only) but was never commanded to "acquire and track" the docking target. Parts obsolescence issues prevent the construction of current design AVGS units to support the NASA Exploration initiative. This flight proven AR&D technology is being modularized and upgraded with additional capabilities through the Hydra project at the Marshall Space Flight Center. Hydra brings a unique engineering approach and sensor architecture to the table, to solve the continuing issues of parts obsolescence and multiple sensor integration. This paper presents an approach to sensor hardware trades, to address the needs of future vehicles that may rendezvous and dock with the International Space Station (ISS). It will also discuss approaches for upgrading AVGS to address parts obsolescence, and concepts for modularizing the sensor to provide configuration flexibility for multiple vehicle applications. Options for complementary sensors to be integrated into the multi-head Hydra system will also be presented. Complementary sensor options include ULTOR, a digital image correlator system that could provide relative six-degree-of-freedom information independently from AVGS, and time-of-flight sensors, which determine the range between vehicles by timing pulses that travel from the sensor to the target and back. Common targets and integrated targets, suitable for use with the multi-sensor options in Hydra, will also be addressed.

Causal Factors and Adverse Events of Aviation Accidents and Incidents Related to Integrated Vehicle Health Management

NASA Technical Reports Server (NTRS)

Reveley, Mary S.; Briggs, Jeffrey L.; Evans, Joni K.; Jones, Sharon M.; Kurtoglu, Tolga; Leone, Karen M.; Sandifer, Carl E.

2011-01-01

Causal factors in aviation accidents and incidents related to system/component failure/malfunction (SCFM) were examined for Federal Aviation Regulation Parts 121 and 135 operations to establish future requirements for the NASA Aviation Safety Program s Integrated Vehicle Health Management (IVHM) Project. Data analyzed includes National Transportation Safety Board (NSTB) accident data (1988 to 2003), Federal Aviation Administration (FAA) incident data (1988 to 2003), and Aviation Safety Reporting System (ASRS) incident data (1993 to 2008). Failure modes and effects analyses were examined to identify possible modes of SCFM. A table of potential adverse conditions was developed to help evaluate IVHM research technologies. Tables present details of specific SCFM for the incidents and accidents. Of the 370 NTSB accidents affected by SCFM, 48 percent involved the engine or fuel system, and 31 percent involved landing gear or hydraulic failure and malfunctions. A total of 35 percent of all SCFM accidents were caused by improper maintenance. Of the 7732 FAA database incidents affected by SCFM, 33 percent involved landing gear or hydraulics, and 33 percent involved the engine and fuel system. The most frequent SCFM found in ASRS were turbine engine, pressurization system, hydraulic main system, flight management system/flight management computer, and engine. Because the IVHM Project does not address maintenance issues, and landing gear and hydraulic systems accidents are usually not fatal, the focus of research should be those SCFMs that occur in the engine/fuel and flight control/structures systems as well as power systems.

Miniaturized Autonomous Extravehicular Robotic Camera (Mini AERCam)

NASA Technical Reports Server (NTRS)

Fredrickson, Steven E.

2001-01-01

The NASA Johnson Space Center (JSC) Engineering Directorate is developing the Autonomous Extravehicular Robotic Camera (AERCam), a low-volume, low-mass free-flying camera system . AERCam project team personnel recently initiated development of a miniaturized version of AERCam known as Mini AERCam. The Mini AERCam target design is a spherical "nanosatellite" free-flyer 7.5 inches in diameter and weighing 1 0 pounds. Mini AERCam is building on the success of the AERCam Sprint STS-87 flight experiment by adding new on-board sensing and processing capabilities while simultaneously reducing volume by 80%. Achieving enhanced capability in a smaller package depends on applying miniaturization technology across virtually all subsystems. Technology innovations being incorporated include micro electromechanical system (MEMS) gyros, "camera-on-a-chip" CMOS imagers, rechargeable xenon gas propulsion system , rechargeable lithium ion battery, custom avionics based on the PowerPC 740 microprocessor, GPS relative navigation, digital radio frequency communications and tracking, micropatch antennas, digital instrumentation, and dense mechanical packaging. The Mini AERCam free-flyer will initially be integrated into an approximate flight-like configuration for demonstration on an airbearing table. A pilot-in-the-loop and hardware-in-the-loop simulation to simulate on-orbit navigation and dynamics will complement the airbearing table demonstration. The Mini AERCam lab demonstration is intended to form the basis for future development of an AERCam flight system that provides beneficial on-orbit views unobtainable from fixed cameras, cameras on robotic manipulators, or cameras carried by EVA crewmembers.

Mini AERCam: A Free-Flying Robot for Space Inspection

NASA Technical Reports Server (NTRS)

Fredrickson, Steven

2001-01-01

The NASA Johnson Space Center Engineering Directorate is developing the Autonomous Extravehicular Robotic Camera (AERCam), a free-flying camera system for remote viewing and inspection of human spacecraft. The AERCam project team is currently developing a miniaturized version of AERCam known as Mini AERCam, a spherical nanosatellite 7.5 inches in diameter. Mini AERCam development builds on the success of AERCam Sprint, a 1997 Space Shuttle flight experiment, by integrating new on-board sensing and processing capabilities while simultaneously reducing volume by 80%. Achieving these productivity-enhancing capabilities in a smaller package depends on aggressive component miniaturization. Technology innovations being incorporated include micro electromechanical system (MEMS) gyros, "camera-on-a-chip" CMOS imagers, rechargeable xenon gas propulsion, rechargeable lithium ion battery, custom avionics based on the PowerPC 740 microprocessor, GPS relative navigation, digital radio frequency communications and tracking, micropatch antennas, digital instrumentation, and dense mechanical packaging. The Mini AERCam free-flyer will initially be integrated into an approximate flight-like configuration for laboratory demonstration on an airbearing table. A pilot-in-the-loop and hardware-in-the-loop simulation to simulate on-orbit navigation and dynamics will complement the airbearing table demonstration. The Mini AERCam lab demonstration is intended to form the basis for future development of an AERCam flight system that provides on-orbit views of the Space Shuttle and International Space Station unobtainable from fixed cameras, cameras on robotic manipulators, or cameras carried by space-walking crewmembers.

New Generation General Purpose Computer (GPC) compact IBM unit

NASA Technical Reports Server (NTRS)

1991-01-01

New Generation General Purpose Computer (GPC) compact IBM unit replaces a two-unit earlier generation computer. The new IBM unit is documented in table top views alone (S91-26867, S91-26868), with the onboard equipment it supports including the flight deck CRT screen and keypad (S91-26866), and next to the two earlier versions it replaces (S91-26869).

Digital Flight Control System Validation.

DTIC Science & Technology

1982-06-01

dastia Lfe syal. an ideatIled in figure I sad table 3. -Fm. sad~~b~ vaw." Tomm abm occu I A Pas sr be eveated, the Structue built upon it r must be...to base the Kseetles faiuLte pruiletles ad Specifi sytem . falue. prob- ability forat lo MoSigt will be 10 bue IMPeLASt Is the requiminas fog mnds

77 FR 51462 - Airworthiness Directives; BRP-Powertrain GmbH & Co KG Rotax Reciprocating Engines

Federal Register 2010, 2011, 2012, 2013, 2014

2012-08-24

... landing and damage to the airplane. DATES: This AD becomes effective September 10, 2012. We must receive... carburetor, which could result in an in-flight engine shutdown, forced landing and damage to the airplane. (e... pump with an S/N listed in Table 1 to paragraph (c) of this AD in any airplane unless it has been...

Advanced Crash Survivable Flight Data Recorder And Accident Information Retrieval System (AIRS).

DTIC Science & Technology

1981-08-01

Costs ................................. 151 Portable Ground Unit (PGU) ............................... 151 Maintenance Readout Unit ( MRU ...95 31 NARROW-BAND CONDUCTED EMISSIONS ON THE AIRS 24 VDC POWER RETURN (CE04 TESI ) ......................... 96 32 BROAD-BAND...Shunt) N/A Any Any Change Change MRU (Shunt) N/A Any Any ...... _Change Change PGU (Shunt) N/A --- Any Any Change Change 15 .. . . .i A, TABLE 4

Improved UUV Positioning Using Acoustic Communications and a Potential for Real-Time Networking and Collaboration

DTIC Science & Technology

2017-06-01

12 III. ACOUSTIC WAVE TRAVEL TIME ESTIMATION...Mission ...............................125 Table 8. Average Horizontal Distance from the UUV to the Reference Points when a Travel Time Measurement is...Taken ............................................126 Table 9. Average UUV Depth when a Travel Time Measurement is Taken .........126 Table 10. Ratio

Analysis of 100 pharmaceuticals and their degradates in water samples by liquid chromatography/quadrupole time-of-flight mass spectrometry.

PubMed

Ferrer, Imma; Thurman, E Michael

2012-10-12

A straightforward methodology for the chromatographic separation and accurate mass identification of 100 pharmaceuticals including some of their degradation products was developed using liquid chromatography/quadrupole time-of-flight mass spectrometry (LC/Q-TOF-MS). A table compiling the protonated or deprotonated exact masses for all compounds, as well as the exact mass of several fragment ions obtained by MS-MS is included. Excellent chromatographic separation was achieved by using 3.5 μm particle size columns and a slow and generic 30-min gradient. Isobaric and isomeric compounds (same nominal mass and same exact mass, respectively) were distinguished by various methods, including chromatography separation, MS-MS fragmentation, and isotopic signal identification. Method reporting limits of detection ranged from 1 to 1000 ng/L, after solid-phase extraction of 100mL aqueous samples. The methodology was successfully applied to the analysis of surface water impacted by wastewater effluent by identifying many of the pharmaceuticals and metabolites included in the list. Examples are given for some of the most unusual findings in environmental samples. This paper is meant to serve as a guide for those doing analysis of pharmaceuticals in environmental samples, by providing exact mass measurements of several well known, as well as newly identified and environmentally relevant pharmaceuticals in water samples. Copyright © 2012 Elsevier B.V. All rights reserved.

High Speed Civil Transport Aircraft Simulation: Reference-H Cycle 1, MATLAB Implementation

NASA Technical Reports Server (NTRS)

Sotack, Robert A.; Chowdhry, Rajiv S.; Buttrill, Carey S.

1999-01-01

The mathematical model and associated code to simulate a high speed civil transport aircraft - the Boeing Reference H configuration - are described. The simulation was constructed in support of advanced control law research. In addition to providing time histories of the dynamic response, the code includes the capabilities for calculating trim solutions and for generating linear models. The simulation relies on the nonlinear, six-degree-of-freedom equations which govern the motion of a rigid aircraft in atmospheric flight. The 1962 Standard Atmosphere Tables are used along with a turbulence model to simulate the Earth atmosphere. The aircraft model has three parts - an aerodynamic model, an engine model, and a mass model. These models use the data from the Boeing Reference H cycle 1 simulation data base. Models for the actuator dynamics, landing gear, and flight control system are not included in this aircraft model. Dynamic responses generated by the nonlinear simulation are presented and compared with results generated from alternate simulations at Boeing Commercial Aircraft Company and NASA Langley Research Center. Also, dynamic responses generated using linear models are presented and compared with dynamic responses generated using the nonlinear simulation.

STS-92 Mission Specialist Chiao looks over equipment during pre- pack

NASA Technical Reports Server (NTRS)

2000-01-01

During pre-pack and fit check in the Operations and Checkout Building, STS-92 Mission Specialist Koichi Wakata of Japan looks over the equipment he will be wearing during launch and entry, such as the helmet and gloves on the table. Wakata and the rest of the crew are at KSC for Terminal Countdown Demonstration Test activities. The TCDT provides emergency egress training, simulated countdown exercises and opportunities to inspect the mission payload. This mission will be Wakata's second Shuttle flight. STS-92 is scheduled to launch Oct. 5 at 9:38 p.m. EDT from Launch Pad 39A on the fifth flight to the International Space Station. It will carry two elements of the Space Station, the Integrated Truss Structure Z1 and the third Pressurized Mating Adapter. The mission is also the 100th flight in the Shuttle program.

Impact of time-resolved MRA on diagnostic accuracy in patients with symptomatic peripheral artery disease of the calf station.

PubMed

Hansmann, Jan; Michaely, Henrik J; Morelli, John N; Diehl, Steffen J; Meyer, Mathias; Schoenberg, Stefan O; Attenberger, Ulrike I

2013-12-01

The purpose of this article is to evaluate the added diagnostic accuracy of time-resolved MR angiography (MRA) of the calves compared with continuous-table-movement MRA in patients with symptomatic lower extremity peripheral artery disease (PAD) using digital subtraction angiography (DSA) correlation. Eighty-four consecutive patients with symptomatic PAD underwent a low-dose 3-T MRA protocol, consisting of continuous-table-movement MRA, acquired from the diaphragm to the calves, and an additional time-resolved MRA of the calves; 0.1 mmol/kg body weight (bw) of contrast material was used (0.07 mmol/kg bw for continuous-table-movement MRA and 0.03 mmol/kg bw for time-resolved MRA). Two radiologists rated image quality on a 4-point scale and stenosis degree on a 3-point scale. An additional assessment determined the degree of venous contamination and whether time-resolved MRA improved diagnostic confidence. The accuracy of stenosis gradation with continuous-table-movement and time-resolved MRA was compared with that of DSA as a correlation. Overall diagnostic accuracy was calculated for continuous-table-movement and time-resolved MRA. Median image quality was rated as good for 578 vessel segments with continuous-table-movement MRA and as excellent for 565 vessel segments with time-resolved MRA. Interreader agreement was excellent (κ = 0.80-0.84). Venous contamination interfered with diagnosis in more than 60% of continuous-table-movement MRA examinations. The degree of stenosis was assessed for 340 vessel segments. The diagnostic accuracies (continuous-table-movement MRA/time-resolved MRA) combined for the readers were obtained for the tibioperoneal trunk (84%/93%), anterior tibial (69%/87%), posterior tibial (85%/91%), and peroneal (67%/81%) arteries. The addition of time-resolved MRA improved diagnostic confidence in 69% of examinations. The addition of time-resolved MRA at the calf station improves diagnostic accuracy over continuous-table-movement MRA alone in symptomatic patients with PAD.

A comparative study of visual reaction time in table tennis players and healthy controls.

PubMed

Bhabhor, Mahesh K; Vidja, Kalpesh; Bhanderi, Priti; Dodhia, Shital; Kathrotia, Rajesh; Joshi, Varsha

2013-01-01

Visual reaction time is time required to response to visual stimuli. The present study was conducted to measure visual reaction time in 209 subjects, 50 table tennis (TT) players and 159 healthy controls. The visual reaction time was measured by the direct RT computerized software in healthy controls and table tennis players. Simple visual reaction time was measured. During the reaction time testing, visual stimuli were given for eighteen times and average reaction time was taken as the final reaction time. The study shows that table tennis players had faster reaction time than healthy controls. On multivariate analysis, it was found that TT players had 74.121 sec (95% CI 98.8 and 49.4 sec) faster reaction time compared to non-TT players of same age and BMI. Also playing TT has a profound influence on visual reaction time than BMI. Our study concluded that persons involved in sports are having good reaction time as compared to controls. These results support the view that playing of table tennis is beneficial to eye-hand reaction time, improve the concentration and alertness.

Flight Services and Aircraft Access: Active Flow Control Vertical Tail and Insect Accretion and Mitigation Flight Test

NASA Technical Reports Server (NTRS)

Whalen, Edward A.

2016-01-01

This document serves as the final report for the Flight Services and Aircraft Access task order NNL14AA57T as part of NASA Environmentally Responsible Aviation (ERA) Project ITD12A+. It includes descriptions of flight test preparations and execution for the Active Flow Control (AFC) Vertical Tail and Insect Accretion and Mitigation (IAM) experiments conducted on the 757 ecoDemonstrator. For the AFC Vertical Tail, this is the culmination of efforts under two task orders. The task order was managed by Boeing Research & Technology and executed by an enterprise-wide Boeing team that included Boeing Research & Technology, Boeing Commercial Airplanes, Boeing Defense and Space and Boeing Test and Evaluation. Boeing BR&T in St. Louis was responsible for overall Boeing project management and coordination with NASA. The 757 flight test asset was provided and managed by the BCA ecoDemonstrator Program, in partnership with Stifel Aircraft Leasing and the TUI Group. With this report, all of the required deliverables related to management of this task order have been met and delivered to NASA as summarized in Table 1. In addition, this task order is part of a broader collaboration between NASA and Boeing.

Drinking and Flying: Does Alcohol Consumption Affect the Flight and Echolocation Performance of Phyllostomid Bats?

PubMed Central

Orbach, Dara N.; Veselka, Nina; Dzal, Yvonne; Lazure, Louis; Fenton, M. Brock

2010-01-01

Background In the wild, frugivorous and nectarivorous bats often eat fermenting fruits and nectar, and thus may consume levels of ethanol that could induce inebriation. To understand if consumption of ethanol by bats alters their access to food and general survival requires examination of behavioural responses to its ingestion, as well as assessment of interspecific variation in those responses. We predicted that bats fed ethanol would show impaired flight and echolocation behaviour compared to bats fed control sugar water, and that there would be behavioural differences among species. Methodology/Principal Findings We fed wild caught Artibeus jamaicensis, A. lituratus, A. phaeotis, Carollia sowelli, Glossophaga soricina, and Sturnira lilium (Chiroptera, Phyllostomidae) sugar water (44 g of table sugar in 500 ml of water) or sugar water with ethanol before challenging them to fly through an obstacle course while we simultaneously recorded their echolocation calls. We used bat saliva, a non-invasive proxy, to measure blood ethanol concentrations ranging from 0 to >0.3% immediately before flight trials. Flight performance and echolocation behaviour were not significantly affected by consumption of ethanol, but species differed in their blood alcohol concentrations after consuming it. Conclusions/Significance The bats we studied display a tolerance for ethanol that could have ramifications for the adaptive radiation of frugivorous and nectarivorous bats by allowing them to use ephemeral food resources over a wide span of time. By sampling across phyllostomid genera, we show that patterns of apparent ethanol tolerance in New World bats are broad, and thus may have been an important early step in the evolution of frugivory and nectarivory in these animals. PMID:20126552

KSC-2009-4337

NASA Image and Video Library

2009-07-30

CAPE CANAVERAL, Fla. – Bohdan Bejmuk, chair of Constellation Program Standing Review Board, is seated at the conference table for the introduces the Augustine Commission, meeting in Cocoa Beach, Fla. At the request of the Office of Science and Technology Policy, NASA established the Review of U.S. Human Space Flight Plans Committee, known as the Augustine Commission. Chaired by Norman R. Augustine, retired chairman and CEO of Lockheed Martin Corp., the committee is conducting an independent review of ongoing U.S. human spaceflight plans and programs, as well as alternatives, to ensure the nation is pursuing the best trajectory for the future of human space flight - one that is safe, innovative, affordable, and sustainable. Photo credit: NASA/Jim Grossmann

KSC00pp1846

NASA Image and Video Library

2000-12-07

KENNEDY SPACE CENTER, FLA. -- As part of In-Flight Maintenance training, members of the STS-107 crew check out one of the Biotube experiments that will be part of their research mission . From left (in uniform) are Mission Specialist David M. Brown, Payload Specialist Ilan Ramon of Israel, and Mission Specialist Kalpana Chawla; Pilot William C. “Willie” McCool (crouching behind the table); Commander Rick D. Husband; and Mission Specialist Laurel Clark. At right is project engineer April Boody. As a research mission, STS-107 will carry the SPACEHAB Double Module in its first research flight into space and a broad collection of experiments ranging from material science to life science. It is scheduled to launch July 19, 2001

KSC-00pp1846

NASA Image and Video Library

2000-12-07

KENNEDY SPACE CENTER, FLA. -- As part of In-Flight Maintenance training, members of the STS-107 crew check out one of the Biotube experiments that will be part of their research mission . From left (in uniform) are Mission Specialist David M. Brown, Payload Specialist Ilan Ramon of Israel, and Mission Specialist Kalpana Chawla; Pilot William C. “Willie” McCool (crouching behind the table); Commander Rick D. Husband; and Mission Specialist Laurel Clark. At right is project engineer April Boody. As a research mission, STS-107 will carry the SPACEHAB Double Module in its first research flight into space and a broad collection of experiments ranging from material science to life science. It is scheduled to launch July 19, 2001

Flight dynamics analysis and simulation of heavy lift airships, volume 4. User's guide: Appendices

NASA Technical Reports Server (NTRS)

Emmen, R. D.; Tischler, M. B.

1982-01-01

This table contains all of the input variables to the three programs. The variables are arranged according to the name list groups in which they appear in the data files. The program name, subroutine name, definition and, where appropriate, a default input value and any restrictions are listed with each variable. The default input values are user supplied, not generated by the computer. These values remove a specific effect from the calculations, as explained in the table. The phrase "not used' indicates that a variable is not used in the calculations and are for identification purposes only. The engineering symbol, where it exists, is listed to assist the user in correlating these inputs with the discussion in the Technical Manual.

Mobile aviation services in the 1545-1559/1646.5-1660.5 MHz band

NASA Astrophysics Data System (ADS)

Kiesling, J. D.

1986-09-01

Plans in the U.S. for a national mobile satellite service (MSS) including satellite services to aviation for air traffic control and airline operational control are outlined. The MSS provides affordable mobile services in nonurban areas where terrestrially based systems are uneconomic. The MSS system also is available on a priority basis for aviation services, specifically AMSS(R) services involving safety and regularity of flight and other aviation services. The U.S. plan is expected to change the U.S. Tables of Allocations and proposes to change the International Table of Allocations so that MSS facilities can and will provide AMSS(R) services on a priority basis. Such arrangements can be implemented worldwide by administrations and organizations having similar interests.

Feasibility of Real-Time Selection of Frequency Tables in an Acoustic Simulation of a Cochlear Implant

PubMed Central

Fitzgerald, Matthew; Sagi, Elad; Morbiwala, Tasnim A.; Tan, Chin-Tuan; Svirsky, Mario A.

2013-01-01

Objectives Perception of spectrally degraded speech is particularly difficult when the signal is also distorted along the frequency axis. This might be particularly important for post-lingually deafened recipients of cochlear implants (CI), who must adapt to a signal where there may be a mismatch between the frequencies of an input signal and the characteristic frequencies of the neurons stimulated by the CI. However, there is a lack of tools that can be used to identify whether an individual has adapted fully to a mismatch in the frequency-to-place relationship and if so, to find a frequency table that ameliorates any negative effects of an unadapted mismatch. The goal of the proposed investigation is to test the feasibility of whether real-time selection of frequency tables can be used to identify cases in which listeners have not fully adapted to a frequency mismatch. The assumption underlying this approach is that listeners who have not adapted to a frequency mismatch will select a frequency table that minimizes any such mismatches, even at the expense of reducing the information provided by this frequency table. Design 34 normal-hearing adults listened to a noise-vocoded acoustic simulation of a cochlear implant and adjusted the frequency table in real time until they obtained a frequency table that sounded “most intelligible” to them. The use of an acoustic simulation was essential to this study because it allowed us to explicitly control the degree of frequency mismatch present in the simulation. None of the listeners had any previous experience with vocoded speech, in order to test the hypothesis that the real-time selection procedure could be used to identify cases in which a listener has not adapted to a frequency mismatch. After obtaining a self-selected table, we measured CNC word-recognition scores with that self-selected table and two other frequency tables: a “frequency-matched” table that matched the analysis filters with the noisebands of the noise-vocoder simulation, and a “right information” table that is similar to that used in most cochlear implant speech processors, but in this simulation results in a frequency shift equivalent to 6.5 mm of cochlear space. Results Listeners tended to select a table that was very close to, but shifted slightly lower in frequency from the frequency-matched table. The real-time selection process took on average 2–3 minutes for each trial, and the between-trial variability was comparable to that previously observed with closely-related procedures. The word-recognition scores with the self-selected table were clearly higher than with the right-information table and slightly higher than with the frequency-matched table. Conclusions Real-time self-selection of frequency tables may be a viable tool for identifying listeners who have not adapted to a mismatch in the frequency-to-place relationship, and to find a frequency table that is more appropriate for them. Moreover, the small but significant improvements in word-recognition ability observed with the self-selected table suggest that these listeners based their selections on intelligibility rather than some other factor. The within-subject variability in the real-time selection procedure was comparable to that of a genetic algorithm, and the speed of the real-time procedure appeared to be faster than either a genetic algorithm or a simplex procedure. PMID:23807089

Demonstration of Helicopter Multi-Towed Array Detection System (MTADS) Magnetometry Technology at Pueblo Precision Bombing Range #2, Colorado

DTIC Science & Technology

2008-08-28

for aircraft pitch measurement Fluxgate magnetometer 10 RS232- ASCII SerialDevice.fluxgate Provides redundant aircraft attitude measurement...Figure 28. Filtered, ’final’ magnetometer data taken at high altitude. ......................................................... 43 LIST OF TABLES...flight. The magnetometer data can be analyzed to extract either distributions of magnetic anomalies (which can be further used to locate and bound

14 CFR Appendix D to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2014 CFR

2014-01-01

... Position/Speed Brake Selection Full range or each discrete position ±2% unless higher accuracy uniquely... REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 135, App...,000 ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1...

14 CFR Appendix D to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2013 CFR

2013-01-01

... Position/Speed Brake Selection Full range or each discrete position ±2% unless higher accuracy uniquely... REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 135, App...,000 ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1...

14 CFR Appendix D to Part 125 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2012 CFR

2012-01-01

... CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 125, App. D... ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1... Stowed, in transit, and reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed...

14 CFR Appendix D to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2011 CFR

2011-01-01

... Position/Speed Brake Selection Full range or each discrete position ±2% unless higher accuracy uniquely... REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 135, App...,000 ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1...

14 CFR Appendix D to Part 135 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2012 CFR

2012-01-01

... Position/Speed Brake Selection Full range or each discrete position ±2% unless higher accuracy uniquely... REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 135, App...,000 ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1...

14 CFR Appendix D to Part 125 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2013 CFR

2013-01-01

... CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 125, App. D... ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1... Stowed, in transit, and reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed...

14 CFR Appendix D to Part 125 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2014 CFR

2014-01-01

... CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 125, App. D... ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1... Stowed, in transit, and reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed...

14 CFR Appendix D to Part 125 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2011 CFR

2011-01-01

... CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Pt. 125, App. D... ft to max certificated altitude of aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1... Stowed, in transit, and reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed...

Thermal conductivity of particulate materials: A summary of measurements taken at the Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

Fountain, J. A.

1973-01-01

Thermal conductivity measurements of particulate materials in vacuum are presented in summary. Particulate basalt and soda lime glass beads of various size ranges were used as samples. The differentiated line heat source method was used for the measurements. A comprehensive table is shown giving all pertinent experimental conditions. Least-squares curve fits to the data are presented.

The complex magnetic field of Jupiter

NASA Technical Reports Server (NTRS)

Acuna, M. H.; Ness, N. F.

1975-01-01

An analysis of the characteristics of the magnetic field of the planet Jupiter is presented. The data were obtained during the flight of Pioneer 11 space probe, using a high field triaxial fluxgate magnetometer. The data are analyzed in terms of traditional Schmitt normalized spherical harmonic expansion fitted to the observations in a least squares sense. Tables of data and graphs are provided to summarize the findings.

Deep learning for media analysis in defense scenariosan evaluation of an open source framework for object detection in intelligence related image sets

DTIC Science & Technology

2017-06-01

Training time statistics from Jones’ thesis. . . . . . . . . . . . . . 15 Table 2.2 Evaluation runtime statistics from Camp’s thesis for a single image. 17...Table 2.3 Training and evaluation runtime statistics from Sharpe’s thesis. . . 19 Table 2.4 Sharpe’s screenshot detector results for combinations of...training resources available and time required for each algorithm Jones [15] tested. Table 2.1. Training time statistics from Jones’ [15] thesis. Algorithm

14 CFR 121.511 - Flight time limitations: Flight engineers: airplanes.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight time limitations: Flight engineers... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time Limitations: Supplemental Operations § 121.511 Flight time limitations: Flight engineers: airplanes. (a) In any operation in which one...

14 CFR 121.511 - Flight time limitations: Flight engineers: airplanes.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitations: Flight engineers... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time Limitations: Supplemental Operations § 121.511 Flight time limitations: Flight engineers: airplanes. (a) In any operation in which one...

14 CFR 121.511 - Flight time limitations: Flight engineers: airplanes.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight time limitations: Flight engineers... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time Limitations: Supplemental Operations § 121.511 Flight time limitations: Flight engineers: airplanes. (a) In any operation in which one...

14 CFR 121.511 - Flight time limitations: Flight engineers: airplanes.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight time limitations: Flight engineers... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time Limitations: Supplemental Operations § 121.511 Flight time limitations: Flight engineers: airplanes. (a) In any operation in which one...

Investigation of Slosh Dynamics on Flight and Ground Platforms

NASA Astrophysics Data System (ADS)

Vergalla, Michael; Zhou, Ran

The slosh dynamics in cryogenic fuel tanks under microgravity is a problem that severely affects the reliability of spacecraft launching. To investigate slosh dynamics and their effects on space vehicle dynamics three levels of testing are presently in progress. Platforms include a 3-DOF ground testing table, parabolic flights, sounding rockets and finally the International Space Station. Ground tests provide an economically viable platform for investigating rotational, translational, and coupled feed-back modes due to repeatable CNC motions. The parabolic flight campaign has conducted four successful flights aboard multiple aircraft using static and tethered slosh packages. Using the PANTHER II student designed rocket, a slosh package was launched as a payload. Finally with collaboration between Florida Institute of Technology and Massachusetts Institute of Technology SPHERES project, two test sessions investigating feedback using partially and fully filled propellant tanks have been completed aboard the In-ternational Space Station. Motion data from all tests will be input to in house Dynamic Mesh Model to further establish confidence in the versatility and accuracy of the method. The results show that it is necessary to construct additional hardware for slosh studies.

SU-F-J-206: Systematic Evaluation of the Minimum Detectable Shift Using a Range- Finding Camera

DOE Office of Scientific and Technical Information (OSTI.GOV)

Platt, M; Platt, M; Lamba, M

2016-06-15

Purpose: The robotic table used for patient alignment in proton therapy is calibrated only at commissioning under well-defined conditions and table shifts may vary over time and with differing conditions. The purpose of this study is to systematically investigate minimum detectable shifts using a time-of-flight (TOF) range-finding camera for table position feedback. Methods: A TOF camera was used to acquire one hundred 424 × 512 range images from a flat surface before and after known shifts. Range was assigned by averaging central regions of the image across multiple images. Depth resolution was determined by evaluating the difference between the actualmore » shift of the surface and the measured shift. Depth resolution was evaluated for number of images averaged, area of sensor over which depth was averaged, distance from camera to surface, central versus peripheral image regions, and angle of surface relative to camera. Results: For one to one thousand images with a shift of one millimeter the range in error was 0.852 ± 0.27 mm to 0.004 ± 0.01 mm (95% C.I.). For varying regions of the camera sensor the range in error was 0.02 ± 0.05 mm to 0.47 ± 0.04 mm. The following results are for 10 image averages. For areas ranging from one pixel to 9 × 9 pixels the range in error was 0.15 ± 0.09 to 0.29 ± 0.15 mm (1σ). For distances ranging from two to four meters the range in error was 0.15 ± 0.09 to 0.28 ± 0.15 mm. For an angle of incidence between thirty degrees and ninety degrees the average range in error was 0.11 ± 0.08 to 0.17 ± 0.09 mm. Conclusion: It is feasible to use a TOF camera for measuring shifts in flat surfaces under clinically relevant conditions with submillimeter precision.« less

HTML 5 Displays for On-Board Flight Systems

NASA Technical Reports Server (NTRS)

Silva, Chandika

2016-01-01

During my Internship at NASA in the summer of 2016, I was assigned to a project which dealt with developing a web-server that would display telemetry and other system data using HTML 5, JavaScript, and CSS. By doing this, it would be possible to view the data across a variety of screen sizes, and establish a standard that could be used to simplify communication and software development between NASA and other countries. Utilizing a web- approach allowed us to add in more functionality, as well as make the displays more aesthetically pleasing for the users. When I was assigned to this project my main task was to first establish communication with the current display server. This display server would output data from the on-board systems in XML format. Once communication was established I was then asked to create a dynamic telemetry table web page that would update its header and change as new information came in. After this was completed, certain minor functionalities were added to the table such as a hide column and filter by system option. This was more for the purpose of making the table more useful for the users, as they can now filter and view relevant data. Finally my last task was to create a graphical system display for all the systems on the space craft. This was by far the most challenging part of my internship as finding a JavaScript library that was both free and contained useful functions to assist me in my task was difficult. In the end I was able to use the JointJs library and accomplish the task. With the help of my mentor and the HIVE lab team, we were able to establish stable communication with the display server. We also succeeded in creating a fully dynamic telemetry table and in developing a graphical system display for the advanced modular power system. Working in JSC for this internship has taught me a lot about coding in JavaScript and HTML 5. I was also introduced to the concept of developing software as a team, and exposed to the different types of programs that are used to simplify team coding such as GitLab. While in JSC, I took full advantage of and attended the lectures that were held here on site. I learned a lot about what it is NASA does and about the interesting projects that are conducted here. One of the lectures I attended was about the selection process and the criteria that is used to select future astronauts for flight missions. This truly had an impact on my future plans as it showed me that this path was a viable option for me. After this internship I plan on completing my undergraduate course work and plan to move on for a masters degree. However, during the time in which I will be completing my masters course work, I would like to apply for the NASA pathways graduate program and, if I am accepted, eventually move on to being a full time civil servant. Working in NASA has not only been enjoyable, but full of information and great experiences that have motivated me to seek a full time employment here in the near future.

Comparison of Sedentary Behaviors in Office Workers Using Sit-Stand Tables With and Without Semiautomated Position Changes.

PubMed

Barbieri, Dechristian França; Srinivasan, Divya; Mathiassen, Svend Erik; Oliveira, Ana Beatriz

2017-08-01

We compared usage patterns of two different electronically controlled sit-stand tables during a 2-month intervention period among office workers. Office workers spend most of their working time sitting, which is likely detrimental to health. Although the introduction of sit-stand tables has been suggested as an effective intervention to decrease sitting time, limited evidence is available on usage patterns of sit-stand tables and whether patterns are influenced by table configuration. Twelve workers were provided with standard sit-stand tables (nonautomated table group) and 12 with semiautomated sit-stand tables programmed to change table position according to a preset pattern, if the user agreed to the system-generated prompt (semiautomated table group). Table position was monitored continuously for 2 months after introducing the tables, as a proxy for sit-stand behavior. On average, the table was in a "sit" position for 85% of the workday in both groups; this percentage did not change significantly during the 2-month period. Switches in table position from sit to stand were, however, more frequent in the semiautomated table group than in the nonautomated table group (0.65 vs. 0.29 hr -1 ; p = .001). Introducing a semiautomated sit-stand table appeared to be an attractive alternative to a standard sit-stand table, because it led to more posture variation. A semiautomated sit-stand table may effectively contribute to making postures more variable among office workers and thus aid in alleviating negative health effects of extensive sitting.

KSC-2011-1810

NASA Image and Video Library

2011-02-24

CAPE CANAVERAL, Fla. -- Chief Mate Jamie Harris works at the chart table on the bridge at night under a red light so as not to compromise night vision on Freedom Star, one of NASA's solid rocket booster retrieval ships plotting a course in the direction of the left spent booster that splashed down into the Atlantic Ocean after space shuttle Discovery's STS-133 launch. The shuttle’s two solid rocket booster casings and associated flight hardware are recovered in the Atlantic Ocean after every launch by Liberty Star and Freedom Star. The boosters impact the Atlantic about seven minutes after liftoff and the retrieval ships are stationed about 10 miles from the impact area at the time of splashdown. After the spent segments are processed, they will be transported to Utah, where they will be refurbished and stored, if needed. Photo credit: NASA/Ben Smegelsky

A time series approach to inferring groundwater recharge using the water table fluctuation method

NASA Astrophysics Data System (ADS)

Crosbie, Russell S.; Binning, Philip; Kalma, Jetse D.

2005-01-01

The water table fluctuation method for determining recharge from precipitation and water table measurements was originally developed on an event basis. Here a new multievent time series approach is presented for inferring groundwater recharge from long-term water table and precipitation records. Additional new features are the incorporation of a variable specific yield based upon the soil moisture retention curve, proper accounting for the Lisse effect on the water table, and the incorporation of aquifer drainage so that recharge can be detected even if the water table does not rise. A methodology for filtering noise and non-rainfall-related water table fluctuations is also presented. The model has been applied to 2 years of field data collected in the Tomago sand beds near Newcastle, Australia. It is shown that gross recharge estimates are very sensitive to time step size and specific yield. Properly accounting for the Lisse effect is also important to determining recharge.

Liquid Motion Experiment Flight Test Results

NASA Technical Reports Server (NTRS)

Chato David J.; Dalton, Penni J.; Dodge, Franklin T.; Green, Steve

1998-01-01

The Liquid Motion Experiment (LME), designed to study the effects of liquid motion in rotating tanks, was flown on STS 84. LME was essentially a spin table that created a realistic nutation motion of scale-model tanks containing liquid. TWo spherical and two cylindrical transparent tanks were tested simultaneously, and three sets of such tanks were employed to vary liquid viscosity, fill level, and propellant management device (PMD) design. All the tanks were approximately 4.5 inches diameter. The primary test measurements were the radial and tangential torques exerted on the tanks by the liquid. Resonant frequencies and damping of the liquid oscillations were determined by sine sweep tests. For a given tank shape, the resonant frequency depended on fill level. For the cylindrical tanks, the resonances had somewhat different frequencies for the tangential axis (0.55 to 0.75 times spin rate) and the radial axis (0.73 to 0.78 times spin rate), and the tangential axis resonance agreed more closely with available analytical models. For the spherical tanks, the resonant frequencies were between 0.74 to 0.77 times the spin rate and were the same for the tangential and radial axes. The damping coefficients varied from about I% to 3% of critical, depending on tank shape, fill level, and liquid viscosity. 'Me viscous energy dissipation rates of the liquid oscillations were determined from sine dwell tests. The LME energy dissipation rates varied from 0.3 to 0.5 times the estimates obtained from scaling previous ground tests and spacecraft flight data. The PNDs sometimes enhanced the resonances and energy dissipation rates and sometimes decreased them, which points out the need to understand better the effects of PMD on liquid motion as a function of PMD and tank design.

[Helicopters and medical first aid units. Role of Medical First Aid Unit 94].

PubMed

Huguenard, P; Hanote, P; Metrot, J

1975-10-01

For the transport of injured and sick patients, the helicopter (even the mono-turbine type) offers greater advantages when compared to land vehicles: - more comfort (less vibrations, accelerations and decelerations); - a greater speed, that is to say a 61 p. 100 gain of time upon the distance and a gain from 29 up to 44 p. 100 upon the total amount of time taken up by each transport. This gain in time enables valuable specialised medical teams to be more available: - more precise time-tables than by land which namely makes it easier to receive the patients. The drawbacks are linked with the risks which are not nonexistent but rather less serious than by land. The drawbacks also depend upon the weather-conditions (although this factor does not matter much in our area), upon nuisances such as the noise (which is more important but far more transitory than by ambulance) and chiefly upon the cost of air-transport. In fact, the mean cost of a medical land transport amounts roughly to one thousand Francs, a quarter of which only does represent the actual cost of medical aid. For a similar transport, the helicopter comes to a 47 mns flight. There are several ways of making good use of a helicopter. Practical problems have been solved. The "SAMU 94" experience goes back to 1973 and includes over 500 transports by helicopter essentially with the help of the teams and the helicopters belonging to the Paris Base (Civil Protection and the Fire-Brigade). For flights over urban areas, it is to be desired in the future that only twin-turbine helicopters should be used.

Effect of Plyometric Training on Handspring Vault Performance and Functional Power in Youth Female Gymnasts

PubMed Central

Hall, Emma; Bishop, Daniel C.; Gee, Thomas I.

2016-01-01

This study aimed to determine the effect of plyometric training (PT) when added to habitual gymnastic training (HT) on handspring vault (HV) performance variables. Twenty youth female competitive gymnasts (Age: 12.5 ± 1.67 y) volunteered to participate and were randomly assigned to two independent groups. The experimental plyometric training group (PTG) undertook a six-week plyometric program, involving two additional 45 min PT sessions a week, alongside their HT, while the control group (CG) performed regular HT only. Videography was used (120 Hz) in the sagittal plane to record both groups performing three HVs for both the baseline and post-intervention trials. Furthermore, participants completed a countermovement jump test (CMJ) to assess the effect of PT on functional power. Through the use of Quintic biomechanics software, significant improvements (P < 0.05) were found for the PTG for run-up velocity, take-off velocity, hurdle to board distance, board contact time, table contact time and post-flight time and CMJ height. However, there were no significant improvements on pre-flight time, shoulder angle or hip angle on the vault for the PTG. The CG demonstrated no improvement for all HV measures. A sport-specific PT intervention improved handspring vault performance measures and functional power when added to the habitual training of youth female gymnasts. The additional two hours plyometric training seemingly improved the power generating capacity of movement-specific musculature, which consequently improved aspects of vaulting performance. Future research is required to examine the whether the improvements are as a consequence of the additional volume of sprinting and jumping activities, as a result of the specific PT method or a combination of these factors. PMID:26859381

Effect of Plyometric Training on Handspring Vault Performance and Functional Power in Youth Female Gymnasts.

PubMed

Hall, Emma; Bishop, Daniel C; Gee, Thomas I

2016-01-01

This study aimed to determine the effect of plyometric training (PT) when added to habitual gymnastic training (HT) on handspring vault (HV) performance variables. Twenty youth female competitive gymnasts (Age: 12.5 ± 1.67 y) volunteered to participate and were randomly assigned to two independent groups. The experimental plyometric training group (PTG) undertook a six-week plyometric program, involving two additional 45 min PT sessions a week, alongside their HT, while the control group (CG) performed regular HT only. Videography was used (120 Hz) in the sagittal plane to record both groups performing three HVs for both the baseline and post-intervention trials. Furthermore, participants completed a countermovement jump test (CMJ) to assess the effect of PT on functional power. Through the use of Quintic biomechanics software, significant improvements (P < 0.05) were found for the PTG for run-up velocity, take-off velocity, hurdle to board distance, board contact time, table contact time and post-flight time and CMJ height. However, there were no significant improvements on pre-flight time, shoulder angle or hip angle on the vault for the PTG. The CG demonstrated no improvement for all HV measures. A sport-specific PT intervention improved handspring vault performance measures and functional power when added to the habitual training of youth female gymnasts. The additional two hours plyometric training seemingly improved the power generating capacity of movement-specific musculature, which consequently improved aspects of vaulting performance. Future research is required to examine the whether the improvements are as a consequence of the additional volume of sprinting and jumping activities, as a result of the specific PT method or a combination of these factors.

X-Ray Calibration Facility/Advanced Video Guidance Sensor Test

NASA Technical Reports Server (NTRS)

Johnston, N. A. S.; Howard, R. T.; Watson, D. W.

2004-01-01

The advanced video guidance sensor was tested in the X-Ray Calibration facility at Marshall Space Flight Center to establish performance during vacuum. Two sensors were tested and a timeline for each are presented. The sensor and test facility are discussed briefly. A new test stand was also developed. A table establishing sensor bias and spot size growth for several ranges is detailed along with testing anomalies.

Thematic mapper protoflight model preshipment review data package. Volume 4: Appendix. Part A: Multiplexer data book 2

NASA Technical Reports Server (NTRS)

1982-01-01

Final performance test data for the thematic mapper flight model multiplexer are presented in tables. Aspects covered include A/D thresholds for bands 5, 6, and 7; cross talk; the thermistor; bilevel commands signal parameters; A/D threshold ambient, voltage margin low bus; serial data and bit clock parameters; and the wire check. Tests were conducted at ambient temperature.

Robotic Follow-up for Human Exploration

DTIC Science & Technology

2010-09-01

layering, structural anomalies and fracturing . While ground ice at Haughton is generally present as continuous permafrost, the depth to the thaw zone...geologist (M. Helper) and a geophysicist (E. Heggy) planned tra- verses using a HMMWV as a simulated pressur - ized crew rover. Each traverse was...mounted on the front of a simulated pressurized crew rover; right, GPR is manually deployed by suited crew. Table 3. Flight rules for simulated crew mission

Training Methods and Tactical Decision-Making Simulations

DTIC Science & Technology

2007-09-01

TDS TDG ALL Standard Deviation 100.60 14.85 87.40 Puzzle, Card , Board Subjects Responding 5 3 8 Total # of Hours/Year 805 774 1579 Minimum...Table 7 shows that participants had the most commercial game experience with puzzle, card , board, and adventure/fantasy type games. Participants...circle all that apply) 1. first person shooter 2. flight simulations 3. racing 4. other sports 5. puzzle, strategy, card , board

14 CFR Appendix B to Part 121 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2011 CFR

2011-01-01

... Reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed Brake Selection Full Range... aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1 Airspeed 50 KIAS to V so, and V so to 1.2 VD... Accurate Systems Installed (IMS Equipped Aircraft Only) 1 0.2% 2 If additional recording capacity is...

14 CFR Appendix B to Part 121 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2013 CFR

2013-01-01

... Reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed Brake Selection Full Range... aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1 Airspeed 50 KIAS to V so, and V so to 1.2 VD... Accurate Systems Installed (IMS Equipped Aircraft Only) 1 0.2% 2 If additional recording capacity is...

14 CFR Appendix B to Part 121 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2014 CFR

2014-01-01

... Reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed Brake Selection Full Range... aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1 Airspeed 50 KIAS to V so, and V so to 1.2VD... Accurate Systems Installed (IMS Equipped Aircraft Only) 1 0.2% 2 If additional recording capacity is...

14 CFR Appendix B to Part 121 - Airplane Flight Recorder Specification

Code of Federal Regulations, 2012 CFR

2012-01-01

... Reverse (Discrete) 1 (per 4 seconds per engine) Ground Spoiler Position/Speed Brake Selection Full Range... aircraft ±100 to ±700 ft (See Table 1, TSO-C51a) 1 5′ to 35′ 1 Airspeed 50 KIAS to V so, and V so to 1.2 VD... Accurate Systems Installed (IMS Equipped Aircraft Only) 1 0.2% 2 If additional recording capacity is...

Cholesterol in serum lipoprotein fractions after spaceflight

NASA Technical Reports Server (NTRS)

Leach, Carolyn S.; Johnson, Philip C., Jr.; Krauhs, Jane M.; Cintron, Nitza M.

1988-01-01

Results are reported from blood-lipid measurements obtained from 125 Space Shuttle crew members before and after space flight. The data are presented in tables and discussed in detail. The main differences noted between preflight and postflight values are a 12.8-percent decrease in high-density lipoproteins on postflight day 1 and significant decreases in total cholesterol and both high- and low-density lipoproteins later in the 23-day postflight period.

OPTIMAL AIRCRAFT TRAJECTORIES FOR SPECIFIED RANGE

NASA Technical Reports Server (NTRS)

Lee, H.

1994-01-01

For an aircraft operating over a fixed range, the operating costs are basically a sum of fuel cost and time cost. While minimum fuel and minimum time trajectories are relatively easy to calculate, the determination of a minimum cost trajectory can be a complex undertaking. This computer program was developed to optimize trajectories with respect to a cost function based on a weighted sum of fuel cost and time cost. As a research tool, the program could be used to study various characteristics of optimum trajectories and their comparison to standard trajectories. It might also be used to generate a model for the development of an airborne trajectory optimization system. The program could be incorporated into an airline flight planning system, with optimum flight plans determined at takeoff time for the prevailing flight conditions. The use of trajectory optimization could significantly reduce the cost for a given aircraft mission. The algorithm incorporated in the program assumes that a trajectory consists of climb, cruise, and descent segments. The optimization of each segment is not done independently, as in classical procedures, but is performed in a manner which accounts for interaction between the segments. This is accomplished by the application of optimal control theory. The climb and descent profiles are generated by integrating a set of kinematic and dynamic equations, where the total energy of the aircraft is the independent variable. At each energy level of the climb and descent profiles, the air speed and power setting necessary for an optimal trajectory are determined. The variational Hamiltonian of the problem consists of the rate of change of cost with respect to total energy and a term dependent on the adjoint variable, which is identical to the optimum cruise cost at a specified altitude. This variable uniquely specifies the optimal cruise energy, cruise altitude, cruise Mach number, and, indirectly, the climb and descent profiles. If the optimum cruise cost is specified, an optimum trajectory can easily be generated; however, the range obtained for a particular optimum cruise cost is not known a priori. For short range flights, the program iteratively varies the optimum cruise cost until the computed range converges to the specified range. For long-range flights, iteration is unnecessary since the specified range can be divided into a cruise segment distance and full climb and descent distances. The user must supply the program with engine fuel flow rate coefficients and an aircraft aerodynamic model. The program currently includes coefficients for the Pratt-Whitney JT8D-7 engine and an aerodynamic model for the Boeing 727. Input to the program consists of the flight range to be covered and the prevailing flight conditions including pressure, temperature, and wind profiles. Information output by the program includes: optimum cruise tables at selected weights, optimal cruise quantities as a function of cruise weight and cruise distance, climb and descent profiles, and a summary of the complete synthesized optimal trajectory. This program is written in FORTRAN IV for batch execution and has been implemented on a CDC 6000 series computer with a central memory requirement of approximately 100K (octal) of 60 bit words. This aircraft trajectory optimization program was developed in 1979.

KENNEDY SPACE CENTER, FLA. - On a tour of the Tile Shop, members of the Stafford-Covey Return to Flight Task Group (SCTG) learn about PU-tiles, part of an orbiter’s Thermal Protection System. At left is Martin Wilson, with United Space Alliance. Others (left to right) around the table are James Adamson, Dr. Kathryn Clark, William Wegner, Richard Covey and Joe Engle. Covey, former Space Shuttle commander, is co-chair of the SCTG, along with Thomas P. Stafford, Apollo commander. Chartered by NASA Administrator Sean O’Keefe, the task group will perform an independent assessment of NASA’s implementation of the final recommendations by the Columbia Accident Investigation Board.

NASA Image and Video Library

2003-08-06

KENNEDY SPACE CENTER, FLA. - On a tour of the Tile Shop, members of the Stafford-Covey Return to Flight Task Group (SCTG) learn about PU-tiles, part of an orbiter’s Thermal Protection System. At left is Martin Wilson, with United Space Alliance. Others (left to right) around the table are James Adamson, Dr. Kathryn Clark, William Wegner, Richard Covey and Joe Engle. Covey, former Space Shuttle commander, is co-chair of the SCTG, along with Thomas P. Stafford, Apollo commander. Chartered by NASA Administrator Sean O’Keefe, the task group will perform an independent assessment of NASA’s implementation of the final recommendations by the Columbia Accident Investigation Board.

Onboard Determination of Vehicle Glide Capability for Shuttle Abort Flight Managment (SAFM)

NASA Technical Reports Server (NTRS)

Straube, Timothy; Jackson, Mark; Fill, Thomas; Nemeth, Scott

2002-01-01

When one or more main engines fail during ascent, the flight crew of the Space Shuttle must make several critical decisions and accurately perform a series of abort procedures. One of the most important decisions for many aborts is the selection ofa landing site. Several factors influence the ability to reach a landing site, including the spacecraft point of atmospheric entry, the energy state at atmospheric entry, the vehicle glide capability from that energy state, and whether one or more suitable landing sites are within the glide capability. Energy assessment is further complicated by the fact that phugoid oscillations in total energy influence glide capability. Once the glide capability is known, the crew must select the "best" site option based upon glide capability and landing site conditions and facilities. Since most of these factors cannot currently be assessed by the crew in flight, extensive planning is required prior to each mission to script a variety of procedures based upon spacecraft velocity at the point of engine failure (or failures). The results of this preflight planning are expressed in tables and diagrams on mission-specific cockpit checklists. Crew checklist procedures involve leafing through several pages of instructions and navigating a decision tree for site selection and flight procedures - all during a time critical abort situation. With the advent of the Cockpit Avionics Upgrade (CAU), the Shuttle will have increased on-board computational power to help alleviate crew workload during aborts and provide valuable situational awareness during nominal operations. One application baselined for the CAU computers is Shuttle Abort Flight Management (SAFM), whose requirements have been designed and prototyped. The SAFM application includes powered and glided flight algorithms. This paper describes the glided flight algorithm which is dispatched by SAFM to determine the vehicle glide capability and make recommendations to the crew for site selection as well as to monitor glide capability while in route to the selected site. Background is provided on Shuttle entry guidance as well as the various types of Shuttle aborts. SAFM entry requirements and cockpit disp lays are discussed briefly to provide background for Glided Flight algorithm design considerations. The central principal of the Glided Flight algorithm is the use of energy-over-weight (EOW) curves to determine range and crossrange boundaries. The major challenges of this technique are exo-atmospheric flight, and phugoid oscillations in energy. During exo-atmospheric flight, energy is constant, so vehicle EOW is not sufficient to determine glide capability. The paper describes how the exo-atmospheric problem is solved by propagating the vehicle state to an "atmospheric pullout" state defined by Shuttle guidance parameters.

14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time...

14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time...

14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time...

14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time...

14 CFR 121.493 - Flight time limitations: Flight engineers and flight navigators.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Flight engineers and flight navigators. 121.493 Section 121.493 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... AND OPERATIONS OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Time...

Life-table methods for detecting age-risk factor interactions in long-term follow-up studies.

PubMed

Logue, E E; Wing, S

1986-01-01

Methodological investigation has suggested that age-risk factor interactions should be more evident in age of experience life tables than in follow-up time tables due to the mixing of ages of experience over follow-up time in groups defined by age at initial examination. To illustrate the two approaches, age modification of the effect of total cholesterol on ischemic heart disease mortality in two long-term follow-up studies was investigated. Follow-up time life table analysis of 116 deaths over 20 years in one study was more consistent with a uniform relative risk due to cholesterol, while age of experience life table analysis was more consistent with a monotonic negative age interaction. In a second follow-up study (160 deaths over 24 years), there was no evidence of a monotonic negative age-cholesterol interaction by either method. It was concluded that age-specific life table analysis should be used when age-risk factor interactions are considered, but that both approaches yield almost identical results in absence of age interaction. The identification of the more appropriate life-table analysis should be ultimately guided by the nature of the age or time phenomena of scientific interest.

Advanced piloted aircraft flight control system design methodology. Volume 1: Knowledge base

NASA Technical Reports Server (NTRS)

Mcruer, Duane T.; Myers, Thomas T.

1988-01-01

The development of a comprehensive and electric methodology for conceptual and preliminary design of flight control systems is presented and illustrated. The methodology is focused on the design stages starting with the layout of system requirements and ending when some viable competing system architectures (feedback control structures) are defined. The approach is centered on the human pilot and the aircraft as both the sources of, and the keys to the solution of, many flight control problems. The methodology relies heavily on computational procedures which are highly interactive with the design engineer. To maximize effectiveness, these techniques, as selected and modified to be used together in the methodology, form a cadre of computational tools specifically tailored for integrated flight control system preliminary design purposes. While theory and associated computational means are an important aspect of the design methodology, the lore, knowledge and experience elements, which guide and govern applications are critical features. This material is presented as summary tables, outlines, recipes, empirical data, lists, etc., which encapsulate a great deal of expert knowledge. Much of this is presented in topical knowledge summaries which are attached as Supplements. The composite of the supplements and the main body elements constitutes a first cut at a a Mark 1 Knowledge Base for manned-aircraft flight control.

ToF diagnostic of Tin resonant laser photoionization in SPES laser offline laboratory

NASA Astrophysics Data System (ADS)

Scarpa, D.; Fedorov, D.; Andrighetto, A.; Mariotti, E.; Nicolosi, P.; Sottili, L.; Tomaselli, A.; Cecchi, R.; Stiaccini, L.

2016-09-01

Tin is the principal element of interest in the SPES ISOL facility, which is under construction at Legnaro INFN Laboratories. Atomic nuclei have a shell structure in which nuclei with \\textquoteleft magic numbers\\textquoteright of protons and neutrons are analogous to the noble gasses in atomic physics. In particular, recent theoretical studies, reveal double-magic nature of radioactive 132Sn. For this reason the nuclear physics community demonstrated, in the last years, a huge interest to produce and study this radioactive neutron rich isotope. Experiments on Tin laser resonant ionization have been performed in the offline SPES laser laboratory to investigate the capability of the new home-made Time of Flight (ToF) mass spectrometer. Several three-step, two color ionization schemes have been tested by comparing fast and slow optogalvanic signals from a Tin Hollow Cathode Lamp (HCL) and Time of Flight signals from the spectrometer. By scanning the wavelength of one of the two dye lasers across the specific resonance, comparisons of ionization signals from both the ToF and the HCL have been made, finding perfect agreement. Furthermore, with the mass spectrometer, resolved peaks of all the natural Tin isotopes have been detected. The natural abundances extracted from these measurements are in agreement with the table values for Tin isotopes. This work, with comparison of OGE and ToF signals, confirm the fully functional SPES offline laser laboratory capability in order to develop scheme studies also for the other possible Radioactive Ion Beam (RIB) elements.

14 CFR 61.411 - What aeronautical experience must I have to apply for a flight instructor certificate with a...

Code of Federal Regulations, 2013 CFR

2013-01-01

...-engine class privileges, (1) 150 hours of flight time as a pilot, (i) 100 hours of flight time as pilot in command in powered aircraft,(ii) 50 hours of flight time in a single-engine airplane, (iii) 25 hours of cross-country flight time, (iv) 10 hours of cross-country flight time in a single-engine...

14 CFR 61.411 - What aeronautical experience must I have to apply for a flight instructor certificate with a...

Code of Federal Regulations, 2012 CFR

2012-01-01

...-engine class privileges, (1) 150 hours of flight time as a pilot, (i) 100 hours of flight time as pilot in command in powered aircraft,(ii) 50 hours of flight time in a single-engine airplane, (iii) 25 hours of cross-country flight time, (iv) 10 hours of cross-country flight time in a single-engine...

14 CFR 61.411 - What aeronautical experience must I have to apply for a flight instructor certificate with a...

Code of Federal Regulations, 2014 CFR

2014-01-01

...-engine class privileges, (1) 150 hours of flight time as a pilot, (i) 100 hours of flight time as pilot in command in powered aircraft,(ii) 50 hours of flight time in a single-engine airplane, (iii) 25 hours of cross-country flight time, (iv) 10 hours of cross-country flight time in a single-engine...

STS-45 crewmembers during LINHOF camera briefing in JSC's Bldg 4 rm 2026A

NASA Image and Video Library

1992-01-14

S92-26522 (Feb 1992) --- Crewmembers assigned to NASA's STS-45 mission are briefed on the use of the Linhof camera in the flight operations facility at the Johnson Space Center (JSC). Charles F. Bolden, mission commander, stands at left. Other crewmembers (seated clockwise around the table from lower left) are Dirk Frimout of Belgium representing the European Space Agency as payload specialist; Charles R. (Rick) Chappell, backup payload specialist; Brian Duffy, pilot; Kathryn D. Sullivan, payload commander; David C. Leestma, mission specialist; Byron K. Lichtenberg, payload specialist; and C. Michael Foale, mission specialist. James H. Ragan (far right), head of the flight equipment section of the flight systems branch in JSC's Man Systems Division, briefs the crewmembers. Donald C. Carico, of the crew training staff and Rockwell International, stands near Bolden. The camera, used for out-the-window observations, is expected to be used frequently on the Atmospheric Laboratory for Applications and Science (ATLAS-1) mission, scheduled for a March date with the Space Shuttle Atlantis.

Orion MPCV GN and C End-to-End Phasing Tests

NASA Technical Reports Server (NTRS)

Neumann, Brian C.

2013-01-01

End-to-end integration tests are critical risk reduction efforts for any complex vehicle. Phasing tests are an end-to-end integrated test that validates system directional phasing (polarity) from sensor measurement through software algorithms to end effector response. Phasing tests are typically performed on a fully integrated and assembled flight vehicle where sensors are stimulated by moving the vehicle and the effectors are observed for proper polarity. Orion Multi-Purpose Crew Vehicle (MPCV) Pad Abort 1 (PA-1) Phasing Test was conducted from inertial measurement to Launch Abort System (LAS). Orion Exploration Flight Test 1 (EFT-1) has two end-to-end phasing tests planned. The first test from inertial measurement to Crew Module (CM) reaction control system thrusters uses navigation and flight control system software algorithms to process commands. The second test from inertial measurement to CM S-Band Phased Array Antenna (PAA) uses navigation and communication system software algorithms to process commands. Future Orion flights include Ascent Abort Flight Test 2 (AA-2) and Exploration Mission 1 (EM-1). These flights will include additional or updated sensors, software algorithms and effectors. This paper will explore the implementation of end-to-end phasing tests on a flight vehicle which has many constraints, trade-offs and compromises. Orion PA-1 Phasing Test was conducted at White Sands Missile Range (WSMR) from March 4-6, 2010. This test decreased the risk of mission failure by demonstrating proper flight control system polarity. Demonstration was achieved by stimulating the primary navigation sensor, processing sensor data to commands and viewing propulsion response. PA-1 primary navigation sensor was a Space Integrated Inertial Navigation System (INS) and Global Positioning System (GPS) (SIGI) which has onboard processing, INS (3 accelerometers and 3 rate gyros) and no GPS receiver. SIGI data was processed by GN&C software into thrust magnitude and direction commands. The processing changes through three phases of powered flight: pitchover, downrange and reorientation. The primary inputs to GN&C are attitude position, attitude rates, angle of attack (AOA) and angle of sideslip (AOS). Pitch and yaw attitude and attitude rate responses were verified by using a flight spare SIGI mounted to a 2-axis rate table. AOA and AOS responses were verified by using a data recorded from SIGI movements on a robotic arm located at NASA Johnson Space Center. The data was consolidated and used in an open-loop data input to the SIGI. Propulsion was the Launch Abort System (LAS) Attitude Control Motor (ACM) which consisted of a solid motor with 8 nozzles. Each nozzle has active thrust control by varying throat area with a pintle. LAS ACM pintles are observable through optically transparent nozzle covers. SIGI movements on robot arm, SIGI rate table movements and LAS ACM pintle responses were video recorded as test artifacts for analysis and evaluation. The PA-1 Phasing Test design was determined based on test performance requirements, operational restrictions and EGSE capabilities. This development progressed during different stages. For convenience these development stages are initial, working group, tiger team, Engineering Review Team (ERT) and final.

Applications of a Forward-Looking Interferometer for the On-board Detection of Aviation Weather Hazards

NASA Technical Reports Server (NTRS)

West, Leanne; Gimmestad, Gary; Smith, William; Kireev, Stanislav; Cornman, Larry B.; Schaffner, Philip R.; Tsoucalas, George

2008-01-01

The Forward-Looking Interferometer (FLI) is a new instrument concept for obtaining measurements of potential weather hazards to alert flight crews. The FLI concept is based on high-resolution Infrared (IR) Fourier Transform Spectrometry (FTS) technologies that have been developed for satellite remote sensing, and which have also been applied to the detection of aerosols and gases for other purposes. It is being evaluated for multiple hazards including clear air turbulence (CAT), volcanic ash, wake vortices, low slant range visibility, dry wind shear, and icing, during all phases of flight. Previous sensitivity and characterization studies addressed the phenomenology that supports detection and mitigation by the FLI. Techniques for determining the range, and hence warning time, were demonstrated for several of the hazards, and a table of research instrument parameters was developed for investigating all of the hazards discussed above. This work supports the feasibility of detecting multiple hazards with an FLI multi-hazard airborne sensor, and for producing enhanced IR images in reduced visibility conditions; however, further research must be performed to develop a means to estimate the intensities of the hazards posed to an aircraft and to develop robust algorithms to relate sensor measurables to hazard levels. In addition, validation tests need to be performed with a prototype system.

46 CFR 502.221 - Briefs; requests for findings.

Code of Federal Regulations, 2010 CFR

2010-10-01

... presiding officer shall fix the time and manner of filing briefs and any enlargement of time. The period of... subject index or table of contents with page references and a list of authorities cited. (f) All briefs... pages containing the table of contents, table of authorities, and certificate of service, unless the...

A Model-Based Optimization Plan for the Naval Helicopter Training Program

DTIC Science & Technology

2011-06-01

FF (E. Lashua, personal communication, January 18, 2011). Table 1. Training Costs: Introductory Flight Screening (IFS) (From AMS Aviation at...within the program is historically 3.3% due to DORs and academic failures (E. Lashua, personal communication, January 18, 2011). 18 7. Stage...duty station of NAS Corpus Christi, students are eligible to receive 10 days of house hunting leave to find and set up their house prior to checking

Environmental Planning Technical Report. Biological Resources

DTIC Science & Technology

1984-01-01

8217 v rini ana va r. Chokecherry melanoca rpa Shrubs Artemisia cana Silver sagebrush Ceratoides l-anata Wi nterf at Cerocarpus mortanus Mountain nahogany...nocarpa Chokecherry ialTix Spp. Wifllo 2-10 Table 2.6.1-i Continued, page 5 of 6 DOMINANT AND CHARACTERISTIC PLANT SPECIES Shrubs Salix spp. Willow...population on the Goshen Hole Rim near Flight S. Some of the more mesic draws support golden currant (Ribes aureum) and chokecherry (Prunus

Experimental Evaluation of the Flight Line Food Service Facility at Travis AFB

DTIC Science & Technology

1974-06-01

8217emm^^mmi - TABLE 1 DINNER MENU SOUPS DAILY Chili Con Came, Chicken Noodle Soup, Vegetable Soup, Cream of Tomato Soup MON - Vegetable-Beef...Soup TUE - Cream of Chicken Soup WED - Minestrone Soup THU - Beef Noodle Soup FRI - Clam Chowder SAT - Chicken Rice Soup SUN...within two days; frozen sandwiches and breakfast meals would be manufactured once a week and dinner meals every two weeks. During the experiment

Dice in space

NASA Image and Video Library

2014-05-31

ISS040-E-006093 (31 May 2014) --- With a few explanatory words attached to a message to Earth, Expedition 40 Flight Engineer Reid Wiseman of NASA sent down this image of a single piece of dice floating in front of one of the windows in the Cupola of the Earth-orbiting International Space Station. Wiseman commented, "This one is just for us board game players, table top strategy gamers, (etc.) whose dice collection behaviour borders on hoarding."

14 CFR 121.511 - Flight time limitations: Flight engineers: airplanes.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Flight engineers: airplanes. 121.511 Section 121.511 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Operations § 121.511 Flight time limitations: Flight engineers: airplanes. (a) In any operation in which one...

Flight results of attitude matching between Space Shuttle and Inertial Upper Stage (IUS) navigation systems

NASA Astrophysics Data System (ADS)

Treder, Alfred J.; Meldahl, Keith L.

The recorded histories of Shuttle/Orbiter attitude and Inertial Upper Stage (IUS) attitude have been analyzed for all joint flights of the IUS in the Orbiter. This database was studied to determine the behavior of relative alignment between the IUS and Shuttle navigation systems. It is found that the overall accuracy of physical alignment has a Shuttle Orbiter bias component less than 5 arcmin/axis and a short-term stability upper bound of 0.5 arcmin/axis, both at 1 sigma. Summaries of the experienced physical and inertial alginment offsets are shown in this paper, together with alignment variation data, illustrated with some flight histories. Also included is a table of candidate values for some error source groups in an Orbiter/IUS attitude errror model. Experience indicates that the Shuttle is much more accurate and stable as an orbiting launch platform than has so far been advertised. This information will be valuable for future Shuttle payloads, especially those (such as the Aeroassisted Flight Experiment) which carry their own inertial navigation systems, and which could update or initialize their attitude determination systems using the Shuttle as the reference.

Analysis of the IMS Location Accuracy in Northern Eurasia and North America Using Regional and Global Pn Travel-time Tables

NASA Astrophysics Data System (ADS)

United States Calibration Working Group, Russian Federation/

- Joint Research Program of Seismic Calibration of the International Monitoring System (IMS) in Northern Eurasia and North America has been signed by the Nuclear Treaty Programs Office (NTPO), Department of Defense USA, and the Special Monitoring Service (SMS) of the Ministry of Defense, Russian Federation (RF). Under the Program historical data from nuclear and large chemical explosions of known location and shot time, together with appropriate geological and geophysical data, has been used to derive regional Pn/P travel-time tables for seismic event location within the lower 48 States of the USA and the European part of the RF. These travel-time tables are up to 5seconds faster in shields than the IASPEI91 tables, and up to 5seconds slower in the Western USA. Relocation experiments using the regional Pn travel-time curves and surrogate networks for the IMS network generally improved locations for regional seismic events. The distance between true and estimated location (mislocation) was decreased from an average of 18.8km for the IASPEI91 tables to 10.1km for the regional Pn travel-time tables. However, the regional travel-time table approach has limitations caused by travel-time variations inside major tectonic provinces and paths crossing several tectonic provinces with substantially different crustal and upper mantle velocity structure.The RF members of the Calibration Working Group (WG): Colonel Vyacheslav Gordon (chairman); Dr. Prof. Marat Mamsurov, and Dr. Nikolai Vasiliev. The US members of the WG: Dr. Anton Dainty (chairman), Dr. Douglas Baumgardt, Mr. John Murphy, Dr. Robert North, and Dr. Vladislav Ryaboy.

Clustergrammer, a web-based heatmap visualization and analysis tool for high-dimensional biological data

PubMed Central

Fernandez, Nicolas F.; Gundersen, Gregory W.; Rahman, Adeeb; Grimes, Mark L.; Rikova, Klarisa; Hornbeck, Peter; Ma’ayan, Avi

2017-01-01

Most tools developed to visualize hierarchically clustered heatmaps generate static images. Clustergrammer is a web-based visualization tool with interactive features such as: zooming, panning, filtering, reordering, sharing, performing enrichment analysis, and providing dynamic gene annotations. Clustergrammer can be used to generate shareable interactive visualizations by uploading a data table to a web-site, or by embedding Clustergrammer in Jupyter Notebooks. The Clustergrammer core libraries can also be used as a toolkit by developers to generate visualizations within their own applications. Clustergrammer is demonstrated using gene expression data from the cancer cell line encyclopedia (CCLE), original post-translational modification data collected from lung cancer cells lines by a mass spectrometry approach, and original cytometry by time of flight (CyTOF) single-cell proteomics data from blood. Clustergrammer enables producing interactive web based visualizations for the analysis of diverse biological data. PMID:28994825

Mariner 9 data storage subsystem flight performance summary

NASA Technical Reports Server (NTRS)

Thomas, N. E.; Larman, B. T.

1973-01-01

The performance is summarized of the Mariner 9 Data Storage Subsystem (DSS) throughout the primary and extended missions. Information presented is limited to reporting of anomalies which occurred during the playback sequences. Tables and figures describe the anomalies (dropouts, missing and added bits, in the imaging data) as a function of time (accumulated tape passes). The data results indicate that the performance of the DSS was satisfactory and within specification throughout the mission. The data presented is taken from the Spacecraft Team Incident/Surprise Anomaly Log recorded during the mission. Pertinent statistics concerning the tape transport performance are given. Also presented is a brief description of DSS operation, particularly that related to the recorded anomalies. This covers the video data encoding and how it is interpreted/decoded by ground data processing and the functional operation of the DSS in abnormal conditions such as loss of lock to the playback signal.

The Sky

ERIC Educational Resources Information Center

Forma, Ray

2008-01-01

Go to the end of this article to find more detailed information about the Star Chart, how to use the chart, and a table of Moon phases. Use this table of phases to help you with the timing of successful astronomy evenings for students. The best time for an astronomy evening is usually six days after New Moon. (Contains 1 table and 3 figures.)

Flight through thunderstorm outflows. [aircraft landing

NASA Technical Reports Server (NTRS)

Frost, W.; Crosby, B.; Camp, D. W.

1978-01-01

Computer simulation of aircraft landing through thunderstorm gust fronts is carried out. The two-dimensional, nonlinear equations or aircraft motion containing all wind shear terms are solved numerically. The gust front spatial wind field inputs are provided in the form of tabulated experimental data which are coupled with a computer table lookup routine to provide the required wind components and shear at any given position within an approximate 500 m by 1 km vertical plane. The aircraft is considered to enter the wind field at a specified position under trimmed conditions. Both fixed control and automatic control landings are simulated. Flight paths, as well as control inputs necessary to maintain specified trajectories, are presented and discussed for aircraft having characteristics of a DC-8, B-747, augmentor-wing STOL, and a DHC-6.

Flight through thunderstorm outflows

NASA Technical Reports Server (NTRS)

Frost, W.; Crosby, B.; Camp, D. W.

1979-01-01

Computer simulation of aircraft landing through thunderstorm gust fronts is carried out. The 3 degree-of-freedom, nonlinear equations of aircraft motion for the longitudinal variables containing all two-dimensional wind shear terms are solved numerically. The gust front spatial wind field inputs are provided in the form of tabulated experimental data which are coupled with a computer table lookup routine to provide the required wind components and shear at any given position within an approximate 500 m x 1 km vertical plane. The aircraft is considered to enter the wind field at a specified position under trimmed conditions. Both fixed control and automatic control landings are simulated. Flight paths, as well as control inputs necessary to maintain specified trajectories, are presented and discussed for aircraft having characteristics of a DC-8, B-747, and a DHC-6.

CM-2 Environmental / Modal Testing of Spacehab Racks

NASA Technical Reports Server (NTRS)

McNelis, Mark E.; Goodnight, Thomas W.; Farkas, Michael A.

2001-01-01

Combined environmental/modal vibration testing has been implemented at the NASA Glenn Research Center's Structural Dynamics Laboratory. The benefits of combined vibration testing are that it facilitates test article modal characterization and vibration qualification testing. The Combustion Module-2 (CM-2) is a space experiment that launches on Shuttle mission STS 107 in the SPACEHAB Research Double Module. The CM-2 flight hardware is integrated into a SPACEHAB single and double rack. CM-2 rack level combined vibration testing was recently completed on a shaker table to characterize the structure's modal response and verify the random vibration response. Control accelerometers and limit force gauges, located between the fixture and rack interface, were used to verify the input excitation. Results of the testing were used to verify the loads and environments for flight on the Shuttle.

A time motion study in the immunization clinic of a tertiary care hospital of kolkata, west bengal.

PubMed

Chattopadhyay, Amitabha; Ghosh, Ritu; Maji, Sucharita; Ray, Tapobroto Guha; Lahiri, Saibendu Kumar

2012-01-01

A time and motion study is used to determine the amount of time required for a specific activity, work function, or mechanical process. Few such studies have been reported in the outpatient department of institutions, and such studies based exclusively on immunization clinic of an institute is a rarity. This was an observational cross sectional study done in the immunization clinic of R.G. Kar Medical College, Kolkata, over a period of 1 month (September 2010). The study population included mother/caregivers attending the immunization clinics with their children. The total sample was 482. Pre-synchronized stopwatches were used to record service delivery time at the different activity points. Median time was the same for both initial registration table and nutrition and health education table (120 seconds), but the vaccination and post vaccination advice table took the highest percentage of overall time (46.3%). Maximum time spent on the vaccination and post vaccination advice table was on Monday (538.1 s) and nutritional assessment and health assessment table took maximum time on Friday (217.1 s). Time taken in the first half of immunization session was more in most of the tables. The goal for achieving universal immunization against vaccine-preventable diseases requires multifaceted collated response from many stakeholders. Efficient functioning of immunization clinics is therefore required to achieve the prescribed goals. This study aims to initiate an effort to study the utilization of time at a certain health care unit with the invitation of much more in depth analysis in future.

Why bigger may in fact be better... in the context of table tennis

NASA Astrophysics Data System (ADS)

Truscott, Tadd; Pan, Zhao; Belden, Jesse

2014-11-01

We submit that table tennis is too fast. Because of the high ball velocities relative to the small table size, players are required to act extremely quickly, often exceeding the limits of human reaction time. Additionally, the Magnus effect resulting from large rotation rates introduces dramatically curved paths and causes rapid direction changes after striking the table or paddle, which effectively reduces reaction time further. Moreover, watching a professional game is often uninteresting and even tiring because the ball is moving too quickly to follow with the naked eye and the action of the players is too subtle to resolve from a distance. These facts isolate table tennis from our quantitatively defined ``fun game club,'' and make it less widely appealing than sports like baseball and soccer. Over the past 100 years, the rules of table tennis have changed several times in an effort to make the game more attractive to players and spectators alike, but the game continues to lose popularity. Here, we experimentally quantify the historic landmark equipment changes of table tennis from a fluid dynamics perspective. Based on theory and observation, we suggest a larger diameter ball for table tennis to make the game more appealing to both spectators and amateur players.

STS-51 pad abort. OV103-engine 2033 (ME-2) fuel flowmeter sensor open circuit

NASA Technical Reports Server (NTRS)

1993-01-01

The STS-51 initial launch attempt of Discovery (OV-103) was terminated on KSC launch pad 39B on 12 Aug. 1993 at 9:12 AM E.S.T. due to a sensor redundancy failure in the liquid hydrogen system of ME-2 (Engine 2033). The event description and time line are summarized. Propellant loading was initiated on 12 Aug. 1993 at 12:00 AM EST. All space shuttle main engine (SSME) chill parameters and Launch Commit Criteria (LCC) were nominal. At engine start plus 1.34 seconds a Failure Identification (FID) was posted against Engine 2033 for exceeding the 1800 spin intra-channel (A1-A2) Fuel Flowrate sensor channel qualification limit. The engine was shut down at 1.50 seconds followed by Engines 2032 and 2030. All shut down sequences were nominal and the mission was safely aborted. SSME Avionics hardware and software performed nominally during the incident. A review of vehicle data table (VDT) data and controller software logic revealed no failure indications other than the single FID 111-101, Fuel Flowrate Intra-Channel Test Channel A disqualification. Software logic was executed according to requirements and there was no anomalous controller software operation. Immediately following the abort, a Rocketdyne/NASA failure investigation team was assembled. The team successfully isolated the failure cause to an open circuit in a Fuel Flowrate Sensor. This type of failure has occurred eight previous times in ground testing. The sensor had performed acceptably on three previous flights of the engine and SSME flight history shows 684 combined fuel flow rate sensor channel flights without failure. The disqualification of an Engine 2 (SSME No. 2033) Fuel Flowrate sensor channel was a result of an instrumentation failure and not engine performance. All other engine operations were nominal. This disqualification resulted in an engine shutdown and safe sequential shutdown of all three engines prior to ignition of the solid boosters.

Increasing the Automation and Autonomy for Spacecraft Operations with Criteria Action Table

NASA Technical Reports Server (NTRS)

Li, Zhen-Ping; Savki, Cetin

2005-01-01

The Criteria Action Table (CAT) is an automation tool developed for monitoring real time system messages for specific events and processes in order to take user defined actions based on a set of user-defined rules. CAT was developed by Lockheed Martin Space Operations as a part of a larger NASA effort at the Goddard Space Flight Center (GSFC) to create a component-based, middleware-based, and standard-based general purpose ground system architecture referred as GMSEC - the GSFC Mission Services Evolution Center. CAT has been integrated into the upgraded ground systems for Tropical Rainfall Measuring Mission (TRMM) and Small Explorer (SMEX) satellites and it plays the central role in their automation effort to reduce the cost and increase the reliability for spacecraft operations. The GMSEC architecture provides a standard communication interface and protocol for components to publish/describe messages to an information bus. It also provides a standard message definition so components can send and receive messages to the bus interface rather than each other, thus reducing the component-to-component coupling, interface, protocols, and link (socket) management. With the GMSEC architecture, components can publish standard event messages to the bus for all nominal, significant, and surprising events in regard to satellite, celestial, ground system, or any other activity. In addition to sending standard event messages, each GMSEC compliant component is required to accept and process GMSEC directive request messages.

14 CFR 91.1059 - Flight time limitations and rest requirements: One or two pilot crews.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Rest 10 Hours 12 Hours. (6) Minimum After Duty Rest Period for Multi-Time Zone Flights 14 Hours 18... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight time limitations and rest... OPERATING AND FLIGHT RULES Fractional Ownership Operations Program Management § 91.1059 Flight time...

14 CFR 91.1057 - Flight, duty and rest time requirements: All crewmembers.

Code of Federal Regulations, 2010 CFR

2010-01-01

... cabin-safety-related responsibilities. Multi-time zone flight means an easterly or westerly flight or multiple flights in one direction in the same duty period that results in a time zone difference of 5 or... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight, duty and rest time requirements...

Structural Area Inspection Frequency Evaluation (SAIFE). Volume 5. Results of Model Demonstration

DTIC Science & Technology

1978-04-01

serlV ice 11 i Stot’)’ .i ’ base~d Otil narrow -bodly at ir-c t’a ftA wh ich have fewer 0 1 euient~s than thle hypothet i cal widve - A body aircaf...kP1 c u TABLE 14. DL40MRATION RESULTS .M WING - SPAR, FMD Defects Per Million Flight Hours Crack Detected Preflight 0.00 0104 Service 0.00 0.49 Phase

Cost/benefit tradeoffs for reducing the energy consumption of the commercial air transportation system. Volume 1: Technical analysis

NASA Technical Reports Server (NTRS)

Kraus, E. F.

1976-01-01

The effectiveness and associated costs of operational and technical options for reduced fuel consumption by Douglas aircraft in the domestic airline fleet are assessed. Areas explored include alternative procedures for airline and flight operations, advanced and state of the art technology, modification and derivative configurations, new near-term aircraft, turboprop configuration studies, and optimum aircraft geometry. Data for each aircraft studied is presented in tables and graphs.

VizieR Online Data Catalog: SOFIA Massive (SOMA) Star Formation Survey. I. (De Buizer+, 2017)

NASA Astrophysics Data System (ADS)

De Buizer, J. M.; Liu, M.; Tan, J. C.; Zhang, Y.; Beltran, M. T.; Shuping, R.; Staff, J. E.; Tanaka, K. E. I.; Whitney, B.

2018-02-01

The following eight sources, AFGL 4029, AFGL 437, IRAS 07299-1651, G35.20-0.74, G45.45+0.05, IRAS 20126+4104, Cepheus A, and NGC 7538 IRS9, were observed by SOFIA with the FORCAST instrument (see Table 1). Data were taken on multiple flights spanning the Early Science period, Cycle 1, and Cycle 2 SOFIA observing cycles (spanning 2011 May to 2014 June). (4 data files).

Helicopter Visual Segment Approach Lighting System (HALS) Test Report

DTIC Science & Technology

1988-08-01

this Pegl 23. Ne. a# Palo$ 22. Ptuco Unclassified Unclassified 316 Form DOT F 1700.7 (8-721 Reproduction of e9Isted Ppe authorized TABLE OF CONTENTS...Subject Pilot Range Rate/Vertical Position Plots lii LIST OF ILLUSTRATIONS Figure Page I Basic Heliport IFR Lighting System 4 2 Heliport Approach...Instrument Flight Rules ( IFR ) Heliport Lighting System and a centerline HALS. The Basic IFR Approach Light System is presented in figure 1. It consists of

Inflight fuel tank temperature survey data

NASA Technical Reports Server (NTRS)

Pasion, A. J.

1979-01-01

Statistical summaries of the fuel and air temperature data for twelve different routes and for different aircraft models (B747, B707, DC-10 and DC-8), are given. The minimum fuel, total air and static air temperature expected for a 0.3% probability were summarized in table form. Minimum fuel temperature extremes agreed with calculated predictions and the minimum fuel temperature did not necessarily equal the minimum total air temperature even for extreme weather, long range flights.

ChemCam for Mars Science Laboratory rover, undergoing pre-flight testing

DOE Office of Scientific and Technical Information (OSTI.GOV)

None

2011-10-20

Los Alamos National Laboratory and partners developed a laser instrument, ChemCam, that will ride on the elevated mast of the Mars Science Laboratory rover Curiosity. The system allows Curiosity to "zap" rocks from a distance, reading their chemical composition through spectroscopic analysis. In this video, laboratory shaker-table testing of the instrument ensures that all of its components are solidly attached and resistant to damage from the rigors of launch, travel and landing.

ChemCam for Mars Science Laboratory rover, undergoing pre-flight testing

ScienceCinema

None

2018-06-06

Los Alamos National Laboratory and partners developed a laser instrument, ChemCam, that will ride on the elevated mast of the Mars Science Laboratory rover Curiosity. The system allows Curiosity to "zap" rocks from a distance, reading their chemical composition through spectroscopic analysis. In this video, laboratory shaker-table testing of the instrument ensures that all of its components are solidly attached and resistant to damage from the rigors of launch, travel and landing.

Software Impact of Selected En Route ATC Computer Replacement Strategies.

DTIC Science & Technology

1979-12-01

Compare 188 SDG Duplicate Flight Plan Search 558 SDU Amendment Output Initiator 3,094 SHA Heading Angle Correction 22 STB Chained -Table Management 278...communications) 1would be required in both systems. However the uses of MK in the two systems to supply information to the two copies of SBB would be...this, all current use of Commniand Chaining -11- and Program Controlled Interrupts will have to be deleted from the existing 9020 programs. For the

Telecom 2-A (TC2A)

NASA Technical Reports Server (NTRS)

Dulac, J.; Latour, J.

1991-01-01

The DSN (Deep Space Network) mission support requirements for Telecom 2-A (TC2A) are summarized. The Telecom 2-A will provide high-speed data link applications, telephone, and television service between France and overseas territories. The mission objectives are outlined and the DSN support requirements are defined through the presentation of tables and narratives describing the spacecraft flight profile; DSN support coverage; frequency assignments; support parameters for telemetry, command and support systems; and tracking support responsibility.

Simultaneous cabin and ambient ozone measurements on two Boeing 747 airplanes, volume 1

NASA Technical Reports Server (NTRS)

Perkins, P. J.; Holdeman, J. D.; Nastrom, G. D.

1979-01-01

Measurements of zone concentrations both outside and in the cabin of an airline operated Boeing 747SP and Boeing 747-100 airliner are presented. Plotted data and the corresponding tables of observations taken at altitude between the departure and destination airports of each flight are arranged chronologically for the two aircraft. Data were taken at five or ten minute intervals by automated instrumentation used in the NACA Global Atmospheric Sampling Program.

NASA MSFC hardware in the loop simulations of automatic rendezvous and capture systems

NASA Technical Reports Server (NTRS)

Tobbe, Patrick A.; Naumann, Charles B.; Sutton, William; Bryan, Thomas C.

1991-01-01

Two complementary hardware-in-the-loop simulation facilities for automatic rendezvous and capture systems at MSFC are described. One, the Flight Robotics Laboratory, uses an 8 DOF overhead manipulator with a work volume of 160 by 40 by 23 feet to evaluate automatic rendezvous algorithms and range/rate sensing systems. The other, the Space Station/Station Operations Mechanism Test Bed, uses a 6 DOF hydraulic table to perform docking and berthing dynamics simulations.

Advanced Flight Simulator: Utilization in A-10 Conversion and Air-to-Surface Attack Training.

DTIC Science & Technology

1981-01-01

ASPT to the A-I0. Finally. the objectivity of the criteria ( parameters of aircraft control. bomb-drop circular error. and percentage of rounds through a...low angle strafe task. Table 4 presents a listing of these tasks and their related release parameters . 12 __ __ _ __ Tab/e .1. A/S Weapons I)eliven...Scoring. Two dependent variables, specific to the phase of student training, were used. In the conversion training phase. specific parameters for

Real-time 4D ERT monitoring of river water intrusion into a former nuclear disposal site using a transient warping-mesh water table boundary (Invited)

NASA Astrophysics Data System (ADS)

Johnson, T.; Hammond, G. E.; Versteeg, R. J.; Zachara, J. M.

2013-12-01

The Hanford 300 Area, located adjacent to the Columbia River in south-central Washington, USA, is the site of former research and uranium fuel rod fabrication facilities. Waste disposal practices at site included discharging between 33 and 59 metric tons of uranium over a 40 year period into shallow infiltration galleries, resulting in persistent uranium contamination within the vadose and saturated zones. Uranium transport from the vadose zone to the saturated zone is intimately linked with water table fluctuations and river water intrusion driven by upstream dam operations. As river stage increases, the water table rises into the vadose zone and mobilizes contaminated pore water. At the same time, river water moves inland into the aquifer, and river water chemistry facilitates further mobilization by enabling uranium desorption from contaminated sediments. As river stage decreases, flow moves toward the river, ultimately discharging contaminated water at the river bed. River water specific conductance at the 300 Area varies around 0.018 S/m whereas groundwater specific conductance varies around 0.043 S/m. This contrast provides the opportunity to monitor groundwater/river water interaction by imaging changes in bulk conductivity within the saturated zone using time-lapse electrical resistivity tomography. Previous efforts have demonstrated this capability, but have also shown that disconnecting regularization constraints at the water table is critical for obtaining meaningful time-lapse images. Because the water table moves with time, the regularization constraints must also be transient to accommodate the water table boundary. This was previously accomplished with 2D time-lapse ERT imaging by using a finely discretized computational mesh within the water table interval, enabling a relatively smooth water table to be defined without modifying the mesh. However, in 3D this approach requires a computational mesh with an untenable number of elements. In order to accommodate the water table boundary in 3D, we propose a time-lapse warping mesh inversion, whereby mesh elements that traverse the water table are modified to generate a smooth boundary at the known water table position, enabling regularization constraints to be accurately disconnected across the water table boundary at a given time. We demonstrate the approach using a surface ERT array installed adjacent to the Columbia River at the 300 Area, consisting of 352 electrodes and covering an area of approximately 350 m x 350 m. Using autonomous data collection, transmission, and filtering tools coupled with high performance computing resources, the 4D imaging process is automated and executed in real time. Each time lapse survey consists of approximately 40,000 measurements and 4 surveys are collected and processed per day from April 1st , 2013 to September 30th, 2013. The data are inverted on an unstructured tetrahedral mesh that honors LiDAR-based surface topography and is comprised of approximately 905,000 elements. Imaging results show the dynamic 4D extent of river water intrusion, and are validated with well-based fluid conductivity measurements at each monitoring well within the imaging domain.

14 CFR 417.221 - Time delay analysis.

Code of Federal Regulations, 2010 CFR

2010-01-01

... OF TRANSPORTATION LICENSING LAUNCH SAFETY Flight Safety Analysis § 417.221 Time delay analysis. (a) General. A flight safety analysis must include a time delay analysis that establishes the mean elapsed time between the violation of a flight termination rule and the time when the flight safety system is...

14 CFR 417.221 - Time delay analysis.

Code of Federal Regulations, 2011 CFR

2011-01-01

... OF TRANSPORTATION LICENSING LAUNCH SAFETY Flight Safety Analysis § 417.221 Time delay analysis. (a) General. A flight safety analysis must include a time delay analysis that establishes the mean elapsed time between the violation of a flight termination rule and the time when the flight safety system is...

Development of an analytical method to predict helicopter main rotor performance in icing conditions

NASA Technical Reports Server (NTRS)

Britton, Randall K.

1992-01-01

Historically, certification of a helicopter for flight into known icing conditions was a problem. This is because of the current emphasis on flight testing for verification of system performance. Flight testing in icing conditions is difficult because, in addition to being dangerous and expensive, many times conditions which are sought after cannot be readily found in nature. The problem is compounded for helicopters because of their small range in comparison to many fixed wing aircraft. Thus, helicopters are forced to wait for conditions to occur in a certain region rather than seeking them out. These and other drawbacks to flight testing prompted extreme interest in developing validated alternatives to flight testing. One such alternative is theoretical prediction. It is desirable to have the ability to predict how a helicopter will perform when subjected to icing conditions. Herein, calculations are restricted to the main rotor, and are illustrated. The computational tool used to obtain performance is the lifting line analysis of B65. B65 incorporates experimental data into data banks in order to determine the section lift, drag, and moment characteristics of various airfoils at different Mach numbers and angles of attack. The local flow angle is calculated at user specified radial locations. This flow angle, along with the local Mach number is then cross referenced with the airfoil tables to obtain the local section characteristics. The local characteristics are then integrated together to obtain the entire rotor attributes. Once the clean performance is known, characterization of the type and shape of ice which accretes on the rotor blades is obtained using the analysis of LEWICE. The Interactive Boundary Layer (IBL) method then calculates the 2-D characteristics of the iced airfoil for input into the airfoil data bank of B65. Calculations are restricted to natural ice shedding and it is assumed that no de-icing takes place. Once the new lift, drag, and moment characteristics are known for the entire blade radius, this information is fed into B65, where the iced performance is then calculated.

Guess who's not coming to dinner? Evaluating online restaurant reservations for disease surveillance.

PubMed

Nsoesie, Elaine O; Buckeridge, David L; Brownstein, John S

2014-01-22

Alternative data sources are used increasingly to augment traditional public health surveillance systems. Examples include over-the-counter medication sales and school absenteeism. We sought to determine if an increase in restaurant table availabilities was associated with an increase in disease incidence, specifically influenza-like illness (ILI). Restaurant table availability was monitored using OpenTable, an online restaurant table reservation site. A daily search was performed for restaurants with available tables for 2 at the hour and at half past the hour for 22 distinct times: between 11:00 am-3:30 pm for lunch and between 6:00-11:30 PM for dinner. In the United States, we examined table availability for restaurants in Boston, Atlanta, Baltimore, and Miami. For Mexico, we studied table availabilities in Cancun, Mexico City, Puebla, Monterrey, and Guadalajara. Time series of restaurant use was compared with Google Flu Trends and ILI at the state and national levels for the United States and Mexico using the cross-correlation function. Differences in restaurant use were observed across sampling times and regions. We also noted similarities in time series trends between data on influenza activity and restaurant use. In some settings, significant correlations greater than 70% were noted between data on restaurant use and ILI trends. This study introduces and demonstrates the potential value of restaurant use data for event surveillance.

Near Real Time Review of Instrument Performance using the Airborne Data Processing and Analysis Software Package

NASA Astrophysics Data System (ADS)

Delene, D. J.

2014-12-01

Research aircraft that conduct atmospheric measurements carry an increasing array of instrumentation. While on-board personnel constantly review instrument parameters and time series plots, there are an overwhelming number of items. Furthermore, directing the aircraft flight takes up much of the flight scientist time. Typically, a flight engineer is given the responsibility of reviewing the status of on-board instruments. While major issues like not receiving data are quickly identified during a flight, subtle issues like low but believable concentration measurements may go unnoticed. Therefore, it is critical to review data after a flight in near real time. The Airborne Data Processing and Analysis (ADPAA) software package used by the University of North Dakota automates the post-processing of aircraft flight data. Utilizing scripts to process the measurements recorded by data acquisition systems enables the generation of data files within an hour of flight completion. The ADPAA Cplot visualization program enables plots to be quickly generated that enable timely review of all recorded and processed parameters. Near real time review of aircraft flight data enables instrument problems to be identified, investigated and fixed before conducting another flight. On one flight, near real time data review resulted in the identification of unusually low measurements of cloud condensation nuclei, and rapid data visualization enabled the timely investigation of the cause. As a result, a leak was found and fixed before the next flight. Hence, with the high cost of aircraft flights, it is critical to find and fix instrument problems in a timely matter. The use of a automated processing scripts and quick visualization software enables scientists to review aircraft flight data in near real time to identify potential problems.

Real Time Correction of Aircraft Flight Fonfiguration

NASA Technical Reports Server (NTRS)

Schipper, John F. (Inventor)

2009-01-01

Method and system for monitoring and analyzing, in real time, variation with time of an aircraft flight parameter. A time-dependent recovery band, defined by first and second recovery band boundaries that are spaced apart at at least one time point, is constructed for a selected flight parameter and for a selected time recovery time interval length .DELTA.t(FP;rec). A flight parameter, having a value FP(t=t.sub.p) at a time t=t.sub.p, is likely to be able to recover to a reference flight parameter value FP(t';ref), lying in a band of reference flight parameter values FP(t';ref;CB), within a time interval given by t.sub.p.ltoreq.t'.ltoreq.t.sub.p.DELTA.t(FP;rec), if (or only if) the flight parameter value lies between the first and second recovery band boundary traces.

Image Quality and Diagnostic Performance of a Digital PET Prototype in Patients with Oncologic Diseases: Initial Experience and Comparison with Analog PET.

PubMed

Nguyen, Nghi C; Vercher-Conejero, Jose L; Sattar, Abdus; Miller, Michael A; Maniawski, Piotr J; Jordan, David W; Muzic, Raymond F; Su, Kuan-Hao; O'Donnell, James K; Faulhaber, Peter F

2015-09-01

We report our initial clinical experience for image quality and diagnostic performance of a digital PET prototype scanner with time-of-flight (DigitalTF), compared with an analog PET scanner with time-of-flight (GeminiTF PET/CT). Twenty-one oncologic patients, mean age 58 y, first underwent clinical (18)F-FDG PET/CT on the GeminiTF. The scanner table was then withdrawn while the patient remained on the table, and the DigitalTF was inserted between the GeminiTF PET and CT scanner. The patients were scanned for a second time using the same PET field of view with CT from the GeminiTF for attenuation correction. Two interpreters reviewed the 2 sets of PET/CT images for overall image quality, lesion conspicuity, and sharpness. They counted the number of suggestive (18)F-FDG-avid lesions and provided the TNM staging for the 5 patients referred for initial staging. Standardized uptake values (SUVs) and SUV gradients as a measure of lesion sharpness were obtained. The DigitalTF showed better image quality than the GeminiTF. In a side-by-side comparison using a 5-point scale, lesion conspicuity (4.3 ± 0.6), lesion sharpness (4.3 ± 0.6), and diagnostic confidence (3.4 ± 0.7) were better with DigitalTF than with GeminiTF (P < 0.01). In 52 representative lesions, the lesion maximum SUV was 36% higher with DigitalTF than with GeminiTF, lesion-to-blood-pool SUV ratio was 59% higher, and SUV gradient was 51% higher, with good correlation between the 2 scanners. Lesions less than 1.5 cm showed a greater increase in SUV from GeminiTF to DigitalTF than those lesions 1.5 cm or greater. In 5 of 21 patients, DigitalTF showed an additional 8 suggestive lesions that were not seen using GeminiTF. In the 15 restaging patients, the true-negative rate was 100% and true-positive rate was 78% for both scanners. In the 5 patients for initial staging, DigitalTF led to upstaging in 2 patients and showed the same staging in the other 3 patients, compared with GeminiTF. DigitalTF provides better image quality, diagnostic confidence, and accuracy than GeminiTF. DigitalTF may be the most beneficial in detecting small tumor lesions and disease staging. © 2015 by the Society of Nuclear Medicine and Molecular Imaging, Inc.

IMS/Satellite Situation Center report. Predicted orbit plots for Hawkeye 1, 1976

NASA Technical Reports Server (NTRS)

1975-01-01

The predicted orbit plots are shown in three projections. The time period covered by each set of projections is 2 days 1 hour, corresponding approximately to the period of Hawkeye 1. The three coordinate systems used are the Geocentric Solar Ecliptic system (GSE), the Geocentric Solar Magnetospheric system (GSM), and the Solar Magnetic system (SM). For each of the three projections, time ticks and codes are given on the satellite trajectories. The codes are interpreted in the table at the base of each plot. Time is given in the table as year/day/decimal hour. The total time covered by each plot is shown at the bottom of each table, and an additional variable is given in the table for each time tick. For the GSM and SM projection this variable is the geocentric distance to the satellite in earth radii, and for the GSE projection the variable is satellite ecliptic latitude in degrees.

14 CFR 61.163 - Aeronautical experience: Powered-lift category rating.

Code of Federal Regulations, 2013 CFR

2013-01-01

... time in a flight simulator or flight training device. (ii) A maximum of 50 hours of training in a flight simulator or flight training device may be credited toward the instrument flight time requirements... training center certificated under part 142 of this chapter. (iii) Training in a flight simulator or flight...

14 CFR 61.163 - Aeronautical experience: Powered-lift category rating.

Code of Federal Regulations, 2014 CFR

2014-01-01

... time in a flight simulator or flight training device. (ii) A maximum of 50 hours of training in a flight simulator or flight training device may be credited toward the instrument flight time requirements... training center certificated under part 142 of this chapter. (iii) Training in a flight simulator or flight...

14 CFR 61.163 - Aeronautical experience: Powered-lift category rating.

Code of Federal Regulations, 2012 CFR

2012-01-01

... time in a flight simulator or flight training device. (ii) A maximum of 50 hours of training in a flight simulator or flight training device may be credited toward the instrument flight time requirements... training center certificated under part 142 of this chapter. (iii) Training in a flight simulator or flight...

14 CFR 398.7 - Timing of flights.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Timing of flights. 398.7 Section 398.7... STATEMENTS GUIDELINES FOR INDIVIDUAL DETERMINATIONS OF BASIC ESSENTIAL AIR SERVICE § 398.7 Timing of flights. To qualify as essential air service, flights must depart at reasonable times, considering the needs...

14 CFR 398.7 - Timing of flights.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Timing of flights. 398.7 Section 398.7... STATEMENTS GUIDELINES FOR INDIVIDUAL DETERMINATIONS OF BASIC ESSENTIAL AIR SERVICE § 398.7 Timing of flights. To qualify as essential air service, flights must depart at reasonable times, considering the needs...

76 FR 774 - Folding Metal Tables and Chairs From the People's Republic of China: Notice of Extension of Time...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-01-06

... DEPARTMENT OF COMMERCE International Trade Administration [A-570-868] Folding Metal Tables and... review of the antidumping duty order on folding metal tables and chairs from the People's Republic of China (``PRC''). See Folding Metal Tables and Chairs: Initiation of New Shipper Review, 75 FR 44767...

Projecting a Stand Table Through Time

Treesearch

Quang V. Cao; V. Clark Baldwin

1999-01-01

Stand tables provide number of trees per acre for each diameter class. This paper presents a general technique to predict a future stand table, based on the current stand table and future stand summary statistics such as trees and basal area per acre, and average diameter. The stand projection technique involves (a) predicting surviving trees for each class, and (b)...

STS-106 Crew Activity Report/Flight Day 1 Highlights

NASA Technical Reports Server (NTRS)

2000-01-01

On this first day of the STS-106 Atlantis mission, the flight crew, Commander Terrence W. Wilcutt, Pilot Scott D. Altman, and Mission Specialists Daniel C. Burbank, Edward T. Lu, Richard A. Mastracchio, Yuri Ivanovich Malenchenko, and Boris V. Morukov are seen performing pre-launch activities. They are shown sitting around the breakfast table with the traditional cake, suiting-up, and riding out to the launch pad. The final inspection team is seen as they conduct their final check of the space shuttle on the launch complex. Also, included are various panoramic views of the shuttle on the pad. The crew is readied in the 'white room' for their mission. After the closing of the hatch and arm retraction, launch activities are shown including countdown, engine ignition, launch, and the separation of the Solid Rocket Boosters.

CM-2 Environmental/Modal Testing of SPACEHAB Racks

NASA Technical Reports Server (NTRS)

McNelis, Mark E.; Goodnight, Thomas W.

2001-01-01

Combined environmental/modal vibration testing has been implemented at the NASA Glenn Research Center's Structural Dynamics Laboratory. The benefits of combined vibration testing are that it facilitates test article modal characterization and vibration qualification testing. The Combustion Module-2 (CM-2) is a space experiment that will launch on shuttle mission STS-107 in the SPACEHAB Research Double Module. The CM-2 flight hardware is integrated into a SPACEHAB single and double rack. CM-2 rack-level combined vibration testing was recently completed on a shaker table to characterize the structure's modal response and verify the random vibration response. Control accelerometers and limit force gauges, located between the fixture and rack interface, were used to verify the input excitation. Results of the testing were used to verify the loads and environments for flight on the shuttles.

On a Formal Tool for Reasoning About Flight Software Cost Analysis

NASA Technical Reports Server (NTRS)

Spagnuolo, John N., Jr.; Stukes, Sherry A.

2013-01-01

A report focuses on the development of flight software (FSW) cost estimates for 16 Discovery-class missions at JPL. The techniques and procedures developed enabled streamlining of the FSW analysis process, and provided instantaneous confirmation that the data and processes used for these estimates were consistent across all missions. The research provides direction as to how to build a prototype rule-based system for FSW cost estimation that would provide (1) FSW cost estimates, (2) explanation of how the estimates were arrived at, (3) mapping of costs, (4) mathematical trend charts with explanations of why the trends are what they are, (5) tables with ancillary FSW data of interest to analysts, (6) a facility for expert modification/enhancement of the rules, and (7) a basis for conceptually convenient expansion into more complex, useful, and general rule-based systems.

Interference tables: a useful model for interference analysis in asynchronous multicarrier transmission

NASA Astrophysics Data System (ADS)

Medjahdi, Yahia; Terré, Michel; Ruyet, Didier Le; Roviras, Daniel

2014-12-01

In this paper, we investigate the impact of timing asynchronism on the performance of multicarrier techniques in a spectrum coexistence context. Two multicarrier schemes are considered: cyclic prefix-based orthogonal frequency division multiplexing (CP-OFDM) with a rectangular pulse shape and filter bank-based multicarrier (FBMC) with physical layer for dynamic spectrum access and cognitive radio (PHYDYAS) and isotropic orthogonal transform algorithm (IOTA) waveforms. First, we present the general concept of the so-called power spectral density (PSD)-based interference tables which are commonly used for multicarrier interference characterization in spectrum sharing context. After highlighting the limits of this approach, we propose a new family of interference tables called `instantaneous interference tables'. The proposed tables give the interference power caused by a given interfering subcarrier on a victim one, not only as a function of the spectral distance separating both subcarriers but also with respect to the timing misalignment between the subcarrier holders. In contrast to the PSD-based interference tables, the accuracy of the proposed tables has been validated through different simulation results. Furthermore, due to the better frequency localization of both PHYDYAS and IOTA waveforms, FBMC technique is demonstrated to be more robust to timing asynchronism compared to OFDM one. Such a result makes FBMC a potential candidate for the physical layer of future cognitive radio systems.

KITAE I: Edge Organisation in Battlespace Helmand

DTIC Science & Technology

2011-06-01

military organization with its own culture that frustrates the timely delivery of complete information to the authority with assets to take synchronized...21st century information technologies, we have a 19th century military organization with its own culture that frustrates the timely delivery of...Table 5.0 QEQ NOV Table 6.0 QEQ DEC Table 7.0 QEQ JAN 4 Asymmetric warfare is a confrontation between political, cultural , social and

V/STOL tilt rotor study. Volume 6: Hover, low speed and conversion tests of a tilt rotor aeroelastic model (Model 300)

NASA Technical Reports Server (NTRS)

Marr, R. L.; Sambell, K. W.; Neal, G. T.

1973-01-01

Stability and control tests of a scale model of a tilt rotor research aircraft were conducted. The characteristics of the model for hover, low speed, and conversion flight were analyzed. Hover tests were conducted in a rotor whirl cage. Helicopter and conversion tests were conducted in a low speed wind tunnel. Data obtained from the tests are presented as tables and graphs. Diagrams and illustrations of the test equipment are provided.

ASTRONAUT ACTIVITY - APOLLO-SOYUZ TEST PROJECT (ASTP) - SOFTWARE - KSC

NASA Image and Video Library

1975-02-08

S75-24108 (8-10 Feb. 1975) --- A group of Apollo-Soyuz Test Project crewmen inspects an Apollo spacesuit during a three-day tour of NASA's Kennedy Space Center. They were at KSC to look over ASTP launch facilities and flight hardware. The six men wearing white caps are, left to right, cosmonaut Valeriy N. Kubasov, interpreter K.S. Samofal (far end of table), astronaut Vance D. Brand, cosmonaut Aleksey A. Leonov, cosmonaut Vladimir A. Shatalov and astronaut Donald K. Slayton.

Detecting Surface Changes from an Underground Explosion in Granite Using Unmanned Aerial System Photogrammetry

DOE PAGES

Schultz-Fellenz, Emily S.; Coppersmith, Ryan T.; Sussman, Aviva J.; ...

2017-08-19

Efficient detection and high-fidelity quantification of surface changes resulting from underground activities are important national and global security efforts. In this investigation, a team performed field-based topographic characterization by gathering high-quality photographs at very low altitudes from an unmanned aerial system (UAS)-borne camera platform. The data collection occurred shortly before and after a controlled underground chemical explosion as part of the United States Department of Energy’s Source Physics Experiments (SPE-5) series. The high-resolution overlapping photographs were used to create 3D photogrammetric models of the site, which then served to map changes in the landscape down to 1-cm-scale. Separate models weremore » created for two areas, herein referred to as the test table grid region and the nearfield grid region. The test table grid includes the region within ~40 m from surface ground zero, with photographs collected at a flight altitude of 8.5 m above ground level (AGL). The near-field grid area covered a broader area, 90–130 m from surface ground zero, and collected at a flight altitude of 22 m AGL. The photographs, processed using Agisoft Photoscan® in conjunction with 125 surveyed ground control point targets, yielded a 6-mm pixel-size digital elevation model (DEM) for the test table grid region. This provided the ≤3 cm resolution in the topographic data to map in fine detail a suite of features related to the underground explosion: uplift, subsidence, surface fractures, and morphological change detection. The near-field grid region data collection resulted in a 2-cm pixel-size DEM, enabling mapping of a broader range of features related to the explosion, including: uplift and subsidence, rock fall, and slope sloughing. This study represents one of the first works to constrain, both temporally and spatially, explosion-related surface damage using a UAS photogrammetric platform; these data will help to advance the science of underground explosion detection.« less

Detecting Surface Changes from an Underground Explosion in Granite Using Unmanned Aerial System Photogrammetry

NASA Astrophysics Data System (ADS)

Schultz-Fellenz, Emily S.; Coppersmith, Ryan T.; Sussman, Aviva J.; Swanson, Erika M.; Cooley, James A.

2017-08-01

Efficient detection and high-fidelity quantification of surface changes resulting from underground activities are important national and global security efforts. In this investigation, a team performed field-based topographic characterization by gathering high-quality photographs at very low altitudes from an unmanned aerial system (UAS)-borne camera platform. The data collection occurred shortly before and after a controlled underground chemical explosion as part of the United States Department of Energy's Source Physics Experiments (SPE-5) series. The high-resolution overlapping photographs were used to create 3D photogrammetric models of the site, which then served to map changes in the landscape down to 1-cm-scale. Separate models were created for two areas, herein referred to as the test table grid region and the nearfield grid region. The test table grid includes the region within 40 m from surface ground zero, with photographs collected at a flight altitude of 8.5 m above ground level (AGL). The near-field grid area covered a broader area, 90-130 m from surface ground zero, and collected at a flight altitude of 22 m AGL. The photographs, processed using Agisoft Photoscan® in conjunction with 125 surveyed ground control point targets, yielded a 6-mm pixel-size digital elevation model (DEM) for the test table grid region. This provided the ≤3 cm resolution in the topographic data to map in fine detail a suite of features related to the underground explosion: uplift, subsidence, surface fractures, and morphological change detection. The near-field grid region data collection resulted in a 2-cm pixel-size DEM, enabling mapping of a broader range of features related to the explosion, including: uplift and subsidence, rock fall, and slope sloughing. This study represents one of the first works to constrain, both temporally and spatially, explosion-related surface damage using a UAS photogrammetric platform; these data will help to advance the science of underground explosion detection.

Detecting Surface Changes from an Underground Explosion in Granite Using Unmanned Aerial System Photogrammetry

DOE Office of Scientific and Technical Information (OSTI.GOV)

Schultz-Fellenz, Emily S.; Coppersmith, Ryan T.; Sussman, Aviva J.

Efficient detection and high-fidelity quantification of surface changes resulting from underground activities are important national and global security efforts. In this investigation, a team performed field-based topographic characterization by gathering high-quality photographs at very low altitudes from an unmanned aerial system (UAS)-borne camera platform. The data collection occurred shortly before and after a controlled underground chemical explosion as part of the United States Department of Energy’s Source Physics Experiments (SPE-5) series. The high-resolution overlapping photographs were used to create 3D photogrammetric models of the site, which then served to map changes in the landscape down to 1-cm-scale. Separate models weremore » created for two areas, herein referred to as the test table grid region and the nearfield grid region. The test table grid includes the region within ~40 m from surface ground zero, with photographs collected at a flight altitude of 8.5 m above ground level (AGL). The near-field grid area covered a broader area, 90–130 m from surface ground zero, and collected at a flight altitude of 22 m AGL. The photographs, processed using Agisoft Photoscan® in conjunction with 125 surveyed ground control point targets, yielded a 6-mm pixel-size digital elevation model (DEM) for the test table grid region. This provided the ≤3 cm resolution in the topographic data to map in fine detail a suite of features related to the underground explosion: uplift, subsidence, surface fractures, and morphological change detection. The near-field grid region data collection resulted in a 2-cm pixel-size DEM, enabling mapping of a broader range of features related to the explosion, including: uplift and subsidence, rock fall, and slope sloughing. This study represents one of the first works to constrain, both temporally and spatially, explosion-related surface damage using a UAS photogrammetric platform; these data will help to advance the science of underground explosion detection.« less

14 CFR 398.7 - Timing of flights.

Code of Federal Regulations, 2012 CFR

2012-01-01

... reasonableness of the time in view of the purpose for which the local passengers are traveling. If travel is primarily to connect with other flights at the hub, local flight times should be designed to link with those.... To qualify as essential air service, flights must depart at reasonable times, considering the needs...

14 CFR 398.7 - Timing of flights.

Code of Federal Regulations, 2010 CFR

2010-01-01

... reasonableness of the time in view of the purpose for which the local passengers are traveling. If travel is primarily to connect with other flights at the hub, local flight times should be designed to link with those.... To qualify as essential air service, flights must depart at reasonable times, considering the needs...

14 CFR 398.7 - Timing of flights.

Code of Federal Regulations, 2011 CFR

2011-01-01

... reasonableness of the time in view of the purpose for which the local passengers are traveling. If travel is primarily to connect with other flights at the hub, local flight times should be designed to link with those.... To qualify as essential air service, flights must depart at reasonable times, considering the needs...

Fatigue-test acceleration with flight-by-flight loading and heating to simulate supersonic-transport operation

NASA Technical Reports Server (NTRS)

Imig, L. A.; Garrett, L. E.

1973-01-01

Possibilities for reducing fatigue-test time for supersonic-transport materials and structures were studied in tests with simulated flight-by-flight loading. In order to determine whether short-time tests were feasible, the results of accelerated tests (2 sec per flight) were compared with the results of real-time tests (96 min per flight). The effects of design mean stress, the stress range for ground-air-ground cycles, simulated thermal stress, the number of stress cycles in each flight, and salt corrosion were studied. The flight-by-flight stress sequences were applied to notched sheet specimens of Ti-8Al-1Mo-1V and Ti-6Al-4V titanium alloys. A linear cumulative-damage analysis accounted for large changes in stress range of the simulated flights but did not account for the differences between real-time and accelerated tests. The fatigue lives from accelerated tests were generally within a factor of two of the lives from real-time tests; thus, within the scope of the investigation, accelerated testing seems feasible.

40 CFR Table 9 to Subpart IIIii of... - Required Records for Work Practice Standards

Code of Federal Regulations, 2012 CFR

2012-07-01

... Mercury Cell Chlor-Alkali Plants Pt. 63, Subpt. IIIII, Table 9 Table 9 to Subpart IIIII of Part 63... other deficiency in a cell room floor, pillar, or beam that could cause liquid mercury to become trapped... hydrogen leak identified during an inspection required by Table 2 to this subpart or at any other time a...

40 CFR Table 9 to Subpart IIIii of... - Required Records for Work Practice Standards

Code of Federal Regulations, 2011 CFR

2011-07-01

... Mercury Cell Chlor-Alkali Plants Pt. 63, Subpt. IIIII, Table 9 Table 9 to Subpart IIIII of Part 63... other deficiency in a cell room floor, pillar, or beam that could cause liquid mercury to become trapped... hydrogen leak identified during an inspection required by Table 2 to this subpart or at any other time a...

Integrative Cardiac Health Project

DTIC Science & Technology

2013-03-01

insulin and leptin is presented below. Table 8 shows levels of insulin and leptin, as well as physiological measures, at baseline. Change over time in...Ornish participants and controls for insulin, leptin, and physiological measures is presented in Tables 9 and 10. Table 11 shows medications known...with other therapeutic or lifestyle regimens. 16 Table 8. Insulin, Leptin, and Physiological Measures at Baseline by Case/Control Status

26 CFR 1.181-0T - Table of contents (temporary).

Code of Federal Regulations, 2010 CFR

2010-04-01

... 26 Internal Revenue 3 2010-04-01 2010-04-01 false Table of contents (temporary). 1.181-0T Section...-0T Table of contents (temporary). This section lists the table of contents for §§ 1.181-1T through 1... deduction allowed. § 1.181-2TElection (temporary). (a) Time and manner of making election. (b) Election by...

26 CFR 1.41-0T - Table of contents (temporary).

Code of Federal Regulations, 2010 CFR

2010-04-01

... 26 Internal Revenue 1 2010-04-01 2010-04-01 true Table of contents (temporary). 1.41-0T Section 1... Credits Against Tax § 1.41-0T Table of contents (temporary). This section lists the table of contents for...) Election. (1) In general. (2) Time and manner of election. (3) Revocation. (4) Special rules for controlled...

Aerial photo volume tables for Douglas-fir in the Pacific Northwest.

Treesearch

Robert B. Pope

1961-01-01

The aerial photo volume tables in this report are tools to be used in obtaining better timber inventories. Volume estimates based on tables such as these, properly field checked, are generally cheaper than ground cruises of comparable accuracy. Photo volume tables also permit rough volume estimates to be made from aerial photos alone when limited time, bad weather, or...

Using Concurrent Cardiovascular Information to Augment Survival Time Data for Evaluating Orthostatic Tilt Test Performance

NASA Technical Reports Server (NTRS)

Feiveson, Alan H.; Fiedler, James; Lee, Stuart M. C.; Koslovsky, Matthew D.; Stenger, Michael B.; Platts, Steven H.

2018-01-01

Head-up tilt (HUT) tests often are used in research to measure orthostatic intolerance (OI) (inability to appropriately control blood pressure while upright) in clinical populations and otherwise healthy individuals after interventions. Post-space flight orthostatic intolerance is a well-known phenomenon, and countermeasures to its development has been an active area of research at NASA. In the NASA HUT protocol, subjects lie horizontally on an automatic tilt table for baseline measurements before being raised to 80deg head-up tilt for a defined period of time or until signs or symptoms of presyncope ensues (light-headedness, nausea, dizziness, sweating, weakness or fainting). Multiple measures are collected to evaluate the cardiovascular system's ability to respond appropriately to the orthostatic challenge. However if the intended duration of the HUT is short, the ability to detect changes in OI due to an intervention or its prevention by a countermeasure may be limited by a small number of failures to permit comparisons based on survival time alone. Thus, the time-trajectory of the cardiovascular data becomes an important additional source of information. In particular, we will show how various measures of trajectory variability can effectively augment survival analysis for the assessment of OI in a joint model when high censoring rates are present.

Development of an ion time-of-flight spectrometer for neutron depth profiling

NASA Astrophysics Data System (ADS)

Cetiner, Mustafa Sacit

Ion time-of-flight spectrometry techniques are investigated for applicability to neutron depth profiling. Time-of-flight techniques are used extensively in a wide range of scientific and technological applications including energy and mass spectroscopy. Neutron depth profiling is a near-surface analysis technique that gives concentration distribution versus depth for certain technologically important light elements. The technique uses thermal or sub-thermal neutrons to initiate (n, p) or (n, alpha) reactions. Concentration versus depth distribution is obtained by the transformation of the energy spectrum into depth distribution by using stopping force tables of the projectiles in the substrate, and by converting the number of counts into concentration using a standard sample of known dose value. Conventionally, neutron depth profiling measurements are based on charged particle spectrometry, which employs semiconductor detectors such as a surface barrier detector (SBD) and the associated electronics. Measurements with semiconductor detectors are affected by a number of broadening mechanisms, which result from the interactions between the projectile ion and the detector material as well as fluctuations in the signal generation process. These are inherent features of the detection mechanism that involve the semiconductor detectors and cannot be avoided. Ion time-of-flight spectrometry offers highly precise measurement capabilities, particularly for slow particles. For high-energy low-mass particles, measurement resolution tends to degrade with all other parameters fixed. The threshold for more precise ion energy measurements with respect to conventional techniques, such as direct energy measurement by a surface barrier detector, is directly related to the design and operating parameters of the device. Time-of-flight spectrometry involves correlated detection of two signals by a coincidence unit. In ion time-of-flight spectroscopy, the ion generates the primary input signal. Without loss of generality, the secondary signal is obtained by the passage of the ion through a thin carbon foil, which produces ion-induced secondary electron emission (IISEE). The time-of-flight spectrometer physically acts as an ion/electron separator. The electrons that enter the active volume of the spectrometer are transported onto the microchannel plate detector to generate the secondary signal. The electron optics can be designed in variety of ways depending on the nature of the measurement and physical requirements. Two ion time-of-flight spectrometer designs are introduced: the parallel electric and magnetic (PEM) field spectrometer and the cross electric and magnetic (CEM) field spectrometer. The CEM field spectrometers have been extensively used in a wide range of applications where precise mass differentiation is required. The PEM field spectrometers have lately found interest in mass spectroscopy applications. The application of the PEM field spectrometer for energy measurements is a novel approach. The PEM field spectrometer used in the measurements employs axial electric and magnetic fields along the nominal direction of the incident ion. The secondary electrons are created by a thin carbon foil on the entrance disk and transported on the microchannel plate that faces the carbon foil. The initial angular distribution of the secondary electrons has virtually no effect on the transport time of the secondary electrons from the surface of the carbon foil to the electron microchannel plate detector. Therefore, the PEM field spectrometer can offer high-resolution energy measurement for relatively lower electric fields. The measurements with the PEM field spectrometer were made with the Tandem linear particle accelerator at the IBM T. J. Watson Research Center at Yorktown Heights, NY. The CEM field spectrometer developed for the thesis employs axial electric field along the nominal direction of the ion, and has perpendicular magnetic field. As the electric field accelerates and then decelerates the emitted secondary electron beam, the magnetic field steers the beam away from the source and focuses it onto the electron microchannel plate detector. The initial momentum distribution of the electron beam is observed to have profound effect on the electron transport time. Hence, the CEM field spectrometer measurements suffer more from spectral broadening at similar operating parameters. The CEM field spectrometer measurements were obtained with a 210Po alpha source at the Penn State Radiation Science and Engineering Center, University Park, PA. Although the PEM field spectrometer suffers less from electron transport time dispersion, the CEM field spectrometer is more suited for application to neutron depth profiling. The multiple small-diameter apertures used in the PEM field configuration considerably reduces the geometric efficiency of the spectrometer. Most of the neutron depth profiling measurements, where isotropic emission of charged particles is observed, have relatively low count rates; hence, high detection efficiency is essential.

Stand Table Construction from Relascope Plots.

Treesearch

Charles B. Briscoe

1957-01-01

When timber is cruised using relascope, basal area and volume figures are obtained without constructing a stand table, through the use of appropriate conversion factors. Although this saving in time is very desirable for most inventories, certain management purposes require stand tables.

Times and locations of explosions; U.S. Geological Survey 1962 field season

USGS Publications Warehouse

Roller, John C.

1962-01-01

The U.S. Geological Survey detonated 86 large charges of chemical explosives in the western United States from 6 June to 9 August 1962, in a study of crustal structure in the western United States. This Technical Letter consists of two tables containing information about these explosions. Table I gives a brief geographical description of the shotpoints, and Table II gives the date, time, location, charge size, surface elevation, and some general information about the shots. In the Remarks column (Table II), the configuration and depth of most of the charges are given. This part of the table is not complete, as some of this information has not yet been compiled. Three types of explosives were used in the program. These were: Nitramon WW, a carbo-nitrate blasting agent; Composition B, a mixture of RDX and TNT; and Tovex-Gel, a non-nitroglycerin blasting slurry. The loading, firing, and surveying was done by United ElectroDynamics, Inc., of Pasadena, California. The timing was done by the U.S. Geological Survey.

Erratum: "A Smaller Radius for the Transiting Exoplanet WASP-10b" (2009, ApJ, 692, L100)

NASA Astrophysics Data System (ADS)

Johnson, John Asher; Winn, Joshua N.; Cabrera, Nicole E.; Carter, Joshua A.

2010-03-01

We have identified an error in our Heliocentric Julian Dates (HJDs) of observation caused by incorrect input to the code used to convert from JD to HJD. The times in Table 1 have been corrected by adding 0.006382 day to each entry in the original Column 1. Similarly, the measured mid-transit time in Table 2 has been changed to Tc = 2454664.037295. We also note that the header in Column 1 of Table 1 is incorrect. The label should read HJD, rather than BJD. The updated Tables 1 and 2 have been included herein. This error has no impact on our main conclusions. We thank Pedro Valdes Sada and Gracjan Maciejewski for pointing out the incorrect mid-transit time.

Time-frequency energy density precipitation method for time-of-flight extraction of narrowband Lamb wave detection signals

DOE Office of Scientific and Technical Information (OSTI.GOV)

Zhang, Y., E-mail: thuzhangyu@foxmail.com; Huang, S. L., E-mail: huangsling@tsinghua.edu.cn; Wang, S.

The time-of-flight of the Lamb wave provides an important basis for defect evaluation in metal plates and is the input signal for Lamb wave tomographic imaging. However, the time-of-flight can be difficult to acquire because of the Lamb wave dispersion characteristics. This work proposes a time-frequency energy density precipitation method to accurately extract the time-of-flight of narrowband Lamb wave detection signals in metal plates. In the proposed method, a discrete short-time Fourier transform is performed on the narrowband Lamb wave detection signals to obtain the corresponding discrete time-frequency energy density distribution. The energy density values at the center frequency formore » all discrete time points are then calculated by linear interpolation. Next, the time-domain energy density curve focused on that center frequency is precipitated by least squares fitting of the calculated energy density values. Finally, the peak times of the energy density curve obtained relative to the initial pulse signal are extracted as the time-of-flight for the narrowband Lamb wave detection signals. An experimental platform is established for time-of-flight extraction of narrowband Lamb wave detection signals, and sensitivity analysis of the proposed time-frequency energy density precipitation method is performed in terms of propagation distance, dispersion characteristics, center frequency, and plate thickness. For comparison, the widely used Hilbert–Huang transform method is also implemented for time-of-flight extraction. The results show that the time-frequency energy density precipitation method can accurately extract the time-of-flight with relative error of <1% and thus can act as a universal time-of-flight extraction method for narrowband Lamb wave detection signals.« less

Time-frequency energy density precipitation method for time-of-flight extraction of narrowband Lamb wave detection signals.

PubMed

Zhang, Y; Huang, S L; Wang, S; Zhao, W

2016-05-01

The time-of-flight of the Lamb wave provides an important basis for defect evaluation in metal plates and is the input signal for Lamb wave tomographic imaging. However, the time-of-flight can be difficult to acquire because of the Lamb wave dispersion characteristics. This work proposes a time-frequency energy density precipitation method to accurately extract the time-of-flight of narrowband Lamb wave detection signals in metal plates. In the proposed method, a discrete short-time Fourier transform is performed on the narrowband Lamb wave detection signals to obtain the corresponding discrete time-frequency energy density distribution. The energy density values at the center frequency for all discrete time points are then calculated by linear interpolation. Next, the time-domain energy density curve focused on that center frequency is precipitated by least squares fitting of the calculated energy density values. Finally, the peak times of the energy density curve obtained relative to the initial pulse signal are extracted as the time-of-flight for the narrowband Lamb wave detection signals. An experimental platform is established for time-of-flight extraction of narrowband Lamb wave detection signals, and sensitivity analysis of the proposed time-frequency energy density precipitation method is performed in terms of propagation distance, dispersion characteristics, center frequency, and plate thickness. For comparison, the widely used Hilbert-Huang transform method is also implemented for time-of-flight extraction. The results show that the time-frequency energy density precipitation method can accurately extract the time-of-flight with relative error of <1% and thus can act as a universal time-of-flight extraction method for narrowband Lamb wave detection signals.

Application of XML to Journal Table Archiving

NASA Astrophysics Data System (ADS)

Shaya, E. J.; Blackwell, J. H.; Gass, J. E.; Kargatis, V. E.; Schneider, G. L.; Weiland, J. L.; Borne, K. D.; White, R. A.; Cheung, C. Y.

1998-12-01

The Astronomical Data Center (ADC) at the NASA Goddard Space Flight Center is a major archive for machine-readable astronomical data tables. Many ADC tables are derived from published journal articles. Article tables are reformatted to be machine-readable and documentation is crafted to facilitate proper reuse by researchers. The recent switch of journals to web based electronic format has resulted in the generation of large amounts of tabular data that could be captured into machine-readable archive format at fairly low cost. The large data flow of the tables from all major North American astronomical journals (a factor of 100 greater than the present rate at the ADC) necessitates the development of rigorous standards for the exchange of data between researchers, publishers, and the archives. We have selected a suitable markup language that can fully describe the large variety of astronomical information contained in ADC tables. The eXtensible Markup Language XML is a powerful internet-ready documentation format for data. It provides a precise and clear data description language that is both machine- and human-readable. It is rapidly becoming the standard format for business and information transactions on the internet and it is an ideal common metadata exchange format. By labelling, or "marking up", all elements of the information content, documents are created that computers can easily parse. An XML archive can easily and automatically be maintained, ingested into standard databases or custom software, and even totally restructured whenever necessary. Structuring astronomical data into XML format will enable efficient and focused search capabilities via off-the-shelf software. The ADC is investigating XML's expanded hyperlinking power to enhance connectivity within the ADC data/metadata and developing XSL display scripts to enhance display of astronomical data. The ADC XML Definition Type Document can be viewed at http://messier.gsfc.nasa.gov/dtdhtml/DTD-TREE.html

Quantification of the Effect of Shuttling on Computed Tomography Perfusion Parameters by Investigation of Aortic Inputs on Different Table Positions From Shuttle-Mode Scans of Lung and Liver Tumors.

PubMed

Ghosh, Payel; Chandler, Adam G; Hobbs, Brian P; Sun, Jia; Rong, John; Hong, David; Subbiah, Vivek; Janku, Filip; Naing, Aung; Hwu, Wen-Jen; Ng, Chaan S

The aim of this study was to quantify the effect of shuttling on computed tomography perfusion (CTp) parameters derived from shuttle-mode body CT images using aortic inputs from different table positions. Axial shuttle-mode CT scans were acquired from 6 patients (10 phases, 2 nonoverlapping table positions 1.4 seconds apart) after contrast agent administration. Artifacts resulting from the shuttling motion were corrected with nonrigid registration before computing CTp maps from 4 aortic levels chosen from the most superior and inferior slices of each table position scan. The effect of shuttling on CTp parameters was estimated by mean differences in mappings obtained from aortic inputs in different table positions. Shuttling effect was also quantified using 95% limits of agreement of CTp parameter differences within-table and between-table aortic positions from the interaortic mean CTp values. Blood flow, permeability surface, and hepatic arterial fraction differences were insignificant (P > 0.05) for both within-table and between-table comparisons. The 95% limits of agreement for within-table blood volume (BV) value deviations obtained from lung tumor regions were less than 4.7% (P = 0.18) compared with less than 12.2% (P = 0.003) for between-table BV value deviations. The 95% limits of agreement of within-table deviations for liver tumor regions were less than 1.9% (P = 0.55) for BV and less than 3.2% (P = 0.23) for mean transit time, whereas between-table BV and mean transit time deviations were less than 11.7% (P < 0.01) and less than 14.6% (P < 0.01), respectively. Values for normal liver tissue regions were concordant. Computed tomography perfusion parameters acquired from aortic levels within-table positions generally yielded higher agreement than mappings obtained from aortic levels between-table positions indicating differences due to shuttling effect.

IMS/Satellite Situation Center report. Predicted orbit plots for IMP-H-1976. [Explorer 47 satellite

NASA Technical Reports Server (NTRS)

1975-01-01

Predicted orbit plots are shown in three projections. The time period covered by each set of projections is 12 days 6 hours, corresponding approximately to the period of IMP-H satellite. The three coordinate systems used are the Geocentric Solar Ecliptic system (GSE), the Geocentric Solar Magnetospheric system (GSM), and the Solar Magnetic system (SM). For each of the three projections, time ticks and codes are given on the satellite trajectories. The codes are interpreted in the table at the base of each plot. Time is given in the table as year/day/decimal hour. The total time covered by each plot is shown at the bottom of each table. An additional variable is given in the table for each time tick. For the GSM and SM projection this variable is the geocentric distance to the satellite in earth radii, and for the GSE projection the variable is satellite ecliptic latitude in degrees.

40 CFR Table 3 to Subpart Ffff of... - Model Rule-Operating Limits for Incinerators and Wet Scrubbers

Code of Federal Regulations, 2012 CFR

2012-07-01

... Emission Guidelines and Compliance Times for Other Solid Waste Incineration Units That Commenced Construction On or Before December 9, 2004 Pt. 60, Subpt. FFFF, Table 3 Table 3 to Subpart FFFF of Part 60...

40 CFR Table 3 to Subpart Ffff of... - Model Rule-Operating Limits for Incinerators and Wet Scrubbers

Code of Federal Regulations, 2013 CFR

2013-07-01

... Emission Guidelines and Compliance Times for Other Solid Waste Incineration Units That Commenced Construction On or Before December 9, 2004 Pt. 60, Subpt. FFFF, Table 3 Table 3 to Subpart FFFF of Part 60...

40 CFR Table 3 to Subpart Ffff of... - Model Rule-Operating Limits for Incinerators and Wet Scrubbers

Code of Federal Regulations, 2014 CFR

2014-07-01

... Emission Guidelines and Compliance Times for Other Solid Waste Incineration Units That Commenced Construction On or Before December 9, 2004 Pt. 60, Subpt. FFFF, Table 3 Table 3 to Subpart FFFF of Part 60...

14 CFR 117.11 - Flight time limitation.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitation. 117.11 Section 117...) AIR CARRIERS AND OPERATORS FOR COMPENSATION OR HIRE: CERTIFICATION AND OPERATIONS FLIGHT AND DUTY LIMITATIONS AND REST REQUIREMENTS: FLIGHTCREW MEMBERS (EFF. 1-4-14) § 117.11 Flight time limitation. (a) No...

14 CFR 121.515 - Flight time limitations: All airmen: airplanes.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitations: All airmen: airplanes. 121.515 Section 121.515 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Operations § 121.515 Flight time limitations: All airmen: airplanes. No airman may be aloft as a flight...

14 CFR 121.515 - Flight time limitations: All airmen: airplanes.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight time limitations: All airmen: airplanes. 121.515 Section 121.515 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Operations § 121.515 Flight time limitations: All airmen: airplanes. No airman may be aloft as a flight...

14 CFR 121.515 - Flight time limitations: All airmen: airplanes.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight time limitations: All airmen: airplanes. 121.515 Section 121.515 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Operations § 121.515 Flight time limitations: All airmen: airplanes. No airman may be aloft as a flight...

14 CFR 121.515 - Flight time limitations: All airmen: airplanes.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight time limitations: All airmen: airplanes. 121.515 Section 121.515 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Operations § 121.515 Flight time limitations: All airmen: airplanes. No airman may be aloft as a flight...

14 CFR 121.515 - Flight time limitations: All airmen: airplanes.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: All airmen: airplanes. 121.515 Section 121.515 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... Operations § 121.515 Flight time limitations: All airmen: airplanes. No airman may be aloft as a flight...

Isobar Separation in a Multiple-Reflection Time-of-Flight Mass Spectrometer by Mass-Selective Re-Trapping.

PubMed

Dickel, Timo; Plaß, Wolfgang R; Lippert, Wayne; Lang, Johannes; Yavor, Mikhail I; Geissel, Hans; Scheidenberger, Christoph

2017-06-01

A novel method for (ultra-)high-resolution spatial mass separation in time-of-flight mass spectrometers is presented. Ions are injected into a time-of-flight analyzer from a radio frequency (rf) trap, dispersed in time-of-flight according to their mass-to-charge ratios and then re-trapped dynamically in the same rf trap. This re-trapping technique is highly mass-selective and after sufficiently long flight times can provide even isobaric separation. A theoretical treatment of the method is presented and the conditions for optimum performance of the method are derived. The method has been implemented in a multiple-reflection time-of-flight mass spectrometer and mass separation powers (FWHM) in excess of 70,000, and re-trapping efficiencies of up to 35% have been obtained for the protonated molecular ion of caffeine. The isobars glutamine and lysine (relative mass difference of 1/4000) have been separated after a flight time of 0.2 ms only. Higher mass separation powers can be achieved using longer flight times. The method will have important applications, including isobar separation in nuclear physics and (ultra-)high-resolution precursor ion selection in multiple-stage tandem mass spectrometry. Graphical Abstract ᅟ.

Isobar Separation in a Multiple-Reflection Time-of-Flight Mass Spectrometer by Mass-Selective Re-Trapping

NASA Astrophysics Data System (ADS)

Dickel, Timo; Plaß, Wolfgang R.; Lippert, Wayne; Lang, Johannes; Yavor, Mikhail I.; Geissel, Hans; Scheidenberger, Christoph

2017-06-01

A novel method for (ultra-)high-resolution spatial mass separation in time-of-flight mass spectrometers is presented. Ions are injected into a time-of-flight analyzer from a radio frequency (rf) trap, dispersed in time-of-flight according to their mass-to-charge ratios and then re-trapped dynamically in the same rf trap. This re-trapping technique is highly mass-selective and after sufficiently long flight times can provide even isobaric separation. A theoretical treatment of the method is presented and the conditions for optimum performance of the method are derived. The method has been implemented in a multiple-reflection time-of-flight mass spectrometer and mass separation powers (FWHM) in excess of 70,000, and re-trapping efficiencies of up to 35% have been obtained for the protonated molecular ion of caffeine. The isobars glutamine and lysine (relative mass difference of 1/4000) have been separated after a flight time of 0.2 ms only. Higher mass separation powers can be achieved using longer flight times. The method will have important applications, including isobar separation in nuclear physics and (ultra-)high-resolution precursor ion selection in multiple-stage tandem mass spectrometry. [Figure not available: see fulltext.

Conversion tables for use with the National Fire-Danger Rating System in the Intermountain area

Treesearch

Dwight S. Stockstad; Richard J. Barney

1964-01-01

Two tables prepared for use with the National Fire-Danger Rating System replace 10 tables previously used with the Model-8 Fire-Danger Rating System. They provide for the conversion of Spread Index values at various altitudes, aspects, and times of day. A rate of spread table facilitates converting Spread Index values to chains per hour of perimeter increase for...

Liquid Motion in a Rotating Tank Experiment (LME)

NASA Technical Reports Server (NTRS)

Deffenbaugh, D. M.; Dodge, F. T.; Green, S. T.

1998-01-01

The Liquid Motion Experiment (LME), which flew on STS 84 in May 1997, was an investigation of liquid motions in spinning, nutating tanks. LME was designed to quantify the effects of such liquid motions on the stability of spinning spacecraft, which are known to be adversely affected by the energy dissipated by the liquid motions. The LME hardware was essentially a spin table which could be forced to nutate at specified frequencies at a constant cone angle, independently of the spin rate. Cylindrical and spherical test tanks, partially filled with liquids of different viscosities, were located at the periphery of the spin table to simulate a spacecraft with off-axis propellant tanks; one set of tanks contained generic propellant management devices (PMDs). The primary quantitative data from the flight tests were the liquid-induced torques exerted on the tanks about radial and tangential axes through the center of the tank. Visual recordings of the liquid oscillations also provided qualitative information. The flight program incorporated two types of tests: sine sweep tests, in which the spin rate was held constant and the nutation frequency varied over a wide range; and sine dwell test, in which both the spin rate and the nutation frequency were held constant. The sine sweep tests were meant to investigate all the prominent liquid resonant oscillations and the damping of the resonances, and the sine dwell tests were meant to quantify the viscous energy dissipation rate of the liquid oscillations for steady state conditions. The LME flight data were compared to analytical results obtained from two companion IR&D programs at Southwest Research Institute. The comparisons indicated that the models predicted the observed liquid resonances, damping, and energy dissipation rates for many test conditions but not for all. It was concluded that improved models and CFD simulations are needed to resolve the differences. This work is ongoing under a current IR&D program.

Qualification of the Tropical Rainfall Measuring Mission Solar Array Deployment System

NASA Technical Reports Server (NTRS)

Lawrence, Jon

1998-01-01

The Tropical Rainfall Measuring Mission (TRMM) solar arrays are placed into orbital configuration by a complex deployment system. Its two wings each comprise twin seven square solar panels located by a twelve foot articulated boom. The four spring-driven hinge lines per wing are rate-limited by viscous dampers. The wings are stowed against the spacecraft kinematically, and released by five pyrotechnically-actuated mechanisms. Since deployment failure would be catastrophic, a total of 17 deployment tests were completed to qualify the system for the worst cast launch environment. This successful testing culminated in the flawless deployment of the solar arrays on orbit, 15 minutes after launch in November 1997. The custom gravity negation system used to perform deployment testing is modular to allow its setup in several locations, including the launch site in Japan. Both platform and height can be varied, to meet the requirements of the test configuration and the test facility. Its air pad floatation system meets tight packaging requirements, allowing installation while stowed against the spacecraft without breaking any flight interfaces, and avoiding interference during motion. This system was designed concurrently with the deployment system, to facilitate its installation, to aid in the integration of the flight system to the spacecraft, while demonstrating deployment capabilities. Critical parameters for successful testing were alignment of deployment axes and tables to gravity, alignment of table seams to minimize discontinuities, and minimizing pressure drops in the air supply system. Orbital performance was similar to that predicted by ground testing.

Time Manager Software for a Flight Processor

NASA Technical Reports Server (NTRS)

Zoerne, Roger

2012-01-01

Data analysis is a process of inspecting, cleaning, transforming, and modeling data to highlight useful information and suggest conclusions. Accurate timestamps and a timeline of vehicle events are needed to analyze flight data. By moving the timekeeping to the flight processor, there is no longer a need for a redundant time source. If each flight processor is initially synchronized to GPS, they can freewheel and maintain a fairly accurate time throughout the flight with no additional GPS time messages received. How ever, additional GPS time messages will ensure an even greater accuracy. When a timestamp is required, a gettime function is called that immediately reads the time-base register.

Report on computation of repetitive hyperbaric-hypobaric decompression tables

NASA Technical Reports Server (NTRS)

Edel, P. O.

1975-01-01

The tables were constructed specifically for NASA's simulated weightlessness training program; they provide for 8 depth ranges covering depths from 7 to 47 FSW, with exposure times of 15 to 360 minutes. These tables were based up on an 8 compartment model using tissue half-time values of 5 to 360 minutes and Workmanline M-values for control of the decompression obligation resulting from hyperbaric exposures. Supersaturation ratios of 1.55:1 to 2:1 were used for control of ascents to altitude following such repetitive dives. Adequacy of the method and the resultant tables were determined in light of past experience with decompression involving hyperbaric-hypobaric interfaces in human exposures. Using these criteria, the method showed conformity with empirically determined values. In areas where a discrepancy existed, the tables would err in the direction of safety.

Table of interplanar spacings for crystal-structure determinations by X-ray diffraction with molybdenum, copper, cobalt, iron, and chromium radiations

NASA Technical Reports Server (NTRS)

Kittel, J Howard

1945-01-01

For a simple diffraction pattern, the time required to calculate interplanar distances from measurements of the pattern is not excessive. If more than a few lines are present, however, or if several patterns are to be studied, it is very advantageous to have available a table giving interplanar spacings directly in terms of the linear measurements made on the film of the lines appearing on the diffraction pattern. The preparation of the table given here was undertaken when the expansion of research activities involving X-ray diffraction techniques indicated that such a table would greatly decrease the time required to analyze diffraction patterns. The table was prepared for use with K alpha(sub 1) radiation from the following target materials: molybdenum, copper, cobalt, iron, and chromium.

Delay banking for air traffic management

NASA Technical Reports Server (NTRS)

Green, Steven M. (Inventor)

2007-01-01

A method and associated system for time delay banking for aircraft arrival time, aircraft departure time and/or en route flight position. The delay credit value for a given flight may decrease with passage of time and may be transferred to or traded with other flights having the same or a different user (airline owner or operator). The delay credit value for a given aircraft flight depends upon an initial delay credit value, which is determined by a central system and depends upon one or more other flight characteristics. Optionally, the delay credit value decreases with passage of time. Optionally, a transaction cost is assessed against a delay credit value that is used on behalf of another flight with the same user or is traded with a different user.

Flight of the Chinese white pine beetle (Coleoptera: Scolytidae) in relation to sex, body weight and energy reserve.

PubMed

Chen, H; Li, Z; Bu, S H; Tian, Z Q

2011-02-01

The flight distance, flight time and individual flight activities of males and females of Dendroctonus armandi were recorded during 96-h flight trials using a flight mill system. The body weight, glucose, glycogen and lipid content of four treatments (naturally emerged, starved, phloem-fed and water-fed) were compared among pre-flight, post-flight and unflown controls. There was no significant difference between males and females in total flight distance and flight time in a given 24-h period. The flight distance and flight time of females showed a significant linear decline as the tethered flying continued, but the sustained flight ability of females was better than that of males. The females had higher glycogen and lipid content than the males; however, there was no significant difference between both sexes in glucose content. Water-feeding and phloem-feeding had significant effects on longevity, survival days and flight potential of D. armandi, which resulted in longer feeding days, poorer flight potential and lower energy substrate content. Our results demonstrate that flight distances in general do not differ between water-fed and starved individuals, whereas phloem-fed females and males fly better than water-fed and starved individuals.

Track and mode controller (TMC): a software executive for a high-altitude pointing and tracking experiment

NASA Astrophysics Data System (ADS)

Michnovicz, Michael R.

1997-06-01

A real-time executive has been implemented to control a high altitude pointing and tracking experiment. The track and mode controller (TMC) implements a table driven design, in which the track mode logic for a tracking mission is defined within a state transition diagram (STD). THe STD is implemented as a state transition table in the TMC software. Status Events trigger the state transitions in the STD. Each state, as it is entered, causes a number of processes to be activated within the system. As these processes propagate through the system, the status of key processes are monitored by the TMC, allowing further transitions within the STD. This architecture is implemented in real-time, using the vxWorks operating system. VxWorks message queues allow communication of status events from the Event Monitor task to the STD task. Process commands are propagated to the rest of the system processors by means of the SCRAMNet shared memory network. The system mode logic contained in the STD will autonomously sequence in acquisition, tracking and pointing system through an entire engagement sequence, starting with target detection and ending with aimpoint maintenance. Simulation results and lab test results will be presented to verify the mode controller. In addition to implementing the system mode logic with the STD, the TMC can process prerecorded time sequences of commands required during startup operations. It can also process single commands from the system operator. In this paper, the author presents (1) an overview, in which he describes the TMC architecture, the relationship of an end-to-end simulation to the flight software and the laboratory testing environment, (2) implementation details, including information on the vxWorks message queues and the SCRAMNet shared memory network, (3) simulation results and lab test results which verify the mode controller, and (4) plans for the future, specifically as to how this executive will expedite transition to a fully functional system.

Model-Based Systems Engineering Approach to Managing Mass Margin

NASA Technical Reports Server (NTRS)

Chung, Seung H.; Bayer, Todd J.; Cole, Bjorn; Cooke, Brian; Dekens, Frank; Delp, Christopher; Lam, Doris

2012-01-01

When designing a flight system from concept through implementation, one of the fundamental systems engineering tasks ismanaging the mass margin and a mass equipment list (MEL) of the flight system. While generating a MEL and computing a mass margin is conceptually a trivial task, maintaining consistent and correct MELs and mass margins can be challenging due to the current practices of maintaining duplicate information in various forms, such as diagrams and tables, and in various media, such as files and emails. We have overcome this challenge through a model-based systems engineering (MBSE) approach within which we allow only a single-source-of-truth. In this paper we describe the modeling patternsused to capture the single-source-of-truth and the views that have been developed for the Europa Habitability Mission (EHM) project, a mission concept study, at the Jet Propulsion Laboratory (JPL).

Cleaning Genesis Mission Payload for Flight with Ultra-Pure Water and Assembly in ISO Class 4 Environment

NASA Technical Reports Server (NTRS)

Allton, Judith H.

2012-01-01

Genesis mission to capture and return to Earth solar wind samples had very stringent contamination control requirements in order to distinguish the solar atoms from terrestrial ones. Genesis mission goals were to measure solar composition for most of the periodic table, so great care was taken to avoid particulate contamination. Since the number 1 and 2 science goals were to determine the oxygen and nitrogen isotopic composition, organic contamination was minimized by tightly controlling offgassing. The total amount of solar material captured in two years is about 400 micrograms spread across one sq m. The contamination limit requirement for each of C, N, and O was <1015 atoms/sq cm. For carbon, this is equivalent to 10 ng/cm2. Extreme vigilance was used in pre-paring Genesis collectors and cleaning hardware for flight. Surface contamination on polished silicon wafers, measured in Genesis laboratory is approximately 10 ng/sq cm.

EnviroNET: An online environmental interactions resource

NASA Technical Reports Server (NTRS)

Lauriente, Michael

1991-01-01

EnviroNET is a centralized depository for technical information on environmentally induced interactions likely to be encountered by spacecraft in both low-altitude and high-altitude orbits. It provides a user-friendly, menu-driven format on networks that are connected globally and is available 24 hours a day - every day. The service pools space data collected over the years by NASA, USAF, other government research facilities, industry, universities, and the European Space Agency. This information contains text, tables and over one hundred high resolution figures and graphs based on empirical data. These graphics can be accessed while still in the chapters, making it easy to flip from text to graphics and back. Interactive graphics programs are also available on space debris, the neutral atmosphere, magnetic field, and ionosphere. EnviroNET can help designers meet tough environmental flight criteria before committing to flight hardware built for experiments, instrumentation, or payloads.

Benchmarking in Universities: League Tables Revisited

ERIC Educational Resources Information Center

Turner, David

2005-01-01

This paper examines the practice of benchmarking universities using a "league table" approach. Taking the example of the "Sunday Times University League Table", the author reanalyses the descriptive data on UK universities. Using a linear programming technique, data envelope analysis (DEA), the author uses the re-analysis to…

Two Meter Flight Path - Time of Flight Positron Annihilation Induced Auger Electron Spectrometer

NASA Astrophysics Data System (ADS)

Mukherjee, S.; Shastry, K.; Maddox, W.; Weiss, A. H.

2008-03-01

Details of the design and construction of a new time of flight positron annihilation induced Auger electron (TOF-PAES) spectrometer are presented. The new spectrometer will be equipped with a 2 meter long ``TOF'' tube that can be biased at a potential different from that of the sample in order to increase or decrease the kinetic energy of the electrons traveling through the tube. The time of flight will be determined from timing signals obtained from the detection of the annihilation gamma (signaling the start of the flight) and detection of the annihilation induced Auger electron at the end of the 2 meter flight path (signaling the end of the flight). The 2 meter long flight path is a factor of two longer than used in previous TOF-PAES systems. The longer flight path can be expected to result in a fractional energy width: delta E/ E that is .5ex1 -.1em/ -.15em.25ex2 as large as the current UTA lab based TOF-PAES spectrometer.

Real-Time Onboard Global Nonlinear Aerodynamic Modeling from Flight Data

NASA Technical Reports Server (NTRS)

Brandon, Jay M.; Morelli, Eugene A.

2014-01-01

Flight test and modeling techniques were developed to accurately identify global nonlinear aerodynamic models onboard an aircraft. The techniques were developed and demonstrated during piloted flight testing of an Aermacchi MB-326M Impala jet aircraft. Advanced piloting techniques and nonlinear modeling techniques based on fuzzy logic and multivariate orthogonal function methods were implemented with efficient onboard calculations and flight operations to achieve real-time maneuver monitoring and analysis, and near-real-time global nonlinear aerodynamic modeling and prediction validation testing in flight. Results demonstrated that global nonlinear aerodynamic models for a large portion of the flight envelope were identified rapidly and accurately using piloted flight test maneuvers during a single flight, with the final identified and validated models available before the aircraft landed.

Analysis of underlying and multiple-cause mortality data: the life table methods.

PubMed

Moussa, M A

1987-02-01

The stochastic compartment model concepts are employed to analyse and construct complete and abbreviated total mortality life tables, multiple-decrement life tables for a disease, under the underlying and pattern-of-failure definitions of mortality risk, cause-elimination life tables, cause-elimination effects on saved population through the gain in life expectancy as a consequence of eliminating the mortality risk, cause-delay life tables designed to translate the clinically observed increase in survival time as the population gain in life expectancy that would occur if a treatment protocol was made available to the general population and life tables for disease dependency in multiple-cause data.

14 CFR 417.219 - Data loss flight time and planned safe flight state analyses.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Data loss flight time and planned safe flight state analyses. 417.219 Section 417.219 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION... flight to a condition where the launch vehicle's hazardous debris impact dispersion extends to any...

14 CFR 417.219 - Data loss flight time and planned safe flight state analyses.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Data loss flight time and planned safe flight state analyses. 417.219 Section 417.219 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION... flight to a condition where the launch vehicle's hazardous debris impact dispersion extends to any...

14 CFR 417.219 - Data loss flight time and planned safe flight state analyses.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Data loss flight time and planned safe flight state analyses. 417.219 Section 417.219 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION... flight to a condition where the launch vehicle's hazardous debris impact dispersion extends to any...

14 CFR 417.219 - Data loss flight time and planned safe flight state analyses.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Data loss flight time and planned safe flight state analyses. 417.219 Section 417.219 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION... flight to a condition where the launch vehicle's hazardous debris impact dispersion extends to any...

14 CFR 417.219 - Data loss flight time and planned safe flight state analyses.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Data loss flight time and planned safe flight state analyses. 417.219 Section 417.219 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION... flight to a condition where the launch vehicle's hazardous debris impact dispersion extends to any...

Strategies for Proximal Femoral Nailing of Unstable Intertrochanteric Fractures: Lateral Decubitus Position or Traction Table.

PubMed

Sonmez, Mesut Mehmet; Camur, Savas; Erturer, Erden; Ugurlar, Meric; Kara, Adnan; Ozturk, Irfan

2017-03-01

The aim of this prospective randomized study was to compare the traction table and lateral decubitus position techniques in the management of unstable intertrochanteric fractures. Eighty-two patients with unstable intertrochanteric fractures between 2011 and 2013 were included in this study. All patients were treated surgically with the Proximal Femoral Nail Antirotation implant (DePuy Synthes). Patients were randomized to undergo the procedure in the lateral decubitus position (42 patients) or with the use of a traction table (40 patients). Patients whose procedure was not performed entirely with a semi-invasive method or who required the use of additional fixation materials, such as cables, were excluded from the study. The groups were compared on the basis of the setup time, surgical time, fluoroscopic exposure time, tip-to-apex distance, collodiaphyseal angle, and modified Baumgaertner criteria for radiologic reduction. The setup time, surgical time, and fluoroscopic exposure time were lower and the differences were statistically significant in the lateral decubitus group compared with the traction table group. The collodiaphyseal angles were significantly different between the groups in favor of the lateral decubitus method. The tip-to-apex distance and the classification of reduction according to the modified Baumgaertner criteria did not demonstrate a statistically significant difference between the groups. The lateral decubitus position is used for most open procedures of the hip. We found that this position facilitates exposure for the surgical treatment of unstable intertrochanteric fractures and has advantages over the traction table in terms of set up time, surgical time and fluoroscopic exposure time.

A Simple Probabilistic Model for Estimating the Risk of Standard Air Dives

DTIC Science & Technology

2004-12-01

Decompression Models Table Al. Decompression Table Based on the StandAir Model and Comparison with the VVaI-1 8 Algorithm. A-l-A-4 Table A2. The VVaI-1 8...cannot be as strong as might be desired - especially for dives with long TDTs. Comparisons of the positions of the dive-outcome symbols with the... comparisons for several depth/bottom-time combinations. The three left-hand panels, for dives with short bottom times, show that the crossover point

Development of an Oculometer Data Collection Subsystem.

DTIC Science & Technology

1982-12-01

number of time increments between 50 and 183 . "Data gone" is a data sample with an instrument number of zero and the total number of time increments...greater than 183 . Table 2 shows the organization of the information in the data tables. Table 3 shows the format of each of the rows. A ’$’ in front of a...APPENDIX A Memory FFFF SYM-1 Operating System Locations EFFF FF80 Resident Assembler/Editor DFFF CFFF BFFF Resident Assembler/Editor AFFF Disk controller

High Pulsed Power, Self Excited Magnetohydrodynamic Power Generation Systems

DTIC Science & Technology

1985-12-27

MHD GENERATOR OUTPUT, CASE G-2 86 TABLE 25:TEMPERATURE IN A SEMI -INFINITE COPPER SLAB EXPOSED TO GAS AT t=O 89 TABLE 26:TIME FOR GAS-Cu INTERFACE TO...REACH 2000 0 F, & BACK SURFACE TEMPERATURE AT THIS TIME,FOR A SEMI -INFINITE SLAB OF GIVEN THICKNESS,d. 89 TABLE 27: CONVECTIVE HEATING OF THE MHD...magnetic field for the explosive MHD generator. A dc room temperature magnet requires too much pow- er for operation at the 5 Tesla fields required by

Visually Lossless Data Compression for Real-Time Frame/Pushbroom Space Science Imagers

NASA Technical Reports Server (NTRS)

Yeh, Pen-Shu; Venbrux, Jack; Bhatia, Prakash; Miller, Warner H.

2000-01-01

A visually lossless data compression technique is currently being developed for space science applications under the requirement of high-speed push-broom scanning. The technique is also applicable to frame based imaging and is error-resilient in that error propagation is contained within a few scan lines. The algorithm is based on a block transform of a hybrid of modulated lapped transform (MLT) and discrete cosine transform (DCT), or a 2-dimensional lapped transform, followed by bit-plane encoding; this combination results in an embedded bit string with exactly the desirable compression rate as desired by the user. The approach requires no unique table to maximize its performance. The compression scheme performs well on a suite of test images typical of images from spacecraft instruments. Flight qualified hardware implementations are in development; a functional chip set is expected by the end of 2001. The chip set is being designed to compress data in excess of 20 Msamples/sec and support quantizations from 2 to 16 bits.

Managing Cassini Safe Mode Attitude at Saturn

NASA Technical Reports Server (NTRS)

Burk, Thomas A.

2010-01-01

The Cassini spacecraft was launched on October 15, 1997 and arrived at Saturn on June 30, 2004. It has performed detailed observations and remote sensing of Saturn, its rings, and its satellites since that time. In the event safe mode interrupts normal orbital operations, Cassini has flight software fault protection algorithms to detect, isolate, and recover to a thermally safe and commandable attitude and then wait for further instructions from the ground. But the Saturn environment is complex, and safety hazards change depending on where Cassini is in its orbital trajectory around Saturn. Selecting an appropriate safe mode attitude that insures safe operation in the Saturn environment, including keeping the star tracker field of view clear of bright bodies, while maintaining a quiescent, commandable attitude, is a significant challenge. This paper discusses the Cassini safe table management strategy and the key criteria that must be considered, especially during low altitude flybys of Titan, in deciding what spacecraft attitude should be used in the event of safe mode.

Neutron Time-of-Flight Spectroscopy

PubMed Central

Copley, John R. D.; Udovic, Terrence J.

1993-01-01

The time-of-flight technique is employed in two of the instruments at the NIST Cold Neutron Research Facility (CNRF). A pulsed monochromatic beam strikes the sample, and the energies of scattered neutrons are determined from their times-of-flight to an array of detectors. The time-of-flight method may be used in a variety of types of experiments such as studies of vibrational and magnetic excitations, tunneling spectroscopy, and quasielastic scattering studies of diffusional behavior; several examples of experiments are discussed. We also present brief descriptions of the CNRF time-of-flight instruments, including their modi operandi and some of their more pertinent parameters and performance characteristics. PMID:28053459

EVA tools and equipment reference book

NASA Technical Reports Server (NTRS)

Fullerton, R. K.

1993-01-01

This document contains a mixture of tools and equipment used throughout the space shuttle-based extravehicular activity (EVA) program. Promising items which have reached the prototype stage of development are also included, but should not be considered certified ready for flight. Each item is described with a photo, a written discussion, technical specifications, dimensional drawings, and points of contact for additional information. Numbers on the upper left-hand corner of each photo may be used to order specific pictures from NASA and contractor photo libraries. Points of contact were classified as either operational or technical. An operational contact is an engineer from JSC Mission Operations Directorate who is familiar with the basic function and on-orbit use of the tool. A technical contact would be the best source of detailed technical specifications and is typically the NASA subsystem manager. The technical information table for each item uses the following terms to describe the availability or status of each hardware item: Standard - Flown on every mission as standard manifest; Flight specific - Potentially available for flight, not flown every mission (flight certification cannot be guaranteed and recertification may be required); Reference only - Item no longer in active inventory or not recommended for future use, some items may be too application-specific for general use; and Developmental - In the prototype stage only and not yet available for flight. The current availability and certification of any flight-specific tool should be verified with the technical point of contact. Those tools built and fit checked for Hubble Space Telescope maintenance are program dedicated and are not available to other customers. Other customers may have identical tools built from the existing, already certified designs as an optional service.

International study of risk-mitigating factors and in-flight allergic reactions to peanut and tree nut.

PubMed

Greenhawt, Matthew; MacGillivray, Fiona; Batty, Geraldine; Said, Maria; Weiss, Christopher

2013-03-01

Three studies have analyzed in-flight peanut/tree nut reactions, although the studies were conducted exclusively among Americans. We studied the international in-flight experience and determined the efficacy of certain risk-mitigation strategies. A 47-question on-line survey was distributed through the websites and social media outlets of the member organizations of the Food Allergy & Anaphylaxis Alliance. Both persons reporting an in-flight reaction and nonreactors were surveyed to assess details of air travel preparation and any reported reaction. Data were analyzed to determine the association among flying behaviors, reported reactions, and nationality. We found that 349 reactions were reported among 3273 respondents from 11 countries; 13.3% received epinephrine as treatment. Flight crews were notified about 50.1% of reactions. Sixty-nine percent of all respondents reported making a preflight accommodation request, although just 55% of reactors did so compared with 71.6% of nonreactors (P < .001). Adjusted odds of epinephrine use were increased with reported gastrointestinal or cardiovascular symptoms or with notifying the crew. Passengers who requested any accommodation, requested a peanut/tree nut-free meal, wiped their tray table, avoided airline pillows or blankets, requested a buffer zone, requested other passengers not consume peanut/tree nut-containing products, or reported not consuming airline-provided food had significantly lower adjusted odds of reporting a reaction. In-flight peanut and tree nut reactions occur internationally. Epinephrine was sparsely used to treat reactions. We identified 8 risk-mitigating behaviors associated with lower odds of a reported reaction. Future study is necessary to further validate the effectiveness of these passenger-initiated risk-mitigating behaviors. Copyright © 2013 American Academy of Allergy, Asthma & Immunology. Published by Elsevier Inc. All rights reserved.

Comparative Research of Navy Voluntary Education at Operational Commands

DTIC Science & Technology

2017-03-01

return on investment, ROI, logistic regression, multivariate analysis, descriptive statistics, Markov, time-series, linear programming 15. NUMBER...21  B.  DESCRIPTIVE STATISTICS TABLES ...............................................25  C.  PRIVACY CONSIDERATIONS...THIS PAGE INTENTIONALLY LEFT BLANK xi LIST OF TABLES Table 1.  Variables and Descriptions . Adapted from NETC (2016). .......................21

76 FR 8965 - National Vaccine Injury Compensation Program: Revisions to the Vaccine Injury Table

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-16

... DEPARTMENT OF HEALTH AND HUMAN SERVICES 42 CFR Part 100 RIN 0907-AA National Vaccine Injury Compensation Program: Revisions to the Vaccine Injury Table AGENCY: Health Resources and Services... ``National Vaccine Injury Compensation Program: Revisions to the Vaccine Injury Table.'' Date and Time: The...

Fast Mix Table Construction for Material Discretization

DOE Office of Scientific and Technical Information (OSTI.GOV)

Johnson, Seth R

2013-01-01

An effective hybrid Monte Carlo--deterministic implementation typically requires the approximation of a continuous geometry description with a discretized piecewise-constant material field. The inherent geometry discretization error can be reduced somewhat by using material mixing, where multiple materials inside a discrete mesh voxel are homogenized. Material mixing requires the construction of a ``mix table,'' which stores the volume fractions in every mixture so that multiple voxels with similar compositions can reference the same mixture. Mix table construction is a potentially expensive serial operation for large problems with many materials and voxels. We formulate an efficient algorithm to construct a sparse mix table inmore » $$O(\\text{number of voxels}\\times \\log \\text{number of mixtures})$$ time. The new algorithm is implemented in ADVANTG and used to discretize continuous geometries onto a structured Cartesian grid. When applied to an end-of-life MCNP model of the High Flux Isotope Reactor with 270 distinct materials, the new method improves the material mixing time by a factor of 100 compared to a naive mix table implementation.« less

TABLES OF VALUES AND SHOOTING TIMES IN NOISY DUELS.

DTIC Science & Technology

A noisy duel is a zero-sum, two-person game with the following structure: Each player has bullets which he can fire at any times in (0, 1). If...shooting times for noisy duels are presented, which, in some cases, can be used to trace the play of the game. An additional table illustrates how

Design Report for the Synchronized Position, Velocity, and Time Code Generator

DTIC Science & Technology

2015-08-01

Stream Specification 4 2.3 Data Packet Format Specification 4 2.3.1 Individual Message Definition 5 3. MATLAB Parsing Software 6 4. Conclusions and...packet format structure ..................................................................4 Table 2 PPS time message definition ...5 Table 3 Position message definition ...................................................................5

The in-flight calibration of the Hubble Space Telescope attitude sensors

NASA Technical Reports Server (NTRS)

Welter, Gary L.

1991-01-01

A detailed review of the in-flight calibration of the Hubble Space Telescope attitude sensors is presented. The review, which covers the period from the April 24, 1990, launch of the spacecraft until the time of this writing (June 1991), describes the calibrations required and accuracies achieved for the four principal attitude sensing systems on the spacecraft: the magnetometers, the fixed head star trackers, the gyroscopes, and the fine guidance sensors (FGS's). In contrast to the other three sensor groups, the Hubble Telecope's FGS's are unique in the precision and performance levels being attempted; spacecraft control and astrometric research at the near-milliarcsecond level are the ultimate goals. FGS calibration accuracies at the 20-milliarcsecond level have already been achieved, and plans for new data acquisitions and reductions that should substantially improve these results are in progress. A summary of the basic attributes of each of the four sensor groups with respect to its usage as an attitude measuring system is presented, followed by a discussion of the calibration items of interest for that group. The calibration items are as follows: for the magnetometers, the corrections for the spacecraft's static and time-varying magnetic fields; for the fixed-head star trackers, their relative alignments and use in performing onboard attitude updates; for the gyroscopes, their scale factors, alignments, and drift rate biases; and for the FGS's, their magnifications, optical distortions, and alignments. The discussion covers the procedures used for each calibration, as well as the order of the calibrations within the general flow of orbital verification activities. It also includes a synopsis of current plans for the eventual calibration of the FGS's to achieve their near-milliarcsecond design accuracy. The conclusions include a table indicating the current and predicted ultimate accuracies for each of the calibration items.

Non-tables look-up search algorithm for efficient H.264/AVC context-based adaptive variable length coding decoding

NASA Astrophysics Data System (ADS)

Han, Yishi; Luo, Zhixiao; Wang, Jianhua; Min, Zhixuan; Qin, Xinyu; Sun, Yunlong

2014-09-01

In general, context-based adaptive variable length coding (CAVLC) decoding in H.264/AVC standard requires frequent access to the unstructured variable length coding tables (VLCTs) and significant memory accesses are consumed. Heavy memory accesses will cause high power consumption and time delays, which are serious problems for applications in portable multimedia devices. We propose a method for high-efficiency CAVLC decoding by using a program instead of all the VLCTs. The decoded codeword from VLCTs can be obtained without any table look-up and memory access. The experimental results show that the proposed algorithm achieves 100% memory access saving and 40% decoding time saving without degrading video quality. Additionally, the proposed algorithm shows a better performance compared with conventional CAVLC decoding, such as table look-up by sequential search, table look-up by binary search, Moon's method, and Kim's method.

Autonomic Computing for Spacecraft Ground Systems

NASA Technical Reports Server (NTRS)

Li, Zhenping; Savkli, Cetin; Jones, Lori

2007-01-01

Autonomic computing for spacecraft ground systems increases the system reliability and reduces the cost of spacecraft operations and software maintenance. In this paper, we present an autonomic computing solution for spacecraft ground systems at NASA Goddard Space Flight Center (GSFC), which consists of an open standard for a message oriented architecture referred to as the GMSEC architecture (Goddard Mission Services Evolution Center), and an autonomic computing tool, the Criteria Action Table (CAT). This solution has been used in many upgraded ground systems for NASA 's missions, and provides a framework for developing solutions with higher autonomic maturity.

Flight Tests of the Head-Up Display (HUD) in DC-9-20 Ship 382, November 1968 - January 1969. IRAD Line Item Description Number D36-69-033f

DTIC Science & Technology

1970-09-14

in this report was carried out as part of an Independent Research and Development program on the contribution of the Head-Up Display to an All...through windshield. W, by partial mirror, M. and imaged at infinity by lens. L. ] 1 »hMWMMMMMHi^^Hik«ni l TABLE I. ORGANIZATIONAL PRINCIPLES USED...movement of the equipment or its components. Translational movements are unlikely to give trouble because the display format is imaged at infinity

Design and Flight Test of a Cable Angle Feedback Control System for Improving Helicopter Slung Load Operations at Low Speed

DTIC Science & Technology

2014-04-01

improve the damping of the load pendulum motions, but the load feedback generally had the effect of making the load feel heavier to the pilot [28...0.25 2 1000lbs 16,000lbs 0.06 Another important parameter is the slung load pendulum frequency. Using a simple pendulum model, this natural...the expected yaw and heave modes. The presence of the load adds oscillatory pendulum modes in the pitch and roll axes, as expected. Table 2-3

Crater Morphology in the Phoenix Landing Ellipse: Insights Into Net Erosion and Ice Table Depth

NASA Technical Reports Server (NTRS)

Noe Dobrea, E. Z.; Stoker, C. R.; McKay, C. P.; Davila, A. F.; Krco, M.

2015-01-01

Icebreaker [1] is a Discovery class mission being developed for future flight opportunities. Under this mission concept, the Icebreaker payload is carried on a stationary lander, and lands in the same landing ellipse as Phoenix. Samples are acquired from the subsurface using a drilling system that penetrates into materials which may include loose or cemented soil, icy soil, pure ice, rocks, or mixtures of these. To avoid the complexity of mating additional strings, the drill is single-string, limiting it to a total length of 1 m.

Skylab 3 crew during training in Orbital Workshop trainer

NASA Technical Reports Server (NTRS)

1973-01-01

The three prime crewmen of the Skylab 3 mission check over flight data during a training session in the crew quarters of the Orbital Workshop (OWS) trainer in the Mission Simulation and Training Facility at JSC. They are from left to right, Scientist-Astronaut Owen K. Garriott, science pilot; and Astronauts Alan L. bean, commander, and Jack R. Lousma, pilot (28419); Skylab 3 crew work with Inflight Medical Support System (IMSS) resupply container atop the food table in the OWS. From left to right are Garriott, Lousma and Bean (28420).

STS-57 inflight maintenance (IFM) tool tray at Boeing FEPF bench review

NASA Technical Reports Server (NTRS)

1993-01-01

STS-57 inflight maintenance (IFM) tool tray is displayed on a table top during the bench review at Boeing's Flight Equipment Processing Facility (FEPF) located near JSC. The tool tray will be located on Endeavour's, Orbiter Vehicle (OV) 105's, middeck in forward locker MF57K and includes pinch bar, deadblow hammer, punch, inspection mirror, speed handle assembly, robbins wrench, adjustable wrench, vise grips, connector pliers, ACCU bypass connector, connector strap wrench, locker tool, and mechanical fingers. Photo taken by NASA JSC contract photographer Benny Benavides.

Skylab (SL)-3 Crew - Training - Orbital Workshop Trainer - JSC

NASA Image and Video Library

1973-06-16

S73-28420 (16 June 1973) --- The three prime crewmen of the Skylab 3 mission check over flight data during a training session in the crew quarters of the Orbital Workshop (OWS) trainer in the Mission Simulation and Training Facility at the Johnson Space Center (JSC). Skylab 3 crew work with Inflight Medical Support System (IMSS) resupply container atop the food table in the OWS. They are from left to right, scientist-astronaut Owen K. Garriott, science pilot; and astronauts Jack R. Lousma, pilot; and Alan L. Bean, commander. Photo credit: NASA

GEMINI-TITAN-8 - PRELAUNCH ACTIVITY

NASA Image and Video Library

1966-03-16

S66-24439 (16 March 1966) --- The Gemini-8 prime crew, along with several fellow astronauts, have a hearty breakfast of steak and eggs on the morning of the Gemini-8 launch. Seated clockwise around the table, starting at lower left, are Donald K. Slayton, Manned Spaceflight Center (MSC) Assistant Director for Flight Crew Operations; astronaut Neil A. Armstrong, Gemini-8 command pilot; scientist-astronaut F. Curtis Michel; astronaut R. Walter Cunningham; astronaut Alan B. Shepard Jr. (face obscured), Chief, MSC Astronaut Office; astronaut David R. Scott, Gemini-8 pilot; and astronaut Roger B. Chaffee. Photo credit: NASA

Nasa Program Plan

NASA Technical Reports Server (NTRS)

1980-01-01

Major facts are given for NASA'S planned FY-1981 through FY-1985 programs in aeronautics, space science, space and terrestrial applications, energy technology, space technology, space transportation systems, space tracking and data systems, and construction of facilities. Competition and cooperation, reimbursable launchings, schedules and milestones, supporting research and technology, mission coverage, and required funding are considered. Tables and graphs summarize new initiatives, significant events, estimates of space shuttle flights, and major missions in astrophysics, planetary exploration, life sciences, environmental and resources observation, and solar terrestrial investigations. The growth in tracking and data systems capabilities is also depicted.

Flight Capacities and Diurnal Flight Patterns of the Ambrosia Beetles, Xyleborus glabratus and Monarthrum mali (Coleoptera: Curculionidae).

PubMed

Seo, Meeja; Martini, Xavier; Rivera, Monique J; Stelinski, Lukasz L

2017-06-01

We compared the flight activity of Xyleborus glabratus Eichhoff, vector and symbiont of the causal agent of laurel wilt disease (Raffaelea lauricola), with a native species Monarthrum mali (Fitch) using flight mills. Flight mills were operated either for 24 h or for three 3-h time intervals. During the 3-h interval experiment, the shortest time to flight initiation for X. glabratus occurred at 1600-1900 hours. The average flight time and total flying distance during 1600-2100 hours were also higher than those quantified during the other two recording times investigated. However, total flight duration and proportion of fliers was highest at 1000-1300 hours. We compared several flight parameters. About 64.0% of tested X. glabratus flew <20 m. During 24-h recording periods, M. mali flew longer distances than X. glabratus. Over 50.0% of M. mali flew over 100 m on the flight mill. Xyleborus glabratus flight activity was greatest between 1200 and 1800 hours, while M. mali flew most frequently between 1500 and 2100 hours. Monarthrum mali flew more than five times more frequently than X. glabratus, and their longest single flight distance (37.5 ± 12.5 m) and total flight distance (213.7 ± 85.5 m) were greater than those of X. glabratus. These data will be useful for development of species-specific control and monitoring protocols for these ambrosia beetles based on greater understanding of their flight capacities and associated invasion distance. © The Authors 2017. Published by Oxford University Press on behalf of Entomological Society of America. All rights reserved. For Permissions, please email: journals.permissions@oup.com.

IMS/Satellite Situation Center report: Predicted orbit plots for IMP-J-1976

NASA Technical Reports Server (NTRS)

1975-01-01

Predicted orbit plots for the IMP-J satellite were given for the time period January-December 1976. These plots are shown in three projections. The time period covered by each set of projections is 12 days and 6 hours, corresponding approximately to the period of IMP-J. The three coordinate systems used are the Geocentric Solar Ecliptic system (GSE), the Geocentric Solar Magnetospheric system (GSM), and the Solar Magnetic system (SM). For each of the three projections, time ticks and codes are given on the satellite trajectories. The codes are interpreted in the table at the base of each plot. Time is given in the table as year/day/decimal hour, and the total time covered by each plot is shown at the bottom of each table.

Preliminary test results of a flight management algorithm for fuel conservative descents in a time based metered traffic environment. [flight tests of an algorithm to minimize fuel consumption of aircraft based on flight time

NASA Technical Reports Server (NTRS)

Knox, C. E.; Cannon, D. G.

1979-01-01

A flight management algorithm designed to improve the accuracy of delivering the airplane fuel efficiently to a metering fix at a time designated by air traffic control is discussed. The algorithm provides a 3-D path with time control (4-D) for a test B 737 airplane to make an idle thrust, clean configured descent to arrive at the metering fix at a predetermined time, altitude, and airspeed. The descent path is calculated for a constant Mach/airspeed schedule from linear approximations of airplane performance with considerations given for gross weight, wind, and nonstandard pressure and temperature effects. The flight management descent algorithms and the results of the flight tests are discussed.

The STS-92 crew pose around a table before suiting up .

NASA Technical Reports Server (NTRS)

2000-01-01

The STS-92 crew pose for a group photo after a snack prior to suiting up for launch. Seated left to right are Mission Specialists Peter J.K. '''Jeff''' Wisoff and Michael E. Lopez- Alegria; Pilot Pamela Ann Melory; Commander Brian Duffy; and Mission Specialists Koichi Wakata of Japan, William S. McArthur Jr. and Leroy Chiao. The mission is the fifth flight for the construction of the ISS. The payload includes the Integrated Truss Structure Z-1 and the third Pressurized Mating Adapter. During the 11-day mission, four extravehicular activities (EVAs), or spacewalks, are planned. The Z-1 truss is the first of 10 that will become the backbone of the International Space Station, eventually stretching the length of a football field. PMA-3 will provide a Shuttle docking port for solar array installation on the sixth ISS flight and Lab installation on the seventh ISS flight. This launch is the fourth for Duffy and Wisoff, the third for Chiao and McArthur, second for Wakata and Lopez-Alegria, and first for Melroy. Launch is scheduled for 8:05 p.m. EDT. Landing is expected Oct. 21 at 3:55 p.m. EDT.

AMOR - the versatile reflectometer at SINQ

NASA Astrophysics Data System (ADS)

Clemens, D.; Gross, P.; Keller, P.; Schlumpf, N.; Könnecke, M.

2000-03-01

We report on a new facility for neutron reflectometry situated at the end position of a cold neutron guide at the Swiss Spallation Neutron Source SINQ. The instrument is a flexible apparatus, adaptable to the needs of the user's individual experiment. Principally designed to operate in the time-of-flight mode it is also capable to exploit the fact that SINQ is a continuous source because PSI's developments in the field of thin film multilayers are fruitfully applied. By means of multilayer monochromators it can be converted into a constant wavelength reflectometer. Polarized neutron reflectometry on AMOR takes advantage of remanent FeCo/Ti:N supermirrors and multilayers which can be operated in a way that no spin flippers are needed. The time and angular contributions to the resolution in momentum transfer are separately determinable in TOF mode. The total length of the instrument is adjustable in order to optimize resolution together with the illumination of the sample's surface. Large sample environments can be placed on the sample table that is actively isolated against vibrations. Single detectors and an EMBL 3He area detector can be chosen, alternatively. The instrument concept as well as parameters of its components are presented.

GUI Type Fault Diagnostic Program for a Turboshaft Engine Using Fuzzy and Neural Networks

NASA Astrophysics Data System (ADS)

Kong, Changduk; Koo, Youngju

2011-04-01

The helicopter to be operated in a severe flight environmental condition must have a very reliable propulsion system. On-line condition monitoring and fault detection of the engine can promote reliability and availability of the helicopter propulsion system. A hybrid health monitoring program using Fuzzy Logic and Neural Network Algorithms can be proposed. In this hybrid method, the Fuzzy Logic identifies easily the faulted components from engine measuring parameter changes, and the Neural Networks can quantify accurately its identified faults. In order to use effectively the fault diagnostic system, a GUI (Graphical User Interface) type program is newly proposed. This program is composed of the real time monitoring part, the engine condition monitoring part and the fault diagnostic part. The real time monitoring part can display measuring parameters of the study turboshaft engine such as power turbine inlet temperature, exhaust gas temperature, fuel flow, torque and gas generator speed. The engine condition monitoring part can evaluate the engine condition through comparison between monitoring performance parameters the base performance parameters analyzed by the base performance analysis program using look-up tables. The fault diagnostic part can identify and quantify the single faults the multiple faults from the monitoring parameters using hybrid method.

Comparison of Communication Architectures for Spacecraft Modular Avionics Systems

NASA Technical Reports Server (NTRS)

Gwaltney, D. A.; Briscoe, J. M.

2006-01-01

This document is a survey of publicly available information concerning serial communication architectures used, or proposed to be used, in aeronautic and aerospace applications. It focuses on serial communication architectures that are suitable for low-latency or real-time communication between physically distributed nodes in a system. Candidates for the study have either extensive deployment in the field, or appear to be viable for near-term deployment. Eleven different serial communication architectures are considered, and a brief description of each is given with the salient features summarized in a table in appendix A. This survey is a product of the Propulsion High Impact Avionics Technology (PHIAT) Project at NASA Marshall Space Flight Center (MSFC). PHIAT was originally funded under the Next Generation Launch Technology (NGLT) Program to develop avionics technologies for control of next generation reusable rocket engines. After the announcement of the Space Exploration Initiative, the scope of the project was expanded to include vehicle systems control for human and robotics missions. As such, a section is included presenting the rationale used for selection of a time-triggered architecture for implementation of the avionics demonstration hardware developed by the project team

[Possible Instrument Contamination in the Operating Room During Implantation of Knee and Hip Arthroplasty].

PubMed

Quint, U; Benen, T

2016-04-01

Integrated ventilation systems with low turbulence displacement flow (TAV) are generally legally required in the architectural structure of operating theatres. However, it seems that the instruments laid out on sterile covered tables do not have the best possible protection from bacteria. Within an operating theatre, different bacteria counts are possible on the instruments. This prospective controlled study was conducted to demonstrate the influence of instrument tables with integrated horizontal flow on contamination with pathogens in comparison with conventional tables. In an operating theatre (OT) with a ceiling legally appropriate for TAV (2.40 m × 1.20 m), microbiological samples were placed on a table with integrated TAV flow (n = 100) and on a conventional instrument table (n = 100). The routine qualification of the OT was on an ongoing basis and was in accordance with DIN 1946-4: 1999 standards (in accordance with DIN measurement of recovery time 1946-4: 12-2008). This corresponds to the OT of the room class Ib. The results show significant differences between the two tables. The bacteria count and the percentage of contamination were many times higher on the conventional table. It is important to understand that the instruments are not completely protected against contamination after opening the pack and during the operation. Remedial measures are possible to optimise the sterility the instrument table. Georg Thieme Verlag KG Stuttgart · New York.

Simulation Training Versus Real Time Console Training for New Flight Controllers

NASA Technical Reports Server (NTRS)

Heaton, Amanda

2010-01-01

For new flight controllers, the two main learning tools are simulations and real time console performance training. These benefit the new flight controllers in different ways and could possibly be improved. Simulations: a) Allow for mistakes without serious consequences. b) Lets new flight controllers learn the working style of other new flight controllers. c) Lets new flight controllers eventually begin to feel like they have mastered the sim world, so therefore they must be competent in the real time world too. Real time: a) Shows new flight controllers some of the unique problems that develop and have to be accounted for when dealing with certain payloads or systems. b) Lets new flight controllers experience handovers - gathering information from the previous shift on what the room needs to be aware of and what still needs to be done. c) Gives new flight controllers confidence that they can succeed in the position they are training for when they can solve real anomalies. How Sims could be improved and more like real-time ops for the ISS Operations Controller position: a) Operations Change Requests to review. b) Fewer anomalies (but still more than real time for practice). c) Payload Planning Manager Handover sheet for the E-1 and E-3 reviews. d) Flight note in system with at least one comment to verify for the E-1 and E-3 reviews How the real time console performance training could be improved for the ISS Operations Controller position: a) Schedule the new flight controller to be on console for four days but with a different certified person each day. This will force them to be the source of knowledge about every OCR in progress, everything that has happened in those few days, and every activity on the timeline. Constellation program flight controllers will have to learn entirely from simulations, thereby losing some of the elements that they will need to have experience with for real time ops. It may help them to practice real time console performance training in the International Space Station or Space Shuttle to gather some general anomaly resolution and day-to-day task management skills.

Statistical analysis of flight times for space shuttle ferry flights

NASA Technical Reports Server (NTRS)

Graves, M. E.; Perlmutter, M.

1974-01-01

Markov chain and Monte Carlo analysis techniques are applied to the simulated Space Shuttle Orbiter Ferry flights to obtain statistical distributions of flight time duration between Edwards Air Force Base and Kennedy Space Center. The two methods are compared, and are found to be in excellent agreement. The flights are subjected to certain operational and meteorological requirements, or constraints, which cause eastbound and westbound trips to yield different results. Persistence of events theory is applied to the occurrence of inclement conditions to find their effect upon the statistical flight time distribution. In a sensitivity test, some of the constraints are varied to observe the corresponding changes in the results.

Minimum Hamiltonian ascent trajectory evaluation (MASTRE) program (update to automatic flight trajectory design, performance prediction, and vehicle sizing for support of shuttle and shuttle derived vehicles) users manual

NASA Technical Reports Server (NTRS)

Lyons, J. T.; Borchers, William R.

1993-01-01

Documentation for the User Interface Program for the Minimum Hamiltonian Ascent Trajectory Evaluation (MASTRE) is provided. The User Interface Program is a separate software package designed to ease the user input requirements when using the MASTRE Trajectory Program. This document supplements documentation on the MASTRE Program that consists of the MASTRE Engineering Manual and the MASTRE Programmers Guide. The User Interface Program provides a series of menus and tables using the VAX Screen Management Guideline (SMG) software. These menus and tables allow the user to modify the MASTRE Program input without the need for learning the various program dependent mnemonics. In addition, the User Interface Program allows the user to modify and/or review additional input Namelist and data files, to build and review command files, to formulate and calculate mass properties related data, and to have a plotting capability.

Two-dimensional aerodynamic characteristics of the OLS/TAAT airfoil

NASA Technical Reports Server (NTRS)

Watts, Michael E.; Cross, Jeffrey L.; Noonan, Kevin W.

1988-01-01

Two flight tests have been conducted that obtained extension pressure data on a modified AH-1G rotor system. These two tests, the Operational Loads Survey (OLS) and the Tip Aerodynamics and Acoustics Test (TAAT) used the same rotor set. In the analysis of these data bases, accurate 2-D airfoil data is invaluable, for not only does it allow comparison studies between 2- and 3-D flow, but also provides accurate tables of the airfoil characteristics for use in comprehensive rotorcraft analysis codes. To provide this 2-D data base, a model of the OLS/TAAT airfoil was tested over a Reynolds number range from 3 x 10 to the 6th to 7 x 10 to the 7th and between Mach numbers of 0.34 to 0.88 in the NASA Langley Research Center's 6- by 28-Inch Transonic Tunnel. The 2-D airfoil data is presented as chordwise pressure coefficient plots, as well as lift, drag, and pitching moment coefficient plots and tables.

Neurologic decompression sickness following cabin pressure fluctuations at high altitude.

PubMed

Auten, Jonathan D; Kuhne, Michael A; Walker, Harlan M; Porter, Henry O

2010-04-01

Decompression sickness (DCS) occurs in diving, altitude chamber exposures, and unpressurized or depressurized high-altitude flights. Because DCS takes many forms, in-flight cases may be misinterpreted as hypoxia, hyperventilation, or viral illness, with resulting failure to respond appropriately. In this case, a 28-yr-old male pilot of a single-seat, tactical aircraft experienced 12 rapid pressure fluctuations while flying at 43,000 ft above sea level. He had no symptoms and decided to complete the flight, which required an additional 2 h in the air. Approximately 1 h later he began to experience fatigue, lightheadedness, and confusion, which he interpreted as onset of a viral illness. However, symptoms progressed to visual, cognitive, motor, and sensory degradations and it was with some difficulty that he landed safely at his destination. Neurologic DCS was suspected on initial evaluation by flight line medical personnel because of the delayed onset and symptom progression. He was transferred to a local Emergency Department and noted to have altered mental status, asymmetric motor deficits, and non-dermatomal paresthesias of the upper and lower extremities. Approximately 3.5 h after the incident and 2.5 h after the onset of symptoms he began hyperbaric oxygen therapy. He received partial relief at 30 min of the Navy DiveTable 6 and full resolution at 90 min; there were no recurrent symptoms at a 1-yr follow-up. This case highlights the importance of early recognition of in-flight DCS symptoms and landing as soon as possible rather than as soon as practical in all likely scenarios.

Erratum: "Discovery of a Second Millisecond Accreting Pulsar: XTE J1751-305"

NASA Technical Reports Server (NTRS)

Markwardt, Craig; Swank, J. H.; Strohmayer, T. E.; in 'tZand, J. J. M.; Marshall, F. E.

2007-01-01

The original Table 1 ("Timing Parameters of XTE J1751-305") contains one error. The epoch of pulsar mean longitude 90deg is incorrect due to a numerical conversion error in the preparation of the original table text. A corrected version of Table 1 is shown. For reference, the epoch of the ascending node is also included. The correct value was used in all of the analysis leading up to the paper. As T(sub 90) is a purely fiducial reference time, the scientific conclusions of the paper are unchanged.

Job Order Contracting: A Procurement Success Story

DTIC Science & Technology

1988-02-01

Engineering/Procurement processing time 279 CI4 TABLE C-2 JOC DELIVERY ORDER PROCESSING TIME Contract size and location Amount Elapsed time- ($000) days...Bragg 2.1 68 Monroe 2.1 196 Sill 2.2 3 bragg 2.3 32 C-5 Ii ~A¶A~.AL&A .LiA..hLI TABLE C-2 JOC DELIVERY ORDER PROCESSING TIME (Continued) Conrat szean...DEUVERY ORDER PROCESSING TIME (Continued) Amount Elapsed time- Contract size and location Amou daps($000) days Bragg S 14.7 11 Monroe 14.8 30 Monroe

Real-time flight conflict detection and release based on Multi-Agent system

NASA Astrophysics Data System (ADS)

Zhang, Yifan; Zhang, Ming; Yu, Jue

2018-01-01

This paper defines two-aircrafts, multi-aircrafts and fleet conflict mode, sets up space-time conflict reservation on the basis of safety interval and conflict warning time in three-dimension. Detect real-time flight conflicts combined with predicted flight trajectory of other aircrafts in the same airspace, and put forward rescue resolutions for the three modes respectively. When accorded with the flight conflict conditions, determine the conflict situation, and enter the corresponding conflict resolution procedures, so as to avoid the conflict independently, as well as ensure the flight safety of aimed aircraft. Lastly, the correctness of model is verified with numerical simulation comparison.

SU-D-209-04: Raise Your Table: An Effective Way to Reduce Radiation Dose for Fluoroscopy

DOE Office of Scientific and Technical Information (OSTI.GOV)

Huo, D; Hoerner, M; Toskich, B

2016-06-15

Purpose: Patient table height plays an important role in estimating patient skin dose for interventional radiology (IR) procedures, because the patient’s skin location is dependent on the height of table. Variation in table height can lead to as much as 150% difference in skin dose for patient exams with similar air kerma meter readings. In our facility, IR procedural workflow was recently changed to require the IR physicians to confirm the patient table height before the procedure. The patient table height data was collected before and after this workflow change to validate the implementation of this practice. Methods: Table heightmore » information was analyzed for all procedures performed in three IR rooms, which were impacted by the workflow change, covering three months before and after the change (Aug 2015 to Jan 2016). In total, 442, 425, and 390 procedures were performed in these three rooms over this time period. There were no personnel or procedure assignment changes during the six-month period of time. Statistical analysis was performed for the average table height changes before and after the workflow change. Results: For the three IR rooms investigated, after the workflow change, the average table heights were increased by 1.43 cm (p=0.004084), 0.66 cm (p=0.187089), and 1.59 cm (p=0.002193), providing a corresponding estimated skin dose savings of 6.76%, 2.94% and 7.62%, respectively. After the workflow change, the average table height was increased by 0.95 cm, 0.63 cm, 0.55 cm, 1.07 cm, 1.12 cm, and 3.36 cm for the six physicians who routinely work in these three rooms. Conclusion: Consistent improvement in table height settings has been observed for all IR rooms and all physicians following a simple workflow change. This change has led to significant patient dose savings by making physicians aware of the pre-procedure table position.« less

The influence of total flight time, recent flight time and age on pilot accident rates

DOT National Transportation Integrated Search

1983-06-30

This paper presents initial finding from a research effort conducted for the Safety Analysis Dvision, Office of Aviation Safety, Federal Aviation Administration (FAA). The analysis considers the influence of recent pilot flight time, total pilot flig...

14 CFR 121.519 - Flight time limitations: Deadhead transportation: airplanes.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight time limitations: Deadhead transportation: airplanes. 121.519 Section 121.519 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.519 Flight time limitations: Deadhead transportation: airplanes...

14 CFR 121.519 - Flight time limitations: Deadhead transportation: airplanes.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitations: Deadhead transportation: airplanes. 121.519 Section 121.519 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.519 Flight time limitations: Deadhead transportation: airplanes...

14 CFR 121.519 - Flight time limitations: Deadhead transportation: airplanes.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight time limitations: Deadhead transportation: airplanes. 121.519 Section 121.519 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.519 Flight time limitations: Deadhead transportation: airplanes...

14 CFR 121.519 - Flight time limitations: Deadhead transportation: airplanes.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight time limitations: Deadhead transportation: airplanes. 121.519 Section 121.519 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.519 Flight time limitations: Deadhead transportation: airplanes...

14 CFR 121.519 - Flight time limitations: Deadhead transportation: airplanes.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Deadhead transportation: airplanes. 121.519 Section 121.519 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.519 Flight time limitations: Deadhead transportation: airplanes...

Deep Impact Spacecraft Collides With Comet Tempel 1-Video

NASA Technical Reports Server (NTRS)

2005-01-01

After 172 days and 268 million miles of deep space travel, the NASA Deep Impact spacecraft successfully reached out and touched comet Tempel 1. The collision between the coffee table-sized space probe and city-sized comet occurred July 4, 2005 at 12:52 a.m. CDT. The objects met at 23,000 miles per hour. The heat produced by the impact was at least several thousand degrees Kelvin and at that extreme temperature, just about any material begins to glow. This movie, made up of images taken by the medium resolution camera aboard the spacecraft, from May 1 to July 2, shows the Deep Impact approach to comet Tempel 1. The spacecraft detected 3 outbursts during this time period, on June 14th, June 22nd, and July 2nd. The movie ends during the final outburst. Mission scientists expect Deep Impact to provide answers to basic questions about the formation of the solar system. Principal investigator, Dr. Michael A'Hearn of the University of Maryland in College Park, is responsible for the mission, and project management is handled by the Jet Propulsion Laboratory in Pasadena, California. The program office at Marshall Space Flight Center MSFC) in Huntsville, Alabama, assisted the Science Mission Directorate at NASA Headquarters in Washington with program management, technology planning, systems assessment, flight assurance and public outreach. The spacecraft was built for NASA by Ball Aerospace & Technologies Corporation of Boulder, Colorado. (NASA/JPL-Caltech/UMD)

Rugby football injuries, 1980-1983.

PubMed Central

Sparks, J P

1985-01-01

The injuries sustained by the boys at one English public school have been recorded and analysed by age, experience, position, phase, duration of the game and of the season. Few injuries have been serious. Detailed reference is made to concussion, injuries from collapsed scrums and injuries of the cervical spine. The paper emphasises that the tackle leads to most injuries. This paper presents the Rugby football injuries sustained by the boarders of Rugby School in the four seasons 1980-1983. The injury rate was 194 per 10,000 player hours, compared with the rate of 198 per 10,000 player hours for the thirty seasons 1950-1979 (Sparks, 1981). Tables I-VI list the injuries by different criteria. Table VII lists the sites of injury; Table VIII the time off Rugby football after injury; Table IX lists some of the more important injuries; Table XI summarises the playing results of the various school teams; Table XIII compares some of the Rugby School figures with those recorded in the Accident and Emergency Department of Christchurch Hospital during the 1979 New Zealand Rugby football season (Inglis and Stewart, 1981); Table XIV records information on three aspects of Rugby football that have occasioned much recent concern, viz:--Time off playing after concussion, injuries caused by collapsed scrums and neck injuries. Images p71-a PMID:4027497

A new algorithm for stand table projection models.

Treesearch

Quang V. Cao; V. Clark Baldwin

1999-01-01

The constrained least squares method is proposed as an algorithm for projecting stand tables through time. This method consists of three steps: (1) predict survival in each diameter class, (2) predict diameter growth, and (3) use the least squares approach to adjust the stand table to satisfy the constraints of future survival, average diameter, and stand basal area....

Diameter class volume tables for California old-growth timber

Treesearch

Duncan Dunning

1945-01-01

Tables giving average tree volumes by breast-height diameter classes frequently may be used in timber cruising to save money, time, and men. Such tables may be appropriate in cruises of large areas having many trees in low-intensity cruises warranting the sacrifice in accuracy that results from omission of individual tree height measurements, during wartime when men...

NCEP BUFR File Structure

Science.gov Websites

. These tables may be defined within a separate ASCII text file (see Description and Format of BUFR Tables time, the BUFR tables are usually read from an external ASCII text file (although it is also possible reports. Click here to view the ASCII text file (called /nwprod/fix/bufrtab.002 on the NCEP CCS machines

Shark: Fast Data Analysis Using Coarse-grained Distributed Memory

DTIC Science & Technology

2013-05-01

Schemes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 7.1.1 Java Objects...often MySQL or Derby) with a namespace for tables, table metadata, and par- tition information. Table data is stored in an HDFS directory, while a...saving time and space for large data sets. This is achieved with support for custom SerDe (serialization/deserialization) java interface implementations

26 CFR 1.1298-0 - Table of contents.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 26 Internal Revenue 11 2010-04-01 2010-04-01 true Table of contents. 1.1298-0 Section 1.1298-0...) INCOME TAXES Special Rules for Determining Capital Gains and Losses § 1.1298-0 Table of contents. This... deemed sale election. (3) Time for making the deemed sale election. (4) Manner of making the deemed sale...

26 CFR 1.1297-0 - Table of contents.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 26 Internal Revenue 11 2010-04-01 2010-04-01 true Table of contents. 1.1297-0 Section 1.1297-0...) INCOME TAXES Special Rules for Determining Capital Gains and Losses § 1.1297-0 Table of contents. This... deemed sale election. (3) Time for making the deemed sale election. (4) Manner of making the deemed sale...

75 FR 81212 - Floor-Standing Metal-Top Ironing Tables and Certain Parts Thereof from the People's Republic of...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-27

... Ironing Tables and Certain Parts Thereof from the People's Republic of China: Extension of Time Limit for... parts thereof from the People's Republic of China. See Floor-Standing, Metal-Top Ironing Tables and Certain Parts Thereof From the People's Republic of China: Preliminary Results of Antidumping Duty...

77 FR 1455 - Floor-Standing, Metal-Top Ironing Tables and Certain Parts Thereof From the People's Republic of...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-01-10

... Ironing Tables and Certain Parts Thereof From the People's Republic of China: Extension of Time Limit for... parts thereof from the People's Republic of China. See Floor-Standing, Metal-Top Ironing Tables and Certain Parts Thereof From the People's Republic of China: Preliminary Results of Antidumping Duty...

40 CFR Table 3 to Subpart Cb of... - Municipal Waste Combustor Operating Guidelines

Code of Federal Regulations, 2010 CFR

2010-07-01

... 40 Protection of Environment 6 2010-07-01 2010-07-01 false Municipal Waste Combustor Operating... and Compliance Times for Large Municipal Waste Combustors That are Constructed on or Before September 20, 1994 Pt. 60, Subpt. Cb, Table 3 Table 3 to Subpart Cb of Part 60—Municipal Waste Combustor...

VizieR Online Data Catalog: Stellar yields and the initial mass function (Molla+, 2015)

NASA Astrophysics Data System (ADS)

Molla, M.; Cavichia, O.; Gavilan, M.; Gibson, B. K.

2017-10-01

These tables give the theoretical chemical evolution models applied for the Milky Way Galaxy (MWG) from the cited paper. Basically give tables 2, 4 of stellar yields used and results of table 6 for the 144 models computed that work. Tables 2 and 4 give the stellar yields q_i(m) and remmnant mass for low and intermediate stars and massive stars, respectively, in a similar format for all authors. Table 6 gives the value of Chi2 for the 144 models computed for MWG using those stellar yields and different Initial Mass Function (see paper). Moreover, we give the table with results of the present time state of the Galactic disk for these 144 models. (12 data files).

Baseline coastal oblique aerial photographs collected from Breton Island, Louisiana, to the Alabama-Florida border, July 13, 2013

USGS Publications Warehouse

Morgan, Karen L.M.; Westphal, Karen A.

2014-01-01

The U.S. Geological Survey (USGS) conducts baseline and storm response photography missions to document and understand the changes in vulnerability of the Nation's coasts to extreme storms. On July 13, 2013, the USGS conducted an oblique aerial photographic survey from Breton Island, Louisiana, to the Alabama-Florida border, aboard a Cessna 172 flying at an altitude of 500 feet (ft) and approximately 1,000 ft offshore. This mission was flown to collect baseline data for assessing incremental changes since the last survey, and the data can be used in the assessment of future coastal change. The images provided here are Joint Photographic Experts Group (JPEG) images. ExifTtool was used to add the following to the header of each photo: time of collection, Global Positioning System (GPS) latitude, GPS longitude, keywords, credit, artist (photographer), caption, copyright, and contact information. The photograph locations are an estimate of the position of the aircraft and do not indicate the location of any feature in the images (see the Navigation Data page). These photographs document the configuration of the barrier islands and other coastal features at the time of the survey. Pages containing thumbnail images of the photographs, referred to as contact sheets, were created in 5-minute segments of flight time. These segements can be found on the Photos and Maps page. Photographs can be opened directly with any JPEG-compatible image viewer by clicking on a thumbnail on the contact sheet. Table 1 provides detailed information about the GPS location, name, date, and time each of the 1242 photographs taken along with links to each photograph. The photography is organized into segments, also referred to as contact sheets, and represent approximately 5 minutes of flight time. (Also see the Photos and Maps page). In addition to the photographs, a Google Earth Keyhole Markup Language (KML) file is provided and can be used to view the images by clicking on the marker and then clicking on either the thumbnail or the link above the thumbnail. The KML files were created using the photographic navigation files.

Baseline coastal oblique aerial photographs collected from Dauphin Island, Alabama, to Breton Island, Louisiana, August 8, 2012

USGS Publications Warehouse

Morgan, Karen L.M.; Westphal, Karen A.

2014-01-01

The U.S. Geological Survey (USGS) conducts baseline and storm response photography missions to document and understand the changes in vulnerability of the Nation's coasts to extreme storms. On August 8, 2012, the USGS conducted an oblique aerial photographic survey from Dauphin Island, Alabama, to Breton Island, Louisiana, aboard a Cessna 172 at an altitude of 500 feet (ft) and approximately 1,000 ft offshore. This mission was flown to collect baseline data for assessing incremental changes since the last survey, and the data can be used in the assessment of future coastal change. The images provided here are Joint Photographic Experts Group (JPEG) images. Exiftool was used to add the following to the header of each photo: time of collection, Global Positioning System (GPS) latitude, GPS longitude, keywords, credit, artist (photographer), caption, copyright, and contact information. The photograph locations are an estimate of the position of the aircraft and do not indicate the location of any feature in the images (see the Navigation Data page). These photographs document the configuration of the barrier islands and other coastal features at the time of the survey. Pages containing thumbnail images of the photographs, referred to as contact sheets, were created in 5-minute segments of flight time. These segements can be found on the Photos and Maps page. Photographs can be opened directly with any JPEG-compatible image viewer by clicking on a thumbnail on the contact sheet. Table 1 provides detailed information about the GPS location, name, date, and time each of the 1241 photographs taken along with links to each photograph. The photography is organized into segments, also referred to as contact sheets, and represent approximately 5 minutes of flight time. (Also see the Photos and Maps page). In addition to the photographs, a Google Earth Keyhole Markup Language (KML) file is provided and can be used to view the images by clicking on the marker and then clicking on either the thumbnail or the link above the thumbnail. The KML files were created using the photographic navigation files.

Effect of Sampling Schedule on Pharmacokinetic Parameter Estimates of Promethazine in Astronauts

NASA Technical Reports Server (NTRS)

Boyd, Jason L.; Wang, Zuwei; Putcha, Lakshmi

2005-01-01

Six astronauts on the Shuttle Transport System (STS) participated in an investigation on the pharmacokinetics of promethazine (PMZ), a medication used for the treatment of space motion sickness (SMS) during flight. Each crewmember completed the protocol once during flight and repeated thirty days after returned to Earth. Saliva samples were collected at scheduled times for 72 h after PMZ administration; more frequent samples were collected on the ground than during flight owing to schedule constraints in flight. PMZ concentrations in saliva were determined by a liquid chromatographic/mass spectrometric (LC-MS) assay and pharmacokinetic parameters (PKPs) were calculated using actual flight and ground-based data sets and using time-matched sampling schedule on ground to that during flight. Volume of distribution (V(sub c)) and clearance (Cl(sub s),) decreased during flight compared to that from time-matched ground data set; however, Cl(sub s) and V(sub c) estimates were higher for all subjects when partial ground data sets were used for analysis. Area under the curve (AUC) normalized with administered dose was similar in flight and partial ground data; however AUC was significantly lower using time-matched sampling compared with the full data set on ground. Half life (t(sub 1/2)) was longest during flight, shorter with matched-sampling schedule on ground and shortest when complete data set from ground was used. Maximum concentration (C(sub max)), time for C(sub max), (t(sub max)), parameters of drug absorption, depicted a similar trend with lowest and longest respectively, during flight, lower with time-matched ground data and highest and shortest with full ground data.

Effect of sampling schedule on pharmacokinetic parameter estimates of promethazine in astronauts

NASA Astrophysics Data System (ADS)

Boyd, Jason L.; Wang, Zuwei; Putcha, Lakshmi

2005-08-01

Six astronauts on the Shuttle Transport System (STS) participated in an investigation on the pharmacokinetics of promethazine (PMZ), a medication used for the treatment of space motion sickness (SMS) during flight. Each crewmember completed the protocol once during flight and repeated thirty days after returned to Earth. Saliva samples were collected at scheduled times for 72 h after PMZ administration; more frequent samples were collected on the ground than during flight owing to schedule constraints in flight. PMZ concentrations in saliva were determined by a liquid chromatographic/mass spectrometric (LC-MS) assay and pharmacokinetic parameters (PKPs) were calculated using actual flight and ground-based data sets and using time-matched sampling schedule on ground to that during flight. Volume of distribution (Vc) and clearance (Cls) decreased during flight compared to that from time-matched ground data set; however, ClS and Vc estimates were higher for all subjects when partial ground data sets were used for analysis. Area under the curve (AUC) normalized with administered dose was similar in flight and partial ground data; however AUC was significantly lower using time-matched sampling compared with the full data set on ground. Half life (t1/2) was longest during flight, shorter with matched-sampling schedule on ground and shortest when complete data set from ground was used. Maximum concentration (Cmax), time for Cmax (tmax), parameters of drug absorption, depicted a similar trend with lowest and longest respectively, during flight, lower with time- matched ground data and highest and shortest with full ground data.

The role of situation assessment and flight experience in pilots' decisions to continue visual flight rules flight into adverse weather.

PubMed

Wiegmann, Douglas A; Goh, Juliana; O'Hare, David

2002-01-01

Visual flight rules (VFR) flight into instrument meteorological conditions (IMC) is a major safety hazard in general aviation. In this study we examined pilots' decisions to continue or divert from a VFR flight into IMC during a dynamic simulation of a cross-country flight. Pilots encountered IMC either early or later into the flight, and the amount of time and distance pilots flew into the adverse weather prior to diverting was recorded. Results revealed that pilots who encountered the deteriorating weather earlier in the flight flew longer into the weather prior to diverting and had more optimistic estimates of weather conditions than did pilots who encountered the deteriorating weather later in the flight. Both the time and distance traveled into the weather prior to diverting were negatively correlated with pilots' previous flight experience. These findings suggest that VFR flight into IMC may be attributable, at least in part, to poor situation assessment and experience rather than to motivational judgment that induces risk-taking behavior as more time and effort are invested in a flight. Actual or potential applications of this research include the design of interventions that focus on improving weather evaluation skills in addition to addressing risk-taking attitudes.

Miracle Flights

MedlinePlus

... the perfect solution for your needs. Book A Flight Request a flight now Click on the link ... Now Make your donation today Saving Lives One Flight At A Time Miracle Flights provides children and ...

Flap or soar? How a flight generalist responds to its aerial environment.

PubMed

Shamoun-Baranes, Judy; Bouten, Willem; van Loon, E Emiel; Meijer, Christiaan; Camphuysen, C J

2016-09-26

The aerial environment is heterogeneous in space and time and directly influences the costs of animal flight. Volant animals can reduce these costs by using different flight modes, each with their own benefits and constraints. However, the extent to which animals alter their flight modes in response to environmental conditions has rarely been studied in the wild. To provide insight into how a flight generalist can reduce the energetic cost of movement, we studied flight behaviour in relation to the aerial environmental and landscape using hundreds of hours of global positioning system and triaxial acceleration measurements of the lesser black-backed gull (Larus fuscus). Individuals differed largely in the time spent in flight, which increased linearly with the time spent in flight at sea. In general, flapping was used more frequently than more energetically efficient soaring flight. The probability of soaring increased with increasing boundary layer height and time closer to midday, reflecting improved convective conditions supportive of thermal soaring. Other forms of soaring flight were also used, including fine-scale use of orographic lift. We explore the energetic consequences of behavioural adaptations to the aerial environment and underlying landscape and implications for individual energy budgets, foraging ecology and reproductive success.This article is part of the themed issue 'Moving in a moving medium: new perspectives on flight'. © 2016 The Author(s).

[Hazard function and life table: an introduction to the failure time analysis].

PubMed

Matsushita, K; Inaba, H

1987-04-01

Failure time analysis has become popular in demographic studies. It can be viewed as a part of regression analysis with limited dependent variables as well as a special case of event history analysis and multistate demography. The idea of hazard function and failure time analysis, however, has not been properly introduced to nor commonly discussed by demographers in Japan. The concept of hazard function in comparison with life tables is briefly described, where the force of mortality is interchangeable with the hazard rate. The basic idea of failure time analysis is summarized for the cases of exponential distribution, normal distribution, and proportional hazard models. The multiple decrement life table is also introduced as an example of lifetime data analysis with cause-specific hazard rates.

76 FR 75504 - Table Saw Blade Contact Injuries; Notice of Extension of Time for Comments

Federal Register 2010, 2011, 2012, 2013, 2014

2011-12-02

... [Docket No. CPSC-2011-0074] Table Saw Blade Contact Injuries; Notice of Extension of Time for Comments... blade contact, regulatory alternatives, other possible means to address this risk, and other topics or... identifiers, contact information, or other personal information provided, to: http://www.regulations.gov . Do...

The Mystical "Quadratic Formula."

ERIC Educational Resources Information Center

March, Robert H.

1993-01-01

Uses projectile motion to explain the two roots found when using the quadratic formula. An example is provided for finding the time of flight for a projectile which has a negative root implying a negative time of flight. This negative time of flight also has a useful physical meaning. (MVL)

14 CFR 121.517 - Flight time limitations: Other commercial flying: airplanes.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight time limitations: Other commercial flying: airplanes. 121.517 Section 121.517 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.517 Flight time limitations: Other commercial flying: airplanes. No...

14 CFR 121.517 - Flight time limitations: Other commercial flying: airplanes.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitations: Other commercial flying: airplanes. 121.517 Section 121.517 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.517 Flight time limitations: Other commercial flying: airplanes. No...

14 CFR 121.517 - Flight time limitations: Other commercial flying: airplanes.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight time limitations: Other commercial flying: airplanes. 121.517 Section 121.517 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.517 Flight time limitations: Other commercial flying: airplanes. No...

14 CFR 121.517 - Flight time limitations: Other commercial flying: airplanes.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight time limitations: Other commercial flying: airplanes. 121.517 Section 121.517 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.517 Flight time limitations: Other commercial flying: airplanes. No...

14 CFR 121.517 - Flight time limitations: Other commercial flying: airplanes.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Other commercial flying: airplanes. 121.517 Section 121.517 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... Limitations: Supplemental Operations § 121.517 Flight time limitations: Other commercial flying: airplanes. No...

Flight Deck Surface Trajectory-Based Operations

NASA Technical Reports Server (NTRS)

Foyle, David C.; Hooey, Becky L.; Bakowski, Deborah L.

2017-01-01

Surface Trajectory-Based Operations (STBO) is a future concept for surface operations where time requirements are incorporated into taxi operations to support surface planning and coordination. Pilot-in-the-loop flight deck simulations have been conducted to study flight deck displays algorithms to aid pilots in complying with the time requirements of time-based taxi operations (i.e., at discrete locations in 3 12 D operations or at all points along the route in 4DT operations). The results of these studies (conformance, time-of-arrival error, eye-tracking data, and safety ratings) are presented. Flight deck simulation work done in collaboration with DLR is described. Flight deck research issues in future auto-taxi operations are also introduced.

Hypersonic Research Vehicle (HRV) real-time flight test support feasibility and requirements study. Part 1: Real-time flight experiment support

NASA Technical Reports Server (NTRS)

Rediess, Herman A.; Ramnath, Rudrapatna V.; Vrable, Daniel L.; Hirvo, David H.; Mcmillen, Lowell D.; Osofsky, Irving B.

1991-01-01

The results are presented of a study to identify potential real time remote computational applications to support monitoring HRV flight test experiments along with definitions of preliminary requirements. A major expansion of the support capability available at Ames-Dryden was considered. The focus is on the use of extensive computation and data bases together with real time flight data to generate and present high level information to those monitoring the flight. Six examples were considered: (1) boundary layer transition location; (2) shock wave position estimation; (3) performance estimation; (4) surface temperature estimation; (5) critical structural stress estimation; and (6) stability estimation.

Assessing and minimizing contamination in time of flight based validation data

NASA Astrophysics Data System (ADS)

Lennox, Kristin P.; Rosenfield, Paul; Blair, Brenton; Kaplan, Alan; Ruz, Jaime; Glenn, Andrew; Wurtz, Ronald

2017-10-01

Time of flight experiments are the gold standard method for generating labeled training and testing data for the neutron/gamma pulse shape discrimination problem. As the popularity of supervised classification methods increases in this field, there will also be increasing reliance on time of flight data for algorithm development and evaluation. However, time of flight experiments are subject to various sources of contamination that lead to neutron and gamma pulses being mislabeled. Such labeling errors have a detrimental effect on classification algorithm training and testing, and should therefore be minimized. This paper presents a method for identifying minimally contaminated data sets from time of flight experiments and estimating the residual contamination rate. This method leverages statistical models describing neutron and gamma travel time distributions and is easily implemented using existing statistical software. The method produces a set of optimal intervals that balance the trade-off between interval size and nuisance particle contamination, and its use is demonstrated on a time of flight data set for Cf-252. The particular properties of the optimal intervals for the demonstration data are explored in detail.

In-flight thrust determination on a real-time basis

NASA Technical Reports Server (NTRS)

Ray, R. J.; Carpenter, T.; Sandlin, T.

1984-01-01

A real time computer program was implemented on a F-15 jet fighter to monitor in-flight engine performance of a Digital Electronic Engine Controlled (DEES) F-100 engine. The application of two gas generator methods to calculate in-flight thrust real time is described. A comparison was made between the actual results and those predicted by an engine model simulation. The percent difference between the two methods was compared to the predicted uncertainty based on instrumentation and model uncertainty and agreed closely with the results found during altitude facility testing. Data was obtained from acceleration runs of various altitudes at maximum power settings with and without afterburner. Real time in-flight thrust measurement was a major advancement to flight test productivity and was accomplished with no loss in accuracy over previous post flight methods.

The Wireless Data Acquisition System for the Vibration Table

NASA Astrophysics Data System (ADS)

Teng, Y. T.; Hu, X.

2014-12-01

The vibration table is a large-scaled tool used for inspecting the performance of seismometers. The output from a seismometer on the table can be directly monitored when the vibration table moves in certain pattern. Compared with other inspection methods, inspecting seismometers' performance indicators (frequency response, degree of linearity, sensitivity, lateral inhibition and dynamic range etc). using vibration tables is more intuitive. Therefore, the vibration tables are an essential testing part in developing new seismometers and seismometer quality control. Whereas, in practice, a cable is needed to connect the seismometer to the ground equipments for its signal outputs and power supply, that means adding a time-varying nonlinear spring between the vibration table and ground. The cable adds nonlinear feature to the table, distorts the table-board movement and bring extra errors to the inspecting work and affected the testing accuracy and precision. In face of this problem, we developed a wireless acquiring system for the vibration table. The system is consisted of a three-channel analog-to-digital conversion, an acquisition control part, local data storage, network interface, wireless router and power management, etc. The analog-to-digital conversion part uses a 24-digit high-precision converter, which has a programmable amplifier at the front end of its artificial circuit, with the function of matching outputs with different amplifier from the vibration table. The acquisition control part uses a 32 bit ARM processor, with low-power dissipation, minute extension and high performance. The application software platform is written in Linux to make the system convenient for multitasking work. Large volume local digital storage is achieved by a 32G SD card, which is used for saving real time acquired data. Data transmission is achieved by network interface and wireless router, which can simplify the application software by the supported TCP/IP protocol. Besides, the acquisition system uses built-in power supply, which provides power to the system with Li-On rechargeable battery with high capacity, then all the cable link between the vibration table and the ground equipment have been removed. With all these changes, the whole system is immobilized on board of the vibration table after being packaged.

Evaluation of the Effects of Light Intensity and Time Interval After the Start of Scotophase on the Female Flight Propensity of Asian Gypsy Moth (Lepidoptera: Erebidae).

PubMed

Chen, Fang; Shi, Juan; Keena, Melody

2016-04-01

Asian gypsy moth, Lymantria dispar L. (Lepidoptera: Erebidae), females are capable of flight, but little is known about what causes the variation in flight propensity that has been observed. The female flight propensity and capability of Asian gypsy moth from seven geographic populations (three from China, two from Russia, one from Japan, and one from Korea) were compared under all combinations of three light intensities (0.05, 0.10, and 0.40 lux) and during three time intervals after the start of scotophase. A total of 567 females were flight tested. Female flight propensity, time to initiate walking, fanning, and flying, and duration of fanning differed significantly among geographic populations. Females were less likely to voluntarily fly during the 0-1-h time interval after the start of scotophase than during the later time intervals (1-2 and 2-3 h), suggesting that the light intensity cue has to occur at the correct time after the expected start of scotophase for flight initiation. Light intensity did not significantly affect the proportion of females that voluntarily flew, but did impact the timing of the walking and fanning preflight behaviors. The interaction between light intensity and time interval after the start of scotophase had a significant effect on the proportion of females that fanned. The proportion of females with sustained flight capability varied among the populations evaluated. These results may aid in determining the risk of Asian gypsy moth dispersal, but further work is needed to assess other factors that play a role in flight propensity. Published by Oxford University Press on behalf of Entomological Society of America 2016. This work is written by US Government employees and is in the public domain in the US.

Reproductive phenologies in a diverse temperate ant fauna

USGS Publications Warehouse

Dunn, R.R.; Parker, C.R.; Geraghty, M.; Sanders, N.J.

2007-01-01

1. Ant nuptial flights are central to understanding ant life history and ecology but have been little studied. This study examined the timing of nuptial flights, the synchronicity of nuptial flights (as a potential index of mating strategy), and variation in nuptial flights with elevation and among years in a diverse temperate ant fauna. 2. Flights occurred throughout the year, but were concentrated in the beginning of summer and in early fall (autumn). Relative to the entire flight season, closely related species tended to be more likely than expected by chance to fly at similar times, perhaps because of phylogenetic constraints on life history evolution. 3. Flights were relatively synchronous within species for nearly all species considered, but synchronicity did not appear to be a robust estimate of overall mating strategy. 4. Overall patterns in nuptial flights among species and the timing of flights for individual species varied with elevation, but did not vary greatly among years. 5. Although this study is one of the most comprehensive on the reproductive flight phenologies of ants, much remains to be learned about the causes and consequences of such spatial and temporal variation in flight phenology. ?? 2007 The Royal Entomological Society.

Time Domain Tool Validation Using ARES I-X Flight Data

NASA Technical Reports Server (NTRS)

Hough, Steven; Compton, James; Hannan, Mike; Brandon, Jay

2011-01-01

The ARES I-X vehicle was launched from NASA's Kennedy Space Center (KSC) on October 28, 2009 at approximately 11:30 EDT. ARES I-X was the first test flight for NASA s ARES I launch vehicle, and it was the first non-Shuttle launch vehicle designed and flown by NASA since Saturn. The ARES I-X had a 4-segment solid rocket booster (SRB) first stage and a dummy upper stage (US) to emulate the properties of the ARES I US. During ARES I-X pre-flight modeling and analysis, six (6) independent time domain simulation tools were developed and cross validated. Each tool represents an independent implementation of a common set of models and parameters in a different simulation framework and architecture. Post flight data and reconstructed models provide the means to validate a subset of the simulations against actual flight data and to assess the accuracy of pre-flight dispersion analysis. Post flight data consists of telemetered Operational Flight Instrumentation (OFI) data primarily focused on flight computer outputs and sensor measurements as well as Best Estimated Trajectory (BET) data that estimates vehicle state information from all available measurement sources. While pre-flight models were found to provide a reasonable prediction of the vehicle flight, reconstructed models were generated to better represent and simulate the ARES I-X flight. Post flight reconstructed models include: SRB propulsion model, thrust vector bias models, mass properties, base aerodynamics, and Meteorological Estimated Trajectory (wind and atmospheric data). The result of the effort is a set of independently developed, high fidelity, time-domain simulation tools that have been cross validated and validated against flight data. This paper presents the process and results of high fidelity aerospace modeling, simulation, analysis and tool validation in the time domain.

14 CFR 121.503 - Flight time limitations: Pilots: airplanes.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Flight time limitations: Pilots: airplanes... Operations § 121.503 Flight time limitations: Pilots: airplanes. (a) A certificate holder conducting supplemental operations may schedule a pilot to fly in an airplane for eight hours or less during any 24...

14 CFR 121.503 - Flight time limitations: Pilots: airplanes.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Flight time limitations: Pilots: airplanes... Operations § 121.503 Flight time limitations: Pilots: airplanes. (a) A certificate holder conducting supplemental operations may schedule a pilot to fly in an airplane for eight hours or less during any 24...

14 CFR 121.503 - Flight time limitations: Pilots: airplanes.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Flight time limitations: Pilots: airplanes... Operations § 121.503 Flight time limitations: Pilots: airplanes. (a) A certificate holder conducting supplemental operations may schedule a pilot to fly in an airplane for eight hours or less during any 24...

14 CFR 121.503 - Flight time limitations: Pilots: airplanes.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Flight time limitations: Pilots: airplanes... Operations § 121.503 Flight time limitations: Pilots: airplanes. (a) A certificate holder conducting supplemental operations may schedule a pilot to fly in an airplane for eight hours or less during any 24...

14 CFR 121.503 - Flight time limitations: Pilots: airplanes.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Flight time limitations: Pilots: airplanes... Operations § 121.503 Flight time limitations: Pilots: airplanes. (a) A certificate holder conducting supplemental operations may schedule a pilot to fly in an airplane for eight hours or less during any 24...

Time-of-flight mass spectrometry: Introduction to the basics.

PubMed

Boesl, Ulrich

2017-01-01

The intention of this tutorial is to introduce into the basic concepts of time-of-flight mass spectrometry, beginning with the most simple single-stage ion source with linear field-free drift region and continuing with two-stage ion sources combined with field-free drift regions and ion reflectors-the so-called reflectrons. Basic formulas are presented and discussed with the focus on understanding the physical relations of geometric and electric parameters, initial distribution of ionic parameters, ion flight times, and ion flight time incertitude. This tutorial is aimed to help the applicant to identify sources of flight time broadening which limit good mass resolution and sources of ion losses which limit sensitivity; it is aimed to stimulate creativity for new experimental approaches by discussing a choice of instrumental options and to encourage those who toy with the idea to build an own time-of-flight mass spectrometer. Large parts of mathematics are shifted into a separate chapter in order not to overburden the text with too many mathematical deviations. Rather, thumb-rule formulas are supplied for first estimations of geometry and potentials when designing a home-built instrument, planning experiments, or searching for sources of flight time broadening. © 2016 Wiley Periodicals, Inc. Mass Spec Rev 36:86-109, 2017. © 2016 Wiley Periodicals, Inc.

Coincidence-anticipation timing requirements are different in racket sports.

PubMed

Akpinar, Selçuk; Devrilmez, Erhan; Kirazci, Sadettin

2012-10-01

The aim of this study was to compare the coincidence-anticipation timing accuracy of athletes of different racket sports with various stimulus velocity requirements. Ninety players (15 girls, 15 boys for each sport) from tennis (M age = 12.4 yr., SD = 1.4), badminton (M age = 12.5 yr., SD = 1.4), and table tennis (M age = 12.4 yr., SD = 1.2) participated in this study. Three different stimulus velocities, low, moderate, and high, were used to simulate the velocity requirements of these racket sports. Tennis players had higher accuracy when they performed under the low stimulus velocity compared to badminton and table tennis players. Badminton players performed better under the moderate speed comparing to tennis and table tennis players. Table tennis players had better performance than tennis and badminton players under the high stimulus velocity. Therefore, visual and motor systems of players from different racket sports may adapt to a stimulus velocity in coincidence-anticipation timing, which is specific to each type of racket sports.

First-principles equation-of-state table of silicon and its effects on high-energy-density plasma simulations

NASA Astrophysics Data System (ADS)

Hu, S. X.; Gao, R.; Ding, Y.; Collins, L. A.; Kress, J. D.

2017-04-01

Using density-functional theory-based molecular-dynamics simulations, we have investigated the equation of state for silicon in a wide range of plasma density and temperature conditions of ρ =0.001 -500 g /c m3 and T =2000 -108K . With these calculations, we have established a first-principles equation-of-state (FPEOS) table of silicon for high-energy-density (HED) plasma simulations. When compared with the widely used SESAME-EOS model (Table 3810), we find that the FPEOS-predicted Hugoniot is ˜20% softer; for off-Hugoniot plasma conditions, the pressure and internal energy in FPEOS are lower than those of SESAME EOS for temperatures above T ≈ 1-10 eV (depending on density), while the former becomes higher in the low-T regime. The pressure difference between FPEOS and SESAME 3810 can reach to ˜50%, especially in the warm-dense-matter regime. Implementing the FPEOS table of silicon into our hydrocodes, we have studied its effects on Si-target implosions. When compared with the one-dimensional radiation-hydrodynamics simulation using the SESAME 3810 EOS model, the FPEOS simulation showed that (1) the shock speed in silicon is ˜10% slower; (2) the peak density of an in-flight Si shell during implosion is ˜20% higher than the SESAME 3810 simulation; (3) the maximum density reached in the FPEOS simulation is ˜40% higher at the peak compression; and (4) the final areal density and neutron yield are, respectively, ˜30% and ˜70% higher predicted by FPEOS versus the traditional simulation using SESAME 3810. All of these features can be attributed to the larger compressibility of silicon predicted by FPEOS. These results indicate that an accurate EOS table, like the FPEOS presented here, could be essential for the precise design of targets for HED experiments.

First-principles equation-of-state table of silicon and its effects on high-energy-density plasma simulations

DOE PAGES

Hu, S. X.; Gao, R.; Ding, Y.; ...

2017-04-21

Using density-functional theory–based molecular-dynamics simulations, we have investigated the equation of state for silicon in a wide range of plasma density and temperature conditions of ρ=0.001–500g/cm 3 and T=2000–10 8K. With these calculations, we have established a first-principles equation-of-state (FPEOS) table of silicon for high-energy-density (HED) plasma simulations. When compared with the widely used SESAME-EOS model (Table 3810), we find that the FPEOS-predicted Hugoniot is ~20% softer; for off-Hugoniot plasma conditions, the pressure and internal energy in FPEOS are lower than those of SESAME EOS for temperatures above T ≈ 1–10 eV (depending on density), while the former becomes highermore » in the low- T regime. The pressure difference between FPEOS and SESAME 3810 can reach to ~50%, especially in the warm-dense-matter regime. Implementing the FPEOS table of silicon into our hydrocodes, we have studied its effects on Si-target implosions. When compared with the one-dimensional radiation-hydrodynamics simulation using the SESAME 3810 EOS model, the FPEOS simulation showed that (1) the shock speed in silicon is ~10% slower; (2) the peak density of an in-flight Si shell during implosion is ~20% higher than the SESAME 3810 simulation; (3) the maximum density reached in the FPEOS simulation is ~40% higher at the peak compression; and (4) the final areal density and neutron yield are, respectively, ~30% and ~70% higher predicted by FPEOS versus the traditional simulation using SESAME 3810. All of these features can be attributed to the larger compressibility of silicon predicted by FPEOS. Furthermore, these results indicate that an accurate EOS table, like the FPEOS presented here, could be essential for the precise design of targets for HED experiments.« less

First-principles equation-of-state table of silicon and its effects on high-energy-density plasma simulations

DOE Office of Scientific and Technical Information (OSTI.GOV)

Hu, S. X.; Gao, R.; Ding, Y.

Using density-functional theory–based molecular-dynamics simulations, we have investigated the equation of state for silicon in a wide range of plasma density and temperature conditions of ρ=0.001–500g/cm 3 and T=2000–10 8K. With these calculations, we have established a first-principles equation-of-state (FPEOS) table of silicon for high-energy-density (HED) plasma simulations. When compared with the widely used SESAME-EOS model (Table 3810), we find that the FPEOS-predicted Hugoniot is ~20% softer; for off-Hugoniot plasma conditions, the pressure and internal energy in FPEOS are lower than those of SESAME EOS for temperatures above T ≈ 1–10 eV (depending on density), while the former becomes highermore » in the low- T regime. The pressure difference between FPEOS and SESAME 3810 can reach to ~50%, especially in the warm-dense-matter regime. Implementing the FPEOS table of silicon into our hydrocodes, we have studied its effects on Si-target implosions. When compared with the one-dimensional radiation-hydrodynamics simulation using the SESAME 3810 EOS model, the FPEOS simulation showed that (1) the shock speed in silicon is ~10% slower; (2) the peak density of an in-flight Si shell during implosion is ~20% higher than the SESAME 3810 simulation; (3) the maximum density reached in the FPEOS simulation is ~40% higher at the peak compression; and (4) the final areal density and neutron yield are, respectively, ~30% and ~70% higher predicted by FPEOS versus the traditional simulation using SESAME 3810. All of these features can be attributed to the larger compressibility of silicon predicted by FPEOS. Furthermore, these results indicate that an accurate EOS table, like the FPEOS presented here, could be essential for the precise design of targets for HED experiments.« less

In-flight sleep, pilot fatigue and Psychomotor Vigilance Task performance on ultra-long range versus long range flights.

PubMed

Gander, Philippa H; Signal, T Leigh; van den Berg, Margo J; Mulrine, Hannah M; Jay, Sarah M; Jim Mangie, Captain

2013-12-01

This study evaluated whether pilot fatigue was greater on ultra-long range (ULR) trips (flights >16 h on 10% of trips in a 90-day period) than on long range (LR) trips. The within-subjects design controlled for crew complement, pattern of in-flight breaks, flight direction and departure time. Thirty male Captains (mean age = 54.5 years) and 40 male First officers (mean age = 48.0 years) were monitored on commercial passenger flights (Boeing 777 aircraft). Sleep was monitored (actigraphy, duty/sleep diaries) from 3 days before the first study trip to 3 days after the second study trip. Karolinska Sleepiness Scale, Samn-Perelli fatigue ratings and a 5-min Psychomotor Vigilance Task were completed before, during and after every flight. Total sleep in the 24 h before outbound flights and before inbound flights after 2-day layovers was comparable for ULR and LR flights. All pilots slept on all flights. For each additional hour of flight time, they obtained an estimated additional 12.3 min of sleep. Estimated mean total sleep was longer on ULR flights (3 h 53 min) than LR flights (3 h 15 min; P(F) = 0.0004). Sleepiness ratings were lower and mean reaction speed was faster at the end of ULR flights. Findings suggest that additional in-flight sleep mitigated fatigue effectively on longer flights. Further research is needed to clarify the contributions to fatigue of in-flight sleep versus time awake at top of descent. The study design was limited to eastward outbound flights with two Captains and two First Officers. Caution must be exercised when extrapolating to different operations. © 2013 European Sleep Research Society.

The NASA Lewis integrated propulsion and flight control simulator

NASA Technical Reports Server (NTRS)

Bright, Michelle M.; Simon, Donald L.

1991-01-01

A new flight simulation facility was developed at NASA-Lewis. The purpose of this flight simulator is to allow integrated propulsion control and flight control algorithm development and evaluation in real time. As a preliminary check of the simulator facility capabilities and correct integration of its components, the control design and physics models for a short take-off and vertical landing fighter aircraft model were shown, with their associated system integration and architecture, pilot vehicle interfaces, and display symbology. The initial testing and evaluation results show that this fixed based flight simulator can provide real time feedback and display of both airframe and propulsion variables for validation of integrated flight and propulsion control systems. Additionally, through the use of this flight simulator, various control design methodologies and cockpit mechanizations can be tested and evaluated in a real time environment.

Flight code validation simulator

NASA Astrophysics Data System (ADS)

Sims, Brent A.

1996-05-01

An End-To-End Simulation capability for software development and validation of missile flight software on the actual embedded computer has been developed utilizing a 486 PC, i860 DSP coprocessor, embedded flight computer and custom dual port memory interface hardware. This system allows real-time interrupt driven embedded flight software development and checkout. The flight software runs in a Sandia Digital Airborne Computer and reads and writes actual hardware sensor locations in which Inertial Measurement Unit data resides. The simulator provides six degree of freedom real-time dynamic simulation, accurate real-time discrete sensor data and acts on commands and discretes from the flight computer. This system was utilized in the development and validation of the successful premier flight of the Digital Miniature Attitude Reference System in January of 1995 at the White Sands Missile Range on a two stage attitude controlled sounding rocket.

Computer Simulation of Ejection Seat Performance and Preliminary Correlation with Empirical Data

DTIC Science & Technology

1980-04-01

L. . .. . 3 I r AFFDL-TR-79-31 50 TABLE OF CONTENTS SECTION PAGE I INTRODUCTION 1 1I SAFEST COMPUTER PROGRAM DESCRIPTION 8 III HITECH ...ZEARTH vs TIME 49E-I1A 53 34 ZEARTH vs XEARTH 49E-IIA 54 AFFDL-TR-79-3150 LIST OF TABLES TABLE PAGE 1 ACES II EVENT-TIME SEQUENCE 3 2 HITECH 49E-JlF...Initial Conditions 13 3 HITECH 49E-I1A Initial Conditions 14 4 HITECH Program Test Data Summary 15 5 SAFEST 49E-JIF Initial Conditions 20 6 SAFEST 49E-IIA

Developmental times and life table statistics of Aulacorthum solani (Hemiptera: Aphididae) at six constant temperatures, with recommendations on the application of temperature-dependent development models

USDA-ARS?s Scientific Manuscript database

Developmental rates and age-specific life tables were determined for Aulacorthum solani (Kaltenbach) (known as foxglove aphid or glasshouse potato aphid) at 6 constant temperatures feeding on pansy (Viola × wittrockiana) (Gams.). Previously, there were no complete life table studies of this species...

Eye on the Ball: Table Tennis as a Pro-Health Form of Leisure-Time Physical Activity

PubMed Central

Buchholtz, Sonia; Krzepota, Justyna

2018-01-01

Background: The article is devoted to an analysis of leisure-time (amateur) table tennis in Poland, its practitioners and the regularities of their activity. Methods: The study examined 12,406 persons in 4689 households (representative for the population). We used binary logistic regression and descriptive statistics in order to identify the patterns and determinants of table-tennis practice in Poland. Results: Table tennis is practised by 2.8% of population, and by 6.6% of physically active Poles. Among adults it is predominantly an occasional recreational game, not performed as a sport per se. Among children, it is often the part of physical education (PE) classes. Statistically significant predictors of contact with table tennis are: gender, age, income, place of residence, children in the household and being a student. Conclusions: Due to the undeniable benefits of table tennis (health, pleasure, personal and social development), the sport is recommended for use as a tool in increasing the (overall low) physical activity of Poles. Its popularization requires promotion in the media (as a health-oriented activity) and using various channels, including public places, the workplace (as part of corporate social responsibility) and physical education classes at school. PMID:29649160

Eye on the Ball: Table Tennis as a Pro-Health Form of Leisure-Time Physical Activity.

PubMed

Biernat, Elżbieta; Buchholtz, Sonia; Krzepota, Justyna

2018-04-12

Background: The article is devoted to an analysis of leisure-time (amateur) table tennis in Poland, its practitioners and the regularities of their activity. Methods: The study examined 12,406 persons in 4689 households (representative for the population). We used binary logistic regression and descriptive statistics in order to identify the patterns and determinants of table-tennis practice in Poland. Results: Table tennis is practised by 2.8% of population, and by 6.6% of physically active Poles. Among adults it is predominantly an occasional recreational game, not performed as a sport per se. Among children, it is often the part of physical education (PE) classes. Statistically significant predictors of contact with table tennis are: gender, age, income, place of residence, children in the household and being a student. Conclusions: Due to the undeniable benefits of table tennis (health, pleasure, personal and social development), the sport is recommended for use as a tool in increasing the (overall low) physical activity of Poles. Its popularization requires promotion in the media (as a health-oriented activity) and using various channels, including public places, the workplace (as part of corporate social responsibility) and physical education classes at school.

Recharge characteristics of an unconfined aquifer from the rainfall-water table relationship

NASA Astrophysics Data System (ADS)

Viswanathan, M. N.

1984-02-01

The determination of recharge levels of unconfined aquifers, recharged entirely by rainfall, is done by developing a model for the aquifer that estimates the water-table levels from the history of rainfall observations and past water-table levels. In the present analysis, the model parameters that influence the recharge were not only assumed to be time dependent but also to have varying dependence rates for various parameters. Such a model is solved by the use of a recursive least-squares method. The variable-rate parameter variation is incorporated using a random walk model. From the field tests conducted at Tomago Sandbeds, Newcastle, Australia, it was observed that the assumption of variable rates of time dependency of recharge parameters produced better estimates of water-table levels compared to that with constant-recharge parameters. It was observed that considerable recharge due to rainfall occurred on the very same day of rainfall. The increase in water-table level was insignificant for subsequent days of rainfall. The level of recharge very much depends upon the intensity and history of rainfall. Isolated rainfalls, even of the order of 25 mm day -1, had no significant effect on the water-table levels.

14 CFR 135.269 - Flight time limitations and rest requirements: Unscheduled three- and four-pilot crews.

Code of Federal Regulations, 2010 CFR

2010-01-01

... requirements: Unscheduled three- and four-pilot crews. 135.269 Section 135.269 Aeronautics and Space FEDERAL... four-pilot crews. (a) No certificate holder may assign any flight crewmember, and no flight crewmember may accept an assignment, for flight time as a member of a three- or four-pilot crew if that...

Examining the Effect of Instructor Experience on Flight Training Time

ERIC Educational Resources Information Center

Polstra, Philip A., Sr.

2012-01-01

Maximizing training efficiency is desirable in many areas of business. The ever increasing costs of flight training combined with a predicted shortage of pilots have resulted in steps being taken to improve flight training efficiency. In the past, the majority of airline pilots received their flight training in the military. Over time a growing…

On the Use of Calibration Explosions at the Former Semipalatinsk Test Site for Compiling a Travel-time Model of the Crust and Upper Mantle

NASA Astrophysics Data System (ADS)

Belyashova, N. N.; Shacilov, V. I.; Mikhailova, N. N.; Komarov, I. I.; Sinyova, Z. I.; Belyashov, A. V.; Malakhova, M. N.

- Two chemical calibration explosions, conducted at the former Semipalatinsk nuclear test site in 1998 with charges of 25 tons and 100 tons TNT, have been used for developing travel-time curves and generalized one-dimensional velocity models of the crust and upper mantle of the platform region of Kazakhstan. The explosions were recorded by a number of digital seismic stations, located in Kazakhstan at distances ranging from 0 to 720km. The travel-time tables developed in this paper cover the phases P, Pn, Pg, S, Sn, Lg in a range of 0-740km and the velocity models apply to the crust down to 44km depth and to the mantle down to 120km. A comparison of the compiled travel-time tables with existing travel-time tables of CSE and IASPEI91 is presented.

14 CFR 61.1 - Applicability and definitions.

Code of Federal Regulations, 2014 CFR

2014-01-01

....2. Aeronautical experience means pilot time obtained in an aircraft, flight simulator, or flight... from an authorized instructor in an aircraft, flight simulator, or flight training device; or (iii) Gives training as an authorized instructor in an aircraft, flight simulator, or flight training device...

A rule-based system for real-time analysis of control systems

NASA Astrophysics Data System (ADS)

Larson, Richard R.; Millard, D. Edward

1992-10-01

An approach to automate the real-time analysis of flight critical health monitoring and system status is being developed and evaluated at the NASA Dryden Flight Research Facility. A software package was developed in-house and installed as part of the extended aircraft interrogation and display system. This design features a knowledge-base structure in the form of rules to formulate interpretation and decision logic of real-time data. This technique has been applied for ground verification and validation testing and flight testing monitoring where quick, real-time, safety-of-flight decisions can be very critical. In many cases post processing and manual analysis of flight system data are not required. The processing is described of real-time data for analysis along with the output format which features a message stack display. The development, construction, and testing of the rule-driven knowledge base, along with an application using the X-31A flight test program, are presented.

A rule-based system for real-time analysis of control systems

NASA Technical Reports Server (NTRS)

Larson, Richard R.; Millard, D. Edward

1992-01-01

An approach to automate the real-time analysis of flight critical health monitoring and system status is being developed and evaluated at the NASA Dryden Flight Research Facility. A software package was developed in-house and installed as part of the extended aircraft interrogation and display system. This design features a knowledge-base structure in the form of rules to formulate interpretation and decision logic of real-time data. This technique has been applied for ground verification and validation testing and flight testing monitoring where quick, real-time, safety-of-flight decisions can be very critical. In many cases post processing and manual analysis of flight system data are not required. The processing is described of real-time data for analysis along with the output format which features a message stack display. The development, construction, and testing of the rule-driven knowledge base, along with an application using the X-31A flight test program, are presented.

Neural integration underlying a time-compensated sun compass in the migratory monarch butterfly

PubMed Central

Shlizerman, Eli; Phillips-Portillo, James; Reppert, Steven M.

2016-01-01

Migrating Eastern North American monarch butterflies use a time-compensated sun compass to adjust their flight to the southwest direction. While the antennal genetic circadian clock and the azimuth of the sun are instrumental for proper function of the compass, it is unclear how these signals are represented on a neuronal level and how they are integrated to produce flight control. To address these questions, we constructed a receptive field model of the compound eye that encodes the solar azimuth. We then derived a neural circuit model, which integrates azimuthal and circadian signals to correct flight direction. The model demonstrates an integration mechanism, which produces robust trajectories reaching the southwest regardless of the time of day and includes a configuration for remigration. Comparison of model simulations with flight trajectories of butterflies in a flight simulator shows analogous behaviors and affirms the prediction that midday is the optimal time for migratory flight. PMID:27149852