Validation of MIL-F-9490D. General Specification for Flight Control System for Piloted Military Aircraft. Volume III. C-5A Heavy Logistics Transport Validation

DTIC Science & Technology

1977-04-01

U* AFFDL-TR-77-7 0 VOLUME III " 󈧦 VALIDATION OF MIL-F-9490D - GENERAL SPECIFICATION FOR FLIGHT CONTROL SYSTEM "FOR PILOTED MILITARY AIRCRAFT VOLUME...ý A1O 1 C I\\.FFBL Ti(-77-7. Vol. III f Validatio~n of UL-P-9-490D#,*. General Spacificatior "~inal 1’l -_t e for Flight ContrsA Zyn’om for Piloted...cation MIL-F-9490D (USAF), "Flight Control Systems - Design, Installation and Test of Piloted Aircraft, General Specifications for," dated 6 June 1975, by

F-18 chase craft with NASA test pilots Schneider and Fulton

NASA Technical Reports Server (NTRS)

1992-01-01

Ed Schneider, (left), is the project pilot for the F-18 High Angle of Attack program at NASA's Dryden Flight Research Center, Edwards, California. He has been a NASA research pilot at Dryden since 1983. In addition to his assignment with the F-18 High Angle of Attack program, Schneider is a project pilot for the F-15B aeronautical research aircraft, the NASA NB-52B launch aircraft, and the SR-71 'Blackbird' aircraft. He is a Fellow and was the 1994 President of the Society of Experimental Test Pilots. In 1996 he was awarded the NASA Exceptional Service Medal. Schneider is seen here with Fitzhugh L. Fulton Jr., (right), who was a civilian research pilot at Dryden. from August 1, 1966, until July 3, 1986, following 23 years of service as a pilot in the U.S. Air Force. Fulton was the project pilot on all early tests of the 747 Shuttle Carrier Aircraft (SCA) used to air launch the Space Shuttle prototype Enterprise in the Approach and Landing Tests (ALT) at Dryden in l977. For his work in the ALT program, Fulton received NASA's Exceptional Service Medal. He also received the Exceptional Service Medal again in 1983 for flying the 747 SCA during the European tour of the Space Shuttle Enterprise. During his career at Dryden, Fulton was project pilot on NASA's NB-52B launch aircraft used to air launch a variety of piloted and unpiloted research aircraft, including the X-15s and lifting bodies. He flew the XB-70 prototype supersonic bomber on both NASA-USAF tests and NASA research flights during the late 1960s, attaining speeds exceeding Mach 3. He was also a project pilot on the YF-12A and YF-12C research program from April 14, 1969, until September 25, 1978. The F/A-18 Hornet seen behind them is used primarily as a safety chase and support aircraft at NASA's Dryden Flight Research Center, Edwards, Calif. As support aircraft, the F-18's are used for safety chase, pilot proficiency and aerial photography. As a safety chase aircraft, F-18's, flown by research pilots, accompany research missions as another 'set of eyes' to visually observe the research event, experiment or test to help make sure the flights are carried out safely. The 'chase' pilots are in constant communication with the research pilots and mission control to report abnormalities that may be seen from the support aircraft. Pilots must also stay proficient by flying a certain number of missions per month. F-18's are used for this. A two-seat support aircraft is also used when research missions require an engineer or photographer on the flights.

Castine Report S-15 Project: Shipbuilding Standards

DTIC Science & Technology

1976-01-01

Fixed Square Windows Ships” Extruded Aluminium Alloy Square Windows “ Ships” Foot Steps Ships* Wooden Hand Rail . Pilot Ladders Panama Canal Pilot...Platforms Aluminium Alloy Accommodation Ladders Mouth Pieces for Voice Tube Chain Drwe Type Telegraphs Fittings for Steam Whistle Llfeboats Radial Type...Cast Steel Angle Valves for Compressed Air F 8001-1957 F 8002-1967 F 8003.1975 F 8004.1975 F 8011 1966 F 8013.1969 F 8101.1969 F 8401.1970 F

Tom McMurtry - chief of Dryden Flight Operations with STS mated to 747 SCA

NASA Technical Reports Server (NTRS)

1991-01-01

Thomas C. McMurtry in front of the 747 Shuttle Carrier Aircraft. He graduated in June 1957 from the University of Notre Dame with a Bachelor of Science degree in Mechanical Engineering. McMurtry had been part of the university's Navy ROTC program, and after graduation he joined the Navy as a pilot. Before retiring from the Navy in 1964 as a Lieutenant, he graduated from the U.S. Navy Test Pilot School, and had flown such aircraft as the F9F, A3D, A4D, F3D, F-8, A-6, and S-2. McMurtry was then a consultant for the Lockheed Corporation until joining NASA as a research pilot in 1967. While at the Dryden Flight Research Center, he was co-project pilot on the F-8 Digital Fly-By-Wire program, and the 747 Shuttle Carrier Aircraft, as well as project pilot on the F-15 Digital Electronic Engine Control (DEEC) project, the KC-135 Winglets, the F-8 Supercritical Wing project, and the AD-1 Oblique Wing Project. He also made research flights in NASA's YF-12C aircraft (actually a modified SR-71). McMurtry made the last glide flight of the X-24B lifting body on November 26, 1975, and was co-pilot of the 747 Shuttle Carrier Aircraft on the first free flight of the space shuttle Enterprise on August 12, 1977. He was involved in several remotely piloted research vehicle programs, including the FAA/NASA 720 Controlled Impact Demonstration and the 3/8 F-15 Spin Research Vehicle. During McMurtry's 32 years as a pilot and manager at Dryden, he received numerous awards. These include the NASA Exceptional Service Award for his work on the F-8 Supercritical Wing, and the Iven C. Kincheloe Award from the Society of Experimental Test Pilots for his role as chief pilot on the AD-1 project, the NASA Distinguished Service Medal, and the 1999 Milton O. Thomson Lifetime Achievement Award. McMurtry also held a number of management positions at Dryden, including Chief Pilot, Director of Flight Operations, Associate Director of Flight Operations, and was the acting Chief Engineer at the time of his retirement on June 3, 1999. Since becoming a pilot in 1958, he logged more than 11,000 hours of flight time, in aircraft ranging from a WACO open cockpit biplane to a Mach 3 YF-12C, as well as navy trainers, fighters and attack airplanes, the U-2, F-104 and FA-18 chase planes, and diverse research aircraft. McMurtry's fondest memories are of early morning take-offs from Edwards AFB.

Prediction of situational awareness in F-15 pilots.

PubMed

Carretta, T R; Perry, D C; Ree, M J

1996-01-01

Situational awareness (SA) is a skill often deemed essential to pilot performance in both combat and noncombat flying. A study was conducted to determine if SA in U.S. Air Force F-15 pilots could be predicted. The participants were 171 active duty F-15 A/C pilots who completed a test battery representative of various psychological constructs proposed or demonstrated to be valid for the prediction of performance in a wide variety of military and civilian jobs. These predictors encompassed measures of cognitive ability, psychomotor ability, and personality. Supervisor and peer ratings of SA were collected. Supervisors and peers showed substantial agreement on the SA ratings of the pilots. The first unrotated principle component extracted from the supervisor and peer ratings accounted for 92.5% of the variability of ratings. The unrotated first principal component served as the SA criterion. Flying experience measured in number of F-15 hours was the best predictor of SA. After controlling for the effects of F-15 flying hours, the measures of general cognitive ability based on working memory, spatial reasoning, and divided attention were found to be predictive of SA. Psychomotor and personality measures were not predictive. With additional F-15 flying hours it is expected that pilots would improve their ratings of SA.

75 FR 70224 - New York Tidal Energy Company; Notice Concluding Pre-Filing Process and Approving Process Plan...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-11-17

... DEPARTMENT OF ENERGY Federal Energy Regulatory Commission [Project No. 12665-003] New York Tidal... Tidal Energy Company. e. Name of Project: East River Tidal Energy Pilot Project. f. Location: In the.... Filed Pursuant to: 18 CFR 5.3 of the Commission's regulations. h. Applicant Contact: Daniel Power...

M2-F3 with test pilot John A. Manke

NASA Image and Video Library

1972-12-20

NASA research pilot John A. Manke is seen here in front of the M2-F3 Lifting Body. Manke was hired by NASA on May 25, 1962, as a flight research engineer. He was later assigned to the pilot's office and flew various support aircraft including the F-104, F5D, F-111 and C-47. After leaving the Marine Corps in 1960, Manke worked for Honeywell Corporation as a test engineer for two years before coming to NASA. He was project pilot on the X-24B and also flew the HL-10, M2-F3, and X-24A lifting bodies. John made the first supersonic flight of a lifting body and the first landing of a lifting body on a hard surface runway. Manke served as Director of the Flight Operations and Support Directorate at the Dryden Flight Research Center prior to its integration with Ames Research Center in October 1981. After this date John was named to head the joint Ames-Dryden Directorate of Flight Operations. He also served as site manager of the NASA Ames-Dryden Flight Research Facility. John is a member of the Society of Experimental Test Pilots. He retired on April 27, 1984.

Cognitive and Neural Effects of Vision-Based Speed-of-Processing Training in Older Adults with Amnestic Mild Cognitive Impairment: A Pilot Study.

PubMed

Lin, Feng; Heffner, Kathi L; Ren, Ping; Tivarus, Madalina E; Brasch, Judith; Chen, Ding-Geng; Mapstone, Mark; Porsteinsson, Anton P; Tadin, Duje

2016-06-01

To examine the cognitive and neural effects of vision-based speed-of-processing (VSOP) training in older adults with amnestic mild cognitive impairment (aMCI) and contrast those effects with an active control (mental leisure activities (MLA)). Randomized single-blind controlled pilot trial. Academic medical center. Individuals with aMCI (N = 21). Six-week computerized VSOP training. Multiple cognitive processing measures, instrumental activities of daily living (IADLs), and two resting state neural networks regulating cognitive processing: central executive network (CEN) and default mode network (DMN). VSOP training led to significantly greater improvements in trained (processing speed and attention: F1,19  = 6.61, partial η(2)  = 0.26, P = .02) and untrained (working memory: F1,19  = 7.33, partial η(2)  = 0.28, P = .01; IADLs: F1,19  = 5.16, partial η(2)  = 0.21, P = .03) cognitive domains than MLA and protective maintenance in DMN (F1, 9  = 14.63, partial η(2)  = 0.62, P = .004). VSOP training, but not MLA, resulted in a significant improvement in CEN connectivity (Z = -2.37, P = .02). Target and transfer effects of VSOP training were identified, and links between VSOP training and two neural networks associated with aMCI were found. These findings highlight the potential of VSOP training to slow cognitive decline in individuals with aMCI. Further delineation of mechanisms underlying VSOP-induced plasticity is necessary to understand in which populations and under what conditions such training may be most effective. © 2016, Copyright the Authors Journal compilation © 2016, The American Geriatrics Society.

Strong and consistently synergistic inactivation of spores of spoilage-associated Bacillus and Geobacillus spp. by high pressure and heat compared with inactivation by heat alone.

PubMed

Olivier, S A; Bull, M K; Stone, G; van Diepenbeek, R J; Kormelink, F; Jacops, L; Chapman, B

2011-04-01

The inactivation of spores of four low-acid food spoilage organisms by high pressure thermal (HPT) and thermal-only processing was compared on the basis of equivalent thermal lethality calculated at a reference temperature of 121.1°C (F(z)(121.1)(°)(C, 0.1 MPa or 600 MPa)) and characterized as synergistic, not different or protective. In addition, the relative resistances of spores of the different spoilage microorganisms to HPT processing were compared. Processing was performed and inactivation was compared in both laboratory and pilot scale systems and in model (diluted) and actual food products. Where statistical comparisons could be made, at least 4 times and up to around 190 times more inactivation (log(10) reduction/minute at F(T)(z)(121.1)(°)(C)) of spores of Bacillus amyloliquefaciens, Bacillus sporothermodurans, and Geobacillus stearothermophilus was achieved using HPT, indicating a strong synergistic effect of high pressure and heat. Bacillus coagulans spores were also synergistically inactivated in diluted and undiluted Bolognese sauce but were protected by pressure against thermal inactivation in undiluted cream sauce. Irrespective of the response characterization, B. coagulans and B. sporothermodurans were identified as the most HPT-resistant isolates in the pilot scale and laboratory scale studies, respectively, and G. stearothermophilus as the least in both studies and all products. This is the first study to comprehensively quantitatively characterize the responses of a range of spores of spoilage microorganisms as synergistic (or otherwise) using an integrated thermal-lethality approach (F(T)(z)). The use of the F(T)(z) approach is ultimately important for the translation of commercial minimum microbiologically safe and stable thermal processes to HPT processes.

F-8 SCW on ramp with test pilot Tom McMurtry

NASA Image and Video Library

1972-12-20

A Vought F-8A Crusader was selected by NASA as the testbed aircraft (designated TF-8A) to install an experimental Supercritical Wing (SCW) in place of the conventional wing. The unique design of the Supercritical Wing reduces the effect of shock waves on the upper surface near Mach 1, which in turn reduces drag. In this photograph the TF-8A Crusader with Supercritical Wing is shown on the ramp with project pilot Tom McMurtry standing beside it. McMurtry received NASA's Exceptional Service Medal for his work on the F-8 SCW aircraft. He also flew the AD-1, F-15 Digital Electronic Engine Control, the KC-130 winglets, the F-8 Digital Fly-By-Wire and other flight research aircraft including the remotely piloted 720 Controlled Impact Demonstration and sub-scale F-15 research projects. In addition, McMurtry was the 747 co-pilot for the Shuttle Approach and Landing Tests and made the last glide flight in the X-24B. McMurtry was Dryden’s Director for Flight Operations from 1986 to 1998, when he became Associate Director for Operations at NASA Dryden. In 1982, McMurtry received the Iven C. Kincheloe Award from the Society of Experimental Test Pilots for his contributions as project pilot on the AD-1 Oblique Wing program. In 1998 he was named as one of the honorees at the Lancaster, Calif., ninth Aerospace Walk of Honor ceremonies. In 1999 he was awarded the NASA Distinguished Service Medal. He retired in 1999 after a distinguished career as pilot and manager at Dryden that began in 1967.

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

Logan, A.; Devenny, D.; Porcari, G.

The activities carried out and the results obtained from a 15 tons/hour oil sands extraction pilot plant operated in Fort McMurray in Northern Alberta are described. The process is the Rio Tinto TIL Holding S.A. (RTR)/Gulf Canada Lt. Oil Sands Extraction Process. It is a modified hot water extraction process. It is used to extract bitumen from Athabasca oil sands. The test ran from July to December 1981 through ambient conditions ranging from plus 38/sup 0/C to minus 30/sup 0/C (100/sup 0/F to -22/sup 0/F). The process, the on-site facilities, the test program, an analysis of plant performance, an appraisalmore » of the process economics, and an evaluation of its potential application are described.« less

Flight Hour Reductions in Fleet Replacement Pilot Training through Simulation.

ERIC Educational Resources Information Center

Smode, Alfred F.

A project was undertaken to integrate the 2F87F operational flight trainer into the program for training replacement patrol plane pilots. The objectives were to determine the potential of the simulator as a substitute environment for learning aircraft tasks and to effectively utilize the simulator in pilot training. The students involved in the…

Pilot Plant Makes Oxygen Difluoride

NASA Technical Reports Server (NTRS)

Humphrey, Marshall F.; Lawton, Emil A.

1989-01-01

Pilot plant makes oxygen difluoride highly-energetic, space-storable oxidizer not made commercially. Designed to handle reactants, product, and byproduct, most of which highly reactive, corrosive, and toxic. Oxygen difluoride evolves continuously from reactor containing potassium hydroxide in water at 10 degree C. Collection tanks alternated; one filled while other drained to storage cylinder. Excess OF2 and F2 dissipated in combustion of charcoal in burn barrel. Toxic byproduct, potassium fluoride, reacted with calcium hydroxide to form nontoxic calcium fluoride and to regenerate potassium hydroxide. Equipment processes toxic, difficult-to-make substance efficiently and safely.

Gender effects in alcohol dependence: an fMRI pilot study examining affective processing.

PubMed

Padula, Claudia B; Anthenelli, Robert M; Eliassen, James C; Nelson, Erik; Lisdahl, Krista M

2015-02-01

Alcohol dependence (AD) has global effects on brain structure and function, including frontolimbic regions regulating affective processing. Preliminary evidence suggests alcohol blunts limbic response to negative affective stimuli and increases activation to positive affective stimuli. Subtle gender differences are also evident during affective processing. Fourteen abstinent AD individuals (8 F, 6 M) and 14 healthy controls (9 F, 5 M), ages 23 to 60, were included in this facial affective processing functional magnetic resonance imaging pilot study. Whole-brain linear regression analyses were performed, and follow-up analyses examined whether AD status significantly predicted depressive symptoms and/or coping. Fearful Condition-The AD group demonstrated reduced activation in the right medial frontal gyrus, compared with controls. Gender moderated the effects of AD in bilateral inferior frontal gyri. Happy Condition-AD individuals had increased activation in the right thalamus. Gender moderated the effects of AD in the left caudate, right middle frontal gyrus, left paracentral lobule, and right lingual gyrus. Interactive AD and gender effects for fearful and happy faces were such that AD men activated more than control men, but AD women activated less than control women. Enhanced coping was associated with greater activation in right medial frontal gyrus during fearful condition in AD individuals. Abnormal affective processing in AD may be a marker of alcoholism risk or a consequence of chronic alcoholism. Subtle gender differences were observed, and gender moderated the effects of AD on neural substrates of affective processing. AD individuals with enhanced coping had brain activation patterns more similar to controls. Results help elucidate the effects of alcohol, gender, and their interaction on affective processing. Copyright © 2015 by the Research Society on Alcoholism.

Gender Effects in Alcohol Dependence: An fMRI Pilot Study Examining Affective Processing

PubMed Central

Padula, Claudia B.; Anthenelli, Robert M.; Eliassen, James C.; Nelson, Erik; Lisdahl, Krista M.

2017-01-01

Background Alcohol dependence (AD) has global effects on brain structure and function, including frontolimbic regions regulating affective processing. Preliminary evidence suggests alcohol blunts limbic response to negative affective stimuli and increases activation to positive affective stimuli. Subtle gender differences are also evident during affective processing. Methods Fourteen abstinent AD individuals (8 F, 6 M) and 14 healthy controls (9 F, 5 M), ages 23 to 60, were included in this facial affective processing functional magnetic resonance imaging pilot study. Whole-brain linear regression analyses were performed, and follow-up analyses examined whether AD status significantly predicted depressive symptoms and/or coping. Results Fearful Condition—The AD group demonstrated reduced activation in the right medial frontal gyrus, compared with controls. Gender moderated the effects of AD in bilateral inferior frontal gyri. Happy Condition—AD individuals had increased activation in the right thalamus. Gender moderated the effects of AD in the left caudate, right middle frontal gyrus, left paracentral lobule, and right lingual gyrus. Interactive AD and gender effects for fearful and happy faces were such that AD men activated more than control men, but AD women activated less than control women. Enhanced coping was associated with greater activation in right medial frontal gyrus during fearful condition in AD individuals. Conclusions Abnormal affective processing in AD may be a marker of alcoholism risk or a consequence of chronic alcoholism. Subtle gender differences were observed, and gender moderated the effects of AD on neural substrates of affective processing. AD individuals with enhanced coping had brain activation patterns more similar to controls. Results help elucidate the effects of alcohol, gender, and their interaction on affective processing. PMID:25684049

Stan Butchart climbing into B-47

NASA Image and Video Library

1954-07-14

From December 10, 1966, until his retirement on February 27, 1976, Stanley P. Butchart served as Chief (later, Director) of Flight Operations at NASA's Flight Research Center (renamed on March 26, 1976, the Hugh L. Dryden Flight Research Center). Initially, his responsibilities in this position included the Research Pilots Branch, a Maintenance and Manufacturing Branch, and an Operations Engineering Branch, the last of which not only included propulsion and electrical/electronic sections but project engineers for the X-15 and lifting bodies. During his tenure, however, the responsibilities of his directorate came to include not only Flight Test Engineering Support but Flight Systems and Loads laboratories. Before becoming Chief of Flight Operations, Butchart had served since June of 1966 as head of the Research Pilots Branch (Chief Pilot) and then as acting chief of Flight Operations. He had joined the Center (then known as the National Advisory Committee for Aeronautics' High-Speed Flight Research Station) as a research pilot on May 10, 1951. During his career as a research pilot, he flew a great variety of research and air-launch aircraft including the D-558-I, D-558-II, B-29 (plus its Navy version, the P2B), X-4, X-5, KC-135, CV-880, CV-990, B-47, B-52, B-747, F-100A, F-101, F-102, F-104, PA-30 Twin Comanche, JetStar, F-111, R4D, B-720, and B-47. Although previously a single-engine pilot, he became the Center's principal multi-engine pilot during a period of air-launches in which the pilot of the air-launch aircraft (B-29 or P2B) basically directed the operations. It was he who called for the chase planes before each drop, directed the positioning of fire rescue vehicles, and released the experimental aircraft after ensuring that all was ready for the drop. As pilot of the B-29 and P2B, Butchart launched the X-1A once, the X-1B 13 times, the X-1E 22 times, and the D-558-II 102 times. In addition, he towed the M2-F1 lightweight lifting body 14 times behind an R4

Pilot Human Factors in Stall/Spin Accidents of Supersonic Fighter Aircraft

NASA Technical Reports Server (NTRS)

Anderson, S. B.; Enevoldson, E. K.; Nguyen, L. T.

1983-01-01

A study has been made of pilot human factors related to stall/spin accidents of supersonic fighter aircraft. The military specifications for flight at high angles of attack are examined. Several pilot human factors problems related to stall/spin are discussed. These problems include (1) unsatisfactory nonvisual warning cues; (2) the inability of the pilot to quickly determine if the aircraft is spinning out of control, or to recognize the type of spin; (3) the inability of the pilot to decide on and implement the correct spin recovery technique; (4) the inability of the pilot to move, caused by high angular rotation; and (5) the tendency of pilots to wait too long in deciding to abandon the irrecoverable aircraft. Psycho-physiological phenomena influencing pilot's behavior in stall/spin situations include (1) channelization of sensory inputs, (2) limitations in precisely controlling several muscular inputs, (3) inaccurate judgment of elapsed time, and (4) disorientation of vestibulo-ocular inputs. Results are given of pilot responses to all these problems in the F14A, F16/AB, and F/A-18A aircraft. The use of departure spin resistance and automatic spin prevention systems incorporated on recent supersonic fighters are discussed. These systems should help to improve the stall/spin accident record with some compromise in maneuverability.

Jay L. King, Joseph D. Huxman, and Orion D. Billeter Assist Pilot Milt Thompson into the M2-F2 Attached to B-52 Mothership

NASA Image and Video Library

1966-02-28

NASA research pilot Milt Thompson is helped into the cockpit of the M2-F2 lifting body research aircraft at NASA’s Flight Research Center (now the Dryden Flight Research Center). The M2-F2 is attached to a wing pylon under the wing of NASA’s B-52 mothership. The flight was a captive flight with the pilot on-board. Milt Thompson flew in the lifting body throughout the flight, but it was never dropped from the mothership.

Minimum time and fuel flight profiles for an F-15 airplane with a Highly Integrated Digital Electronic Control (HIDEC) system

NASA Technical Reports Server (NTRS)

Haering, E. A., Jr.; Burcham, F. W., Jr.

1984-01-01

A simulation study was conducted to optimize minimum time and fuel consumption paths for an F-15 airplane powered by two F100 Engine Model Derivative (EMD) engines. The benefits of using variable stall margin (uptrim) to increase performance were also determined. This study supports the NASA Highly Integrated Digital Electronic Control (HIDEC) program. The basis for this comparison was minimum time and fuel used to reach Mach 2 at 13,716 m (45,000 ft) from the initial conditions of Mach 0.15 at 1524 m (5000 ft). Results were also compared to a pilot's estimated minimum time and fuel trajectory determined from the F-15 flight manual and previous experience. The minimum time trajectory took 15 percent less time than the pilot's estimate for the standard EMD engines, while the minimum fuel trajectory used 1 percent less fuel than the pilot's estimate for the minimum fuel trajectory. The F-15 airplane with EMD engines and uptrim, was 23 percent faster than the pilot's estimate. The minimum fuel used was 5 percent less than the estimate.

Using near infrared spectroscopy and heart rate variability to detect mental overload.

PubMed

Durantin, G; Gagnon, J-F; Tremblay, S; Dehais, F

2014-02-01

Mental workload is a key factor influencing the occurrence of human error, especially during piloting and remotely operated vehicle (ROV) operations, where safety depends on the ability of pilots to act appropriately. In particular, excessively high or low mental workload can lead operators to neglect critical information. The objective of the present study is to investigate the potential of functional near infrared spectroscopy (fNIRS) - a non-invasive method of measuring prefrontal cortex activity - in combination with measurements of heart rate variability (HRV), to predict mental workload during a simulated piloting task, with particular regard to task engagement and disengagement. Twelve volunteers performed a computer-based piloting task in which they were asked to follow a dynamic target with their aircraft, a task designed to replicate key cognitive demands associated with real life ROV operating tasks. In order to cover a wide range of mental workload levels, task difficulty was manipulated in terms of processing load and difficulty of control - two critical sources of workload associated with piloting and remotely operating a vehicle. Results show that both fNIRS and HRV are sensitive to different levels of mental workload; notably, lower prefrontal activation as well as a lower LF/HF ratio at the highest level of difficulty, suggest that these measures are suitable for mental overload detection. Moreover, these latter measurements point toward the existence of a quadratic model of mental workload. Copyright © 2013 Elsevier B.V. All rights reserved.

Production Support Flight Control Computers: Research Capability for F/A-18 Aircraft at Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

Carter, John F.

1997-01-01

NASA Dryden Flight Research Center (DFRC) is working with the United States Navy to complete ground testing and initiate flight testing of a modified set of F/A-18 flight control computers. The Production Support Flight Control Computers (PSFCC) can give any fleet F/A-18 airplane an in-flight, pilot-selectable research control law capability. NASA DFRC can efficiently flight test the PSFCC for the following four reasons: (1) Six F/A-18 chase aircraft are available which could be used with the PSFCC; (2) An F/A-18 processor-in-the-loop simulation exists for validation testing; (3) The expertise has been developed in programming the research processor in the PSFCC; and (4) A well-defined process has been established for clearing flight control research projects for flight. This report presents a functional description of the PSFCC. Descriptions of the NASA DFRC facilities, PSFCC verification and validation process, and planned PSFCC projects are also provided.

Disturbance in the neural circuitry underlying positive emotional processing in post-traumatic stress disorder (PTSD). An fMRI study.

PubMed

Jatzko, Alexander; Schmitt, Andrea; Demirakca, Traute; Weimer, Erik; Braus, Dieter F

2006-03-01

This study was designed to investigate the circuitry underlying movie-induced positive emotional processing in subjects with chronic PTSD. Ten male subjects with chronic PTSD and ten matched controls were studied. In an fMRI-paradigm a sequence of a wellknown Walt Disney cartoon with positive emotional valence was shown. PTSD subjects showed an increased activation in the right posterior temporal, precentral and superior frontal cortex. Controls recruited more emotion-related regions bilateral in the temporal pole and areas of the left fusiform and parahippocampal gyrus. This pilot study is the first to reveal alterations in the processing of positive emotions in PTSD possibly reflecting a neuronal correlate of the symptom of emotional numbness in PTSD.

Radio frequency radiation exposure of the F-15 crewmember.

PubMed

Laughrey, Michael S; Grayson, J Kevin; Jauchem, James R; Misener, Andrea E

2003-08-01

In the United States Air Force, pilots of F-15 fighter aircraft use fire control radars to search for enemy targets and to launch beyond visual range radar missiles. The fire control radars must be of a sufficient power output to enable a target return, but pilots are concerned about deleterious health effects from the levels of radio frequency radiation (RFR) they are exposed to. Measurement of RFR while actually in flight in the F-15 has never been performed. This study was designed to document the RFR levels that pilots are exposed to on normal missions while in flight with the radar on and active. A hand-held meter was used to measure electromagnetic fields during three F-15 flights. Instrumentation consisted of a Narda Microwave Model 8718 digital survey meter and Model 8723 broadband isotropic E-field probe with a frequency range between 300 MHz and 50 GHz. The measurements were conducted in the rear cockpit of an F-15D aircraft. Three missions were flown representing the standard missions an F-15 pilot flies on an everyday basis. The missions were: night intercepts, offensive basic fighter maneuvers, and defensive basic fighter maneuvers. Based on the data collected during three F-15 missions, all recorded RFR exposure to the crewmember in the F-15 was within the OSHA Permissible Exposure Limit (PEL) of 10 mW x cm(-2). Based on a limited sample, RFR exposures in F-15 cockpits appear to be well below the PEL.

Identification of pilot dynamics from in-flight tracking data

NASA Technical Reports Server (NTRS)

Hess, R. A.; Mnich, M. A.

1985-01-01

Data from a representative flight task involving an F-14 'pursuer' aircraft tracking a T-38 'target' aircraft in a 3G wind-up turn and in level flight are processed using a least squares identification technique in an attempt to identify pilot/vehicle dynamics. Comparative identification results are provided by a Fourier coefficient method which requires a carefully designed and implemented input consisting of a sum of sinusoids. The least-squares results compare favorably with those obtained by the Fourier technique. An example of crossover frequency regression is discussed in the light of the conditions of one of the flight configurations.

U.S. Air Force positive-pressure breathing anti-G system (PBG): subjective health effects and acceptance by pilots.

PubMed

Travis, T W; Morgan, T R

1994-05-01

Current high-performance fighter aircraft subject pilots to acceleration forces that can adversely effect performance and induce unconsciousness during flight. The main strategies to help the fighter pilot sustain +Gz include a pressurized anti-G garment (G-suit), the anti-G straining maneuver, and centrifuge training to optimize this effective, but very fatiguing, maneuver. To improve anti-G support for aircrew, a positive-pressure breathing anti-G system (PBG) has been developed in the COMBAT EDGE program. In order to determine if any acute adverse health effects are occurring from the use of PBG, a survey of 241 (F-15 and F-16) pilots (49 using PBG and 192 using standard methods) was conducted. Questions were asked regarding acute health effects and the impact of PBG on mission accomplishment. With the exception of dry cough, no significant increases in adverse events were found, and acceptance in the F-16 was much greater than in the F-15.

EC88-0052-4

NASA Image and Video Library

1988-03-29

View of the left cockpit and pilot's seat of the F-111 MAW aircraft. Unlike most fighter aircraft of the time, the F-111 had side-by-side seating. The pilot sat on the left side, and the weapons systems officer on the right. Both had control sticks to fly the aircraft. The two yellow and black striped handles would be used in an emergency to eject the entire F-111 cockpit. The F-111 also did not have ejection seats, but used a capsule.

The F-18 simulator at NASA's Dryden Flight Research Center, Edwards, California

NASA Image and Video Library

2004-10-04

The F-18 simulator at NASA's Dryden Flight Research Center, Edwards, California. Simulators offer a safe and economical alternative to actual flights to gather data, as well as being excellent facilities for pilot practice and training. The F-18 Hornet is used primarily as a safety chase and mission support aircraft at NASA's Dryden Flight Research Center, Edwards, California. As support aircraft, the F-18's are used for safety chase, pilot proficiency, aerial photography and other mission support functions.

HL-10 landing on lakebed with F-104 chase aircraft

NASA Technical Reports Server (NTRS)

1970-01-01

In this photo, the HL-10 has touched down on its main landing gear, while the pilot was holding the nose up to slow the vehicle. The F-104 in the background was used as a chase plane. Its pilot would give the HL-10's pilot calls on his altitude above the lakebed as well as warnings about any problems. The NASA F-104s were also used for lifting-body training. With the landing gear extended and flaps lowered, the F-104 could simulate the steep, high-speed descent and landing of a lifting body. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Effect of cognitive load on speech prosody in aviation: Evidence from military simulator flights.

PubMed

Huttunen, Kerttu; Keränen, Heikki; Väyrynen, Eero; Pääkkönen, Rauno; Leino, Tuomo

2011-01-01

Mental overload directly affects safety in aviation and needs to be alleviated. Speech recordings are obtained non-invasively and as such are feasible for monitoring cognitive load. We recorded speech of 13 military pilots while they were performing a simulator task. Three types of cognitive load (load on situation awareness, information processing and decision making) were rated by a flight instructor separately for each flight phase and participant. As a function of increased cognitive load, the mean utterance-level fundamental frequency (F0) increased, on average, by 7 Hz and the mean vocal intensity increased by 1 dB. In the most intensive simulator flight phases, mean F0 increased by 12 Hz and mean intensity, by 1.5 dB. At the same time, the mean F0 range decreased by 5 Hz, on average. Our results showed that prosodic features of speech can be used to monitor speaker state and support pilot training in a simulator environment. Copyright © 2010 Elsevier Ltd and The Ergonomics Society. All rights reserved.

NASA Dryden research pilot Gordon Fullerton flies his final mission in NASA F/A-18B #852 in formation with NASA F/A-18A #850 on Dec. 21, 2007.

NASA Image and Video Library

2007-12-21

Long-time NASA Dryden research pilot and former astronaut C. Gordon Fullerton capped an almost 50-year flying career, including more than 38 years with NASA, with a final flight in a NASA F/A-18 on Dec. 21, 2007. Fullerton and Dryden research pilot Jim Smolka flew a 90-minute pilot proficiency formation aerobatics flight with another Dryden F/A-18 and a Dryden T-38 before concluding with two low-level formation flyovers of Dryden before landing. Fullerton was honored with a water-cannon spray arch provided by two fire trucks from the Edwards Air Force Base fire department as he taxied the F/A-18 up to the Dryden ramp, and was then greeted by his wife Marie and several hundred Dryden staff after his final flight. Fullerton began his flying career with the U.S. Air Force in 1958 after earning bachelor's and master's degrees in mechanical engineering from the California Institute of Technology. Initially trained as a fighter pilot, he later transitioned to multi-engine bombers and became a bomber operations test pilot after attending the Air Force Aerospace Research Pilot School at Edwards Air Force Base, Calif. He then was assigned to the flight crew for the planned Air Force Manned Orbital Laboratory in 1966. Upon cancellation of that program, the Air Force assigned Fullerton to NASA's astronaut corps in 1969. He served on the support crews for the Apollo 14, 15, 16 and 17 lunar missions, and was later assigned to one of the two flight crews that piloted the space shuttle prototype Enterprise during the Approach and Landing Test program at Dryden. He then logged some 382 hours in space when he flew on two early space shuttle missions, STS-3 on Columbia in 1982 and STS-51F on Challenger in 1985. He joined the flight crew branch at NASA Dryden after leaving the astronaut corps in 1986. During his 21 years at Dryden, Fullerton was project pilot on a number of high-profile research efforts, including the Propulsion Controlled Aircraft, the high-speed landing tests of sp

Former Dryden pilot and NASA astronaut Neil Armstrong

NASA Technical Reports Server (NTRS)

1991-01-01

Famed astronaut Neil A. Armstrong, the first man to set foot on the moon during the historic Apollo 11 space mission in July 1969, served for seven years as a research pilot at the NACA-NASA High-Speed Flight Station, now the Dryden Flight Research Center, at Edwards, California, before he entered the space program. Armstrong joined the National Advisory Committee for Aeronautics (NACA) at the Lewis Flight Propulsion Laboratory (later NASA's Lewis Research Center, Cleveland, Ohio, and today the Glenn Research Center) in 1955. Later that year, he transferred to the High-Speed Flight Station at Edwards as an aeronautical research scientist and then as a pilot, a position he held until becoming an astronaut in 1962. He was one of nine NASA astronauts in the second class to be chosen. As a research pilot Armstrong served as project pilot on the F-100A and F-100C aircraft, F-101, and the F-104A. He also flew the X-1B, X-5, F-105, F-106, B-47, KC-135, and Paresev. He left Dryden with a total of over 2450 flying hours. He was a member of the USAF-NASA Dyna-Soar Pilot Consultant Group before the Dyna-Soar project was cancelled, and studied X-20 Dyna-Soar approaches and abort maneuvers through use of the F-102A and F5D jet aircraft. Armstrong was actively engaged in both piloting and engineering aspects of the X-15 program from its inception. He completed the first flight in the aircraft equipped with a new flow-direction sensor (ball nose) and the initial flight in an X-15 equipped with a self-adaptive flight control system. He worked closely with designers and engineers in development of the adaptive system, and made seven flights in the rocket plane from December 1960 until July 1962. During those fights he reached a peak altitude of 207,500 feet in the X-15-3, and a speed of 3,989 mph (Mach 5.74) in the X-15-1. Armstrong has a total of 8 days and 14 hours in space, including 2 hours and 48 minutes walking on the Moon. In March 1966 he was commander of the Gemini 8 orbital space flight with David Scott as pilot - the first successful docking of two vehicles in orbit. On July 20, 1969, during the Apollo 11 lunar mission, he became the first human to set foot on the Moon. In this 1991 photo, he is in the cockpit of a NASA SR-71 aircraft.

Former Dryden pilot and NASA astronaut Neil Armstrong being inducted into the Aerospace Walk of Hono

NASA Technical Reports Server (NTRS)

1991-01-01

Famed astronaut Neil A. Armstrong, the first man to set foot on the moon during the historic Apollo 11 space mission in July 1969, served for seven years as a research pilot at the NACA-NASA High-Speed Flight Station, now the Dryden Flight Research Center, at Edwards, California, before he entered the space program. Armstrong joined the National Advisory Committee for Aeronautics (NACA) at the Lewis Flight Propulsion Laboratory (later NASA's Lewis Research Center, Cleveland, Ohio, and today the Glenn Research Center) in 1955. Later that year, he transferred to the High-Speed Flight Station at Edwards as an aeronautical research scientist and then as a pilot, a position he held until becoming an astronaut in 1962. He was one of nine NASA astronauts in the second class to be chosen. As a research pilot Armstrong served as project pilot on the F-100A and F-100C aircraft, F-101, and the F-104A. He also flew the X-1B, X-5, F-105, F-106, B-47, KC-135, and Paresev. He left Dryden with a total of over 2450 flying hours. He was a member of the USAF-NASA Dyna-Soar Pilot Consultant Group before the Dyna-Soar project was cancelled, and studied X-20 Dyna-Soar approaches and abort maneuvers through use of the F-102A and F5D jet aircraft. Armstrong was actively engaged in both piloting and engineering aspects of the X-15 program from its inception. He completed the first flight in the aircraft equipped with a new flow-direction sensor (ball nose) and the initial flight in an X-15 equipped with a self-adaptive flight control system. He worked closely with designers and engineers in development of the adaptive system, and made seven flights in the rocket plane from December 1960 until July 1962. During those fights he reached a peak altitude of 207,500 feet in the X-15-3, and a speed of 3,989 mph (Mach 5.74) in the X-15-1. Armstrong has a total of 8 days and 14 hours in space, including 2 hours and 48 minutes walking on the Moon. In March 1966 he was commander of the Gemini 8 orbital space flight with David Scott as pilot - the first successful docking of two vehicles in orbit. On July 20, 1969, during the Apollo 11 lunar mission, he became the first human to set foot on the Moon.

Closeup of research pilot Neil Armstrong operating the Iron Cross Attitude Simulator reaction contro

NASA Technical Reports Server (NTRS)

1956-01-01

Famed astronaut Neil A. Armstrong, the first man to set foot on the moon during the historic Apollo 11 space mission in July 1969, served for seven years as a research pilot at the NACA-NASA High-Speed Flight Station, now the Dryden Flight Research Center, at Edwards, California, before he entered the space program. Armstrong joined the National Advisory Committee for Aeronautics (NACA) at the Lewis Flight Propulsion Laboratory (later NASA's Lewis Research Center, Cleveland, Ohio, and today the Glenn Research Center) in 1955. Later that year, he transferred to the High-Speed Flight Station at Edwards as an aeronautical research scientist and then as a pilot, a position he held until becoming an astronaut in 1962. He was one of nine NASA astronauts in the second class to be chosen. As a research pilot Armstrong served as project pilot on the F-100A and F-100C aircraft, F-101, and the F-104A. He also flew the X-1B, X-5, F-105, F-106, B-47, KC-135, and Paresev. He left Dryden with a total of over 2450 flying hours. He was a member of the USAF-NASA Dyna-Soar Pilot Consultant Group before the Dyna-Soar project was cancelled, and studied X-20 Dyna-Soar approaches and abort maneuvers through use of the F-102A and F5D jet aircraft. Armstrong was actively engaged in both piloting and engineering aspects of the X-15 program from its inception. He completed the first flight in the aircraft equipped with a new flow-direction sensor (ball nose) and the initial flight in an X-15 equipped with a self-adaptive flight control system. He worked closely with designers and engineers in development of the adaptive system, and made seven flights in the rocket plane from December 1960 until July 1962. During those fights he reached a peak altitude of 207,500 feet in the X-15-3, and a speed of 3,989 mph (Mach 5.74) in the X-15-1. Armstrong has a total of 8 days and 14 hours in space, including 2 hours and 48 minutes walking on the Moon. In March 1966 he was commander of the Gemini 8 orbital space flight with David Scott as pilot - the first successful docking of two vehicles in orbit. On July 20, 1969, during the Apollo 11 lunar mission, he became the first human to set foot on the Moon.

Study of the presence of fluorine in the recycled fractions during carbothermal treatment of EAF dust.

PubMed

Menad, N; Ayala, J N; Garcia-Carcedo, Fernando; Ruiz-Ayúcar, E; Hernández, A

2003-01-01

Carbothermal treatment tests of electric arc furnace dusts (EAFD) using the Waelz kiln process were carried out in pilot-scale for the production of zinc oxide. The association of halides in the EAFD, and the recycled products, such as zinc oxide fumes and high-grade iron contents fractions were examined by X-ray diffraction (XRD), scanning electron microscope (SEM) and transmission electron microscope (TEM) analysis. XRD reveals the presence of chlorine and fluorine in the dusts in the form of KCl, NaCl and CaF2. An ultra-pure fraction of zinc was obtained after the Double Leaching Waelz Oxide (DLWO) process was performed on the zinc oxide fumes. The halide contents were reduced to approximately 100 ppm Cl and 700 ppm F. The rest of these elements are in the form of CaF2. About 65% F is volatilised as lead and zinc fluorides, 15% is expected in the magnetic fractions and 20% in non-magnetic fractions as CaF2 and MnF2, respectively.

Individual, work-, and flight-related issues in F-16 pilots reporting neck pain.

PubMed

De Loose, Veerle; Van den Oord, Marieke; Burnotte, Frédéric; Van Tiggelen, Damien; Stevens, Veerle; Cagnie, Barbara; Witvrouw, Erik; Danneels, Lieven

2008-08-01

Neck pain is a common problem in F-16 pilots. A cross-sectional survey was used to determine the self-reported 1-yr prevalence of neck pain and to compare individual, work-related, and flight-related characteristics in F-16 pilots with and without neck pain. There were 90 male F-16 pilots of the Belgian Air Force and The Royal Netherlands Air Force who voluntarily completed an anonymous survey. The 1-yr prevalence of neck pain was 18.9%. Pilots were divided into two groups: healthy (HG) and neck pain group (NPG). This study could not identify individual or specific flight-related differences between these two groups. High force demands, often sitting for a long time, frequently holding the neck in a forward bent posture, and being physically tired were all physical work-related factors that were reported significantly more often in the NPG. The NPG also reported significantly more psychosocial factors, such as being mentally tired at the end of the day and being annoyed by others at the workplace. Since the specific flight-related factors were not significantly different between the HG and the NPG, physical and psychosocial factors could have been important factors in the development or maintenance of neck pain in F-16 pilots. The results of this study highlight for the first time that, in addition to flight-related issues, other aspects must be considered in analyzing neck pain. These other aspects stress the importance of a broader approach when considering neck pain, even in this population that is exposed to very high loads during flight.

C. Gordon Fullerton

NASA Technical Reports Server (NTRS)

1989-01-01

C. Gordon Fullerton is a research pilot at NASA's Dryden Flight Research Center, Edwards, California. His assignments include a variety of flight research and support activities piloting NASA's B-52 launch aircraft, the 747 Shuttle Carrier Aircraft (SCA), and other multi-engine and high performance aircraft. Fullerton, who has logged 382 hours in space flight, was a NASA astronaut from September 1969 until November 1986 when he joined the Flight Crew Branch at Dryden. In July 1988, he completed a 30-year career with the U.S. Air Force and retired as a colonel. As the project pilot on the NASA B-52 launch aircraft, Fullerton flew during the first six air launches of the commercially developed Pegasus space vehicle. He was involved in a series of development air launches of the X-38 Crew Recovery Vehicle and in the Pegasus launch of the X-43A Hyper-X advanced propulsion project. Fullerton also flies Dryden's DC-8 Airborne Science aircraft, regularly deployed worldwide to support a variety of research studies, including atmospheric physics, ground mapping and meteorology. In addition to these current activities, Fullerton has been involved in numerous other research programs at Dryden. He was the project pilot on the Propulsion Controlled Aircraft program, during which he successfully landed both a modified F-15 and an MD-11 transport with all control surfaces neutralized, using only engine thrust modulation for control. Assigned to evaluate the flying qualities of the Russian Tu-144 supersonic transport during two flights in 1998, he reached a speed of Mach 2 and became one of only two non-Russian pilots to fly that aircraft. He piloted a Convair 990 modified to test space shuttle landing gear components during many very high-speed landings. Other projects for which he has flown in the past include the C-140 JetStar Laminar Flow Control; F-111 Mission Adaptive Wing; F-14 Variable Sweep Flow Transition; Space Shuttle drag chute and F-111 crew module parachute tests with the B-52; X-29 vortex flow control; and the F-18 Systems Research Aircraft. With more than15,000 hours of flying time, Fullerton has piloted 135 different types of aircraft, including full qualification in the T-33, T-34, T-37, T-38, T-39, F-86, F-101, F-104, F-106, F-111, F-14, F-15, X-29, KC-135, C-140, B-47, and he currently flies the F/A-18, B-52, DC-8, B-747, and T-34C. Born Oct. 11, 1936, in Rochester, N. Y., Fullerton graduated from U.S. Grant High School, Portland, Ore. He earned bachelor of science and master of science degrees in mechanical engineering from the California Institute of Technology, Pasadena, California, in 1957 and l958, respectively. Fullerton entered the U. S. Air Force in July 1958 after working as a mechanical design engineer for Hughes Aircraft Co., Culver City, California. After flight school, he was trained as an F-86 interceptor pilot, and later became a B-47 bomber pilot at Davis-Monthan Air Force Base, Tucson, Ariz. In 1964 he was selected to attend the Air Force Aerospace Research Pilot School (now the Air Force Test Pilot School), Edwards Air Force Base, Calif. Upon graduation he was assigned as a test pilot with the Bomber Operations Division at Wright-Patterson Air Force Base, Dayton, Ohio. Fullerton served as a flight crew member for the Air Force Manned Orbiting Laboratory program from 1966 through1969. After assignment to the NASA Johnson Space Center, as an astronaut Fullerton served on the support crews for the Apollo 14, 15, 16, and 17 lunar missions. In 1977, Fullerton was assigned to one of the two two-man flight crews that piloted the Space Shuttle prototype Enterprise during the Approach and Landing Test Program at Dryden. Fullerton was the pilot on the eight-day STS-3 Space Shuttle orbital flight test mission Mar. 22-30, 1982. The mission exposed the orbiter Columbia to extremes in thermal stress and tested the 50-foot Remote Manipulator System used to grapple and maneuver payloads in orbit. STS-3 landed at White Sands, N.M., because Rogers Dry Lake at Edwards was wet due to heavy seasonal rains. Fullerton was commander of the STS-51F Spacelab 2 mission, launched on July 29, 1985. This mission, with the orbiter Challenger, was the first pallet-only Spacelab mission and the first to operate the Spacelab Instrument Pointing System (IPS). It carried 13 major experiments in the fields of astronomy, solar physics, ionospheric science, life science, and materiel science (a super fluid helium experiment). The mission ended August 6, 1985, with a landing at Dryden. Among the special awards and honors Fullerton has received are the Iven C. Kincheloe Award from the Society of Experimental Test Pilots in 1978; Department of Defense Distinguished Service and Superior Service Medals; Air Force Distinguished Flying Cross; NASA Distinguished and Exceptional Service Medals; NASA Space Flight Medals in 1983 and 1985; General Thomas D. White Space Trophy; Haley Space Flight Award from the American Institute of Aeronautics and Astronautics; American Astronautical Society Flight Achievement Awards for 1977, 1981, and 1985; the Certificate of Achievement Award from the Soaring Society of America; and the Ray E. Tenhoff Award from the Society of Experimental Test Pilots in 1992 and 1993. Fullerton was inducted into the International Space Hall of Fame in 1982. He is a Fellow of the Society of Experimental Test Pilots; member of Tau Beta Pi, an engineering honorary fraternity; honorary member of the National World War II Glider Pilot Association; and a Fellow of the American Astronautical Society.

Head positioning for high +Gz loads: an analysis of the techniques used by F/A-18 pilots.

PubMed

Newman, D G

1997-08-01

A study was undertaken among Royal Australian Air Force fighter pilots to determine whether, as an occupational group, they had developed any particular protective head positioning strategies in order to minimize their risk of sustaining a +Gz-induced neck injury during air combat maneuvering. There were 42 F/A-18 Hornet pilots who responded to an anonymous questionnaire which asked about head positioning strategies. Of these, 29 pilots reported using a protective strategy. Several pilots reported using several different techniques. The most popular strategy reported was positioning the head prior to the application of +Gz (13 respondents). Eleven pilots reported using aircraft structures to wedge or brace their heads against. The results of this study show that fighter pilots who are regularly exposed to high +Gz forces develop an individualized approach to protecting their cervical spines from +Gz-induced injury.

Social Ecology and Group Cohesion in Pilot Whales and their Responses to Playback of Anthropogenic and Natural Sounds

DTIC Science & Technology

2014-09-30

responses to biologically relevant ( killer whale and conspecific) and anthropogenic (mid-frequency sonar) sound stimuli that will be analysed in a...Curé, C., Antunes, R., Samarra, F., Alves, A. C., Visser, F., Kvadsheim, P. H. and Miller, P. J. O. (2012). Pilot Whales Attracted to Killer Whale ... Killer (Orcinus orca), Long-Finned Pilot (Globicephala melas), and Sperm (Physeter macrocephalus) Whales to Naval Sonar. Aquatic Mammals 38, 362-401

Primary display latency criteria based on flying qualities and performance data

NASA Technical Reports Server (NTRS)

Funk, John D., Jr.; Beck, Corin P.; Johns, John B.

1993-01-01

With a pilots' increasing use of visual cue augmentation, much requiring extensive pre-processing, there is a need to establish criteria for new avionics/display design. The timeliness and synchronization of the augmented cues is vital to ensure the performance quality required for precision mission task elements (MTEs) where augmented cues are the primary source of information to the pilot. Processing delays incurred while transforming sensor-supplied flight information into visual cues are unavoidable. Relationships between maximum control system delays and associated flying qualities levels are documented in MIL-F-83300 and MIL-F-8785. While cues representing aircraft status may be just as vital to the pilot as prompt control response for operations in instrument meteorological conditions, presently, there are no specification requirements on avionics system latency. To produce data relating avionics system latency to degradations in flying qualities, the Navy conducted two simulation investigations. During the investigations, flying qualities and performance data were recorded as simulated avionics system latency was varied. Correlated results of the investigation indicates that there is a detrimental impact of latency on flying qualities. Analysis of these results and consideration of key factors influencing their application indicate that: (1) Task performance degrades and pilot workload increases as latency is increased. Inconsistency in task performance increases as latency increases. (2) Latency reduces the probability of achieving Level 1 handling qualities with avionics system latency as low as 70 ms. (3) The data suggest that the achievement of desired performance will be ensured only at display latency values below 120 ms. (4) These data also suggest that avoidance of inadequate performance will be ensured only at display latency values below 150 ms.

A water-cannon salute from two Air Force fire trucks heralds NASA research pilot Gordon Fullerton's final mission as his NASA F/A-18 taxis beneath the spray.

NASA Image and Video Library

2007-12-21

Long-time NASA Dryden research pilot and former astronaut C. Gordon Fullerton capped an almost 50-year flying career, including more than 38 years with NASA, with a final flight in a NASA F/A-18 on Dec. 21, 2007. Fullerton and Dryden research pilot Jim Smolka flew a 90-minute pilot proficiency formation aerobatics flight with another Dryden F/A-18 and a Dryden T-38 before concluding with two low-level formation flyovers of Dryden before landing. Fullerton was honored with a water-cannon spray arch provided by two fire trucks from the Edwards Air Force Base fire department as he taxied the F/A-18 up to the Dryden ramp, and was then greeted by his wife Marie and several hundred Dryden staff after his final flight. Fullerton began his flying career with the U.S. Air Force in 1958 after earning bachelor's and master's degrees in mechanical engineering from the California Institute of Technology. Initially trained as a fighter pilot, he later transitioned to multi-engine bombers and became a bomber operations test pilot after attending the Air Force Aerospace Research Pilot School at Edwards Air Force Base, Calif. He then was assigned to the flight crew for the planned Air Force Manned Orbital Laboratory in 1966. Upon cancellation of that program, the Air Force assigned Fullerton to NASA's astronaut corps in 1969. He served on the support crews for the Apollo 14, 15, 16 and 17 lunar missions, and was later assigned to one of the two flight crews that piloted the space shuttle prototype Enterprise during the Approach and Landing Test program at Dryden. He then logged some 382 hours in space when he flew on two early space shuttle missions, STS-3 on Columbia in 1982 and STS-51F on Challenger in 1985. He joined the flight crew branch at NASA Dryden after leaving the astronaut corps in 1986. During his 21 years at Dryden, Fullerton was project pilot on a number of high-profile research efforts, including the Propulsion Controlled Aircraft, the high-speed landing tests of

Joseph A. Walker after X-15 flight #2-14-28

NASA Image and Video Library

1961-03-30

Joseph A. Walker was a Chief Research Pilot at the NASA Dryden Flight Research Center during the mid-1960s. He joined the NACA in March 1945, and served as project pilot at the Edwards flight research facility on such pioneering research projects as the D-558-1, D-558-2, X-1, X-3, X-4, X-5, and the X-15. He also flew programs involving the F-100, F-101, F-102, F-104, and the B-47. Walker made the first NASA X-15 flight on March 25, 1960. He flew the research aircraft 24 times and achieved its fastest speed and highest altitude. He attained a speed of 4,104 mph (Mach 5.92) during a flight on June 27, 1962, and reached an altitude of 354,300 feet on August 22, 1963 (his last X-15 flight). He was the first man to pilot the Lunar Landing Research Vehicle (LLRV) that was used to develop piloting and operational techniques for lunar landings. Walker was born February 20, 1921, in Washington, Pa. He lived there until graduating from Washington and Jefferson College in 1942, with a B.A. degree in Physics. During World War II he flew P-38 fighters for the Air Force, earning the Distinguished Flying Cross and the Air Medal with Seven Oak Clusters. Walker was the recipient of many awards during his 21 years as a research pilot. These include the 1961 Robert J. Collier Trophy, 1961 Harmon International Trophy for Aviators, the 1961 Kincheloe Award and 1961 Octave Chanute Award. He received an honorary Doctor of Aeronautical Sciences degree from his alma mater in June of 1962. Walker was named Pilot of the Year in 1963 by the National Pilots Association. He was a charter member of the Society of Experimental Test Pilots, and one of the first to be designated a Fellow. He was fatally injured on June 8, 1966, in a mid-air collision between an F-104 he was piloting and the XB-70.

Evaluation of iconic versus F-map microburst displays

NASA Technical Reports Server (NTRS)

Salzberger, Mark; Hansman, R. John; Wanke, Craig

1994-01-01

Previous studies have shown graphical presentation methods of hazardous wind shear to be superior to textual or audible warnings alone. Positional information and the strength of the hazard were observed to be and were cited by pilots as the most important factors in a display. In this experiment the use of the three different graphical presentations of hazardous wind shear are examined. Airborne predictive detectors of wind shear enable the dissemination of varying levels of information. The effectiveness of iconic and mapping display modes of different complexities are addressed through simulation and analysis. Different positional and time-varying situations are presented in a 'part-task' Boeing 767 simulator using data from actual microburst events. Experienced airline pilots fly approach profiles using both iconic and F-map wind shear alerting displays. Microburst accompanied each event is also shown to the pilot. Mapping display types are expected to be found exceptionally efficient at conveying location comparison information while iconic displays simplify the threat recognition process. Preliminary results from the simulator study are presented. Recommendations concerning the suitability of multilevel iconic and mapping displays are made. Situational problems with current display prototypes are also addressed.

Systematic Evaluation and Uncertainty Analysis of the Refuse-Derived Fuel Process in Taiwan.

PubMed

Chang, Ying-Hsi; Chang, Ni-Bin; Chen, W C

1998-06-01

In the last few years, Taiwan has set a bold agenda in solid waste recycling and incineration programs. Not only were the recycling activities and incineration projects promoted by government agencies, but the related laws and regulations were continuously promulgated by the Legislative Yen. The solid waste presorting process that is to be considered prior to the existing incineration facilities has received wide attention. This paper illustrates a thorough evaluation for the first refuse-derived fuel pilot process from both quantitative and qualitative aspects. The process is to be installed and integrated with a large-scale municipal incinerator. This pilot process, developed by an engineering firm in Tainan County, consists of standard unit operations of shredding, magnetic separation, trommel screening, and air classification. A series of sampling and analyses were initialized in order to characterize its potentials in the solid waste management system. The probabilistic modeling for various types o f waste pro perties derived in this analysis may provide a basic understanding of system reliability.

Fate of virginiamycin through the fuel ethanol production process.

PubMed

Bischoff, Kenneth M; Zhang, Yanhong; Rich, Joseph O

2016-05-01

Antibiotics are frequently used to prevent and treat bacterial contamination of commercial fuel ethanol fermentations, but there is concern that antibiotic residues may persist in the distillers grains coproducts. A study to evaluate the fate of virginiamycin during the ethanol production process was conducted in the pilot plant facilities at the National Corn to Ethanol Research Center, Edwardsville, IL. Three 15,000-liter fermentor runs were performed: one with no antibiotic (F1), one dosed with 2 parts per million (ppm) of a commercial virginiamycin product (F2), and one dosed at 20 ppm of virginiamycin product (F3). Fermentor samples, distillers dried grains with solubles (DDGS), and process intermediates (whole stillage, thin stillage, syrup, and wet cake) were collected from each run and analyzed for virginiamycin M and virginiamycin S using a liquid chromatography-mass spectrometry method. Virginiamycin M was detected in all process intermediates of the F3 run. On a dry-weight basis, virginiamycin M concentrations decreased approximately 97 %, from 41 μg/g in the fermentor to 1.4 μg/g in the DDGS. Using a disc plate bioassay, antibiotic activity was detected in DDGS from both the F2 and F3 runs, with values of 0.69 μg virginiamycin equivalent/g sample and 8.9 μg/g, respectively. No antibiotic activity (<0.6 μg/g) was detected in any of the F1 samples or in the fermentor and process intermediate samples from the F2 run. These results demonstrate that low concentrations of biologically active antibiotic may persist in distillers grains coproducts produced from fermentations treated with virginiamycin.

Differential activation of brain regions involved with error-feedback and imitation based motor simulation when observing self and an expert's actions in pilots and non-pilots on a complex glider landing task.

PubMed

Callan, Daniel E; Terzibas, Cengiz; Cassel, Daniel B; Callan, Akiko; Kawato, Mitsuo; Sato, Masa-Aki

2013-05-15

In this fMRI study we investigate neural processes related to the action observation network using a complex perceptual-motor task in pilots and non-pilots. The task involved landing a glider (using aileron, elevator, rudder, and dive brake) as close to a target as possible, passively observing a replay of one's own previous trial, passively observing a replay of an expert's trial, and a baseline do nothing condition. The objective of this study is to investigate two types of motor simulation processes used during observation of action: imitation based motor simulation and error-feedback based motor simulation. It has been proposed that the computational neurocircuitry of the cortex is well suited for unsupervised imitation based learning, whereas, the cerebellum is well suited for error-feedback based learning. Consistent with predictions, pilots (to a greater extent than non-pilots) showed significant differential activity when observing an expert landing the glider in brain regions involved with imitation based motor simulation (including premotor cortex PMC, inferior frontal gyrus IFG, anterior insula, parietal cortex, superior temporal gyrus, and middle temporal MT area) than when observing one's own previous trial which showed significant differential activity in the cerebellum (only for pilots) thought to be concerned with error-feedback based motor simulation. While there was some differential brain activity for pilots in regions involved with both Execution and Observation of the flying task (potential Mirror System sites including IFG, PMC, superior parietal lobule) the majority was adjacent to these areas (Observation Only Sites) (predominantly in PMC, IFG, and inferior parietal loblule). These regions showing greater activity for observation than for action may be involved with processes related to motor-based representational transforms that are not necessary when actually carrying out the task. Copyright © 2013 Elsevier Inc. All rights reserved.

Loads and motions of an F-106B flying through thunderstorms

NASA Technical Reports Server (NTRS)

Winebarger, R. M.

1986-01-01

Data are presented on loads and motions of a NASA F-106B airplane flying inside thunderstorms. No significant differences in piloting techniques were observed among the three pilots involved. It is indicated that airliners in normal operations occasionally encounter turbulence almost as severe as those encountered in these thunderstorm flights.

Feasibility and Acceptability of Brighter Bites: A Food Co-Op in Schools to Increase Access, Continuity and Education of Fruits and Vegetables Among Low-Income Populations.

PubMed

Sharma, Shreela; Helfman, Lisa; Albus, Katherine; Pomeroy, Mike; Chuang, Ru-Jye; Markham, Christine

2015-08-01

Intake of fruits and vegetables (F&V) continues to be low in children in the United States. The purpose of this study was to conduct a pilot feasibility evaluation of Brighter Bites, a school-based food co-op to provide access to fresh F&V and nutrition education to low-income children and their families. Brighter Bites is a 16-week school-based food co-op consisting of: (1) Weekly distribution of 50-60 servings of fresh F&V; (2) Weekly bilingual parent handouts and recipe demonstrations; and (3) implementing CATCH, a coordinated school health program in schools. Brighter Bites was pilot tested using a pre-post evaluation design in one charter school in Houston, TX, USA (n = 57 3rd grade parent-child dyads; 94.1 % Hispanic, 91 % low-income). Evaluation, at baseline, midpoint, and post-intervention, included self-reported child and parent surveys on psychosocial factors, dietary habits and mealtime practices. Pearson's Chi square test, Fisher's exact-test or paired t test were used to determine changes pre- to post-intervention (at p < 0.05). Process data using parent surveys, teacher surveys, attendance logs, and produce cost data were used to determine feasibility and acceptability of program. Participants received on average 61 servings of F&V weekly for 16 weeks at the cost of $4.31/family/week. Results showed significant increases in child reported self-efficacy, outcome expectations and attitudes towards consuming F&V (p < 0.05). We found significant increases in child exposure to F&V and child preference of various F&V from baseline to post-intervention (p < 0.05). Parent surveys showed significant improvements in mealtime practices at home: decrease in children eating while watching TV, increase in eating dinner with the family, less fast food, less sugary drinks with meals, more children asking for F&V as snacks. Process data showed 98 % retention rate and high parent acceptability of program components. Brighter Bites is a promising strategy to increase F&V access and education in low-income populations using existing infrastructure of schools and food banks.

Major General Robert A. Rushworth

NASA Technical Reports Server (NTRS)

1982-01-01

Air Force test pilot Robert A. Rushworth is shown in an X-15. He was selected for the X-15 program in 1958, and made his first flight on November 4, 1960. Over the next six years, he made 34 flights in the X-15, the most of any pilot. This included a flight to an altitude of 285,000 feet, made on June 27, 1963. This flight above 50 miles qualified Rushworth for astronaut wings. On a later X-15 flight, he was awarded a Distinguished Flying Cross for successfully landing an X-15 after its nose wheel extended while flying at nearly Mach 5. He made his final X-15 flight on July 1, 1966, then returned to regular Air Force duties. These included a tour in Vietnam as an F-4 pilot, flying 189 combat missions. He also served as the Commander of the Air Force Flight Test Center at Edwards AFB, and as the Commander of the Air Force Test and Evaluation Center at Kirtland AFB. At the time of his retirement as a major general, he was Vice Commander, Aeronautical Systems Division, Air Force Systems Command, at Wright-Patterson AFB. Rushworth flew C-47s and C-46s as a transport pilot in World War II, as well as F-80Cs, F-101s, TF-102s, F-104s, F-105s, F-106s, and F-4s. He died on March 17, 1993.

Human and behavioral factors contributing to spine-based neurological cockpit injuries in pilots of high-performance aircraft: recommendations for management and prevention

NASA Technical Reports Server (NTRS)

Jones, J. A.; Hart, S. F.; Baskin, D. S.; Effenhauser, R.; Johnson, S. L.; Novas, M. A.; Jennings, R.; Davis, J.

2000-01-01

In high-performance aircraft, the need for total environmental awareness coupled with high-g loading (often with abrupt onset) creates a predilection for cervical spine injury while the pilot is performing routine movements within the cockpit. In this study, the prevalence and severity of cervical spine injury are assessed via a modified cross-sectional survey of pilots of multiple aircraft types (T-38 and F-14, F-16, and F/A-18 fighters). Ninety-five surveys were administered, with 58 full responses. Fifty percent of all pilots reported in-flight or immediate post-flight spine-based pain, and 90% of fighter pilots reported at least one event, most commonly (> 90%) occurring during high-g (> 5 g) turns of the aircraft with the head deviated from the anatomical neutral position. Pre-flight stretching was not associated with a statistically significant reduction in neck pain episodes in this evaluation, whereas a regular weight training program in the F/A-18 group approached a significant reduction (mean = 2.492; p < 0.064). Different cockpit ergonomics may vary the predisposition to cervical injury from airframe to airframe. Several strategies for prevention are possible from both an aircraft design and a preventive medicine standpoint. Countermeasure strategies against spine injury in pilots of high-performance aircraft require additional research, so that future aircraft will not be limited by the human in control.

John B. McKay after X-15 flight #3-27-44

NASA Image and Video Library

1964-03-13

John B. McKay was one of the first pilots assigned to the X-15 flight research program at NASA's Flight Research Center, Edwards, Calif. As a civilian research pilot and aeronautical engineer, he made 30 flights in X-15s from October 28, 1960, until September 8, 1966. His peak altitude was 295,600 feet, and his highest speed was 3863 mph (Mach 5.64). McKay was with the NACA and NASA from February 8,1951 until October 5, 1971 and specialized in high-speed flight research programs. He began as an NACA intern, but assumed pilot status on July 11, 1952. In addition to the X-l5, he flew such experimental aircraft as the D-558-1, D-558-2, X-lB, and the X-lE. He has also served as a research pilot on flight programs involving the F-100, F-102, F-104, and the F-107. Born on December 8, 1922, in Portsmouth, Va., McKay graduated from Virginia Polytechnic Institute in 195O with a Bachelor of Science degree in Aeronautical Engineering. During World War II he served as a Navy pilot in the Pacific Theater, earning the Air Medal and Two Clusters, and a Presidential Unit Citation. McKay wrote several technical papers, and was a member of the American Institute of Aeronautics and Astronautics, as well as the Society of Experimental Test Pilots. He passed away on April 27, 1975.

Development of systems and techniques for landing an aircraft using onboard television

NASA Technical Reports Server (NTRS)

Gee, S. W.; Carr, P. C.; Winter, W. R.; Manke, J. A.

1978-01-01

A flight program was conducted to develop a landing technique with which a pilot could consistently and safely land a remotely piloted research vehicle (RPRV) without outside visual reference except through television. Otherwise, instrumentation was standard. Such factors as the selection of video parameters, the pilot's understanding of the television presentation, the pilot's ground cockpit environment, and the operational procedures for landing were considered. About 30 landings were necessary for a pilot to become sufficiently familiar and competent with the test aircraft to make powered approaches and landings with outside visual references only through television. When steep approaches and landings were made by remote control, the pilot's workload was extremely high. The test aircraft was used as a simulator for the F-15 RPRV, and as such was considered to be essential to the success of landing the F-15 RPRV.

Two NASA Dryden F/A-18s flown by Gordon Fullerton and Nils Larson fly in tight formation Dec. 21, 2007 during Fullerton's final flight before his retirement.

NASA Image and Video Library

2007-12-21

Long-time NASA Dryden research pilot and former astronaut C. Gordon Fullerton capped an almost 50-year flying career, including more than 38 years with NASA, with a final flight in a NASA F/A-18 on Dec. 21, 2007. Fullerton and Dryden research pilot Jim Smolka flew a 90-minute pilot proficiency formation aerobatics flight with another Dryden F/A-18 and a Dryden T-38 before concluding with two low-level formation flyovers of Dryden before landing. Fullerton was honored with a water-cannon spray arch provided by two fire trucks from the Edwards Air Force Base fire department as he taxied the F/A-18 up to the Dryden ramp, and was then greeted by his wife Marie and several hundred Dryden staff after his final flight. Fullerton began his flying career with the U.S. Air Force in 1958 after earning bachelor's and master's degrees in mechanical engineering from the California Institute of Technology. Initially trained as a fighter pilot, he later transitioned to multi-engine bombers and became a bomber operations test pilot after attending the Air Force Aerospace Research Pilot School at Edwards Air Force Base, Calif. He then was assigned to the flight crew for the planned Air Force Manned Orbital Laboratory in 1966. Upon cancellation of that program, the Air Force assigned Fullerton to NASA's astronaut corps in 1969. He served on the support crews for the Apollo 14, 15, 16 and 17 lunar missions, and was later assigned to one of the two flight crews that piloted the space shuttle prototype Enterprise during the Approach and Landing Test program at Dryden. He then logged some 382 hours in space when he flew on two early space shuttle missions, STS-3 on Columbia in 1982 and STS-51F on Challenger in 1985. He joined the flight crew branch at NASA Dryden after leaving the astronaut corps in 1986. During his 21 years at Dryden, Fullerton was project pilot on a number of high-profile research efforts, including the Propulsion Controlled Aircraft, the high-speed landing tests of

A preliminary investigation of the use of throttles for emergency flight control

NASA Technical Reports Server (NTRS)

Burcham, F. W., Jr.; Fullerton, C. Gordon; Gilyard, Glenn B.; Wolf, Thomas D.; Stewart, James F.

1991-01-01

A preliminary investigation was conducted regarding the use of throttles for emergency flight control of a multiengine aircraft. Several airplanes including a light twin-engine piston-powered airplane, jet transports, and a high performance fighter were studied during flight and piloted simulations. Simulation studies used the B-720, B-727, MD-11, and F-15 aircraft. Flight studies used the Lear 24, Piper PA-30, and F-15 airplanes. Based on simulator and flight results, all the airplanes exhibited some control capability with throttles. With piloted simulators, landings using manual throttles-only control were extremely difficult. An augmented control system was developed that converts conventional pilot stick inputs into appropriate throttle commands. With the augmented system, the B-720 and F-15 simulations were evaluated and could be landed successfully. Flight and simulation data were compared for the F-15 airplane.

Flight test evaluation of an RAF high altitude partial pressure protective assembly

NASA Technical Reports Server (NTRS)

Ashworth, G. R.; Putnam, T. W.; Dana, W. J.; Enevoldson, E. K.; Winter, W. R.

1979-01-01

A partial pressure suit was evaluated during tests in an F-104 and F-15 as a protective garment for emergency descents. The garment is an pressure jerkin and modified anti-g suit combined with an oronasal mask. The garment can be donned and doffed at the aircraft to minimize thermal buildup. The oronasal mask was favored by the pilots due to its immobility on the face during high g-loading. The garment was chosen to provide optimum dexterity for the pilot, which is not available in a full pressure suit, while protecting the pilot at altitudes up to 18,288 meters, during a cabin decompression, and subsequent aircraft descent. During cabin decompressions in the F-104 and F-15, cabin pressure altitude was measured at various aircraft angles of attack, Mach numbers, and altitudes to determine the effect of the aerodynamic slipstream on the cabin altitude.

Pilots' Attention Distributions Between Chasing a Moving Target and a Stationary Target.

PubMed

Li, Wen-Chin; Yu, Chung-San; Braithwaite, Graham; Greaves, Matthew

2016-12-01

Attention plays a central role in cognitive processing; ineffective attention may induce accidents in flight operations. The objective of the current research was to examine military pilots' attention distributions between chasing a moving target and a stationary target. In the current research, 37 mission-ready F-16 pilots participated. Subjects' eye movements were collected by a portable head-mounted eye-tracker during tactical training in a flight simulator. The scenarios of chasing a moving target (air-to-air) and a stationary target (air-to-surface) consist of three operational phases: searching, aiming, and lock-on to the targets. The findings demonstrated significant differences in pilots' percentage of fixation during the searching phase between air-to-air (M = 37.57, SD = 5.72) and air-to-surface (M = 33.54, SD = 4.68). Fixation duration can indicate pilots' sustained attention to the trajectory of a dynamic target during air combat maneuvers. Aiming at the stationary target resulted in larger pupil size (M = 27,105, SD = 6565), reflecting higher cognitive loading than aiming at the dynamic target (M = 23,864, SD = 8762). Pilots' visual behavior is not only closely related to attention distribution, but also significantly associated with task characteristics. Military pilots demonstrated various visual scan patterns for searching and aiming at different types of targets based on the research settings of a flight simulator. The findings will facilitate system designers' understanding of military pilots' cognitive processes during tactical operations. They will assist human-centered interface design to improve pilots' situational awareness. The application of an eye-tracking device integrated with a flight simulator is a feasible and cost-effective intervention to improve the efficiency and safety of tactical training.Li W-C, Yu C-S, Braithwaite G, Greaves M. Pilots' attention distributions between chasing a moving target and a stationary target. Aerosp Med Hum Perform. 2016; 87(12):989-995.

F-16 Class A mishaps in the U.S. Air Force, 1975-93.

PubMed

Knapp, C J; Johnson, R

1996-08-01

All USAF F-16 fighter Class A (major) aircraft mishaps from 1975-93 were analyzed, using records from the U.S. Air Force Safety Agency (AFSA). There were 190 Class A mishaps involving 204 F-16's and 217 aircrew during this 19-yr period. The overall Class A rate was 5.09 per 100,000 flight hours, more than double the overall USAF rate. The mishaps are categorized by year, month, time of day and model of aircraft in relation to mishap causes as determined and reported by AFSA. Formation position, phase of flight and primary cause of the mishap indicate that maneuvering, cruise and low-level phases account for the majority of the mishaps (71%), with air-to-air engagements associated with a higher proportion of pilot error (71%) than was air-to-ground (49%). Engine failure was the number one cause of mishaps (35%), and collision with the ground the next most frequent (24%). Pilot error was determined as causative in 55% of all the mishaps. Pilot error was often associated with other non-pilot related causes. Channelized attention, loss of situational awareness, and spatial disorientation accounted for approximately 30% of the total pilot error causes found. Pilot demographics, flight hour/sortie profiles, and aircrew injuries are also listed. Fatalities occurred in 27% of the mishaps, with 97% of those involving pilot errors.

Gemini 8 prime and backup crews during press conference

NASA Image and Video Library

1966-02-26

S66-24380 (26 Feb. 1966) --- Gemini-8 prime and backup crews during press conference. Left to right are astronauts David R. Scott, prime crew pilot; Neil A. Armstrong, prime crew command pilot; Charles Conrad Jr., backup crew command pilot; and Richard F. Gordon Jr., backup crew pilot. Photo credit: NASA

More than 200 Dryden staff formed two long lines on the Dryden ramp to greet retired research pilot Gordon Fullerton after his final flight in a NASA F/A-18.

NASA Image and Video Library

2007-12-21

Long-time NASA Dryden research pilot and former astronaut C. Gordon Fullerton capped an almost 50-year flying career, including more than 38 years with NASA, with a final flight in a NASA F/A-18 on Dec. 21, 2007. Fullerton and Dryden research pilot Jim Smolka flew a 90-minute pilot proficiency formation aerobatics flight with another Dryden F/A-18 and a Dryden T-38 before concluding with two low-level formation flyovers of Dryden before landing. Fullerton was honored with a water-cannon spray arch provided by two fire trucks from the Edwards Air Force Base fire department as he taxied the F/A-18 up to the Dryden ramp, and was then greeted by his wife Marie and several hundred Dryden staff after his final flight. Fullerton began his flying career with the U.S. Air Force in 1958 after earning bachelor's and master's degrees in mechanical engineering from the California Institute of Technology. Initially trained as a fighter pilot, he later transitioned to multi-engine bombers and became a bomber operations test pilot after attending the Air Force Aerospace Research Pilot School at Edwards Air Force Base, Calif. He then was assigned to the flight crew for the planned Air Force Manned Orbital Laboratory in 1966. Upon cancellation of that program, the Air Force assigned Fullerton to NASA's astronaut corps in 1969. He served on the support crews for the Apollo 14, 15, 16 and 17 lunar missions, and was later assigned to one of the two flight crews that piloted the space shuttle prototype Enterprise during the Approach and Landing Test program at Dryden. He then logged some 382 hours in space when he flew on two early space shuttle missions, STS-3 on Columbia in 1982 and STS-51F on Challenger in 1985. He joined the flight crew branch at NASA Dryden after leaving the astronaut corps in 1986. During his 21 years at Dryden, Fullerton was project pilot on a number of high-profile research efforts, including the Propulsion Controlled Aircraft, the high-speed landing tests of

Membrane Bioreactor/Ultra Low Energy Reverse Osmosis Membrane Process for Forward Operating Base Wastewater Reuse

DTIC Science & Technology

2014-08-01

of the GEGR pilot membrane coater; b) configuration of the coating station; and c) web path of the dip-knife coating process for RO membrane...Energy-dispersive X-ray spectroscopy EPA Environmental Protection Agency F:M Food-To-Microorganism Ratio FOB Forward Operating Base FT- IR Fourier...report 03/2014 3.3 Submit draft Interim report/Go No-Go decision point white paper 05/2013 3.4 Submit final report 05/2014 3.5 Final debrief

HL-10 pilots assist with pilot entry into lifting body

NASA Technical Reports Server (NTRS)

1969-01-01

Not every moment of a test pilot's day is serious business. In a moment of levity, NASA pilots Bill Dana (left) and John A. Manke try to drag Air Force test pilot Peter Hoag away from the HL-10 lifting body while Air Force Major Jerauld R. Gentry helps from the cockpit. These four men were the principal pilots for the HL-10 program. This was not the only prank involving the HL-10 and its pilots. Once 'Captain Midnight' (Gentry) and the 'Midnight skulkers' sneaked into the NASA hangar and put 'U.S. Air Force' on the aircraft using stick-on letters. Later, while Gentry was making a lifting-body flight, his 1954 Ford was 'borrowed' from the parking lot, painted with yellow-green zinc-chromate primer, and decorated with large stick-on flowers about one foot in diameter. After Gentry returned from the flight, he was surprised to see what had happened to his car. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

E56-2607

NASA Image and Video Library

1956-10-08

Famed astronaut Neil A. Armstrong, the first man to set foot on the moon during the historic Apollo 11 space mission in July 1969, served for seven years as a research pilot at the NACA-NASA High-Speed Flight Station, now the Dryden Flight Research Center, at Edwards, California, before he entered the space program. Armstrong joined the National Advisory Committee for Aeronautics (NACA) at the Lewis Flight Propulsion Laboratory (later NASA's Lewis Research Center, Cleveland, Ohio, and today the Glenn Research Center) in 1955. Later that year, he transferred to the High-Speed Flight Station at Edwards as an aeronautical research scientist and then as a pilot, a position he held until becoming an astronaut in 1962. He was one of nine NASA astronauts in the second class to be chosen. As a research pilot Armstrong served as project pilot on the F-100A and F-100C aircraft, F-101, and the F-104A. He also flew the X-1B, X-5, F-105, F-106, B-47, KC-135, and Paresev. He left Dryden with a total of over 2450 flying hours. He was a member of the USAF-NASA Dyna-Soar Pilot Consultant Group before the Dyna-Soar project was cancelled, and studied X-20 Dyna-Soar approaches and abort maneuvers through use of the F-102A and F5D jet aircraft. Armstrong was actively engaged in both piloting and engineering aspects of the X-15 program from its inception. He completed the first flight in the aircraft equipped with a new flow-direction sensor (ball nose) and the initial flight in an X-15 equipped with a self-adaptive flight control system. He worked closely with designers and engineers in development of the adaptive system, and made seven flights in the rocket plane from December 1960 until July 1962. During those fights he reached a peak altitude of 207,500 feet in the X-15-3, and a speed of 3,989 mph (Mach 5.74) in the X-15-1. Armstrong has a total of 8 days and 14 hours in space, including 2 hours and 48 minutes walking on the Moon. In March 1966 he was commander of the Gemini 8 or

Oxygen Mask Related Nasal Integument and Osteocartilagenous Disorders in F-16 Fighter Pilots

PubMed Central

Schreinemakers, J. Rieneke C.; Westers, Paul; van Amerongen, Pieter; Kon, Moshe

2013-01-01

Background A preliminary survey showed half of the participating Royal Netherlands Air Force (RNLAF) F-16 fighter pilots to have nasal integument and osteocartilagenous disorders related to wearing in-flight oxygen masks. Aim To make an inventory of these disorders and possible associated factors. Methods All RNLAF F-16 pilots were requested to fill out a semi-structured questionnaire for a cross-sectional survey. Additionally, one squadron in The Netherlands and pilots in operational theater were asked to participate in a prospective study that required filling out a pain score after each flight. Pilot- and flight-related variables on all participants were collected from the RNLAF database. A linear mixed model was built to identify associated factors with the post-flight pain score. Results The response rate to the survey was 83%. Ninety of the 108 participants (88%, 6 missing) reported tenderness, irritation, pain, erythema, skin lesions, callous skin, or swelling of nasal bridge integument or architecture. Seventy-two participants (71%, 6 missing) reported their symptoms to be troublesome after a mean of 6±3 out of 10 flights (0;10, 54 missing). Sixty-six pilots participated in scoring post-flight pain. Pain scores were significantly higher if a participant had ≥3 nasal disorders, after longer than average flights, after flying abroad, and after flying with night vision goggles (respectively +2.7 points, p = 0.003; +0.2 points, p = 0.027; +1.8 points, p = 0.001; +1.2 points p = 0.005). Longer than average NVG flights and more than average NVG hours per annum decreased painscores (respectively −0.8 points, p = 0.017; −0.04 points, p = 0.005). Conclusions The majority of the RNLAF F-16 fighter pilot community has nasal disorders in the contact area of the oxygen mask, including pain. Six pilot- or flight-related characteristics influence the experienced level of pain. PMID:23505413

Oxygen mask related nasal integument and osteocartilagenous disorders in F-16 fighter pilots.

PubMed

Schreinemakers, J Rieneke C; Westers, Paul; van Amerongen, Pieter; Kon, Moshe

2013-01-01

A preliminary survey showed half of the participating Royal Netherlands Air Force (RNLAF) F-16 fighter pilots to have nasal integument and osteocartilagenous disorders related to wearing in-flight oxygen masks. To make an inventory of these disorders and possible associated factors. All RNLAF F-16 pilots were requested to fill out a semi-structured questionnaire for a cross-sectional survey. Additionally, one squadron in The Netherlands and pilots in operational theater were asked to participate in a prospective study that required filling out a pain score after each flight. Pilot- and flight-related variables on all participants were collected from the RNLAF database. A linear mixed model was built to identify associated factors with the post-flight pain score. The response rate to the survey was 83%. Ninety of the 108 participants (88%, 6 missing) reported tenderness, irritation, pain, erythema, skin lesions, callous skin, or swelling of nasal bridge integument or architecture. Seventy-two participants (71%, 6 missing) reported their symptoms to be troublesome after a mean of 6±3 out of 10 flights (0;10, 54 missing). Sixty-six pilots participated in scoring post-flight pain. Pain scores were significantly higher if a participant had ≥3 nasal disorders, after longer than average flights, after flying abroad, and after flying with night vision goggles (respectively +2.7 points, p = 0.003; +0.2 points, p = 0.027; +1.8 points, p = 0.001; +1.2 points p = 0.005). Longer than average NVG flights and more than average NVG hours per annum decreased painscores (respectively -0.8 points, p = 0.017; -0.04 points, p = 0.005). The majority of the RNLAF F-16 fighter pilot community has nasal disorders in the contact area of the oxygen mask, including pain. Six pilot- or flight-related characteristics influence the experienced level of pain.

Research pilot and former astronaut C. Gordon Fullerton in an F/A-18

NASA Image and Video Library

2002-05-14

Former NASA astronaut C. Gordon Fullerton, seated in the cockpit of an F/A-18, is a research pilot at NASA's Dryden Flight Research Center, Edwards, Calif. Since transferring to Dryden in 1986, his assignments have included a variety of flight research and support activities piloting NASA's B-52 launch aircraft, the 747 Shuttle Carrier Aircraft (SCA), and other multi-engine and high performance aircraft. He flew a series of development air launches of the X-38 prototype Crew Return Vehicle and in the launches for the X-43A Hyper-X project. Fullerton also flies Dryden's DC-8 Airborne Science aircraft in support a variety of atmospheric physics, ground mapping and meteorology studies. Fullerton also was project pilot on the Propulsion Controlled Aircraft program, during which he successfully landed both a modified F-15 and an MD-11 transport with all control surfaces neutralized, using only engine thrust modulation for control. Fullerton also evaluated the flying qualities of the Russian Tu-144 supersonic transport during two flights in 1998, one of only two non-Russian pilots to fly that aircraft. With more than 15,000 hours of flying time, Fullerton has piloted 135 different types of aircraft in his career. As an astronaut, Fullerton served on the support crews for the Apollo 14, 15, 16, and 17 lunar missions. In 1977, Fullerton was on one of the two flight crews that piloted the Space Shuttle prototype Enterprise during the Approach and Landing Test Program at Dryden. Fullerton was the pilot on the STS-3 Space Shuttle orbital flight test mission in 1982, and commanded the STS-51F Spacelab 2 mission in 1985. He has logged 382 hours in space flight. In July 1988, he completed a 30-year career with the U.S. Air Force and retired as a colonel.

Commander Brand and Pilot Overmyer operate controls on forward flight deck

NASA Technical Reports Server (NTRS)

1982-01-01

On forward flight deck, Commander Brand and Pilot Overmyer operate controls from commanders and pilots seats. Overall view taken from the aft flight deck looking forward shows Overmyer pointing to data on Panel 7 (F7) CRT 1 screen.

M2-F1 in flight over lakebed on tow line

NASA Image and Video Library

1963-08-30

Following the first M2-F1 airtow flight on 16 August 1963, the Flight Research Center used the vehicle for both research flights and to check out new lifting-body pilots. These included Bruce Peterson, Don Mallick, Fred Haise, and Bill Dana from NASA. Air Force pilots who flew the M2-F1 included Chuck Yeager, Jerry Gentry, Joe Engle, Jim Wood, and Don Sorlie, although Wood, Haise, and Engle only flew on car tows. In the three years between the first and last flights of the M2-F1, it made about 400 car tows and 77 air tows.

Flight testing the digital electronic engine control in the F-15 airplane

NASA Technical Reports Server (NTRS)

Myers, L. P.

1984-01-01

The digital electronic engine control (DEEC) is a full-authority digital engine control developed for the F100-PW-100 turbofan engine which was flight tested on an F-15 aircraft. The DEEC hardware and software throughout the F-15 flight envelope was evaluated. Real-time data reduction and data display systems were implemented. New test techniques and stronger coordination between the propulsion test engineer and pilot were developed which produced efficient use of test time, reduced pilot work load, and greatly improved quality data. The engine pressure ratio (EPR) control mode is demonstrated. It is found that the nonaugmented throttle transients and engine performance are satisfactory.

Real-Time State Estimation in a Flight Simulator Using fNIRS

PubMed Central

Gateau, Thibault; Durantin, Gautier; Lancelot, Francois; Scannella, Sebastien; Dehais, Frederic

2015-01-01

Working memory is a key executive function for flying an aircraft. This function is particularly critical when pilots have to recall series of air traffic control instructions. However, working memory limitations may jeopardize flight safety. Since the functional near-infrared spectroscopy (fNIRS) method seems promising for assessing working memory load, our objective is to implement an on-line fNIRS-based inference system that integrates two complementary estimators. The first estimator is a real-time state estimation MACD-based algorithm dedicated to identifying the pilot’s instantaneous mental state (not-on-task vs. on-task). It does not require a calibration process to perform its estimation. The second estimator is an on-line SVM-based classifier that is able to discriminate task difficulty (low working memory load vs. high working memory load). These two estimators were tested with 19 pilots who were placed in a realistic flight simulator and were asked to recall air traffic control instructions. We found that the estimated pilot’s mental state matched significantly better than chance with the pilot’s real state (62% global accuracy, 58% specificity, and 72% sensitivity). The second estimator, dedicated to assessing single trial working memory loads, led to 80% classification accuracy, 72% specificity, and 89% sensitivity. These two estimators establish reusable blocks for further fNIRS-based passive brain computer interface development. PMID:25816347

HL-10 on lakebed with pilot Major Jerauld R. Gentry

NASA Technical Reports Server (NTRS)

1968-01-01

Pilot Major Jerauld R. Gentry stands in front of the HL-10 Lifting Body. Gentry was the Air Force project pilot for the HL-10 while it was making the early glide and powered flights in 1968 following its modification. He made a total of nine flights in the vehicle. For his work on the HL-10, Gentry was awarded the Harmon International Trophy for his outstanding contribution to the science of flying. He later became the Air Force pilot for the X-24A. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Retired NASA research pilot and former astronaut Gordon Fullerton was greeted by scores of NASA Dryden staff who bid him farewell after his final NASA flight.

NASA Image and Video Library

2007-12-21

Long-time NASA Dryden research pilot and former astronaut C. Gordon Fullerton capped an almost 50-year flying career, including more than 38 years with NASA, with a final flight in a NASA F/A-18 on Dec. 21, 2007. Fullerton and Dryden research pilot Jim Smolka flew a 90-minute pilot proficiency formation aerobatics flight with another Dryden F/A-18 and a Dryden T-38 before concluding with two low-level formation flyovers of Dryden before landing. Fullerton was honored with a water-cannon spray arch provided by two fire trucks from the Edwards Air Force Base fire department as he taxied the F/A-18 up to the Dryden ramp, and was then greeted by his wife Marie and several hundred Dryden staff after his final flight. Fullerton began his flying career with the U.S. Air Force in 1958 after earning bachelor's and master's degrees in mechanical engineering from the California Institute of Technology. Initially trained as a fighter pilot, he later transitioned to multi-engine bombers and became a bomber operations test pilot after attending the Air Force Aerospace Research Pilot School at Edwards Air Force Base, Calif. He then was assigned to the flight crew for the planned Air Force Manned Orbital Laboratory in 1966. Upon cancellation of that program, the Air Force assigned Fullerton to NASA's astronaut corps in 1969. He served on the support crews for the Apollo 14, 15, 16 and 17 lunar missions, and was later assigned to one of the two flight crews that piloted the space shuttle prototype Enterprise during the Approach and Landing Test program at Dryden. He then logged some 382 hours in space when he flew on two early space shuttle missions, STS-3 on Columbia in 1982 and STS-51F on Challenger in 1985. He joined the flight crew branch at NASA Dryden after leaving the astronaut corps in 1986. During his 21 years at Dryden, Fullerton was project pilot on a number of high-profile research efforts, including the Propulsion Controlled Aircraft, the high-speed landing tests of

HL-10 on lakebed with Jerauld R. Gentry, Peter Hoag, John A. Manke, and Bill Dana

NASA Technical Reports Server (NTRS)

1969-01-01

The four principal HL-10 pilots are seen here with the lifting body aircraft. They are, left to right; Air Force Major Jerauld R. Gentry, Air Force test pilot Peter Hoag, and NASA pilots John A. Manke and Bill Dana. All are wearing the pressure suits needed for flying above 50,000 feet. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Functional neuroimaging of emotional processing in women with polycystic ovary syndrome: a case-control pilot study

PubMed Central

Marsh, Courtney A.; Berent-Spillson, Alison; Love, Tiffany; Persad, Carol C.; Pop-Busui, Rodica; Zubieta, Jon-Kar; Smith, Yolanda R.

2013-01-01

Objective To evaluate emotional processing in women with insulin-resistant polycystic ovary syndrome (IR-PCOS) and its relationship to glucose regulation and the mu-opioid system. Design Case-control pilot. Setting Tertiary referring medical center. Patient(s) Seven women with IR-PCOS and five non-insulin-resistant controls, aged 21–40 years, recruited from the general population. Intervention(s) Sixteen weeks of metformin (1,500 mg/day) in women with IR-PCOS. Main Outcome Measure(s) Assessment of mood, metabolic function, and neuronal activation during an emotional task using functional magnetic resonance imaging (fMRI), and mu-opioid receptor availability using positive emission tomography (PET). Result(s) We found that insulin-resistant PCOS patients [1] had greater limbic activation during an emotion task than controls (n = 5); [2] trended toward decreased positive affect and increased trait anxiety; [3] after metformin treatment, had limbic activation that no longer differed from controls; and [4] had positive correlations between fMRI limbic activation during emotional processing and mu-opioid binding potential. Conclusion(s) Patients with IR-PCOS had greater regional activation during an emotion task than the controls, although this resolved with metformin therapy. Alterations in mu-opioid neurotransmission may underlie limbic system activity and mood disorders in IR-PCOS. Clinical Trial Registration Number NCT00670800. PMID:23557757

Piloted Parameter Identification Flight Test Maneuvers for Closed Loop Modeling of the F-18 High Alpha Research Vehicle (HARV)

NASA Technical Reports Server (NTRS)

Morelli, Eugene A.

1996-01-01

Flight test maneuvers are specified for the F-18 High Alpha Research Vehicle (HARV). The maneuvers were designed for closed loop parameter identification purposes, specifically for longitudinal and lateral linear model parameter estimation at 5, 20, 30, 45, and 60 degrees angle of attack, using the NASA 1A control law. Each maneuver is to be realized by the pilot applying square wave inputs to specific pilot station controls. Maneuver descriptions and complete specifications of the time/amplitude points defining each input are included, along with plots of the input time histories.

Aircraft digital flight control technical review

NASA Technical Reports Server (NTRS)

Davenport, Otha B.; Leggett, David B.

1993-01-01

The Aircraft Digital Flight Control Technical Review was initiated by two pilot induced oscillation (PIO) incidents in the spring and summer of 1992. Maj. Gen. Franklin (PEO) wondered why the Air Force development process for digital flight control systems was not preventing PIO problems. Consequently, a technical review team was formed to examine the development process and determine why PIO problems continued to occur. The team was also to identify the 'best practices' used in the various programs. The charter of the team was to focus on the PIO problem, assess the current development process, and document the 'best practices.' The team reviewed all major USAF aircraft programs with digital flight controls, specifically, the F-15E, F-16C/D, F-22, F-111, C-17, and B-2. The team interviewed contractor, System Program Office (SPO), and Combined Test Force (CTF) personnel on these programs. The team also went to NAS Patuxent River to interview USN personnel about the F/A-18 program. The team also reviewed experimental USAF and NASA systems with digital flight control systems: X-29, X-31, F-15 STOL and Maneuver Technology Demonstrator (SMTD), and the Variable In-Flight Stability Test Aircraft (VISTA). The team also discussed the problem with other experts in the field including Ralph Smith and personnel from Calspan. The major conclusions and recommendations from the review are presented.

Evaluation of Two Unique Side Stick Controllers in a Fixed-Base Flight Simulator

NASA Technical Reports Server (NTRS)

Mayer, Jann; Cox, Timothy H.

2003-01-01

A handling qualities analysis has been performed on two unique side stick controllers in a fixed-base F-18 flight simulator. Each stick, which uses a larger range of motion than is common for similar controllers, has a moving elbow cup that accommodates movement of the entire arm for control. The sticks are compared to the standard center stick in several typical fighter aircraft tasks. Several trends are visible in the time histories, pilot ratings, and pilot comments. The aggressive pilots preferred the center stick, because the side sticks are underdamped, causing overshoots and oscillations when large motions are executed. The less aggressive pilots preferred the side sticks, because of the smooth motion and low breakout forces. The aggressive pilots collectively gave the worst ratings, probably because of increased sensitivity of the simulator (compared to the actual F-18 aircraft), which can cause pilot-induced oscillations when aggressive inputs are made. Overall, the elbow cup is not a positive feature, because using the entire arm for control inhibits precision. Pilots had difficulty measuring their performance, particularly during the offset landing task, and tended to overestimate.

Sustaining the Drone Enterprise: How Manpower Analysis Engendered Policy Reform in the United States Air Force

DTIC Science & Technology

2016-01-17

permanently transitioned to the RPA community. (E.g., an F-16 pilot who permanently becomes an RPA pilot). “Borrowed” pilots, officially called “ ALFAs ...initiative as of October 2015. 2) Hold ALFA pilots an additional 3 “Vulnerable to Move List” (VML) cycles. The standard ALFA tour for pilots of manned...Given this policy to hold the ALFAs for an additional three VML cycles, the RPA enterprise will retain approximately 60 ALFA pilots for an additional

Symposium on the reprocessing of irradiated fuels. Book 2, Session IV

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

None

1958-12-31

Book two of this conference has a single-focused session IV entitled Nonaqueous Processing, with 8 papers. The session deals with fluoride volatility processes and pyrometallurgical or pyrochemical processes. The latter involves either an oxide drossing or molten metal extraction or fused salt extraction technique and results in only partial decontamination. Fluoride volatility processes appear to be especially favorable for recovery of enriched uranium and decontamination factors of 10/sup 7/ to 10/sup 8/ would be achieved by simpler means than those employed in solvent extraction. Data from lab research on the BrF/sub 3/ process and the ClF/sub 3/ process are givenmore » and discussed and pilot plant experience is described, all in connection with natural uranium or slightly enriched uranium processing. Fluoride volatility processes for enriched or high alloy fuels are described step by step. The economic and engineering considerations of both types of nonaqueous processing are treated separately and as fully as present knowledge allows. A comprehensive review of the chemistry of pyrometallurgical processes is included.« less

Measuring Pilot Proficiency on an Instrument Training Maneuver

DTIC Science & Technology

1977-08-01

Psychological research on pilot training. Was--sngton, D. C.: Army Air Force Aviation Psychology Program, Research Report No. 8, 1947. Ericksen, S. C. A review...10 15 20 su m I S =. 24 S". **muz . Atars &f 300ft. of clim (Mappro&W~may 15300’) a&& at J.5W f t. Soabding P. Mmcav ad nmur4 thwouoww.c tb. &*ou 25 mvi

46 CFR 15.812 - Pilots.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 46 Shipping 1 2010-10-01 2010-10-01 false Pilots. 15.812 Section 15.812 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY MERCHANT MARINE OFFICERS AND SEAMEN MANNING REQUIREMENTS Computations § 15.812 Pilots. (a) Except as specified in paragraph (f) of this section, the following vessels, not...

46 CFR 15.812 - Pilots.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 1 2011-10-01 2011-10-01 false Pilots. 15.812 Section 15.812 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY MERCHANT MARINE OFFICERS AND SEAMEN MANNING REQUIREMENTS Computations § 15.812 Pilots. (a) Except as specified in paragraph (f) of this section, the following vessels, not...

46 CFR 15.812 - Pilots.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 46 Shipping 1 2013-10-01 2013-10-01 false Pilots. 15.812 Section 15.812 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY MERCHANT MARINE OFFICERS AND SEAMEN MANNING REQUIREMENTS Computations § 15.812 Pilots. (a) Except as specified in paragraph (f) of this section, the following vessels, not...

46 CFR 15.812 - Pilots.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 46 Shipping 1 2012-10-01 2012-10-01 false Pilots. 15.812 Section 15.812 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY MERCHANT MARINE OFFICERS AND SEAMEN MANNING REQUIREMENTS Computations § 15.812 Pilots. (a) Except as specified in paragraph (f) of this section, the following vessels, not...

46 CFR 15.812 - Pilots.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 46 Shipping 1 2014-10-01 2014-10-01 false Pilots. 15.812 Section 15.812 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY MERCHANT MARINE OFFICERS AND SEAMEN MANNING REQUIREMENTS Computations § 15.812 Pilots. (a) Except as specified in paragraph (f) of this section, the following vessels, not...

14 CFR 121.439 - Pilot qualification: Recent experience.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot qualification: Recent experience. 121... Pilot qualification: Recent experience. Link to an amendment published at 78 FR 67841, Nov. 12, 2013. (a... qualification: Recent experience. (f) Deviation authority based upon designation of related aircraft in...

M2-F2 with test pilot Bruce A. Peterson

NASA Image and Video Library

1966-09-22

Bruce A. Peterson standing beside the M2-F2 lifting body on Rogers Dry Lake. Peterson became the NASA project pilot for the lifting body program after Milt Thompson retired from flying in late 1966. Peterson had flown the M2-F1, and made the first glide flight of the HL-10 heavy-weight lifting body in December 1966. On May 10, 1967, Peterson made his fourth glide flight in the M2-F2. This was also the M2-F2's 16th glide flight, scheduled to be the last one before the powered flights began. However, as pilot Bruce Peterson neared the lakebed, the M2-F2 suffered a pilot induced oscillation (PIO). The vehicle rolled from side to side in flight as he tried to bring it under control. Peterson recovered, but then observed a rescue helicopter that seemed to pose a collision threat. Distracted, Peterson drifted in a cross-wind to an unmarked area of the lakebed where it was very difficult to judge the height over the lakebed because of a lack of the guidance the markers provided on the lakebed runway. Peterson fired the landing rockets to provide additional lift, but he hit the lakebed before the landing gear was fully down and locked. The M2-F2 rolled over six times, coming to rest upside down. Pulled from the vehicle by Jay King and Joseph Huxman, Peterson was rushed to the base hospital, transferred to March Air Force Base and then the UCLA Hospital. He recovered but lost vision in his right eye due to a staph infection.

Richard G. Ewers

NASA Image and Video Library

1998-12-02

Richard G. (Dick) Ewers became a pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, California, in May 1998. His flying duties focus on operation of the Airborne Science DC-8 and Systems Research F/A-18 aircraft, but he also maintains qualifications in the King Air and T-34C. He has more than 32 years and nearly 9,000 hours of military and civilian flight experience in all types of aircraft from jet fighters to blimps. Ewers came to NASA Dryden from a position as an engineering test pilot with Northrop Grumman's Electronic Sensors and Systems Division (formerly Westinghouse's Electronic Systems Group). He spent eight and a half years with Westinghouse flight testing radar and forward looking infrared systems under development for military and civilian use. Before going to work for Westinghouse, Ewers served for more than 21 years as a U.S. Marine Corps fighter and test pilot, flying F-4, A-4, and F/A-18 aircraft. He underwent flight training at Naval Air Station Pensacola, Fla., in 1969-70. He was subsequently assigned to both fighter/attack and reconnaissance squadrons before ultimately commanding an F-4S squadron for two years. Additionally, his flying included combat service in Vietnam and operational exchange tours with both U.S. Navy and U.S. Air Force squadrons flying F-4s around the world, including off aircraft carriers. Ewers graduated from the U.S. Naval Test Pilot School in 1981 and subsequently served two tours as a test pilot at the Naval Air Test Center, Patuxent River, Md. Most of his flight test experience was with the F/A-18 Hornet. He retired from the Marine Corps in 1989 with the rank of lieutenant colonel. Ewers graduated from the U.S. Air Force Academy in 1968 with a bachelor of science degree in engineering mechanics. He earned a master of science degree in aeronautical systems from the University of West Florida in 1970.

Subsonic stability and control derivatives for an unpowered, remotely piloted 3/8-scale F-15 airplane model obtained from flight test

NASA Technical Reports Server (NTRS)

Iliff, K. W.; Maine, R. E.; Shafer, M. F.

1976-01-01

In response to the interest in airplane configuration characteristics at high angles of attack, an unpowered remotely piloted 3/8-scale F-15 airplane model was flight tested. The subsonic stability and control characteristics of this airplane model over an angle of attack range of -20 to 53 deg are documented. The remotely piloted technique for obtaining flight test data was found to provide adequate stability and control derivatives. The remotely piloted technique provided an opportunity to test the aircraft mathematical model in an angle of attack regime not previously examined in flight test. The variation of most of the derivative estimates with angle of attack was found to be consistent, particularly when the data were supplemented by uncertainty levels.

Development and manufacture of visor for helmet-mounted display

NASA Astrophysics Data System (ADS)

Krevor, David H.; McNelly, Gregg; Skubon, John; Speirs, Robert

2004-01-01

The manufacturing design and process development for the Visor for the JHMCS (Joint Helmet Mounted Cueing System) are discussed. The JHMCS system is a Helmet Mounted Display (HMD) system currently flying on the F-15, F-16 and F/A-18 aircraft. The Visor manufacturing processes are essential to both system performance and economy. The Visor functions both as the system optical combiner and personal protective equipment for the pilot. The Visor material is optical polycarbonate. For a military HMD system, the mechanical and environmental properties of the Visor are as necessary as the optical properties. The visor must meet stringent dimensional requirements to assure adequate system optical performance. Injection molding can provide dimensional fidelity to the requirements, if done properly. Concurrent design of the visor and the tool (i.e., the injection mold) is essential. The concurrent design necessarily considers manufacturing operations and the use environment of the Visor. Computer modeling of the molding process is a necessary input to the mold design. With proper attention to product design and tool development, it is possible to improve upon published standard dimensional tolerances for molded polycarbonate articles.

Description and theory of operation of the computer by-pass system for the NASA F-8 digital fly-by-wire control system

NASA Technical Reports Server (NTRS)

1978-01-01

A triplex digital flight control system was installed in a NASA F-8C airplane to provide fail operate, full authority control. The triplex digital computers and interface circuitry process the pilot commands and aircraft motion feedback parameters according to the selected control laws, and they output the surface commands as an analog signal to the servoelectronics for position control of the aircraft's power actuators. The system and theory of operation of the computer by pass and servoelectronics are described and an automated ground test for each axis is included.

Preparation and Design for a Training Effectiveness Evaluation of Device 2F64C for Replacement Pilot Training.

ERIC Educational Resources Information Center

Browning, Robert F.; And Others

This report details the setting up of a program to assess the training potential of a new simulator (Device 2F64C) for training SH-3 replacement helicopter pilots. Section 2 describes the training situation at the fleet readiness squadron prior to and during the transition to a new curriculum that resulted from an instructional system development…

Pilot Decision-Making Training

DTIC Science & Technology

1990-05-01

Pilot Decisional Attitude Questionnaire (PDAQ). 2. Aeronautical Decision Making . a. The pilot judgment problem b. Relationship of judgment to training...lmEr OAT . REPOR TYPE ANO GATES COVEIRO May 1990 Final - June 1985 - December 1988 4 .MU AN m . .m m t 4i C ’u. SUM L FUNING MUMBRS Pilot Decision - Making ...13 AGSTRACT (Maxu’m 200 wo f -The effectiveness of a simulator-based approach to training pilot skills in risk assessment and decision making was

Higher landing accuracy in expert pilots is associated with lower activity in the caudate nucleus.

PubMed

Adamson, Maheen M; Taylor, Joy L; Heraldez, Daniel; Khorasani, Allen; Noda, Art; Hernandez, Beatriz; Yesavage, Jerome A

2014-01-01

The most common lethal accidents in General Aviation are caused by improperly executed landing approaches in which a pilot descends below the minimum safe altitude without proper visual references. To understand how expertise might reduce such erroneous decision-making, we examined relevant neural processes in pilots performing a simulated landing approach inside a functional MRI scanner. Pilots (aged 20-66) were asked to "fly" a series of simulated "cockpit view" instrument landing scenarios in an MRI scanner. The scenarios were either high risk (heavy fog-legally unsafe to land) or low risk (medium fog-legally safe to land). Pilots with one of two levels of expertise participated: Moderate Expertise (Instrument Flight Rules pilots, n = 8) or High Expertise (Certified Instrument Flight Instructors or Air-Transport Pilots, n = 12). High Expertise pilots were more accurate than Moderate Expertise pilots in making a "land" versus "do not land" decision (CFII: d' = 3.62 ± 2.52; IFR: d' = 0.98 ± 1.04; p<.01). Brain activity in bilateral caudate nucleus was examined for main effects of expertise during a "land" versus "do not land" decision with the no-decision control condition modeled as baseline. In making landing decisions, High Expertise pilots showed lower activation in the bilateral caudate nucleus (0.97 ± 0.80) compared to Moderate Expertise pilots (1.91 ± 1.16) (p<.05). These findings provide evidence for increased "neural efficiency" in High Expertise pilots relative to Moderate Expertise pilots. During an instrument approach the pilot is engaged in detailed examination of flight instruments while monitoring certain visual references for making landing decisions. The caudate nucleus regulates saccade eye control of gaze, the brain area where the "expertise" effect was observed. These data provide evidence that performing "real world" aviation tasks in an fMRI provide objective data regarding the relative expertise of pilots and brain regions involved in it.

Space shuttle pilot-induced-oscillation research testing

NASA Technical Reports Server (NTRS)

Powers, B. G.

1984-01-01

The simulation requirements for investigation of pilot-induced-oscillation (PIO) characteristics during the landing phase are discussed. Orbiters simulations and F-8 digital fly-by-wire aircraft tests are addressed.

Ed Schneider gives a "thumbs-up" after his last flight at the Dryden Flight Research Center

NASA Image and Video Library

2000-09-19

In a lighter mood, Ed Schneider gives a "thumbs-up" after his last flight at the Dryden Flight Research Center on September 19, 2000. Schneider arrived at the NASA Ames-Dryden Flight Research Facility on July 5, 1982, as a Navy Liaison Officer, becoming a NASA research pilot one year later. He has been project pilot for the F-18 High Angle-of-Attack program (HARV), the F-15 aeronautical research aircraft, the NASA B-52 launch aircraft, and the SR-71 "Blackbird" aircraft. He also participated in such programs as the F-8 Digital Fly-By-Wire, the FAA/NASA 720 Controlled Impact Demonstration, the F-14 Automatic Rudder Interconnect and Laminar Flow, and the F-104 Aeronautical Research and Microgravity projects.

Analysis of pilot control strategy

NASA Technical Reports Server (NTRS)

Heffley, R. K.; Hanson, G. D.; Jewell, W. F.; Clement, W. F.

1983-01-01

Methods for nonintrusive identification of pilot control strategy and task execution dynamics are presented along with examples based on flight data. The specific analysis technique is Nonintrusive Parameter Identification Procedure (NIPIP), which is described in a companion user's guide (NASA CR-170398). Quantification of pilot control strategy and task execution dynamics is discussed in general terms followed by a more detailed description of how NIPIP can be applied. The examples are based on flight data obtained from the NASA F-8 digital fly by wire airplane. These examples involve various piloting tasks and control axes as well as a demonstration of how the dynamics of the aircraft itself are identified using NIPIP. Application of NIPIP to the AFTI/F-16 flight test program is discussed. Recommendations are made for flight test applications in general and refinement of NIPIP to include interactive computer graphics.

Faith-based intervention to increase fruit and vegetable intake among Koreans in the USA: a feasibility pilot.

PubMed

Hughes, Suzanne C; Obayashi, Saori

2017-02-01

In the USA, adults of Korean descent tend to eat fewer vegetables than adults in South Korea. The present pilot study examined the feasibility of developing and implementing a faith-based intervention to improve knowledge, attitudes and intake of fruit and vegetables (F&V) for Koreans in the USA. Feasibility pilot using a cluster-randomized intervention trial design. The multicomponent intervention included motivational interviewing sessions by telephone and church-based group activities. Eleven of the largest Korean churches in Southern California. Adults (n 71) from the eleven Korean churches. Feasibility was demonstrated for the study procedures, including recruitment of churches and individual participants. Allocating time throughout the study for church collaboration and having a study church coordinator to coordinate multiple churches were crucial. Participants' attendance at church activities (89 %) and participation by pastors and fellow churchgoers exceeded expectations. Participants' use of intervention materials was high (94 % or above) and satisfaction with coaching sessions was also high (75 % or above). Having a centralized coach trained in motivational interviewing, instead of one at each church, proved practical. Pilot results are promising for F&V knowledge, attitudes and behaviours. The intervention group improved knowledge and intake of the recommended amounts of F&V, above that of the control group. This pilot suggests that Koreans in the USA can be reached through their church and that a faith-based intervention study can be implemented to increase F&V intake. Preliminary results for the intervention appear promising but further research is needed to properly evaluate its efficacy.

HL-10 after first flight with pilot Bruce Peterson

NASA Technical Reports Server (NTRS)

1966-01-01

The HL-10 after its first flight, shown with pilot Bruce Peterson. Although the lifting-body aircraft was predicted to have good flying qualities, this first flight showed major control and stability problems. The cause was airflow separation from the vehicle's fins. Changes to the fins' leading-edge shape fixed the problem. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 on lakebed with pilot John Manke

NASA Technical Reports Server (NTRS)

1969-01-01

John Manke is shown here on the lakebed next to the HL-10, one of four different lifting-body vehicles he flew, including the X-24B, which he flew 16 times. His total of 42 lifting-body flights was second only to the 51 flights Milt Thompson achieved, including one in the remotely piloted Hyper III. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 on lakebed with pilot Bill Dana

NASA Technical Reports Server (NTRS)

1969-01-01

This photo shows the HL-10 on Rogers Dry Lakebed with pilot Bill Dana in the foreground. Bill joined the HL-10 program in 1969 after flying the M2-F1 and the X-15, among other aircraft. His first glide flight was on April 25, 1969. Some months later, on September 3, 1969, he reached an altitude of 77,960 feet. This was one of a series of HL-10 flights to collect stability and control data at higher speeds and altitudes and at different angles of attack. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

General Aviation Weather Encounter Case Studies

DOT National Transportation Integrated Search

2012-09-01

This study presents a compilation of 24 cases involving general aviation (GA) pilots weather encounters over the : continental U.S. The project team interviewed pilots who had experienced a weather encounter, and we : examined their backgrounds, f...

Development of a remote digital augmentation system and application to a remotely piloted research vehicle

NASA Technical Reports Server (NTRS)

Edwards, J. W.; Deets, D. A.

1975-01-01

A cost-effective approach to flight testing advanced control concepts with remotely piloted vehicles is described. The approach utilizes a ground based digital computer coupled to the remotely piloted vehicle's motion sensors and control surface actuators through telemetry links to provide high bandwidth feedback control. The system was applied to the control of an unmanned 3/8-scale model of the F-15 airplane. The model was remotely augmented; that is, the F-15 mechanical and control augmentation flight control systems were simulated by the ground-based computer, rather than being in the vehicle itself. The results of flight tests of the model at high angles of attack are discussed.

53 Piloting patch - providing assessment and treatment for children at home - and piecing together what works.

PubMed

Ward, Caroline; Knight, Katie; Ballard, Mary-Rose; Keogh, Georgina; Samuel, Miriam; Buttle, Sara; Robb, Claire; Cleugh, Francesca

2017-12-01

PATCH is a pilot acute community children's nurse led service delivering assessment and treatment for children at home who are moderately unwell and might otherwise be admitted to hospital or attend Paediatric Emergency Department (PED). Children are referred by PED or GP and followed up via telephone support and home visits depending on clinical need for duration of acute illness. Pilot year funded by Imperial Charity. Using evaluation to build business case for sustained commissioned service. Phase 1 Sept 2016 - May 2017 : reduced short stay admissions and re-attendances to PED for common mild-moderate respiratory conditions e.g., viral wheeze, bronchiolitis. Phase 2 from May 2017 : piloting direct GP referrals to PATCH team to evaluate impact in reducing attendances to PED for children needing further assessment or support beyond GP consultation, and enabling families to manage common acute conditions at home.Using QI methodology, Model for Improvement we developed a driver diagram and used real-time PDSA cycles to capture our learning and inform small iterative changes of service development. Process mapping and world cafe style events were held with local community nurses, health visitor leads, GPs and commissioners to co-design referral pathways and explore more widely how PATCH fits into the whole urgent care system.emermed;34/12/A895-b/F1F1F1Figure 1Parental feedback evaluated via semi structured interviews. Activity - Appendix 1Phase 1 - Concentrated on respiratory conditions from PED.Total 188 referrals in first 7 months. Bronchiolitis 45%; viral wheeze 37.5%; asthma 7%; lower respiratory tract infections 5.4%.emermed;34/12/A895-b/F2F2F2Figure 250% of patients received home visits and telephone consultations; 50% only telephone support.Successes: Cost effective - Appendix 273 acute admissions avoided, costing c£400 per/night97 PED re-attendances prevented at £117 per attendance.Projected cost avoidance within acute care provider £3 27 640 pa.Estimated cost of service £2 84 000 pa.Positive feedback and reported health seeking behaviour change - Appendix 3 CHALLENGES: Information governance, cross organisational working, complex commissioning arrangements.emermed;34/12/A895-b/F3F3F3Figure 3 DISCUSSION: Within first 7 months PATCH has had a significant impact on avoiding admissions and re-attendances, thus improving flow and performance in PED. The projected financial impact is that it is cost effective.We are using this data to pursue a business case internally and with local CCGs. We are optimistic of succeeding and using phase 2 to build on partnerships garnered across the whole system to expand PATCH's impact further by reducing PED attendances and continuing to improve our local urgent care pathway for children. © 2017, Published by the BMJ Publishing Group Limited. For permission to use (where not already granted under a licence) please go to http://group.bmj.com/group/rights-licensing/permissions.

GORDON, RICHARD F., ASTRONAUT - MISC. - GEMINI-TITAN (GT)-XI - RECOVERY - FROGMEN - ATLANTIC

NASA Image and Video Library

1966-09-15

S66-50759 (15 Sept. 1966) --- Astronaut Richard F. Gordon Jr., pilot of the Gemini-11 spaceflight, is hoisted from the water by a recovery helicopter from the prime recovery ship USS Guam. Gemini-11 splashed down in the western Atlantic recovery area at 9 a.m. (EST), Sept. 15, 1966, to conclude the three-day mission in space. Astronaut Charles Conrad Jr. (out of frame) is the Gemini-11 command pilot. Photo credit: NASA

Research Pilot Milt Thompson in M2-F2 Aircraft Attached to B-52 Mothership

NASA Image and Video Library

1966-02-28

NASA research pilot Milt Thompson sits in the M2-F2 "heavyweight" lifting body research vehicle before a 1966 test flight. The M2-F2 and the other lifting-body designs were all attached to a wing pylon on NASA’s B-52 mothership and carried aloft. The vehicles were then drop-launched and, at the end of their flights, glided back to wheeled landings on the dry lake or runway at Edwards AFB. The lifting body designs influenced the design of the Space Shuttle and were also reincarnated in the design of the X-38 in the 1990s.

A learning flight control system for the F8-DFBW aircraft. [Digital Fly-By-Wire

NASA Technical Reports Server (NTRS)

Montgomery, R. C.; Mekel, R.; Nachmias, S.

1978-01-01

This report contains a complete description of a learning control system designed for the F8-DFBW aircraft. The system is parameter-adaptive with the additional feature that it 'learns' the variation of the control system gains needed over the flight envelope. It, thus, generates and modifies its gain schedule when suitable data are available. The report emphasizes the novel learning features of the system: the forms of representation of the flight envelope and the process by which identified parameters are used to modify the gain schedule. It contains data taken during piloted real-time 6 degree-of-freedom simulations that were used to develop and evaluate the system.

Development of high temperature service polyimide based adhesives for titanium and composite bonding applications

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

Mayhew, R.T.; Kohli, D.K.

CYTEC Engineered Materials Inc. has developed several adhesives based on LaRC{trademark} PETI-5 Polyimide Resin for bonding titanium and composite substrates. These adhesives are intended for long term service at 177{degrees}C (350{degrees}F) and are processed at 350{degrees}C (660{degrees}F) in conventional autoclaves under 50 psi pressure. Titanium lap shears range from 48.3MPa (7000 psi) at room temperature to 31MPa (4500 psi) at 177{degrees}C (350{degrees}F). Excellent metal-to-metal peels and honeycomb bonding properties are reported for these products. In addition to film adhesive, primer and paste products have been described. Pilot line quantities of several hundred square feet of the film adhesive have beenmore » produced and sampled under the CYTEC designation FM{reg_sign} x5.« less

Technicians close hatches on Gemini 11 spacecraft during countdown

NASA Technical Reports Server (NTRS)

1966-01-01

Technicians in the White Room atop Pad 19 prepare to close hatches on the Gemini 11 spacecraft during prelaunch countdown. Inside the spacecraft are Astronauts Charles Conrad Jr., command pilot, and Richard F. Gordon Jr., pilot.

Craig R. Bomben

NASA Technical Reports Server (NTRS)

2001-01-01

Craig R. Bomben became a pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, Calif., in June 2001. His flying duties include a variety of research and support activities while piloting the F/A-18, DC-8, T-34C and King Air aircraft. He has more than 17 years and 3,800 hours of military and civilian flight experience in over 50 different aircraft types. Bomben came to NASA Dryden from a U.S. Navy assignment to the Personnel Exchange Program, Canada. He served as a test pilot in the Canadian Armed Forces located in Cold Lake, Alberta. He participated in numerous developmental programs to include CT-133 airborne ejection seat testing, F/A-18 weapons flutter testing and F/A-18 night vision goggles integration. Bomben performed U.S. Navy fleet service in 1995 as a strike-fighter department head. He completed two overseas deployments onboard the USS George Washington and USS Stennis. As a combat strike leader, he headed numerous multi-national missions over Iraq in support of Operation Southern Watch. Bomben graduated from the U.S. Naval Test Pilot School in 1992 and was subsequently assigned to the Naval Weapons Test Squadron at Pt. Mugu, Calif. During this tour he developed the F-14D bombsight and worked on various other F-14D and F/A-18 weapon systems developmental programs. Bomben is a 1985 graduate of Washington State University with a bachelor of science degree in electrical engineering. He graduated from naval flight training in 1987 and was recognized as a Commodore List graduate. His first assignment was to Naval Air Station Pensacola, Fla., where he was an instructor in the T-2B Buckeye. When selected to fly the F/A-18 in 1989, he joined a fleet squadron and deployed aboard the USS Forrestal. Bomben is married to the former Aissa Asuncion. They live in Lancaster, Calif., with their 3 children.

Craig R. Bomben

NASA Image and Video Library

2001-06-19

Craig R. Bomben became a pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, Calif., in June 2001. His flying duties include a variety of research and support activities while piloting the F/A-18, DC-8, T-34C and King Air aircraft. He has more than 17 years and 3,800 hours of military and civilian flight experience in over 50 different aircraft types. Bomben came to NASA Dryden from a U.S. Navy assignment to the Personnel Exchange Program, Canada. He served as a test pilot in the Canadian Armed Forces located in Cold Lake, Alberta. He participated in numerous developmental programs to include CT-133 airborne ejection seat testing, F/A-18 weapons flutter testing and F/A-18 night vision goggles integration. Bomben performed U.S. Navy fleet service in 1995 as a strike-fighter department head. He completed two overseas deployments onboard the USS George Washington and USS Stennis. As a combat strike leader, he headed numerous multi-national missions over Iraq in support of Operation Southern Watch. Bomben graduated from the U.S. Naval Test Pilot School in 1992 and was subsequently assigned to the Naval Weapons Test Squadron at Pt. Mugu, Calif. During this tour he developed the F-14D bombsight and worked on various other F-14D and F/A-18 weapon systems developmental programs. Bomben is a 1985 graduate of Washington State University with a bachelor of science degree in electrical engineering. He graduated from naval flight training in 1987 and was recognized as a Commodore List graduate. His first assignment was to Naval Air Station Pensacola, Fla., where he was an instructor in the T-2B Buckeye. When selected to fly the F/A-18 in 1989, he joined a fleet squadron and deployed aboard the USS Forrestal. Bomben is married to the former Aissa Asuncion. They live in Lancaster, Calif., with their 3 children.

Nils Larson

NASA Image and Video Library

2007-03-16

Nils Larson is a research pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, Calif. Larson joined NASA in February 2007 and will fly the F-15, F-18, T-38 and ER-2. Prior to joining NASA, Larson was on active duty with the U.S. Air Force. He has accumulated more that 4,900 hours of military and civilian flight experience in more than 70 fixed and rotary winged aircraft. Larson completed undergraduate pilot training at Williams Air Force Base, Chandler, Ariz., in 1987. He remained at Williams as a T-37 instructor pilot. In 1991, Larson was assigned to Beale Air Force Base, Calif., as a U-2 pilot. He flew 88 operational missions from Korea, Saudi Arabia, the United Kingdom, Panama and other locations. Larson graduated from the U.S. Air Force Test Pilot School at Edwards Air Force Base, Calif., in Class 95A. He became a flight commander and assistant operations officer for the 445th squadron at Edwards. He flew the radar, avionics integration and engine tests in F-15 A-D, the early flights of the glass cockpit T-38C and airworthiness flights of the Coast Guard RU-38. He was selected to serve as an Air Force exchange instructor at the U.S. Naval Test Pilot School, Patuxent River, Md. He taught systems and fixed-wing flight test and flew as an instructor pilot in the F-18, T-2, U-6A Beaver and X-26 Schweizer sailplane. Larson commanded U-2 operations for Warner Robins Air Logistics Center's Detachment 2 located in Palmdale, Calif. In addition to flying the U-2, Larson supervised the aircraft's depot maintenance and flight test. He was the deputy group commander for the 412th Operations Group at Edwards before retiring from active duty in 2007 with the rank of lieutenant colonel. His first experience with NASA was at the Glenn Research Center, Cleveland, where he served a college summer internship working on arcjet engines. Larson is a native of Bethany, W.Va,, and received his commission from the U.S. Air Force Academy in 1986 with a

Odour in composting processes at pilot scale: monitoring and biofiltration.

PubMed

Gutiérrez, M C; Serrano, A; Martín, M A; Chica, A F

2014-08-01

Although odour emissions associated with the composting process, especially during the hydrolytic stage, are widely known, their impact on surrounding areas is not easily quantifiable, For this reason, odour emissions during the first stage ofcomposting were evaluated by dynamic olfactometry at pilot scale in order to obtain results which can be extrapolated to industrial facilities. The composting was carried out in a commercial dynamic respirometer equipped with two biofilters at pilot scale filled with prunings (Populus) and mature compost obtained from the organic fraction of municipal solid waste. Given that the highest odour emissions occur in the first stage of the composting process, this stage was carried out in a closed system to better control the odour emissions, whose maximum value was estimated to be 2.78 ouF S-1 during the experiments. Odour concentration, the dynamic respiration index and temperature showed the same evolution during composting, thus indicating that odour could be a key variable in the monitoring process. Other variables such as total organic carbon (CTOC) and pH were also found to be significant in this study due to their influence over odour emissions. The efficiency of the biofilters (empty bed residence time of 86 s) was determined by quantifying the odour emissions at the inlet and outlet of both biofilters. The moisture content in the biofilters was found to be an important variable for improving odour removal efficiency, while the minimum moisture percentage to obtain successful results was found to be 55% (odour removal efficiency of 95%).

3S2: Behavioral Response Studies of Cetaceans to Navy Sonar Signals in Norwegian Waters

DTIC Science & Technology

2014-09-30

severity of behavioral changes observed during experimental exposures of killer (Orcinus orca), long-finned pilot (Globicephala melas ), and sperm...finned pilot whales (Globicephala melas ). Marine Mammal sci (DOI: 10.1111/mms.12099). Antunes R., Kvadsheim P.H., Lam F.P.A., Tyack, P.L., Thomas, L... melas ). Mar. Poll. Bull. (DOI: 10.1016/j.marpolbul.2014.03.056) Aoki K, Sakai M, Miller PJO, Visser F, Sato K (2013) Body contact and synchronous dives

Taking Off the Wedding Ring: The Consequences of the Netherlands’ Choice to Forgo a Nuclear Capable F-35

DTIC Science & Technology

2015-02-17

F-16. After his commission, flying assignments included duties as Weapons Instructor Pilot, Flight Commander and Operations Officer at Volkel AB ...the Netherlands. He also served a tour at the Tactical Leadership Program (TLP) at Florennes AB , Belgium as a Seminar Leader. He is a command pilot...the glue that keeps NATO together.40 The deepening crisis between Russia, NATO, EU and the United States over Ukraine that has emerged over the last

Cetacean Social Behavioral Response to Sonar Exposure

DTIC Science & Technology

2015-09-30

Lam FPA, Tyack PLT, Miller PJO (in review). Disturbance-specific social responses in long-finned pilot whales, Globicephala melas .  Fieldwork...the social behavioral response of long-finned pilot whales (Globicephala melas ) revealed that a unifying characteristic of their behavioral response...Globicephala melas . 6 Visser F. et al. (in review). Vocal foragers and silent crowds: the socio-behavioural context of long- finned pilot whale

75 FR 11151 - Pacific Gas and Electric Company; Notice of Intent To File License Application, Filing of Draft...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-10

.... Name of Project: Humboldt WaveConnect Pilot Project. f. Location: The project would be located in the... Commission must include on the first page, the project name (Humboldt WaveConnect Pilot Project) and number (P-12779-005), and bear the heading ``Comments on the proposed Humboldt WaveConnect Pilot Project...

Predicting Performance Breakdown in Pilots Through Objective Measures of Stress Sensitivity: Final Report

DTIC Science & Technology

1991-04-01

episodes . In recent years, however, there has been 15 increasing interest in implicit memory in which conscious recollection is not a necessity but...and Coanition, 13, 501-518. 32. Craik F.I.M. & Tulving E. (1975) Depth of processing and and the retention of words in episodic memory . Journal of...35. Baddeley A.D. & Warrington E.K. (1970) Amnesia and the distinction between long-and short-term memory . Journal of Verbal Learnina and Verbal

Changes in alcohol-related brain networks across the first year of college: a prospective pilot study using fMRI effective connectivity mapping.

PubMed

Beltz, Adriene M; Gates, Kathleen M; Engels, Anna S; Molenaar, Peter C M; Pulido, Carmen; Turrisi, Robert; Berenbaum, Sheri A; Gilmore, Rick O; Wilson, Stephen J

2013-04-01

The upsurge in alcohol use that often occurs during the first year of college has been convincingly linked to a number of negative psychosocial consequences and may negatively affect brain development. In this longitudinal functional magnetic resonance imaging (fMRI) pilot study, we examined changes in neural responses to alcohol cues across the first year of college in a normative sample of late adolescents. Participants (N=11) were scanned three times across their first year of college (summer, first semester, second semester), while completing a go/no-go task in which images of alcoholic and non-alcoholic beverages were the response cues. A state-of-the-art effective connectivity mapping technique was used to capture spatiotemporal relations among brain regions of interest (ROIs) at the level of the group and the individual. Effective connections among ROIs implicated in cognitive control were greatest at the second assessment (when negative consequences of alcohol use increased), and effective connections among ROIs implicated in emotion processing were lower (and response times were slower) when participants were instructed to respond to alcohol cues compared to non-alcohol cues. These preliminary findings demonstrate the value of a prospective effective connectivity approach for understanding adolescent changes in alcohol-related neural processes. Copyright © 2013 Elsevier Ltd. All rights reserved.

Gemini 11 prime crew in life rafts after splashdown

NASA Technical Reports Server (NTRS)

1966-01-01

Astronauts Richard F. Gordon Jr. (left), pilot, and Charles Conrad Jr., command pilot, sit in life raft while awaiting pickup by a helicopter from the U.S.S. Guam. Members of the Navy frogman team wait with them.

HL-10 in flight over lakebed

NASA Technical Reports Server (NTRS)

1969-01-01

The HL-10 lifting body is seen here in flight over Rogers Dry Lake at Edwards AFB. After the vehicle's fins were modified following its first flight, the HL-10 proved to be the best handling of the heavy-weight lifting bodies flown at Edwards Air Force Base. The HL-10 flew much better than the M2-F2, and pilots were eager to fly it. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Pilot James Barrilleaux with ER-2 aircraft on ramp

NASA Image and Video Library

1998-03-18

James Barrilleaux is the assistant chief pilot for ER-2s in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, California. The ER-2s--civilian variants of the military U-2S reconnaissance aircraft--are part of NASA's Airborne Science program. The ER-2s can carry airborne scientific payloads of up to 2,600 pounds to altitudes of about 70,000 feet to investigate such matters as earth resources, celestial phenomena, atmospheric chemistry and dynamics, and oceanic processes. Barrilleaux has held his current position since February 1998. Barrilleaux joined NASA in 1986 as a U-2/ER-2 pilot with NASA's Airborne Science program at Ames Research Center, Moffett Field, California. He flew both the U-2C (until 1989) and the ER-2 on a wide variety of missions both domestic and international. Barrilleaux flew high-altitude operations over Antarctica in which scientific instruments aboard the ER-2 defined the cause of ozone depletion over the continent, known as the ozone hole. He has also flown the ER-2 over the North Pole. Barrilleaux served for 20 years in the U.S. Air Force before he joined NASA. He completed pilot training at Reese Air Force Base, Lubbock, Texas, in 1966. He flew 120 combat missions as a F-4 fighter pilot over Laos and North Vietnam in 1970 and 1971. He joined the U-2 program in 1974, becoming the commander of an overseas U-2 operation in 1982. In 1983, he became commander of the squadron responsible for training all U-2 pilots and SR-71 crews located at Beale Air Force Base, Marysville, California. He retired from the Air Force as a lieutenant colonel in 1986. On active duty, he flew the U-2, F-4 Phantom, the T-38, T-37, and the T-33. His decorations included two Distinguished Flying Crosses, 12 Air Medals, two Meritorious Service Medals, and other Air Force and South Vietnamese awards. Barrilleaux earned a bachelor of science degree in chemical engineering from Texas A&M University, College Station, in 1964 and a master of science

Higher Landing Accuracy in Expert Pilots is Associated with Lower Activity in the Caudate Nucleus

PubMed Central

Adamson, Maheen M.; Taylor, Joy L.; Heraldez, Daniel; Khorasani, Allen; Noda, Art; Hernandez, Beatriz; Yesavage, Jerome A.

2014-01-01

The most common lethal accidents in General Aviation are caused by improperly executed landing approaches in which a pilot descends below the minimum safe altitude without proper visual references. To understand how expertise might reduce such erroneous decision-making, we examined relevant neural processes in pilots performing a simulated landing approach inside a functional MRI scanner. Pilots (aged 20–66) were asked to “fly” a series of simulated “cockpit view” instrument landing scenarios in an MRI scanner. The scenarios were either high risk (heavy fog–legally unsafe to land) or low risk (medium fog–legally safe to land). Pilots with one of two levels of expertise participated: Moderate Expertise (Instrument Flight Rules pilots, n = 8) or High Expertise (Certified Instrument Flight Instructors or Air-Transport Pilots, n = 12). High Expertise pilots were more accurate than Moderate Expertise pilots in making a “land” versus “do not land” decision (CFII: d′ = 3.62±2.52; IFR: d′ = 0.98±1.04; p<.01). Brain activity in bilateral caudate nucleus was examined for main effects of expertise during a “land” versus “do not land” decision with the no-decision control condition modeled as baseline. In making landing decisions, High Expertise pilots showed lower activation in the bilateral caudate nucleus (0.97±0.80) compared to Moderate Expertise pilots (1.91±1.16) (p<.05). These findings provide evidence for increased “neural efficiency” in High Expertise pilots relative to Moderate Expertise pilots. During an instrument approach the pilot is engaged in detailed examination of flight instruments while monitoring certain visual references for making landing decisions. The caudate nucleus regulates saccade eye control of gaze, the brain area where the “expertise” effect was observed. These data provide evidence that performing “real world” aviation tasks in an fMRI provide objective data regarding the relative expertise of pilots and brain regions involved in it. PMID:25426935

Brain response to taste in overweight children: A pilot feasibility study.

PubMed

Bohon, Cara

2017-01-01

Understanding the neural response to food and food cues during early stages of weight gain in childhood may help us determine the drive processes involved in unhealthy eating behavior and risk for obesity. Healthy weight and overweight children ages 6-8 (N = 18; 10 with BMI between 5th and 85th %ile and 8 with BMI >85th %ile) underwent fMRI scans while anticipating and receiving tastes of chocolate milkshake. Parents completed a Children's Eating Behaviour Questionnaire. Results reveal greater response to milkshake taste receipt in overweight children in the right insula, operculum, precentral gyrus, and angular gyrus, and bilateral precuneus and posterior cingulate. No group differences were found for brain response to a visual food cue. Exploratory analyses revealed interactions between self-report measures of eating behavior and weight status on brain response to taste. This pilot study provides preliminary evidence of feasibility of studying young children's taste processing and suggests a possible developmental shift in brain response to taste.

Brain response to taste in overweight children: A pilot feasibility study

PubMed Central

Bohon, Cara

2017-01-01

Understanding the neural response to food and food cues during early stages of weight gain in childhood may help us determine the drive processes involved in unhealthy eating behavior and risk for obesity. Healthy weight and overweight children ages 6–8 (N = 18; 10 with BMI between 5th and 85th %ile and 8 with BMI >85th %ile) underwent fMRI scans while anticipating and receiving tastes of chocolate milkshake. Parents completed a Children’s Eating Behaviour Questionnaire. Results reveal greater response to milkshake taste receipt in overweight children in the right insula, operculum, precentral gyrus, and angular gyrus, and bilateral precuneus and posterior cingulate. No group differences were found for brain response to a visual food cue. Exploratory analyses revealed interactions between self-report measures of eating behavior and weight status on brain response to taste. This pilot study provides preliminary evidence of feasibility of studying young children’s taste processing and suggests a possible developmental shift in brain response to taste. PMID:28235080

Development and Flight Evaluation of an Emergency Digital Flight Control System Using Only Engine Thrust on an F-15 Airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Maine, Trindel A.; Fullerton, C. Gordon; Webb, Lannie Dean

1996-01-01

A propulsion-controlled aircraft (PCA) system for emergency flight control of aircraft with no flight controls was developed and flight tested on an F-15 aircraft at the NASA Dryden Flight Research Center. The airplane has been flown in a throttles-only manual mode and with an augmented system called PCA in which pilot thumbwheel commands and aircraft feedback parameters were used to drive the throttles. Results from a 36-flight evaluation showed that the PCA system can be used to safety land an airplane that has suffered a major flight control system failure. The PCA system was used to recover from a severe upset condition, descend, and land. Guest pilots have also evaluated the PCA system. This paper describes the principles of throttles-only flight control; a history of loss-of-control accidents; a description of the F-15 aircraft; the PCA system operation, simulation, and flight testing; and the pilot comments.

Flight testing a propulsion-controlled aircraft emergency flight control system on an F-15 airplane

NASA Technical Reports Server (NTRS)

Burcham, F. W., Jr.; Burken, John; Maine, Trindel A.

1994-01-01

Flight tests of a propulsion-controlled aircraft (PCA) system on an F-15 airplane have been conducted at the NASA Dryden Flight Research Center. The airplane was flown with all flight control surfaces locked both in the manual throttles-only mode and in an augmented system mode. In the latter mode, pilot thumbwheel commands and aircraft feedback parameters were used to position the throttles. Flight evaluation results showed that the PCA system can be used to land an airplane that has suffered a major flight control system failure safely. The PCA system was used to recover the F-15 airplane from a severe upset condition, descend, and land. Pilots from NASA, U.S. Air Force, U.S. Navy, and McDonnell Douglas Aerospace evaluated the PCA system and were favorably impressed with its capability. Manual throttles-only approaches were unsuccessful. This paper describes the PCA system operation and testing. It also presents flight test results and pilot comments.

Ceteacean Social Behavioral Response to Sonar

DTIC Science & Technology

2013-09-30

review). The social context of individual foraging behaviour in long-finned pilot whales (Globicephala melas ). Aoki K, Sakai M, Miller JO, Visser F...during 8 experimental exposures of killer (Orcinus orca), long-finned pilot whale (Globicephala melas ), and sperm whale (Physeter macrocephalus

Gemini 11 prime crew during water egress training in Gulf of Mexico

NASA Technical Reports Server (NTRS)

1966-01-01

Gemini 11 prime crew, Astronauts Richard F. Gordon Jr. (left), pilot, and Charles Conrad Jr., command pilot, relax on deck of the NASA Motor Vessel Retriever after suiting up for water egress training in Gulf of Mexico.

Download SolarPILOT | Concentrating Solar Power | NREL

Science.gov Websites

fill out this input box. First Name Last Name Email Address * Organization Planned Use of SolarPILOT software's Help system. Just click Help Contents under the Help menu, or press F1 from any input page to

A Collection of Nonlinear Aircraft Simulations in MATLAB

NASA Technical Reports Server (NTRS)

Garza, Frederico R.; Morelli, Eugene A.

2003-01-01

Nonlinear six degree-of-freedom simulations for a variety of aircraft were created using MATLAB. Data for aircraft geometry, aerodynamic characteristics, mass / inertia properties, and engine characteristics were obtained from open literature publications documenting wind tunnel experiments and flight tests. Each nonlinear simulation was implemented within a common framework in MATLAB, and includes an interface with another commercially-available program to read pilot inputs and produce a three-dimensional (3-D) display of the simulated airplane motion. Aircraft simulations include the General Dynamics F-16 Fighting Falcon, Convair F-106B Delta Dart, Grumman F-14 Tomcat, McDonnell Douglas F-4 Phantom, NASA Langley Free-Flying Aircraft for Sub-scale Experimental Research (FASER), NASA HL-20 Lifting Body, NASA / DARPA X-31 Enhanced Fighter Maneuverability Demonstrator, and the Vought A-7 Corsair II. All nonlinear simulations and 3-D displays run in real time in response to pilot inputs, using contemporary desktop personal computer hardware. The simulations can also be run in batch mode. Each nonlinear simulation includes the full nonlinear dynamics of the bare airframe, with a scaled direct connection from pilot inputs to control surface deflections to provide adequate pilot control. Since all the nonlinear simulations are implemented entirely in MATLAB, user-defined control laws can be added in a straightforward fashion, and the simulations are portable across various computing platforms. Routines for trim, linearization, and numerical integration are included. The general nonlinear simulation framework and the specifics for each particular aircraft are documented.

M2-F1 on lakebed with pilot Milt Thompson

NASA Technical Reports Server (NTRS)

1963-01-01

NASA Flight Research Pilot Milt Thompson, shown here on the lakebed with the M2-F1 lifting body, was an early backer of R. Dale Reed's lifting-body proposal. He urged Flight Research Center director Paul Bikle to approve the M2-F1's construction. Thompson also made the first glide flights in both the M2-F1 and its successor, the heavyweight M2-F2. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, NASA Flight Research Center (later Dryden Flight Research Center, Edwards, CA) management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

76 FR 13063 - Airworthiness Directives; EUROCOPTER FRANCE Model SA330F, SA330G, and SA330J Helicopters

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-10

... beyond the end limit (``tall pilot'' position). This resulted in the separation of the pedal adjustment... the ``tall pilot'' stop nut was damaged, most likely due to aging of the adhesive. The nut came loose... the pedal unit on a SA 330 helicopter, the copilot set the position beyond the end limit (``tall pilot...

75 FR 55492 - Airworthiness Directives; Eurocopter France Models SA330F, SA330G, and SA330J Helicopters

Federal Register 2010, 2011, 2012, 2013, 2014

2010-09-13

... helicopter, the copilot set the position beyond the end limit (``tall pilot'' position). This resulted in the... determined that the Loctite bond on the ``tall pilot'' stop nut was damaged, most likely due to aging of the... position beyond the end limit (``tall pilot'' position). This resulted in the separation of the pedal...

Evaluation of Piloted Inputs for Onboard Frequency Response Estimation

NASA Technical Reports Server (NTRS)

Grauer, Jared A.; Martos, Borja

2013-01-01

Frequency response estimation results are presented using piloted inputs and a real-time estimation method recently developed for multisine inputs. A nonlinear simulation of the F-16 and a Piper Saratoga research aircraft were subjected to different piloted test inputs while the short period stabilator/elevator to pitch rate frequency response was estimated. Results show that the method can produce accurate results using wide-band piloted inputs instead of multisines. A new metric is introduced for evaluating which data points to include in the analysis and recommendations are provided for applying this method with piloted inputs.

Neuroimaging Correlates of Post-Stroke Aphasia Rehabilitation in a Pilot Randomized Trial of Constraint-Induced Aphasia Therapy.

PubMed

Nenert, Rodolphe; Allendorfer, Jane B; Martin, Amber M; Banks, Christi; Ball, Angel; Vannest, Jennifer; Dietz, Aimee R; Szaflarski, Jerzy P

2017-07-18

BACKGROUND Recovery from post-stroke aphasia is a long and complex process with an uncertain outcome. Various interventions have been proposed to augment the recovery, including constraint-induced aphasia therapy (CIAT). CIAT has been applied to patients suffering from post-stroke aphasia in several unblinded studies to show mild-to-moderate linguistic gains. The aim of the present study was to evaluate the neuroimaging correlates of CIAT in patients with chronic aphasia related to left middle cerebral artery stroke. MATERIAL AND METHODS Out of 24 patients recruited in a pilot randomized blinded trial of CIAT, 19 patients received fMRI of language. Eleven of them received CIAT (trained) and eight served as a control group (untrained). Each patient participated in three fMRI sessions (before training, after training, and 3 months later) that included semantic decision and verb generation fMRI tasks, and a battery of language tests. Matching healthy control participants were also included (N=38; matching based on age, handedness, and sex). RESULTS Language testing showed significantly improved performance on Boston Naming Test (BNT; p<0.001) in both stroke groups over time and fMRI showed differences in the distribution of the areas involved in language production between groups that were not present at baseline. Further, regression analysis with BNT indicated changes in brain regions correlated with behavioral performance (temporal gyrus, postcentral gyrus, precentral gyrus, thalamus, left middle and superior frontal gyri). CONCLUSIONS Overall, our results suggest the possibility of language-related cortical plasticity following stroke-induced aphasia with no specific effect from CIAT training.

Pilot James Barrilleaux with ER-2 aircraft on ramp

NASA Technical Reports Server (NTRS)

1998-01-01

James Barrilleaux is the assistant chief pilot for ER-2s in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, California. The ER-2s--civilian variants of the military U-2S reconnaissance aircraft--are part of NASA's Airborne Science program. The ER-2s can carry airborne scientific payloads of up to 2,600 pounds to altitudes of about 70,000 feet to investigate such matters as earth resources, celestial phenomena, atmospheric chemistry and dynamics, and oceanic processes. Barrilleaux has held his current position since February 1998. Barrilleaux joined NASA in 1986 as a U-2/ER-2 pilot with NASA's Airborne Science program at Ames Research Center, Moffett Field, California. He flew both the U-2C (until 1989) and the ER-2 on a wide variety of missions both domestic and international. Barrilleaux flew high-altitude operations over Antarctica in which scientific instruments aboard the ER-2 defined the cause of ozone depletion over the continent, known as the ozone hole. He has also flown the ER-2 over the North Pole. Barrilleaux served for 20 years in the U.S. Air Force before he joined NASA. He completed pilot training at Reese Air Force Base, Lubbock, Texas, in 1966. He flew 120 combat missions as a F-4 fighter pilot over Laos and North Vietnam in 1970 and 1971. He joined the U-2 program in 1974, becoming the commander of an overseas U-2 operation in 1982. In 1983, he became commander of the squadron responsible for training all U-2 pilots and SR-71 crews located at Beale Air Force Base, Marysville, California. He retired from the Air Force as a lieutenant colonel in 1986. On active duty, he flew the U-2, F-4 Phantom, the T-38, T-37, and the T-33. His decorations included two Distinguished Flying Crosses, 12 Air Medals, two Meritorious Service Medals, and other Air Force and South Vietnamese awards. Barrilleaux earned a bachelor of science degree in chemical engineering from Texas A&M University, College Station, in 1964 and a master of science degree in systems management from the University of Southern California in 1979. He has accumulated more than 5,800 hours of flying time over a period of 33 years and is currently the oldest active U-2/ER-2 pilot.

HL-10 on lakebed with pilot Bill Dana

NASA Technical Reports Server (NTRS)

1966-01-01

NASA research pilot Bill Dana stands in front of the HL-10 Lifting Body following his first glide flight on April 25, 1969. Dana later retired Chief Engineer at NASA's Dryden Flight Research Center, which was called only the NASA Flight Research Center in 1969. Prior to his lifting body assignment, Dana flew the famed X-15 research airplane. He flew the rocket-powered aircraft 16 times, reaching a top speed of 3,897 miles per hour and a peak altitude of 310,000 feet (almost 59 miles high). The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 after landing with pilot Bill Dana

NASA Technical Reports Server (NTRS)

1960-01-01

This movie clip, running about 56 seconds, shows NASA pilot Bill Dana exiting the cockpit of the HL-10 and waving to his B-52 drop aircraft, just after landing on the dry lakebed at Edwards Air Force Base, California. A fleet of lifting bodies flown at the NASA Flight Research Center, Edwards, California, from 1963 to l975 demonstrated the ability of pilots to maneuver (in the atmosphere) and safely land a wingless vehicle. These lifting bodies were basically designed so they could fly back to Earth from space and be landed like an aircraft at a pre-determined site. (In 1976 NASA renamed the FRC as the NASA Dryden Flight Research Center in honor of Hugh L. Dryden.) These unique research vehicles, with their unconventional aerodynamic shapes, were the M2-F1, M2-F2, M2-F3, HL-10, X-24A, and the X-24B. The information the lifting body program generated contributed to the database that led to development of the current space shuttle program as well as the X-33 and X-38 technology demonstrators. Aerodynamic lift -- essential to flight in the atmosphere -- was obtained from the shape of the vehicles rather than from wings on a normal aircraft. The addition of fins and control surfaces allowed the pilots to stabilize and control the vehicles and regulate their flight paths. All but the M2-F1 were powered by the same type of XLR-11 rocket engine used in the famed Bell X-1 -- first aircraft to fly faster than the speed of sound. The M2-F1, a lightweight prototype, was unpowered. The success of the Dryden M2-F1 program led to the NASA development and construction of two heavyweight lifting bodies based on studies at NASA Ames and Langley research centers -- the M2-F2 and the HL-10, both built by the Northrop Corporation. The 'M' refers to 'manned' and 'F' refers to 'flight' version. 'HL' comes from 'horizontal landing' and '10' is for the tenth lifting body model to be investigated by Langley Research Center, Hampton, Virginia. The HL-10 was delivered to the FRC by Northrop in January 1966. Its first flight was on December 22 of the same year. The pilot was Bruce Peterson, before he was injured in the M2-F2 accident. The HL-10 was flown 37 times and it set several program records. On Feb. 18, 1970, Air Force test pilot Major Peter Hoag flew it to 1,228 m.p.h. (Mach 1.86), fastest speed of any of the lifting bodies. Nine days later, NASA pilot Bill Dana flew the HL-10 to 90,303 feet, the highest altitude reached by any of the lifting body vehicles. The HL-10 was also the first lifting body to fly supersonically -- on May 9, 1969, with NASA pilot John Manke at the controls. The HL-10 featured a flat bottom and rounded top -- much like an airfoil -- and it had a delta planform. In its final configuration, three vertical fins, two of them canted outwards from the body and a tall center fin, gave the craft directional control. A flush canopy blended into the smooth rounded nose. It was about 21 feet long, with a span of 13.6 feet. Its glide-flight weight was 6,473 pounds and its maximum gross weight was over 10,000 pounds. Flights with the HL-10 contributed substantially to the decision to design the space shuttles without air-breathing engines that would have been used for landings. Its final flight was on July 17, 1970. The HL-10 is now on public display at Dryden.

Stability and Controls Analysis and Flight Test Results of a 24-Foot Telescoping Nose Boom on an F-15B Airplane

NASA Technical Reports Server (NTRS)

Moua, Cheng M.; Cox, Timothy H.; McWherter, Shaun C.

2008-01-01

The Quiet Spike(TradeMark) F-15B flight research program investigated supersonic shock reduction using a 24-ft telescoping nose boom on an F-15B airplane. The program goal was to collect flight data for model validation up to 1.8 Mach. In the area of stability and controls, the primary concerns were to assess the potential destabilizing effect of the oversized nose boom on the stability, controllability, and handling qualities of the airplane and to ensure adequate stability margins across the entire research flight envelope. This paper reports on the stability and control analytical methods, flight envelope clearance approach, and flight test results of the F-15B telescoping nose boom configuration. Also discussed are brief pilot commentary on typical piloting tasks and refueling tasks.

PORTRAIT - APOLLO 7 - PRIME CREW - KSC

NASA Image and Video Library

1968-05-22

S68-33744 (22 May 1968) --- The prime crew of the first manned Apollo space mission, Apollo 7 (Spacecraft 101/Saturn 205), left to right, are astronauts Donn F. Eisele, command module pilot, Walter M. Schirra Jr., commander; and Walter Cunningham, lunar module pilot.

Prime crew photographed during Apollo 7 mission

NASA Technical Reports Server (NTRS)

1968-01-01

Astronaut Walter M. Schirra Jr., Apollo 7 commander, is photographed during the Apollo 7 mission (1582); Astronaut Donn F. Eisele, Apollo 7 command module pilot, is photographed during the mission (1583); Astronaut Walter Cunningham, Apollo 7 lunar module pilot, is photographed during mission (1584).

Prime crew photographed during Apollo 7 mission

NASA Technical Reports Server (NTRS)

1968-01-01

Astronaut Walter M. Schirra Jr., Apollo 7 commander, is photographed during the Apollo 7 mission (1582); Astronaut Donn F. Eisele, Apollo 7 command module pilot, is phtographed during the mission (1583); Astronaut Walter Cunningham, Apollo 7 lunar module pilot, is photographed during mission (1584).

5-HT2 receptor distribution shown by [18F] setoperone PET in high-functioning autistic adults.

PubMed

Beversdorf, David Q; Nordgren, Richard E; Bonab, Ali A; Fischman, Alan J; Weise, Steven B; Dougherty, Darin D; Felopulos, Gretchen J; Zhou, Feng C; Bauman, Margaret L

2012-01-01

The serotonergic system is implicated in disordered emotional behavior. Autism is characterized by impaired processing of emotional information. The serotonergic (5-HT) system is also critically involved in brain development, and abnormal brain synthesis of serotonin is observed in autism. Furthermore, whole blood and platelet serotonin have been reported to be elevated in autism. The authors examined the CNS serotonin system in autism in vivo. 5-HT2 receptors were visualized by PET imaging of [18F]setoperone-binding in this pilot study of 6 high-functioning autistic adults and 10 matched-control participants. Autism subjects had less thalamic [18F]setoperone binding than controls, when covaried for age, but no difference reached significance in other areas. A negative relationship between thalamic binding and history of language impairment was also observed. Further studies will be needed to gain a clearer picture of the role of the 5-HT system in autism.

MAS Bulletin. Papers Presented at Advisory Group for Aerospace Research and Development (AGARD) Symposium on Machine Intelligence for Aerospace Electronic Systems.

DTIC Science & Technology

1991-08-01

neural networks, and machine learning . This list ie not all 9. Future ESM Systems and the Potential for Neural Processing inclusive. This research could...U.S. CAPT James M. Skinner , USAF, Air Force Space Technology 17. Development of Tactical Doecisiont Akid. Center, and Prof. Georg* F. Luger...ntegrat11111ng Macine I~1e900enc Into the Co~pi to Aid t" Pilot 26. Integrated Communications, Navigatlion. Ideintiflocation Avionics Dr. Edward J

78 FR 49116 - Airworthiness Directives; Eurocopter France Helicopters

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-13

..., B2, B3, BA, C, D, and D1 helicopters; and Model AS355E, F, F1, F2, N, and NP helicopters. The... certain Eurocopter Model AS350B, B1, B2, B3, BA, C, D, and D1 and Model AS355E, F, F1, F2, N, and NP... pilot if certain regulatory recordkeeping requirements are met. As such, AD 2011-22-05 currently...

Estimation of the longitudinal and lateral-directional aerodynamic parameters from flight data for the NASA F/A-18 HARV

NASA Technical Reports Server (NTRS)

Napolitano, Marcello R.

1996-01-01

This progress report presents the results of an investigation focused on parameter identification for the NASA F/A-18 HARV. This aircraft was used in the high alpha research program at the NASA Dryden Flight Research Center. In this study the longitudinal and lateral-directional stability derivatives are estimated from flight data using the Maximum Likelihood method coupled with a Newton-Raphson minimization technique. The objective is to estimate an aerodynamic model describing the aircraft dynamics over a range of angle of attack from 5 deg to 60 deg. The mathematical model is built using the traditional static and dynamic derivative buildup. Flight data used in this analysis were from a variety of maneuvers. The longitudinal maneuvers included large amplitude multiple doublets, optimal inputs, frequency sweeps, and pilot pitch stick inputs. The lateral-directional maneuvers consisted of large amplitude multiple doublets, optimal inputs and pilot stick and rudder inputs. The parameter estimation code pEst, developed at NASA Dryden, was used in this investigation. Results of the estimation process from alpha = 5 deg to alpha = 60 deg are presented and discussed.

HL-10 cockpit

NASA Technical Reports Server (NTRS)

1967-01-01

Cockpit of the HL-10 lifting body. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 on ramp

NASA Technical Reports Server (NTRS)

1966-01-01

The HL-10, seen here parked on the ramp, was one of five lifting body designs flown at NASA's Dryden Flight Research Center, Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Recurrence of Neurological Deficits in an F/A-18D Pilot Following Loss of Cabin Pressure at Altitude.

PubMed

Robinson, Tom; Evangelista, Jose S; Latham, Emi; Mukherjee, Samir T; Pilmanis, Andrew

2016-08-01

Supersonic, high altitude aviation places its pilots and aircrew in complex environments, which may lead to injury that is not easily diagnosed or simply treated. Decompression illness (either venous or arterial) and environmental conditions (e.g., abnormal gases and pressure) are the most likely adverse effects aircrew often face. Though symptomatic aircrew personnel may occasionally require hyperbaric oxygen treatment, it is rare to require more than one treatment before returning to baseline function. This challenging aviation case details the clinical course and discusses the salient physiological factors of an F/A-18D pilot who presented with neurological symptoms following loss of cabin pressure at altitude. Most crucial to this discussion was the requirement for multiple hyperbaric oxygen treatments over several days due to recurrence of symptoms. The likelihood of recurrence during and after future flights cannot be estimated with accuracy. This case illustrates a degree of recurrences for neurological symptoms in aviation (hypobaric exposure to hyperbaric baseline environment) that has not previously been described. Robinson T, Evangelista JS III, Latham E, Mukherjee ST, Pilmanis A. Recurrence of neurological deficits in an F/A-18D pilot following loss of cabin pressure at altitude. Aerosp Med Hum Perform. 2016; 87(8):740-744.

M2-F2 cockpit instrument panels

NASA Image and Video Library

1966-03-27

This photo shows the right side cockpit instrumentation panel of the M2-F2 Lifting Body. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers -- the M2-F2 and the HL-10, both built by the Northrop Corporation. The "M" refers to "manned" and "F" refers to "flight" version. "HL" comes from "horizontal landing" and 10 is for the tenth lifting body model to be investigated by Langley. The first flight of the M2-F2 -- which looked much like the "F1" -- was on July 12, 1966. Milt Thompson was the pilot. By then, the same B-52 used to air launch the famed X-15 rocket research aircraft was modified to also carry the lifting bodies. Thompson was dropped from the B-52's wing pylon mount at an altitude of 45,000 feet on that maiden glide flight. The M2-F2 weighed 4,620 pounds, was 22 feet long, and had a width of about 10 feet. On May 10, 1967, during the sixteenth glide flight leading up to powered flight, a landing accident severely damaged the vehicle and seriously injured the NASA pilot, Bruce Peterson. NASA pilots and researchers realized the M2-F2 had lateral control problems, even though it had a stability augmentation control system. When the M2-F2 was rebuilt at Dryden and redesignated the M2-F3, it was modified with an additional third vertical fin -- centered between the tip fins -- to improve control characteristics. The M2-F2/F3 was the first of the heavy-weight, entry-configuration lifting bodies. Its successful development as a research test vehicle answered many of the generic questions about these vehicles. NASA donated the M2-F3 vehicle to the Smithsonian Institute in December 1973. It is currently hanging in the Air and Space Museum along with the X-15 aircraft number 1, which was its hangar partner at Dryden from 1965 to 1969.

M2-F2 cockpit instrument panels

NASA Image and Video Library

1966-03-27

This photo shows the left side cockpit instrumentation panel of the M2-F2 Lifting Body. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers -- the M2-F2 and the HL-10, both built by the Northrop Corporation. The "M" refers to "manned" and "F" refers to "flight" version. "HL" comes from "horizontal landing" and 10 is for the tenth lifting body model to be investigated by Langley. The first flight of the M2-F2 -- which looked much like the "F1" -- was on July 12, 1966. Milt Thompson was the pilot. By then, the same B-52 used to air launch the famed X-15 rocket research aircraft was modified to also carry the lifting bodies. Thompson was dropped from the B-52's wing pylon mount at an altitude of 45,000 feet on that maiden glide flight. The M2-F2 weighed 4,620 pounds, was 22 feet long, and had a width of about 10 feet. On May 10, 1967, during the sixteenth glide flight leading up to powered flight, a landing accident severely damaged the vehicle and seriously injured the NASA pilot, Bruce Peterson. NASA pilots and researchers realized the M2-F2 had lateral control problems, even though it had a stability augmentation control system. When the M2-F2 was rebuilt at Dryden and redesignated the M2-F3, it was modified with an additional third vertical fin -- centered between the tip fins -- to improve control characteristics. The M2-F2/F3 was the first of the heavy-weight, entry-configuration lifting bodies. Its successful development as a research test vehicle answered many of the generic questions about these vehicles. NASA donated the M2-F3 vehicle to the Smithsonian Institute in December 1973. It is currently hanging in the Air and Space Museum along with the X-15 aircraft number 1, which was its hangar partner at Dryden from 1965 to 1969.

M2-F2 on ramp

NASA Image and Video Library

1966-02-24

The M2-F2 Lifting Body is seen here on the ramp at the NASA Dryden Flight Research Center. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers -- the M2-F2 and the HL-10, both built by the Northrop Corporation. The "M" refers to "manned" and "F" refers to "flight" version. "HL" comes from "horizontal landing" and 10 is for the tenth lifting body model to be investigated by Langley. The first flight of the M2-F2 -- which looked much like the "F1" -- was on July 12, 1966. Milt Thompson was the pilot. By then, the same B-52 used to air launch the famed X-15 rocket research aircraft was modified to also carry the lifting bodies. Thompson was dropped from the B-52's wing pylon mount at an altitude of 45,000 feet on that maiden glide flight. The M2-F2 weighed 4,620 pounds, was 22 feet long, and had a width of about 10 feet. On May 10, 1967, during the sixteenth glide flight leading up to powered flight, a landing accident severely damaged the vehicle and seriously injured the NASA pilot, Bruce Peterson. NASA pilots and researchers realized the M2-F2 had lateral control problems, even though it had a stability augmentation control system. When the M2-F2 was rebuilt at Dryden and redesignated the M2-F3, it was modified with an additional third vertical fin -- centered between the tip fins -- to improve control characteristics. The M2-F2/F3 was the first of the heavy-weight, entry-configuration lifting bodies. Its successful development as a research test vehicle answered many of the generic questions about these vehicles. NASA donated the M2-F3 vehicle to the Smithsonian Institute in December 1973. It is currently hanging in the Air and Space Museum along with the X-15 aircraft number 1, which was its hangar partner at Dryden from 1965 to 1969.

Design Criteria for the Future of Flight Controls. Proceedings of the Flight Dynamics Laboratory Flying Qualities and Flight Control Symposium 2-5 March 1982.

DTIC Science & Technology

1982-07-01

robustness of the closed-loop system as compared to state feedback. The observer theory of Luenberger specifies the conditions that must be satisfied for...No. ID-17SI-F-l, October 1963. 8. Rynaski, E. G. and Whitbeck, R. F.: "The Theory and Application of Linear Optimal Control," Calspan Report No. IH...pilots tend to control them open-loop. Frequencies much beyond 10 rad/sec are generally beyond pilots’ control capability. Control theory indicates a need

T-4G Simulator and T-4 Ground Training Devices in USAF Undergraduate Pilot Training.

ERIC Educational Resources Information Center

Woodruff, Robert R.; Smith, James F.

The objective of the project was to investigate the utility of using an A/F37A-T4G T-37 flight simulator within the context of Air Force undergraduate pilot training. Twenty-one subjects, selected from three undergraduate pilot training classes, were given contact flight training in a TP4G/EPT simulator before going to T-37 aircraft for further…

BIMOMASS GASIFICATION PILOT PLANT STUDY

EPA Science Inventory

The report gives results of a gasification pilot program using two biomass feedstocks: bagasse pellets and wood chips. he object of the program was to determine the properties of biomass product gas and its suitability as a fuel for gas-turbine-based power generation cycles. he f...

The Integration of Operations and Intelligence Getting Information to the Warfighter

DTIC Science & Technology

1997-03-01

strike missions in the Negev Desert against highly accurate replicas of the missile sites. On the day of the attack, Syrian airspace was scanned by E-2C...With F-15 and F-16 pilots flying combat air patrols, IAF F-4s armed with SHRIKE anti- radiation missiles, and F-16s loaded with standoff Maverick

M2-F1 simulator cockpit

NASA Technical Reports Server (NTRS)

1963-01-01

This early simulator of the M2-F1 lifting body was used for pilot training, to test landing techniques before the first ground tow attempts, and to test new control configurations after the first tow attempts and wind-tunnel tests. The M2-F1 simulator was limited in some ways by its analog simulator. It had only limited visual display for the pilot, as well. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Towards a genetics-based adaptive agent to support flight testing

NASA Astrophysics Data System (ADS)

Cribbs, Henry Brown, III

Although the benefits of aircraft simulation have been known since the late 1960s, simulation almost always entails interaction with a human test pilot. This "pilot-in-the-loop" simulation process provides useful evaluative information to the aircraft designer and provides a training tool to the pilot. Emulation of a pilot during the early phases of the aircraft design process might provide designers a useful evaluative tool. Machine learning might emulate a pilot in a simulated aircraft/cockpit setting. Preliminary work in the application of machine learning techniques, such as reinforcement learning, to aircraft maneuvering have shown promise. These studies used simplified interfaces between machine learning agent and the aircraft simulation. The simulations employed low order equivalent system models. High-fidelity aircraft simulations exist, such as the simulations developed by NASA at its Dryden Flight Research Center. To expand the applicational domain of reinforcement learning to aircraft designs, this study presents a series of experiments that examine a reinforcement learning agent in the role of test pilot. The NASA X-31 and F-106 high-fidelity simulations provide realistic aircraft for the agent to maneuver. The approach of the study is to examine an agent possessing a genetic-based, artificial neural network to approximate long-term, expected cost (Bellman value) in a basic maneuvering task. The experiments evaluate different learning methods based on a common feedback function and an identical task. The learning methods evaluated are: Q-learning, Q(lambda)-learning, SARSA learning, and SARSA(lambda) learning. Experimental results indicate that, while prediction error remain quite high, similar, repeatable behaviors occur in both aircraft. Similar behavior exhibits portability of the agent between aircraft with different handling qualities (dynamics). Besides the adaptive behavior aspects of the study, the genetic algorithm used in the agent is shown to play an additive role in the shaping of the artificial neural network to the prediction task.

Baseline Behavior of Pilot Whales and their Responses to Playback of Anthropogenic and Natural Sounds

DTIC Science & Technology

2014-09-30

Minvielle- Sebastia, L. and Guinet, C. (2008b). Diet of the social groups of long-finned pilot whales (Globicephala melas ) in the Strait of Gibraltar. Marine...structure of long-finned pilot whales (Globicephala melas ) in the Strait of Gibraltar. Acta Ethologica 11, 81-94. DeRuiter, S. L., Boyd, I. L...Aoki Kagari A, Lam F-Pa, Kvadsheim PH, Huisman J, Tyack PL (2014): The social contect of individual foraging behaviour in long-finned pilot whales (Globicephala melas ). Behaviour 151: 1453-77. [published, refereed

HL-10 in flight, turning to line up with lakebed runway 18

NASA Technical Reports Server (NTRS)

1969-01-01

This photo shows the HL-10 in flight, turning to line up with lakebed runway 18. The pilot for this flight, the 29th of the HL-10 series, was Bill Dana. The HL-10 reached a peak altitude of 64,590 feet and a top speed of Mach 1.59 on this particular flight. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 flight simulator

NASA Technical Reports Server (NTRS)

1968-01-01

As shown in this photo of the HL-10 flight simulator, the lifting-body pilots and engineers made use of early simulators for both training and the determination of a given vehicle's handling at various speeds, attitudes, and altitudes. This provided warning of possible problems. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 on lakebed with B-52 flyby

NASA Technical Reports Server (NTRS)

1969-01-01

NASA research pilot Bill Dana takes a moment to watch NASA's NB-52B cruise overhead after a research flight in the HL-10. On the left, John Reeves can be seen at the cockpit of the lifting body. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Pilot Peter Hoag and HL-10

NASA Technical Reports Server (NTRS)

1969-01-01

Air Force Major Peter Hoag stands in front of the HL-10 Lifting Body. Maj. Hoag joined the HL-10 program in 1969 and made his first glide flight on June 6, 1969. He made a total of 8 flights in the HL-10. They included the fastest lifting-body flight, which reached Mach 1.861 on Feb. 18, 1970. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

F-100A with nose through hangar wall following Scott Crossfield's emergency landing

NASA Technical Reports Server (NTRS)

1954-01-01

A NACA High-Speed Flight Station hangar wall meets the nose of a North American F-100A Super Sabre airplane on 8 September 1954. On the first NACA research flight of airplane #52-5778, pilot Scott Crossfield had to make a powerless 'deadstick' landing following an engine fire warning. This was something North American's own test pilots doubted could be done, for the early F-100 lacked flaps and landed 'hot as hell.' Crossfield followed up the flawless approach and landing by coasting off the lakebed, up the ramp, and then through the front door of the NACA hangar, frantically trying to stop the F-100A, which had used up its emergency brake power. Crossfield missed the NACA X fleet, but crunched the nose of the aircraft through the hangar's side wall. It is reported that Chuck Yeager then proclaimed that while the sonic wall had been his, the hangar wall was Crossfield's! The hangar wall and the F-100A were repaired, and the airplane flew again.

14 CFR 61.45 - Practical tests: Required aircraft and equipment.

Code of Federal Regulations, 2010 CFR

2010-01-01

... TRANSPORTATION (CONTINUED) AIRMEN CERTIFICATION: PILOTS, FLIGHT INSTRUCTORS, AND GROUND INSTRUCTORS General § 61... in paragraphs (e) and (f) of this section, at least two pilot stations with adequate visibility for... applicant from performing all of the tasks required for the practical test. However, the applicant's...

Effect of cognitive load on articulation rate and formant frequencies during simulator flights.

PubMed

Huttunen, Kerttu H; Keränen, Heikki I; Pääkkönen, Rauno J; Päivikki Eskelinen-Rönkä, R; Leino, Tuomo K

2011-03-01

It was explored how three types of intensive cognitive load typical of military aviation (load on situation awareness, information processing, or decision-making) affect speech. The utterances of 13 male military pilots were recorded during simulated combat flights. Articulation rate was calculated from the speech samples, and the first formant (F1) and second formant (F2) were tracked from first-syllable short vowels in pre-defined phoneme environments. Articulation rate was found to correlate negatively (albeit with low coefficients) with loads on situation awareness and decision-making but not with changes in F1 or F2. Changes were seen in the spectrum of the vowels: mean F1 of front vowels usually increased and their mean F2 decreased as a function of cognitive load, and both F1 and F2 of back vowels increased. The strongest associations were seen between the three types of cognitive load and F1 and F2 changes in back vowels. Because fluent and clear radio speech communication is vital to safety in aviation and temporal and spectral changes may affect speech intelligibility, careful use of standard aviation phraseology and training in the production of clear speech during a high level of cognitive load are important measures that diminish the probability of possible misunderstandings. © 2011 Acoustical Society of America

3S(expn 2): Behavioral Response Studies of Cetaceans to Navy Sonar Signals in Norwegian Waters

DTIC Science & Technology

2013-09-30

orca), long-finned pilot (Globicephala melas ), and sperm whales (Physeter macrocephalus) to naval sonar. Aquatic Mammals 38: 362-401. 9...of sonar signals by long-finned pilot whales (Globicephala melas ). Marine Mammal sci Aoki K, Sakai M, Miller PJO, Visser F, Sato K (2013) Body...Orcinus orca), long-finned pilot (Globicephala melas ), and sperm whales (Physeter macrocephalus) to naval sonar. Aquatic Mammals 38: 362-401

Methylphenidate in the management of asthenia in breast cancer patients treated with docetaxel: results of a pilot study.

PubMed

Cueva, Juan F; Calvo, Marcos; Anido, Urbano; León, Luis; Gallardo, Elena; Areses, Carmen; Bernárdez, Beatriz; Gayoso, Lucía; García, Jorge; Jesús Lamas, María; Curiel, Teresa; Vázquez, Francisca; Candamio, Sonia; Vidal, Yolanda; Javier Barón, Francisco; López, Rafael

2012-04-01

The objectives of this pilot study were to evaluate the safety and efficacy of the central nervous system stimulant methylphenidate in the management of asthenia in breast cancer patients treated with docetaxel. Patients with early breast cancer who presented asthenia >3 on the Visual Analogue Scale (VAS) after the first cycle of docetaxel-based chemotherapy were included. Patients received two additional cycles of chemotherapy, one with methylphenidate (10 mg bid) and the other without methylphenidate. Asthenia was evaluated using VAS and the Functional Assessment of Cancer Therapy-Fatigue (FACT-F) scale. Distress was assessed using the Hospital Anxiety and Depression Scale (HADS), and quality of life using FACT-F. Ten patients were included and evaluated for efficacy and safety. Overall, cycles with methylphenidate were better tolerated than those without methylphenidate in terms of asthenia (VAS, p = 0.004; FACT-F, p = 0.027) and quality of life (FACT-F, p = 0.047). No significant differences were observed in terms of distress (HADS, p = 0.297). Six (60%) patients continued with methylphenidate after study end. Main adverse events during study were palpitations and insomnia (30% of patients each). This pilot study suggests that methylphenidate may reduce asthenia and improve quality of life in breast cancer patients treated with docetaxel.

[Implementation of the EndoCert system for certification of arthroplasty centers. Experiences from the pilot phase].

PubMed

Haas, H; Mittelmeier, W

2014-06-01

EndoCert is an initiative of the Deutschen Gesellschaft für Orthopädie und Orthopädische Chirurgie (DGOOC, German Society for Orthopedics and Orthopedic Surgery) which has been available since October 2012 and is the first system worldwide for certification of specialized arthroplasty centers. Before implementation of this certification concept two sequential pilot phases were carried out with representative treatment institutions. The results from these pilot clinics are presented with respect to quality improvement effects. Early effects on the quality of treatment have been achieved by rectification of nonconformities determined in the audit with respect to structural and process quality. A total of 172 nonconformities found in the 23 participating pilot clinics could be rectified. Long-term effects on the quality of results will in future be analyzed in cooperation with the German endoprosthesis register (EPRD) and by accompanying evaluations. A close feedback of the collated experiences and results to the certification committee, which is responsible for the procedure together with the DGOOC, allows continuous further development of the system EndoCert represents a substantial step towards a nationwide safety and improvement of the quality in arthroplasty treatment within the preoperative, perioperative and postoperative framework and can in future represent a decisive tool together with the EPRD in quality management.

ATG-Fresenius or daclizumab induction therapy in immunologically high risk kidney recipients: a prospective randomized pilot trial.

PubMed

Kim, Min Jeong; Tsinalis, Dimitrios; Franz, Stefan; Binet, Isabelle; Gürke, Lorenz; Mihatsch, Michael J; Steiger, Jürg; Thiel, Gilbert; Dickenmann, Michael

2008-01-01

Despite all the advantages in the immunosuppressive therapy, kidney transplantation in immunologically high risk patients remains a challenge. Ideally, an induction therapy should provide maximal graft protection, while adverse events rate and costs remain as low as possible. Immunologically high risk kidney recipients with CDC-PRA ł 25% within the last 3 years, a positive B-cell CDC-crossmatch or graft loss due to rejection within 3 years following a prior transplantation, were randomized 1:1 to receive ATG-Fresenius (ATG-F) (9 mg/kg day 0; 3 mg/kg day 1-4) or Daclizumab therapy (1 mg/kg day 0, 14, 28, 42, 56) in a pilot study. Additional immunosuppression consisted of cyclosporine, mycophenolate mofetil, and steroids. 11 patients were included in each group. The patient (90% in ATG-F; 100% in Daclizumab) and graft survival (censored for death) (100% in ATG-F; 90% in Daclizumab) and the mean creatinine concentration at 24 months (139+/-68 mol/l in ATG-F; 176+/-103 mol/l in Daclizumab) were similar in both groups. More severe graft rejections (3 vascular rejections in Daclizumab) and adverse events (5.3/patient in ATG-F; 6.7/patient in Daclizumab) were observed in the Daclizumab group. The costs for hospitalization/ day within 24 months were lower in ATG-F (2.32+/-3.51 USD vs. 12.25+/-9.75 USD; p=0.02) resulting in an average cost-difference of more than 10'435 USD /patient. In this pilot trial, both treatments were comparably successful regarding graft and patient outcome.

The effect of hypoxia on the critical flicker fusion threshold in pilots.

PubMed

Truszczyński, Olaf; Wojtkowiak, Mieczysław; Biernacki, Marcin; Kowalczuk, Krzysztof

2009-01-01

Human reactions to environmental changes have been the subject of numerous investigations related to pathophysiology, aviation psychology, aviation, and sports. The present study aimed at evaluating the perception of light stimulus via the Critical Flicker Fusion threshold (CFF) measurements among aviation pilots. The study was carried out under hypoxic conditions corresponding to 5000 m altitude, for a period of 30 min, without the use of supplemental oxygen. Fourteen volunteer pilots, 23-30 years of age, were examined in the hypobaric chamber (HC). The measurements were performed at normobaria and at the initial and final phase of hypoxia. Heart rate (HR) and blood oxygen saturation (SaO2) were monitored. The high altitude hypoxia was found to produce a decrease in the CFF threshold F(3.39) = 3.207, p < 0.05, and SaO2 F(3.39) = 52.651, p < 0.001, as well as HR increase F(3.39) = 7.356, p < 0.001. The results indicate that the higher the decrease in SaO2 under hypoxic conditions, the higher the decrease in CFF r = .567 p < 0.05. Likewise, the higher the increase in HR, the higher the decrease in CFF r = -0.491 p < 0.05. Under hypoxic conditions, the perceptual ability of the pilots is gradually decreasing. This has been confirmed by the findings of the physiological examinations. The authors express an opinion that it would be advisable to introduce CFF measurement into the hypobaric chamber tests as it allows individual assessment of the pilot's perceptual ability under conditions of incomplete physiological compensation of the high altitude hypoxia.

F-8 DFBW simulating STS contro l system - Pilot-induced oscillation (PIO) on landing

NASA Technical Reports Server (NTRS)

1978-01-01

From 1972 to 1985 the NASA Dryden Flight Research Center conducted flight research with an F-8C employing the first digital fly-by-wire flight control system without a mechanical back up. The decision to replace all mechanical control linkages to rudder, ailerons, and other flight control surfaces was made for two reasons. First, it forced the research engineers to focus on the technology and issues that were truly critical for a production fly-by-wire aircraft. Secondly, it would give industry the confidence it needed to apply the technology--confidence it would not have had if the experimental system relied on a mechanical back up. In the first few decades of flight, pilots had controlled aircraft through direct force--moving control sticks and rudder pedals linked to cables and pushrods that pivoted control surfaces on the wings and tails. As engine power and speeds increased, more force was needed and hydraulically boosted controls emerged. Soon, all high-performance and large aircraft had hydraulic-mechanical flight-control systems. These conventional flight control systems restricted designers in the configuration and design of aircraft because of the need for flight stability. As the electronic era grew in the 1960s, so did the idea of aircraft with electronic flight-control systems. Wires replacing mechanical devices would give designers greater flexibility in configuration and in the size and placement of components such as tail surfaces and wings. A fly-by-wire system also would be smaller, more reliable, and in military aircraft, much less vulnerable to battle damage. A fly-by-wire aircraft would also be much more responsive to pilot control inputs. The result would be more efficient, safer aircraft with improved performance and design. The Aircraft By the late 1960s, engineers at Dryden began discussing how to modify an aircraft and create a fly-by-wire testbed. Support for the concept at NASA Headquarters came from Neil Armstrong, former research pilot at Dryden. He served in the Office of Advanced Research and Technology following his historic Apollo 11 lunar landing and knew electronic control systems from his days training in and operating the lunar module. Armstrong supported the proposed Dryden project and backed the transfer of an F-8C Crusader from the U.S. Navy to NASA to become the Digital Fly-By-Wire (DFBW) research aircraft. It was given the tail number 'NASA 802.' Wires from the control stick in the cockpit to the control surfaces on the wings and tail surfaces replaced the entire mechanical flight-control system in the F-8. The heart of the system was an off-the-shelf backup Apollo digital flight-control computer and inertial sensing unit, which transmitted pilot inputs to the actuators on the control surfaces. On May 25, 1972, the highly modified F-8 became the first aircraft to fly completely dependent upon an electronic flight-control system without any mechanical backup. The pilot was Gary Krier. The first phase of the DFBW program validated the fly-by-wire concept and quickly showed that a refined system, especially in large aircraft, would greatly enhance flying qualities by sensing motion changes and applying pilot inputs instantaneously. The Phase 1 system had a backup analog fly-by-wire system in the event of a failure in the Apollo computer unit, but it was never necessary to use the system in flight. In a joint program carried out with the Langley Research Center in the second phase of research, the original Apollo system was replaced with a triply redundant digital system. It would provide backup computer capabilities if a failure occurred. The DFBW program lasted 13 years. The final research flight, the 210th of the program, was made April 2, 1985, with Dryden Research Pilot Ed Schneider at the controls. Research Benefits The F-8 DFBW validated the principal concepts of the all-electric flight control systems now used in a variety of airplanes ranging from the F/A-18 to the Boeing 777 and the space shuttles. A DFBW flight control system also is used on the space shuttles. NASA 802 was the testbed for the sidestick-controller used in the F-16 fighter, the second U.S. high performance aircraft with a DFBW system. In addition to pioneering the space shuttle's fly-by-wire flight-control system, NASA 802 was the testbed that explored Pilot Induced Oscillations (PIO) and validated methods to suppress them. PIOs occur when a pilot over-controls an aircraft and a sustained oscillation results. On the last of five free flights of the prototype Space Shuttle Enterprise during approach and landing tests in l977, a PIO developed as the vehicle settled onto the runway. The problem was duplicated with the F-8 DFBW and a series of PIO suppression filters was developed and tested on the aircraft for the shuttle program office. DFBW research carried out with NASA 802 at Dryden is now considered one of the most significant and successful aeronautical programs in NASA history. In this clip we see NASA research pilot John Manke at the controls of Dryden's F-8 Digital Fly-By-Wire aircraft as it enters a severe pilot induced oscillation or PIO just after completion of a touch-and-go landing while testing for a signal-delay-related problem that occurred during an approach to landing on the shuttle prototype Enterprise.

Pilot Overmyer completes hygiene activities / demostrates IVA foot restraint

NASA Image and Video Library

1982-11-16

STS005-06-230 (11-16 Nov. 1982) --- On middeck, astronaut Robert F. Overmyer, STS-5 pilot, drying his face with a towel from forward single tray personal item stowage locker, completes personal hygiene activities (shaving) and demonstrates use of intravehicular activity (IVA) foot restraint on floor. Photo credit: NASA

Pilot interaction with automated airborne decision making systems

NASA Technical Reports Server (NTRS)

Rouse, W. B.

1981-01-01

The role of the pilot and crew for future aircraft is discussed. Fifteen formal experimental studies and the development of a variety of models of human behavior based on queueing history, pattern recognition methods, control theory, fuzzy set theory, and artificial intelligence concepts are presented. L.F.M.

Saturn Apollo Program

NASA Image and Video Library

1968-06-03

Pictured left to right, in the Apollo 7 Crew Portrait, are astronauts R. Walter Cunningham, Lunar Module pilot; Walter M. Schirra, Jr., commander; and Donn F. Eisele, Command Module Pilot. The Apollo 7 mission, boosted by a Saturn IB launch vehicle on October 11, 1968, was the first manned flight of the Apollo spacecraft.

M2-F3 on lakebed

NASA Image and Video Library

1970-06-19

The M2-F3 Lifting Body is seen here on the lakebed next to the NASA Flight Research Center (later the Dryden Flight Research Center), Edwards, California. Redesigned and rebuilt from the M2-F2, the M2-F3 featured as its most visible change a center fin for greater stability. While the M2-F3 was still demanding to fly, the center fin eliminated the high risk of pilot induced oscillation (PIO) that was characteristic of the M2-F2.

Preparing Specialized Undergraduate Pilot Training Graduates for F-35A Training

DTIC Science & Technology

2010-06-11

the two sides of this argument and analyze the new data acquired from an F-22A lead-in program and the fact that the F-35A has started flying with...flight operations under Instrument or Visual Flight Rules to include day / night IFR operations in the terminal and enroute environment. Have limited

Final Report for Low Pressure Tests of the CPU-400 Pilot ...

EPA Pesticide Factsheets

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NASA/RAE collaboration on nonlinear control using the F-8C digital fly-by-wire aircraft

NASA Technical Reports Server (NTRS)

Butler, G. F.; Corbin, M. J.; Mepham, S.; Stewart, J. F.; Larson, R. R.

1983-01-01

Design procedures are reviewed for variable integral control to optimize response (VICTOR) algorithms and results of preliminary flight tests are presented. The F-8C aircraft is operated in the remotely augmented vehicle (RAV) mode, with the control laws implemented as FORTRAN programs on a ground-based computer. Pilot commands and sensor information are telemetered to the ground, where the data are processed to form surface commands which are then telemetered back to the aircraft. The RAV mode represents a singlestring (simplex) system and is therefore vulnerable to a hardover since comparison monitoring is not possible. Hence, extensive error checking is conducted on both the ground and airborne computers to prevent the development of potentially hazardous situations. Experience with the RAV monitoring and validation procedures is described.

Flight-testing of the self-repairing flight control system using the F-15 highly integrated digital electronic control flight research facility

NASA Technical Reports Server (NTRS)

Stewart, James F.; Shuck, Thomas L.

1990-01-01

Flight tests conducted with the self-repairing flight control system (SRFCS) installed on the NASA F-15 highly integrated digital electronic control aircraft are described. The development leading to the current SRFCS configuration is highlighted. Key objectives of the program are outlined: (1) to flight-evaluate a control reconfiguration strategy with three types of control surface failure; (2) to evaluate a cockpit display that will inform the pilot of the maneuvering capacity of the damage aircraft; and (3) to flight-evaluate the onboard expert system maintenance diagnostics process using representative faults set to occur only under maneuvering conditions. Preliminary flight results addressing the operation of the overall system, as well as the individual technologies, are included.

Pilot Comments From the Boeing High Speed Research Aircraft, Cycle 3, Simulation Study of the Effects of Aeroservoelasticity (LaRC.3)

NASA Technical Reports Server (NTRS)

Bailey, Melvin L. (Editor)

2000-01-01

This is a compilation of pilot comments from the Boeing High Speed Research Aircraft, Cycle 3, simulation study (LaRC.3) of the effects of aeroservoelasticity, conducted from October to December 1997 at NASA Langley Research Center. This simulation study was conducted using the Visual Motion Simulator. The comments are from direct tape transcriptions and have been edited for spelling only. These comments were made on tape following the completion of each flight card, immediately after the pilot was satisfied with his practice and data recording runs. Six pilots were used in the evaluation and they are identified as pilots A through F.

F-8 DFBW in flight

NASA Image and Video Library

1972-10-07

F-8 Digital Fly-By-Wire aircraft in flight. The computer-controlled flight systems pioneered by the F-8 DFBW created a revolution in aircraft design. The F-117A, X-29, X-31, and many other aircraft have relied on computers to make them flyable. Built with inherent instabilities to make them more maneuverable, they would be impossible for human pilots to fly if the computers failed or received incorrect data.

F-15A Remotely Piloted Research Vehicle (RPRV)/Spin Research Vehicle(SRV) launch and flight

NASA Technical Reports Server (NTRS)

1981-01-01

This 33-second film clip begins with the release of the F-15 RPRV from the wing pylon of the NASA Dryden NB-52B carrier aircraft. Then a downward camera view just after release from the pylon, a forward camera view from the F-15 RPRV nose, and followed by air-to-air footage of an actual F-15 vehicle executing spin maneuvers.

Veggie Van Pilot Study: Impact of a Mobile Produce Market for Underserved Communities on Fruit and Vegetable Access and Intake

PubMed Central

Leone, Lucia A.; Haynes-Maslow, Lindsey; Ammerman, Alice S.

2016-01-01

We conducted a pilot evaluation of the Veggie Van, a mobile produce market that brings weekly boxes of reduced-cost locally grown fruits and vegetables (F&V) to lower-income communities and offers cooking and nutrition education to customers. We conducted surveys just prior to starting Veggie Van at each of 3 sites and again at 2–3 months. F&V intake was measured with a 2-question item and a 10-item food frequency questionnaire (FFQ) in a subset of participants. At baseline, average servings/day of F&V was 4.9 (SD = 2.6, n = 60). At follow-up, individuals who reported shopping at Veggie Van frequently (n = 32) increased their F&V consumption by 0.41 servings/day compared with a decrease of −1.19 for those who rarely/never used Veggie Van (n = 27), a total difference of 1.6 servings/day (P = .01). There were no statistically significant differences in F&V consumption between groups based on the FFQ measure. Frequent shoppers reported additional health improvements and increases in their ability to buy enough F&V. We conclude that offering weekly boxes of affordable F&V paired with education in underserved communities may improve F&V consumption for frequent program users. PMID:28529669

Veggie Van Pilot Study: Impact of a Mobile Produce Market for Underserved Communities on Fruit and Vegetable Access and Intake.

PubMed

Leone, Lucia A; Haynes-Maslow, Lindsey; Ammerman, Alice S

2017-01-01

We conducted a pilot evaluation of the Veggie Van, a mobile produce market that brings weekly boxes of reduced-cost locally grown fruits and vegetables (F&V) to lower-income communities and offers cooking and nutrition education to customers. We conducted surveys just prior to starting Veggie Van at each of 3 sites and again at 2-3 months. F&V intake was measured with a 2-question item and a 10-item food frequency questionnaire (FFQ) in a subset of participants. At baseline, average servings/day of F&V was 4.9 (SD = 2.6, n = 60). At follow-up, individuals who reported shopping at Veggie Van frequently (n = 32) increased their F&V consumption by 0.41 servings/day compared with a decrease of -1.19 for those who rarely/never used Veggie Van (n = 27), a total difference of 1.6 servings/day (P = .01). There were no statistically significant differences in F&V consumption between groups based on the FFQ measure. Frequent shoppers reported additional health improvements and increases in their ability to buy enough F&V. We conclude that offering weekly boxes of affordable F&V paired with education in underserved communities may improve F&V consumption for frequent program users.

Serum BDNF correlates with connectivity in the (pre)motor hub in the aging human brain--a resting-state fMRI pilot study.

PubMed

Mueller, Karsten; Arelin, Katrin; Möller, Harald E; Sacher, Julia; Kratzsch, Jürgen; Luck, Tobias; Riedel-Heller, Steffi; Villringer, Arno; Schroeter, Matthias L

2016-02-01

Brain-derived neurotrophic factor (BDNF) has been discussed to be involved in plasticity processes in the human brain, in particular during aging. Recently, aging and its (neurodegenerative) diseases have increasingly been conceptualized as disconnection syndromes. Here, connectivity changes in neural networks (the connectome) are suggested to be the most relevant and characteristic features for such processes or diseases. To further elucidate the impact of aging on neural networks, we investigated the interaction between plasticity processes, brain connectivity, and healthy aging by measuring levels of serum BDNF and resting-state fMRI data in 25 young (mean age 24.8 ± 2.7 (SD) years) and 23 old healthy participants (mean age, 68.6 ± 4.1 years). To identify neural hubs most essentially related to serum BDNF, we applied graph theory approaches, namely the new data-driven and parameter-free approach eigenvector centrality (EC) mapping. The analysis revealed a positive correlation between serum BDNF and EC in the premotor and motor cortex in older participants in contrast to young volunteers, where we did not detect any association. This positive relationship between serum BDNF and EC appears to be specific for older adults. Our results might indicate that the amount of physical activity and learning capacities, leading to higher BDNF levels, increases brain connectivity in (pre)motor areas in healthy aging in agreement with rodent animal studies. Pilot results have to be replicated in a larger sample including behavioral data to disentangle the cause for the relationship between BDNF levels and connectivity. Copyright © 2016 Elsevier Inc. All rights reserved.

Pilot testing of dissolved air flotation (DAF) in a highly effective coagulation-flocculation integrated (FRD) system.

PubMed

Wang, Yili; Guo, Jinlong; Tang, Hongxiao

2002-01-01

Factors of pretreatment coagulation/flocculation units were studied using raw water of low temperature and low turbidity. Aluminum sulfate (AS) and selected polyaluminium chlorides (PACls) were all effective in the DAF process when used under favorable conditions of coagulant addition, coagulation, flocculation and flotation units. Compared with the AS coagulant, PACls, at lower dosage, could give the same effective performance even with shorter coagulation/flocculation time or lower recycle ratio during the treatment of cold water. This is attributed to the higher-charged polymeric Al species, and the lower hydrophilic and more compact flocculated flocs of PACl coagulant. Based on results of pilot experiments, the goal of FRD system can be achieved by combining a DAF heterocoagulation reactor with PACl coagulant (F), an efficient flocculation reactor (R), as well as an economical auto-dosing system (D).

Analysis procedures and subjective flight results of a simulator validation and cue fidelity experiment

NASA Technical Reports Server (NTRS)

Carr, Peter C.; Mckissick, Burnell T.

1988-01-01

A joint experiment to investigate simulator validation and cue fidelity was conducted by the Dryden Flight Research Facility of NASA Ames Research Center (Ames-Dryden) and NASA Langley Research Center. The primary objective was to validate the use of a closed-loop pilot-vehicle mathematical model as an analytical tool for optimizing the tradeoff between simulator fidelity requirements and simulator cost. The validation process includes comparing model predictions with simulation and flight test results to evaluate various hypotheses for differences in motion and visual cues and information transfer. A group of five pilots flew air-to-air tracking maneuvers in the Langley differential maneuvering simulator and visual motion simulator and in an F-14 aircraft at Ames-Dryden. The simulators used motion and visual cueing devices including a g-seat, a helmet loader, wide field-of-view horizon, and a motion base platform.

Joseph (Joe) A. Walker

NASA Technical Reports Server (NTRS)

1956-01-01

In March 1945 Joseph A. Walker joined the National Advisory Committee for Aeronautics' Aircraft Engine Research Laboratory, Cleveland, Ohio, (later NASA's Lewis Research Center, now the Glenn Research Center) as a physicist. He transferred to the NACA High-Speed Flight Research Station, Edwards, California in 1951, as a research pilot. For the next fifteen years Walker served as a pilot at the Edwards flight research facility (today known as NASA's Dryden Flight Research Center) on such projects as the Bell X-1#2 (2 flights, first on August 27, 1951), Bell X-1A (1 flight on July 20, 1955), X-1E (21 flights, first on December 12, 1955), Douglas D-558-I #3 Skystreak (14 flights, first on June 29, 1951), Douglas D-558-II #2 Skyrocket (3 flights, first on April 29, 1955), Douglas D-558-II #3 Skyrocket (2 flights, first on May 7, 1954). On the Douglas X-3, Joe was project pilot and made all 20 flights, the first on August 1, 1954. Joe considered this aircraft the 'worst' plane he ever flew. He flew the Northrup X-4 (2 flights, first on October 18, 1951), Bell X-5 (78 flights, first on January 9, 1952). He also flew programs involving the F-100, F-101, F-102, F-104 and the B-47. Walker made the first NASA flight on the North American X-15 on March 25, 1960. His 25th and final X-15 flight on August 22, 1963, reached 354,200 feet, an unofficial record altitude of almost 67 miles. On October 30, 1964, Walker took the first Bell Lunar Landing Research Vehicle (LLRV) on its maiden flight, reaching a peak altitude of 10 feet and a free flight time of just under one minute. Two LLRV's and three Lunar Landing Training Vehicles developed from them were used to develop piloting and operational techniques for lunar landings. In November, he left the program after 35 flights on the first LLRV. Walker flew chase flights as well as research flights. On June 8, 1966 he was flying chase in NASA's F-104N for the Air Force's experimental bomber, North American XB-70A, when he was fatally injured in a mid-air collision between the planes. Joe graduated from Washington and Jefferson College in 1942, with a Bachelors degree in Physics. He enrolled in the civilian pilot training program in 1941 and, after graduation from college, entered the Army Air Forces. During World War II he flew P-38 fighters and F-5A photo reconnaissance for the Air Force, earning the Distinguished Flying Cross and the Air Medal with Seven Oak Clusters. Walker was a charter member of the Society of Experimental Test Pilots and one of the first to be designated a Fellow. He was honored with the Robert J. Collier Trophy, the Harmon International Trophy for Aviators, the Iven C. Kincheloe Award and the Octave Chanute Award, all in 1961. He received an honorary Doctor of Aeronautical Sciences degree from his alma mater in June of 1961 and was named Pilot of the Year in 1963 by the National Pilots Association. Joseph Albert Walker was born February 20, 1921, in Washington, Pennsylvania; he died on June 8, 1966 at Edwards, California.

Digital Fly-By-Wire Flight Control Validation Experience

NASA Technical Reports Server (NTRS)

Szalai, K. J.; Jarvis, C. R.; Krier, G. E.; Megna, V. A.; Brock, L. D.; Odonnell, R. N.

1978-01-01

The experience gained in digital fly-by-wire technology through a flight test program being conducted by the NASA Dryden Flight Research Center in an F-8C aircraft is described. The system requirements are outlined, along with the requirements for flight qualification. The system is described, including the hardware components, the aircraft installation, and the system operation. The flight qualification experience is emphasized. The qualification process included the theoretical validation of the basic design, laboratory testing of the hardware and software elements, systems level testing, and flight testing. The most productive testing was performed on an iron bird aircraft, which used the actual electronic and hydraulic hardware and a simulation of the F-8 characteristics to provide the flight environment. The iron bird was used for sensor and system redundancy management testing, failure modes and effects testing, and stress testing in many cases with the pilot in the loop. The flight test program confirmed the quality of the validation process by achieving 50 flights without a known undetected failure and with no false alarms.

Experiments and Modeling to Support Field Test Design

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

Johnson, Peter Jacob; Bourret, Suzanne Michelle; Zyvoloski, George Anthony

Disposition of heat-generating nuclear waste (HGNW) remains a continuing technical and sociopolitical challenge. We define HGNW as the combination of both heat generating defense high level waste (DHLW) and civilian spent nuclear fuel (SNF). Numerous concepts for HGNW management have been proposed and examined internationally, including an extensive focus on geologic disposal (c.f. Brunnengräber et al., 2013). One type of proposed geologic material is salt, so chosen because of its viscoplastic deformation that causes self-repair of damage or deformation induced in the salt by waste emplacement activities (Hansen and Leigh, 2011). Salt as a repository material has been tested atmore » several sites around the world, notably the Morsleben facility in Germany (c.f. Fahland and Heusermann, 2013; Wollrath et al., 2014; Fahland et al., 2015) and at the Waste Isolation Pilot Plant (WIPP) near Carlsbad, NM. Evaluating the technical feasibility of a HGNW repository in salt is an ongoing process involving experiments and numerical modeling of many processes at many facilities.« less

M2-F1 in flight over lakebed on tow line

NASA Technical Reports Server (NTRS)

1963-01-01

Following the first M2-F1 airtow flight on 16 August 1963, the Flight Research Center used the vehicle for both research flights and to check out new lifting-body pilots. These included Bruce Peterson, Don Mallick, Fred Haise, and Bill Dana from NASA. Air Force pilots who flew the M2-F1 included Chuck Yeager, Jerry Gentry, Joe Engle, Jim Wood, and Don Sorlie, although Wood, Haise, and Engle only flew on car tows. In the three years between the first and last flights of the M2-F1, it made about 400 car tows and 77 air tows. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

PORTRAIT - APOLLO 7

NASA Image and Video Library

1968-02-13

S68-21590 (September 1968) --- This is a portrait of the Apollo-Saturn 7 crew members. They are, left to right, astronauts Walter M. Schirra Jr., commander; Walter Cunningham, lunar module pilot; and Donn F. Eisele, command module pilot. EDITOR'S NOTE: Since this photograph was made astronaut Eisele died Dec. 2, 1987 in Tokyo, Japan, of a heart attack.

HL-10 mounted on a pedestal in front of the Dryden main gate at sunset

NASA Technical Reports Server (NTRS)

1992-01-01

The HL-10 Lifting Body, as shown here, is currently displayed on a pedestal in front of the main gate at NASA's Dryden Flight Research Center, Edwards, California. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

ED07-0110-12

NASA Image and Video Library

2007-05-24

Two NASA Dryden F/A-18s flown by research pilots Frank Batteas and Nils Larson were captured by photographer Lori Losey from a third F/A-18 flown by Dick Ewers as they flew in tight formation over the desert at Edwards Air Force Base.

AFRC2016-0082-13

NASA Image and Video Library

2016-03-10

NASA photographer Jim Ross captured this shot while pilot Troy Asher flew inverted in an F-15D. The F-15B is seen here flying over the mirror farm, AKA the Abengoa Mojave Solar Project, east of Four Corners off of Highway 58 in Southern California.

NASA Dryden's two T-38A mission support aircraft fly in tight formation while conducting a pitot-static airspeed calibration check near Edwards Air Force Base

NASA Image and Video Library

2007-09-26

NASA Dryden Flight Research Center's two T-38A Talon mission support aircraft flew together for the first time on Sept. 26, 2007 while conducting pitot-static airspeed calibration checks during routine pilot proficiency flights. The two aircraft, flown by NASA research pilots Kelly Latimer and Frank Batteas, joined up with a NASA Dryden F/A-18 flown by NASA research pilot Dick Ewers to fly the airspeed calibrations at several speeds and altitudes that would be flown by the Stratospheric Observatory for Infrared Astronomy (SOFIA) Boeing 747SP during its initial flight test phase. The T-38s, along with F/A-18s, serve in a safety chase role during those test missions, providing critical instrument and visual monitoring for the flight test series.

Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration. Volume 2; Bibliography Appendices

NASA Technical Reports Server (NTRS)

Hodge, Kenneth E. (Compiler); Kellogg, Yvonne (Editor)

1996-01-01

A technical symposium, aircraft display dedication, and pilots' panel discussion were held on May 27, 1992. to commemorate the 20th anniversary of the first flights of the F-8 Digital Fly-By-Wire (DFBW) and Supercritical Wing (SCW) research aircraft. The symposium featured technical presentations by former key government and industry participants in the advocacy, design, aircraft modification, and flight research program activities. The DFBW and SCW technical contributions are cited. A dedication ceremony marked permanent display of both program aircraft. The panel discussion participants included eight of the eighteen research and test pilots who flew these experimental aircraft. Pilots' remarks include descriptions of their most memorable flight experiences. The report also includes a survey of the Gulf Air War, an after-dinner presentation by noted aerospace author and historian Dr. Richard Hallion.

Proceedings of the F-8 Digital Fly-By-Wire and Supercritical Wing First Flight's 20th Anniversary Celebration. Volume 1

NASA Technical Reports Server (NTRS)

Hodge, Kenneth E. (Compiler)

1996-01-01

A technical symposium, aircraft display dedication, and pilots' panel discussion were held on May 27, 1992, to commemorate the 20th anniversary of the first flights of the F-8 Digital Fly-By-Wire (DFBW) and Supercrit- ical Wing (SCW) research aircraft. The symposium featured technical presentations by former key government and industry participants in the advocacy, design, aircraft modification, and flight research program activities. The DFBW and SCW technical contributions are cited. A dedication ceremony marked permanent display of both program aircraft. The panel discussion participants included eight of the eighteen research and test pilots who flew these experimental aircraft. Pilots' remarks include descriptions of their most memorable flight experiences The report also includes a survey of the Gulf Air War, and an after-dinner presentation by noted aerospace author and historian Dr. Richard Hallion.

Pictorial Format Display Evaluation

DTIC Science & Technology

1984-05-01

FIGR) under- Contract No. F33615-81-C-3610. Dr. John M. Reising served as Project Manager .with Capt. Carole Jean Kopala and, later, Major James S...Typo (SAM or AAA) Mode (Seahr, trac or launch) Air or Troak or Treat Type (MIG 21, MIK 23. SAM. or AAA" aa le Iunc Mode (Sara, trock or- lmxch) Clock...presentation (l pilot). Should come up automatically (I pilot). Airplane this smart should be able to fix these problems and just announce fix (1 pilot

Enabling HST UV Exploration of the Low Surface Brightness Universe: A Pilot Study with the WFC3 X Filter Set

NASA Astrophysics Data System (ADS)

Thilker, David

2017-08-01

We request 17 orbits to conduct a pilot study to examine the effectiveness of the WFC3/UVIS F300X filter for studying fundamental problems in star formation in the low density regime. In principle, the broader bandpass and higher throughput of F300X can halve the required observing time relative to F275W, the filter of choice for studying young stellar populations in nearby galaxies. Together with F475W and F600LP, this X filter set may be as effective as standard UVIS broadband filters for characterizing the physical properties of such populations. We will observe 5 low surface brightness targets with a range of properties to test potential issues with F300X: the red tail to 4000A and a red leak beyond, ghosts, and the wider bandpass. Masses and ages of massive stars, young star clusters, and clumps derived from photometry from the X filter set will be compared with corresponding measurements from standard filters. Beyond testing, our program will provide the first sample spanning a range of LSB galaxy properties for which HST UV imaging will be obtained, and a glimpse into the ensemble properties of the quanta of star formation in these strange environments. The increased observing efficiency would make more tractable programs which require several tens to hundreds of orbits to aggregate sufficient numbers of massive stars, young star clusters, and clumps to build statistical samples. We are hopeful that our pilot observations will broadly enable high-resolution UV imaging exploration of the low density frontier of star formation while HST is still in good health.

ArF excimer laser debrides burns without destruction of viable tissue: A pilot study.

PubMed

Prasad, Atulya; Sawicka, Katarzyna M; Pablo, Kelly B; Macri, Lauren K; Felsenstein, Jerome; Wynne, James J; Clark, Richard A F

2018-05-01

Recent evidence indicates that early removal of eschar by tangential debridement can promote healing. Laser debridement can be used for debridement of areas that prove challenging for debridement using tangential excision. In particular, irradiation with an ArF excimer laser ablates desiccated eschar and is self-terminating, preserving hydrated or viable tissue. Thermal burns were created on the flanks of two outbred, female Yorkshire pigs using aluminum bars heated to 70°C and applied for different lengths of time. Three days after injury, burns were debrided using an ArF excimer laser (193nm). Tissue was harvested immediately after debridement and 7days after debridement (10days after burn). Data from a pilot study demonstrates that ArF excimer laser irradiation removes burn eschar and promotes healing at 10days after burn. ArF excimer laser debridement is self-terminating and preserves underlying and adjacent perfused tissue. Potentially, this modality would be ideal for the complex curvilinear structures of the body. Copyright © 2017 Elsevier Ltd and ISBI. All rights reserved.

HL-10 first flight landing

NASA Technical Reports Server (NTRS)

1966-01-01

The HL-10 Lifting Body completes its first research flight with a landing on Rogers Dry Lake. Due to control problems, pilot Bruce Peterson had to land at a higher speed than originally planned in order to keep the vehicle under control. The actual touchdown speed was about 280 knots. This was 30 knots above the speed called for in the flight plan. The HL-10's first flight had lasted 3 minutes and 9 seconds. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 first flight landing

NASA Technical Reports Server (NTRS)

1966-01-01

The HL-10 Lifting Body completes its first research flight with a landing on Rogers Dry Lake at Edwards AFB, California, on December 22, 1966. The HL-10 suffered from buffeting and poor control during the flight. Pilot Bruce Peterson was able to make a successful landing despite the severe problems. These were traced to airflow separation from the fins. As a result, the fins were no longer able to stabilize the vehicle. A small reshaping of the fins' leading edges cured the airflow separation, but it was not until March 15, 1968, that the second HL-10 flight occurred. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

HL-10 in flight after launch

NASA Technical Reports Server (NTRS)

1969-01-01

The HL-10 Lifting Body is seen here in powered flight shortly after launch from the B-52 mothership. When HL-10 powered flights began on October 23, 1968, the vehicle used the same basic XLR-11 rocket engine that powered the original X-1s. A total of five powered flights were made before the HL-10 first flew supersonically on May 9, 1969, with John Manke in the pilot's seat. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

KSC-08pd3555

NASA Image and Video Library

2008-11-06

CAPE CANAVERAL, Fla. – A pilot with the 920th Rescue Wing gets ready to disembark his plane after landing at NASA's Kennedy Space Center in Florida. The Rescue Wing will join the U.S. Navy's Blue Angels for the Space and Air Show Nov. 8-9 at the Kennedy Space Center Visitor Complex. The Navy's elite flight demonstration squadron will take to the skies in military aircraft demonstrations by the F-16 Fighting Falcon and F/A-18 Super Hornet jets for the second annual Space & Air Show at Kennedy. This year’s show brings together the best in military aircraft, coupled with precision pilots and veteran astronauts to celebrate spaceflight and aviation. The event includes military aircraft demonstrations by the F-16 Fighting Falcon and a water rescue demonstration by the 920th Rescue Wing. Photo credit: NASA/Kim Shiflett

EC88-0052-1

NASA Image and Video Library

1988-03-29

View of the right cockpit of the F-111 MAW aircraft. Unlike most fighter aircraft of the time, the F-111 had side-by-side seating. The pilot sat on the left side, and the weapons systems officer on the right. Both had control sticks to fly the aircraft.

AD-1 with research pilot Richard E. Gray

NASA Technical Reports Server (NTRS)

1982-01-01

Standing in front of the AD-1 Oblique Wing research aircraft is research pilot Richard E. Gray. Richard E. Gray joined National Aeronautics and Space Administration's Johnson Space Center, Houston, Texas, in November 1978, as an aerospace research pilot. In November 1981, Dick joined the NASA's Ames-Dryden Flight Research Facility, Edwards, California, as a research pilot. Dick was a former Co-op at the NASA Flight Research Center (a previous name of the Ames-Dryden Flight Research Facility), serving as an Operations Engineer. At Ames-Dryden, Dick was a pilot for the F-14 Aileron Rudder Interconnect Program, AD-1 Oblique Wing Research Aircraft, F-8 Digital Fly-By-Wire and Pilot Induced Oscillations investigations. He also flew the F-104, T-37, and the F-15. On November 8, 1982, Gray was fatally injured in a T-37 jet aircraft while making a pilot proficiency flight. Dick graduated with a Bachelors degree in Aeronautical Engineering from San Jose State University in 1969. He joined the U.S. Navy in July 1969, becoming a Naval Aviator in January 1971, when he was assigned to F-4 Phantoms at Naval Air Station (NAS) Miramar, California. In 1972, he flew 48 combat missions in Vietnam in F-4s with VF-111 aboard the USS Coral Sea. After making a second cruise in 1973, Dick was assigned to Air Test and Evaluation Squadron Four (VX-4) at NAS Point Mugu, California, as a project pilot on various operational test and evaluation programs. In November 1978, Dick retired from the Navy and joined NASA's Johnson Space Center. At JSC Gray served as chief project pilot on the WB-57F high-altitude research projects and as the prime television chase pilot in a T-38 for the landing portion of the Space Shuttle orbital flight tests. Dick had over 3,000 hours in more than 30 types of aircraft, an airline transport rating, and 252 carrier arrested landings. He was a member of the Society of Experimental Test Pilots serving on the Board of Directors as Southwest Section Technical Adviser in 1981/1982. Richard E. Gray was born March 11, 1945 in Newport News, Virginia; he died on November 8, 1982 at Edwards, California, in a T-37 spin accident. The Ames-Dryden-1 (AD-1) aircraft was designed to investigate the concept of an oblique (pivoting) wing. The wing could be rotated on its center pivot, so that it could be set at its most efficient angle for the speed at which the aircraft was flying. NASA Ames Research Center Aeronautical Engineer Robert T. Jones conceived the idea of an oblique wing. His wind tunnel studies at Ames (Moffett Field, CA) indicated that an oblique wing design on a supersonic transport might achieve twice the fuel economy of an aircraft with conventional wings. The oblique wing on the AD-1 pivoted about the fuselage, remaining perpendicular to it during slow flight and rotating to angles of up to 60 degrees as aircraft speed increased. Analytical and wind tunnel studiesthat Jones conducted at Ames indicated that a transport-sized oblique-wing aircraft flying at speeds of up to Mach 1.4 (1.4 times the speed of sound) would have substantially better aerodynamic performance than aircraft with conventional wings. The AD-1 structure allowed the project to complete all of its technical objectives. The type of low-speed, low-cost vehicle - as expected - exhibited aeroelastic and pitch-roll-coupling effects that contributed to poor handling at sweep angles above 45 degrees. The fiberglass structure limited the wing stiffness that would have improved the handling qualities. Thus, after completion of the AD-1 project, there was still a need for a transonic oblique-wing research aircraft to assess the effects of compressibility, evaluate a more representative structure, and analyze flight performance at transonic speeds (those on either side of the speed of sound). The aircraft was delivered to the Dryden Flight Research Center, Edwards, CA, in March 1979 and its first flight was on December 21, 1979. Piloting the aircraft on that flight, as well as on its last flight on August 7, 1982, was NASA Research Pilot Thomas C. McMurtry. The AD-1 flew a total of 79 times during the research program. The aircraft was constructed by the Ames Industrial Co., Bohemia, NY, under a $240, 000 fixed-price contract. NASA specified the design based on a geometric configuration provided by the Boeing company. The Rutan Aircraft Factory, Mojave, CA, provided the detailed design and loads analysis for the vehicle. The aircraft was 38.8 feet long and 6.75 feet high with a wing span of 32.3 feet, unswept. It was constructed of plastic reinforced with fiberglass and weighed 1,450 pounds,empty. The vehicle was powered by two small turbojet engines, each producing 220 pounds of thrust at sea level. Due to safety concerns, the aircraft was limited to speeds of 170 mph.

Flying Quality Analysis of a JAS 39 Gripen Ministick Controller in an F/A-18 Aircraft

NASA Technical Reports Server (NTRS)

Carter, John F.; Stoliker, P. C.

2000-01-01

NASA Dryden conducted a handling qualities experiment using a small displacement centerstick controller that Saab-Scania developed for the JAS 39 Gripen aircraft. The centerstick, or ministick, was mounted in the rear cockpit of an F/A-18 aircraft. Production support flight control computers (PSFCC) provided a pilot-selectable research control system. The objectives for this experiment included determining whether the mechanical characteristics of the centerstick controller had any significant effect on the handling qualities of the F/A-18, and determining the usefulness of the PSFCCs for this kind of experiment. Five pilots evaluated closed-loop tracking tasks, including echelon and column formation flight and target following. Cooper-Harper ratings and pilot comments were collected for each maneuver. This paper describes the test system, including the PSFCCs, the Gripen centerstick, and the flight test experiment. The paper presents results of longitudinal handling qualities maneuvers, including low order equivalent systems, Neal-Smith, and controls anticipation parameter analyses. The experiment showed that, while the centerstick controller provided a different aircraft feel, few handling qualities deficiencies resulted. It also demonstrated that the PSFCCs were useful for this kind of investigation.

Interspecific Introgression in Cetaceans: DNA Markers Reveal Post-F1 Status of a Pilot Whale

PubMed Central

Miralles, Laura; Lens, Santiago; Rodríguez-Folgar, Antonio; Carrillo, Manuel; Martín, Vidal; Mikkelsen, Bjarni; Garcia-Vazquez, Eva

2013-01-01

Visual species identification of cetacean strandings is difficult, especially when dead specimens are degraded and/or species are morphologically similar. The two recognised pilot whale species (Globicephala melas and Globicephala macrorhynchus) are sympatric in the North Atlantic Ocean. These species are very similar in external appearance and their morphometric characteristics partially overlap; thus visual identification is not always reliable. Genetic species identification ensures correct identification of specimens. Here we have employed one mitochondrial (D-Loop region) and eight nuclear loci (microsatellites) as genetic markers to identify six stranded pilot whales found in Galicia (Northwest Spain), one of them of ambiguous phenotype. DNA analyses yielded positive amplification of all loci and enabled species identification. Nuclear microsatellite DNA genotypes revealed mixed ancestry for one individual, identified as a post-F1 interspecific hybrid employing two different Bayesian methods. From the mitochondrial sequence the maternal species was Globicephala melas. This is the first hybrid documented between Globicephala melas and G. macrorhynchus, and the first post-F1 hybrid genetically identified between cetaceans, revealing interspecific genetic introgression in marine mammals. We propose to add nuclear loci to genetic databases for cetacean species identification in order to detect hybrid individuals. PMID:23990883

How to Make Feedback More Effective? Qualitative Findings from Pilot Testing of an Audit and Feedback Report for Endoscopists

PubMed Central

Webster, Fiona; Patel, Jigisha; Rice, Kathleen; Baxter, Nancy; Paszat, Lawrence; Rabeneck, Linda

2016-01-01

Background. Audit and feedback (A/F) reports are one of the few knowledge translation activities that can effect change in physician behavior. In this study, we pilot-tested an endoscopist A/F report to elicit opinions about the proposed report's usability, acceptability and usefulness, and implications for knowledge translation. Methods. Semi-structured qualitative interviews were conducted with eleven endoscopists in Ontario, Canada. We tested an A/F report template comprising 9 validated, accepted colonoscopy quality indicators populated with simulated data. Interview transcripts were coded using techniques such as constant comparison and themes were identified inductively over several team meetings. Results. Four interrelated themes were identified: (1) overall perceptions of the A/F report; (2) accountability and consequences for poor performance; (3) motivation to change/improve skills; and (4) training for performance enhancement and available resources. The A/F report was well received; however, participants cited some possible threats to the report's effectiveness including the perceived threat of loss of privileges or licensing and the potential for the data to be dismissed. Conclusions. Participants agreed that A/F has the potential to improve colonoscopy performance. However, in order to be effective in changing physician behavior, A/F must be thoughtfully implemented with attention to the potential concerns of its recipients. PMID:27722149

How to Make Feedback More Effective? Qualitative Findings from Pilot Testing of an Audit and Feedback Report for Endoscopists.

PubMed

Webster, Fiona; Patel, Jigisha; Rice, Kathleen; Baxter, Nancy; Paszat, Lawrence; Rabeneck, Linda; Tinmouth, Jill

2016-01-01

Background . Audit and feedback (A/F) reports are one of the few knowledge translation activities that can effect change in physician behavior. In this study, we pilot-tested an endoscopist A/F report to elicit opinions about the proposed report's usability, acceptability and usefulness, and implications for knowledge translation. Methods . Semi-structured qualitative interviews were conducted with eleven endoscopists in Ontario, Canada. We tested an A/F report template comprising 9 validated, accepted colonoscopy quality indicators populated with simulated data. Interview transcripts were coded using techniques such as constant comparison and themes were identified inductively over several team meetings. Results . Four interrelated themes were identified: (1) overall perceptions of the A/F report; (2) accountability and consequences for poor performance; (3) motivation to change/improve skills; and (4) training for performance enhancement and available resources. The A/F report was well received; however, participants cited some possible threats to the report's effectiveness including the perceived threat of loss of privileges or licensing and the potential for the data to be dismissed. Conclusions . Participants agreed that A/F has the potential to improve colonoscopy performance. However, in order to be effective in changing physician behavior, A/F must be thoughtfully implemented with attention to the potential concerns of its recipients.

Apollo 12 crewmen participate in water egress training

NASA Technical Reports Server (NTRS)

1969-01-01

A member of the prime crew of the Apollo 12 lunar landing mission is hoisted up to a U.S. Coast Guard helicopter during water egress training in the Gulf of Mexico. Participating in the training were Astronauts Charles Conrad Jr., commander; Richard F. Gordon Jr., command module pilot; and Alan L. Bean, lunar module pilot.

Technicians prepare to close hatches on Gemini 11 spacecraft during countdown

NASA Technical Reports Server (NTRS)

1966-01-01

Technicians in the White Room atop Pad 19 prepare to close hatches on the Gemini 11 spacecraft during prelaunch countdown. Inside the spacecraft are Astronauts Charles Conrad Jr., command pilot, and Richard F. Gordon Jr., pilot. There is a humorous sign stating 'This is ABSOLUTELY your Last Chance' being held by one of the technicians.

INFLIGHT - APOLLO 7 (CREW ACTIVITIES)

NASA Image and Video Library

1968-10-15

S68-50713 (14 Oct. 1968) --- Astronauts Walter M. Schirra Jr. (on right), mission commander; and Donn F. Eisele, command module pilot; are seen in the first live television transmission from space. Schirra is holding a sign which reads, "Keep those cards and letters coming in, folks!" Out of view at left is astronaut Walter Cunningham, lunar module pilot.

Drug Usage in Pilots Involved in Aviation Accidents Compared With Drug Usage in the General Population: From 1990 to 2005

DTIC Science & Technology

2008-04-01

Unclassified 11 Form DOT F 1700.7 (8-72) Reproduction of completed page authorized 1 DRUG USAGE IN PILOTS INVOLVED IN AVIATION ACCIDENTS COMPARED WITH DRUG...0.01% during the examined time period (5192 accidents). Benzodiazepines Psychotherapeutic agents, anxiolytics, sedatives, and hypnotics occurred in

Astronaut Alan Bean steps from ladder of Lunar Module for EVA

NASA Technical Reports Server (NTRS)

1969-01-01

Astronaut Alan L. Bean, lunar module pilot for the Apollo 12 lunar landing mission, steps from the ladder of the Lunar Module to join Astronaut Charles Conrad Jr., commander, in extravehicular activity on November 19, 1969. Astronaut Ricard F. Gordon Jr., command module pilot, remained with the Command/Service Modules in lunar orbit.

Pilot Edwards reads a rendezvous timeline

NASA Image and Video Library

1998-03-03

STS089-385-004 (22-31 Jan. 1998) --- Astronaut Joe F. Edwards Jr., STS-89 pilot, highlights important data on a checklist while temporarily occupying the commander's station on the port side of the space shuttle Endeavour's flight deck. Edwards, making his first spaceflight, is an alumnus of the 1995 class of astronaut candidates (ASCAN). Photo credit: NASA

Astronaut Curtis L. Brown, Jr., pilot, works with his life raft during emergency bailout training

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 TRAINING VIEW --- Astronaut Curtis L. Brown, Jr., pilot, works with his life raft during emergency bailout training for crew members in the Johnson Space Centers (JSC) Weightless Environment Training Facility (WET-F). Brown will join five other astronauts for nine days aboard the Space Shuttle Endeavour next month.

In silico vs. Over the Clouds: On-the-Fly Mental State Estimation of Aircraft Pilots, Using a Functional Near Infrared Spectroscopy Based Passive-BCI

PubMed Central

Gateau, Thibault; Ayaz, Hasan; Dehais, Frédéric

2018-01-01

There is growing interest for implementing tools to monitor cognitive performance in naturalistic work and everyday life settings. The emerging field of research, known as neuroergonomics, promotes the use of wearable and portable brain monitoring sensors such as functional near infrared spectroscopy (fNIRS) to investigate cortical activity in a variety of human tasks out of the laboratory. The objective of this study was to implement an on-line passive fNIRS-based brain computer interface to discriminate two levels of working memory load during highly ecological aircraft piloting tasks. Twenty eight recruited pilots were equally split into two groups (flight simulator vs. real aircraft). In both cases, identical approaches and experimental stimuli were used (serial memorization task, consisting in repeating series of pre-recorded air traffic control instructions, easy vs. hard). The results show pilots in the real flight condition committed more errors and had higher anterior prefrontal cortex activation than pilots in the simulator, when completing cognitively demanding tasks. Nevertheless, evaluation of single trial working memory load classification showed high accuracy (>76%) across both experimental conditions. The contributions here are two-fold. First, we demonstrate the feasibility of passively monitoring cognitive load in a realistic and complex situation (live piloting of an aircraft). In addition, the differences in performance and brain activity between the two experimental conditions underscore the need for ecologically-valid investigations. PMID:29867411

In silico vs. Over the Clouds: On-the-Fly Mental State Estimation of Aircraft Pilots, Using a Functional Near Infrared Spectroscopy Based Passive-BCI.

PubMed

Gateau, Thibault; Ayaz, Hasan; Dehais, Frédéric

2018-01-01

There is growing interest for implementing tools to monitor cognitive performance in naturalistic work and everyday life settings. The emerging field of research, known as neuroergonomics, promotes the use of wearable and portable brain monitoring sensors such as functional near infrared spectroscopy (fNIRS) to investigate cortical activity in a variety of human tasks out of the laboratory. The objective of this study was to implement an on-line passive fNIRS-based brain computer interface to discriminate two levels of working memory load during highly ecological aircraft piloting tasks. Twenty eight recruited pilots were equally split into two groups (flight simulator vs. real aircraft). In both cases, identical approaches and experimental stimuli were used (serial memorization task, consisting in repeating series of pre-recorded air traffic control instructions, easy vs. hard). The results show pilots in the real flight condition committed more errors and had higher anterior prefrontal cortex activation than pilots in the simulator, when completing cognitively demanding tasks. Nevertheless, evaluation of single trial working memory load classification showed high accuracy (>76%) across both experimental conditions. The contributions here are two-fold. First, we demonstrate the feasibility of passively monitoring cognitive load in a realistic and complex situation (live piloting of an aircraft). In addition, the differences in performance and brain activity between the two experimental conditions underscore the need for ecologically-valid investigations.

Establishing an Operational Data System for Surface Currents Derived from Satellite Altimeters and Scatterometers; Pilot Study for the Tropical Pacific

NASA Astrophysics Data System (ADS)

Lagerloef, G. S.; Cheney, R.; Mitchum, G. T.

2001-12-01

We are initiating a pilot processing system and data center to provide operational ocean surface velocity fields from satellite altimeter and vector wind data. The team includes the above authors plus M. Bourassa (FSU), V.Kousky (NOAA/NCEP), J.Polovina (NOAA/NMFS/Hawaii CoastWatch), R.Legeckis (NOAA/NESDIS), G. Jacobs (NRL), F. Bonjean (ESR), E.Johnson (ESR) and J.Gunn (ESR). Methods to derive surface currents are the outcome of several years of NASA sponsored research and the pilot project will transition that capability to operational oceanographic applications. The regional focus will be the tropical Pacific. Data applications include large scale climate diagnostics and prediction, fisheries management and recruitment, monitoring debris drift, larvae drift, oil spills, fronts and eddies. Additional uses for search and rescue, naval and maritime operations will be investigated. The pilot study will produce velocity maps to be updated on a weekly basis initially, with a goal for eventual 2-day maximum delay from time of satellite measurement. Grid resolution will be 100 km for the basin scale, and finer resolution in the vicinity of the Pacific Islands. Various illustrations of the velocity maps and their applications will be presented. The project's goal is to leave in place an automated system running at NOAA/NESDIS, with an established user clientele and open Internet data access.

IDAHO CHEMICAL PROCESSING PLANT TECHNICAL PROGRESS REPORT FOR APRIL THROUGH JUNE 1958

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

Stevenson, C.E.

1958-11-01

Processing of uranium -aluminum alloy was continued with slight process modifications. Means for recovering rare gases from dissolver off-gas are described. Results of extensive decontamination procedures required to enable entrance to the continuous dissolver cell are also indicated. Pilot plant studies of dissolving aluminum continuously showed that rates of dissolution were decreased by factors of 2 to 4 as the concentration of nitric acid fed was increased from 5.4 to 11N. The rate of aluminum dissolution was found to be proportional to initial area exposed for pieces of different shape. It was found possible to produce a highly basic aluminummore » nitrate solution at a reasonable rate by dissolving to low concentration in dilute acid, followed by evaporation to the desired level. Uranium exchange rate measurements for the TBP extraction process are described. A canned rotor pump under test with graphite bearings operated 6000 hours with nominal wear. Difficulties were experienced in testing a nutating disc pump. Measurements of the potential of zirconium in hydrofluoric acid as a function of pH confirmed the predicted equation. In teflon vessels, zirconium dissolves a little more rapidly in nitric-hydrofluoric acid mixtures than in glass vessels, presumably due to reaction of fluoride with silica. Titunium alloy Types 55A and 75A were found to resist corrosion by certain boiling nitric-hydrochloric acid mixtures. Initial tests have commenced with a NaK-heated 100 liter/hour pilot plant aluminum nitrate calciner to continue process demonstration. In tests in the smaller pilot plant unit, increasing feed spray air ratio was found to increase particle loading in the cyclone effluent. Laboratory studies indicated that a venturi scrubber using dilute nitric acid at 80 C should remove ruthenium effectively from calciner off-gas. In a pilot plant test in which a significant fraction of ruthenium feed was retained by the alumina, substantial absorption of volatilized ruthenium was obtained. Thermal conductivity of alumina near 3000 F was about 0.26 Btu/hr)(ft)( F). In leaching studies, very little strontium or plutonium was removed by water from alumina calcined at 550 C. Dilute nitric acid, however, extracted strontium from this material to the same degree (~ 50 percent) as from material calcined at 400 C. Concentrated basic aluminum nitrate was produced from simulated aluminum nitrate waste by slow hydrolysis with urea followed by evaporation. Aluminum was efficiently extracted from buffered aluminum nitrate solution by acetylacetone and was stripped back into nitric acid. A filterable aluminum phosphate was precipituted from aluminum nitrate solution by urea hydrolysis; the phosphate effectively carried fission products, however. Spectrophotometric methods were developed for macro and micro quantities of uranium, in the presence of high concentrations of other ions, based on tetrapropylammonium nitrate extraction. (For preceding period see ID0-14443.) (auth)« less

F-8 DFBW on-board electronics

NASA Technical Reports Server (NTRS)

1971-01-01

The Apollo hardware jammed into the F-8C. The computer is partially visible in the avionics bay at the top of the fuselage behind the cockpit. Note the display and keyboard unit in the gun bay. To carry the computers and other equipment, the F-8 DFBW team removed the aircraft's guns and ammunition boxes. The F-8 Digital Fly-By-Wire (DFBW) flight research project validated the principal concepts of all-electric flight control systems now used on nearly all modern high-performance aircraft and on military and civilian transports. The first flight of the 13-year project was on May 25, 1972, with research pilot Gary E. Krier at the controls of a modified F-8C Crusader that served as the testbed for the fly-by-wire technologies. The project was a joint effort between the NASA Flight Research Center, Edwards, California, (now the Dryden Flight Research Center) and Langley Research Center. It included a total of 211 flights. The last flight was December 16, 1985, with Dryden research pilot Ed Schneider at the controls. The F-8 DFBW system was the forerunner of current fly-by-wire systems used in the space shuttles and on today's military and civil aircraft to make them safer, more maneuverable, and more efficient. Electronic fly-by-wire systems replaced older hydraulic control systems, freeing designers to design aircraft with reduced in-flight stability. Fly-by-wire systems are safer because of their redundancies. They are more maneuverable because computers can command more frequent adjustments than a human pilot can. For airliners, computerized control ensures a smoother ride than a human pilot alone can provide. Digital-fly-by-wire is more efficient because it is lighter and takes up less space than the hydraulic systems it replaced. This either reduces the fuel required to fly or increases the number of passengers or pounds of cargo the aircraft can carry. Digital fly-by-wire is currently used in a variety of aircraft ranging from F/A-18 fighters to the Boeing 777. The DFBW research program is considered one of the most significant and most successful NASA aeronautical programs since the inception of the agency. F-8 aircraft were built originally for the U.S. Navy by LTV Aerospace of Dallas, Texas. The aircraft had a wingspan of 35 feet, 2 inches; was 54 feet, 6 inches long; and was powered by a Pratt & Whitney J57 turbojet engine.

HL-10 on ramp

NASA Technical Reports Server (NTRS)

1966-01-01

The HL-10, seen here parked on the ramp at NASA's Flight Research Center in 1966, had a radically different shape from that of the M2-F2/F3. While the M2s were flat on top and had rounded undersides (giving them a bathtub shape), the HL-10 had a flat lower surface and a rounded top. Both shapes provided lift without wings, however. This photo was taken before the HL-10's fins were modified. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. The vehicle was unstable and required modifications to its fins to improve its handling qualities and stability. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Pilot-Scale Silicone Process for Low-Cost Carbon Dioxide Capture. Final Scientific/Technical Report

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

Hancu, Dan; Wood, Benjamin; Genovese, Sarah

GE Global Research has developed, over the last 8 years, a platform of cost effective CO 2 capture technologies based on a non-aqueous aminosilicone solvent (GAP-1m). As demonstrated in a previous funded DOE project (DE-FE0007502), the GAP-1m solvent has increased CO 2 working capacity, lower volatility and corrosivity than the benchmark aqueous amine technology. The current report describes the cooperative program between GE Global Research (GE GRC), and the National Carbon Capture Center (NCCC) to design, construct, and operate a pilot-scale process using GAP-1m solvent to demonstrate its performance at 0.5 MWe. (i) Performance of the GAP-1m solvent was demonstratedmore » in a 0.5 MWe pilot with real flue gas for over 900 hrs. of operation using two alternative desorption designs: a Continuous Stirred Tank Reactor (CSTR), and a Steam Stripper Column (SSC). The CSTR is a one-stage separation unit with reduced space requirements, and capital cost. The alternative is a multi-stage separation column, with improved desorption efficiency. Testing the two desorber options allowed us to identify the most cost effective, and space efficient desorber solution. (ii) CSTR Campaign: The CSTR desorber unit was designed, fabricated and integrated with the pilot solvent test unit (PSTU), replacing the PSTU Steam Stripper Column at NCCC. Solvent management and waste water special procedures were implemented to accommodate operation of the non-aqueous solvent in the PSTU. Performance of the GAP-1m solvent with the CSTR was demonstrated for over 500 hrs. while varying temperature of the desorption (230 – 265 oF), solvent circulation rate (GAP-1m : CO 2 (molar) = 1.5 – 4), and flue gas flow rates (0.2 – 0.5 MWe). Solvent carry-over in the CO 2 product was minimized by maintaining water content below 5 wt.%, and desorption pressure at 7 psig. CO 2 capture efficiency achieved was 95% at 0.25 MWe (GAP-1m : CO 2 = 4 (molar), 230 oF desorption), and 65% at 0.5 MWe (GAP-1m : CO 2 (molar) = 1.5, 248 oF). Solvent loss was dominated by thermal degradation of the rich solvent. (iii) Steam Stripper Column Campaign: Higher expected cost of the solvent vs. aqueous amines makes solvent management a top priority to maintain the low cost for the process. During the testing of the GAP-1m solvent with the CSTR, thermal degradation of the rich solvent was found to be the main mechanism in solvent loss. Small amounts of water in the working solution were found to be an effective way to enable steam stripping, thereby lowering desorption temperature, and hence reducing thermal degradation. Steam stripping also increased working capacity by 30% due to a more efficient desorption. The concept was first tested in a glass stripping column (lab scale, GE GRC), optimized in a continuous bench scale system (2 kWe, GE GRC), and demonstrated in a 0.5 MWe PSTU at NCCC. No special system modifications were required to the PSTU to accommodate the testing of the non-aqueous GAP-1 solvent with the regenerator column. SSC was found to be more robust towards solvent entrainment (H 2O < 35 wt.%). 90 – 95% CO 2 capture efficiency was achieved under stoichiometric conditions at 0.5 MWe (235 oF desorption, 2 psig and 19 wt. % H 2O). Both CO 2 capture efficiency and specific duty reached optimum conditions at 18 wt.% H 2O. Low amine degradation (< 0.05 wt.%/day) was recorded over 350 hrs. of operation. Controlled water addition to GAP-1m solvent decreased the desorption temperature, thermal degradation, and improved the CO 2 working capacity due to more efficient absorption and desorption processes. Under these conditions, the GAP-1m solvent exhibited a 25% increased working capacity, and 10% reduction in specific steam duty vs. MEA, at 10 oF lower desorption temperature. (iv) Techno-economic Analysis: The pilot-scale PSTU engineering data were used to update the capture system process models, and the techno-economic analysis was performed for a 550 MW coal fired power plant. The 1st year CO 2 removal cost for the aminosilicone-based carbon-capture process was evaluated at $48/ton CO 2 using the steam stripper column. This is a 20% reduction compared to MEA, primarily due to lower overall capital cost. CO 2 cost using the CSTR desorber is dominated by the economics of the solvent make-up. The steam stripper desorber is the preferred unit operation due to a more efficient desorption, and reduced solvent make-up rate. Further reduction in CO 2 capture cost is expected by lowering the manufacturing cost of the solvent, implementing flowsheet optimization and/or implementing the next generation aminosilicone solvent with improved stability and increased CO 2 working capacity.« less

M2-F1 in flight over lakebed on tow line

NASA Technical Reports Server (NTRS)

1963-01-01

After initial ground-tow flights of the M2-F1 using the Pontiac as a tow vehicle, the way was clear to make air tows behind a C-47. The first air tow took place on 16 August 1963. Pilot Milt Thompson found that the M2-F1 flew well, with good control. This first flight lasted less than two minutes from tow-line release to touchdown. The descent rate was 4,000 feet per minute. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

77 FR 35961 - Environmental Impacts Statements; Notice of Availability

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-15

... ENVIRONMENTAL PROTECTION AGENCY [ER-FRL-9003-5] Environmental Impacts Statements; Notice of....epa.gov/compliance/nepa/ . Weekly receipt of Environmental Impact Statements Filed 06/04/2012 through..., 00, F-35A Training Basing, To Base a Pilot Training Center with the Beddown of F-35A Training...

Complex performance during exposure to high temperatures.

DOT National Transportation Integrated Search

1969-06-01

The effects of high temperature on psychomotor performance and physiological function were studied on male pilots (age 30-51) holding a current medical certificate. A total of 41 runs were made at neutral (23.8C (75F), or hot (60.0C (140F), 71.1C (16...

Transformation of Bisphenol A in Water Distribution Systems, A Pilot-scale Study

EPA Science Inventory

Halogenations of bisphenol A (BPA) in a pilot-scale water distribution system (WDS) of cement-lined ductile cast iron pipe were investigated under the condition: pH 7.3±0.3, water flow velocity of 1.0 m/s, and 25 °C ± 1 °C in water temperature. The testing water was chlorinated f...

Impact of Increased Undergraduate Pilot Training (UPT) Activity Duty Service Commitment on the Air National Guard (ANG)

DTIC Science & Technology

1988-05-01

index of retention. To maintain the pilot force, USAF needs a CCR of about sixty percent-and the overall rate Is running lower thatt that. SOJA (E Aor...159th Tactical Fighter Group, USNAS New Orleans, New Orleans, LA : 22 January 1988. 23 22. Doty, James F. Major, ANG. Telephone Interview with

Home Cervical Traction to Reduce Neck Pain in Fighter Pilots.

PubMed

Chumbley, Eric M; O'Hair, Nicole; Stolfi, Adrienne; Lienesch, Christopher; McEachen, James C; Wright, Bruce A

2016-12-01

Most fighter pilots report cervical pain during their careers. Recommendations for remediation lack evidence. We sought to determine whether regular use of a home cervical traction device could decrease reported cervical pain in F-15C pilots. An institutional review board-approved, Health Insurance Portability and Accountability Act-compliant, controlled crossover study was undertaken with 21 male F-15C fighter pilots between February and June 2015. Of the 21 subjects, 12 completed 6 wk each of traction and control, while logging morning, postflying, and post-traction pain. Pain was compared with paired t-tests between the periods, from initial pain scores to postflying, and postflying to post-traction. In the traction phase, initial pain levels increased postflight, from 1.2 (0.7) to 1.6 (1.0) Subsequent post-traction pain levels decreased to 1.3 (0.9), with a corresponding linear decrease in pain relative to pain reported postflight. The difference in pain levels after traction compared to initial levels was not significant, indicating that cervical traction was effective in alleviating flying-related pain. Control pain increased postflight from 1.4 (0.9) to 1.9 (1.3). Daily traction phase pain was lower than the control, but insignificant. To our knowledge, this is the first study of home cervical traction to address fighter pilots' cervical pain. We found a small but meaningful improvement in daily pain rating when using cervical traction after flying. These results help inform countermeasure development for pilots flying high-performance aircraft. Further study should clarify the optimal traction dose and timing in relation to flying.Chumbley EM, O'Hair N, Stolfi A, Lienesch C, McEachen JC, Wright BA. Home cervical traction to reduce neck pain in fighter pilots. Aerosp Med Hum Perform. 2016; 87(12):1010-1015.

High-Alpha Research Vehicle (HARV) longitudinal controller: Design, analyses, and simulation resultss

NASA Technical Reports Server (NTRS)

Ostroff, Aaron J.; Hoffler, Keith D.; Proffitt, Melissa S.; Brown, Philip W.; Phillips, Michael R.; Rivers, Robert A.; Messina, Michael D.; Carzoo, Susan W.; Bacon, Barton J.; Foster, John F.

1994-01-01

This paper describes the design, analysis, and nonlinear simulation results (batch and piloted) for a longitudinal controller which is scheduled to be flight-tested on the High-Alpha Research Vehicle (HARV). The HARV is an F-18 airplane modified for and equipped with multi-axis thrust vectoring. The paper includes a description of the facilities, a detailed review of the feedback controller design, linear analysis results of the feedback controller, a description of the feed-forward controller design, nonlinear batch simulation results, and piloted simulation results. Batch simulation results include maximum pitch stick agility responses, angle of attack alpha captures, and alpha regulation for full lateral stick rolls at several alpha's. Piloted simulation results include task descriptions for several types of maneuvers, task guidelines, the corresponding Cooper-Harper ratings from three test pilots, and some pilot comments. The ratings show that desirable criteria are achieved for almost all of the piloted simulation tasks.

Investigations at Site 32 (41EP325), Keystone Dam Project. A Multicomponent Archeological Site in Western El Paso County, Texas.

DTIC Science & Technology

1983-03-01

were roost oftenr taken from the fill around the rcotks- aml )from the larger nonroo-k features; (Features lF and 29) wert tcken frcm. at leas t...Fi:s ~ A wi tph i;.taii H FcA. 4,l~ ruh r <I i i K’ t to’’ "aitit I it t wI cft I r. . ia i: i" ro nhc V p~jct !: i! cxtorus ruTm tIt mocn: :: linfji cur...pilot study. Aray:; of the remaining . aml ; Irs was to be dependent or, the results of the pilot study. ’)f these eleven samples, only two contained

ECN-22193

NASA Image and Video Library

1982-12-22

A close-up photo of the spin chute mounted on the rear fuselage of the AFTI F-16, a safety device designed to prevent the loss of aircraft in spin conditions. Under some circumstances, pilots cannot recover from spins using normal controls. It these instances, the spin chute is deployed, thus "breaking" the spin and enabling the pilot to recover. The spin chute is held in a metal cylinder attached to the AFTI F-16 by four tubes, a structure strong enough to withstand the shock of the spin chute opening. Unlike the air probe in the last photo, spin chutes are not standard equipment on research or prototype aircraft but are commonly attached expressly for actual spin tests.

Scott Crossfield - Portraits

NASA Technical Reports Server (NTRS)

1954-01-01

Albert Scott Crossfield joined the U.S. Navy and was commissioned an ensign in 1943. After completing his military flight training, he served as a fighter and gunnery instructor and maintenance officer before spending six months overseas. He did not see combat duty, but flew such aircraft as the F6F and F4U fighters. Crossfield attended the University of Washington, receiving a Bachelor degree in aeronautical engineering in 1949 and a Masters in aeronautical engineering the following year. He joined the National Advisory Committee for Aeronautics as a pilot at the High-Speed Flight Research Station in June 1950. For the next five years Crossfield flew high speed jets and rocket planes for NACA, including the Bell X-1#2 (10 flights, first on April 20, 1951), Douglas D-558-I #3 Skystreak (15 flights, first on November 29, 1950), D-558-II #2 (53 flights, first on September 28, 1951), D-558-II #3 Skyrocket (36 flights, first on December 22, 1950), Northrop X-4 (29 flights, first on December 6, 1950), Bell X-5 (10 flights, first on April 3, 1952), Convair XF-92A (25 flights, first on April 9, 1953), and the F-100. On November 20, 1953, Crossfield made the first piloted Mach 2 flight in the D-558-II Skyrocket. Crossfield left NACA in December 1955 to join North American Aviation. North American won the competition to build the X-15 a high altitude, high speed piloted research aircraft.

Toward Adaptation of fNIRS Instrumentation to Airborne Environments

NASA Technical Reports Server (NTRS)

Adamovsky, Grigory; Mackey, Jeffrey R.

2013-01-01

The paper reviews potential applications of functional Near-Infrared Spectroscopy (fNIRS), a well-known medical diagnostic technique, to monitoring the cognitive state of pilots with a focus on identifying ways to adopt this technique to airborne environments. We also discuss various fNIRS techniques and the direction of technology maturation of associated hardware in view of their potential for miniaturization, maximization of data collection capabilities, and user friendliness.

Toward Adaptation of fNIRS Instrumentation to Airborne Environments

NASA Technical Reports Server (NTRS)

Adamovsky, Grigory; Mackey, Jeffrey; Harrivel, Angela; Hearn, Tristan; Floyd, Bertram

2014-01-01

The paper reviews potential applications of functional Near-Infrared Spectroscopy (fNIRS), a well-known medical diagnostic technique, to monitoring the cognitive state of pilots with a focus on identifying ways to adopt this technique to airborne environments. We also discuss various fNIRS techniques and the direction of technology maturation of associated hardware in view of their potential for miniaturization, maximization of data collection capabilities, and user friendliness.

M2-F1 in flight during low-speed car tow

NASA Technical Reports Server (NTRS)

1963-01-01

The M2-F1 shown in flight during a low-speed car tow runs across the lakebed. Such tests allowed about two minutes to test the vehicle's handling in flight. NASA Flight Research Center (later redesignated the Dryden Flight Research Center) personnel conducted as many as 8 to 14 ground-tow flights in a single day either to test the vehicle in preparation for air tows or to train pilots to fly the vehicle before they undertook air tows. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Flight Test Results on the Stability and Control of the F-15 Quiet Spike(TradeMark) Aircraft

NASA Technical Reports Server (NTRS)

Moua, Cheng M.; McWherter, Shaun C.; Cox, Timothy H.; Gera, Joe

2012-01-01

The Quiet Spike F-15B flight research program investigated supersonic shock reduction using a 24-ft sub-scale telescoping nose boom on an F-15B airplane. The program primary flight test objective was to collect flight data for aerodynamic and structural models validation up to 1.8 Mach. Other objectives were to validate the mechanical feasibility of a morphing fuselage at the operational conditions and determine the near-field shock wave characterization. The stability and controls objectives were to assess the effect of the spike on the stability, controllability, and handling qualities of the aircraft and to ensure adequate stability margins across the entire research flight envelop. The two main stability and controls issues were the effects of the telescoping nose boom influenced aerodynamics on the F-15B aircraft flight dynamics and air data and angle of attack sensors. This paper reports on the stability and controls flight envelope clearance methods and flight test analysis of the F-15B Quiet Spike. Brief pilot commentary on typical piloting tasks, approach and landing, refueling task, and air data sensitivity to the flight control system are also discussed in this report.

Convair F-106B Delta Dart Prepares for a Flight

NASA Image and Video Library

1969-05-21

National Aeronautics and Space Administration (NASA) pilot Cliff Crabbs and the flight operations crew prepare a Convair F-106B Delta Dart for a flight from the Lewis Research Center in Cleveland, Ohio. NASA acquired the aircraft three years earlier to investigate noise-reducing inlet and nozzle designs for the supersonic transport engine program. Two General Electric J85 engines were installed underneath the aircraft’s delta wings to simulate the general shape of the supersonic transport’s engines. One of the engines was modified with experimental inlet or nozzle configurations. The unmodified engine was used for comparison. Most F-106B flights were flown in a 200-mile path over the lake between Buffalo and Sandusky, known as the Lake Erie Corridor. The 1100-miles per hour flight took only 11 minutes at an altitude of 30,000 feet. The aircraft almost always returned with a depleted fuel supply so a Visual Flight Rules operation was required. Following the crash of another jet fighter at Lewis in July 1969, the F-106s were stationed at Selfridge Air Force Base in Michigan. NASA pilots flew transport planes each morning to the base before commencing the F-106B missions.

A computerized tablet with visual feedback of hand position for functional magnetic resonance imaging

PubMed Central

Karimpoor, Mahta; Tam, Fred; Strother, Stephen C.; Fischer, Corinne E.; Schweizer, Tom A.; Graham, Simon J.

2015-01-01

Neuropsychological tests behavioral tasks that very commonly involve handwriting and drawing are widely used in the clinic to detect abnormal brain function. Functional magnetic resonance imaging (fMRI) may be useful in increasing the specificity of such tests. However, performing complex pen-and-paper tests during fMRI involves engineering challenges. Previously, we developed an fMRI-compatible, computerized tablet system to address this issue. However, the tablet did not include visual feedback of hand position (VFHP), a human factors component that may be important for fMRI of certain patient populations. A real-time system was thus developed to provide VFHP and integrated with the tablet in an augmented reality display. The effectiveness of the system was initially tested in young healthy adults who performed various handwriting tasks in front of a computer display with and without VFHP. Pilot fMRI of writing tasks were performed by two representative individuals with and without VFHP. Quantitative analysis of the behavioral results indicated improved writing performance with VFHP. The pilot fMRI results suggest that writing with VFHP requires less neural resources compared to the without VFHP condition, to maintain similar behavior. Thus, the tablet system with VFHP is recommended for future fMRI studies involving patients with impaired brain function and where ecologically valid behavior is important. PMID:25859201

Pilot scale-SO{sub 2} control by dry sodium bicarbonate injection and an electrostatic precipitator

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

Pliat, M.J.; Wilder, J.M.

2007-10-15

A 500 actual cubic feet gas per minute (acfm) pilot-scale SO{sub 2} control study was undertaken to investigate flue gas desulfurization (FGD) by dry sodium sorbents in 400{sup o}F (204.5{sup o}C) flue gases emitted from a coal fired boiler with flue gas concentrations between 350 and 2500 ppm SO{sub 2}. Powdered sodium alkaline reagents were injected into the hot flue gas downstream of the air preheater and the spent reagents were collected using an electrostatic precipitator. Three different sorbents were used: processed sodium bicarbonate of two particle sizes; solution mined sodium bicarbonate, and processed sodium sesquicarbonate. SO{sub 2} concentrations weremore » measured upstream of the reagent injection, 25-ft (7.62 m) downstream of the injection point, and downstream of the electrostatic precipitator. SO{sub 2} collection efficiencies ranged from 40 to 80% using sodium bicarbonate stoichiometric ratios from 0.5 to 3.0. Much of the in-duct SO{sub 2} removal occurred during the first second of reagent reaction time, indicating that the sulfur dioxide-sodium reaction rates may be faster than have been measured for fixed bed measurements reported in the literature.« less

Jeff Greulich, DynCorp life support technician, adjusts a prototype helmet on a NASA Dryden pilot. F

NASA Technical Reports Server (NTRS)

2002-01-01

Jeff Greulich, DynCorp life support technician, adjusts a prototype helmet on pilot Craig Bomben at NASA Dryden Flight Research Center, Edwards, Calif. Built by Gentex Corp., Carbondale, Pa., the helmet was evaluated by five NASA pilots during the summer and fall of 2002. The objective was to obtain data on helmet fit, comfort and functionality. The inner helmet of the modular system is fitted to the individual crewmember. The outer helmet features a fully integrated spectral mounted helmet display and a binocular helmet mounted display. The helmet will be adaptable to all flying platforms. The Dryden evaluation was overseen by the Center's Life Support office. Assessments have taken place during normal proficiency flights and some air-to-air combat maneuvering. Evaluation platforms included the F-18, B-52 and C-12. The prototype helmet is being developed by the Naval Air Science and Technology Office and the Aircrew Systems Program Office, Patuxent River, Md.

An investigation of motion base cueing and G-seat cueing on pilot performance in a simulator

NASA Technical Reports Server (NTRS)

Mckissick, B. T.; Ashworth, B. R.; Parrish, R. V.

1983-01-01

The effect of G-seat cueing (GSC) and motion-base cueing (MBC) on performance of a pursuit-tracking task is studied using the visual motion simulator (VMS) at Langley Research Center. The G-seat, the six-degree-of-freedom synergistic platform motion system, the visual display, the cockpit hardware, and the F-16 aircraft mathematical model are characterized. Each of 8 active F-15 pilots performed the 2-min-43-sec task 10 times for each experimental mode: no cue, GSC, MBC, and GSC + MBC; the results were analyzed statistically in terms of the RMS values of vertical and lateral tracking error. It is shown that lateral error is significantly reduced by either GSC or MBC, and that the combination of cues produces a further, significant decrease. Vertical error is significantly decreased by GSC with or without MBC, whereas MBC effects vary for different pilots. The pattern of these findings is roughly duplicated in measurements of stick force applied for roll and pitch correction.

Circadian adaptation of airline pilots during extended duration operations between the USA and Asia.

PubMed

Gander, Philippa; van den Berg, Margo; Mulrine, Hannah; Signal, Leigh; Mangie, Jim

2013-10-01

This study tracked circadian adaptation among airline pilots before, during, and after trips where they flew from Seattle (SEA) or Los Angeles (LAX) to Asia (7--9 time zones westward), spent 7--12 d in Asia, and then flew back to the USA. In Asia, pilots' exposures to local time cues and sleep opportunities were constrained by duty (short-haul flights crossing ≤ 1 time zone/24 h). Fourteen captains and 16 first officers participated (median age = 56 versus 48 yrs, p.U) < 0.001). Their sleep was monitored (actigraphy, duty/sleep diaries) from 3 d pre-trip to 5 d post-trip. For every flight, Karolinska Sleepiness and Samn-Perelli Fatigue scales and 5-min psychomotor vigilance task (PVT) tests were completed pre-flight and at top of descent (TOD). Participants had ≥ 3 d free of duty prior to outbound flight(s). From 72--24 h prior to departure (baseline sleep), mean total sleep/24 h (TST) = 7.00 h (SD = 1.18 h) and mean sleep efficiency = 87% (SD = 4.9%). Most pilots (23/30) flew direct to and from Asia, but 7 LAX-based pilots flew via a 1-d layover in Honolulu (HNL). On flights with ≥ 2 pilots, mean total in-flight sleep varied from 0.40 to 2.09 h outbound and from 0.74 to 1.88 h inbound. Duty patterns in Asia were variable, with ≤ 2 flights/d (mean flight duration = 3.53 h, SD = 0.53 h). TST on days 17 in Asia did not differ from baseline (p.F) = 0.2031). However, mean sleep efficiency was significantly lower than baseline on days 5--7 (p.F) = 0.0041). More pilots were on duty between 20:00 and 24:00 h on days 57 (mean = 21%) than on days 24 (mean = 14%). Sleep propensity distribution phase markers and chi-square periodogram analyses suggest that adaptation to local time was complete by day 4 in Asia. On pre-flight PVT tests in Asia, the slowest 10% of responses improved for flights departing 14:00--19:59 h (p.F) = 0.0484). At TOD, the slowest 10% of responses improved across days for flights arriving 14:00--19:59 h (p.F) = 0.0349) and 20:00--01:59 h (p.F) = 0.0379). Sleepiness and fatigue ratings pre-flight and at TOD did not change across days in Asia. TST on post-trip day 1 was longer than baseline (estimated mean extension = 1.68 h; adjusted p(t) < 0.0001). On all post-trip days, sleep efficiency was comparable to baseline. Sleep propensity distribution phase markers and chi-square periodogram analyses suggest complete readaptation in 12 d. Two opposing influences appeared to affect sleep and PVT performance across days in Asia: progressive circadian adaptation to local time and increasing duty during local night, which displaced sleep from the optimal physiological time. Cumulative sleep restriction across the return flight may explain the large rebound in TST on day 1 post-trip. Thereafter TST, sleep efficiency, and sleep timing suggest that readaptation was complete. Rapid post-trip readaptation may be facilitated by pilots having unconstrained nocturnal sleep opportunities, coupled with stronger patterns of family and social cues than in Asia.

HL-10 on lakebed showing subsonic control surface configuration

NASA Technical Reports Server (NTRS)

1966-01-01

This photo shows the HL-10 on lakebed with its subsonic control surface configuration. The unusual shapes of the lifting bodies, as well as the demands of flying a re-entry shape to comparative low-speed landings, required a complex set of control surfaces. The rudders also served as speed brakes, allowing the pilot to adjust his speed during descent. Moving the flaps at the rear of the fuselage in the same direction pitched the nose up, while moving them in opposite directions rolled the vehicle to the right or left. After the HL-10's fins were modified to improve its handling qualities, the vehicle proved to be the best handling of the original heavy-weight lifting bodies. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

The perception of roll tilt in pilots during a simulated coordinated turn in a gondola centrifuge.

PubMed

Tribukait, Arne; Grönkvist, Mikael; Eiken, Ola

2011-05-01

It has previously been reported that nonpilots underestimate the roll tilt angle after acceleration in a gondola centrifuge. The aim of the present work was to elucidate the significance of flight experience for roll tilt perception based on vestibular information. The subjective visual horizontal (SVH) was measured by means of an adjustable luminous line in darkness. Eight nonpilots (N), nine fighter pilots (F), and eight helicopter pilots (H) underwent two centrifuge runs (2 G, 5 min) heading forward and backward, respectively. The roll position of the gondola (60 degrees at 2 G) was controlled so that the subject was always upright with respect to the gravitoinertial force. Upon acceleration of the centrifuge there was a tilt of the SVH in a direction compensatory to the inclination of the gondola. This tilt was larger in the forward position [N: 17.2 +/- 6.4 degrees, F: 31.2 +/- 16.4 degrees, H: 33.6 +/- 18.2 degrees (means +/- SD)] than in the backward position (N: -5.0 +/- 6.8 degrees, F: -12.2 +/- 17.4 degrees, H: -10.4 +/- 15.4 degrees). In N the tilt declined with time, approaching zero by the end of the 2-G plateau. In the pilots it was significantly larger and did not decline. Flight experience results in an increased ability to perceive the roll tilt during movement along a curved path. That this can be revealed in a centrifuge might suggest that acceleration of the centrifuge constitutes a movement pattern which is similar, from a vestibular point of view, to that of an airplane entering a coordinated turn.

Synthesis and analysis of jet fuels from shale oil and coal syncrudes

NASA Technical Reports Server (NTRS)

Antoine, A. C.; Gallagher, J. P.

1976-01-01

The technical problems involved in converting a significant portion of a barrel of either a shale oil or coal syncrude into a suitable aviation turbine fuel were studied. TOSCO shale oil, H-Coal and COED coal syncrudes were the starting materials. They were processed by distillation and hydrocracking to produce two levels of yield (20 and 40 weight percent) of material having a distillation range of approximately 422 to 561 K (300 F to 550 F). The full distillation range 311 to 616 K (100 F to 650 F) materials were hydrotreated to meet two sets of specifications (20 and 40 volume percent aromatics, 13.5 and 12.75 weight percent H, 0.2 and 0.5 weight percent S, and 0.1 and 0.2 weight percent N). The hydrotreated materials were distilled to meet given end point and volatility requirements. The syntheses were carried out in laboratory and pilot plant equipment scaled to produce thirty-two 0.0757 cu m (2-gal)samples of jet fuel of varying defined specifications. Detailed analyses for physical and chemical properties were made on the crude starting materials and on the products.

Pilot Joseph Algranti entering a McDonnell F2H-2B Banshee

NASA Image and Video Library

1958-02-21

Pilot Joe Algranti climbs into the cockpit of a McDonnell F2H-2B Banshee on the tarmac at the National Advisory Committee for Aeronautics (NACA) Lewis Flight Propulsion Laboratory. Nine months later the laboratory became part of the new National Aeronautics and Space Administration, and the NACA logo was permanently removed from the hangar. Algranti served as a Navy fighter pilot from 1946 to 1947 and earned a Physics degree from the University of North Carolina. He joined the NACA Lewis staff in 1951 witnessed the technological transformation from high speed flight to space. At Lewis Algranti piloted icing research flights, operated the liquid-hydrogen pump system for Project Bee, and served as the primary test subject for the Multi-Axis Space Test Inertia Facility (MASTIF). The MASTIF was a device used to train the Mercury astronauts how to control a spinning capsule. In 1960, Algranti and fellow Lewis pilots Warren North and Harold Ream transferred to NASA’s Space Task Group at Langley to actively participate in the space program. Two years later, Algranti became the Chief of Aircraft Operations and Chief Test Pilot at NASA’s new Manned Space Center in Houston. Algranti earned notoriety in 1968 when he test flew the first Lunar Landing Training Vehicle. He operated the vehicle four minutes before being forced to eject moments before it impacted the ground. Algranti also flew the NASA’s modified Boeing 747 Shuttle Carrier Aircraft, the Super Guppy, and the KC-135 "Vomit Comet" training aircraft. He retired in 1992 with over 40 years of NASA service.

76 FR 60459 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-29

... Consideration for Purchase: continuation of a pilot training program and logistics support for F-16 aircraft at... program and logistics support for F-16 aircraft at Luke Air Force Base, Arizona to include flight training..., which will contribute to an acceptable military balance in the area. This proposed sale is consistent...

78 FR 15874 - Airworthiness Directives; Airbus Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-13

... Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of... Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F... ground threat avoidance, an Airbus A310 aeroplane experienced an uncommanded slide back of the co-pilot...

AFTI/F-16 Spin chute close-up

NASA Technical Reports Server (NTRS)

1982-01-01

A close-up photo of the spin chute mounted on the rear fuselage of the AFTI F-16, a safety device designed to prevent the loss of aircraft in spin conditions. Under some circumstances, pilots cannot recover from spins using normal controls. It these instances, the spin chute is deployed, thus 'breaking' the spin and enabling the pilot to recover. The spin chute is held in a metal cylinder attached to the AFTI F-16 by four tubes, a structure strong enough to withstand the shock of the spin chute opening. Unlike the air probe in the last photo, spin chutes are not standard equipment on research or prototype aircraft but are commonly attached expressly for actual spin tests. During the 1980s and 1990s, NASA and the U.S. Air Force participated in a joint program to integrate and demonstrate new avionics technologies to improve close air support capabilities in next-generation aircraft. The testbed aircraft, seen here in flight over the desert at NASA's Dryden Flight Research Center, Edwards, California, was called the Advanced Fighter Technology Integration (AFTI) F-16. The tests demonstrated technologies to improve navigation and the pilot's ability to find and destroy enemy ground targets day or night, including adverse weather. The aircraft--an F-16A Fighting Falcon (Serial #75-0750)--underwent numerous modifications. A relatively low-cost testbed, it evaluated the feasability of advanced, intergrated-sensor, avionics, and flight control technologies. During the first phase of the AFTI/F-16 program, which began in 1983, the aircraft demonstrated voice-actuated commands, helmet-mounted sights, flat turns, and selective fuselage pointing using forward-mounted canards and a triplex digital flight control computer system. The second phase of research, which began in the summer of 1991, demonstrated advanced technologies and capabilities to find and destroy ground targets day or night, and in adverse weather while using maneuverability and speed at low altitude. This phase was known as the close air support and battlefield air interdiction (CAS/BAI) phase. Finally, the aircraft was used to assess the Automatic Ground Collision Avoidance System (Auto - GCAS), a joint project with the Swedish Government. For these tests, the pilot flew the aircraft directly toward the ground, simulating a total loss of control. The GCAS was designed to take command in such emergencies and bring the aircraft back to level flight. The AFTI F-16 program ended at Dryden on November 4, 1997 after 15 years and over 700 research flights. The USAF continued to fly the aircraft until retiring it to the Air Force Museum on January 9, 2001.

Biosorption of Zn(II) from industrial effluents using sugar beet pulp and F. vesiculosus: From laboratory tests to a pilot approach.

PubMed

Castro, Laura; Blázquez, M Luisa; González, Felisa; Muñoz, Jesús A; Ballester, Antonio

2017-11-15

The aim of this work was to demonstrate the feasibility of the application of biosorption in the treatment of metal polluted wastewaters through the development of several pilot plants to be implemented by the industry. The use as biosorbents of both the brown seaweed Fucus vesiculosus and a sugar beet pulp was investigated to remove heavy metal ions from a wastewater generated in an electroplating industry: Industrial Goñabe (Valladolid, Spain). Batch experiments were performed to study the effects of pH, contact time and initial metal concentration on metal biosorption. It was observed that the adsorption capacity of the biosorbents strongly depended on the pH, increasing as the pH rises from 2 to 5. The adsorption kinetic was studied using three models: pseudo first order, pseudo second order and Elovich models. The experimental data were fitted to Langmuir and Freundlich isotherm models and the brown alga F. vesiculosus showed higher metal uptake than the sugar beet pulp. The biomasses were also used for zinc removal in fixed-bed columns. The performance of the system was evaluated in different experimental conditions. The mixture of the two biomasses, the use of serial columns and the inverse flow can be interesting attempts to improve the biosorption process for large-scale applications. Copyright © 2017 Elsevier B.V. All rights reserved.

NASA Test Flights Examine Effect of Atmospheric Turbulence on Sonic Booms

NASA Image and Video Library

2016-07-20

NASA pilot Nils Larson, and flight test engineer and pilot Wayne Ringelberg, head for a mission debrief after flying a NASA F/A-18 at Mach 1.38 to create sonic booms as part of the SonicBAT flight series at NASA’s Armstrong Flight Research Center in California, to study sonic boom signatures with and without the element of atmospheric turbulence.

STS-31 Pilot Bolden with beverages on the FB-SMS middeck during JSC training

NASA Technical Reports Server (NTRS)

1988-01-01

STS-31 Pilot Charles F. Bolden holds three beverage containers while in front of the galley on the middeck of the fixed based (FB) shuttle mission simulator (SMS) during a training simulation at JSC's Mission Simulation and Training Facility Bldg 5. From the middeck, Bolden, wearing lightweight headset, simulates a communications link with ground controllers and fellow crewmembers.

Astronaut Alan Bean steps from ladder of Lunar Module for EVA

NASA Image and Video Library

1969-11-19

AS12-46-6729 (19 Nov. 1969) --- Astronaut Alan L. Bean, lunar module pilot for the Apollo 12 lunar landing mission, steps from the ladder of the Lunar Module to join astronaut Charles Conrad Jr., commander, in extravehicular activity on Nov. 19, 1969. Astronaut Richard F. Gordon Jr., command module pilot, remained with the Command and Service Modules in lunar orbit.

F-14 modeling study

NASA Technical Reports Server (NTRS)

Levison, W. H.; Baron, S.

1984-01-01

Preliminary results in the application of a closed loop pilot/simulator model to the analysis of some simulator fidelity issues are discussed in the context of an air to air target tracking task. The closed loop model is described briefly. Then, problem simplifications that are employed to reduce computational costs are discussed. Finally, model results showing sensitivity of performance to various assumptions concerning the simulator and/or the pilot are presented.

Human Factors Engineering #3 Crewstation Assessment for the OH-58F Helicopter

DTIC Science & Technology

2014-03-01

Additionally, workload was assessed for level of interoperability 2 (LOI 2) tasks that the aircrew performed with an unmanned aircraft system (UAS...TTP tactics, techniques, and procedures UAS unmanned aircraft system 47 VFR visual flight rules VMC visual meteorological conditions VTR...For example, pilots often perform navigation tasks, communicate via multiple radios, monitor aircraft systems , and assist the pilot on the controls

Pilot Neil Armstrong in the X-15 #1 cockpit

NASA Technical Reports Server (NTRS)

1961-01-01

NASA pilot Neil Armstrong is seen here in the cockpit of the X-15 ship #1 (56-6670) after a research flight. A U.S. Navy pilot in the Korean War who flew 78 combat missions in F9F-2 jet fighters and who was awarded the Air Medal and two Gold Stars, Armstrong graduated from Purdue University in 1955 with a bachelor degree in aeronautical engineering. That same year, he joined the National Advisory Committee for Aeronautics' Lewis Flight Propulsion Laboratory in Cleveland, Ohio (today, the NASA Glenn Research Center). In July 1955, Armstrong transferred to the High-Speed Flight Station (HSFS, as Dryden Flight Research Center was then called) as an aeronautical research engineer. Soon thereafter, he became a research pilot. For the first few years at the HSFS, Armstrong worked on a number of projects. He was a pilot on the Navy P2B-1S used to launch the D-558-2 and also flew the F-100A, F-100C, F-101, F-104A, and X-5. His introduction to rocket flight came on August 15, 1957, with his first flight (of four, total) on the X-1B. He then became one of the first three NASA pilots to fly the X-15, the others being Joe Walker and Jack McKay. (Scott Crossfield, a former NACA pilot, flew the X-15 first but did so as a North American Aviation pilot.) The X-15 was a rocket-powered aircraft. The original three aircraft were about 50 ft long with a wingspan of 22 ft. The modified #2 aircraft (X-15A-2 was longer.) They were a missile-shaped vehicles with unusual wedge-shaped vertical tails, thin stubby wings, and unique side fairings that extended along the side of the fuselage. The X-15 weighed about 14,000 lb empty and approximately 34,000 lb at launch. The XLR-99 rocket engine, manufactured by Thiokol Chemical Corp., was pilot controlled and was rated at 57,000 lb of thrust, although there are indications that it actually achieved up to 60,000 lb. North American Aviation built three X-15 aircraft for the program. The X-15 research aircraft was developed to provide in-flight information and data on aerodynamics, structures, flight controls, and the physiological aspects of high-speed, high-altitude flight. A follow-on program used the aircraft as testbeds to carry various scientific experiments beyond the Earth's atmosphere on a repeated basis. For flight in the dense air of the usable atmosphere, the X-15 used conventional aerodynamic controls such as rudder surfaces on the vertical stabilizers to control yaw and movable horizontal stabilizers to control pitch when moving in synchronization or roll when moved differentially. For flight in the thin air outside of the appreciable Earth's atmosphere, the X-15 used a reaction control system. Hydrogen peroxide thrust rockets located on the nose of the aircraft provided pitch and yaw control. Those on the wings provided roll control. Because of the large fuel consumption, the X-15 was air launched from a B-52 aircraft at approximately 45,000 ft and a speed of about 500 mph. Depending on the mission, the rocket engine provided thrust for the first 80 to 120 sec of flight. The remainder of the normal 10 to 11 min. flight was powerless and ended with a 200-mph glide landing. Generally, one of two types of X-15 flight profiles was used; a high-altitude flight plan that called for the pilot to maintain a steep rate of climb, or a speed profile that called for the pilot to push over and maintain a level altitude. The X-15 was flown over a period of nearly 10 years -- June 1959 to Oct. 1968 -- and set the world's unofficial speed and altitude records of 4,520 mph (Mach 6.7) and 354,200 ft in a program to investigate all aspects of manned hypersonic flight. Information gained from the highly successful X-15 program contributed to the development of the Mercury, Gemini, and Apollo manned spaceflight programs, and also the Space Shuttle program. The X-15s made a total of 199 flights, and were manufactured by North American Aviation. X-15-1, serial number 56-6670, is now located at the National Air and Space Museum, Washington DC. North American X-15A-2, serial number 56-6671, is at the United States Air Force Museum, Wright-Patterson AFB, Ohio. X-15-3, serial number 56-6672, crashed on 15 November 1967, resulting in the death of Maj. Michael J. Adams.

Test pilots 1962 - Armstrong, Walker, Dana, Peterson, McKay, Thompson, Butchart

NASA Technical Reports Server (NTRS)

1962-01-01

The research pilots at what in 1962 was called the Flight Research Center standing in front of the X-1E. They are (left to right) Neil Armstrong, Joe Walker, Bill Dana, Bruce Peterson, Jack McKay, Milt Thompson, and Stan Butchart. of the group, Armstrong, Walker, Dana, McKay and Thompson all flew the X-15. Bruce Peterson flew the M2-F2 and HL-10 lifting bodies, while Stan Butchart was the B-29 drop plane pilot for many of the D-558-II and X-1 series research aircraft.

A Handling Qualities Investigation of Conventional, Rate Command/ Attitude Hold, and Attitude Command/Attitude Hold Response-Types in the Probe and Drogue Air Refueling Task

DTIC Science & Technology

1994-03-01

Mr. Lou Knotts , Mr. Jeff Peer, and Mr. Eric Ohmit for their support. Mr. Knotts and Mr. Peer served as safety pilots during the inflight evaluations...5129 Taschner Peer 1.6 Griffith, Rauch Hoy, Mattedi 5 5130 Watrous Peer 1.5 Griffith, Rauch Hoy, Mattedi 6 5131 Taschner Knotts 1.5 Griffith, Rauch Hoy...Mattedi 7 5132 Watrous Knott : 1.6 Andreas, Hill Kipp 8 5133 Taschner Knotts 1.6 Andreas, Hill Wiflcox F.2 Pilot Commentary The pilot commentary from

Effect of Brief Mindfulness Practice on Self-Reported Affect, Craving, and Smoking: A Pilot Randomized Controlled Trial Using Ecological Momentary Assessment.

PubMed

Ruscio, Aimee C; Muench, Christine; Brede, Emily; Waters, Andrew J

2016-01-01

Despite efficacious pharmacological and behavioral treatments, most smokers attempt to quit without assistance and fail to quit. Mindfulness practice may be useful in smoking cessation. This ecological momentary assessment (EMA) study was a pilot parallel group randomized controlled trial of a brief mindfulness practice (Brief-MP) intervention on self-reported smoking behavior delivered to smokers on a Personal Digital Assistant (PDA) in the field. Adult community smokers (N = 44) were randomly assigned to a Brief-MP (n = 24) or Control (sham meditation; n = 20) group. Participants were instructed to smoke as much or as little as they liked. Participants carried a PDA for 2 weeks and were instructed to initiate 20 minutes of meditation (or control) training on the PDA daily, completing an assessment of cognitive and affective processes immediately afterwards. Additionally, they completed assessments at random times up to four times per day. Primary outcome variables were negative affect, craving, and cigarettes smoked per day, all self-reported. Thirty-seven participants provided EMA data totaling 1874 assessments. Linear Mixed Model analyses on EMA data revealed that Brief-MP (vs. Control) reduced overall negative affect, F(1, 1798) = 13.8, P = .0002; reduced craving immediately post-meditation, (Group × Assessment Type interaction, F(2, 1796) = 12.3, P = .0001); and reduced cigarettes smoked per day over time (Group × Day interaction, F(1, 436) = 5.50, P = .01). Brief-MP administered in the field reduced negative affect, craving, and cigarette use, suggesting it may be a useful treatment. Published by Oxford University Press on behalf of the Society for Research on Nicotine and Tobacco 2015. This work is written by (a) US Government employee(s) and is in the public domain in the US.

APOLLO-SOYUZ TEST PROJECT (ASTP) - CREWMEN - JSC

NASA Image and Video Library

1975-07-09

S75-28361 (9 July 1975) --- These ten American astronauts compose the U.S. prime crew, the backup crew and the crew support team for the joint U.S.-USSR Apollo-Soyuz Test Project docking mission in Earth orbit. They are, left to right, Robert L. Crippen, support team; Robert F. Overmyer, support team; Richard H. Truly, support team; Karol J. Bobko, support team; Donald K. Slayton, prime crew docking module pilot; Thomas P. Stafford, prime crew commander; Vance D. Brand, prime crew command module pilot; Jack R. Lousma, backup crew docking module pilot; Ronald E. Evans, backup crew command module pilot; and Alan L. Bean, backup crew commander. They are photographed by the Apollo Mission Simulator console in Building 5 at NASA's Johnson Space Center.

Verification of geomechanical integrity and prediction of long-term mineral trapping for the Ketzin CO2 storage pilot site

NASA Astrophysics Data System (ADS)

Kempka, Thomas; De Lucia, Marco; Kühn, Michael

2014-05-01

Static and dynamic numerical modelling generally accompany the entire CO2 storage site life cycle. Thereto, it is required to match the employed models with field observations on a regular basis in order to predict future site behaviour. We investigated the coupled processes at the Ketzin CO2 storage pilot site [1] using a model coupling concept focusing on the temporal relevance of processes involved (hydraulic, chemical and mechanical) at given time-scales (site operation, abandonment and long-term stabilization). For that purpose, long-term dynamic multi-phase flow simulations [2], [3] established the basis for all simulations discussed in the following. Hereby, pressure changes resulting in geomechanical effects are largest during site operation, whereas geochemical reactions are governed by slow kinetics resulting in a long-term stabilization. To account for mechanical integrity, which may be mainly affected during site operation, we incorporated a regional-scale coupled hydro-mechanical model. Our simulation results show maximum ground surface displacements of about 4 mm, whereas shear and tensile failure are not observed. Consequently, the CO2 storage operation at the Ketzin pilot site does not compromise reservoir, caprock and fault integrity. Chemical processes responsible for mineral trapping are expected to mainly occur during long-term stabilization at the Ketzin pilot site [4]. Hence, our previous assessment [3] was extended by integrating two long-term mineral trapping scenarios. Thereby, mineral trapping contributes to the trapping mechanisms with 11.7 % after 16,000 years of simulation in our conservative and with 30.9 % in our maximum reactivity scenarios. Dynamic flow simulations indicate that only 0.2 % of the CO2 injected (about 67,270 t CO2 in total) is in gaseous state, but structurally trapped after 16,000 years. Depending on the studied long-term scenario, CO2 dissolution is the dominating trapping mechanism with 68.9 % and 88.1 %, respectively. We verified the mechanical integrity of the storage system during site operation and predicted the trapping mechanisms for the Ketzin pilot site based on a time-dependent integration of relevant processes for a time period of 16,000 years. Supported by our coupled modelling results, we conclude that CO2 storage at the Ketzin site is safe and reliable on the pilot scale. References [1] Martens, S., Kempka, T., Liebscher, A., Lüth, S., Möller, F., Myrttinen, A., Norden, B., Schmidt-Hattenberger, C., Zimmer, M., Kühn, M. Europe's longest-operating on-shore CO2 storage site at Ketzin, Germany: a progress report after three years of injection. Environmental Earth Sciences 2012 67(2): 323-334. [2] Kempka, T., Kühn, M. Numerical simulations of CO2 arrival times and reservoir pressure coincide with observations from the Ketzin pilot site, Germany. Environmental Earth Sciences 2013 70(8): 3675-3685. [3] Kempka, T., Klein, E., De Lucia, M., Tillner, E., Kühn, M. Assessment of Long-term CO2 Trapping Mechanisms at the Ketzin Pilot Site (Germany) by Coupled Numerical Modelling. Energy Procedia 2013 37: 5419-5426. [4] Klein, E., De Lucia, M., Kempka, T., Kühn, M. Evaluation of long-term mineral trapping at the Ketzin pilot site for CO2 storage: An integrative approach using geochemical modelling and reservoir simulation. International Journal of Greenhouse Gas Control 2013 19: 720-730.

Arsenic Contaminated Groundwater Treatment Pilot Study at the Sharpe Army Depot (SHAD) Lathrop, California. Task Order 9

DTIC Science & Technology

1990-12-01

I- I IIIIII 11HI ca~ 1- 1.cc III I HHo I H [I I 5-12 December 1990 Revision: 1 in Table 5-6, the performance of F-1 AA, in terms of the equilibrium...required. In treatment of water for boiler makeup, the relative freedom of Amberlite I RA-402 from *. ..IOEAIGCHRCEITC organic fouling insures good...hydroxide form) 1400 F (600 C) medium pressure boilers . This represents a considerable f chloride form) 1700 F (77 0C) saving over the use of deionization

F-100A on lakebed

NASA Technical Reports Server (NTRS)

1955-01-01

North American F-100A (52-5778) Super Sabre is parked on the Rogers Dry Lakebed at Edwards Air Force Base, California, 1955. This photo shows the large tail on the F-100A. When the basic research was completed on this F-100A another program was assigned. On March 5, 1957 two aeronautical engineers and a test pilot from NACA High-Speed Flight Station took the airplane to participate in a Gunnery Operations program at Nellis Air Force Base, Nevada. When the program was completed the aircraft returned for other assignments to NACA, at Edwards, California.

A situation-response model for intelligent pilot aiding

NASA Technical Reports Server (NTRS)

Schudy, Robert; Corker, Kevin

1987-01-01

An intelligent pilot aiding system needs models of the pilot information processing to provide the computational basis for successful cooperation between the pilot and the aiding system. By combining artificial intelligence concepts with the human information processing model of Rasmussen, an abstraction hierarchy of states of knowledge, processing functions, and shortcuts are developed, which is useful for characterizing the information processing both of the pilot and of the aiding system. This approach is used in the conceptual design of a real time intelligent aiding system for flight crews of transport aircraft. One promising result was the tentative identification of a particular class of information processing shortcuts, from situation characterizations to appropriate responses, as the most important reliable pathway for dealing with complex time critical situations.

Combustion characterization of carbonized RDF, Joint Venture Task No. 7. Topical Report

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

None, None

1995-04-30

The overall objective of this research program was to demonstrate EnerTech's and the Energy & Environmental Research Center's (EERC) process of slurry carbonization for producing homogeneous, pumpable titels from refuse-derived fuel (RDF) with continuous pilot plant facilities, and to characterize flue gas and ash emissions from combustion of the carbonizd RDF slurry fuel. Please note that "Wet Thermal Oxidation" is EnerTech's trademark mme for combustion of the carbonized RDF slurry fuel. Carbonized RDF slurry fuels were produced with the EERC'S 7.5-tpd (wet basis) pilot plant facility. A hose diaphragm pump pressurized a 7- lo-wt% feed RDF slurry, with a viscositymore » of 500 cP, to approximately 2500 psig. The pressurized RDF slurry was heated by indirect heat exchangers to between 5850 -626°F, and its temperature and pressure was maintained in a downflow reactor. The carbonized slurry was flashed, concentrated in a filter press, and ground in an attritor. During operation of the pilot plant, samples of the feed RDF slurry, carbonization gas, condensate, carbonized solids, and filtrate were taken and analyzed. Pilot-scale slurry carbonization experiments with RDF produced a homogeneous pumpable slurry fuel with a higher heating value (HHV) of 3,000-6,600 Btu/lb (as-received basis), at a viscosity of 500 CP at 100 Hz decreasing, and ambient temperature. Greater-heating-value slurry fuels were produced at higher slurry carbonization temperatures. During slurry carbonization, polyvinyl chloride (PVC) plastics in the feed RDF also decompose to form hydrochloric acid and salts. Pilot-scale slurty carbonization experiments extracted 82-94% of the feed RDF chlorine content as chloride salts. Higher carbonization temperatures and higher alkali additions to the feed slurry produced a higher chlorine extraction.« less

M2-F1 ejection seat test at South Edwards

NASA Technical Reports Server (NTRS)

1963-01-01

The M2-F1 was fitted with an ejection seat before the airtow flights began. The project selected the seat used in the T-37 as modified by the Weber Company to use a rocket rather than a ballistic charge for ejection. To test the ejection seat, the Flight Research Center's Dick Klein constructed a plywood mockup of the M2-F1's top deck and canopy. On the first firings, the test was unsuccessful, but on the final test the dummy in the seat landed safely. The M2-F1 ejection seat was later used in the two Lunar Landing Research Vehicles and the three Lunar Landing Training Vehicles. Three of them crashed, but in each case the pilot ejected from the vehicle successfully. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Solar photocatalytic treatment of trimethoprim in four environmental matrices at a pilot scale: transformation products and ecotoxicity evaluation.

PubMed

Michael, I; Hapeshi, E; Osorio, V; Perez, S; Petrovic, M; Zapata, A; Malato, S; Barceló, D; Fatta-Kassinos, D

2012-07-15

The pilot-scale solar degradation of trimethoprim (TMP) in different water matrices (demineralized water: DW, simulated natural freshwater: SW; simulated wastewater: SWW; and real effluent: RE) was investigated in this study. DOC removal was lower in the case of SW compared to DW, which can be attributed to the presence of inorganic anions which may act as scavengers of the HO·. Furthermore, the presence of organic carbon and higher salt content in SWW and RE led to lower mineralization per dose of hydrogen peroxide compared to DW and SW. Toxicity assays in SWW and RE were also performed indicating that toxicity is attributed to the compounds present in RE and their by-products formed during solar Fenton treatment and not to the intermediates formed by the oxidation of TMP. A large number of compounds generated by the photocatalytic transformation of TMP were identified by UPLC-QToF/MS. The degradation pathway revealed differences among the four matrices; however hydroxylation, demethylation and cleavage reactions were observed in all matrices. To the best of our knowledge this is the first time that TMP degradation products have been identified by adopting a solar Fenton process at a pilot-scale set-up, using four different aqueous matrices. Copyright © 2012 Elsevier B.V. All rights reserved.

Optimizing an F-16 Squadron Weekly Pilot Schedule for the Turkish Air Force

DTIC Science & Technology

2010-03-01

disrupted schedules are rescheduled , minimizing the total number of changes with respect to the previous schedule’s objective function. Output...producing rosters for a nursing staff in a large general hospital (Dowsland, 1998) and afterwards Aickelin and Dowsland use an Indirect Genetic...algorithm to improve the solutions of the nurse scheduling problem which is similar to the fighter squadron pilot scheduling problem (Aickelin and

Astronaut Alan Bean assisted with egressing command module after landing

NASA Technical Reports Server (NTRS)

1969-01-01

Astronaut Alan L. Bean, lunar module pilot, is assisted with egressing the Apollo 12 Command Module by a U.S. Navy underwater demolition team swimmer during recovery operations in the Pacific Ocean. Already in the life raft are Astronauts Charles Conrad Jr., commander; and Richard F. Gordon Jr., command module pilot. The Apollo 12 splashdown occured at 2:58 p.m., November 24, 1969 near American Samoa.

Apollo 7 crew arrives aboard recovery ship, U.S.S. Essex

NASA Image and Video Library

1968-10-15

S68-49744 (22 Oct. 1968) --- The Apollo 7 crew is welcomed aboard the USS Essex, the prime recovery ship for the mission. Left to right, are astronauts Walter M. Schirra Jr., commander; Donn F. Eisele, command module pilot; and Walter Cunningham, lunar module pilot. In left background is Dr. Donald E. Stullken, NASA Recovery Team Leader from the Manned Spacecraft Center's (MSC) Landing and Recovery Division.

Apollo 7 crew post-flight

NASA Image and Video Library

1968-10-28

S68-52542 (22 Oct. 1968) --- The Apollo 7 crew arrives aboard the USS Essex, the prime recovery ship for the mission. Left to right, are astronauts Walter M. Schirra Jr., commander; Donn F. Eisele, command module pilot; Walter Cunningham, lunar module pilot; and Dr. Donald E. Stullken, NASA Recovery Team Leader from the Manned Spacecraft Center's (MSC) Landing and Recovery Division. The crew is pausing in the doorway of the recovery helicopter.

Apollo 12 crewmembers shown in Apollo Lunar Module Mission Simulator

NASA Image and Video Library

1969-11-04

S69-56699 (22 Oct. 1969) --- Astronauts Charles Conrad Jr. (left), Apollo 12 commander; and Alan L. Bean, lunar module pilot, are shown in the Apollo Lunar Module Mission Simulator during simulator training at the Kennedy Space Center (KSC). Apollo 12 will be the National Aeronautics and Space Administration's (NASA) second lunar landing mission. The third Apollo 12 crewmember will be astronaut Richard F. Gordon Jr., command module pilot.

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

Autogenic-feedback training as a treatment for airsickness in high-performance military aircraft: Two case studies

NASA Technical Reports Server (NTRS)

Cowings, Patricia S.; Toscano, William B.; Miller, Neal E.; Reynoso, Samuel

1994-01-01

The purpose of this paper is to present a detailed description of the physiological and performance responses of two military pilots undergoing a treatment for motion sickness. The treatment used, Autogenic-Feedback Training (AFT), is an operant conditioning procedure where subjects are taught to control several of their autonomic responses and thereby suppress their motion sickness symptoms. Two male, active duty military pilots (U.S. Navy and U. S. Marine Corps), ages 30 and 35, were each given twelve 30-minute training sessions. The primary criterion for success of training was the subject's ability to tolerate rotating chair motion sickness tests for progressively longer periods of time and at higher rotational velocities. A standardized diagnostic scale was used during motion sickness to assess changes in the subject's perceived malaise. Physiological data were obtained from one pilot during tactical maneuvers in an F-18 aircraft after completion of his training. A significant increase in tolerance to laboratory-induced motion sickness tests and a reduction in autonomic nervous system (ANS) response variability was observed for both subjects after training. Both pilots were successful in applying AFT for controlling their airsickness during subsequent qualification tests on F-18 and T-38 aircraft and were returned to active duty flight status.

27 CFR 21.54 - Formula No. 27-B.

Code of Federal Regulations, 2012 CFR

2012-04-01

... gallon of lavender oil, N.F., and 100 pounds of green soap, U.S.P. Note. The requirements of this formula may be met by adding 1 gallon of lavender oil, N.F., and 66.5 pounds of U.S.P. quality soap... other biocides. (2) Miscellaneous uses: 812.Product development and pilot plant uses (own use only). ...

27 CFR 21.54 - Formula No. 27-B.

Code of Federal Regulations, 2011 CFR

2011-04-01

... gallon of lavender oil, N.F., and 100 pounds of green soap, U.S.P. Note. The requirements of this formula may be met by adding 1 gallon of lavender oil, N.F., and 66.5 pounds of U.S.P. quality soap... other biocides. (2) Miscellaneous uses: 812.Product development and pilot plant uses (own use only). ...

F-100A on ramp

NASA Technical Reports Server (NTRS)

1957-01-01

North American F-100A Super Sabre on the ramp near the NACA High-Speed Flight Station in 1957. Some airplane characteristics are: Fuselage length, feet 45.64 Wing span, feet Original wing 36.58 Extended wing 38.58 Power Plant: Pratt & Whitney J57-P7 turbojet engine with afterburner Airplane weight, pounds: Basic (without fuel, oil, water, pilot) 19,662

Flight Testing the X-36: The Test Pilots Perspective

NASA Technical Reports Server (NTRS)

Walker, Laurence A.

1997-01-01

The X-36 is a 28% scale, remotely piloted research aircraft, designed to demonstrate tailless fighter agility. Powered by a modified Williams International F-112 jet engine, the X-36 uses thrust vectoring and a fly-by-wire control system. Although too small for an onboard pilot, a full-sized remote cockpit was designed to virtually place the test pilot into the aircraft using a variety of innovative techniques. To date, 22 flights have been flown, successfully completing the second phase of testing. Handling qualities have been matching predictions; the test operation is flown similarly to that for full sized manned aircraft. All takeoffs, test maneuvers and landings are flown by the test pilot, affording a greater degree of flexibility and the ability to handle the inevitable unknowns which may occur during highly experimental test programs. The cockpit environment, cues, and display techniques used in this effort have proven to enhance the 'virtual' test pilot's awareness and have helped ensure a successful RPV test program.

Altered spinal cord activity during sexual stimulation in women with SCI: a pilot fMRI study.

PubMed

Alexander, Marcalee; Kozyrev, Natalie; Figley, Chase R; Richards, J Scott

2017-01-01

The objective of this study was to assess the feasibility of the use of functional magnetic resonance imaging (fMRI) to evaluate the spinal activation during sexual response of the thoracic, lumbar and sacral spinal cord. This is a laboratory-based pilot study in human females at a University-based medical center in the United States. In three healthy spinal cord injury (SCI) females, spinal cord activations during sexual audiovisual stimulation (alone), genital self-stimulation (alone) and simultaneous audiovisual and genital self-stimulation (combined) were assessed and then compared with each subjects' remaining sensory and motor function. Spinal fMRI responses of the intermediolateral columns were found during audiovisual stimulation in both subjects with incomplete injuries, but they were not observed in the subject with a complete injury. Moreover, sacral responses to combined stimulation differed greatly between the subjects with complete and incomplete injuries. These results not only provide the first in vivo documentation of spinal fMRI responses associated with sexual arousal in women with SCIs, but also suggest that spinal cord fMRI is capable of distinguishing between injury subtypes. Therefore, although there are certain limitations associated with fMRI during sexual stimulation (for example, movement artifacts, an artificially controlled environment and so), these findings demonstrate the potential utility of incorporating spinal cord fMRI in future research to evaluate the impact of specific patterns of SCI on sexual responses and/or the effects of treatment.

Fighter pilots' heart rate, heart rate variation and performance during an instrument flight rules proficiency test.

PubMed

Mansikka, Heikki; Virtanen, Kai; Harris, Don; Simola, Petteri

2016-09-01

Increased task demand will increase the pilot mental workload (PMWL). When PMWL is increased, mental overload may occur resulting in degraded performance. During pilots' instrument flight rules (IFR) proficiency test, PMWL is typically not measured. Therefore, little is known about workload during the proficiency test and pilots' potential to cope with higher task demands than those experienced during the test. In this study, fighter pilots' performance and PMWL was measured during a real IFR proficiency test in an F/A-18 simulator. PMWL was measured using heart rate (HR) and heart rate variation (HRV). Performance was rated using Finnish Air Force's official rating scales. Results indicated that HR and HRV differentiate varying task demands in situations where variations in performance are insignificant. It was concluded that during a proficiency test, PMWL should be measured together with the task performance measurement. Copyright © 2016 Elsevier Ltd. All rights reserved.

Assessment of the unattached fraction of indoor radon progeny and its contribution to dose: a pilot study in China.

PubMed

Guo, Qiuju; Zhang, Lei; Guo, Lu

2012-12-01

The unattached fraction of radon progeny (f(p)) is one of the most important factors for accurate evaluation of the effective dose from a unit of radon exposure, and it may vary greatly in different environments. For precise evaluation of the indoor radon exposure dose and the influence of unattached radon progeny, a pilot survey of f(p) in different environments was carried out in China with a portable and integrating monitor. The dose conversion factors for radon progeny are calculated with LUDEP(®) code, and the dose contributions from the unattached and the attached radon progenies were simultaneously evaluated based on the results of field measurements. The results show that even though the concentrations of radon progeny vary significantly among different indoor environments, the variations of f(p) seem relatively small (9.3-16.9%). The dose contribution from unattached radon progeny is generally larger (30.2-46.2%) in an indoor environment.

KSC-08pd3552

NASA Image and Video Library

2008-11-06

CAPE CANAVERAL, Fla. – At the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida, the U.S. Navy's Blue Angel pilots and support team are greeted by (from right) Special Operations Director Joe Dowdy, External Relations Director Lisa Malone, External Relations Acting Deputy Director Cheryl Hurst and Pam Steele, chief of the Public Services Division at Kennedy. The Blue Angels will perform at the Kennedy Space Center Visitor Complex Space and Air Show Nov. 8-9. The Navy's elite flight demonstration squadron will take to the skies in military aircraft demonstrations by the F-16 Fighting Falcon and F/A-18 Super Hornet jets for the second annual Space & Air Show at Kennedy. This year’s show brings together the best in military aircraft, coupled with precision pilots and veteran astronauts to celebrate spaceflight and aviation. The event includes military aircraft demonstrations by the F-16 Fighting Falcon and a water rescue demonstration by the 920th Rescue Wing. Photo credit: NASA/Kim Shiflett

Flight Test Results on the Stability and Control of the F-15B Quiet Spike Aircraft

NASA Technical Reports Server (NTRS)

Moua, Cheng; McWherter, Shaun H.; Cox, Timothy H.; Gera, Joseph

2007-01-01

The Quiet Spike (QS) flight research program was an aerodynamic and structural proof-of-concept of a telescoping sonic-boom suppressing nose boom on an F-15 B aircraft. The program goal was to collect flight data for model validation up to 1.8 Mach. The primary test philosophy was maintaining safety of flight. In the area of stability and controls the primary concerns were to assess the potential destabilizing effect of the spike on the stability, controllability, and handling qualities of the aircraft and to ensure adequate stability margins across the entire QS flight envelop. This paper reports on the stability and control methods used for flight envelope clearance and flight test results of the F-15B Quiet Spike. Also discussed are the flight test approach, the criteria to proceed to the next flight condition, brief pilot commentary on typical piloting tasks, approach and landing, and refueling task, and air data sensitivity to the flight control system.

M2-F1 in flight

NASA Technical Reports Server (NTRS)

1965-01-01

The M2-F1 Lifting Body is seen here under tow, high above Rogers Dry Lake near the Flight Research Center (later redesignated the Dryden Flight Research Center), Edwards, California. R. Dale Reed effectively advocated the project with the support of NASA research pilot Milt Thompson. Together, they gained the support of Flight Research Center Director Paul Bikle. After a six-month feasibility study, Bikle gave approval in the fall of 1962 for the M2-F1 to be built. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Flight Research Center management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. These initial tests produced enough flight data about the M2-F1 to proceed with flights behind a NASA C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight research vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Association of aircraft noise stress to periodontal disease in aircrew members.

PubMed

Haskell, B S

1975-08-01

A review of the literature reveals a multitude of effects that noise may contribute to periodontal disease, including cardiovascular disease, angiospasm of peripheral vessels, hypertension, and an increase in inflammatory cells with concurrent inhibition of healing. Three groups of 25 men were selected from the Pennsylvania Air National Guard for study. Group 1 consisted of F-102 jet fighter pilots; Group 2, pilots and crew of a four-engine, propeller-driven C-121 aircraft; and Group 3, enlisted men not exposed to aircraft noise, as a control. The degree of alveolar, intraceptal bone loss for each subject was measured from full-mouth radiographs of all groups. The greatest amount of bone loss occurred in crew members of propeller-driven aircraft. Jet pilots had considerably less bone loss while the average number of millimeters of bone lost per tooth revealed a difference between the three groups to the 0.01 significance level (F=24.7). The data suggests there is a degree of alveolar bone loss over a period of years associated with exposure to propeller aircraft noise and vibration, and negligible loss for jet aircraft noise.

Scaled Composites' Proteus aircraft and an F/A-18 Hornet from NASA's Dryden Flight Research Center d

NASA Technical Reports Server (NTRS)

2002-01-01

Scaled Composites' Proteus aircraft and an F/A-18 Hornet from NASA's Dryden Flight Research Center during a low-level flyby at Las Cruces Airport in New Mexico. The unique Proteus aircraft served as a test bed for NASA-sponsored flight tests designed to validate collision-avoidance technologies proposed for uninhabited aircraft. The tests, flown over southern New Mexico in March, 2002, used the Proteus as a surrogate uninhabited aerial vehicle (UAV) while three other aircraft flew toward the Proteus from various angles on simulated collision courses. Radio-based 'detect, see and avoid' equipment on the Proteus successfully detected the other aircraft and relayed that information to a remote pilot on the ground at Las Cruces Airport. The pilot then transmitted commands to the Proteus to maneuver it away from the potential collisions. The flight demonstration, sponsored by NASA Dryden Flight Research Center, New Mexico State University, Scaled Composites, the U.S. Navy and Modern Technology Solutions, Inc., were intended to demonstrate that UAVs can be flown safely and compatibly in the same skies as piloted aircraft.

Absorbing and Developing Qualified Fighter Pilots. The Role of the Advanced Simulator

DTIC Science & Technology

2007-01-01

This document and trademark(s) contained herein are protected by law as indicated in a notice appearing later in this work . This electronic...NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) RAND Corporation,1776 Main Street,Santa Monica,CA,90401-3208 8...should be available to all pilots working with given a mission design series. Funding for fielding new systems, providing ongoing essential software

Absorbing and Developing Qualified Fighter Pilots. The Role of the Advanced Simulator

DTIC Science & Technology

2007-01-01

This document and trademark(s) contained herein are protected by law as indicated in a notice appearing later in this work . This electronic...NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Rand Corporation...be available to all pilots working with given a mission design series. Funding for fielding new systems, providing ongoing essential software

FY2017 National Defense Authorization Act: Selected Military Personnel Issues

DTIC Science & Technology

2017-01-23

Report RL31664, The Military Survivor Benefit Plan: A Description of Its Provisions, by David F. Burrelli. 13Congressional Budget Office, Cost Estimate...P.L. 114-328 No provision Sec. 702 would modify cost - sharing amounts for the TRICARE pharmacy benefits program for years 2017 through 2025. After...prescription drug acquisition cost parity in the TRICARE pharmacy benefits program. DOD (90 days after pilot program completion) Sec. 744 Pilot program

Left to right, astronauts John H. Casper, mission commander, and Curtis L. Brown, Jr., pilot, get

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 TRAINING VIEW --- Left to right, astronauts John H. Casper, mission commander, and Curtis L. Brown, Jr., pilot, get help with the final touches of suit donning during emergency bailout training for STS-77 crew members in the Johnson Space Centers (JSC) Weightless Environment Training Facility (WET-F). Casper and Brown will join four other astronauts for nine days aboard the Space Shuttle Endeavour next month.

Apollo 12 Mission image - Close-up view of the Solar Wind Panel

NASA Image and Video Library

1969-11-19

AS12-47-6898 (19 Nov. 1969) --- A close-up view of the Solar Wind Composition device. Astronaut Alan L. Bean, lunar module pilot, took this photograph, after having deployed the device. Astronauts Charles Conrad Jr., commander, and Bean descended in the Apollo 12 Lunar Module (LM) to explore the moon, while astronaut Richard F. Gordon Jr., command module pilot, remained in lunar orbit with the Command and Service Modules (CSM).

Apollo 12 Mission image - View of lunar surface mound

NASA Image and Video Library

1969-11-19

AS12-46-6825 (19 Nov. 1969) --- Close-up view of a lunar rock, small crater, and lunar mound as photographed during the Apollo 12 extravehicular activity (EVA). Astronaut Richard F. Gordon Jr., command module pilot, remained with the Apollo 12 Command and Service Modules (CSM) in lunar orbit while astronauts Charles Conrad Jr., commander, and Alan L. Bean, lunar module pilot, descended in the Lunar Module (LM) to explore the moon.

The Effects of System and Environmental Factors Upon Experienced Pilot Performance in the Advanced Simulator for Pilot Training

DTIC Science & Technology

1977-04-01

System by System Variable Interactions Across All Maneuvers ... .......... 23 11 Field of View by Motion Interaction Cell Means for Takeoff...23 12 Motion by Field :f View Interaction Cell Means for GCA ..... ................. 24 13 Motion by FOV Interaction Mc--n Ratings for the...GCA and Takeoff Maneuvers ... ....... 24 14 Motion by G.Seat Interaction Cell Means for Takeoff ...... ................... 25 15 Motion by G.Seat

NACA/NASA test pilot Stanley P. Butchart

NASA Technical Reports Server (NTRS)

1954-01-01

Stanley P. Butchart joined the National Advisory Committee for Aeronautics' High-Speed Flight Research Station on May 10, 1951. Stan was the fourth research pilot hired at the Station affording him the opportunity to fly the early research aircraft. Stan began a flying career while attending Junior College. He received primary and secondary civilian pilot training, enlisting in the U.S. Navy in July 1942. Stan took his Navy air training at Corpus Christi, Texas. Upon completion of training he was assigned to a torpedo-bomber Air Group, VT-51, flying Grumman-General Motors TBM Avenger, a torpedo-bomber, from the carrier San Jacinto in the South Pacific. When World War II ended, Stan was released from active duty as a Navy Lieutenant, with a Distinguished Flying Cross and a Presidential Unit Citation among his service medals. Butchart elected to stay in the Naval Reserve group and flew for an additional 5 years while he attended the University of Washington. By 1950, Stan had earned bachelor degrees in aeronautical engineering and mechanical engineering. After graduation he went to work for Boeing Aircraft as a junior design engineer and was assigned to the B-47 body group. In May 1951, he arrived at the NACA facility to start a career as a research pilot. Stan flew the Douglas D-558-I #3 (12 flights, first on October 19, 1951), the Douglas D-558-II #3 (2 pilot check-out flights, first on June 26, 1953), Northrop X-4 (4 flights, first on May 27, 1952), Bell X-5 (13 flights, first in early December 1952). Other aircraft flown on research projects were the Boeing KC-135 Stratotanker, Convair CV-990, Boeing B-52-003, Boeing B-747, North American F-100A, Convair F-102, Piper PA-30 Twin Comanche, General Dynamics F-111, Boeing B-720, Convair CV-880, and the Boeing B-47 Stratojet, his favorite. he also flew many other aircraft. Stan did nearly all of the big airplane work at the Center. The biggest work load was flying the Boeing B-29 Stratofortress (Navy designation: P2B). At this time the pilot of the aircraft was the one in charge. It was the pilot who called for the chase planes before drop time, then for the fire trucks to be in position, and he counted down for the launch of the experimental aircraft after making sure everything and everyone was `ready.' The P2B was used in the launching of the D-558s while the B-29 carried the X-1s to altitude for drops. Stan was pilot of the P2B for 1 drop of the D-558-II #1 (1951 - 1954), 63 drops of the D-558-II #2 (1951 - 1956), and 38 drops of the D-558-II #3 (1951 - 1956). As pilot of the B-29 Stan flew for 1 drop of the Bell X-1A (1955), 13 drops of the Bell X-1B (1956-1958) and 22 drops of the X-1E (1955 - 1958). During the lifting body tow tests Stan was pilot of the R4D that towed the M2-F1 to altitude for release. He made 14 tows in 1966. On June 13, 1966, Stanley P. Butchart became the Chief Pilot at the National Aeronautics and Space Administrations' Flight Research Center and a few weeks later was named Acting Director of Flight Operations. There were 6 pilots assigned to the flight office at this time. On December 10, 1966, Stan became Chief of Flight Operations a position he held until his retirement on February 27, 1976. Stan authored several reports and presented research papers. He is a charter member of the Society of Experimental Test Pilots that had a membership of 65 in 1955, when chartered. Stan was elected to be a Fellow and had the honor of being the President in 1980. Butchart was presented the NACA Exceptional Service Medal for his decisions and actions in the X-1A explosion while attached to the B-29 aircraft on August 8, 1955.

Lessons from a One-to-One Laptop Pilot

ERIC Educational Resources Information Center

Peterson, Lana; Scharber, Cassandra

2017-01-01

The purpose of this study was to document the process one district used to design, develop, and implement a one-to-one pilot at its high school as part of its broader commitment to contemporary learning. Specifically, this qualitative case study (a) outlines the process of the laptop pilot, (b) describes the pilot implementation experience for…

Transferring cognitive tasks between brain imaging modalities: implications for task design and results interpretation in FMRI studies.

PubMed

Warbrick, Tracy; Reske, Martina; Shah, N Jon

2014-09-22

As cognitive neuroscience methods develop, established experimental tasks are used with emerging brain imaging modalities. Here transferring a paradigm (the visual oddball task) with a long history of behavioral and electroencephalography (EEG) experiments to a functional magnetic resonance imaging (fMRI) experiment is considered. The aims of this paper are to briefly describe fMRI and when its use is appropriate in cognitive neuroscience; illustrate how task design can influence the results of an fMRI experiment, particularly when that task is borrowed from another imaging modality; explain the practical aspects of performing an fMRI experiment. It is demonstrated that manipulating the task demands in the visual oddball task results in different patterns of blood oxygen level dependent (BOLD) activation. The nature of the fMRI BOLD measure means that many brain regions are found to be active in a particular task. Determining the functions of these areas of activation is very much dependent on task design and analysis. The complex nature of many fMRI tasks means that the details of the task and its requirements need careful consideration when interpreting data. The data show that this is particularly important in those tasks relying on a motor response as well as cognitive elements and that covert and overt responses should be considered where possible. Furthermore, the data show that transferring an EEG paradigm to an fMRI experiment needs careful consideration and it cannot be assumed that the same paradigm will work equally well across imaging modalities. It is therefore recommended that the design of an fMRI study is pilot tested behaviorally to establish the effects of interest and then pilot tested in the fMRI environment to ensure appropriate design, implementation and analysis for the effects of interest.

Changing the Introduction to Fighter Fundamentals Course for 21st Century F-15C Pilots

DTIC Science & Technology

2016-01-01

IFF model based on the success the USAF has enjoyed in establishing Air Superiority. There is no argument the United States has enjoyed the blanket ...dangerous place and so is the air superiority domain. Our country has gone to great lengths procuring new advanced weapons such as the F-22A and...F-35A, meanwhile updating older aircraft with advanced technology to ensure air dominance.9 So have her near peer adversaries, such as Russia and

M2-F1 in flight over lakebed on tow line

NASA Image and Video Library

1963-08-16

After initial ground-tow flights of the M2-F1 using the Pontiac as a tow vehicle, the way was clear to make air tows behind a C-47. The first air tow took place on 16 August 1963. Pilot Milt Thompson found that the M2-F1 flew well, with good control. This first flight lasted less than two minutes from tow-line release to touchdown. The descent rate was 4,000 feet per minute.

KSC-08pd3599

NASA Image and Video Library

2008-11-08

CAPE CANAVERAL, Fla. – An F-104G Starfighter races through the sky over NASA's Kennedy Space Center in Florida during the Kennedy Space Center Visitor Complex Space and Air Show Nov. 8-9. This year’s show brought together the best in military aircraft, such as the F/A-18 Super Hornet and F-16 Fighting Falcon, coupled with precision pilots and veteran astronauts to celebrate spaceflight and aviation. The event included a water rescue demonstration by the 920th Rescue Wing. Photo credit: NASA/Kim Shiflett

HL-10 in flight over lakebed

NASA Technical Reports Server (NTRS)

1969-01-01

The HL-10 Lifting Body is seen here in flight over Rogers Dry lakebed. Like the other lifting bodies, the HL-10 made a steep descent toward the lakebed, followed by a high-speed landing. This was due to the vehicle's low lift-over-drag ratio. The first 11 flights of the HL-10 were unpowered, flown to check the vehicle's handling and stability before rocket-powered flights began using the XLR-11 rocket engine. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

Pilot Ed Lewis with T-34C aircraft on ramp

NASA Image and Video Library

1998-03-04

NASA pilot Ed Lewis with the T-34C aircraft on the Dryden Flight Research Center Ramp. The aircraft was previously used at the Lewis Research Center in propulsion experiments involving turboprop engines, and was used as a chase aircraft at Dryden for smaller and slower research projects. Chase aircraft accompany research flights for photography and video purposes, and also as support for safety and research. At Dryden, the T-34 is used mainly for smaller remotely piloted vehicles which fly slower than NASA's F-18's, used for larger scale projects. This aircraft was returned to the U.S. Navy in May of 2002.

19 CFR 122.22 - Electronic manifest requirement for all individuals onboard private aircraft arriving in and...

Code of Federal Regulations, 2012 CFR

2012-04-01

... section. Pilot. “Pilot” means the individual(s) responsible for operation of an aircraft while in flight...: (i) Full name (last, first, and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M..., and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M=male); (iv) Citizenship; (v...

19 CFR 122.22 - Electronic manifest requirement for all individuals onboard private aircraft arriving in and...

Code of Federal Regulations, 2011 CFR

2011-04-01

... section. Pilot. “Pilot” means the individual(s) responsible for operation of an aircraft while in flight...: (i) Full name (last, first, and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M..., and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M=male); (iv) Citizenship; (v...

19 CFR 122.22 - Electronic manifest requirement for all individuals onboard private aircraft arriving in and...

Code of Federal Regulations, 2013 CFR

2013-04-01

... section. Pilot. “Pilot” means the individual(s) responsible for operation of an aircraft while in flight...: (i) Full name (last, first, and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M..., and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M=male); (iv) Citizenship; (v...

19 CFR 122.22 - Electronic manifest requirement for all individuals onboard private aircraft arriving in and...

Code of Federal Regulations, 2014 CFR

2014-04-01

... section. Pilot. “Pilot” means the individual(s) responsible for operation of an aircraft while in flight...: (i) Full name (last, first, and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M..., and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M=male); (iv) Citizenship; (v...

19 CFR 122.22 - Electronic manifest requirement for all individuals onboard private aircraft arriving in and...

Code of Federal Regulations, 2010 CFR

2010-04-01

... section. Pilot. “Pilot” means the individual(s) responsible for operation of an aircraft while in flight...: (i) Full name (last, first, and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M..., and, if available, middle); (ii) Date of birth; (iii) Gender (F=female; M=male); (iv) Citizenship; (v...

Applications of Simulator Freeze to Carrier Guideslope Tracking Instruction. Cooperative Study Series. Final Report, May 1, 1980-August 31, 1981.

ERIC Educational Resources Information Center

Hughes, R. G.; And Others

Twenty-five experienced F-4 and F-16 Air Force pilots were instructed in carrier landings in the Visual Technology Research Simulator (VTRS). The training was conducted under three instructional conditions, two of which employed the simulator's "freeze" feature. Additionally, two methods of defining errors for carrier glideslope tracking…

The Plain Dealer High School Newspaper Workshop Program. John F. Kennedy and West Technical High Schools, 1994-1995.

ERIC Educational Resources Information Center

Cleveland Public Schools, OH.

The Plain Dealer High School Newspaper Workshop was a pilot program created to introduce minority high school students (although not limited to minority students) to career opportunities in the newspaper business. Forty-four students from the Cleveland Public Schools' John F. Kennedy and West Technical High School participated in the 9-week…

Monitoring early response to taxane therapy in advanced breast cancer with circulating tumor cells and [(18)F] 3´-deoxy-3´-fluorothymidine PET: a pilot study.

PubMed

Contractor, Kaiyumars; Aboagye, Eric O; Jacob, Jimmy; Challapalli, Amarnath; Coombes, R Charles; Stebbing, Justin

2012-04-01

Early markers of response to chemotherapy, measured by blood markers and imaging, may ultimately lead to tailored therapies that avoid cumulative toxicity. We performed a small pilot study to compare early changes in levels of circulatory tumor cells (CTCs) with changes in tumor proliferation, using metabolic imaging with [(18)F] 3´-deoxy-3´-fluorothymidine PET (FLT-PET) in women with advanced breast cancer, before and during docetaxel therapy. In those individuals in whom we could detect CTCs, a decrease in CTC count correlated with a decrease in FLT-PET signal, within 2 weeks. Combined, these two technologies are likely to provide a powerful, albeit expensive, tool to assess immediate responses to therapy.

M2-F1 in flight

NASA Technical Reports Server (NTRS)

1964-01-01

The M2-F1 Lifting Body is seen here under tow by an unseen C-47 at the NASA Flight Research Center (later redesignated the Dryden Flight Research Center), Edwards, California. The low-cost vehicle was the first piloted lifting body to be test flown. The lifting-body concept originated in the mid-1950s at the National Advisory Committee for Aeronautics' Ames Aeronautical Laboratory, Mountain View California. By February 1962, a series of possible shapes had been developed, and R. Dale Reed was working to gain support for a research vehicle. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. These initial tests produced enough flight data about the M2-F1 to proceed with flights behind a NASA C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting-body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight research vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Cognitive models of pilot categorization and prioritization of flight-deck information

NASA Technical Reports Server (NTRS)

Jonsson, Jon E.; Ricks, Wendell R.

1995-01-01

In the past decade, automated systems on modern commercial flight decks have increased dramatically. Pilots now regularly interact and share tasks with these systems. This interaction has led human factors research to direct more attention to the pilot's cognitive processing and mental model of the information flow occurring on the flight deck. The experiment reported herein investigated how pilots mentally represent and process information typically available during flight. Fifty-two commercial pilots participated in tasks that required them to provide similarity ratings for pairs of flight-deck information and to prioritize this information under two contextual conditions. Pilots processed the information along three cognitive dimensions. These dimensions included the flight function and the flight action that the information supported and how frequently pilots refer to the information. Pilots classified the information as aviation, navigation, communications, or systems administration information. Prioritization results indicated a high degree of consensus among pilots, while scaling results revealed two dimensions along which information is prioritized. Pilot cognitive workload for flight-deck tasks and the potential for using these findings to operationalize cognitive metrics are evaluated. Such measures may be useful additions for flight-deck human performance evaluation.

Frank Batteas

NASA Image and Video Library

1999-01-04

Frank Batteas is a research test pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, California. He is currently a project pilot for the F/A-18 and C-17 flight research projects. In addition, his flying duties include operation of the DC-8 Flying Laboratory in the Airborne Science program, and piloting the B-52B launch aircraft, the King Air, and the T-34C support aircraft. Batteas has accumulated more than 4,700 hours of military and civilian flight experience in more than 40 different aircraft types. Batteas came to NASA Dryden in April 1998, following a career in the U.S. Air Force. His last assignment was at Wright-Patterson Air Force Base, Dayton, Ohio, where Lieutenant Colonel Batteas led the B-2 Systems Test and Evaluation efforts for a two-year period. Batteas graduated from Class 88A of the Air Force Test Pilot School, Edwards Air Force Base, California, in December 1988. He served more than five years as a test pilot for the Air Force's newest airlifter, the C-17, involved in nearly every phase of testing from flutter and high angle-of-attack tests to airdrop and air refueling envelope expansion. In the process, he achieved several C-17 firsts including the first day and night aerial refuelings, the first flight over the North Pole, and a payload-to-altitude world aviation record. As a KC-135 test pilot, he also was involved in aerial refueling certification tests on a number of other Air Force aircraft. Batteas received his commission as a second lieutenant in the U. S. Air Force through the Reserve Officer Training Corps and served initially as an engineer working on the Peacekeeper and Minuteman missile programs at the Ballistic Missile Office, Norton Air Force Base, Calif. After attending pilot training at Williams Air Force Base, Phoenix, Ariz., he flew operational flights in the KC-135 tanker aircraft and then was assigned to research flying at the 4950th Test Wing, Wright-Patterson. He flew extensively modified C-135

18F-FLT PET/CT in the Evaluation of Pheochromocytomas and Paragangliomas: A Pilot Study.

PubMed

Blanchet, Elise M; Taieb, David; Millo, Corina; Martucci, Victoria; Chen, Clara C; Merino, Maria; Herscovitch, Peter; Pacak, Karel

2015-12-01

(18)F-FDG PET/CT has been proven to be a highly sensitive method for pheochromocytomas/paragangliomas (PHEOs/PGLs) associated with succinate dehydrogenase (SDH) mutations. This finding has been attributed to altered tumor cell metabolism resulting from these mutations and does not provide additional prognostic information to genotype. Therefore, identification of new biomarkers for aggressiveness is needed. A high Ki-67 index was proposed to be an additional prognostic factor. This pilot study aimed to evaluate 3'-deoxy-3'-(18)F-fluorothymidine ((18)F-FLT) PET/CT, a PET proliferation tracer, as a potential imaging agent in a series of 12 PHEO/PGL patients with different genetic backgrounds, to compare (18)F-FLT uptake with (18)F-FDG PET/CT, and to evaluate classic factors of aggressiveness. Twelve patients (7 metastatic and 5 nonmetastatic) were prospectively evaluated with (18)F-FDG and (18)F-FLT and followed for at least 2 y after the initial imaging work-up. Uptake was assessed at a lesion level, visually and quantitatively by maximum standardized uptake values (SUVmax) for both tracers. (18)F-FLT uptake was compared with risk factors known to be linked with a poor prognosis in PGLs (SDHB-mutated status, lesion size, dopaminergic phenotype) and with (18)F-FDG uptake. In 12 patients, 77 lesions were assessed. All lesions had low (18)F-FLT uptake (median SUVmax, 2.25; range, 0.7-4.5). There was no apparent superiority of (18)F-FLT uptake in progressive lesions, and most of the lesions showed a mismatch, with high (18)F-FDG uptake (median SUVmax, 10.8; range, 1.1-79.0) contrasting with low (18)F-FLT uptake. This study suggests that PHEOs/PGLs-even those that progress-do not exhibit intense (18)F-FLT uptake. It provides the first in vivo demonstration that proliferation may not be a major determinant of (18)F-FDG uptake in these tumors. These findings provide new insight into the biologic behavior of PGL and suggest that antiproliferative agents may be suboptimal for treatment of these tumors. © 2015 by the Society of Nuclear Medicine and Molecular Imaging, Inc.

Detecting Pilot's Engagement Using fNIRS Connectivity Features in an Automated vs. Manual Landing Scenario

PubMed Central

Verdière, Kevin J.; Roy, Raphaëlle N.; Dehais, Frédéric

2018-01-01

Monitoring pilot's mental states is a relevant approach to mitigate human error and enhance human machine interaction. A promising brain imaging technique to perform such a continuous measure of human mental state under ecological settings is Functional Near-InfraRed Spectroscopy (fNIRS). However, to our knowledge no study has yet assessed the potential of fNIRS connectivity metrics as long as passive Brain Computer Interfaces (BCI) are concerned. Therefore, we designed an experimental scenario in a realistic simulator in which 12 pilots had to perform landings under two contrasted levels of engagement (manual vs. automated). The collected data were used to benchmark the performance of classical oxygenation features (i.e., Average, Peak, Variance, Skewness, Kurtosis, Area Under the Curve, and Slope) and connectivity features (i.e., Covariance, Pearson's, and Spearman's Correlation, Spectral Coherence, and Wavelet Coherence) to discriminate these two landing conditions. Classification performance was obtained by using a shrinkage Linear Discriminant Analysis (sLDA) and a stratified cross validation using each feature alone or by combining them. Our findings disclosed that the connectivity features performed significantly better than the classical concentration metrics with a higher accuracy for the wavelet coherence (average: 65.3/59.9 %, min: 45.3/45.0, max: 80.5/74.7 computed for HbO/HbR signals respectively). A maximum classification performance was obtained by combining the area under the curve with the wavelet coherence (average: 66.9/61.6 %, min: 57.3/44.8, max: 80.0/81.3 computed for HbO/HbR signals respectively). In a general manner all connectivity measures allowed an efficient classification when computed over HbO signals. Those promising results provide methodological cues for further implementation of fNIRS-based passive BCIs. PMID:29422841

An investigation into pilot and system response to critical in-flight events. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Rockwell, T. H.; Griffin, W. C.

1981-01-01

Critical in-flight events (CIFE) that threaten the aircraft were studied. The scope of the CIFE was described and defined with emphasis on characterizing event development, detection and assessment; pilot information requirements, sources, acquisition, and interpretation, pilot response options, decision processed, and decision implementation and event outcome. Detailed scenarios were developed for use in simulators and paper and pencil testing for developing relationships between pilot performance and background information as well as for an analysis of pilot reaction decision and feedback processes. Statistical relationships among pilot characteristics and observed responses to CIFE's were developed.

[Spanish validation of the Boston Carpal Tunnel Questionnaire].

PubMed

Oteo-Álvaro, Ángel; Marín, María T; Matas, José A; Vaquero, Javier

2016-03-18

To describe the process of cultural adaptation and validation of the Boston Carpal Tunnel Questionnaire (BCTQ) measuring symptom intensity, functional status and quality of life in carpal tunnel syndrome patients and to report the psychometric properties of this version. A 3 expert panel supervised the adaptation process. After translation, review and back-translation of the original instrument, a new Spanish version was obtained, which was administered to 2 patient samples: a pilot sample of 20 patients for assessing comprehension, and a 90 patient sample for assessing structural validity (factor analysis and reliability), construct validity and sensitivity to change. A re-test measurement was carried out in 21 patients. Follow-up was accomplished in 40 patients. The questionnaire was well accepted by all participants. Celling effect was observed for 3 items. Reliability was very good, internal consistency: αS=0.91 y αF=0.87; test-retest stability: rS=0.939 and rF=0.986. Both subscales fitted to a general dimension. Subscales correlated with dynamometer measurements (rS=0.77 and rF=0.75) and showed to be related to abnormal 2-point discrimination, muscle atrophy and electromyography deterioration level. Scores properly correlated with other validated instruments: Douleur Neuropatique 4 questions and Brief Pain Inventory. BCTQ demonstrated to be sensitive to clinical changes, with large effect sizes (dS=-3.3 and dF=-1.9). The Spanish version of the BCTQ shows good psychometric properties warranting its use in clinical settings. Copyright © 2015 Elsevier España, S.L.U. All rights reserved.

Research pilot Fred Haise

NASA Image and Video Library

1966-04-07

Fred W. Haise Jr. was a research pilot and an astronaut for the National Aeronautics and Space Administration from 1959 to 1979. He began flying at the Lewis Research Center in Cleveland, Ohio (today the Glenn Research Center), in 1959. He became a research pilot at the NASA Flight Research Center (FRC), Edwards, Calif., in 1963, serving NASA in that position for three years until being selected to be an astronaut in 1966 His best-known assignment at the FRC (later redesignated the Dryden Flight Research Center) was as a lifting body pilot. Shortly after flying the M2-F1 on a car tow to about 25 feet on April 22, 1966, he was assigned as an astronaut to the Johnson Space Center in Houston, Texas. While at the FRC he had also flown a variety of other research and support aircraft, including the variable-stability T-33A to simulate the M2-F2 heavyweight lifting body, some light aircraft including the Piper PA-30 to evaluate their handling qualities, the Apache helicopter, the Aero Commander, the Cessna 310, the Douglas F5D, the Lockheed F-104 and T-33, the Cessna T-37, and the Douglas C-47. After becoming an astronaut, Haise served as a backup crewmember for the Apollo 8, 11, and 16 missions. He flew on the aborted Apollo 13 lunar mission in 1970, spending 142 hours and 54 minutes in space before returning safely to Earth. In 1977, he was the commander of three free flights of the Space Shuttle prototype Enterprise when it flew its Approach and Landing Tests at Edwards Air Force Base, Calif. Meanwhile, from April 1973 to January 1976, Haise served as the Technical Assistant to the Manager of the Space Shuttle Orbiter Project. In 1979, he left NASA to become the Vice President for Space Programs with the Grumman Aerospace Corporation. He then served as President of Grumman Technical Services, an operating division of Northrop Grumman Corporation, from January 1992 until his retirement. Haise was born in Biloxi, Miss., on November 14, 1933. He underwent flight traini

APOLLO XII - ART CONCEPT - COMMAND MODULE

NASA Image and Video Library

1969-11-10

S69-58005 (10 Nov. 1969) --- An artist's concept of the Apollo 12 Command Module's (CM) interior, with the command module pilot at the controls. The Apollo 12 Lunar Module (LM) and a portion of the lunar surface are seen out of the window. Astronaut Richard F. Gordon Jr. will maneuver the Apollo 12 Command and Service Modules (CSM) in lunar orbit while astronauts Charles Conrad Jr., commander, and Alan L. Bean, lunar module pilot, explore the moon.

APOLLO XII CREW - WELCOME - USS HORNET - REAR ADMIRAL DONALD DAVID

NASA Image and Video Library

1969-11-24

S69-22876 (24 Nov. 1969) --- Rear Admiral Donald C. David, Commander, Manned Spacecraft Recovery Force, Pacific, welcomes the crew of the Apollo 12 lunar landing mission aboard the USS Hornet, prime recovery vessel for the mission. A color guard was also on hand for the welcoming ceremonies. Inside the Mobile Quarantine Facility (MQF) are (left to right) astronauts Charles Conrad Jr., commander; Richard F. Gordon Jr., command module pilot; and Alan L. Bean, lunar module pilot.

Astronaut Curtis L. Brown, Jr., pilot, gets helped with the final touches of suit donning during

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 TRAINING VIEW --- Astronaut Curtis L. Brown, Jr., pilot, gets helped with the final touches of suit donning during emergency bailout training for crew members in the Johnson Space Centers (JSC) Weightless Environment Training Facility (WET-F). Astronaut John H. Casper (in background), mission commander, awaits the actual training to begin. Brown and Casper will join four other astronauts for nine days aboard the Space Shuttle Endeavour next month.

Apollo 12 crewmembers shown in Apollo Lunar Module Mission Simulator

NASA Image and Video Library

1969-11-04

S69-56700 (22 Oct. 1969) --- A fish-eye lens view of astronauts Charles Conrad Jr. (on left), Apollo 12 commander, and Alan L. Bean, lunar module pilot, inside the Apollo Lunar Module Mission Simulator during simulator training at the Kennedy Space Center (KSC). Apollo 12 will be the National Aeronautics and Space Administration's (NASA) second lunar landing mission. The third Apollo 12 crewmember will be astronaut Richard F. Gordon Jr., command module pilot.

LAUNCH - APOLLO VII - KSC

NASA Image and Video Library

1968-10-11

S68-48666 (11 Oct. 1968) --- The Apollo 7/Saturn IB space vehicle is launched from the Kennedy Space Center's Launch Complex 34 at 11:03 a.m. (EDT), Oct. 11, 1968. Apollo 7 (Spacecraft 101/Saturn 205) is the first of several manned flights aimed at qualifying the spacecraft for the half-million-mile round trip to the moon. Aboard the Apollo spacecraft are astronauts Walter M. Schirra Jr., commander; Donn F. Eisele, command module pilot; and Walter Cunningham, lunar module pilot.

Reduction of dioxin emission by a multi-layer reactor with bead-shaped activated carbon in simulated gas stream and real flue gas of a sinter plant.

PubMed

Hung, Pao Chen; Lo, Wei Chiao; Chi, Kai Hsien; Chang, Shu Hao; Chang, Moo Been

2011-01-01

A laboratory-scale multi-layer system was developed for the adsorption of PCDD/Fs from gas streams at various operating conditions, including gas flow rate, operating temperature and water vapor content. Excellent PCDD/F removal efficiency (>99.99%) was achieved with the multi-layer design with bead-shaped activated carbons (BACs). The PCDD/F removal efficiency achieved with the first layer adsorption bed decreased as the gas flow rate was increased due to the decrease of the gas retention time. The PCDD/F concentrations measured at the outlet of the third layer adsorption bed were all lower than 0.1 ng I-TEQ Nm⁻³. The PCDD/Fs desorbed from BAC were mainly lowly chlorinated congeners and the PCDD/F outlet concentrations increased as the operating temperature was increased. In addition, the results of pilot-scale experiment (real flue gases of an iron ore sintering plant) indicated that as the gas flow rate was controlled at 15 slpm, the removal efficiencies of PCDD/F congeners achieved with the multi-layer reactor with BAC were better than that in higher gas flow rate condition (20 slpm). Overall, the lab-scale and pilot-scale experiments indicated that PCDD/F removal achieved by multi-layer reactor with BAC strongly depended on the flow rate of the gas stream to be treated. Copyright © 2010 Elsevier Ltd. All rights reserved.

Effect of fly ash on catalytic removal of gaseous dioxins over V{sub 2}O{sub 5}-WO{sub 3} catalyst of a sinter plant

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

Shu Hao Chang; Kai Hsien Chi; Chi Wei Young

2009-10-01

A PCDD/F (polychlorinated dibenzo-p-dioxin and dibenzofuran)-containing gas stream generating system was developed to investigate the efficiency and effectiveness of V{sub 2}O{sub 5}-WO{sub 3} catalyst for PCDD/F destruction. Catalytic decomposition of PCDD/Fs (simulated gas streams) was evaluated with lab-scale pelletized and plate-type catalyst based on V{sub 2}O{sub 5}-WO{sub 3}/TiO{sub 2} at controlled temperature, space velocity, and inlet PCDD/F concentration. Due to the lower porosity of the pelletized catalyst, PCDD/F destruction efficiencies reach 72.9-83.2% for different levels of inlet PCDD/F concentrations (1.08-3.04 ng-TEQ/Nm{sup 3}) of the gas stream (space velocity: 5000 h-1). As the surface area is increased from 287 m{sup 2}/m{supmore » 3} (plate-type A) to 550 m{sup 2}/m{sup 3} (plate-type B), the PCDD/F destruction achieved with plate-type catalyst increases from 76.0% to 85.3% at 320{sup o}C (space velocity: 5000 h{sup -1}). In addition, the results of pilot-scale experiment (real flue gases of a sinter plant) indicate that relatively lower PCDD/F destruction efficiencies (62.1-65.7%) were achieved with the plate-type B catalyst as the solid-phase PCDD/F and fly ash passed through the reactor (space velocity: 5000 h{sup -1}). Overall, the lab-scale and pilot-scale experiments indicate that PCDD/F destructions achieved with pelletized and plate-type catalysts strongly depend on the operating temperature of the catalyst. The results also indicate that the presence of fly ash lowers PCDD/F destruction due to significant PCDD/F formation via de novo synthesis at 320{sup o}C. 20 refs., 5 figs., 3 tabs.« less

The Airman and the State: An F-22 Pilot’s Perspective on Civil-Military Relations

DTIC Science & Technology

2010-02-18

often than not. President Truman fired General MacArthur for continuing 22 Ibid. 23 Russell F...theory, oversight mechanisms can include contract incentives, screening and selection, fire alarms, institutional checks, police patrols, and revising...right sort of agent enters into the contractual relationship. Fire alarms Use of outsiders to watch the agent and report on key outputs

Incentivizing Children's Fruit and Vegetable Consumption: Results of a United States Pilot Study of the "Food Dudes" Program

ERIC Educational Resources Information Center

Wengreen, Heidi J.; Madden, Gregory J.; Aguilar, Sheryl S.; Smits, Rochelle R.; Jones, Brooke A.

2013-01-01

Objective: Preliminary evaluation in the United States (US) of a school-based fruit and vegetable (F/V) intervention, known as the "Food Dudes" (FD) program, developed in the United Kingdom. Methods: Over 16 days (Phase 1), elementary-school children (n = 253) watched short videos featuring heroic peers (the FD) eating F/V and received a…

Collaborative Learning across Physical and Virtual Worlds: Factors Supporting and Constraining Learners in a Blended Reality Environment

ERIC Educational Resources Information Center

Bower, Matt; Lee, Mark J. W.; Dalgarno, Barney

2017-01-01

This article presents the outcomes of a pilot study investigating factors that supported and constrained collaborative learning in a blended reality environment. Pre-service teachers at an Australian university took part in a hybrid tutorial lesson involving a mixture of students who were co-located in the same face-to-face (F2F) classroom along…

Imaging Cellular Proliferation During Chemo-Radiotherapy: A Pilot Study of Serial {sup 18}F-FLT Positron Emission Tomography/Computed Tomography Imaging for Non-Small-Cell Lung Cancer

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

Everitt, Sarah, E-mail: Sarah.Everitt@petermac.or; Department of Medical Imaging and Radiation Sciences, Faculty of Medicine, Nursing and Health Sciences, Monash University, Clayton, Victoria; Hicks, Rodney J.

2009-11-15

Purpose: To establish whether {sup 18}F-3'-deoxy-3'-fluoro-L-thymidine ({sup 18}F-FLT) can monitor changes in cellular proliferation of non-small-cell lung cancer (NSCLC) during radical chemo-radiotherapy (chemo-RT). Methods and Materials: As part of a prospective pilot study, 5 patients with locally advanced NSCLC underwent serial {sup 18}F-FLT positron emission tomography (PET)/computed tomography (CT) scans during treatment. Baseline {sup 18}F-FLT PET/CT scans were compared with routine staging {sup 18}F-FDG PET/CT scans. Two on-treatment {sup 18}F-FLT scans were performed for each patient on Days 2, 8, 15 or 29, providing a range of time points for response assessment. Results: In all 5 patients, baseline lesional uptakemore » of {sup 18}F-FLT on PET/CT corresponded to staging {sup 18}F-FDG PET/CT abnormalities. {sup 18}F-FLT uptake in tumor was observed on five of nine (55%) on-treatment scans, on Days 2, 8 and 29, but not Day 15. A 'flare' of {sup 18}F-FLT uptake in the primary tumor of one case was observed after 2 Gy of radiation (1.22 x baseline). The remaining eight on-treatment scans demonstrated a mean reduction in {sup 18}F-FLT tumor uptake of 0.58 x baseline. A marked reduction of {sup 18}F-FLT uptake in irradiated bone marrow was observed for all cases. This reduction was observed even after only 2 Gy, and all patients demonstrated a complete absence of proliferating marrow after 10 Gy. Conclusions: This proof of concept study indicates that {sup 18}F-FLT uptake can monitor the distinctive biologic responses of epithelial cancers and highly radiosensitive normal tissue changes during radical chemo-RT. Further studies of {sup 18}F-FLT PET/CT imaging during therapy may suggest that this tracer is useful in developing response-adapted RT for NSCLC.« less

Acquired left bundle branch block in an asymptomatic fighter pilot: a case report.

PubMed

Newman, D G

1999-12-01

This report describes a case of acquired left bundle branch block (LBBB) in an asymptomatic F/A-18 fighter pilot of the Royal Australian Air Force. The previously fit and healthy pilot was found to have LBBB on routine electrocardiographic screening prior to his annual aircrew medical. He was completely asymptomatic, and the only potential etiological factor was a short-lived acute gastrointestinal infectious illness some 4 mo previously. The pilot was extensively investigated with the full range of available diagnostic procedures, including coronary angiography and cardiac biopsy. No cause was determined for his LBBB pattern, and he was assessed as having normal cardiovascular function. The aeromedical disposition of this aviator and the issues involved in determining fitness to fly in such a case are discussed. The importance of thorough clinical investigation and appropriate follow-up are highlighted.

Comparison of NASA-TLX scale, Modified Cooper-Harper scale and mean inter-beat interval as measures of pilot mental workload during simulated flight tasks.

PubMed

Mansikka, Heikki; Virtanen, Kai; Harris, Don

2018-04-30

The sensitivity of NASA-TLX scale, modified Cooper-Harper (MCH) scale and the mean inter-beat interval (IBI) of successive heart beats, as measures of pilot mental workload (MWL), were evaluated in a flight training device (FTD). Operational F/A-18C pilots flew instrument approaches with varying task loads. Pilots' performance, subjective MWL ratings and IBI were measured. Based on the pilots' performance, three performance categories were formed; high-, medium- and low-performance. Values of the subjective rating scales and IBI were compared between categories. It was found that all measures were able to differentiate most task conditions and there was a strong, positive correlation between NASA-TLX and MCH scale. An explicit link between IBI, NASA-TLX, MCH and performance was demonstrated. While NASA-TLX, MCH and IBI have all been previously used to measure MWL, this study is the first one to investigate their association in a modern FTD, using a realistic flying mission and operational pilots.

M2-F2 flight preparation and launch

NASA Technical Reports Server (NTRS)

1969-01-01

This movie clip runs about 27 seconds and shows the cockpit canopy close-out by the ground crew, the aircraft hanging from the NB-52B wing pylon, and the M2-F2 being dropped away from the mothership. A fleet of lifting bodies flown at the NASA Flight Research Center (FRC), Edwards, California, from 1963 to l975 demonstrated the ability of pilots to maneuver (in the atmosphere) and safely land a wingless vehicle. These lifting bodies were basically designed so they could fly back to Earth from space and be landed like an aircraft at a pre-determined site. They served as precursors of today's Space Shuttle, the X-33, and the X-38, providing technical and operational engineering data that shaped all three space vehicles. (In 1976 NASA renamed the FRC as the NASA Dryden Flight Research Center (DFRC) in honor of Hugh L. Dryden.) In 1962, FRC Director Paul Bikle approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1. Built by Gus Briegleb, a sailplane builder from El Mirage, California, it featured a plywood shell, placed over a tubular steel frame crafted at the FRC. Construction was completed in 1963. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA Ames Research Center and NASA and Langley Research Center -- the M2-F2 and the HL-10, both built by the Northrop Corporation, Los Angeles, California. The 'M' refers to 'manned' and 'F' refers to 'flight' version. 'HL' comes from 'horizontal landing' and '10' is for the tenth lifting body model to be investigated by Langley. The first flight of the M2-F2 -- which looked much like the M2-F1 -- occurred on July 12, 1966. Thompson was the pilot. By then, the same B-52 used to air launch the famed X-15 rocket research aircraft had been modified to also carry the lifting bodies into the air and Thompson was dropped from the B-52 wing pylon mount at an altitude of 45,000 feet on that maiden glide flight. On May 10, 1967, during the sixteenth glide flight leading up to powered flight, a landing accident severely damaged the vehicle and seriously injured the NASA pilot, Bruce Peterson. Following the mishap, the M2-F2 was redesigned with a center fin as the M2-F3, which flew from 1970 to 1972. The M2-F2 weighed 4,620 pounds without ballast, was roughly 22 feet long, and had a width of about 10 feet.

Utah Regional Differences in Respirator Use and Fit Testing among Pesticide Applicators.

PubMed

Pate, Michael L; Beard, F Richard; Hall, Kelsey

2017-01-26

The purpose of this study was to determine regional differences within Utah in response to piloting a mobile respirator training and fit assessment program for pesticide applicators. The objectives were to describe worker perceptions of respirator use and training experiences. Pilot trainings were offered in two southern counties and two northern counties of Utah. A total of 141 individuals completed the post-training questionnaire regarding use and fit testing experience with respirators as well as perceptions of the benefits to protecting respiratory health. The majority of respondents were male (95.7%, f = 112). The proportion of participants in the southern counties who had respirator training experience (61.0%, f = 25) was not significantly higher (2 = 3.763, df = 1, p = 0.05) than the proportion of participants in the northern counties (43.0%, f = 43). Three-fourths (73.5%, f = 72) of participants in the northern counties agreed that they expect to wear a respirator in dusty conditions, while two-thirds (61.0%, f = 25) of participants in the southern counties agreed that they expect to wear a respirator in dusty conditions. The results indicated that more training should be done to improve perceptions and beliefs about using respirators. A high priority for this population will be identification of comfortable respirator options as well as communicating the importance of proper fit testing. Copyright© by the American Society of Agricultural Engineers.

Utilization of geothermal heat in tropical fruit-drying process

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

Chen, B.H.; Lopez, L.P.; King, R.

1982-10-01

The power plant utilizes only the steam portion of the HGP-A well production. There are approximately 50,000 pounds per hour of 360/sup 0/F water produced (approximately 10 million Btu per hour) and the water is currently not used and is considered a waste. This tremendous resource could very well be used in applications such as food processing, food dehydration and other industrial processing that requires low-grade heat. One of the applications is examined, namely the drying of tropical fruits particularly the papaya. The papaya was chosen for the obvious reason that it is the biggest crop of all fruits producedmore » on the Big Island. A conceptual design of a pilot plant facility capable of processing 1000 pounds of raw papaya per day is included. This facility is designed to provide a geothermally heated dryer to dehydrate papayas or other tropical fruits available on an experimental basis to obtain data such as drying time, optimum drying temperature, etc.« less

The ATLAS PanDA Pilot in Operation

NASA Astrophysics Data System (ADS)

Nilsson, P.; Caballero, J.; De, K.; Maeno, T.; Stradling, A.; Wenaus, T.; ATLAS Collaboration

2011-12-01

The Production and Distributed Analysis system (PanDA) [1-2] was designed to meet ATLAS [3] requirements for a data-driven workload management system capable of operating at LHC data processing scale. Submitted jobs are executed on worker nodes by pilot jobs sent to the grid sites by pilot factories. This paper provides an overview of the PanDA pilot [4] system and presents major features added in light of recent operational experience, including multi-job processing, advanced job recovery for jobs with output storage failures, gLExec [5-6] based identity switching from the generic pilot to the actual user, and other security measures. The PanDA system serves all ATLAS distributed processing and is the primary system for distributed analysis; it is currently used at over 100 sites worldwide. We analyze the performance of the pilot system in processing real LHC data on the OSG [7], EGI [8] and Nordugrid [9-10] infrastructures used by ATLAS, and describe plans for its evolution.

27 CFR 21.70 - Formula No. 39-A.

Code of Federal Regulations, 2012 CFR

2012-04-01

.... Cinchonidine sulfate, N.F. IX. (b) Authorized uses. (1) As a solvent: 111.Hair and scalp preparations. 122.Toilet waters and colognes. 141.Shampoos. (2) Miscellaneous uses: 812.Product development and pilot plant...

27 CFR 21.70 - Formula No. 39-A.

Code of Federal Regulations, 2011 CFR

2011-04-01

.... Cinchonidine sulfate, N.F. IX. (b) Authorized uses. (1) As a solvent: 111.Hair and scalp preparations. 122.Toilet waters and colognes. 141.Shampoos. (2) Miscellaneous uses: 812.Product development and pilot plant...

27 CFR 21.70 - Formula No. 39-A.

Code of Federal Regulations, 2013 CFR

2013-04-01

.... Cinchonidine sulfate, N.F. IX. (b) Authorized uses. (1) As a solvent: 111.Hair and scalp preparations. 122.Toilet waters and colognes. 141.Shampoos. (2) Miscellaneous uses: 812.Product development and pilot plant...

27 CFR 21.70 - Formula No. 39-A.

Code of Federal Regulations, 2010 CFR

2010-04-01

.... Cinchonidine sulfate, N.F. IX. (b) Authorized uses. (1) As a solvent: 111.Hair and scalp preparations. 122.Toilet waters and colognes. 141.Shampoos. (2) Miscellaneous uses: 812.Product development and pilot plant...

27 CFR 21.70 - Formula No. 39-A.

Code of Federal Regulations, 2014 CFR

2014-04-01

.... Cinchonidine sulfate, N.F. IX. (b) Authorized uses. (1) As a solvent: 111.Hair and scalp preparations. 122.Toilet waters and colognes. 141.Shampoos. (2) Miscellaneous uses: 812.Product development and pilot plant...

14 CFR 23.1329 - Automatic pilot system.

Code of Federal Regulations, 2011 CFR

2011-01-01

... control. (c) Unless there is automatic synchronization, each system must have a means to readily indicate... that corrective action begins within a reasonable period of time. (f) Each system must be designed so...

14 CFR 23.1329 - Automatic pilot system.

Code of Federal Regulations, 2013 CFR

2013-01-01

... control. (c) Unless there is automatic synchronization, each system must have a means to readily indicate... that corrective action begins within a reasonable period of time. (f) Each system must be designed so...

14 CFR 23.1329 - Automatic pilot system.

Code of Federal Regulations, 2010 CFR

2010-01-01

... control. (c) Unless there is automatic synchronization, each system must have a means to readily indicate... that corrective action begins within a reasonable period of time. (f) Each system must be designed so...

14 CFR 23.1329 - Automatic pilot system.

Code of Federal Regulations, 2012 CFR

2012-01-01

... control. (c) Unless there is automatic synchronization, each system must have a means to readily indicate... that corrective action begins within a reasonable period of time. (f) Each system must be designed so...

14 CFR 23.1329 - Automatic pilot system.

Code of Federal Regulations, 2014 CFR

2014-01-01

... control. (c) Unless there is automatic synchronization, each system must have a means to readily indicate... that corrective action begins within a reasonable period of time. (f) Each system must be designed so...

Hormonal responses of pilots flying high-performance aircraft during seven repetitive flight missions.

PubMed

Tarui, H; Nakamura, A

1991-12-01

Hormonal responses during seven repetitive flight missions (7RFM) were evaluated on F-4EJ fighter pilots. The following biochemical constituents were measured: 1) cortisol in saliva; 2) 17-OHCS; 3) unbound cortisol; 4) catecholamines in urine; and 5) electrolytes in urine. Samples were collected at about 30 min before the mission, 20 min after each flight, and in a nonflight day for control. The levels of saliva and urine corticosteroids slightly increased during 7RFM when compared with controls. The concentrations of urine catecholamines during 7RFM were significantly higher than those of preflight and control. These data suggest that flight stresses were moderate for the pilots flying 7RFM.

Use of conventional and alternative treatment strategies for a case of low back pain in a F/A-18 aviator

PubMed Central

Green, Bart N; Sims, John; Allen, Rachel

2006-01-01

Background Low back pain can diminish jet pilot concentration and function during flight and be severe enough to ground pilots or cause decreased flying time. The objective of this case report is to present an example of the integration of chiropractic care with conventional treatments for the management of low back pain in a F/A-18 aviator. Case presentation The patient had insidious severe low back pain without radiation or neurological deficit, resulting in 24 hours of hospitalization. Spinal degeneration was discovered upon imaging. Four months later, it still took up to 10 minutes for him to get out of bed and several minutes to exit the jet due to stiffness and pain. He had discontinued his regular Marine Corps fitness training due to pain avoidance. Pain severity ranged from 1.5–7.1 cm on a visual analog scale. His Roland Morris Disability Questionnaire score was 5 out of 24. The pilot's pain was managed with the coordinated efforts of the flight surgeon, physiatrist, physical therapist, and doctor of chiropractic. Following this regimen he had no pain and no functional disability; he was able to fly multiple training missions per week and exercise to Marine Corps standards. Conclusion A course of care integrating flight medicine, chiropractic, physical therapy, and physiatry appeared to alleviate pain and restore function to this F/A-18 aviator with low back pain. PMID:16820063

Promoting healthy eating and active playtime by connecting to nature families with preschool children: evaluation of pilot study "Play&Grow".

PubMed

Sobko, Tanja; Jia, Zhenzhen; Kaplan, Matthew; Lee, Alfred; Tseng, Chia-Huei

2017-04-01

This pilot project aimed to evaluate the "Play&Grow" program which promotes age-appropriate dietary habits and playtime healthy routines through "connectedness to nature" experiences in Hong Kong families with young children. Thirty-eight preschoolers (aged 33.97 ± 9.38 mo), mothers, and their domestic workers were recruited. The families attended one workshop/week for a 4-mo period, consisting of: (i) health topic; (ii) food games; (iii) nature-related outdoor activities. Feeding practices, particularly Promoting and Encouragement to eat (PE) and Instrumental Feeding (IF) improved after the intervention (P = 0.008 and P = 0.016, respectively). Mother's BMI, responsibility for child's meal, child's birth weight had a bearing on the improvement of PE, r 2 = 0.243, F(3,33) = 3.54, P = 0.025. Domestic helper's responsibility for child's cooking and her IF practices could predict child's picky eating (r 2 = 0.203, F(2,34) = 4.322, P = 0.021). Mother's responsibility for child and helper's responsibility for cooking could predict child's consumption of salty foods (r 2 = 0.252, F(2,34) = 5.737, P = 0.007). Physical activity of caregivers improved after the intervention. The pilot confirmed the design, protocols, evaluation instruments, and logistics of the study. Modified "Play&Grow" intervention will be conducted in a more rigorous randomized controlled trial to determine the long-term impact on obesity prevention in Hong Kong.

Head and neck lymphedema management: Evaluation of a therapy program.

PubMed

Pigott, Amanda; Nixon, Jodie; Fleming, Jennifer; Porceddu, Sandro

2018-06-01

The purpose of this pilot study was to examine a therapeutic intervention for head and neck lymphedema. The 22-week intervention involved therapist-led care and participant self-management. Effectiveness was evaluated using a previously described lymphedema assessment tool, the Assessment of Lymphedema of the Head and Neck (ALOHA) to detect change over the course of the 22 weeks of treatment, and before and after a single treatment session. A prospective observational pilot study was conducted with a cohort of 10 participants assessed. Measurements of size (tape measurements) and water content (tissue dielectric constant [TDC]) were used, per the ALOHA protocol. Participants received 13 lymphedema therapy treatments at reducing frequencies over 22 weeks and daily self-management. There was an overall significant reduction in lower neck circumference (F [2.15,19.35] = 7.11; P = .004), upper neck circumference (F [5,45] = 7.27; P < .001) and TDC (F (5,45) = 8.92; P < .001) over time. There were no significant differences over the course of treatment for mean ear-to-ear measurements or before and after a single session of treatment. This pilot study found a reduction in head and neck lymphedema over the 22-week lymphedema treatment course. This intervention may be successful in reducing head and neck lymphedema; however, further studies are needed to investigate these findings in a larger sample with the use of a control group to negate improvements from healing over time. © 2018 Wiley Periodicals, Inc.

Chemical analysis and biological testing of materials from the EDS coal liquefaction process: a status report

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

Later, D.W.; Pelroy, R.A.; Wilson, B.W.

1984-05-01

Representative process materials were obtained from the EDS pilot plant for chemical and biological analyses. These materials were characterized for biological activity and chemical composition using a microbial mutagenicity assay and chromatographic and mass spectrometric analytical techniques. The two highest boiling distillation cuts, as well as process solvent (PS) obtained from the bottoms recycle mode operation, were tested for initiation of mouse skin tumorigenicity. All three materials were active; the crude 800/sup 0 +/F cut was substantially more potent than the crude bottoms recycle PS or 750 to 800/sup 0/F distillate cut. Results from chemical analyses showed the EDS materials,more » in general, to be more highly alkylated and have higher hydroaromatic content than analogous SRC II process materials (no in-line process hydrogenation) used for comparison. In the microbial mutagenicity assays the N-PAC fractions showed greater activity than did the aliphatic hydrocarbon, hydroxy-PAH, or PAH fractions, although mutagenicity was detected in certain PAH fractions by a modified version of the standard microbial mutagenicity assay. Mutagenic activities for the EDS materials were lower, overall, than those for the corresponding materials from the SRC II process. The EDS materials produced under different operational modes had distinguishable differences in both their chemical constituency and biological activity. The primary differences between the EDS materials studied here and their SRC II counterparts used for comparison are most likely attributable to the incorporation of catalytic hydrogenation in the EDS process. 27 references, 28 figures, 27 tables.« less

Evaluation of US Air Force Survival/Armor Vest in US Army OH-58 Helicopters

DTIC Science & Technology

1976-02-01

Camera D. EVALUATION RESULTS: In releasing the cyclic friction, figures 3 £ 4, the left top *.Ige -f the armor insert and carrier hit the pilot’s chits ...ow4 -4 40 N) .44 .4 T- ek N . f. f0 r- 0 4 0 %nf𔃾 1035 -4 m) ko OD 4 m , ~ N0 4 4 -4 r4 -4 + 4 % 9 1 9 1 , 1 9 9 9 at ’ 4 . 4 0 a 0 0 ’I + 9 C a 94 9

High alpha feedback control for agile half-loop maneuvers of the F-18 airplane

NASA Technical Reports Server (NTRS)

Stalford, Harold

1988-01-01

A nonlinear feedback control law for the F/A-18 airplane that provides time-optimal or agile maneuvering of the half-loop maneuver at high angles of attack is given. The feedback control law was developed using the mathematical approach of singular perturbations, in which the control devices considered were conventional aerodynamic control surfaces and thrusting. The derived nonlinear control law was used to simulate F/A-18 half-loop maneuvers. The simulated results at Mach 0.6 and 0.9 compared well with pilot simulations conducted at NASA.

Autonomous Formation Flight: Project Overview

NASA Technical Reports Server (NTRS)

Cole, Jennifer; Cobleigh, Brent; Vachon, Jake; Ray, Ronald J.; Ennix, Kimberly; Walsh, Kevin

2008-01-01

Objectives: a) Map the vortex effects; b) Formation Auto-Pilot Requirements. Two NASA F/A-18 aircraft in formation: a) NASA 845 Systems Research Aircraft; b) NASA 847 Support Aircraft. Flight Conditions: M = 0.56, 25000 feet (Subsonic condition); b) M = 0.86, 36000 feet (Transonic condition). Nose-To-Tail (N2T) Distances: 20, 55, 110 and 190 feet. Lessons learned: a) Controllable flight in vortex is possible with pilot feedback (displays); b) Position hold at best C(sub D), is attainable; c) Best drag location is close to max rolling moment; e) Drag reductions demonstrated up to 22% (WFE up to 20%); f) Induced drag results compare favorably with simple prediction model; g) "Sweet Spot" (lateral & vertical area > 25%) is larger than predicted; h) Larger wing overlaps result in sign reversals in roll, yaw; i) As predicted, favorable effects degrade gradually with increased nose-to-tail distances after peaking at 3 span lengths aft; and j) Demonstrated - over 100 N mi (>15%) range improvement and 650 lbs (14%) fuel savings on actual simulated F/A-18 cruise mission.

KSC-07pd3103

NASA Image and Video Library

2007-11-02

KENNEDY SPACE CENTER, FLA. -- In a cavalcade of veteran Apollo and Mercury astronauts, John Glenn rides in the back of a Corvette driven by Al Worden. On Feb. 20, 1962, John Glenn piloted the Mercury-Atlas 6 "Friendship 7" spacecraft on the first U.S. manned orbital mission. Worden was command module pilot for Apollo 15, July 26-Aug. 7, 1971. The astronauts were part of the World Space Expo, an event to commemorate humanity's first 50 years in space while looking forward to returning people to the moon and exploring beyond. Commemorating humanity's first 50 years in space while looking forward to returning people to the moon and exploring beyond, the expo showcased various panels, presentations and educational programs, as well as an aerial salute featuring the U.S. Air Force Thunderbirds, U.S. Air Force F-22 Raptor, U.S. Navy F-18 Super Hornet, U.S. Air Force F-15 Eagle, the P-51 Mustang Heritage Flight, and the U.S. Air Force 920th Rescue Wing, which was responsible for Mercury and Gemini capsule recovery. The U.S. Army Golden Knights also demonstrated precision skydiving. Photo credit: NASA/George Shelton

KSC-07pd3076

NASA Image and Video Library

2007-11-02

KENNEDY SPACE CENTER, FLA. — On stage for the World Space Expo's Pioneering Women of Aerospace forum are Ret. Colonel Eileen Collins, the first female shuttle commander; Dr. Kathryn D. Sullivan, the first American woman to spacewalk; Patricia Grace Smith, with the FAA, the first associate administrator of commercial space transportation; Dr. Anousheh Ansari, a spaceflight participant; Major Nicole Malachowski, the first female pilot with the U.S. Air Force Thunderbirds; and Major Samantha Weeks, the first female solo pilot with the U.S. Air Force Thunderbirds. The expo commemorates humanity's first 50 years in space while looking forward to returning people to the moon and exploring beyond. The expo showcased various panels, presentations and educational programs, as well as an aerial salute featuring the U.S. Air Force Thunderbirds, U.S. Air Force F-22 Raptor, U.S. Navy F-18 Super Hornet, U.S. Air Force F-15 Eagle, the P-51 Mustang Heritage Flight, and the U.S. Air Force 920th Rescue Wing, which was responsible for Mercury and Gemini capsule recovery. The U.S. Army Golden Knights also demonstrated precision skydiving. Photo credit: NASA/Kim Shiflett

KSC-07pd3074

NASA Image and Video Library

2007-11-02

KENNEDY SPACE CENTER, FLA. — On stage for the World Space Expo's Pioneering Women of Aerospace forum are Ret. Colonel Eileen Collins, the first female shuttle commander; Dr. Kathryn D. Sullivan, the first American woman to spacewalk; Patricia Grace Smith, with the FAA, the first associate administrator of commercial space transportation; Dr. Anousheh Ansari, a spaceflight participant ; Major Nicole Malachowski, the first female pilot with the U.S. Air Force Thunderbirds; and Major Samantha Weeks, the first female solo pilot with the U.S. Air Force Thunderbirds. The expo commemorates humanity's first 50 years in space while looking forward to returning people to the moon and exploring beyond. The expo showcased various panels, presentations and educational programs, as well as an aerial salute featuring the U.S. Air Force Thunderbirds, U.S. Air Force F-22 Raptor, U.S. Navy F-18 Super Hornet, U.S. Air Force F-15 Eagle, the P-51 Mustang Heritage Flight, and the U.S. Air Force 920th Rescue Wing, which was responsible for Mercury and Gemini capsule recovery. The U.S. Army Golden Knights also demonstrated precision skydiving. Photo credit: NASA/Kim Shiflett

KSC-07pd3077

NASA Image and Video Library

2007-11-02

KENNEDY SPACE CENTER, FLA. — In the spotlight for the World Space Expo's Pioneering Women of Aerospace forum are Ret. Colonel Eileen Collins, the first female shuttle commander; Dr. Kathryn D. Sullivan, the first American woman to spacewalk; Patricia Grace Smith, with the FAA, the first associate administrator of commercial space transportation; Dr. Anousheh Ansari, a spaceflight participant; Major Nicole Malachowski, the first female pilot with the U.S. Air Force Thunderbirds; and Major Samantha Weeks, the first female solo pilot with the U.S. Air Force Thunderbirds. The expo commemorates humanity's first 50 years in space while looking forward to returning people to the moon and exploring beyond. The expo showcased various panels, presentations and educational programs, as well as an aerial salute featuring the U.S. Air Force Thunderbirds, U.S. Air Force F-22 Raptor, U.S. Navy F-18 Super Hornet, U.S. Air Force F-15 Eagle, the P-51 Mustang Heritage Flight, and the U.S. Air Force 920th Rescue Wing, which was responsible for Mercury and Gemini capsule recovery. The U.S. Army Golden Knights also demonstrated precision skydiving. Photo credit: NASA/Kim Shiflett

KSC-07pd3075

NASA Image and Video Library

2007-11-02

KENNEDY SPACE CENTER, FLA. — On stage for the World Space Expo's Pioneering Women of Aerospace forum are Ret. Colonel Eileen Collins, the first female shuttle commander; Dr. Kathryn D. Sullivan, the first American woman to spacewalk; Patricia Grace Smith, with the FAA, the first associate administrator of commercial space transportation; Dr. Anousheh Ansari, a spaceflight participant; Major Nicole Malachowski, the first female pilot with the U.S. Air Force Thunderbirds; and Major Samantha Weeks, the first female solo pilot with the U.S. Air Force Thunderbirds. The expo commemorates humanity's first 50 years in space while looking forward to returning people to the moon and exploring beyond. The expo showcased various panels, presentations and educational programs, as well as an aerial salute featuring the U.S. Air Force Thunderbirds, U.S. Air Force F-22 Raptor, U.S. Navy F-18 Super Hornet, U.S. Air Force F-15 Eagle, the P-51 Mustang Heritage Flight, and the U.S. Air Force 920th Rescue Wing, which was responsible for Mercury and Gemini capsule recovery. The U.S. Army Golden Knights also demonstrated precision skydiving. Photo credit: NASA/Kim Shiflett

M2-F1 mounted in NASA Ames Research Center 40x80 foot wind tunnel

NASA Technical Reports Server (NTRS)

1962-01-01

After the first attempted ground-tow tests of the M2-F1 in March 1963, the vehicle was taken to the Ames Research Center, Mountain View, CA, for wind-tunnel testing. During these tests, Milt Thompson and others were in the M2-F1 to position the control surfaces for each test. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Wooden shell of M2-F1 being assembled at El Mirage

NASA Technical Reports Server (NTRS)

1962-01-01

Wooden shell of the M2-F1 being assembled at El Mirage, CA. While Flight Research Center technicians built the internal steel structure of the M2-F1, sailplane builder Gus Briegleb built the vehicle's outer wooden shell. Its skin was 3/32-inch mahogany plywood, with 1/8-inch mahogany rib sections reinforced with spruce. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

M2-F1 cockpit

NASA Technical Reports Server (NTRS)

1963-01-01

This photo shows the cockpit configuration of the M2-F1 wingless lifting body. With a top speed of about 120 knots, the M2-F1 had a simple instrument panel. Besides the panel itself, the ribs of the wooden shell (left) and the control stick (center) are also visible. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Apollo 12 Mission image - High oblique view of Craters 285,287 and Tsiolkovski

NASA Image and Video Library

1969-11-19

AS12-47-6870 (November 1969) --- An Apollo 12 high-oblique view of the crater Tsiolkovsky (in center of horizon) on the lunar farside, as photographed from lunar orbit. The crew men of the Apollo 12 lunar landing mission were astronauts Charles Conrad Jr., commander; Richard F. Gordon Jr., command module pilot; and Alan L. Bean, lunar module pilot. Tsiolkovsky is centered at 128.5 degrees east longitude and 20.5 degrees south latitude. This view is looking south.

Apollo 12 crewmen participate in water egress training

NASA Technical Reports Server (NTRS)

1969-01-01

The three prime crewmen of the Apollo 12 lunar landing mission participate in water egress training in the Gulf of Mexico. They have just egressed the Apollo Command Module trainer. The man standing at left is a Manned Spacecraft Center (MSC) swimmer. The crewmen await life raft for helicopter pickup. All four persons are wearing biological isoloation garments. Participating in the training exercise were Astronauts Charles Conrad Jr., commander; Richard F. Gordon Jr., command module pilot; and Alan L. Bean, lunar module pilot.

F-22 Pilot Heart Rate Response to +Gz and Relationship to Pilot Fitness Using U.S. Air Force Fitness Test Scores

DTIC Science & Technology

2015-08-19

finger-mounted units that produced a significant amount of artifact. The collection method matured to a helmet-mounted pulse oximeter (HMPO) unit...2015-5343. Helmet-mounted pulse oximeter data exist for 5847 sorties. Each sortie contains multiple +Gz exposures and each +Gz exposure is of...AGSM anti-G straining maneuver BMI body mass index CO cardiac output HMPO helmet-mounted pulse oximeter HR heart rate ID identification

Astronaut Alan Bean works on Modular Equipment Stowage Assembly

NASA Image and Video Library

1969-11-19

AS12-46-6749 (19 Nov. 1969) --- Astronaut Alan L. Bean, lunar module pilot for the Apollo 12 lunar landing mission, works at the Modular Equipment Stowage Assembly (MESA) on the Apollo 12 Lunar Module (LM) during the mission's first extravehicular activity, (EVA) on Nov. 19, 1969. Astronaut Charles Conrad Jr., commander, and Bean descended in the Apollo 12 LM to explore the moon while astronaut Richard F. Gordon Jr., command module pilot, remained with the Command and Service Modules (CSM) in lunar orbit.

Apollo 12 Mission image - Dark view of Astronaut Alan L. Bean climbing down the ladder of the Lunar Module (LM)

NASA Image and Video Library

1969-11-19

AS12-46-6728 (19 Nov. 1969) --- Astronaut Alan L. Bean, lunar module pilot for the Apollo 12 mission, is about to step off the ladder of the Lunar Module to join astronaut Charles Conrad Jr., mission commander, in extravehicular activity (EVA). Conrad and Bean descended in the Apollo 12 LM to explore the moon while astronaut Richard F. Gordon Jr., command module pilot, remained with the Command and Service Modules in lunar orbit.

U.S.S. Hornet crewmen greeted by crew of Apollo 12 lunar landing mission

NASA Image and Video Library

1969-11-24

S69-22849 (24 Nov. 1969) --- USS Hornet crewmen are greeted by the crew of the Apollo 12 lunar landing mission as the three astronauts are transferred from a U.S. Navy helicopter to a Mobile Quarantine Facility (MQF) aboard the prime recovery vessel. Charles Conrad Jr., right, commander; Richard F. Gordon Jr., command module pilot, left front; and Alan L. Bean, lunar module pilot, splashed down safely at 2:58 p.m., Nov. 24, 1969.

X-15 landing on lakebed

NASA Technical Reports Server (NTRS)

1960-01-01

In this 17-second video clip, the X-15 is shown in flight and then landing on Rogers Dry Lakebed adjacent to Edwards Air Force Base. It is followed by an F-104A chase aircraft, whose pilot provided a second set of eyes to the X-15 pilot on landing in case of any problems. The video shows the skids on the back of the X-15 contacting the lakebed, with the aircraft's nose then rotating downward until the nose landing gear was on the lakebed.

STS-29 Pilot Blaha with SE83-9 'Chix in Space' incubator on OV-103's middeck

NASA Technical Reports Server (NTRS)

1989-01-01

On aft middeck of Discovery, Orbiter Vehicle (OV) 103, Pilot John E. Blaha opens incubator hatch on STS-29 Student Experiment (SE) 83-9 Chicken Embryo Development in Space or 'Chix in Space'. SE83-9 developed by John C. Vellinger is located in middeck aft locker MA16F. The student's sponsor is Kentucky Fried Chicken (KFC). Behind Blaha are starboard wall-mounted sleep restraints, freefloating headset, and checklists velcroed to wall.

APOLLO VIII - LAUNCH - KSC

NASA Image and Video Library

1968-12-21

S68-56002 (21 Dec. 1968) --- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 was the first manned Saturn V launch. (F-ls 1/3 way from top of mobile launch tower.)

Verification and Validation of Adaptive and Intelligent Systems with Flight Test Results

NASA Technical Reports Server (NTRS)

Burken, John J.; Larson, Richard R.

2009-01-01

F-15 IFCS project goals are: a) Demonstrate Control Approaches that can Efficiently Optimize Aircraft Performance in both Normal and Failure Conditions [A] & [B] failures. b) Advance Neural Network-Based Flight Control Technology for New Aerospace Systems Designs with a Pilot in the Loop. Gen II objectives include; a) Implement and Fly a Direct Adaptive Neural Network Based Flight Controller; b) Demonstrate the Ability of the System to Adapt to Simulated System Failures: 1) Suppress Transients Associated with Failure; 2) Re-Establish Sufficient Control and Handling of Vehicle for Safe Recovery. c) Provide Flight Experience for Development of Verification and Validation Processes for Flight Critical Neural Network Software.

14 CFR 23.415 - Ground gust conditions.

Code of Federal Regulations, 2014 CFR

2014-01-01

...) If pilot forces less than the minimums specified in § 23.397(b) are used for design, the effects of... according to the formula: H=K c S q where— H=limit hinge moment (ft.-lbs.); c=mean chord of the control... pressure (p.s.f.) based on a design speed not less than 14.6 √(W/S) + 14.6 (f.p.s.) where W/S=wing loading...

14 CFR 23.415 - Ground gust conditions.

Code of Federal Regulations, 2012 CFR

2012-01-01

...) If pilot forces less than the minimums specified in § 23.397(b) are used for design, the effects of... according to the formula: H=K c S q where— H=limit hinge moment (ft.-lbs.); c=mean chord of the control... pressure (p.s.f.) based on a design speed not less than 14.6 √(W/S) + 14.6 (f.p.s.) where W/S=wing loading...

14 CFR 23.415 - Ground gust conditions.

Code of Federal Regulations, 2013 CFR

2013-01-01

...) If pilot forces less than the minimums specified in § 23.397(b) are used for design, the effects of... according to the formula: H=K c S q where— H=limit hinge moment (ft.-lbs.); c=mean chord of the control... pressure (p.s.f.) based on a design speed not less than 14.6 √(W/S) + 14.6 (f.p.s.) where W/S=wing loading...

Vista/F-16 Multi-Axis Thrust Vectoring (MATV) control law design and evaluation

NASA Technical Reports Server (NTRS)

Zwerneman, W. D.; Eller, B. G.

1994-01-01

For the Multi-Axis Thrust Vectoring (MATV) program, a new control law was developed using multi-axis thrust vectoring to augment the aircraft's aerodynamic control power to provide maneuverability above the normal F-16 angle of attack limit. The control law architecture was developed using Lockheed Fort Worth's offline and piloted simulation capabilities. The final flight control laws were used in flight test to demonstrate tactical benefits gained by using thrust vectoring in air-to-air combat. Differences between the simulator aerodynamics data base and the actual aircraft aerodynamics led to significantly different lateral-directional flying qualities during the flight test program than those identified during piloted simulation. A 'dial-a-gain' flight test control law update was performed in the middle of the flight test program. This approach allowed for inflight optimization of the aircraft's flying qualities. While this approach is not preferred over updating the simulator aerodynamic data base and then updating the control laws, the final selected gain set did provide adequate lateral-directional flying qualities over the MATV flight envelope. The resulting handling qualities and the departure resistance of the aircraft allowed the 422nd_squadron pilots to focus entirely on evaluating the aircraft's tactical utility.

14 CFR 67.401 - Special issuance of medical certificates.

Code of Federal Regulations, 2014 CFR

2014-01-01

... commercial or airline transport pilot privileges, and, at the same time, considers the need to protect the... Regional Flight Surgeon. (i) If an Authorization or SODA is withdrawn under paragraph (f) of this section...

14 CFR 67.401 - Special issuance of medical certificates.

Code of Federal Regulations, 2013 CFR

2013-01-01

... commercial or airline transport pilot privileges, and, at the same time, considers the need to protect the... Regional Flight Surgeon. (i) If an Authorization or SODA is withdrawn under paragraph (f) of this section...

14 CFR 67.401 - Special issuance of medical certificates.

Code of Federal Regulations, 2011 CFR

2011-01-01

... commercial or airline transport pilot privileges, and, at the same time, considers the need to protect the... Regional Flight Surgeon. (i) If an Authorization or SODA is withdrawn under paragraph (f) of this section...

14 CFR 67.401 - Special issuance of medical certificates.

Code of Federal Regulations, 2012 CFR

2012-01-01

... commercial or airline transport pilot privileges, and, at the same time, considers the need to protect the... Regional Flight Surgeon. (i) If an Authorization or SODA is withdrawn under paragraph (f) of this section...

14 CFR 67.401 - Special issuance of medical certificates.

Code of Federal Regulations, 2010 CFR

2010-01-01

... commercial or airline transport pilot privileges, and, at the same time, considers the need to protect the... Regional Flight Surgeon. (i) If an Authorization or SODA is withdrawn under paragraph (f) of this section...

Assessment of glucose metabolism and cellular proliferation in multiple myeloma: a first report on combined 18F-FDG and 18F-FLT PET/CT imaging.

PubMed

Sachpekidis, C; Goldschmidt, H; Kopka, K; Kopp-Schneider, A; Dimitrakopoulou-Strauss, A

2018-04-10

Despite the significant upgrading in recent years of the role of 18 F-FDG PET/CT in multiple myeloma (MM) diagnostics, there is a still unmet need for myeloma-specific radiotracers. 3'-Deoxy-3'-[ 18 F]fluorothymidine ( 18 F-FLT) is the most studied cellular proliferation PET agent, considered a potentially new myeloma functional imaging tracer. The aim of this pilot study was to evaluate 18 F-FLT PET/CT in imaging of MM patients, in the context of its combined use with 18 F-FDG PET/CT. Eight patients, four suffering from symptomatic MM and four suffering from smoldering MM (SMM), were enrolled in the study. All patients underwent 18 F-FDG PET/CT and 18 F-FLT PET/CT imaging by means of static (whole body) and dynamic PET/CT of the lower abdomen and pelvis (dPET/CT) in two consecutive days. The evaluation of PET/CT studies was based on qualitative evaluation, semi-quantitative (SUV) calculation, and quantitative analysis based on two-tissue compartment modeling. 18 F-FDG PET/CT demonstrated focal, 18 F-FDG avid, MM-indicative bone marrow lesions in five patients. In contrary, 18 F-FLT PET/CT showed focal, 18 F-FLT avid, myeloma-indicative lesions in only two patients. In total, 48 18 F-FDG avid, focal, MM-indicative lesions were detected with 18 F-FDG PET/CT, while 17 18 F-FLT avid, focal, MM-indicative lesions were detected with 18 F-FLT PET/CT. The number of myeloma-indicative lesions was significantly higher for 18 F-FDG PET/CT than for 18 F-FLT PET/CT. A common finding was a mismatch of focally increased 18 F-FDG uptake and reduced 18 F-FLT uptake (lower than the surrounding bone marrow). Moreover, 18 F-FLT PET/CT was characterized by high background activity in the bone marrow compartment, further complicating the evaluation of bone marrow lesions. Semi-quantitative evaluation revealed that both SUV mean and SUV max were significantly higher for 18 F-FLT than for 18 F-FDG in both MM lesions and reference tissue. SUV values were higher in MM lesions than in reference bone marrow for both tracers. Despite the limited number of patients analyzed in this pilot study, the first results of the trial indicate that 18 F-FLT does not seem suitable as a single tracer in MM diagnostics. Further studies with a larger patient population are warranted to generalize the herein presented results.

Comparison of bacteriophage and enteric virus removal in pilot scale activated sludge plants.

PubMed

Arraj, A; Bohatier, J; Laveran, H; Traore, O

2005-01-01

The aim of this experimental study was to determine comparatively the removal of two types of bacteriophages, a somatic coliphage and an F-specific RNA phage and of three types of enteric viruses, hepatitis A virus (HAV), poliovirus and rotavirus during sewage treatment by activated sludge using laboratory pilot plants. The cultivable simian rotavirus SA11, the HAV HM 175/18f cytopathic strain and poliovirus were quantified by cell culture. The bacteriophages were quantified by plaque formation on the host bacterium in agar medium. In each experiment, two pilots simulating full-scale activated sludge plants were inoculated with viruses at known concentrations, and mixed liquor and effluent samples were analysed regularly. In the mixed liquor, liquid and solid fractions were analysed separately. The viral behaviour in both the liquid and solid phases was similar between pilots of each experiment. Viral concentrations decreased rapidly following viral injection in the pilots. Ten minutes after the injections, viral concentrations in the liquid phase had decreased from 1.0 +/- 0.4 log to 2.2 +/- 0.3 log. Poliovirus and HAV were predominantly adsorbed on the solid matters of the mixed liquor while rotavirus was not detectable in the solid phase. In our model, the estimated mean log viral reductions after 3-day experiment were 9.2 +/- 0.4 for rotavirus, 6.6 +/- 2.4 for poliovirus, 5.9 +/- 3.5 for HAV, 3.2 +/- 1.2 for MS2 and 2.3 +/- 0.5 for PhiX174. This study demonstrates that the pilots are useful models to assess the removal of infectious enteric viruses and bacteriophages by activated sludge treatment. Our results show the efficacy of the activated sludge treatment on the five viruses and suggest that coliphages could be an acceptable indicator of viral removal in this treatment system.

HL-10 on lakebed

NASA Technical Reports Server (NTRS)

1968-01-01

The HL-10 Lifting Body is seen here parked on Rogers Dry Lake, the unique location where it landed after research flights. This 1968 photo shows the vehicle after the fins were modified to remove instabilities encountered on the first flight. It involved a change to the shape of the leading edge of the fins to eliminate flow separation. It required extensive wind-tunnel testing at Langley Research Center, Hampton, Va. NASA Flight Research Center (FRC) engineer Bob Kempel than plotted thousands of data points by hand to come up with the modification, which involved a fiberglass glove backed with a metal structure on each fin's leading edge. This transformed the vehicle from a craft that was difficult to control into the best handling of the original group of lifting bodies at the FRC. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

M2-F1 fabrication by Grierson Hamilton, Bob Green, and Ed Browne

NASA Technical Reports Server (NTRS)

1962-01-01

Flight Research Center discretionary funds paid for the M2-F-1's construction. NASA mechanics, sheet-metal smiths, and technicians did much of the work in a curtained-off area of a hangar called the 'Wright Bicycle Shop.' The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Internal steel structure of M2-F1

NASA Technical Reports Server (NTRS)

1963-01-01

The internal steel structure for the M2-F1 was built at the Flight Research Center (predecessor of the Dryden Flight Research Center, Edwards, CA) in a section of the calibration hangar dubbed 'Wright Bicycle Shop.' Visible are the stick, rudder pedals, and ejection seat. The external wooden shell was attached to the steel structure. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Centrifuge-induced neck and back pain in F-16 pilots: a report of four cases.

PubMed

Lange, Britt; Nielsen, René Tyranski; Skejø, Pernille Bro; Toft, Palle

2013-07-01

Early in their careers, as an important part of their training to become fighter pilots, pilots undergo centrifuge training in order to learn effective anti-G straining maneuvers (AGSM) and to test their G tolerance. The exposure of pilots, especially early in their careers, to training that could lead to injuries should be avoided. This is a report of four cases of neck pain experienced during G-tolerance training, some of which may have caused ongoing problems for the pilot. Four cases, describing four different injuries experienced during G-tolerance training, are presented, including the history of the incident, radiographic description, and physical examination. Three main questions were identified in regards to the training of fighter pilots in centrifuges: 1) should the seat be positioned to imitate a specific aircraft's seat? 2) should the pilot wear a helmet and a mask? 3) what is the appropriate amount of head support? Based on the four cases reported it is recommended that pilots should be given the best possible conditions concerning neck support and load on the neck and the back for G-tolerance testing. Training the pilot in an anatomical neutral sitting position, without a helmet, and with maximal neck support minimizes head movements in cases of conscious or unconscious loss of muscle control. To test the stability of the neck in a setup similar to the environment where the pilot is going to operate, the pilot should be given the opportunity to prepare himself or herself accordingly in advance.

33 CFR 385.12 - Pilot projects.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Pilot projects. 385.12 Section... Processes § 385.12 Pilot projects. (a) The Plan includes pilot projects to address uncertainties associated... management, and wastewater reuse. The purpose of the pilot projects is to develop information necessary to...

33 CFR 385.12 - Pilot projects.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 33 Navigation and Navigable Waters 3 2011-07-01 2011-07-01 false Pilot projects. 385.12 Section... Processes § 385.12 Pilot projects. (a) The Plan includes pilot projects to address uncertainties associated... management, and wastewater reuse. The purpose of the pilot projects is to develop information necessary to...

33 CFR 385.12 - Pilot projects.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 33 Navigation and Navigable Waters 3 2014-07-01 2014-07-01 false Pilot projects. 385.12 Section... Processes § 385.12 Pilot projects. (a) The Plan includes pilot projects to address uncertainties associated... management, and wastewater reuse. The purpose of the pilot projects is to develop information necessary to...

33 CFR 385.12 - Pilot projects.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 33 Navigation and Navigable Waters 3 2012-07-01 2012-07-01 false Pilot projects. 385.12 Section... Processes § 385.12 Pilot projects. (a) The Plan includes pilot projects to address uncertainties associated... management, and wastewater reuse. The purpose of the pilot projects is to develop information necessary to...

A high 18F-FDOPA uptake is associated with a slow growth rate in diffuse Grade II-III gliomas.

PubMed

Isal, Sibel; Gauchotte, Guillaume; Rech, Fabien; Blonski, Marie; Planel, Sophie; Chawki, Mohammad B; Karcher, Gilles; Marie, Pierre-Yves; Taillandier, Luc; Verger, Antoine

2018-04-01

In diffuse Grade II-III gliomas, a high 3,4-dihydroxy-6-( 18 F)-fluoro-L-phenylalanine ( 18 F-FDOPA) positron emission tomography (PET) uptake, with a standardized uptake value (SUV max )/contralateral brain tissue ratio greater than 1.8, was previously found to be consistently associated with the presence of an isocitrate dehydrogenase (IDH) mutation, whereas this mutation is typically associated with a better prognosis. This pilot study was aimed to ascertain the prognostic value of this high 18 F-FDOPA uptake in diffuse Grade II-III gliomas with regard to the velocity of diameter expansion (VDE), which represents an established landmark of better prognosis when below 4 mm per year. 20 patients (42 ± 10 years, 10 female) with newly-diagnosed diffuse Grade II-III gliomas (17 with IDH mutation) were retrospectively included. All had a 18 F-FDOPA PET, quantified with SUV max ratio, along with a serial MRI enabling VDE determination. SUV max ratio was above 1.8 in 5 patients (25%) all of whom had a VDE <4 mm/year (100%) and IDH mutation (100%). Moreover, a SUV max ratio above 1.8 was associated with higher rates of VDE <4 mm/year in the overall population (45 vs 0%, p = 0.04) and also in the subgroup of patients with IDH mutation (45 vs 0%, p = 0.10). This pilot study shows that in diffuse Grade II-III gliomas, a high 18 F-FDOPA uptake would be predictive of low tumour growth, with a different prognostic significance than IDH mutation. Advances in knowledge: 18 F-FDOPA PET in a single session imaging could have prognostic value in initial diagnosis of diffuse Grade II-III gliomas.

KSC-08pd3573

NASA Image and Video Library

2008-11-06

CAPE CANAVERAL, Fla. – Military aircraft are lined up on the Shuttle Landing Facility at NASA's Kennedy Space Center in Florida. The F/A-18s, F-4, F-16 and F-104G Starfighter will take part in demonstrations at the Kennedy Space Center Visitor Complex Space and Air Show Nov. 8-9. The Navy's elite flight demonstration squadron, the Blue Angels, will take to the skies in military aircraft demonstrations for the second annual Space & Air Show at Kennedy. This year’s show brings together the best in military aircraft, coupled with precision pilots and veteran astronauts to celebrate spaceflight and aviation. The event also includes demonstrations by the F-16 Fighting Falcon and a water rescue demonstration by the 920th Rescue Wing. Photo credit: NASA/Kim Shiflett

Apollo display and keyboard unit (DSKY) used on F-8 DFBW

NASA Technical Reports Server (NTRS)

1996-01-01

The display and keyboard (DSKY) unit used on the F-8 Digital Fly-By-Wire (DFBW) aircraft during Phase I of the fly-by-wire program. Warning lights are in the upper left section, displays in the upper right, and the keyboard is in the lower section. The Apollo flight-control system used in Phase I of the DFBW program had been used previously on the Lunar Module and was incredibly reliable. The DSKY was one element of the system. Also part of the fly-by-wire control system was the inertial platform. Both the computer and the inertial platform required a cooling system that used liquid nitrogen to keep the system within temperature limits. Should the primary flight control system fail, a backup system using three analog computers would automatically take over. The F-8 DFBW had no manual backup. The F-8 Digital Fly-By-Wire (DFBW) flight research project validated the principal concepts of all-electric flight control systems now used on nearly all modern high-performance aircraft and on military and civilian transports. The first flight of the 13-year project was on May 25, 1972, with research pilot Gary E. Krier at the controls of a modified F-8C Crusader that served as the testbed for the fly-by-wire technologies. The project was a joint effort between the NASA Flight Research Center, Edwards, California, (now the Dryden Flight Research Center) and Langley Research Center. It included a total of 211 flights. The last flight was December 16, 1985, with Dryden research pilot Ed Schneider at the controls. The F-8 DFBW system was the forerunner of current fly-by-wire systems used in the space shuttles and on today's military and civil aircraft to make them safer, more maneuverable, and more efficient. Electronic fly-by-wire systems replaced older hydraulic control systems, freeing designers to design aircraft with reduced in-flight stability. Fly-by-wire systems are safer because of their redundancies. They are more maneuverable because computers can command more frequent adjustments than a human pilot can. For airliners, computerized control ensures a smoother ride than a human pilot alone can provide. Digital-fly-by-wire is more efficient because it is lighter and takes up less space than the hydraulic systems it replaced. This either reduces the fuel required to fly or increases the number of passengers or pounds of cargo the aircraft can carry. Digital fly-by-wire is currently used in a variety of aircraft ranging from F/A-18 fighters to the Boeing 777. The DFBW research program is considered one of the most significant and most successful NASA aeronautical programs since the inception of the agency. F-8 aircraft were built originally for the U.S. Navy by LTV Aerospace of Dallas, Texas. The aircraft had a wingspan of 35 feet, 2 inches; was 54 feet, 6 inches long; and was powered by a Pratt & Whitney J57 turbojet engine.

Dryden F-8 Research Aircraft Fleet 1973 in flight, DFBW and SCW

NASA Technical Reports Server (NTRS)

1973-01-01

F-8 Digital Fly-By-Wire (left) and F-8 Supercritical Wing in flight. These two aircraft fundamentally changed the nature of aircraft design. The F-8 DFBW pioneered digital flight controls and led to such computer-controlled airacrft as the F-117A, X-29, and X-31. Airliners such as the Boeing 777 and Airbus A320 also use digital fly-by-wire systems. The other aircraft is a highly modified F-8A fitted with a supercritical wing. Dr. Richard T. Whitcomb of Langley Research Center originated the supercritical wing concept in the late 1960s. (Dr. Whitcomb also developed the concept of the 'area rule' in the early 1950s. It singificantly reduced transonic drag.) The F-8 Digital Fly-By-Wire (DFBW) flight research project validated the principal concepts of all-electric flight control systems now used on nearly all modern high-performance aircraft and on military and civilian transports. The first flight of the 13-year project was on May 25, 1972, with research pilot Gary E. Krier at the controls of a modified F-8C Crusader that served as the testbed for the fly-by-wire technologies. The project was a joint effort between the NASA Flight Research Center, Edwards, California, (now the Dryden Flight Research Center) and Langley Research Center. It included a total of 211 flights. The last flight was December 16, 1985, with Dryden research pilot Ed Schneider at the controls. The F-8 DFBW system was the forerunner of current fly-by-wire systems used in the space shuttles and on today's military and civil aircraft to make them safer, more maneuverable, and more efficient. Electronic fly-by-wire systems replaced older hydraulic control systems, freeing designers to design aircraft with reduced in-flight stability. Fly-by-wire systems are safer because of their redundancies. They are more maneuverable because computers can command more frequent adjustments than a human pilot can. For airliners, computerized control ensures a smoother ride than a human pilot alone can provide. Digital-fly-by-wire is more efficient because it is lighter and takes up less space than the hydraulic systems it replaced. This either reduces the fuel required to fly or increases the number of passengers or pounds of cargo the aircraft can carry. Digital fly-by-wire is currently used in a variety of aircraft ranging from F/A-18 fighters to the Boeing 777. The DFBW research program is considered one of the most significant and most successful NASA aeronautical programs since the inception of the agency. F-8 aircraft were built originally for the U.S. Navy by LTV Aerospace of Dallas, Texas. The aircraft had a wingspan of 35 feet, 2 inches; was 54 feet, 6 inches long; and was powered by a Pratt & Whitney J57 turbojet engine. The F-8 Supercritical Wing was a flight research project designed to test a new wing concept designed by Dr. Richard Whitcomb, chief of the Transonic Aerodynamics Branch, Langley Research Center, Hampton, Virginia. Compared to a conventional wing, the supercritical wing (SCW) is flatter on the top and rounder on the bottom with a downward curve at the trailing edge. The Supercritical Wing was designed to delay the formation of and reduce the shock wave over the wing just below and above the speed of sound (transonic region of flight). Delaying the shock wave at these speeds results in less drag. Results of the NASA flight research at the Flight Research Center, Edwards, California, (later renamed the Dryden Flight Research Center) demonstrated that aircraft using the supercritical wing concept would have increased cruising speed, improved fuel efficiency, and greater flight range than those using conventional wings. As a result, supercritical wings are now commonplace on virtually every modern subsonic commercial transport. Results of the NASA project showed the SCW had increased the transonic efficiency of the F-8 as much as 15 percent and proved that passenger transports with supercritical wings, versus conventional wings, could save $78 million (in 1974 dollars) per year for a fleet of 280 200-passenger airliners. The F-8 Supercritical Wing (SCW) project flew from 1970 to 1973. Dryden engineer John McTigue was the first SCW program manager and Tom McMurtry was the lead project pilot. The first SCW flight took place on March 9, 1971. The last flight of the Supercritical wing was on May 23, 1973, with Ron Gerdes at the controls. Original wingspan of the F-8 is 35 feet, 2 inches while the wingspan with the supercritical wing was 43 feet, 1 inch. F-8 aircraft were powered by Pratt & Whitney J57 turbojet engines. The TF-8A Crusader was made available to the NASA Flight Research Center by the U.S. Navy. F-8 jet aircraft were built, originally, by LTV Aerospace, Dallas, Texas. Rockwell International's North American Aircraft Division received a $1.8 million contract to fabricate the supercritical wing, which was delivered to NASA in December 1969.

Final Report of NATO/SPS Pilot Study on Clean Products and Processes (Phase I and II)

EPA Science Inventory

Early in 1998 the NATO Committee for Challenges to Modern Society (SPS) (Science for Peace and Security) approved the Pilot Study on Clean Products and Processes for an initial period of five years. The pilot was to provide a forum for member country representatives to discuss t...

F-8 DFBW with test pilot Gary E. Krier

NASA Technical Reports Server (NTRS)

1971-01-01

Former research pilot Gary E. Krier is the Director of Flight Operations of the NASA Dryden Flight Research Center, Edwards, Calif. He was the acting Deputy Director effective June 30, 2001 to September 9, 2001. Until that time he was the Chief Engineer and also the Director of the Systems Management Office at Dryden. He had held the position of Chief Engineer since August 1, 1999, and he was appointed Systems Management Office Director in October 1999. Before August 1999, he had been the Director of the Airborne Science Directorate since August 1998. Prior to assuming this position, Krier headed the Aerospace Projects Directorate from March 1997 to August 1998. He had previously been in charge of the Intercenter Aircraft Operations Directorate at Dryden from 1995 to 1997. From 1992 to 1994, he served as Manager, Operations and Facilities, for the New Launch System at NASA Headquarters, where he developed operational procedures and facilities for the next generation of Expendable Launch Vehicles and participated in policy making for the program. From 1987 to 1992, he held two different management positions at NASA Headquarters relating to Space Shuttle operations. Among other positions he held before that time were Director of the Commercial Development Division, Office of Commercial Programs, at NASA Headquarters (1984-1987); Director of the Aircraft Management Office at NASA Headquarters (1983-1984); and attorney in the Office of the Chief Counsel at Ames Research Center (1982-1983). Earlier in his career, Krier was an aerospace research pilot and engineer at Dryden after first going to work for NASA in 1967. He was the first pilot to fly the F-8 Digital Fly-by-Wire aircraft and the Integrated Propulsion Control System F-111 with digital fuel and inlet control. He was also co-project pilot with Thomas C. McMurtry on the F-8 Supercritical Wing project. In addition, he flew the YF-17 research aircraft and has flown more than 30 types of aircraft ranging from light planes to the B-52 and the triple-sonic YF-12. Before joining NASA, Krier served as an engineer for Pratt & Whitney, Martin Marietta, and Hercules Powder Company. He is the author of 7 technical reports. He earned his B.S. in mechanical engineering at the University of Utah in 1960 and went on to achieve an M.B.A. (with Distinction) from Golden Gate University in 1978 and a J.D. from the UCLA School of Law in 1982. He also completed the Program for Management Development at Harvard University on a NASA Fellowship in 1975. He is a member of the State Bar of California, of the Society of Experimental Test Pilots (for which he served as legal officer in 1989 and continues to serve as legal advisor and scholarship foundation trustee), and the Quiet Birdmen.

PASTE: patient-centered SMS text tagging in a medication management system.

PubMed

Stenner, Shane P; Johnson, Kevin B; Denny, Joshua C

2012-01-01

To evaluate the performance of a system that extracts medication information and administration-related actions from patient short message service (SMS) messages. Mobile technologies provide a platform for electronic patient-centered medication management. MyMediHealth (MMH) is a medication management system that includes a medication scheduler, a medication administration record, and a reminder engine that sends text messages to cell phones. The object of this work was to extend MMH to allow two-way interaction using mobile phone-based SMS technology. Unprompted text-message communication with patients using natural language could engage patients in their healthcare, but presents unique natural language processing challenges. The authors developed a new functional component of MMH, the Patient-centered Automated SMS Tagging Engine (PASTE). The PASTE web service uses natural language processing methods, custom lexicons, and existing knowledge sources to extract and tag medication information from patient text messages. A pilot evaluation of PASTE was completed using 130 medication messages anonymously submitted by 16 volunteers via a website. System output was compared with manually tagged messages. Verified medication names, medication terms, and action terms reached high F-measures of 91.3%, 94.7%, and 90.4%, respectively. The overall medication name F-measure was 79.8%, and the medication action term F-measure was 90%. Other studies have demonstrated systems that successfully extract medication information from clinical documents using semantic tagging, regular expression-based approaches, or a combination of both approaches. This evaluation demonstrates the feasibility of extracting medication information from patient-generated medication messages.

M2-F1 in flight on tow line

NASA Technical Reports Server (NTRS)

1964-01-01

The M2-F1 Lifting Body is seen here under tow at the Flight Research Center (later redesignated the Dryden Flight Research Center), Edwards, California. The wingless, lifting-body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Flight Research Center management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The M2-F1 project had limited goals. They were to show that a piloted lifting body could be built, that it could not only fly but be controlled in flight, and that it could make a successful landing. While the M2-F1 did prove the concept, with a wooden fuselage and fixed landing gear, it was far from an operational spacecraft. The next step in the lifting-body development was to build a heavyweight, rocket-powered vehicle that was more like an operational lifting body, albeit one without the thermal protection system that would be needed for reentry into the atmosphere from space at near-orbital speeds. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. These initial tests produced enough flight data about the M2-F1 to proceed with flights behind a NASA C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Complexity and Pilot Workload Metrics for the Evaluation of Adaptive Flight Controls on a Full Scale Piloted Aircraft

NASA Technical Reports Server (NTRS)

Hanson, Curt; Schaefer, Jacob; Burken, John J.; Larson, David; Johnson, Marcus

2014-01-01

Flight research has shown the effectiveness of adaptive flight controls for improving aircraft safety and performance in the presence of uncertainties. The National Aeronautics and Space Administration's (NASA)'s Integrated Resilient Aircraft Control (IRAC) project designed and conducted a series of flight experiments to study the impact of variations in adaptive controller design complexity on performance and handling qualities. A novel complexity metric was devised to compare the degrees of simplicity achieved in three variations of a model reference adaptive controller (MRAC) for NASA's F-18 (McDonnell Douglas, now The Boeing Company, Chicago, Illinois) Full-Scale Advanced Systems Testbed (Gen-2A) aircraft. The complexity measures of these controllers are also compared to that of an earlier MRAC design for NASA's Intelligent Flight Control System (IFCS) project and flown on a highly modified F-15 aircraft (McDonnell Douglas, now The Boeing Company, Chicago, Illinois). Pilot comments during the IRAC research flights pointed to the importance of workload on handling qualities ratings for failure and damage scenarios. Modifications to existing pilot aggressiveness and duty cycle metrics are presented and applied to the IRAC controllers. Finally, while adaptive controllers may alleviate the effects of failures or damage on an aircraft's handling qualities, they also have the potential to introduce annoying changes to the flight dynamics or to the operation of aircraft systems. A nuisance rating scale is presented for the categorization of nuisance side-effects of adaptive controllers.

27 CFR 21.53 - Formula No. 27-A.

Code of Federal Regulations, 2012 CFR

2012-04-01

...-five pounds of camphor, U.S.P., and 1 gallon of clove oil, N.F. (b) Authorized uses. (1) As a solvent... other biocides. (2) Miscellaneous uses: 812.Product development and pilot plant uses (own use only). ...

27 CFR 21.53 - Formula No. 27-A.

Code of Federal Regulations, 2011 CFR

2011-04-01

...-five pounds of camphor, U.S.P., and 1 gallon of clove oil, N.F. (b) Authorized uses. (1) As a solvent... other biocides. (2) Miscellaneous uses: 812.Product development and pilot plant uses (own use only). ...

27 CFR 21.53 - Formula No. 27-A.

Code of Federal Regulations, 2010 CFR

2010-04-01

...-five pounds of camphor, U.S.P., and 1 gallon of clove oil, N.F. (b) Authorized uses. (1) As a solvent... other biocides. (2) Miscellaneous uses: 812.Product development and pilot plant uses (own use only). ...

Unmanned Aircraft Pilot Medical Certification Requirements

DTIC Science & Technology

2007-02-01

Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified Unclassified 14 Form DOT F 1700.7 (8-72) Reproduction of completed...and hypnotics , anxiolytics, marijuana, cocaine, opiods, amphetamines, hallucinogens, and other psychoactive drugs or chemicals.) Disqualifying

Astronaut Richard Gordon walks away from Pad 19 following postponement

NASA Image and Video Library

1966-09-10

S66-50775 (10 Sept. 1966) --- Astronaut Richard F. Gordon Jr., pilot, walks away from Pad 19 following postponement of the Gemini-11 spaceflight. The mission was rescheduled for Sept. 12, 1966. Photo credit: NASA

Pre-compensation combined with TS-aided and ISFA-enhanced scheme for UWB system

NASA Astrophysics Data System (ADS)

He, Jing; Xiang, Changqing; Long, Fengting; Wu, Kaiquan; Chen, Lin

2017-08-01

In this paper, a pre-compensation combined with training sequence (TS)-aided and intra-symbol frequency-domain averaging (ISFA)-enhanced scheme is proposed to improve the transmission performance in 64-quadrature amplitude modulation multiband orthogonal-frequency-division-multiplexing ultra-wide band over fiber (64QAM MB-OFDM UWBoF) system. We theoretically analyze and experimentally demonstrate that the proposed scheme is suitable for the 64QAM MB-OFDM UWBoF system in contrast with two other cases: (I) only pilot-aided channel estimation and (II) pilot-aided and pre-compensation combined with ISFA-enhanced channel estimation. The experimental results demonstrate that the performance of system with the proposed scheme can be improved by about 1.25 dB and 0.37 dB compared with the case I and the case II, respectively, at the BER of 3.8×10-3 after 70 km transmission in standard single mode fiber (SSMF).

Increase of frontal neuronal activity in chronic neglect after training in virtual reality.

PubMed

Ekman, U; Fordell, H; Eriksson, J; Lenfeldt, N; Wåhlin, A; Eklund, A; Malm, J

2018-05-16

A third of patients with stroke acquire spatial neglect associated with poor rehabilitation outcome. New effective rehabilitation interventions are needed. Scanning training combined with multisensory stimulation to enhance the rehabilitation effect is suggested. In accordance, we have designed a virtual-reality based scanning training that combines visual, audio and sensori-motor stimulation called RehAtt ® . Effects were shown in behavioural tests and activity of daily living. Here, we use fMRI to evaluate the change in brain activity during Posner's Cuing Task (attention task) after RehAtt ® intervention, in patients with chronic neglect. Twelve patients (mean age = 72.7 years, SD = 6.1) with chronic neglect (persistent symptoms >6 months) performed the interventions 3 times/wk during 5 weeks, in total 15 hours. Training effects on brain activity were evaluated using fMRI task-evoked responses during the Posner's cuing task before and after the intervention. Patients improved their performance in the Posner fMRI task. In addition, patients increased their task-evoked brain activity after the VR interventions in an extended network including pre-frontal and temporal cortex during attentional cueing, but showed no training effects during target presentations. The current pilot study demonstrates that a novel multisensory VR intervention has the potential to benefit patients with chronic neglect in respect of behaviour and brain changes. Specifically, the fMRI results show that strategic processes (top-down control during attentional cuing) were enhanced by the intervention. The findings increase knowledge of the plasticity processes underlying positive rehabilitation effects from RehAtt ® in chronic neglect. © 2018 John Wiley & Sons A/S. Published by John Wiley & Sons Ltd.

Retention-oxidation-adsorption process for emergent treatment of organic liquid spills.

PubMed

Liu, Xianjun; Li, Yu; Zhang, Xingwang; Lei, Lecheng

2011-11-15

The feasibility and effectiveness of retention-oxidation-adsorption process (ROA) for the elimination of organic contaminants induced by chemical accidents were investigated in this study. Organobentonites (DTMA-, TTA-, CTMA- and OTMA-bentonite), potassium ferrate (Fe(VI)), ozone and granular activated carbon (GAC) were used as rapid and efficient materials in the treatment and recovery of organic liquid spills. Results indicated that the retention capacities of organobentonites (especially CTMA-bentonite) were much higher than that of natural bentonite towards the chosen organic compounds. Additionally, pH, oxidant dosage, initial concentration of contaminant and chemical structure had significant influences on the effectiveness of the oxidation process. In a pilot-scale experiment, the ferrate/GAC (F/G) and ozone/GAC (O/G) processes made a comparatively good performance in the treatment of wastewater containing aniline or nitrobenzene, with the removal efficiencies of the contaminants greater than 80%. Overall, the ROA process showed a high efficiency and steady operation in the removal of hazardous organic liquids and subsequent clean up of the contaminated site. Crown Copyright © 2011. Published by Elsevier B.V. All rights reserved.

The Brain's Response to Digital Math Apps: A Pilot Study Examining Children's Cortical Responses during Touch-Screen Interactions

ERIC Educational Resources Information Center

Baker, Joseph M.; Moyer-Packenham, Patricia S.; Tucker, Stephen I.; Shumway, Jessica F.; Jordan, Kerry E.; Gillam, Ronald B.

2018-01-01

Functional near-infrared spectroscopy (fNIRS) is an easy to use neuroimaging technique that is portable and maintains a liberal tolerance to movement. As such, fNIRS represents an ideal tool to observe children's neural activity as they engage in real-world classroom activities, such as the interaction with digital math apps on an iPad. Here, we…

F-15E Beddown at Seymour Johnson AFB, North Carolina

DTIC Science & Technology

1988-03-01

fuel tanks for extended range, an expanded weapons capacity, and LANTIRN for enhanced night operations. Procurement of 392 F-15Es is required to address...target recognizer. These capabilities permit the pilot of a single or dual seat aircraft to deliver guided and 1.1-i unguided weapons under day/night...functional subsystems. The targeting pod permits day or night precision delivery of conventional, laser guided bomb, and electro-optical weapons . The

Air Force/Industry F-35/F-22 Technology Interchange Workshop for Small Business Innovation Research (SBIR): Plenary Session

DTIC Science & Technology

2007-11-28

order to optimize pilot performance in the JSF tactical maneuvering environment • Binaural Capture and Synthesis of Ambient Soundscapes –Create a...technique for capturing and replicating ambient soundscapes , and use the technique to statistically model ambient soundscapes for a wide range of...Actuator (HTCA) • Binaural Capture and Synthesis of Ambient Soundscapes • High Temperature PM Actuator Motor • Manufacturing of New Active Noise

M2-F1 on lakebed with pilots Milt Thompson, Chuck Yeager, Don Mallick, and Bruce Peterson

NASA Technical Reports Server (NTRS)

1963-01-01

After the initial M2-F1 airtow flights, the NASA Flight Research Center used the vehicle to check out other pilots. Bruce Peterson was scheduled to take over as the M2-F1 project pilot from Milt Thompson, while Don Mallick was to be his backup. Col. (later Brig. Gen.) Charles (Chuck) Yeager, then commandant of the Air Force's Aerospace Research Pilots School, wanted to evaluate a possible lifting-body trainer for the school. This photo shows all of these distinguished pilots on or in the M2-F1, with Col. Yeager in the pilot's seat. The lifting body concept evolved in the mid-1950s as researchers considered alternatives to ballistic reentries of piloted space capsules. The designs for hypersonic, wingless vehicles were on the boards at NASA Ames and NASA Langley facilities, while the US Air Force was gearing up for its Dyna-Soar program, which defined the need for a spacecraft that would land like an airplane. Despite favorable research on lifting bodies, there was little support for a flight program. Dryden engineer R. Dale Reed was intrigued with the lifting body concept, and reasoned that some sort of flight demonstration was needed before wingless aircraft could be taken seriously. In February 1962, he built a model lifting body based upon the Ames M2 design, and air-launched it from a radio controlled 'mothership.' Home movies of these flights, plus the support of research pilot Milt Thompson, helped pursuade the facilities director, Paul Bikle, to give the go-ahead for the construction of a full-scale version, to be used as a wind-tunnel model and possibly flown as a glider. Comparing lifting bodies to space capsules, an unofficial motto of the project was, 'Don't be Rescued from Outer Space--Fly Back in Style.' The construction of the M2-F1 was a joint effort by Dryden and a local glider manufacturer, the Briegleb Glider Company. The budget was $30,000. NASA craftsmen and engineers built the tubular steel interior frame. Its mahogany plywood shell was hand-made by Gus Briegleb and company. Ernie Lowder, a NASA craftsman who had worked on the Howard Hughes 'Spruce Goose,' was assigned to help Briegleb. The prototype of a 21st Century spacecraft required the fabrication of hundreds of small wooden parts meticulously nailed and glued together. It was a product of craftsmanship that was nearly obsolete in the 1940s. Final assembly of the remaining components (including aluminum tail surfaces, push rod controls, and landing gear from a Cessna 150) was done back at the NASA facility. In the meantime, other NASA engineers devised a special M2-F1 flight simulator, and a hot rod shop near Long Beach souped-up a Pontiac convertible to be used as the lifting body ground-tow vehicle. The M2-F1 did not have ailerons. Instead, it had elevons which were attached to each of the two rudders. A large flap on the trailing edge of the body acted as an elevator. This unconventional arrangement prompted the engineers to rethink the flight control system as well. They eventually devised two schemes. One system was fairly traditional. It used rudder pedal inputs to move the rudders for yaw control, and stick inputs to provide differential deflections of the elevons for roll. The other system used stick inputs to control the rudders for yaw, while rudder pedal deflections moved the elevons for roll. Milt Thompson tried both systems in the simulator and surprised the design team when he said he preferred system number two. He reasoned that although sideslip delayed roll (which was a result of dihedral effect), the roll rate was twice as high using the rudders instead of the elevons. He said he would rather have the higher roll rates available to him if needed, while the slip could be overcome with proper piloting technique. This was the system that Thompson practiced on the simulator, and he used it during the initial auto tows. Auto tows were done using a 1000 foot rope fastened to the NASA Pontiac. Rogers Dry Lake provided miles of unobstructed motoring. On April 5, 1963, Thompson lifted the M2-F1's nose off of the ground for the first time on tow. Speed was 86 miles per hour. The little craft seemed to bounce uncontrollably back and forth on the main landing gear, and stopped when he lowered the nose to the ground. He tried again, but each time with the same results. He felt it was a landing gear problem that could have caused the aircraft to roll on its back if he had lifting the main gear off of the ground. Looking at movies of the tests, engineers decided that the bouncing was probably caused by unwanted rudder movements. Flight control system number two was replaced in favor of number one, and it never bounced again. Speeds on tow inched up to 110 miles per hour, which allowed Thompson to climb to about 20 feet, then glide for about 20 seconds after releasing the line. That was the most that could be expected during an auto tow. In the spring of 1963 the M2-F1 was shipped to Ames Research Center, where it was mounted on twenty-foot poles inside the 40-foot by 80-foot wind tunnel. For two weeks, Thompson and engineers Ed Browne and Dick Eldredge took turns 'flying' it as air blasted by at a 135 miles per hour. They learned more about its flying qualities, and accumulated important data for the upcoming aero tows. A NASA C-47 was used for all of the aero tows. The first was on August 16, 1963. The M2-F1 had recently been equipped with an ejection seat, small rockets in the tail to extend the landing flare for about 5 seconds (if needed), and Thompson prepared for the flight with a few more tows behind the Pontiac. Forward visibility in the M2-F1 was very limited on tow, requiring Thompson to fly about 20 feet higher than the C-47 so he could see the plane through the nose window. Towing speed was about 100 miles per hour. Tow release was at 12,000 feet. The lifting body descended at an average rate of about 3,600 feet-per-minute. At 1,000 feet above the ground, the nose was lowered to increase speed to about 150 mph, flare was at 200 feet from a 20 degree dive. The landing was smooth, and the lifting body program was on its way. The M2-F1 was flown until August 16, 1966. It proved the lifting body concept and lead the way for subsequent, metal 'heavyweight' designs. Chuck Yeager, Bruce Peterson, Bill Dana, Jerry Gentry, James Wood, Don Sorlie, Fred Haise, Joe Engle, and Don Mallick also flew the M2-F1. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and to the Air Force's X-24 program, for which the vehicles were built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program.

EVALUATION OF FGD DRY INJECTION SORBENTS AND ADDITIVES - VOLUME 2 - PILOT PLANT EVALUATION OF HIGH REACTIVITY SORBENTS

EPA Science Inventory

The report describes a mini-pilot test program to investigate potential new sorbents and processes for dry SO2 removal. Initial tests showed that the 85 cu m/h pilot plant could be used successfully to evaluate both spray dryer and dry injection processes using traditional calciu...

An Exploration of the Importance of Piloting and Access as Action Research

ERIC Educational Resources Information Center

Gudmundsdottir, Greta Bjork; Brock-Utne, Birgit

2010-01-01

In this article we illustrate how the piloting process has influenced two widely different studies within the educational sciences. These studies differ in design but have as a common denominator that they used piloting methods in their preparatory process. They are also similar in the intention of the main researchers of conducting research with…

F-18 sodium fluoride PET/CT does not effectively image myocardial inflammation due to suspected cardiac sarcoidosis.

PubMed

Weinberg, Richard L; Morgenstern, Rachelle; DeLuca, Albert; Chen, Jennifer; Bokhari, Sabahat

2017-12-01

Sarcoidosis is an inflammatory disorder of unknown etiology that can involve the heart. While effective in imaging cardiac sarcoidosis, F-18 fluorodeoxyglucose (FDG) PET/CT often shows non-specific myocardial uptake. F-18 sodium fluoride (NaF) has been used to image inflammation in coronary artery plaques and has low background myocardial uptake. Here, we evaluated whether F-18 NaF can image myocardial inflammation due to clinically suspected cardiac sarcoidosis. We performed a single institution pilot study testing if F-18 NaF PET/CT can detect myocardial inflammation in patients with suspected cardiac sarcoidosis. Patients underwent cardiac PET/CT with F-18 FDG as part of their routine care and subsequently received an F-18 NaF PET/CT scan. Three patients underwent F-18 FDG and F-18 NaF imaging. In all patients, there was F-18 FDG uptake consistent with cardiac sarcoidosis. The F-18 NaF PET/CT scans showed no myocardial uptake. In this small preliminary study, PET/CT scan using F-18 NaF does not appear to detect myocardial inflammation caused by suspected cardiac sarcoidosis.

The effects of Above Real-Time Training (ARTT) in an F-16 simulator

NASA Technical Reports Server (NTRS)

Guckenberger, Dutch; Stanney, Kay; Lane, Norman E.

1994-01-01

In this application of above real-time training (ARTT), 24 mission-capable F-16 pilots performed three tasks on a part-task F-16A flight simulator under varying levels of time compression (i.e., 1.0x, 1.5x, 2.0x, and random). All subjects were then tested in a real-time (1.0x) environment. The three tasks under study were an emergency procedure (EP) task, a one versus two air combat maneuvering (ACM) task, and a stern conversion or air intercept task. All ARTT pilots performed the EP task with 28 percent greater accuracy and were better at dealing with a simultaneous MIG threat, reflected by a six-fold increase in the number of MIG kills compared to a real-time control group. In the stern conversion task, there were no statistical differences between groups. In the ACM task, those pilots trained in the mixed time accelerations were faster to acquire lock and were faster to kill both MIG threats than the other groups. These findings are generally consistent with previous findings that show positive effects of task variations (including time variations) during training. Also discussed are related research findings that support the benefits of ARTT and ARTT's impact on emergency procedure training. Further, a synthesis of multidiscipline research outlining the underlying theoretical basis for ARTT is presented. A proposed model of ARTT based on an analogy to Einstein's theory of special relativity is suggested. Conclusions and an outline of future research directions are presented. Successful current commercialization efforts are related as well as future efforts.

THE PRENATAL PARENTAL REFLECTIVE FUNCTIONING QUESTIONNAIRE: EXPLORING FACTOR STRUCTURE AND CONSTRUCT VALIDITY OF A NEW MEASURE IN THE FINN BRAIN BIRTH COHORT PILOT STUDY.

PubMed

Pajulo, Marjukka; Tolvanen, Mimmi; Karlsson, Linnea; Halme-Chowdhury, Elina; Öst, Camilla; Luyten, Patrick; Mayes, Linda; Karlsson, Hasse

2015-01-01

Parental reflective functioning (PRF) is the capacity to focus on experience and feelings in oneself and in the child. Individual differences in PRF reportedly affect child attachment and socioemotional development. In this study, we report work on developing a questionnaire to assess PRF during pregnancy (Prenatal Parental Reflective Functioning Questionnaire; P-PRFQ). The factor structure of the 33-item version of the P-PRFQ was explored using pilot study data from the Finn Brain Birth Cohort Study (n = 124 mothers, n = 82 fathers). Construct validity was assessed against the Pregnancy Interview (PI; A. Slade, L. Grunebaum, L. Huganir, & M. Reeves, 1987, 2002, 2011) in a subsample of 29 mothers from the same pilot sample. Exploratory and confirmatory factor analysis resulted in a 14-item P-PRFQ, with three factors which seem to capture relevant aspects of prenatal parental mentalization-F1: "Opacity of mental states," F2: "Reflecting on the fetus-child," and F3: "The dynamic nature of the mental states." Functioning of the factor structure was further tested in the large cohort with 600 mothers and 600 fathers. Correlations with the PI result were high, both regarding total and factor scores of the P-PRFQ. Cost-effective tools to assess key areas of early parenting are needed for both research and clinical purposes. The 14-item P-PRFQ seems to be an applicable and promising new tool for assessing very early parental mentalizing capacity. © 2015 Michigan Association for Infant Mental Health.

A double-blind randomized controlled pilot trial examining the safety and efficacy of therapeutic touch in premature infants.

PubMed

Whitley, Julie Anne; Rich, Bonnie L

2008-12-01

To explore the hypothesis that nontouch therapy such as therapeutic touch (TT) reduces stress to a clinically important degree and is safe to use in preterm infants. A pilot randomized, double-blind, controlled trial. Two groups of 10 infants were enrolled and randomly assigned to treatment or nontreatment groups. Gestational age was less than 29 weeks. Demographic descriptions of the 2 groups were statistically similar. The observer and staff were blinded to assignment; the TT practitioner was blinded to observed measurements. Each infant received either TT or no therapeutic touch (NTT) for 5 minutes on 3 consecutive days at the same time of day, behind a curtain. Heart period variability (HPV) was measured 5 minutes before, during, and after the treatment phase. Examination of the parameters of oxygen saturation and episodes of apnea demonstrated no increase in adverse events in TT group compared with NTT group. Repeated-measures multivariate analysis of variance on HPV revealed differences in the interaction of group assignment with low-frequency, high-frequency, and low-to-high- frequency ratio interaction (F2,143 = 8.076, P = .000) and for group, day, and low-frequency, high-frequency, and low-to-high-frequency ratio (F2,288 = 3.146, P = .015), and in the posttreatment time period (F1,16 = 6.259, P = .024), reflective of greater parasympathetic activity in TT group. In this pilot trial, HPV showed an increase for the TT group compared with the NTT group. The study reveals no adverse effects of TT in preterm infants.

Installation Restoration General Environmental Technology Development. Task II. Pilot Investigation of Low Temperature Thermal Stripping of Volatile Organic Compounds (VOC’s) from Soil. Volume 2. Appendices

DTIC Science & Technology

1986-06-01

15 celitimeterh Ca p,.ragraph. ifllCll (.q f oifice n nabe US (2) At the end of eachl operating da:Y. or at least once eve’ry 24-huur perlod while...fn Droc64 os ~S"m 0oftfe SOW .0 C10" onn odcoo.f o fOE ar6t1.foW Ireeffflso wn from* tൈ 14 11100 cowf o.,cess A0 orion’.. C~odaCf T 9031 Sy -onoducf

EC63-00221

NASA Image and Video Library

1963-10-24

All three NASA F-104N's fly in formation. Aircraft numbers 011, 012 and 013. These would be changed to 811, 812 and 813 in 1965. Pilots are Bruce Peterson in 011, Milt Thompson in 012 and Joe Walker in 013. October 24, 1963

A Pilot Study Treatment of Malignant Tumors Using [18F] Fluorodeoxyglucose (FDG)

ClinicalTrials.gov

2018-05-08

Radiosensitive Stage IV Solid and Hematological Tumors With High FDG Uptake Not Responding to Standard of Care; Lung Cancer, Head and Neck Cancer, Breast Cancer, Gastric Cancer, Pancreatic Cancer, Colon Cancer, Lymphomas, Sarcomas, Etc

Process and apparatus for igniting a burner in an inert atmosphere

DOEpatents

Coolidge, Dennis W.; Rinker, Franklin G.

1994-01-01

According to this invention there is provided a process and apparatus for the ignition of a pilot burner in an inert atmosphere without substantially contaminating the inert atmosphere. The process includes the steps of providing a controlled amount of combustion air for a predetermined interval of time to the combustor then substantially simultaneously providing a controlled mixture of fuel and air to the pilot burner and to a flame generator. The controlled mixture of fuel and air to the flame generator is then periodically energized to produce a secondary flame. With the secondary flame the controlled mixture of fuel and air to the pilot burner and the combustion air is ignited to produce a pilot burner flame. The pilot burner flame is then used to ignited a mixture of main fuel and combustion air to produce a main burner flame. The main burner flame then is used to ignite a mixture of process derived fuel and combustion air to produce products of combustion for use as an inert gas in a heat treatment process.

Introduction to cognitive processes of expert pilots.

PubMed

Adams, R J; Ericsson, A E

2000-10-01

This report addresses the historical problem that a very high percentage of accidents have been classified as involving "pilot error." Through extensive research since 1977, the Federal Aviation Administration determined that the predominant underlying cause of these types of accidents involved decisional problems or cognitive information processing. To attack these problems, Aeronautical Decision Making (ADM) training materials were developed and tested for ten years. Since the publication of the ADM training manuals in 1987, significant reductions in human performance error (HPE) accidents have been documented both in the U.S. and world wide. However, shortcomings have been observed in the use of these materials for recurrency training and in their relevance to more experienced pilots. The following discussion defines the differences between expert and novice decision makers from a cognitive information processing perspective, correlates the development of expert pilot cognitive processes with training and experience, and reviews accident scenarios which exemplify those processes. This introductory material is a necessary prerequisite to an understanding of how to formulate expert pilot decision making training innovations; and, to continue the record of improved safety through ADM training.

Investigation of the Influence of Air Defense Artillery on Combat Pilot Suppression and Attrition Management Practices

DTIC Science & Technology

1992-05-01

low as possible for better accuracy." (Mamyer, 1979, p. 280) "With the advent of the jamming pod, F-105D flights could once again penetrate at medium...or pumpkins coming at the aircraft." (Fulbrook, 1986a, pp. 43-44) "Generally, there are two types of aviators when bullets start flying. All of us... jamming ; ECM and flare equipment onboard * Importance of targets (both to cummand and control and to pilot) and necessity of achieving target damage

STS-79 Commander Readdy and Pilot Wilcutt at slidewire

NASA Technical Reports Server (NTRS)

1996-01-01

Clad in their launch/entry suits, STS-79 Commander William F. Readdy (left) and Pilot Terrence W. Wilcutt test the fit of a slidewire basket on the emergency egress system at Launch Pad 39A. The six astronauts assigned to the fourth Shuttle-Mir docking flight are completing Terminal Countdown Demonstration Test (TCDT) activities. A dress rehearsal for launch, the TCDT includes emergency egress training at the launch pad and culminates with a simulated countdown. The Space Shuttle Atlantis is undergoing preparations for liftoff on STS-79 no earlier than Sept. 12.

Pilot Overmyer looks over food selections and experiments with beverage

NASA Image and Video Library

1982-11-16

STS005-07-255 (19 Nov. 1982) --- Astronaut Robert F. Overmyer, STS-5 pilot, using beverage container and drinking straw secured in meal tray assembly (ASSY), experiments with microgravity characteristics of liquid on middeck in front of forward lockers. Overmyer also looks over packages of food attached to middeck lockers in meal tray assemblies. Carry-on food warmer appears overhead and other meal tray assemblies, personal hygiene mirror assembly, personal hygiene kit, and portrait of G.W.S. Abbey, Johnson Space Center's (JSC) Director of Flight Operations, appear on lockers. Photo credit: NASA

Apollo 12 Mission image - View of lunar surface mound

NASA Image and Video Library

1969-11-19

AS12-46-6795 (19-20 Nov. 1969) --- A view of the lunar surface in the vicinity of the Apollo 12 lunar landing site, photographed during the extravehicular activity (EVA) of astronauts Charles Conrad Jr., commander, and Alan L. Bean, lunar module pilot. Conrad and Bean encountered the odd, anthill-shaped mound during their lunar traverse. The two descended in the Apollo 12 Lunar Module (LM) to explore the moon, while astronaut Richard F. Gordon Jr., command module pilot, remained with the Command and Service Modules (CSM) in lunar orbit.

Saturn Apollo Program

NASA Image and Video Library

1969-01-01

The Apollo 12 three-man crew pictured left to right are: Astronauts Charles Conrad, Spacecraft Commander; Richard F. Gordon, pilot of the Command Module `Yankee Clipper'; and Alan L. Bean, pilot of the Lunar Module `Intrepid'. Activities of astronauts Conrad and Bean on the lunar soil included setting out experiments, finding the unmarned Surveyor 3 that landed on the Moon on April 19, 1967, and collecting 75 pounds (34 kilograms) of rock samples. The second mission of the manned lunar landing and return to Earth, Apollo 12 lifted off on November 14, 1969.

APOLLO XII - LAUNCH DAY ACTIVITIES - LAUNCH COMPLEX 39A - KSC

NASA Image and Video Library

1969-11-14

S69-58880 (14 Nov. 1969) --- Astronaut Alan L. Bean, Apollo 12 lunar module pilot, suits up in the Kennedy Space Center's (KSC) Manned Spacecraft Operations Building during the Apollo 12 prelaunch countdown. Minutes later astronauts Bean; Charles Conrad Jr., commander; and Richard F. Gordon Jr., command module pilot, rode a special transport van over to Pad A, Launch Complex 39, where their spacecraft awaited. The Apollo 12 liftoff occurred at 11:22 a.m. (EST), Nov. 14, 1969. Apollo 12 is the United States' second lunar landing mission.

Astronaut Alan Bean holds Special Environmental Sample Container

NASA Image and Video Library

1969-11-20

AS12-49-7278 (19-20 Nov. 1969) --- Astronaut Alan L. Bean holds a Special Environmental Sample Container filled with lunar soil collected during the extravehicular activity (EVA) in which astronauts Charles Conrad Jr., commander, and Bean, lunar module pilot, participated. Conrad, who took this picture, is reflected in Bean's helmet visor. Conrad and Bean descended in the Apollo 12 Lunar Module (LM) to explore the lunar surface while astronaut Richard F. Gordon Jr., command module pilot, remained with the Command and Service Modules (CSM) in lunar orbit. Photo credit: NASA

Apollo 12 Mission image - Dark view of Astronaut Alan L. Bean climbing down the ladder of the Lunar Module (LM)

NASA Image and Video Library

1969-11-19

AS12-46-6726 (19 Nov. 1969) --- Astronaut Alan L. Bean, lunar module pilot for the Apollo 12 mission, starts down the ladder of the Lunar Module (LM) to join astronaut Charles Conrad Jr., mission commander, in extravehicular activity (EVA). While astronauts Conrad and Bean descended in the LM "Intrepid" to explore the Ocean of Storms region of the moon, astronaut Richard F. Gordon Jr., command module pilot, remained with the Command and Service Modules (CSM) "Yankee Clipper" in lunar orbit.

Precursors to Gender Attitudes in the Air Cadet Gliding Population

DTIC Science & Technology

2011-04-01

Hendriks (2008) révélait également une différence de traitement entre les hommes et les femmes dans le contexte de la formation de pilotage de ...Toutefois, les recherches indiquent aussi qu’en comparaison des hommes , les élèves pilotes de sexe féminin peuvent saisir plus rapidement les...menace du stéréotype et qui mesure le rendement des hommes et des femmes pilotes est la prochaine étape logique pour étudier l’écart entre les hommes

EC97-44354-2

NASA Image and Video Library

1997-12-16

An image of the F-16XL #1 during its functional flight check of the Digital Flight Control System (DFCS) on December 16, 1997. The mission was flown by NASA research pilot Dana Purifoy, and lasted 1 hour and 25 minutes. The tests included pilot familiarly, functional check, and handling qualities evaluation maneuvers to a speed of Mach 0.6 and 300 knots. Purifoy completed all the briefed data points with no problems, and reported that the DFCS handled as well, if not better than the analog computer system that it replaced.

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

Apollo 12 crewmen participate in water egress training

NASA Image and Video Library

1969-09-20

S69-52990 (20 Sept. 1969) --- The three prime crew men of the Apollo 12 lunar landing mission participate in water egress training in the Gulf of Mexico. They have just egressed the Apollo Command Module (CM) trainer. The man standing at left is a Manned Spacecraft Center's (MSC) swimmer. The crew men await in life raft for helicopter pickup. All four persons are wearing biological isolation garments. Participating in the training exercise were astronauts Charles Conrad Jr., commander; Richard F. Gordon Jr., command module pilot; and Alan L. Bean, lunar module pilot.

A Low Cost Simulation System to Demonstrate Pilot Induced Oscillation Phenomenon

NASA Technical Reports Server (NTRS)

Ali, Syed Firasat

1997-01-01

A flight simulation system with graphics and software on Silicon Graphics computer workstations has been installed in the Flight Vehicle Design Laboratory at Tuskegee University. The system has F-15E flight simulation software from NASA Dryden which uses the graphics of SGI flight simulation demos. On the system, thus installed, a study of pilot induced oscillations is planned for future work. Preliminary research is conducted by obtaining two sets of straight level flights with pilot in the loop. In one set of flights no additional delay is used between the stick input and the appearance of airplane response on the computer monitor. In another set of flights, a 500 ms additional delay is used. The flight data is analyzed to find cross correlations between deflections of control surfaces and response of the airplane. The pilot dynamics features depicted from cross correlations of straight level flights are discussed in this report. The correlations presented here will serve as reference material for the corresponding correlations in a future study of pitch attitude tracking tasks involving pilot induced oscillations.

Hidden Markov Models as a tool to measure pilot attention switching during simulated ILS approaches

DOT National Transportation Integrated Search

2003-04-14

The pilot's instrument scanning data contain information about not only the pilot's eye movements, but also the pilot's : cognitive process during flight. However, it is often difficult to interpret the scanning data at the cognitive level : because:...

M2-F1 lifting body aircraft on a flatbed truck

NASA Technical Reports Server (NTRS)

1997-01-01

After the grounding of the M2-F1 in 1966, it was kept in outside storage on the Dryden complex. After several years, its fabric and plywood structure was damaged by the sun and weather. Restoration of the vehicle began in February 1994 under the leadership of NASA retiree Dick Fischer, with other retirees who had originally worked on the M2-F1's construction and flight research three decades before also participating. The photo shows the now-restored M2-F1 returning to the site of its flight research, now called the Dryden Flight Research Center, on 22 August 1997. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, NASA Flight Research Center (later Dryden Flight Research Center, Edwards, CA) management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

A pilot study for determining the optimal operation condition for simultaneously controlling the emissions of PCDD/Fs and PAHs from the iron ore sintering process.

PubMed

Chen, Yu-Cheng; Tsai, Perng-Jy; Mou, Jin-Luh; Kuo, Yu-Chieh; Wang, Shih-Min; Young, Li-Hao; Wang, Ya-Fen

2012-09-01

In this study, the cost-benefit analysis technique was developed and incorporated into the Taguchi experimental design to determine the optimal operation combination for the purpose of providing a technique solution for controlling both emissions of PCDD/Fs and PAHs, and increasing both the sinter productivity (SP) and sinter strength (SS) simultaneously. Four operating parameters, including the water content, suction pressure, bed height, and type of hearth layer, were selected and all experimental campaigns were conducted on a pilot-scale sinter pot to simulate various sintering operating conditions of a real-scale sinter plant. The resultant optimal combination could reduce the total carcinogenic emissions arising from both emissions of PCDD/Fs and PAHs by 49.8%, and increase the sinter benefit associated with the increase in both SP and SS by 10.1%, as in comparison with the operation condition currently used in the real plant. The ANOVA results indicate that the suction pressure was the most dominant parameter in determining the optimal operation combination. The above result was theoretically plausible since the higher suction pressure provided more oxygen contents leading to the decrease in both PCDD/F and PAH emissions. But it should be noted that the results obtained from the present study were based on pilot scale experiments, conducting confirmation tests in a real scale plant are still necessary in the future. Copyright © 2012 Elsevier Ltd. All rights reserved.

Whole-body biodistribution and brain PET imaging with [18F]AV-45, a novel amyloid imaging agent--a pilot study.

PubMed

Lin, Kun-Ju; Hsu, Wen-Chuin; Hsiao, Ing-Tsung; Wey, Shiaw-Pyng; Jin, Lee-Way; Skovronsky, Daniel; Wai, Yau-Yau; Chang, Hsiu-Ping; Lo, Chuan-Wei; Yao, Cheng Hsiang; Yen, Tzu-Chen; Kung, Mei-Ping

2010-05-01

The compound (E)-4-(2-(6-(2-(2-(2-(18)F-fluoroethoxy)ethoxy)ethoxy) pyridin-3-yl)vinyl)-N-methylbenzenamine ([(18)F]AV-45) is a novel radiopharmaceutical capable of selectively binding to beta-amyloid (A beta) plaques. This pilot study reports the safety, biodistribution, and radiation dosimetry of [(18)F]AV-45 in human subjects. In vitro autoradiography and fluorescent staining of postmortem brain tissue from patients with Alzheimer's disease (AD) and cognitively healthy subjects were performed to assess the specificity of the tracer. Biodistribution was assessed in three healthy elderly subjects (mean age: 60.0+/-5.2 years) who underwent 3-h whole-body positron emission tomography (PET)/computed tomographic (CT) scans after a bolus injection of 381.9+/-13.9 MBq of [(18)F]AV-45. Another six subjects (three AD patients and three healthy controls, mean age: 67.7+/-13.6 years) underwent brain PET studies. Source organs were delineated on PET/CT. All subjects underwent magnetic resonance imaging (MRI) for obtaining structural information. In vitro autoradiography revealed exquisitely high specific binding of [(18)F]AV-45 to postmortem AD brain sections, but not to the control sections. There were no serious adverse events throughout the study period. The peak uptake of the tracer in the brain was 5.12+/-0.41% of the injected dose. The highest absorbed organ dose was to the gallbladder wall (184.7+/-78.6 microGy/MBq, 4.8 h voiding interval). The effective dose equivalent and effective dose values for [(18)F]AV-45 were 33.8+/-3.4 microSv/MBq and 19.3+/-1.3 microSv/MBq, respectively. [(18)F]AV-45 binds specifically to A beta in vitro, and is a safe PET tracer for studying A beta distribution in human brain. The dosimetry is suitable for clinical and research application. (c) 2010 Elsevier Inc. All rights reserved.

KSC-2011-2938

NASA Image and Video Library

2011-04-18

CAPE CANAVERAL, Fla. -- In the Training Auditorium at NASA's Kennedy Space Center in Florida the STS-133 crew signs autographs for Kennedy employees during a crew return event. From left are Commander Steve Lindsey, Pilot Eric Boe, Mission Specialists Michael Barratt, Steve Bowen, Alvin Drew (obscured) and Nicole Stott. The crew launched from Kennedy's Launch Pad 39A aboard space shuttle Discovery on its final flight on February 24, 2011 to the International Space Station. The crew delivered Robonaut 2 and the Permanent Multipurpose Module packed with supplies and critical spare parts on a 13-day mission. Discovery is being processed for retirement and will be displayed at the National Air and Space Museum's Steven F. Udvar-Hazy Center in Chantilly, Va. Photo credit: NASA/Kim Shiflett

STS-51 astronauts participate in emergency bailout training in WETF

NASA Image and Video Library

1993-03-24

S93-31929 (24 March 1993) --- The three mission specialists for NASA's STS-51 mission watch as a crewmate (out of frame) simulates a parachute jump into water during emergency bailout training exercises at the Johnson Space Center's Weightless Environment Training Facility (WET-F). Left to right are astronauts Daniel W. Bursch, Carl E. Walz and James H. Newman. Out of frame are astronauts Frank L. Culbertson and William F. Readdy, commander and pilot, respectively.

Radiotherapy volume delineation using dynamic [18F]-FDG PET/CT imaging in patients with oropharyngeal cancer: a pilot study.

PubMed

Silvoniemi, Antti; Din, Mueez U; Suilamo, Sami; Shepherd, Tony; Minn, Heikki

2016-11-01

Delineation of gross tumour volume in 3D is a critical step in the radiotherapy (RT) treatment planning for oropharyngeal cancer (OPC). Static [ 18 F]-FDG PET/CT imaging has been suggested as a method to improve the reproducibility of tumour delineation, but it suffers from low specificity. We undertook this pilot study in which dynamic features in time-activity curves (TACs) of [ 18 F]-FDG PET/CT images were applied to help the discrimination of tumour from inflammation and adjacent normal tissue. Five patients with OPC underwent dynamic [ 18 F]-FDG PET/CT imaging in treatment position. Voxel-by-voxel analysis was performed to evaluate seven dynamic features developed with the knowledge of differences in glucose metabolism in different tissue types and visual inspection of TACs. The Gaussian mixture model and K-means algorithms were used to evaluate the performance of the dynamic features in discriminating tumour voxels compared to the performance of standardized uptake values obtained from static imaging. Some dynamic features showed a trend towards discrimination of different metabolic areas but lack of consistency means that clinical application is not recommended based on these results alone. Impact of inflammatory tissue remains a problem for volume delineation in RT of OPC, but a simple dynamic imaging protocol proved practicable and enabled simple data analysis techniques that show promise for complementing the information in static uptake values.

Comprehensive Analysis of Two Downburst-Related Aircraft Accidents

NASA Technical Reports Server (NTRS)

Shen, J.; Parks, E. K.; Bach, R. E.

1996-01-01

Although downbursts have been identified as the major cause of a number of aircraft takeoff and landing accidents, only the 1985 Dallas/Fort Worth (DFW) and the more recent (July 1994) Charlotte, North Carolina, landing accidents provided sufficient onboard recorded data to perform a comprehensive analysis of the downburst phenomenon. The first step in the present analysis was the determination of the downburst wind components. Once the wind components and their gradients were determined, the degrading effect of the wind environment on the airplane's performance was calculated. This wind-shear-induced aircraft performance degradation, sometimes called the F-factor, was broken down into two components F(sub 1) and F(sub 2), representing the effect of the horizontal wind gradient and the vertical wind velocity, respectively. In both the DFW and Charlotte cases, F(sub 1) was found to be the dominant causal factor of the accident. Next, the aircraft in the two cases were mathematically modeled using the longitudinal equations of motion and the appropriate aerodynamic parameters. Based on the aircraft model and the determined winds, the aircraft response to the recorded pilot inputs showed good agreement with the onboard recordings. Finally, various landing abort strategies were studied. It was concluded that the most acceptable landing abort strategy from both an analytical and pilot's standpoint was to hold constant nose-up pitch attitude while operating at maximum engine thrust.

33 CFR 385.12 - Pilot projects.

Code of Federal Regulations, 2013 CFR

2013-07-01

... management, and wastewater reuse. The purpose of the pilot projects is to develop information necessary to... Processes § 385.12 Pilot projects. (a) The Plan includes pilot projects to address uncertainties associated...-Federal sponsor shall develop a Project Management Plan as described in § 385.24. (c) Project...

Astronaut Donn Eisele photographed during Apollo 7 mission

NASA Image and Video Library

1968-10-20

AS07-04-1600 (20 Oct. 1968) --- Astronaut Donn F. Eisele, Apollo 7 command module pilot, smiles through a heavy growth of beard as he is photographed during a momentary pause on the ninth day of the Apollo 7 mission.

Collegiate Aviation Review, 2001.

ERIC Educational Resources Information Center

Carney, Thomas Q., Ed.

2001-01-01

This issue contains these 12 papers: "Exploring the Viability of an Organizational Readiness Assessment for Participatory Management Programs in a Passenger Airline Carrier" (Al Bellamy); "Teaching the Pilots of the New Millennium: Adult Cooperative Education in Aviation Education" (Joseph F. Clark, III); "The Transfer of…

The analysis of the pilot's cognitive and decision processes

NASA Technical Reports Server (NTRS)

Curry, R. E.

1975-01-01

Articles are presented on pilot performance in zero-visibility precision approach, failure detection by pilots during automatic landing, experiments in pilot decision-making during simulated low visibility approaches, a multinomial maximum likelihood program, and a random search algorithm for laboratory computers. Other topics discussed include detection of system failures in multi-axis tasks and changes in pilot workload during an instrument landing.

Review and Assessment of Commercial Vendors/Options for Feeding and Pumping Biomass Slurries for Hydrothermal Liquefaction

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

Berglin, Eric J.; Enderlin, Carl W.; Schmidt, Andrew J.

2012-11-01

The National Advanced Biofuels Consortium is working to develop improved methods for producing high-value hydrocarbon fuels. The development of one such method, the hydrothermal liquefaction (HTL) process, is being led by the Pacific Northwest National Laboratory (PNNL). The HTL process uses a wet biomass slurry at elevated temperatures (i.e., 300 to 360°C [570 to 680°F]) and pressures above the vapor pressure of water (i.e., 15 to 20 MPa [2200 to 3000 psi] at these temperatures) to facilitate a condensed-phase reaction medium. The process has been successfully tested at bench-scale and development and testing at a larger scale is required tomore » prove the viability of the process at production levels. Near-term development plans include a pilot-scale system on the order of 0.5 to 40 gpm, followed by a larger production-scale system on the order of 2000 dry metric tons per day (DMTPD). A significant challenge to the scale-up of the HTL process is feeding a highly viscous fibrous biomass wood/corn stover feedstock into a pump system that provides the required 3000 psi of pressure for downstream processing. In October 2011, PNNL began investigating commercial feed and pumping options that would meet these HTL process requirements. Initial efforts focused on generating a HTL feed and pump specification and then providing the specification to prospective vendors to determine the suitability of their pumps for the pilot-scale and production-scale plants. Six vendors were identified that could provide viable equipment to meet HTL feed and/or pump needs. Those six vendors provided options consisting three types of positive displacement pumps (i.e., diaphragm, piston, and lobe pumps). Vendors provided capabilities and equipment related to HTL application. This information was collected, assessed, and summarized and is provided as appendices to this report.« less

Extension of effective date for temporary pilot program setting the time and place for a hearing before an administrative law judge. Final rule.

PubMed

2013-07-29

: We are extending our pilot program that authorizes the agency to set the time and place for a hearing before an administrative law judge (ALJ). This final rule will extend the pilot program for 1 year. The extension of the pilot program continues our commitment to improve the efficiency of our hearing process and maintain a hearing process that results in accurate, high-quality decisions for claimants. The current pilot program will expire on August 9, 2013. In this final rule, we are extending the effective date to August 9, 2014. We are making no other substantive changes.

Frank Batteas

NASA Technical Reports Server (NTRS)

1999-01-01

Frank Batteas is a research test pilot in the Flight Crew Branch of NASA's Dryden Flight Research Center, Edwards, California. He is currently a project pilot for the F/A-18 and C-17 flight research projects. In addition, his flying duties include operation of the DC-8 Flying Laboratory in the Airborne Science program, and piloting the B-52B launch aircraft, the King Air, and the T-34C support aircraft. Batteas has accumulated more than 4,700 hours of military and civilian flight experience in more than 40 different aircraft types. Batteas came to NASA Dryden in April 1998, following a career in the U.S. Air Force. His last assignment was at Wright-Patterson Air Force Base, Dayton, Ohio, where Lieutenant Colonel Batteas led the B-2 Systems Test and Evaluation efforts for a two-year period. Batteas graduated from Class 88A of the Air Force Test Pilot School, Edwards Air Force Base, California, in December 1988. He served more than five years as a test pilot for the Air Force's newest airlifter, the C-17, involved in nearly every phase of testing from flutter and high angle-of-attack tests to airdrop and air refueling envelope expansion. In the process, he achieved several C-17 firsts including the first day and night aerial refuelings, the first flight over the North Pole, and a payload-to-altitude world aviation record. As a KC-135 test pilot, he also was involved in aerial refueling certification tests on a number of other Air Force aircraft. Batteas received his commission as a second lieutenant in the U. S. Air Force through the Reserve Officer Training Corps and served initially as an engineer working on the Peacekeeper and Minuteman missile programs at the Ballistic Missile Office, Norton Air Force Base, Calif. After attending pilot training at Williams Air Force Base, Phoenix, Ariz., he flew operational flights in the KC-135 tanker aircraft and then was assigned to research flying at the 4950th Test Wing, Wright-Patterson. He flew extensively modified C-135 and C-18 aircraft. In addition, he was project manager and research pilot for aurora borealis studies on the Airborne Ionospheric Observatory. Batteas earned a bachelor of science degree in nuclear engineering from Rensselaer Polytechnic Institute, Troy, N.Y., in 1977 and was awarded master of science degrees in systems management from the University of Southern California in 1980 and in mechanical engineering from California State University Fresno in 1991.

Neil A. Armstrong

NASA Technical Reports Server (NTRS)

1958-01-01

Neil A. Armstrong joined the National Advisory Committee for Aeronautics at the Lewis Flight Propulsion Laboratory, Cleveland, Ohio, in 1955. He transferred to the NACA High-Speed Flight Station at Edwards Air Force Base, California, in July 1955, as an aeronautical research scientist. He became a research pilot later that year. Neil was named as one of nine astronauts for NASA's Gemini and Apollo Projects, leaving the Center for the National Aeronautics and Space Administration's Manned Spacecraft Center, Houston, Texas, in September 1962. Upon graduation from High School in 1947, Armstrong received a scholarship from the U.S. Navy. He enrolled at Purdue University to begin the study of aeronautical engineering. In 1949, the Navy called him to active duty and he became a navy pilot. In 1950, he was sent to Korea where he flew 78 combat missions from the carrier USS Essex in a Grumman F9F-2 Panther. He received the Air Medal and two Gold Stars. In 1952, Armstrong returned to Purdue University and graduated with a bachelors degree in aeronautical engineering in 1955. He later earned a masters degree in aerospace engineering from the University of Southern California. At the High-Speed Flight Station (which later became the NASA Dryden Flight Research Center) Armstrong served as project pilot on the North American F-100A and -C aircraft, McDonnell F-101, and the Lockheed F-104A. He also flew the Bell X-1B (4 flights, first on August 15, 1957), Bell X-5 (one flight, the last in the program, on October 25, 1955) and the Paresev. On November 30, 1960, Armstrong made his first flight in the X-15. He made a total of seven flights in the rocket plane reaching an altitude of 207,500 feet in the X-15-3 and a Mach number of 5.74 (3,989 mph) in the X-15-1. He left the Flight Research Center with a total of 2450 flying hours in more than 50 aircraft types. He was a member of the USAF-NASA Dyna-Soar Pilot Consultant Group, and studied X-20 Dyna-Soar approaches and abort maneuvers through use of the F-102A and F5D jet aircraft. Armstrong later accumulated a total of 8 days and 14 hours in space, including 2 hours and 48 minutes walking on the Moon. In March 1966, he was commander of the Gemini 8 mission that performed the first successful docking of two vehicles in space. As spacecraft commander for the Apollo 11 lunar mission, on July 20, 1969, he became the first human to set foot on the Moon. In 1970 he was appointed Deputy Associate Administrator for Aeronautics at NASA Headquarters. He resigned in 1971. Neil wrote several technical reports and presented a number of research papers. In June 1962, the Octave Chanute Award was presented to Neil by the Institute of the Aerospace Sciences. Other awards received by Neil have included the NASA Distinguished Service Medal and the NASA Exceptional Service Medal.

A Flexible Pilot-Scale Setup for Real-Time Studies in Process Systems Engineering

ERIC Educational Resources Information Center

Panjapornpon, Chanin; Fletcher, Nathan; Soroush, Masoud

2006-01-01

This manuscript describes a flexible, pilot-scale setup that can be used for training students and carrying out research in process systems engineering. The setup allows one to study a variety of process systems engineering concepts such as design feasibility, design flexibility, control configuration selection, parameter estimation, process and…

Copycats in Pilot Aircraft-Assisted Suicides after the Germanwings Incident

PubMed Central

Vuorio, Alpo; Bor, Robert; Budowle, Bruce; Navathe, Pooshan; Pukkala, Eero; Sajantila, Antti

2018-01-01

Aircraft-assisted pilot suicide is a rare but serious phenomenon. The aim of this study was to evaluate changes in pilot aircraft-assisted suicide risks, i.e., a copycat effect, in the U.S. and Germany after the Germanwings 2015 incident in the French Alps. Aircraft-assisted pilot suicides were searched in the U.S. National Transportation Safety Board (NTSB) accident investigation database and in the German Bundestelle für Flugunfalluntersuchung (BFU) Reports of Investigation database five years before and two years after the deliberate crash of the Germanwings flight into the French Alps in 2015. The relative risk (RR) of the aircraft-assisted pilot suicides was calculated. Two years after the incident, three out of 454 (0.66%) fatal incidents were aircraft-assisted suicides compared with six out of 1292 (0.46%) in the prior five years in the NTSB database. There were no aircraft-assisted pilot suicides in the German database during the two years after or five years prior to the Germanwings crash. The relative aircraft-assisted pilot suicide risk for the U.S. was 1.4 (95% CI 0.3–4.2) which was not statistically significant. Six of the pilots who died by suicide had told someone of their suicidal intentions. We consider changes in the rate to be within a normal variation. Responsible media coverage of aircraft incidents is important due to the large amount of publicity that these events attract. PMID:29534475

Thermochemical Users Facility | Bioenergy | NREL

Science.gov Websites

collaborate on research and development efforts or to use our equipment to test their materials and processes NREL's thermochemical process integration, scale-up, and piloting research. Schematic diagram of NRELs about NREL's thermochemical process integration, scale-up, and piloting research. Thermochemical

Vermont lakes and ponds: a pilot recreation planning process

Treesearch

Daniel T. Malone; John J. Lindsay

1992-01-01

This report analyzes a pilot planning study conducted on two Vermont ponds by University of Vermont outdoor recreation planning students. It discusses the planning process used for these ponds and offers ways in which a statewide lake and pond planning process could be implemented.

NASA Pilot and Researcher Prepare for a Solar Cell Calibration Flight

NASA Image and Video Library

1964-04-21

Pilot Earle Boyer and researcher Henry Brandhorst prepare for a solar cell calibration flight in a Martin B-57B Canberra at the National Aeronautics and Space Administration (NASA) Lewis Research Center. Lewis was in the early stages of decades-long energy conversion and space power research effort. Brandhorst, a member of the Chemistry and Energy Conversion Division, led a team of Lewis researchers in a quest to develop new power sources to sustain spacecraft in orbit. Solar cells proved to be an important source of energy, but researchers discovered that their behavior varied at different atmospheric levels. Their standardization and calibration were critical. Brandhorst initiated a standardized way to calibrate solar cells in the early 1960s using the B-57B aircraft. The pilots would take the aircraft up into the troposphere and open the solar cell to the sunlight. The aircraft would steadily descend while instruments recorded how much energy was being captured by the solar cell. From this data, Brandhorst could determine the estimated power for a particular solar cell at any altitude. Pilot Earle Boyer joined NASA Lewis in October 1962. He had flown Convair F-102 Delta Dagger fighters in the Air Force and served briefly in the National Guard before joining the Langley Research Center. Boyer was only at Langley a few months before he transferred to Cleveland. He flew the B-57B, a Convair F-106 Delta Dart, Gulfstream G-1 with an experimental turboprop, Learjet and many other aircraft over the next 32 years at Lewis.

Volitional control of the anterior insula in criminal psychopaths using real-time fMRI neurofeedback: a pilot study

PubMed Central

Sitaram, Ranganatha; Caria, Andrea; Veit, Ralf; Gaber, Tilman; Ruiz, Sergio; Birbaumer, Niels

2014-01-01

This pilot study aimed to explore whether criminal psychopaths can learn volitional regulation of the left anterior insula with real-time fMRI neurofeedback. Our previous studies with healthy volunteers showed that learned control of the blood oxygenation-level dependent (BOLD) signal was specific to the target region, and not a result of general arousal and global unspecific brain activation, and also that successful regulation modulates emotional responses, specifically to aversive picture stimuli but not neutral stimuli. In this pilot study, four criminal psychopaths were trained to regulate the anterior insula by employing negative emotional imageries taken from previous episodes in their lives, in conjunction with contingent feedback. Only one out of the four participants learned to increase the percent differential BOLD in the up-regulation condition across training runs. Subjects with higher Psychopathic Checklist-Revised (PCL:SV) scores were less able to increase the BOLD signal in the anterior insula than their lower PCL:SV counterparts. We investigated functional connectivity changes in the emotional network due to learned regulation of the successful participant, by employing multivariate Granger Causality Modeling (GCM). Learning to up-regulate the left anterior insula not only increased the number of connections (causal density) in the emotional network in the single successful participant but also increased the difference between the number of outgoing and incoming connections (causal flow) of the left insula. This pilot study shows modest potential for training psychopathic individuals to learn to control brain activity in the anterior insula. PMID:25352793

Proposed Ames M2-F1, M1-L half-cone, and Langley lenticular bodies.

NASA Technical Reports Server (NTRS)

1962-01-01

Dale Reed, who inaugurated the lifting-body flight research at NASA's Flight Research Center (later, Dryden Flight Research Center, Edwards, CA), originally proposed that three wooden outer shells be built. These would then be attached to the single internal steel structure. The three shapes were (viewer's left to right) the M2-F1, the M1-L, and a lenticular shape. Milt Thompson, who supported Reed's advocacy for a lifting-body research project, recommended that only the M2-F1 shell be built, believing that the M1-L shape was 'too radical,' while the lenticular one was 'too exotic.' Although the lenticular shape was often likened to that of a flying saucer, Reed's wife Donna called it the 'powder puff.' The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

M2-F1 in hangar with Pontiac tow vehicle

NASA Technical Reports Server (NTRS)

1963-01-01

The M2-F1 Lifting Body is seen here in a hangar with its hotrod Pontiac convertible tow vehicle at the Flight Research Center (later the Dryden Flight Research Center), Edwards, California. The car was a 1963 Pontiac Catalina convertible, fitted with a 421-cubic-inch tripower engine like those being run at the Daytona 500 auto race. The vehicle also had a four-speed transmission and a heavy-duty suspension and cooling system. A roll bar was also added and the passenger seat turned around so an observer could watch the M2-F1 while it was being towed. The rear seat was removed and a second, side-facing seat installed. The lifting-body team used the Pontiac for all the ground-tow flights over the next three years. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30 seconds. It proved adequate for the roughly 400 car tows that got the M2-F1 airborne to prove it could fly safely and to train pilots before they were towed behind a C-47 aircraft and released. These initial car-tow tests produced enough flight data about the M2-F1 to proceed with flights behind the C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. A small solid landing rocket, referred to as the 'instant L/D rocket,' was installed in the rear base of the M2-F1. This rocket, which could be ignited by the pilot, provided about 250 pounds of thrust for about 10 seconds. The rocket could be used to extend the flight time near landing if needed. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program, with an X-24A and -B built by Martin. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

Formation of PCDD and PCDF in the thermal treatment of footwear leather wastes.

PubMed

Godinho, Marcelo; Marcilio, Nilson Romeu; Masotti, Leonardo; Martins, Celso Brisolara; Ritter, Diego Elias; Wenzel, Bruno München

2009-08-15

The leather waste generated by the footwear industry is considered dangerous due to the presence of trivalent chromium, derived from the salt utilized to tan hides. In Brazil, the majority of this waste is disposed on landfills and only about 3% are recycled. The thermal treatment is an alternative method for purification of such residues. By using this technique it is possible to generate energy and recover the chromium present in the ash for the production of basic chromium sulfate (tanning industry), high carbon ferrochromium or carbon-free ferrochromium (steel industry). In the last 10 years, the gasification and combustion of footwear leather waste have been intensively studied at the Federal University of Rio Grande do Sul. The research experiment for characterization of the emissions of polychlorinated dibenzo-p-dioxins and dibenzofurans (PCDD/F) were carried out in a semi-pilot unit (350 kW(th)). From new investments the thermal capacity of the unit will increase to 600 kW(th). The unit will produce power from the heat generated in the combustion. The experimental results indicated that during the thermal treatment of footwear leather wastes, the formation mechanism of PCDD/F is the de novo synthesis. Most of PCDD/F were found in the particulate phase (>95%). A kinetic model was used for discussion of the achieved experimental results. The model is based in the carbon gasification, PCDD/F formation, desorption and degradation. From the conclusions obtained in this work will be possible minimize the PCDD/F formation in process of combustion of footwear leather wastes.

Effects of foveal information processing

NASA Technical Reports Server (NTRS)

Harris, R. L., Sr.

1984-01-01

The scanning behavior of pilots must be understood so that cockpit displays can be assembled which will provide the most information accurately and quickly to the pilot. The results of seven years of collecting and analyzing pilot scanning data are summarized. The data indicate that pilot scanning behavior is: (1) subsconscious; (2) situation dependent; and (3) can be disrupted if pilots are forced to make conscious decisions. Testing techniques and scanning analysis techniques have been developed that are sensitive to pilot workload.

A Simultaneous Genetic Screen for Zygotic and Sterile Mutants in a Hermaphroditic Vertebrate (Kryptolebias marmoratus)

PubMed Central

Sucar, Sofia; Moore, Ginger L.; Ard, Melissa E.; Ring, Brian C.

2016-01-01

The mangrove killifish, Kryptolebias marmoratus, is unique among vertebrates due to its self-fertilizing mode of reproduction involving an ovotestis. As a result, it constitutes a simplistic and desirable vertebrate model for developmental genetics as it is easily maintained, reaches sexual maturity in about 100 days, and provides a manageable number of relatively clear embryos. After the establishment and characterization of an initial mutagenesis pilot screen using N-ethyl-N-nitrosourea, a three-generation genetic screen was performed to confirm zygotic mutant allele heritability and simultaneously score for homozygous recessive mutant sterile F2 fish. From a total of 307 F2 fish screened, 10 were found to be 1° males, 16 were sterile, 92 wild-type, and the remaining 189, carriers of zygotic recessive alleles. These carriers produced 25% progeny exhibiting several zygotic phenotypes similar to those previously described in zebrafish and in the aforementioned pilot screen, as expected. Interestingly, new phenotypes such as golden yolk, no trunk, and short tail were observed. The siblings of sterile F2 mutants were used to produce an F3 generation in order to confirm familial sterility. Out of the 284 F3 fish belonging to 10 previously identified sterile families, 12 were found to be 1° males, 69 were wild-type, 83 sterile, and 120 were classified as */+ (either wild-type or carriers) with undefined genotypes. This screen provides proof of principle that K. marmoratus is a powerful vertebrate model for developmental genetics and can be used to identify mutations affecting fertility. PMID:26801648

Nonthermal processing of orange juice using a pilot-plant scale supercritical carbon dioxide system with a gas-liquid metal contactor

USDA-ARS?s Scientific Manuscript database

To evaluate the effect of pilot-plant scale, non-thermal supercritical carbon dioxide (SCCO2) processing on the safety and the quality of orange juice (OJ), SCCO2 processed juice was compared with untreated fresh juice and equivalently thermal processed juice in terms of lethality. SCCO2 processing ...

REMOVAL OF PCBS FROM A CONTAMINATED SOIL USING CF-SYSTEMS SOLVENT EXTRACTION PROCESS

EPA Science Inventory

The US EPA's START team in cooperation with EPA's SITE program evaluated a pilot scale solvent extraction process developed by CF-Systems. This process uses liquified propane to extract organic contaminants from soils, sludges, and sediments. A pilot-scale evaluation was conducte...

ARCHITECTURAL FLOOR PLAN OF PROCESS AND ACCESS AREAS HOT PILOT ...

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

ARCHITECTURAL FLOOR PLAN OF PROCESS AND ACCESS AREAS HOT PILOT PLANT (CPP-640). INL DRAWING NUMBER 200-0640-00-279-111679. ALTERNATE ID NUMBER 8952-CPP-640-A-2. - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

75 FR 70074 - Consensus Standards, Light-Sport Aircraft

Federal Register 2010, 2011, 2012, 2013, 2014

2010-11-16

... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Consensus Standards, Light-Sport... accepted consensus standards relating to the provisions of the Sport Pilot and Light-Sport Aircraft rule issued July 16, 2004, and effective September 1, 2004. ASTM International Committee F37 on Light Sport...

Astronaut Richard Gordon returns to hatch of spacecraft following EVA

NASA Technical Reports Server (NTRS)

1966-01-01

Astronaut Richard F. Gordon Jr., pilot for the Gemini 11 space flight, returns to the hatch of the spacecraft following extravehicular activity (EVA). This picture was taken over the Atlantic Ocean at approximately 160 nautical miles above the earth's surface.

14 CFR 1214.115 - Standard services.

Code of Federal Regulations, 2011 CFR

2011-01-01

...: commander, pilot and three mission specialists. (e) Orbiter flight planning services. (f) One day of... Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT General Provisions Regarding Space Shuttle Flights of Payloads for Non-U.S. Government, Reimbursable Customers § 1214.115 Standard...

Piloted simulation tests of propulsion control as backup to loss of primary flight controls for a mid-size jet transport

NASA Technical Reports Server (NTRS)

Bull, John; Mah, Robert; Davis, Gloria; Conley, Joe; Hardy, Gordon; Gibson, Jim; Blake, Matthew; Bryant, Don; Williams, Diane

1995-01-01

Failures of aircraft primary flight-control systems to aircraft during flight have led to catastrophic accidents with subsequent loss of lives (e.g. , DC-1O crash, B-747 crash, C-5 crash, B-52 crash, and others). Dryden Flight Research Center (DFRC) investigated the use of engine thrust for emergency flight control of several airplanes, including the B-720, Lear 24, F-15, C-402, and B-747. A series of three piloted simulation tests have been conducted at Ames Research Center to investigate propulsion control for safely landing a medium size jet transport which has experienced a total primary flight-control failure. The first series of tests was completed in July 1992 and defined the best interface for the pilot commands to drive the engines. The second series of tests was completed in August 1994 and investigated propulsion controlled aircraft (PCA) display requirements and various command modes. The third series of tests was completed in May 1995 and investigated PCA full-flight envelope capabilities. This report describes the concept of a PCA, discusses pilot controls, displays, and procedures; and presents the results of piloted simulation evaluations of the concept by a cross-section of air transport pilots.

Heavy Lift Helicopter - Advanced Technology Component Program - Hub and Upper Controls

DTIC Science & Technology

1977-09-01

horsepov.er increasces or decreases at a rate which is determined by the pilot’s rate of collective input. The change in rotor horse - power produces a...34;TATU’ H-31 1"O1 RMANC1• T’I’.- J’ - MOD IFl El) FSD I.1’:AKA(;I’ ARIEA U .00025 IN’ Unuodit ied ModI. iud Spec. I; trkt,. F I:(._ ’z’u1.11, % Nnl-,’F

Remotely Piloted Vehicle (RPV) Two versus Three Level Maintenance Support Concept Study.

DTIC Science & Technology

1988-01-15

Abri:.ms ML-C, Technic:al Arid lysi!;&2jp7 f D~onnie Joyce Al ler Ad:va-.ncecd Sys.tems Coric epts oft ic.e, -,Je etaty Robo r t Bac-et RPV Pti...en ter, Al TN Conccept,-* & [h ct norii ’’ t Fort Lee, VA 2D501 ,c ient f ii: Advisor , ATIN: ATCI. SP(A, At my C eq 1 t mPFr [ pp Ft VA :27: C.1. Do

Spearhead echo and downburst near the approach end of a John F. Kennedy Airport runway, New York City

NASA Technical Reports Server (NTRS)

Fujita, T. T.

1976-01-01

Radar echoes of a storm at John F. Kennedy International Airport are examined. Results regarding the phenomena presented suggest the existence of downburst cells. These cells are characterized by spearhead echoes. About 2% of the echoes in the New York area were spearhead echoes. The detection and identification of downburst cells, their potential hazard to approaching and landing aircraft, and communication of this information to the pilots of those aircraft are discussed.

PASTE: patient-centered SMS text tagging in a medication management system

PubMed Central

Johnson, Kevin B; Denny, Joshua C

2011-01-01

Objective To evaluate the performance of a system that extracts medication information and administration-related actions from patient short message service (SMS) messages. Design Mobile technologies provide a platform for electronic patient-centered medication management. MyMediHealth (MMH) is a medication management system that includes a medication scheduler, a medication administration record, and a reminder engine that sends text messages to cell phones. The object of this work was to extend MMH to allow two-way interaction using mobile phone-based SMS technology. Unprompted text-message communication with patients using natural language could engage patients in their healthcare, but presents unique natural language processing challenges. The authors developed a new functional component of MMH, the Patient-centered Automated SMS Tagging Engine (PASTE). The PASTE web service uses natural language processing methods, custom lexicons, and existing knowledge sources to extract and tag medication information from patient text messages. Measurements A pilot evaluation of PASTE was completed using 130 medication messages anonymously submitted by 16 volunteers via a website. System output was compared with manually tagged messages. Results Verified medication names, medication terms, and action terms reached high F-measures of 91.3%, 94.7%, and 90.4%, respectively. The overall medication name F-measure was 79.8%, and the medication action term F-measure was 90%. Conclusion Other studies have demonstrated systems that successfully extract medication information from clinical documents using semantic tagging, regular expression-based approaches, or a combination of both approaches. This evaluation demonstrates the feasibility of extracting medication information from patient-generated medication messages. PMID:21984605

Cerebral Correlates of Emotional and Action Appraisals During Visual Processing of Emotional Scenes Depending on Spatial Frequency: A Pilot Study.

PubMed

Campagne, Aurélie; Fradcourt, Benoit; Pichat, Cédric; Baciu, Monica; Kauffmann, Louise; Peyrin, Carole

2016-01-01

Visual processing of emotional stimuli critically depends on the type of cognitive appraisal involved. The present fMRI pilot study aimed to investigate the cerebral correlates involved in the visual processing of emotional scenes in two tasks, one emotional, based on the appraisal of personal emotional experience, and the other motivational, based on the appraisal of the tendency to action. Given that the use of spatial frequency information is relatively flexible during the visual processing of emotional stimuli depending on the task's demands, we also explored the effect of the type of spatial frequency in visual stimuli in each task by using emotional scenes filtered in low spatial frequency (LSF) and high spatial frequencies (HSF). Activation was observed in the visual areas of the fusiform gyrus for all emotional scenes in both tasks, and in the amygdala for unpleasant scenes only. The motivational task induced additional activation in frontal motor-related areas (e.g. premotor cortex, SMA) and parietal regions (e.g. superior and inferior parietal lobules). Parietal regions were recruited particularly during the motivational appraisal of approach in response to pleasant scenes. These frontal and parietal activations, respectively, suggest that motor and navigation processes play a specific role in the identification of the tendency to action in the motivational task. Furthermore, activity observed in the motivational task, in response to both pleasant and unpleasant scenes, was significantly greater for HSF than for LSF scenes, suggesting that the tendency to action is driven mainly by the detailed information contained in scenes. Results for the emotional task suggest that spatial frequencies play only a small role in the evaluation of unpleasant and pleasant emotions. Our preliminary study revealed a partial distinction between visual processing of emotional scenes during identification of the tendency to action, and during identification of personal emotional experiences. It also illustrates flexible use of the spatial frequencies contained in scenes depending on their emotional valence and on task demands.

Artificial Icing Test, Utility Tactical Transport Aircraft System (UTTAS), Boeing Vertol YUH-61A Helicopter

DTIC Science & Technology

1977-01-01

FOR OFFIC!AL USE ONLY VTT 0ff4 -40. -26-: a 20 TEMPATURE (-Q FIGUR~E t:. VMRATIOI4 (W THEMMONMIC FUNCTIOUt WITfLt -EA~UrT IOMMI4MTSRS- SOMiRE; jym...JOHN F. HAGEN MAJ, FA US ARMY JAMES C. O’CONNOR PROJECT OFFICER/PILOT CPT, CE US ARMY EDWARD J. TAVARES PROJECT PILOT CPT, TC US ARMY PROJECT...is no longer needed. Do not return it to the originator. TRADE NAMES The use of trade names in this report does not constitute an official endorsement

STS-29 Pilot Blaha with SE83-9 "Chix in Space" incubator on OV-103's middeck

NASA Image and Video Library

1989-03-16

STS029-01-001 (16 Marach 1989) --- Astronaut John E. Blaha, STS-29 pilot, checks an incubator on the mid deck of Earth-orbiting Discovery during Flight Day 4 activity. The incubator is part of a student involvement program experiment titled, "Chicken Embryo Development in Space." The student experimenter is John C. Vellinger. The experiment's sponsor is Kentucky Fried Chicken. This photographic frame was among NASA's third STS-29 photo release. Monday, March 20, 1989. Crewmembers were Astronauts Michael L. Coats, John E. Blaha, James F. Buchli, Robert C. Springer and James P. Bagian.

Pilot vehicle interface on the advanced fighter technology integration F-16

NASA Technical Reports Server (NTRS)

Dana, W. H.; Smith, W. B.; Howard, J. D.

1986-01-01

This paper focuses on the work load aspects of the pilot vehicle interface in regard to the new technologies tested during AMAS Phase II. Subjects discussed in this paper include: a wide field-of-view head-up display; automated maneuvering attack system/sensor tracker system; master modes that configure flight controls and mission avionics; a modified helmet mounted sight; improved multifunction display capability; a voice interactive command system; ride qualities during automated weapon delivery; a color moving map; an advanced digital map display; and a g-induced loss-of-consciousness and spatial disorientation autorecovery system.

STS-31 crewmembers during simulation on the flight deck of JSC's FB-SMS

NASA Technical Reports Server (NTRS)

1988-01-01

On the flight deck of JSC's fixed based (FB) shuttle mission simulator (SMS), Mission Specialist (MS) Steven A. Hawley (left), on aft flight deck, looks over the shoulders of Commander Loren J. Shriver, seated at the commanders station (left) and Pilot Charles F. Bolden, seated at the pilots station and partially blocked by the seat's headrest (right). The three astronauts recently named to the STS-31 mission aboard Discovery, Orbiter Vehicle (OV) 103, go through a procedures checkout in the FB-SMS. The training simulation took place in JSC's Mission Simulation and Training Facility Bldg 5.