Aircraft Engine-Monitoring System And Display

NASA Technical Reports Server (NTRS)

Abbott, Terence S.; Person, Lee H., Jr.

1992-01-01

Proposed Engine Health Monitoring System and Display (EHMSD) provides enhanced means for pilot to control and monitor performances of engines. Processes raw sensor data into information meaningful to pilot. Provides graphical information about performance capabilities, current performance, and operational conditions in components or subsystems of engines. Provides means to control engine thrust directly and innovative means to monitor performance of engine system rapidly and reliably. Features reduce pilot workload and increase operational safety.

Design for improved maintenance of the fiber-optic cable system (As carried out in a concurrent engineering environment)

NASA Astrophysics Data System (ADS)

Tremoulet, P. C.

The author describes a number of maintenance improvements in the Fiber Optic Cable System (FOCS). They were achieved during a production phase pilot concurrent engineering program. Listed in order of importance (saved maintenance time and material) by maintenance level, they are: (1) organizational level: improved fiber optic converter (FOC) BITE; (2) Intermediate level: reduced FOC adjustments from 20 to 2; partitioned FOC into electrical and optical parts; developed cost-effective fault isolation test points and test using standard test equipment; improved FOC chassis to have lower mean time to repair; and (3) depot level: revised test requirements documents (TRDs) for common automatic test equipment and incorporated ATE testability into circuit and assemblies and application-specific integrated circuits. These improvements met this contract's tailored logistics MIL-STD 1388-1A requirements of monitoring the design for supportability and determining the most effective support equipment. Important logistics lessons learned while accomplishing these maintainability and supportability improvements on the pilot concurrent engineering program are also discussed.

14 CFR 13.18 - Civil penalties: Administrative assessment against an individual acting as a pilot, flight...

Code of Federal Regulations, 2013 CFR

2013-01-01

... against an individual acting as a pilot, flight engineer, mechanic, or repairman. 13.18 Section 13.18... assessment against an individual acting as a pilot, flight engineer, mechanic, or repairman. (a) General. (1... procedures against an individual acting as a pilot, flight engineer, mechanic, or repairman, under 49 U.S.C...

The development and piloting of electronic standardized measures on nursing work: combining engineering and nursing knowledge.

PubMed

Bragadóttir, Helga; Gunnarsdóttir, Sigrún; Ingason, Helgi T

2013-05-01

This paper describes the development and piloting of electronic standardized measures on nursing work (e-SMNW) for rich data gathering on the work and work environment of registered nurses (RNs) and practical nurses (PNs). Efficient and valid methods are needed to measure nursing work to enhance the optimal use of the nursing workforce for safe patient care. The study combined human factors engineering (HFE) and nursing knowledge to develop electronic standardized measures for observational studies on nursing work in acute care. The work and work environment of RNs and PNs in acute care medical and surgical inpatient units was successfully measured using e-SMNW. With predetermined items of work activities and influencing factors in the work of nurses, and full use of computer technology, multi-layered rich standardized data were gathered, analysed and displayed. The combination of nursing knowledge, HFE and computer technology enables observational data collection for a rich picture of the complex work of nursing. Information collected by standardized and multi-layered measures makes it easier to identify potential improvements, with regard to influencing factors and management of the work and work environment of nurses. Further use of computer technology in health services research is encouraged. © 2012 Blackwell Publishing Ltd.

Assessing the impact of modeling limits on intelligent systems

NASA Technical Reports Server (NTRS)

Rouse, William B.; Hammer, John M.

1990-01-01

The knowledge bases underlying intelligent systems are validated. A general conceptual framework is provided for considering the roles in intelligent systems of models of physical, behavioral, and operational phenomena. A methodology is described for identifying limits in particular intelligent systems, and the use of the methodology is illustrated via an experimental evaluation of the pilot-vehicle interface within the Pilot's Associate. The requirements and functionality are outlined for a computer based knowledge engineering environment which would embody the approach advocated and illustrated in earlier discussions. Issues considered include the specific benefits of this functionality, the potential breadth of applicability, and technical feasibility.

California four cities program, 1971 - 1973. [aerospace-to-urban technology application

NASA Technical Reports Server (NTRS)

Macomber, H. L.; Wilson, J. H.

1974-01-01

A pilot project in aerospace-to-urban technology application is reported. Companies assigned senior engineering professionals to serve as Science and Technology Advisors to participating city governments. Technical support was provided by the companies and JPL. The cities, Anaheim, Fresno, Pasadena, and San Hose, California, provided the working environment and general service support. Each city/company team developed and carried out one or more technical or management pilot projects together with a number of less formalized technology efforts and studies. An account and evaluation is provided of the initial two-year phase of the program.

PVD thermal barrier coating applications and process development for aircraft engines

NASA Astrophysics Data System (ADS)

Rigney, D. V.; Viguie, R.; Wortman, D. J.; Skelly, D. W.

1997-06-01

Thermal barrier coatings (TBCs) have been developed for application to aircraft engine components to improve service life in an increasingly hostile thermal environment. The choice of TBC type is related to the component, intended use, and economics. Selection of electron beam physical vapor deposition proc-essing for turbine blade is due in part to part size, surface finish requirements, thickness control needs, and hole closure issues. Process development of PVD TBCs has been carried out at several different sites, including GE Aircraft Engines (GEAE). The influence of processing variables on microstructure is dis-cussed, along with the GEAE development coater and initial experiences of pilot line operation.

14 CFR 121.419 - Pilots and flight engineers: Initial, transition, and upgrade ground training.

Code of Federal Regulations, 2012 CFR

2012-01-01

...; (ix) Flight planning; (x) Each normal and emergency procedure; and (xi) The approved Airplane Flight... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilots and flight engineers: Initial... Program § 121.419 Pilots and flight engineers: Initial, transition, and upgrade ground training. (a...

14 CFR 121.419 - Pilots and flight engineers: Initial, transition, and upgrade ground training.

Code of Federal Regulations, 2011 CFR

2011-01-01

...; (ix) Flight planning; (x) Each normal and emergency procedure; and (xi) The approved Airplane Flight... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilots and flight engineers: Initial... Program § 121.419 Pilots and flight engineers: Initial, transition, and upgrade ground training. (a...

14 CFR 121.419 - Pilots and flight engineers: Initial, transition, and upgrade ground training.

Code of Federal Regulations, 2014 CFR

2014-01-01

...; (ix) Flight planning; (x) Each normal and emergency procedure; and (xi) The approved Airplane Flight... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilots and flight engineers: Initial... Program § 121.419 Pilots and flight engineers: Initial, transition, and upgrade ground training. Link to...

14 CFR 121.419 - Pilots and flight engineers: Initial, transition, and upgrade ground training.

Code of Federal Regulations, 2010 CFR

2010-01-01

...; (ix) Flight planning; (x) Each normal and emergency procedure; and (xi) The approved Airplane Flight... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilots and flight engineers: Initial... Program § 121.419 Pilots and flight engineers: Initial, transition, and upgrade ground training. (a...

14 CFR 121.419 - Pilots and flight engineers: Initial, transition, and upgrade ground training.

Code of Federal Regulations, 2013 CFR

2013-01-01

...; (ix) Flight planning; (x) Each normal and emergency procedure; and (xi) The approved Airplane Flight... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilots and flight engineers: Initial... Program § 121.419 Pilots and flight engineers: Initial, transition, and upgrade ground training. (a...

A Demonstration of a Retrofit Architecture for Intelligent Control and Diagnostics of a Turbofan Engine

NASA Technical Reports Server (NTRS)

Litt, Jonathan S.; Turso, James A.; Shah, Neerav; Sowers, T. Shane; Owen, A. Karl

2005-01-01

A retrofit architecture for intelligent turbofan engine control and diagnostics that changes the fan speed command to maintain thrust is proposed and its demonstration in a piloted flight simulator is described. The objective of the implementation is to increase the level of autonomy of the propulsion system, thereby reducing pilot workload in the presence of anomalies and engine degradation due to wear. The main functions of the architecture are to diagnose the cause of changes in the engine s operation, warning the pilot if necessary, and to adjust the outer loop control reference signal in response to the changes. This requires that the retrofit control architecture contain the capability to determine the changed relationship between fan speed and thrust, and the intelligence to recognize the cause of the change in order to correct it or warn the pilot. The proposed retrofit architecture is able to determine the fan speed setting through recognition of the degradation level of the engine, and it is able to identify specific faults and warn the pilot. In the flight simulator it was demonstrated that when degradation is introduced into an engine with standard fan speed control, the pilot needs to take corrective action to maintain heading. Utilizing the intelligent retrofit control architecture, the engine thrust is automatically adjusted to its expected value, eliminating yaw without pilot intervention.

Integrated System Health Management: Pilot Operational Implementation in a Rocket Engine Test Stand

NASA Technical Reports Server (NTRS)

Figueroa, Fernando; Schmalzel, John L.; Morris, Jonathan A.; Turowski, Mark P.; Franzl, Richard

2010-01-01

This paper describes a credible implementation of integrated system health management (ISHM) capability, as a pilot operational system. Important core elements that make possible fielding and evolution of ISHM capability have been validated in a rocket engine test stand, encompassing all phases of operation: stand-by, pre-test, test, and post-test. The core elements include an architecture (hardware/software) for ISHM, gateways for streaming real-time data from the data acquisition system into the ISHM system, automated configuration management employing transducer electronic data sheets (TEDS?s) adhering to the IEEE 1451.4 Standard for Smart Sensors and Actuators, broadcasting and capture of sensor measurements and health information adhering to the IEEE 1451.1 Standard for Smart Sensors and Actuators, user interfaces for management of redlines/bluelines, and establishment of a health assessment database system (HADS) and browser for extensive post-test analysis. The ISHM system was installed in the Test Control Room, where test operators were exposed to the capability. All functionalities of the pilot implementation were validated during testing and in post-test data streaming through the ISHM system. The implementation enabled significant improvements in awareness about the status of the test stand, and events and their causes/consequences. The architecture and software elements embody a systems engineering, knowledge-based approach; in conjunction with object-oriented environments. These qualities are permitting systematic augmentation of the capability and scaling to encompass other subsystems.

14 CFR 13.16 - Civil Penalties: Administrative assessment against a person other than an individual acting as a...

Code of Federal Regulations, 2012 CFR

2012-01-01

... against a person other than an individual acting as a pilot, flight engineer, mechanic, or repairman... assessment against a person other than an individual acting as a pilot, flight engineer, mechanic, or... as a pilot, flight engineer, mechanic, or repairman for a violation cited in the first sentence of 49...

14 CFR 13.16 - Civil Penalties: Administrative assessment against a person other than an individual acting as a...

Code of Federal Regulations, 2011 CFR

2011-01-01

... against a person other than an individual acting as a pilot, flight engineer, mechanic, or repairman... assessment against a person other than an individual acting as a pilot, flight engineer, mechanic, or... as a pilot, flight engineer, mechanic, or repairman for a violation cited in the first sentence of 49...

14 CFR 13.16 - Civil Penalties: Administrative assessment against a person other than an individual acting as a...

Code of Federal Regulations, 2014 CFR

2014-01-01

... against a person other than an individual acting as a pilot, flight engineer, mechanic, or repairman... assessment against a person other than an individual acting as a pilot, flight engineer, mechanic, or... as a pilot, flight engineer, mechanic, or repairman for a violation cited in the first sentence of 49...

14 CFR 13.16 - Civil Penalties: Administrative assessment against a person other than an individual acting as a...

Code of Federal Regulations, 2013 CFR

2013-01-01

... against a person other than an individual acting as a pilot, flight engineer, mechanic, or repairman... assessment against a person other than an individual acting as a pilot, flight engineer, mechanic, or... as a pilot, flight engineer, mechanic, or repairman for a violation cited in the first sentence of 49...

14 CFR 13.16 - Civil Penalties: Administrative assessment against a person other than an individual acting as a...

Code of Federal Regulations, 2010 CFR

2010-01-01

... against a person other than an individual acting as a pilot, flight engineer, mechanic, or repairman... assessment against a person other than an individual acting as a pilot, flight engineer, mechanic, or... as a pilot, flight engineer, mechanic, or repairman for a violation cited in the first sentence of 49...

SolarPILOT | Concentrating Solar Power | NREL

Science.gov Websites

tools. Unlike exclusively ray-tracing tools, SolarPILOT runs the analytical simulation engine that uses engine alongside a ray-tracing core for more detailed simulations. The SolTrace simulation engine is

Hardware-in-the-loop environment facility to address pilot-vehicle-interface issues of a fighter aircraft

NASA Astrophysics Data System (ADS)

Pandurangareddy, Meenige

2002-07-01

The evolution of Pilot-Vehicle-Interface (PVI) of a fighter aircraft is a complex task. The PVI design involves both static and dynamic issues. Static issues involve the study of reach of controls and switches, ejection path clearance, readability of indicators and display symbols, etc. Dynamic issues involve the study of the effect of aircraft motion on display symbols, pilot emergency handling, situation awareness, weapon aiming, etc. This paper describes a method of addressing the above issues by building a facility with cockpit, which is ergonomically similar to the fighter cockpit. The cockpit is also fitted with actual displays, controls and switches. The cockpit is interfaced with various simulation models of aircraft and outside-window-image generators. The architecture of the facility is designed to represent the latencies of the aircraft and facilitates replacement of simulation models with actual units. A parameter injection facility could be used to induce faults in a comprehensive manner. Pilots could use the facility right from familiarising themselves with procedures to start the engine, take-off, navigate, aim the weapons, handling of emergencies and landing. This approach is being followed and further being enhanced on Cockpit-Environment-Facility (CEF) at Aeronautical Development Agency (ADA), Bangalore, India.

Draft environmental assessment: Ocean Thermal Energy Conversion (OTEC) Pilot Plants

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

Sullivan, S.M.; Sands, M.D.; Donat, J.R.

This Environmental Assessment (EA) has been prepared, in accordance with the National Environmental Policy Act of 1969, for the deployment and operation of a commercial 40-Megawatt (MW) Ocean Thermal Energy Conversion (OTEC) Pilot Plant (hereafter called the Pilot Plant). A description of the proposed action is presented, and a generic environment typical of the candidate Pilot Plant siting regions is described. An assessment of the potential environmental impacts associated with the proposed action is given, and the risk of credible accidents and mitigating measures to reduce these risks are considered. The Federal and State plans and policies the proposed actionmore » will encompass are described. Alternatives to the proposed action are presented. Appendix A presents the navigation and environmental information contained in the US Coast Pilot for each of the candidate sites; Appendix B provides a brief description of the methods and calculations used in the EA. It is concluded that environmental disturbances associated with Pilot Plant activities could potentially cause significant environmental impacts; however, the magnitude of these potential impacts cannot presently be assessed, due to insufficient engineering and environmental information. A site- and design-specific OTEC Pilot Plant Environmental Impact Statement (EIS) is required to resolve the potentially significant environmental effects associated with Pilot Plant deployment and operation. (WHK)« less

Baseline design of an OTEC pilot plantship. Volume A. Detailed report. [Performance analysis of OTEC power plant

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

George, J. F.; Richards, D.; Perini, L. L.

1979-05-01

The Applied Physics Laboratory (APL) of the Johns Hopkins University has engineered a baseline design of an Ocean Thermal Energy Conversion (OTEC) pilot plantship. The work was sponsored jointly by the Department of Energy and the US Maritime Administration of the Department of Commerce. The design, drawings, specifications, supporting calculations, and narrative documentation are available through APL for use by the Government and industry for the acquisition of a pilot OTEC system. The baseline design features a platform that is configured to produce up to 20 MW(e) (net) power, using low-cost folded-tube aluminum heat exchangers, while it grazes slowly inmore » tropical waters where the thermal gradient is greatest and the ocean environment is least severe. The design was developed by a team of contractors whose capabilities provided a systems approach to the design process. The work is documented in three volumes. Volume A is the Detailed report, which develops the design rationale, summarizes important calculations, outlines areas for future work, and presents a study of system costs. Volumes B and C, respectively, contain the engineering drawings and specifications.« less

Distributed ignition method and apparatus for a combustion engine

DOEpatents

Willi, Martin L.; Bailey, Brett M.; Fiveland, Scott B.; Gong, Weidong

2006-03-07

A method and apparatus for operating an internal combustion engine is provided. The method comprises the steps of introducing a primary fuel into a main combustion chamber of the engine, introducing a pilot fuel into the main combustion chamber of the engine, determining an operating load of the engine, determining a desired spark plug ignition timing based on the engine operating load, and igniting the primary fuel and pilot fuel with a spark plug at the desired spark plug ignition timing. The method is characterized in that the octane number of the pilot fuel is lower than the octane number of the primary fuel.

Human systems integration in remotely piloted aircraft operations.

PubMed

Tvaryanas, Anthony P

2006-12-01

The role of humans in remotely piloted aircraft (RPAs) is qualitatively different from manned aviation, lessening the applicability of aerospace medicine human factors knowledge derived from traditional cockpits. Aerospace medicine practitioners should expect to be challenged in addressing RPA crewmember performance. Human systems integration (HSI) provides a model for explaining human performance as a function of the domains of: human factors engineering; personnel; training; manpower; environment, safety, and occupational health (ESOH); habitability; and survivability. RPA crewmember performance is being particularly impacted by issues involving the domains of human factors engineering, personnel, training, manpower, ESOH, and habitability. Specific HSI challenges include: 1) changes in large RPA operator selection and training; 2) human factors engineering deficiencies in current RPA ground control station design and their impact on human error including considerations pertaining to multi-aircraft control; and 3) the combined impact of manpower shortfalls, shiftwork-related fatigue, and degraded crewmember effectiveness. Limited experience and available research makes it difficult to qualitatively or quantitatively predict the collective impact of these issues on RPA crewmember performance. Attending to HSI will be critical for the success of current and future RPA crewmembers. Aerospace medicine practitioners working with RPA crewmembers should gain first-hand knowledge of their task environment while the larger aerospace medicine community needs to address the limited information available on RPA-related aerospace medicine human factors. In the meantime, aeromedical decisions will need to be made based on what is known about other aerospace occupations, realizing this knowledge may have only partial applicability.

Study of occupational stress among railway engine pilots

PubMed Central

Kumar, Devesh; Singh, Jai Vir; Kharwar, Poonam S.

2011-01-01

Background: Traffic volume and speed is going to be increased in Indian Railways successively, leading to higher stress in staff connected with train operations. The jobs of railway engine pilots come under the category of high-strain jobs, necessitating a need to conduct multicentric study to unfold the factors associated with occupational stress and organizational strategies. Materials and Methods: Present study covered 185 railway engine pilots and office clerks working in various railway zones by incidental method. Occupational Stress Index (OSI) test developed by Srivastva and Singh, questionnaire of specific stressors constructed by authors and laboratory test battery for psychological screening of high-speed train pilots were used as tools. Results: Means of OSI and all the 12 occupational stressors of railway engine pilots were found significantly higher to that of office clerks. Means of OSI and occupational stressors of goods train pilots were significantly higher in comparison to high-speed train pilots and passenger train pilots. Study revealed positive correlation of speed perception and complex reaction time tests and negative correlation of other constituent tests of laboratory test battery to OSI test. Highest subgroup of stressor observedwas role overload followed by role conflict. Conclusions: These findings provide a prima facie evidence of higher occupational stress among railway engine pilots because of identified specific stressors prevalent in their job and explore the possible intervention strategies for its reduction. Significant correlation is noticed between OSI and laboratory test results, indicating its relevant utility in preliminary psychological screening. PMID:21808497

Development Status of Reusable Rocket Engine

NASA Astrophysics Data System (ADS)

Yoshida, Makoto; Takada, Satoshi; Naruo, Yoshihiro; Niu, Kenichi

A 30-kN rocket engine, a pilot engine, is being developed in Japan. Development of this pilot engine has been initiated in relation to a reusable sounding rocket, which is also being developed in Japan. This rocket takes off vertically, reaches an altitude of 100 km, lands vertically at the launch site, and is launched again within several days. Due to advantage of reusability, successful development of this rocket will mean that observation missions can be carried out more frequently and economically. In order to realize this rocket concept, the engines installed on the rocket should be characterized by reusability, long life, deep throttling and health monitoring, features which have not yet been established in Japanese rocket engines. To solve the engineering factors entitled by those features, a new design methodology, advanced engine simulations and engineering testing are being focused on in the pilot engine development stage. Especially in engineering testing, limit condition data is acquired to facilitate development of new diagnostic techniques, which can be applied by utilizing the mobility of small-size hardware. In this paper, the development status of the pilot engine is described, including fundamental design and engineering tests of the turbopump bearing and seal, turbine rig, injector and combustion chamber, and operation and maintenance concepts for one hundred flights by a reusable rocket are examined.

Seamless Integration of Desktop and Mobile Learning Experience through an Ontology-Based Adaptation Engine: Report of a Pilot-Project

ERIC Educational Resources Information Center

Mercurio, Marco; Torre, Ilaria; Torsani, Simone

2014-01-01

The paper describes a module within the distance language learning environment of the Language Centre at the Genoa University which adapts, through an ontology, learning activities to the device in use. Adaptation means not simply resizing a page but also the ability to transform the nature of a task so that it fits the device with the smallest…

Pilot interaction with automated airborne decision making systems

NASA Technical Reports Server (NTRS)

Rouse, W. B.; Hammer, J. M.; Morris, N. M.; Knaeuper, A. E.; Brown, E. N.; Lewis, C. M.; Yoon, W. C.

1984-01-01

Two project areas were pursued: the intelligent cockpit and human problem solving. The first area involves an investigation of the use of advanced software engineering methods to aid aircraft crews in procedure selection and execution. The second area is focused on human problem solving in dynamic environments, particulary in terms of identification of rule-based models land alternative approaches to training and aiding. Progress in each area is discussed.

Staged direct injection diesel engine

DOEpatents

Baker, Quentin A.

1985-01-01

A diesel engine having staged injection for using lower cetane number fuels than No. 2 diesel fuel. The engine includes a main fuel injector and a pilot fuel injector. Pilot and main fuel may be the same fuel. The pilot injector injects from five to fifteen percent of the total fuel at timings from 20.degree. to 180.degree. BTDC depending upon the quantity of pilot fuel injected, the fuel cetane number and speed and load. The pilot fuel injector is directed toward the centerline of the diesel cylinder and at an angle toward the top of the piston, avoiding the walls of the cylinder. Stratification of the early injected pilot fuel is needed to reduce the fuel-air mixing rate, prevent loss of pilot fuel to quench zones, and keep the fuel-air mixture from becoming too fuel lean to become effective. In one embodiment, the pilot fuel injector includes a single hole for injection of the fuel and is directed at approximately 48.degree. below the head of the cylinder.

78 FR 66252 - Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) Helicopters

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-05

... actions are intended to alert pilots to avoid certain engine speeds during steady- state operations...%. The proposed requirements were intended to alert pilots to avoid certain engine speeds during steady... the RFMs, advising pilots of the change, and installing a decal as described in Bell Alert Service...

Pilot Transition Courses for Complex Single-Engine and Light Twin-Engine Airplanes.

ERIC Educational Resources Information Center

Federal Aviation Administration (DOT), Washington, DC.

This publication is intended for use by certificated airplane pilots and provides transitional knowledge and skills for more complex single-engine or light twin-engine airplanes. The training should be conducted by a competent flight instructor certified in the class of airplane and familiar with the make and model. A syllabus outline of ground…

A simulation evaluation of the engine monitoring and control system display

NASA Technical Reports Server (NTRS)

Abbott, Terence S.

1990-01-01

The Engine Monitoring and Control System (E-MACS) display is a new concept for an engine instrument display, the purpose of which is to provide an enhanced means for a pilot to control and monitor aircraft engine performance. It provides graphically-presented information about performance capabilities, current performance, and engine component or subsystem operational conditions relative to nominal conditions. The concept was evaluated by sixteen pilot-subjects against a traditional, state-of-the-art electronic engine display format. The results of this evaluation showed a substantial pilot preference for the E-MACS display relative to the traditional display. The results of the failure detection portion of the evaluation showed a 100 percent detection rate for the E-MACS display relative to a 57 percent rate for the traditional display. From these results, it is concluded that by providing this type of information in the cockpit, a reduction in pilot workload and an enhanced ability for detecting degraded or off-nominal conditions is probable, thus leading to an increase in operational safety.

Pilots and Flight Engineers. Aviation Careers Series.

ERIC Educational Resources Information Center

Zaharevitz, Walter

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

MD-11 PCA - Research flight team photo

NASA Technical Reports Server (NTRS)

1995-01-01

On Aug. 30, 1995, a the McDonnell Douglas MD-11 transport aircraft landed equipped with a computer-assisted engine control system that has the potential to increase flight safety. In landings at NASA Dryden Flight Research Center, Edwards, California, on August 29 and 30, the aircraft demonstrated software used in the aircraft's flight control computer that essentially landed the MD-11 without a need for the pilot to manipulate the flight controls significantly. In partnership with McDonnell Douglas Aerospace (MDA), with Pratt & Whitney and Honeywell helping to design the software, NASA developed this propulsion-controlled aircraft (PCA) system following a series of incidents in which hydraulic failures resulted in the loss of flight controls. This new system enables a pilot to operate and land the aircraft safely when its normal, hydraulically-activated control surfaces are disabled. This August 29, 1995, photo shows the MD-11 team. Back row, left to right: Tim Dingen, MDA pilot; John Miller, MD-11 Chief pilot (MDA); Wayne Anselmo, MD-11 Flight Test Engineer (MDA); Gordon Fullerton, PCA Project pilot; Bill Burcham, PCA Chief Engineer; Rudey Duran, PCA Controls Engineer (MDA); John Feather, PCA Controls Engineer (MDA); Daryl Townsend, Crew Chief; Henry Hernandez, aircraft mechanic; Bob Baron, PCA Project Manager; Don Hermann, aircraft mechanic; Jerry Cousins, aircraft mechanic; Eric Petersen, PCA Manager (Honeywell); Trindel Maine, PCA Data Engineer; Jeff Kahler, PCA Software Engineer (Honeywell); Steve Goldthorpe, PCA Controls Engineer (MDA). Front row, left to right: Teresa Hass, Senior Project Management Analyst; Hollie Allingham (Aguilera), Senior Project Management Analyst; Taher Zeglum, PCA Data Engineer (MDA); Drew Pappas, PCA Project Manager (MDA); John Burken, PCA Control Engineer.

Taking emotion seriously: meeting students where they are.

PubMed

Sunderland, Mary E

2014-03-01

Emotions are often portrayed as subjective judgments that pose a threat to rationality and morality, but there is a growing literature across many disciplines that emphasizes the centrality of emotion to moral reasoning. For engineers, however, being rational usually means sequestering emotions that might bias analyses-good reasoning is tied to quantitative data, math, and science. This paper brings a new pedagogical perspective that strengthens the case for incorporating emotions into engineering ethics. Building on the widely established success of active and collaborative learning environments, in particular the problem-based learning (PBL) philosophy and methodology, the paper articulates new strategies for incorporating emotion into engineering ethics education. An ethics education pilot study is analyzed to explore how PBL can engage students' emotions. Evidence suggests that PBL empowers students to cultivate value for engineering ethics and social responsibility, and in doing so, redefine the societal role of the engineer. Taking students' emotions seriously in engineering ethics offers an effective strategy to meaningfully engage students in ethical learning.

Aircraft control forces and EMG activity in a C-130 Hercules during strength-critical maneuvers.

PubMed

Hewson, D J; McNair, P J; Marshall, R N

2001-03-01

The force levels required to operate aircraft controls should be readily generated by pilots, without undue fatigue or exertion. However, maximum pilot applied forces, as specified in aircraft design standards, were empirically derived from the subjective comments of test pilots, and may not be applicable for the majority of pilots. Further, experienced RNZAF Hercules flying instructors have indicated that endurance and fatigue are problems for Hercules pilots. The aim of this study was to quantify aircraft control forces during emergency maneuvers in a Hercules aircraft and compare these forces with design standards. In addition, EMG data were recorded as an indicator of muscle fatigue during flight. Six subjects were tested in a C-130 Hercules aircraft. The maneuvers performed were low-level dynamic flight, one engine-off straight-and-level flight, and a two-engines-off simulated approach. The variables recorded were pilot-applied forces and EMG activity. Left rudder pedal force and vastus lateralis activity were both significantly greater during engine-off maneuvers than during low-level dynamic flight (p < 0.05). Maximum aircraft control forces for all controls were within 10% of the design standards. The mean EMG activity across all muscles and maneuvers was 26% MVC, with a peak of 61% MVC in vastus lateralis during the two-engine-off approach. The median frequency of the vastus lateralis EMG signal decreased 13.0% and 16.0% for the one engine-off and two-engine-off maneuvers, respectively. The forces required to fly a Hercules aircraft during emergency maneuvers are similar to the aircraft design standards. However, the levels of vastus lateralis muscle activation observed during the engine-off maneuvers can be sustained for approximately 1 min only. Thus, if two engines fail more than 1 min before landing, pilots may have to alternate control of the aircraft to share the workload and enable the aircraft to land safely.

Pilot-Scale Laboratory Instruction for Chemical Engineering: The Specific Case of the Pilot-Unit Leading Group

ERIC Educational Resources Information Center

Billet, Anne-Marie; Camy, Severine; Coufort-Saudejaud, Carole

2010-01-01

This paper presents an original approach for Chemical Engineering laboratory teaching that is currently applied at INP-ENSIACET (France). This approach, referred to as "pilot-unit leading group" is based on a partial management of the laboratories by the students themselves who become temporarily in charge of one specific laboratory. In…

Domain-specific languages and diagram customization for a concurrent engineering environment

NASA Astrophysics Data System (ADS)

Cole, B.; Dubos, G.; Banazadeh, P.; Reh, J.; Case, K.; Wang, Y.; Jones, S.; Picha, F.

A major open question for advocates of Model-Based Systems Engineering (MBSE) is the question of how system and subsystem engineers will work together. The Systems Modeling Language (SysML), like any language intended for a large audience, is in tension between the desires for simplicity and for expressiveness. In order to be more expressive, many specialized language elements may be introduced, which will unfortunately make a complete understanding of the language a more daunting task. While this may be acceptable for systems modelers, it will increase the challenge of including subsystem engineers in the modeling effort. One possible answer to this situation is the use of Domain-Specific Languages (DSL), which are fully supported by the Unified Modeling Language (UML). SysML is in fact a DSL for systems engineering. The expressive power of a DSL can be enhanced through the use of diagram customization. Various domains have already developed their own schematic vocabularies. Within the space engineering community, two excellent examples are the propulsion and telecommunication subsystems. A return to simple box-and-line diagrams (e.g., the SysML Internal Block Diagram) are in many ways a step backward. In order allow subsystem engineers to contribute directly to the model, it is necessary to make a system modeling tool at least approximate in accessibility to drawing tools like Microsoft PowerPoint and Visio. The challenge is made more extreme in a concurrent engineering environment, where designs must often be drafted in an hour or two. In the case of the Jet Propulsion Laboratory's Team X concurrent design team, a subsystem is specified using a combination of PowerPoint for drawing and Excel for calculation. A pilot has been undertaken in order to meld the drawing portion and the production of master equipment lists (MELs) via a SysML authoring tool, MagicDraw. Team X currently interacts with its customers in a process of sharing presentations. There are severa- inefficiencies that arise from this situation. The first is that a customer team must wait two weeks to a month (which is 2-4 times the duration of most Team X studies themselves) for a finalized, detailed design description. Another is that this information must be re-entered by hand into the set of engineering artifacts and design tools that the mission concept team uses after a study is complete. Further, there is no persistent connection to Team X or institutionally shared formulation design tools and data after a given study, again reducing the direct reuse of designs created in a Team X study. This paper presents the underpinnings of subsystem DSLs as they were developed for this pilot. This includes specialized semantics for different domains as well as the process by which major categories of objects were derived in support of defining the DSLs. The feedback given to us by the domain experts on usability, along with a pilot study with the partial inclusion of these tools is also discussed.

Domain-Specific Languages and Diagram Customization for a Concurrent Engineering Environment

NASA Technical Reports Server (NTRS)

Cole, Bjorn; Dubos, Greg; Banazadeh, Payam; Reh, Jonathan; Case, Kelley; Wang, Yeou-Fang; Jones, Susan; Picha, Frank

2013-01-01

A major open question for advocates of Model-Based Systems Engineering (MBSE) is the question of how system and subsystem engineers will work together. The Systems Modeling Language (SysML), like any language intended for a large audience, is in tension between the desires for simplicity and for expressiveness. In order to be more expressive, many specialized language elements may be introduced, which will unfortunately make a complete understanding of the language a more daunting task. While this may be acceptable for systems modelers, it will increase the challenge of including subsystem engineers in the modeling effort. One possible answer to this situation is the use of Domain-Specific Languages (DSL), which are fully supported by the Unified Modeling Language (UML). SysML is in fact a DSL for systems engineering. The expressive power of a DSL can be enhanced through the use of diagram customization. Various domains have already developed their own schematic vocabularies. Within the space engineering community, two excellent examples are the propulsion and telecommunication subsystems. A return to simple box-and-line diagrams (e.g., the SysML Internal Block Diagram) are in many ways a step backward. In order allow subsystem engineers to contribute directly to the model, it is necessary to make a system modeling tool at least approximate in accessibility to drawing tools like Microsoft PowerPoint and Visio. The challenge is made more extreme in a concurrent engineering environment, where designs must often be drafted in an hour or two. In the case of the Jet Propulsion Laboratory's Team X concurrent design team, a subsystem is specified using a combination of PowerPoint for drawing and Excel for calculation. A pilot has been undertaken in order to meld the drawing portion and the production of master equipment lists (MELs) via a SysML authoring tool, MagicDraw. Team X currently interacts with its customers in a process of sharing presentations. There are several inefficiencies that arise from this situation. The first is that a customer team must wait two weeks to a month (which is 2-4 times the duration of most Team X studies themselves) for a finalized, detailed design description. Another is that this information must be re-entered by hand into the set of engineering artifacts and design tools that the mission concept team uses after a study is complete. Further, there is no persistent connection to Team X or institutionally shared formulation design tools and data after a given study, again reducing the direct reuse of designs created in a Team X study. This paper presents the underpinnings of subsystem DSLs as they were developed for this pilot. This includes specialized semantics for different domains as well as the process by which major categories of objects were derived in support of defining the DSLs. The feedback given to us by the domain experts on usability, along with a pilot study with the partial inclusion of these tools is also discussed.

Pilot-in-the-Loop Evaluation of a Yaw Rate to Throttle Feedback Control with Enhanced Engine Response

NASA Technical Reports Server (NTRS)

Litt, Jonathan S.; Guo, Ten-Huei; Sowers, T. Shane; Chicatelli, Amy K.; Fulton, Christopher E.; May, Ryan D.; Owen, A. Karl

2012-01-01

This paper describes the implementation and evaluation of a yaw rate to throttle feedback system designed to replace a damaged rudder. It can act as a Dutch roll damper and as a means to facilitate pilot input for crosswind landings. Enhanced propulsion control modes were implemented to increase responsiveness and thrust level of the engine, which impact flight dynamics and performance. Piloted evaluations were performed to determine the capability of the engines to substitute for the rudder function under emergency conditions. The results showed that this type of implementation is beneficial, but the engines' capability to replace the rudder is limited.

Using Genre Analysis To Teach Writing in Engineering. Report on a Pilot Video-Teleconference for Engineering Teaching Assistants and Writing Center Consultants.

ERIC Educational Resources Information Center

Alford, Elisabeth; And Others

A pilot project tested and evaluated teleconferencing as a medium for training engineering teaching assistants in technical writing. The teleconference, which linked 15 participants in the engineering departments and writing centers of the University of South Carolina and Ohio State University, also included a training session on the use of genre…

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…

Engineering workstation: Sensor modeling

NASA Technical Reports Server (NTRS)

Pavel, M; Sweet, B.

1993-01-01

The purpose of the engineering workstation is to provide an environment for rapid prototyping and evaluation of fusion and image processing algorithms. Ideally, the algorithms are designed to optimize the extraction of information that is useful to a pilot for all phases of flight operations. Successful design of effective fusion algorithms depends on the ability to characterize both the information available from the sensors and the information useful to a pilot. The workstation is comprised of subsystems for simulation of sensor-generated images, image processing, image enhancement, and fusion algorithms. As such, the workstation can be used to implement and evaluate both short-term solutions and long-term solutions. The short-term solutions are being developed to enhance a pilot's situational awareness by providing information in addition to his direct vision. The long term solutions are aimed at the development of complete synthetic vision systems. One of the important functions of the engineering workstation is to simulate the images that would be generated by the sensors. The simulation system is designed to use the graphics modeling and rendering capabilities of various workstations manufactured by Silicon Graphics Inc. The workstation simulates various aspects of the sensor-generated images arising from phenomenology of the sensors. In addition, the workstation can be used to simulate a variety of impairments due to mechanical limitations of the sensor placement and due to the motion of the airplane. Although the simulation is currently not performed in real-time, sequences of individual frames can be processed, stored, and recorded in a video format. In that way, it is possible to examine the appearance of different dynamic sensor-generated and fused images.

Complex Adaptive Systems of Systems (CASoS) engineering and foundations for global design.

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

Brodsky, Nancy S.; Finley, Patrick D.; Beyeler, Walter Eugene

2012-01-01

Complex Adaptive Systems of Systems, or CASoS, are vastly complex ecological, sociological, economic and/or technical systems which must be recognized and reckoned with to design a secure future for the nation and the world. Design within CASoS requires the fostering of a new discipline, CASoS Engineering, and the building of capability to support it. Towards this primary objective, we created the Phoenix Pilot as a crucible from which systemization of the new discipline could emerge. Using a wide range of applications, Phoenix has begun building both theoretical foundations and capability for: the integration of Applications to continuously build common understandingmore » and capability; a Framework for defining problems, designing and testing solutions, and actualizing these solutions within the CASoS of interest; and an engineering Environment required for 'the doing' of CASoS Engineering. In a secondary objective, we applied CASoS Engineering principles to begin to build a foundation for design in context of Global CASoS« less

Aviation-Related Wildland Firefighter Fatalities--United States, 2000-2013.

PubMed

Butler, Corey R; O'Connor, Mary B; Lincoln, Jennifer M

2015-07-31

Airplanes and helicopters are integral to the management and suppression of wildfires, often operating in high-risk, low-altitude environments. To update data on aviation-related wildland firefighting fatalities, identify risk factors, and make recommendations for improved safety, CDC's National Institute for Occupational Safety and Health (NIOSH) analyzed reports from multiple data sources for the period 2000-2013. Among 298 wildland firefighter fatalities identified during 2000-2013, 78 (26.2%) were aviation-related occupational fatalities that occurred during 41 separate events involving 42 aircraft. Aircraft crashes accounted for 38 events. Pilots, copilots, and flight engineers represented 53 (68%) of the aviation-related fatalities. The leading causes of fatal aircraft crashes were engine, structure, or component failure (24%); pilot loss of control (24%); failure to maintain clearance from terrain, water, or objects (20%); and hazardous weather (15%). To reduce fatalities from aviation-related wildland firefighting activities, stringent safety guidelines need to be followed during all phases of firefighting, including training exercises. Crew resource management techniques, which use all available resources, information, equipment, and personnel to achieve safe and efficient flight operations, can be applied to firefighting operations.

The technology improvement and development of the new design-engineering principles of pilot bore directional drilling

NASA Astrophysics Data System (ADS)

Shadrina, A.; Saruev, L.; Vasenin, S.

2016-09-01

This paper addresses the effectiveness of impact energy use in pilot bore directional drilling at pipe driving. We establish and develop new design-engineering principles for this method. These principles are based on a drill string construction with a new nipple thread connection and a generator construction of strain waves transferred through the drill string. The experiment was conducted on a test bench. Strain measurement is used to estimate compression, tensile, shear and bending stresses in the drill string during the propagation of elastic waves. Finally, the main directions of pilot bore directional drilling improvement during pipe driving are determinated. The new engineering design, as components of the pilot bore directional drilling technology are presented.

Mixer assembly for a gas turbine engine having a pilot mixer with a corner flame stabilizing recirculation zone

NASA Technical Reports Server (NTRS)

Dai, Zhongtao (Inventor); Cohen, Jeffrey M. (Inventor); Fotache, Catalin G. (Inventor)

2012-01-01

A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing in which a corner is formed between an aft portion of the housing and a bulkhead wall in which a corner recirculation zone is located to stabilize and anchor the flame of the pilot mixer. The pilot mixer can further include features to cool the annular housing, including in the area of the corner recirculation zone.

Engine monitoring display study

NASA Technical Reports Server (NTRS)

Hornsby, Mary E.

1992-01-01

The current study is part of a larger NASA effort to develop displays for an engine-monitoring system to enable the crew to monitor engine parameter trends more effectively. The objective was to evaluate the operational utility of adding three types of information to the basic Boeing Engine Indicating and Crew Alerting System (EICAS) display formats: alphanumeric alerting messages for engine parameters whose values exceed caution or warning limits; alphanumeric messages to monitor engine parameters that deviate from expected values; and a graphic depiction of the range of expected values for current conditions. Ten training and line pilots each flew 15 simulated flight scenarios with five variants of the basic EICAS format; these variants included different combinations of the added information. The pilots detected engine problems more quickly when engine alerting messages were included in the display; adding a graphic depiction of the range of expected values did not affect detection speed. The pilots rated both types of alphanumeric messages (alert and monitor parameter) as more useful and easier to interpret than the graphic depiction. Integrating engine parameter messages into the EICAS alerting system appears to be both useful and preferred.

Use of a remotely piloted aircraft system for hazard assessment in a rocky mining area (Lucca, Italy)

NASA Astrophysics Data System (ADS)

Salvini, Riccardo; Mastrorocco, Giovanni; Esposito, Giuseppe; Di Bartolo, Silvia; Coggan, John; Vanneschi, Claudio

2018-01-01

The use of remote sensing techniques is now common practice in different working environments, including engineering geology. Moreover, in recent years the development of structure from motion (SfM) methods, together with rapid technological improvement, has allowed the widespread use of cost-effective remotely piloted aircraft systems (RPAS) for acquiring detailed and accurate geometrical information even in evolving environments, such as mining contexts. Indeed, the acquisition of remotely sensed data from hazardous areas provides accurate 3-D models and high-resolution orthophotos minimizing the risk for operators. The quality and quantity of the data obtainable from RPAS surveys can then be used for inspection of mining areas, audit of mining design, rock mass characterizations, stability analysis investigations and monitoring activities. Despite the widespread use of RPAS, its potential and limitations still have to be fully understood.In this paper a case study is shown where a RPAS was used for the engineering geological investigation of a closed marble mine area in Italy; direct ground-based techniques could not be applied for safety reasons. In view of the re-activation of mining operations, high-resolution images taken from different positions and heights were acquired and processed using SfM techniques to obtain an accurate and detailed 3-D model of the area. The geometrical and radiometrical information was subsequently used for a deterministic rock mass characterization, which led to the identification of two large marble blocks that pose a potential significant hazard issue for the future workforce. A preliminary stability analysis, with a focus on investigating the contribution of potential rock bridges, was then performed in order to demonstrate the potential use of RPAS information in engineering geological contexts for geohazard identification, awareness and reduction.

Single-Lever Power Control for General Aviation Aircraft Promises Improved Efficiency and Simplified Pilot Controls

NASA Technical Reports Server (NTRS)

Musgrave, Jeffrey L.

1997-01-01

General aviation research is leading to major advances in internal combustion engine control systems for single-engine, single-pilot aircraft. These advances promise to increase engine performance and fuel efficiency while substantially reducing pilot workload and increasing flight safety. One such advance is a single-lever power control (SLPC) system, a welcome departure from older, less user-friendly, multilever engine control systems. The benefits of using single-lever power controls for general aviation aircraft are improved flight safety through advanced engine diagnostics, simplified powerplant operations, increased time between overhauls, and cost-effective technology (extends fuel burn and reduces overhaul costs). The single-lever concept has proven to be so effective in preliminary studies that general aviation manufacturers are making plans to retrofit current aircraft with the technology and are incorporating it in designs for future aircraft.

[Communication and noise. Speech intelligibility of airplane pilots with and without active noise compensation].

PubMed

Matschke, R G

1994-08-01

Noise exposure measurements were performed with pilots of the German Federal Navy during flight situations. The ambient noise levels during regular flight were maintained at levels above a 90 dB A-weighted level. This noise intensity requires wearing ear protection to avoid sound-induced hearing loss. To be able to understand radio communication (ATC) in spite of a noisy environment, headphone volume must be raised above the noise of the engines. The use of ear plugs in addition to the headsets and flight helmets is only of limited value because personal ear protection affects the intelligibility of ATC. Whereas speech intelligibility of pilots with normal hearing is affected to only a smaller degree, pilots with pre-existing high-frequency hearing losses show substantial impairments of speech intelligibility that vary in proportion to the hearing deficit present. Communication abilities can be reduced drastically, which in turn can affect air traffic security. The development of active noise compensation devices (ANC) that make use of the "anti-noise" principle may be a solution to this dilemma. To evaluate the effectiveness of an ANC-system and its influence on speech intelligibility, speech audiometry was performed with a German standardized test during simulated flight conditions with helicopter pilots. Results demonstrate the helpful effect on speech understanding especially for pilots with noise-induced hearing losses. This may help to avoid pre-retirement professional disability.

78 FR 65161 - Airworthiness Directives; Agusta S.p.A. (Type Certificate Currently Held by AgustaWestland S.p.A...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-10-31

... engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain... alert pilots to avoid certain engine speeds during steady-state operations, prevent failure of the third...

Use of traffic displays for general aviation approach spacing : a human factors study

DOT National Transportation Integrated Search

2007-12-01

A flight experiment was conducted to assess human factors issues associated with pilot use of traffic displays for approach : spacing. Sixteen multi-engine rated pilots participated. Eight flew approaches in a twin-engine Piper Aztec originating in :...

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.

Simulator Investigation of Pilot Aids for Helicopter Terminal Area Operations with One Engine Inoperative

NASA Technical Reports Server (NTRS)

Iseler, Laura; Chen, Robert; Dearing, Munro; Decker, William; Aiken, Edwin W. (Technical Monitor)

1995-01-01

Two recent piloted simulation experiments have investigated advanced display concepts applied to civil transport helicopter terminal area operations. Civil Category A helicopter operations apply to multi-engine helicopters wherein a safe recovery (land or fly out) is required in the event of a single engine failure. The investigation used the NASA Ames Research Center Vertical Motion Simulator, which has a full six degrees of freedom, to simulate the flight task as closely as possible. The goal of these experiments was to use advanced cockpit displays to improve flight safety and enhance the mission performance of Category A terminal area operations in confined areas. The first experiment investigated the use of military display formats to assist civil rotorcraft in performing a Category A takeoff in confined terminal areas. Specifically, it addressed how well a difficult hovering backup path could be followed using conventional instruments in comparison to panel mounted integrated displays. The hovering backup takeoff, which enables pilots to land back to the confined area pad in the event of an engine failure, was chosen since it is a difficult task to perform. Seven NASA and Army test pilots participated in the experiment. Evaluations, based on task performance and pilot workload, showed that an integrated display enabled the pilot to consistently achieve adequate or desired performance with reasonable pilot workload. Use of conventional instruments, however, frequently resulted in unacceptable performance (poor flight path tracking), higher pilot workload, and poor situational awareness. Although OEI landbacks were considered a visual task, the improved performance on the backup portion, in conjunction with increased situational awareness resulting from use of integrated displays, enabled the pilots to handle an engine failure and land back safely. In contrast, use of conventional instruments frequently led to excessive rates of sink at touchdown. A second simulation (in progress - July - August) is being conducted to investigate the use of advanced displays to perform vertical and short takeoffs and landings. One Engine Inoperative trajectories, which were optimized based on safety of flight restrictions, are utilized. Based on comments from the first experiment and further analytic development, appropriate fly out and approach guidance was added. Displays include conventional instruments with raw data, and the following integrated displays: multi-view and side-view hover displays based on the Apache Pilot Night Vision System, and variations of the pathway-in-the-sky displays with a flight-path-vector, a leader and flight director modifications. Panel mounted and head-up displays are being evaluated. Engine modifications have been incorporated to simulate 30 second and 2 minute contingency power ratings. Evaluations are based on task performance and pilot workload. NASA, Army, FAA, and industry test pilots participated. Details concerning the design, conduct, and the results of the experiment will be reported in the proposed paper.

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

Code of Federal Regulations, 2013 CFR

2013-01-01

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

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

Code of Federal Regulations, 2012 CFR

2012-01-01

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

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

Code of Federal Regulations, 2014 CFR

2014-01-01

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

Model-Based Systems Engineering Pilot Program at NASA Langley

NASA Technical Reports Server (NTRS)

Vipavetz, Kevin G.; Murphy, Douglas G.; Infeld, Samatha I.

2012-01-01

NASA Langley Research Center conducted a pilot program to evaluate the benefits of using a Model-Based Systems Engineering (MBSE) approach during the early phase of the Materials International Space Station Experiment-X (MISSE-X) project. The goal of the pilot was to leverage MBSE tools and methods, including the Systems Modeling Language (SysML), to understand the net gain of utilizing this approach on a moderate size flight project. The System Requirements Review (SRR) success criteria were used to guide the work products desired from the pilot. This paper discusses the pilot project implementation, provides SysML model examples, identifies lessons learned, and describes plans for further use on MBSE on MISSE-X.

Connecting NASA Airborne Scientists, Engineers, and Pilots to K-12 Classrooms

NASA Astrophysics Data System (ADS)

Schaller, E. L.

2015-12-01

The NASA Airborne Science Program (ASP) conducts Earth system science research missions with NASA aircraft all over the world. During ASP missions, NASA scientists, engineers and pilots are deployed to remote parts of the world such as Greenland, Antarctica, Chile, and Guam. These ASP mission personnel often have a strong desire to share the excitement of their mission with local classrooms near their deployment locations as well as classrooms back home in the United States. Here we discuss ongoing efforts to connect NASA scientists, engineers and pilots in the field directly with K-12 classrooms through both in-person interactions and remotely via live web-based chats.

14 CFR 25.149 - Minimum control speed.

Code of Federal Regulations, 2014 CFR

2014-01-01

... (7) If applicable, the propeller of the inoperative engine— (i) Windmilling; (ii) In the most..., the propeller of the inoperative engine in the position it achieves without pilot action, assuming the... propeller of the more critical inoperative engine in the position it achieves without pilot action, assuming...

14 CFR 25.149 - Minimum control speed.

Code of Federal Regulations, 2013 CFR

2013-01-01

... (7) If applicable, the propeller of the inoperative engine— (i) Windmilling; (ii) In the most..., the propeller of the inoperative engine in the position it achieves without pilot action, assuming the... propeller of the more critical inoperative engine in the position it achieves without pilot action, assuming...

14 CFR 25.149 - Minimum control speed.

Code of Federal Regulations, 2012 CFR

2012-01-01

... (7) If applicable, the propeller of the inoperative engine— (i) Windmilling; (ii) In the most..., the propeller of the inoperative engine in the position it achieves without pilot action, assuming the... propeller of the more critical inoperative engine in the position it achieves without pilot action, assuming...

A comparison of effects of peripheral vision cues on pilot performance during instrument flight in dissimilar aircraft simulators.

DOT National Transportation Integrated Search

1968-09-01

Pilot response to peripheral vision cues relating to aircraft bank angle was studied during instrument flight in two simulators representing (1) a conventional, medium weight, piston engine airliner, and (2) a heavy, jet engine, sweptwing transport. ...

Towards the Integration of APECS with VE-Suite to Create a Comprehensive Virtual Engineering Environment

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

McCorkle, D.; Yang, C.; Jordan, T.

2007-06-01

Modeling and simulation tools are becoming pervasive in the process engineering practice of designing advanced power generation facilities. These tools enable engineers to explore many what-if scenarios before cutting metal or constructing a pilot scale facility. While such tools enable investigation of crucial plant design aspects, typical commercial process simulation tools such as Aspen Plus®, gPROMS®, and HYSYS® still do not explore some plant design information, including computational fluid dynamics (CFD) models for complex thermal and fluid flow phenomena, economics models for policy decisions, operational data after the plant is constructed, and as-built information for use in as-designed models. Softwaremore » tools must be created that allow disparate sources of information to be integrated if environments are to be constructed where process simulation information can be accessed. At the Department of Energy’s (DOE) National Energy Technology Laboratory (NETL), the Advanced Process Engineering Co-Simulator (APECS) has been developed as an integrated software suite that combines process simulation (e.g., Aspen Plus) and high-fidelity equipment simulation (e.g., Fluent® CFD), together with advanced analysis capabilities including case studies, sensitivity analysis, stochastic simulation for risk/uncertainty analysis, and multi-objective optimization. In this paper, we discuss the initial phases of integrating APECS with the immersive and interactive virtual engineering software, VE-Suite, developed at Iowa State University and Ames Laboratory. VE-Suite utilizes the ActiveX (OLE Automation) controls in Aspen Plus wrapped by the CASI library developed by Reaction Engineering International to run the process simulation and query for unit operation results. This integration permits any application that uses the VE-Open interface to integrate with APECS co-simulations, enabling construction of the comprehensive virtual engineering environment needed for the rapid engineering of advanced power generation facilities.« less

Piloted simulation study of the effects of an automated trim system on flight characteristics of a light twin-engine airplane with one engine inoperative

NASA Technical Reports Server (NTRS)

Stewart, E. C.; Brown, P. W.; Yenni, K. R.

1986-01-01

A simulation study was conducted to investigate the piloting problems associated with failure of an engine on a generic light twin-engine airplane. A primary piloting problem for a light twin-engine airplane after an engine failure is maintaining precise control of the airplane in the presence of large steady control forces. To address this problem, a simulated automatic trim system which drives the trim tabs as an open-loop function of propeller slipstream measurements was developed. The simulated automatic trim system was found to greatly increase the controllability in asymmetric powered flight without having to resort to complex control laws or an irreversible control system. However, the trim-tab control rates needed to produce the dramatic increase in controllability may require special design consideration for automatic trim system failures. Limited measurements obtained in full-scale flight tests confirmed the fundamental validity of the proposed control law.

Pilot Specialists--The Potential for Dual-Track Personnel Management of U.S. Air Force Pilots

DTIC Science & Technology

1980-06-06

1976 MA, Management and Supervision, Central Michigan University (Extension), Washington, D.C. 1969 BS, Aeronautical Engineering , United States Air ...of Naval Research May 1976. 9C .. .. 64. Thomas, James M. "Retention of Scientists and Engineers -• in the Air Force; A modified Model for Interpreting...CATALOG NUMBER 4. __(mu #btle)S. TYPE OF REPORT & PERIOD COVERED Track Personnel Management-of U.*S. Air Force Pilots S. PERFORMING ORG. REPORT NUMBE 7

Career Profile- Subscale UAS engineer/pilot Robert "Red" Jensen- Operations Engineering Branch

NASA Image and Video Library

2015-08-03

Robert “Red” Jensen is an Operations Engineer and Pilot for subscale aircraft here at NASA’s Armstrong Flight Research Center. As part fabricator, engineer and integrator, Red is responsible for testing subscale models of aircraft and ensuring they are safe, capable of flight and ready to support the center’s needs. Operations engineers are key leaders from technical concept to flight to ensure flight safety and mission success. This video highlights Red’s responsibilities and daily activities as well as some of the projects and missions he is currently working on.

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

7. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK ...

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

7. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK FROM POINT NEAR ENGINE ROOM SKYLIGHT. ENGINE ROOM SKYLIGHT IS AT EXTREME LEFT, FOLLOWED BY PILOTS' CABIN SKYLIGHT, AFT COMPANIONWAY AND STEERING GEAR BOX - Pilot Schooner "Alabama", Moored in harbor at Vineyard Haven, Vineyard Haven, Dukes County, MA

General Aviation Pilot Advisory and Training System (GAPATS)

NASA Technical Reports Server (NTRS)

Painter, John; Ward, Donald T.; Kelly, Wallace; Crump, John W.; Phillips, Ron; Trang, Jeff; Lee, Kris; Branham, Paul A.; Krishnamurthy, Karthik; Alcorn, William P., Jr.;

[Pilot plant for microbiological synthesis. Engineer and technological aspects].

PubMed

Lukanin, A V

2007-01-01

A biotechnological pilot plant (National Research Centre of Antibiotics) and its technical potentialities in production of various biosynthetic products are described. Some engineer and technological aspects of the fermentation equipment and particularly sterilization of the media and apparatus, fermentation broth aeration under sterile conditions and control of biosynthesis technological parameters (t degrees, pO2, P, pH, foaming, etc.) are considered. The pilot plant is designed for fermentation processes under aseptic conditions with the use practically of any object, from bacteria to tissue cultures.

Investigation of the effect of pilot burner on lean blow out performance of a staged injector

NASA Astrophysics Data System (ADS)

Yang, Jinhu; Zhang, Kaiyu; Liu, Cunxi; Ruan, Changlong; Liu, Fuqiang; Xu, Gang

2014-12-01

The staged injector has exhibited great potential to achieve low emissions and is becoming the preferable choice of many civil airplanes. Moreover, it is promising to employ this injector design in military engine, which requires most of the combustion air enters the combustor through injector to reduce smoke emission. However, lean staged injector is prone to combustion instability and extinction in low load operation, so techniques for broadening its stable operation ranges are crucial for its application in real engine. In this work, the LBO performance of a staged injector is assessed and analyzed on a single sector test section. The experiment was done in atmospheric environment with optical access. Kerosene-PLIF technique was used to visualize the spray distribution and common camera was used to record the flame patterns. Emphasis is put on the influence of pilot burner on LBO performance. The fuel to air ratios at LBO of six injectors with different pilot swirler vane angle were evaluated and the obtained LBO data was converted into data at idle condition. Results show that the increase of pilot swirler vane angle could promote the air assisted atomization, which in turn improves the LBO performance slightly. Flame patterns typical in the process of LBO are analyzed and attempts are made to find out the main factors which govern the extinction process with the assistance of spray distribution and numerical flow field results. It can be learned that the flame patterns are mainly influenced by structure of the flow field just behind the pilot burner when the fuel mass flow rate is high; with the reduction of fuel, atomization quality become more and more important and is the main contributing factor of LBO. In the end of the paper, conclusions are drawn and suggestions are made for the optimization of the present staged injector.

Intelligent Adaptive Interfaces: Summary Report on Design, Development, and Evaluation of Intelligent Adaptive Interfaces for the Control of Multiple UAVs from an Airborne Platform

DTIC Science & Technology

2006-12-01

gestion de la masse d’informations nécessaires pour appuyer la prise de décision efficace. De l’avis des opérateurs d’engins télépilotés...opérateurs d’engins télépilotés risque de croître exponentiellement, de sorte que de fortes contraintes seront imposées au personnel exécutant les missions...commande réelle des engins télépilotés que la gestion des données, y compris la conversion de ces données en information et l’acheminement

Effects of visual and motion simulation cueing systems on pilot performance during takeoffs with engine failures

NASA Technical Reports Server (NTRS)

Parris, B. L.; Cook, A. M.

1978-01-01

Data are presented that show the effects of visual and motion during cueing on pilot performance during takeoffs with engine failures. Four groups of USAF pilots flew a simulated KC-135 using four different cueing systems. The most basic of these systems was of the instrument-only type. Visual scene simulation and/or motion simulation was added to produce the other systems. Learning curves, mean performance, and subjective data are examined. The results show that the addition of visual cueing results in significant improvement in pilot performance, but the combined use of visual and motion cueing results in far better performance.

Coal-water slurry fuel internal combustion engine and method for operating same

DOEpatents

McMillian, Michael H.

1992-01-01

An internal combustion engine fueled with a coal-water slurry is described. About 90 percent of the coal-water slurry charge utilized in the power cycle of the engine is directly injected into the main combustion chamber where it is ignited by a hot stream of combustion gases discharged from a pilot combustion chamber of a size less than about 10 percent of the total clearance volume of main combustion chamber with the piston at top dead center. The stream of hot combustion gases is provided by injecting less than about 10 percent of the total coal-water slurry charge into the pilot combustion chamber and using a portion of the air from the main combustion chamber that has been heated by the walls defining the pilot combustion chamber as the ignition source for the coal-water slurry injected into the pilot combustion chamber.

Development of a virtual flight simulator.

PubMed

Kuntz Rangel, Rodrigo; Guimarães, Lamartine N F; de Assis Correa, Francisco

2002-10-01

We present the development of a flight simulator that allows the user to interact in a created environment by means of virtual reality devices. This environment simulates the sight of a pilot in an airplane cockpit. The environment is projected in a helmet visor and allows the pilot to see inside as well as outside the cockpit. The movement of the airplane is independent of the movement of the pilot's head, which means that the airplane might travel in one direction while the pilot is looking at a 30 degrees angle with respect to the traveled direction. In this environment, the pilot will be able to take off, fly, and land the airplane. So far, the objects in the environment are geometrical figures. This is an ongoing project, and only partial results are available now.

10. VIEW LOOKING FORWARD ON STARBOARD SIDE OF MAIN DECK ...

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

10. VIEW LOOKING FORWARD ON STARBOARD SIDE OF MAIN DECK FROM POINT NEAR ENGINE CONTROL PANEL. DECKHOUSES, FROM LEFT TO RIGHT (STERN TO BOW), ARE AFT COMPANIONWAY, PILOTS' CABIN SKYLIGHT, ENGINE ROOM SKYLIGHT, AND GALLEY SKYLIGHT/COMPANIONWAY - Pilot Schooner "Alabama", Moored in harbor at Vineyard Haven, Vineyard Haven, Dukes County, MA

77 FR 25189 - Extension of Agency Information Collection Activity Under OMB Review: Federal Flight Deck Officer...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-04-27

... February 28, 2012, 77 FR 12069. The collection requires interested volunteers to fill out an application to... collection. OMB Control Number: 1652-0011. Forms(s): N/A. Affected Public: Volunteer pilots, flight engineers..., train, deputize, and supervise qualified volunteer pilots, flight engineers, and navigators to defend...

78 FR 65206 - Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) Helicopters

Federal Register 2010, 2011, 2012, 2013, 2014

2013-10-31

... engine speeds during steady- state operations. These actions are intended to alert pilots to avoid... intended to alert pilots to avoid certain engine speeds during steady- state operations, prevent failure of... decal as described in Bell Alert Service Bulletin (ASB) No. 430-05-34, dated June 10, 2005 (ASB 430-05...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2012 CFR

2012-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2010 CFR

2010-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2013 CFR

2013-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2014 CFR

2014-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

14 CFR 25.857 - Cargo compartment classification.

Code of Federal Regulations, 2011 CFR

2011-01-01

... detector or fire detector system to give warning at the pilot or flight engineer station. (c) Class C. A... compartment but in which— (1) There is a separate approved smoke detector or fire detector system to give... a separate approved smoke or fire detector system to give warning at the pilot or flight engineer...

2. CHANNEL DIMENSIONS AND ALIGNMENT RESEARCH INSTRUMENTATION. HYDRAULIC ENGINEER PILOTING ...

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

2. CHANNEL DIMENSIONS AND ALIGNMENT RESEARCH INSTRUMENTATION. HYDRAULIC ENGINEER PILOTING VIDEO-CONTROLED BOAT MODEL FROM CONTROL TRAILER. NOTE VIEW FROM BOAT-MOUNTED VIDEO CAMERA SHOWN ON MONITOR, AND MODEL WATERWAY VISIBLE THROUGH WINDOW AT LEFT. - Waterways Experiment Station, Hydraulics Laboratory, Halls Ferry Road, 2 miles south of I-20, Vicksburg, Warren County, MS

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.

New Engineering & Development Initiatives -- Policy and Technology Choices: Consensus Views of User/Aviation Industry Representatives. Volume I.

DTIC Science & Technology

1979-03-01

253 7.2 Enhancing MLS or ATARS 253 7.3 Weather Information 254 7.4 Other Safety Benefits 254 7.5 Human Factors 255 8.0 Pilot Training 256 8.1...Service (D)ABS/ ATARS ) in the terminal environment, what are the capacity/noise relation- ships under the new noise regulations at key hub airports, etc...whether manual or automatic, must be maintained at least during the DABS transition period and perhaps thereafter. Together with DABS/ ATARS the en

Medical symptoms among pilots associated with work and home environments: a 3-year cohort study.

PubMed

Fu, Xi; Lindgren, Torsten; Norbäck, Dan

2015-05-01

To study associations between the cockpit environment, psychosocial work environment, home environment, and medical symptoms in a cohort of commercial pilots followed over 3 yr. A standardized questionnaire was mailed in February-March 1997 to all Stockholm-based pilots on duty in a Scandinavian flight company (N = 622); 577 (93%) participated. During this time smoking was allowed on long haul flights, but not on shorter flights. Smoking was prohibited on all flights after September 1997. The same questionnaire was sent to the cohort of 577 pilots in February-March 2000; 436 participated (76%). The questionnaire contained questions on symptoms, the psychosocial work environment, and the home environment. Associations were investigated using multiple logistic and ordinal regression. Symptoms were common, especially eye symptoms (38.5%), nose symptoms (39.9%), and tiredness (29.9%). Pilots exposed to environmental tobacco smoke (ETS) on long haul flights had more eye symptoms (odds ratio = 1.91) and tiredness (odds ratio = 2.73). These symptoms were reduced when no longer exposed to ETS. Those who started working on long haul flights developed more nose symptoms. Pilots reporting increased work demands developed more nose and dermal symptoms and tiredness and those with decreased work control developed more eye symptoms. Pilots living in new houses, multifamily houses, and in recently painted homes reported more symptoms. Eliminating ETS exposure on board reduced medical symptoms. Further work to reduce ETS exposure globally is needed. Psychosocial aspects of the work environment for commercial pilots should be considered, as well as the home environment.

Laboratory and Pilot Scale Evaluation of Coagulation, Clarification, and Filtration for Upgrading Sewage Lagoon Effluents.

DTIC Science & Technology

1980-08-01

AD-AGAB 906 ARMY ENGINEER WATERWAYS EXPERIMENT STATION VICKSBURG--ETC FIG 14/2 LABORATORY AND PILOT SCALE EVALUATION OF COAGULATION, CLARIFICA -ETC U...FILTRATION FOR LWGRADING JEWAGE LAGOON EFFLUENTS~ w IL j0 ( M John ullinane, Jr., Richard A. hafer (0 Environmental Laboratory gel U. S. Army Engineer ...Shafer 9. PERFORMING ORGANIZATION NAME AND ADORESS SO. PROGRAM ELEMENT, PROJECT, TASK AREA a WORK UNIT NUMBERS U. S. Army Engineer Waterways Experiment

Deicing System Protects General Aviation Aircraft

NASA Technical Reports Server (NTRS)

2007-01-01

Kelly Aerospace Thermal Systems LLC worked with researchers at Glenn Research Center on deicing technology with assistance from the Small Business Innovation Research (SBIR) program. Kelly Aerospace acquired Northcoast Technologies Ltd., a firm that had conducted work on a graphite foil heating element under a NASA SBIR contract and developed a lightweight, easy-to-install, reliable wing and tail deicing system. Kelly Aerospace engineers combined their experiences with those of the Northcoast engineers, leading to the certification and integration of a thermoelectric deicing system called Thermawing, a DC-powered air conditioner for single-engine aircraft called Thermacool, and high-output alternators to run them both. Thermawing, a reliable anti-icing and deicing system, allows pilots to safely fly through ice encounters and provides pilots of single-engine aircraft the heated wing technology usually reserved for larger, jet-powered craft. Thermacool, an innovative electric air conditioning system, uses a new compressor whose rotary pump design runs off an energy-efficient, brushless DC motor and allows pilots to use the air conditioner before the engine even starts

Dropping In a Microgravity Environment (DIME) contest

NASA Technical Reports Server (NTRS)

2001-01-01

The first NASA Dropping In a Microgravity Environment (DIME) student competition pilot project came to a conclusion at the Glenn Research Center in April 2001. The competition involved high-school student teams who developed the concept for a microgravity experiment and prepared an experiment proposal. The two student teams - COSI Academy, sponsored by the Columbus Center of Science and Industry, and another team from Cincinnati, Ohio's Sycamore High School, designed a microgravity experiment, fabricated the experimental apparatus, and visited NASA Glenn to operate their experiment in the 2.2 Second Drop Tower. Here, students are briefed by NASA engineer Daniel Dietrich at the top of the drop tower. This image is from a digital still camera; higher resolution is not available.

NACA Pilots at the Aircraft Engine Research Laboratory

NASA Image and Video Library

1945-07-21

The Aircraft Engine Research Laboratory’s pilot corps during the final days of World War II: from left to right, Joseph Vensel, Howard Lilly, William Swann, and Joseph Walker. William “Eb” Gough joined the group months after this photograph. These men were responsible for flying the various National Advisory Committee for Aeronautics (NACA) aircraft to test new engine modifications, study ice buildup, and determine fuel performance. Vensel, a veteran pilot from Langley, was the Chief of Flight Operations and a voice of reason at the laboratory. In April 1947 Vensel was transferred to lead the new Muroc Flight Tests Unit in California until 1966. Lilly was a young pilot with recent Navy experience. Lilly also flew in the 1946 National Air Races. He followed Vensel to Muroc in July 1947 where he became the first NACA pilot to penetrate the sound barrier. On May 3, 1948, Lilly became the first NACA pilot to die in the line of duty. Swann was a young civilian pilot when he joined the NACA. He spent his entire career at the Cleveland laboratory, and led the flight operations group from the early 1960s until 1979. Two World War II veterans joined the crew after the war. Walker was a 24-year-old P–38 reconnaissance pilot. He joined the NACA as a physicist in early 1945 but soon worked his way into the cadre of pilots. Walker later gained fame as an X-plane pilot at Muroc and was killed in a June 1966 fatal crash. Gough survived being shot down twice during the war and was decorated for flying rescue missions in occupied areas.

Simulating Visual Attention Allocation of Pilots in an Advanced Cockpit Environment

NASA Technical Reports Server (NTRS)

Frische, F.; Osterloh, J.-P.; Luedtke, A.

2011-01-01

This paper describes the results of experiments conducted with human line pilots and a cognitive pilot model during interaction with a new 40 Flight Management System (FMS). The aim of these experiments was to gather human pilot behavior data in order to calibrate the behavior of the model. Human behavior is mainly triggered by visual perception. Thus, the main aspect was to setup a profile of human pilots' visual attention allocation in a cockpit environment containing the new FMS. We first performed statistical analyses of eye tracker data and then compared our results to common results of familiar analyses in standard cockpit environments. The comparison has shown a significant influence of the new system on the visual performance of human pilots. Further on, analyses of the pilot models' visual performance have been performed. A comparison to human pilots' visual performance revealed important improvement potentials.

Hybrid vehicle motor alignment

DOEpatents

Levin, Michael Benjamin

2001-07-03

A rotor of an electric motor for a motor vehicle is aligned to an axis of rotation for a crankshaft of an internal combustion engine having an internal combustion engine and an electric motor. A locator is provided on the crankshaft, a piloting tool is located radially by the first locator to the crankshaft. A stator of the electric motor is aligned to a second locator provided on the piloting tool. The stator is secured to the engine block. The rotor is aligned to the crankshaft and secured thereto.

Quick-disconnect harness system for helmet-mounted displays

NASA Astrophysics Data System (ADS)

Bapu, P. T.; Aulds, M. J.; Fuchs, Steven P.; McCormick, David M.

1992-10-01

We have designed a pilot's harness-mounted, high voltage quick-disconnect connectors with 62 pins, to transmit voltages up to 13.5 kV and video signals with 70 MHz bandwidth, for a binocular helmet-mounted display system. It connects and disconnects with power off, and disconnects 'hot' without pilot intervention and without producing external sparks or exposing hot embers to the explosive cockpit environment. We have implemented a procedure in which the high voltage pins disconnect inside a hermetically-sealed unit before the physical separation of the connector. The 'hot' separation triggers a crowbar circuit in the high voltage power supplies for additional protection. Conductor locations and shields are designed to reduce capacitance in the circuit and avoid crosstalk among adjacent circuits. The quick- disconnect connector and wiring harness are human-engineered to ensure pilot safety and mobility. The connector backshell is equipped with two hybrid video amplifiers to improve the clarity of the video signals. Shielded wires and coaxial cables are molded as a multi-layered ribbon for maximum flexibility between the pilot's harness and helmet. Stiff cabling is provided between the quick-disconnect connector and the aircraft console to control behavior during seat ejection. The components of the system have been successfully tested for safety, performance, ergonomic considerations, and reliability.

Using VineUp to Match Students with Alumni Industry Mentors in Engineering: A Pilot Study

ERIC Educational Resources Information Center

Halupa, Colleen; Henry, Matthew

2015-01-01

This pilot study evaluated users' perceptions of the effectiveness of the VineUp platform to match mentors from a large United States manufacturing firm and mechanical engineering students in an honors program at a small private university. Four mentor/mentee pairs were surveyed and interviewed at the end of the nine-month program. Although the…

Moving Real Exergaming Engines on the Web: The webFitForAll Case Study in an Active and Healthy Ageing Living Lab Environment.

PubMed

Konstantinidis, Evdokimos I; Bamparopoulos, Giorgos; Bamidis, Panagiotis D

2017-05-01

Exergames have been the subject of research and technology innovations for a number of years. Different devices and technologies have been utilized to train the body and the mind of senior people or different patient groups. In the past, we presented FitForAll, the protocol efficacy of which was proven through widely taken (controlled) pilots with more than 116 seniors for a period of two months. The current piece of work expands this and presents the first truly web exergaming platform, which is solely based on HTML5 and JavaScript without any browser plugin requirements. The adopted architecture (controller application communication framework) combines a unified solution for input devices such as MS Kinect and Wii Balance Βoard which may seamlessly be exploited through standard physical exercise protocols (American College of Sports Medicine guidelines) and accommodate high detail logging; this allows for proper pilot testing and usability evaluations in ecologically valid Living Lab environments. The latter type of setups is also used herein for evaluating the web application with more than a dozen of real elderly users following quantitative approaches.

Pilot Joe Walker in Lunar Landing Research Vehicle (LLRV) on ramp

NASA Technical Reports Server (NTRS)

1964-01-01

In this 1964 NASA Flight Research Center photograph, NASA Pilot Joe Walker is setting in the pilot's platform of the the Lunar Landing Research Vehicle (LLRV) number 1. This photograph provides a good view of the pilot setting in front of the primary instrumentation panel. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV, in case of jet engine failure, six-500-pounds-of thrust rockets could be used by the pilot to carefully apply lift thrust during the rapid descent to hopefully achieve a controllable landing. The pilot's platform extended forward between two legs while an electronics platform, similarly located, extended rearward. The pilot had a zero-zero ejection seat that would then lift him away to safety. Weight and balance design constraints were among the most challenging to meet for all phases of the program (design, development, operations). The two LLRVs were shipped disassembled from Bell to the FRC in April 1964, with program emphasis placed on vehicle No. 1. The scene then shifted to the old South Base area of Edwards Air Force Base. On the day of the first flight, Oct. 30, 1964, NASA research pilot Joe Walker flew it three times for a total of just under 60 seconds, to a peak altitude of approximately 10 feet. By mid-1966 the NASA Flight Research Center had accumulated enough data from the LLRV flight program to give Bell a contract to deliver three Lunar Landing Training Vehicles (LLTVs) at a cost of $2.5 million each. As 1966 ended, the LLRV #1 had flown 198 flights, and the LLRV #2 was being assembled, instrumented and cockpit modifications made at the South Base. The first flight of the number two LLRV in early January 1967 was quickly followed by five more. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in mid January 1967. When Dryden's LLRVs arrived at Houston they joined the first of the LLTVs to eventually make up the five-vehicle training and simulator fleet. All five vehicles were relied on for simulation and training of moon landings.

A System Engineering Approach to Strategic Partnership Development: A pilot study with NASA's Orbiting Carbon Observatory-2 (OCO-2) and the National Laboratory for Agriculture and the Environment (NLAE)

NASA Astrophysics Data System (ADS)

Yuen, K.; Chang, G.; Basilio, R. R.; Hatfield, J.; Cox, E. L.

2017-12-01

The prevalence and availability of NASA remote sensing data over the last 40+ years have produced many opportunities for the development of science derived data applications. However, extending and systematically integrating the applications into decision support models and tools have been sporadic and incomplete. Despite efforts among the research communities and external partners, implementation challenges exist and still remain to be addressed. In order to effectively address the systemic gap between the research and applications communities, steps must be taken to effectively bridge that gap: specific goals, a clear plan, and a concerted and diligent effort are needed to produce the desired results. The Orbiting Carbon Observatory-2 (OCO-2) mission sponsored a pilot effort on science data applications with the specific intent of building strategic partnerships, so that organizations and individuals could effectively use OCO-2 data products for application development. The successful partnership with the USDA/ARS National Laboratory for Agriculture and the Environment (NLAE) has laid the foundation for: 1) requirements and lessons for establishing a strategic partnership for application development, 2) building opportunities and growing partnerships for new missions such as OCO-3, and 3) the development of a methodology and approach for integrating application development into a mission life cycle. This presentation will provide an overview of the OCO-2 pilot effort, deliverables, the methodology, implementation, and best practices.

Virtual reality: a reality for future military pilotage?

NASA Astrophysics Data System (ADS)

McIntire, John P.; Martinsen, Gary L.; Marasco, Peter L.; Havig, Paul R.

2009-05-01

Virtual reality (VR) systems provide exciting new ways to interact with information and with the world. The visual VR environment can be synthetic (computer generated) or be an indirect view of the real world using sensors and displays. With the potential opportunities of a VR system, the question arises about what benefits or detriments a military pilot might incur by operating in such an environment. Immersive and compelling VR displays could be accomplished with an HMD (e.g., imagery on the visor), large area collimated displays, or by putting the imagery on an opaque canopy. But what issues arise when, instead of viewing the world directly, a pilot views a "virtual" image of the world? Is 20/20 visual acuity in a VR system good enough? To deliver this acuity over the entire visual field would require over 43 megapixels (MP) of display surface for an HMD or about 150 MP for an immersive CAVE system, either of which presents a serious challenge with current technology. Additionally, the same number of sensor pixels would be required to drive the displays to this resolution (and formidable network architectures required to relay this information), or massive computer clusters are necessary to create an entirely computer-generated virtual reality with this resolution. Can we presently implement such a system? What other visual requirements or engineering issues should be considered? With the evolving technology, there are many technological issues and human factors considerations that need to be addressed before a pilot is placed within a virtual cockpit.

Modeling Sources of Teaching Self-Efficacy for Science, Technology, Engineering, and Mathematics Graduate Teaching Assistants

PubMed Central

DeChenne, Sue Ellen; Koziol, Natalie; Needham, Mark; Enochs, Larry

2015-01-01

Graduate teaching assistants (GTAs) in science, technology, engineering, and mathematics (STEM) have a large impact on undergraduate instruction but are often poorly prepared to teach. Teaching self-efficacy, an instructor’s belief in his or her ability to teach specific student populations a specific subject, is an important predictor of teaching skill and student achievement. A model of sources of teaching self-efficacy is developed from the GTA literature. This model indicates that teaching experience, departmental teaching climate (including peer and supervisor relationships), and GTA professional development (PD) can act as sources of teaching self-efficacy. The model is pilot tested with 128 GTAs from nine different STEM departments at a midsized research university. Structural equation modeling reveals that K–12 teaching experience, hours and perceived quality of GTA PD, and perception of the departmental facilitating environment are significant factors that explain 32% of the variance in the teaching self-efficacy of STEM GTAs. This model highlights the important contributions of the departmental environment and GTA PD in the development of teaching self-efficacy for STEM GTAs. PMID:26250562

Technologies Render Views of Earth for Virtual Navigation

NASA Technical Reports Server (NTRS)

2012-01-01

On a December night in 1995, 159 passengers and crewmembers died when American Airlines Flight 965 flew into the side of a mountain while in route to Cali, Colombia. A key factor in the tragedy: The pilots had lost situational awareness in the dark, unfamiliar terrain. They had no idea the plane was approaching a mountain until the ground proximity warning system sounded an alarm only seconds before impact. The accident was of the kind most common at the time CFIT, or controlled flight into terrain says Trey Arthur, research aerospace engineer in the Crew Systems and Aviation Operations Branch at NASA s Langley Research Center. In situations such as bad weather, fog, or nighttime flights, pilots would rely on airspeed, altitude, and other readings to get an accurate sense of location. Miscalculations and rapidly changing conditions could contribute to a fully functioning, in-control airplane flying into the ground. To improve aviation safety by enhancing pilots situational awareness even in poor visibility, NASA began exploring the possibilities of synthetic vision creating a graphical display of the outside terrain on a screen inside the cockpit. How do you display a mountain in the cockpit? You have to have a graphics-powered computer, a terrain database you can render, and an accurate navigation solution, says Arthur. In the mid-1990s, developing GPS technology offered a means for determining an aircraft s position in space with high accuracy, Arthur explains. As the necessary technologies to enable synthetic vision emerged, NASA turned to an industry partner to develop the terrain graphical engine and database for creating the virtual rendering of the outside environment.

Systems Engineering Education Development(SEED)Case Study

NASA Technical Reports Server (NTRS)

Bagg, Thomas C., III; Brumfield, Mark D.; Jamison, Donald E.; Granata, Raymond L.; Casey, Carolyn A.

2003-01-01

The Systems Engineering Development Program (SEED) was initiated to help Goddard resolve a Systems Engineering skill shortage. The chronology of events and the experiences of the pilot program are outlined to describe the development of the present program. The program goals are included in order to give a focus on what the developers saw as the program drivers. Lessons learned from a pilot program were incorporated into the present program. This program is constantly learning from its past efforts and looks for continuous improvement. We list several future ideas for improvement and change.

UH-60A Black Hawk engineering simulation program. Volume 1: Mathematical model

NASA Technical Reports Server (NTRS)

Howlett, J. J.

1981-01-01

A nonlinear mathematical model of the UR-60A Black Hawk helicopter was developed. This mathematical model, which was based on the Sikorsky General Helicopter (Gen Hel) Flight Dynamics Simulation, provides NASA with an engineering simulation for performance and handling qualities evaluations. This mathematical model is total systems definition of the Black Hawk helicopter represented at a uniform level of sophistication considered necessary for handling qualities evaluations. The model is a total force, large angle representation in six rigid body degrees of freedom. Rotor blade flapping, lagging, and hub rotational degrees of freedom are also represented. In addition to the basic helicopter modules, supportive modules were defined for the landing interface, power unit, ground effects, and gust penetration. Information defining the cockpit environment relevant to pilot in the loop simulation is presented.

Genetic engineering approach to toxic waste management: case study for organophosphate waste treatment.

PubMed

Coppella, S J; DelaCruz, N; Payne, G F; Pogell, B M; Speedie, M K; Karns, J S; Sybert, E M; Connor, M A

1990-01-01

Currently, there has been limited use of genetic engineering for waste treatment. In this work, we are developing a procedure for the in situ treatment of toxic organophosphate wastes using the enzyme parathion hydrolase. Since this strategy is based on the use of an enzyme and not viable microorganisms, recombinant DNA technology could be used without the problems associated with releasing genetically altered microorganisms into the environment. The gene coding for parathion hydrolase was cloned into a Streptomyces lividans, and this transformed bacterium was observed to express and excrete this enzyme. Subsequently, fermentation conditions were developed to enhance enzyme production, and this fermentation was scaled-up to the pilot scale. The cell-free culture fluid (i.e., a nonpurified enzyme solution) was observed to be capable of effectively hydrolyzing organophosphate compounds under laboratory and simulated in situ conditions.

Aeronautical Research Engineer Milt Thompson computing data

NASA Technical Reports Server (NTRS)

1956-01-01

Milton O. Thompson was hired as an engineer at the National Advisory Committee for Aeronautics' High-Speed Flight Station (later renamed the National Aeronautics and Space Administration's Dryden Flight Research Center) on March 19, 1956. In 1958 he became a research pilot, but in this photo Milt is working on data from another pilot's research flight. Thompson began flying with the U.S. Navy as a pilot trainee at the age of 19. He subsequently served during World War II, with duty in China and Japan. Following six years of active naval service, he entered the University of Washington, in Seattle, Washington. Milt graduated in 1953 with a Bachelor of Science degree in Engineering. He remained in the Naval Reserves during college, and continued flying--not only naval aircraft but crop dusters and forest-spraying aircraft. After college graduation, Milt became a flight test engineer for the Boeing Aircraft Company in Seattle, where he was employed for two years before coming to the High-Speed Flight Station.

Flight deck engine advisor

NASA Technical Reports Server (NTRS)

Shontz, W. D.; Records, R. M.; Antonelli, D. R.

1992-01-01

The focus of this project is on alerting pilots to impending events in such a way as to provide the additional time required for the crew to make critical decisions concerning non-normal operations. The project addresses pilots' need for support in diagnosis and trend monitoring of faults as they affect decisions that must be made within the context of the current flight. Monitoring and diagnostic modules developed under the NASA Faultfinder program were restructured and enhanced using input data from an engine model and real engine fault data. Fault scenarios were prepared to support knowledge base development activities on the MONITAUR and DRAPhyS modules of Faultfinder. An analysis of the information requirements for fault management was included in each scenario. A conceptual framework was developed for systematic evaluation of the impact of context variables on pilot action alternatives as a function of event/fault combinations.

Motivational Engineering for Pilot Training.

ERIC Educational Resources Information Center

Herzberg, Frederick I.; And Others

The study was an investigation of student pilot motivation for, and toward, the Air Training Command's undergraduate pilot training (UPT) program. The motivation hygiene approach was used to identify the motivational factors operating in the UPT program systematically. This approach has been used extensively in industry and with success in a…

40 CFR 403.20 - Pretreatment Program Reinvention Pilot Projects Under Project XL.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 40 Protection of Environment 30 2013-07-01 2012-07-01 true Pretreatment Program Reinvention Pilot Projects Under Project XL. 403.20 Section 403.20 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY... OF POLLUTION § 403.20 Pretreatment Program Reinvention Pilot Projects Under Project XL. The Approval...

14 CFR 63.42 - Flight engineer certificate issued on basis of a foreign flight engineer license.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight engineer certificate issued on basis of a foreign flight engineer license. 63.42 Section 63.42 Aeronautics and Space FEDERAL AVIATION... PILOTS Flight Engineers § 63.42 Flight engineer certificate issued on basis of a foreign flight engineer...

14 CFR 63.42 - Flight engineer certificate issued on basis of a foreign flight engineer license.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Flight engineer certificate issued on basis of a foreign flight engineer license. 63.42 Section 63.42 Aeronautics and Space FEDERAL AVIATION... PILOTS Flight Engineers § 63.42 Flight engineer certificate issued on basis of a foreign flight engineer...

14 CFR 63.42 - Flight engineer certificate issued on basis of a foreign flight engineer license.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Flight engineer certificate issued on basis of a foreign flight engineer license. 63.42 Section 63.42 Aeronautics and Space FEDERAL AVIATION... PILOTS Flight Engineers § 63.42 Flight engineer certificate issued on basis of a foreign flight engineer...

14 CFR 63.42 - Flight engineer certificate issued on basis of a foreign flight engineer license.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Flight engineer certificate issued on basis of a foreign flight engineer license. 63.42 Section 63.42 Aeronautics and Space FEDERAL AVIATION... PILOTS Flight Engineers § 63.42 Flight engineer certificate issued on basis of a foreign flight engineer...

14 CFR 63.42 - Flight engineer certificate issued on basis of a foreign flight engineer license.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight engineer certificate issued on basis of a foreign flight engineer license. 63.42 Section 63.42 Aeronautics and Space FEDERAL AVIATION... PILOTS Flight Engineers § 63.42 Flight engineer certificate issued on basis of a foreign flight engineer...

Flight decks and free flight: where are the system boundaries?

PubMed

Hollnagel, Erik

2007-07-01

The change from managed to free flight is expected to have large effects, over and above the intended efficiency gains. Human factor concerns have understandably focused on how free flight may affect the pilots in the cockpit. Yet it is necessary to see the change from managed to free flight as more than just an increment to the pilots' work. Despite the best intentions the transition will not be a case of a smooth, carefully planned and therefore uneventful introduction of a new technology. It is more likely to be a substantial change to an already challenging working environment, in the air as well as on the ground. The significant effects will therefore not just happen within the existing structure or distribution of work and responsibilities, but affect the structure of work itself. This paper takes a look at free flight from a cognitive systems engineering perspective and identifies two major concerns: first what effects free flight has on the boundaries of the joint cognitive systems, and second how this affects demands to control. The conclusion is that both will change considerably and that we need to understand the nature of these changes before focusing on the possible effects of free flight on pilots' performance.

The Alert Program for Self-Management of Behaviour in Second Level Schools: Results of Phase 1 of a Pilot Study

ERIC Educational Resources Information Center

Mac Cobb, Siobhan; Fitzgerald, Brian; Lanigan-O'Keeffe, Carolyn

2014-01-01

This article reports on Phase 1 of a pilot programme on self-management of behaviour with challenging class groups of students as part of the evidence-informed practice of the National Behaviour Support Service. The Alert Program is a structured active learning programme using an engine analogy. The person's engine runs on high, low or just right…

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

Evaluation of engineering foods for Controlled Ecological Life Support Systems (CELSS)

NASA Technical Reports Server (NTRS)

Karel, M.

1982-01-01

The feasibility of developing acceptable and reliable engineered foods for use in controlled ecological support systems (CELSS) was evaluated. Food resupply and regeneration are calculated, flow charts of food processes in a multipurpose food pilot plant are presented, and equipment for a multipurpose food pilot plant and potential simplification of processes are discussed. Food-waste treatment and water usage in food processing and preparation are also considered.

Jet Engines - The New Masters of Advanced Flight Control

NASA Astrophysics Data System (ADS)

Gal-Or, Benjamin

2018-05-01

ANTICIPATED UNITED STATES CONGRESS ACT should lead to reversing a neglected duty to the people by supporting FAA induced bill to civilize classified military air combat technology to maximize flight safety of airliners and cargo jet transports, in addition to FAA certifying pilots to master Jet-Engine Steering ("JES") as automatic or pilot recovery when Traditional Aerodynamic-only Flight Control ("TAFC") fails to prevent a crash and other related damages

14 CFR 63.43 - Flight engineer courses.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight engineer courses. 63.43 Section 63...) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.43 Flight engineer courses. An applicant for approval of a flight engineer course must submit a letter to the Administrator...

14 CFR 63.43 - Flight engineer courses.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight engineer courses. 63.43 Section 63...) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.43 Flight engineer courses. An applicant for approval of a flight engineer course must submit a letter to the Administrator...

14 CFR 63.43 - Flight engineer courses.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Flight engineer courses. 63.43 Section 63...) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.43 Flight engineer courses. An applicant for approval of a flight engineer course must submit a letter to the Administrator...

14 CFR 121.565 - Engine inoperative: Landing; reporting.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Engine inoperative: Landing; reporting. 121... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Operations § 121.565 Engine... engine fails or whenever an engine is shutdown to prevent possible damage, the pilot in command must land...

14 CFR 63.43 - Flight engineer courses.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Flight engineer courses. 63.43 Section 63...) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.43 Flight engineer courses. An applicant for approval of a flight engineer course must submit a letter to the Administrator...

14 CFR 63.43 - Flight engineer courses.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Flight engineer courses. 63.43 Section 63...) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.43 Flight engineer courses. An applicant for approval of a flight engineer course must submit a letter to the Administrator...

14 CFR 121.565 - Engine inoperative: Landing; reporting.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Engine inoperative: Landing; reporting. 121... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Operations § 121.565 Engine... engine fails or whenever an engine is shutdown to prevent possible damage, the pilot in command must land...

14 CFR 121.565 - Engine inoperative: Landing; reporting.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Engine inoperative: Landing; reporting. 121... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Operations § 121.565 Engine... engine fails or whenever an engine is shutdown to prevent possible damage, the pilot in command must land...

14 CFR 121.565 - Engine inoperative: Landing; reporting.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Engine inoperative: Landing; reporting. 121... OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS Flight Operations § 121.565 Engine... engine fails or whenever an engine is shutdown to prevent possible damage, the pilot in command must land...

A Risk Assessment Architecture for Enhanced Engine Operation

NASA Technical Reports Server (NTRS)

Litt, Jonathan S.; Sharp. Lauren M.; Guo, Ten-Huei

2010-01-01

On very rare occasions, in-flight emergencies have occurred that required the pilot to utilize the aircraft's capabilities to the fullest extent possible, sometimes using actuators in ways for which they were not intended. For instance, when flight control has been lost due to damage to the hydraulic systems, pilots have had to use engine thrust to maneuver the plane to the ground and in for a landing. To assist the pilot in these situations, research is being performed to enhance the engine operation by making it more responsive or able to generate more thrust. Enabled by modification of the propulsion control, enhanced engine operation can increase the probability of a safe landing during an inflight emergency. However, enhanced engine operation introduces risk as the nominal control limits, such as those on shaft speed, temperature, and acceleration, are exceeded. Therefore, an on-line tool for quantifying this risk must be developed to ensure that the use of an enhanced control mode does not actually increase the overall danger to the aircraft. This paper describes an architecture for the implementation of this tool. It describes the type of data and algorithms required and the information flow, and how the risk based on engine component lifing and operability for enhanced operation is determined.

6. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK ...

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

6. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK FROM POINT NEAR GALLEY STOVE CHIMNEY. DECKHOUSES ARE (FORE TO AFT) GALLEY COMPANIONWAY, ENGINE ROOM SKYLIGHT, PILOTS' CABIN SKYLIGHT, AFT COMPANIONWAY TO PILOTS' CABIN AND STEERING GEAR BOX - Pilot Schooner "Alabama", Moored in harbor at Vineyard Haven, Vineyard Haven, Dukes County, MA

78 FR 65202 - Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) Helicopters

Federal Register 2010, 2011, 2012, 2013, 2014

2013-10-31

... engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain... operation between speeds of 71% and 92%. The proposed requirements were intended to alert pilots to avoid... amending the RFM, advising pilots of the change, and installing a decal as described in Bell Alert Service...

ON-SITE ENGINEERING REPORT OF THE SLURRY-PHASE BIOLOGICAL REACTOR FOR PILOT-SCALE TESTING ON CONTAMINATED SOIL

EPA Science Inventory

The performance of pilot-scale bioslurry treatment on creosote-contaminated soil was evaluated. Five reactors containing 66 L of slurry (30% soil by weight), were operated in parallel. The soil was a sandy soil with minor gravel content. The pilot-scale phase utilized an inoculum...

Pilot-in-the-Loop Analysis of Propulsive-Only Flight Control Systems

NASA Technical Reports Server (NTRS)

Chou, Hwei-Lan; Biezad, Daniel J.

1996-01-01

Longitudinal control system architectures are presented which directly couple flight stick motions to throttle commands for a multi-engine aircraft. This coupling enables positive attitude control with complete failure of the flight control system. The architectures chosen vary from simple feedback gains to classical lead-lag compensators with and without prefilters. Each architecture is reviewed for its appropriateness for piloted flight. The control systems are then analyzed with pilot-in-the-loop metrics related to bandwidth required for landing. Results indicate that current and proposed bandwidth requirements should be modified for throttles only flight control. Pilot ratings consistently showed better ratings than predicted by analysis. Recommendations are made for more robust design and implementation. The use of Quantitative Feedback Theory for compensator design is discussed. Although simple and effective augmented control can be achieved in a wide variety of failed configurations, a few configuration characteristics are dominant for pilot-in-the-loop control. These characteristics will be tested in a simulator study involving failed flight controls for a multi-engine aircraft.

Flight test experience and controlled impact of a large, four-engine, remotely piloted airplane

NASA Technical Reports Server (NTRS)

Kempel, R. W.; Horton, T. W.

1985-01-01

A controlled impact demonstration (CID) program using a large, four engine, remotely piloted transport airplane was conducted. Closed loop primary flight control was performed from a ground based cockpit and digital computer in conjunction with an up/down telemetry link. Uplink commands were received aboard the airplane and transferred through uplink interface systems to a highly modified Bendix PB-20D autopilot. Both proportional and discrete commands were generated by the ground pilot. Prior to flight tests, extensive simulation was conducted during the development of ground based digital control laws. The control laws included primary control, secondary control, and racetrack and final approach guidance. Extensive ground checks were performed on all remotely piloted systems. However, manned flight tests were the primary method of verification and validation of control law concepts developed from simulation. The design, development, and flight testing of control laws and the systems required to accomplish the remotely piloted mission are discussed.

[Distance learning using internet in the field of bioengineering].

PubMed

Ciobanu, O

2003-01-01

The Leonardo da Vinci training programme supports innovative transnational initiatives for promoting the knowledge, aptitudes and skills necessary for successful integration into working life. Biomedical engineering is an emerging interdisciplinary field that contributes to understand, define and solve problems in biomedical technology within industrial and health service contexts. Paper presents a Leonardo da Vinci pilot-project called Web-based learning and training in the field of biomedical and design engineering (WEBD). This project has started on 2001. The WEBD project proposes to use advanced learning technologies to provide education in the www. Project uses interactive 3D graphics and virtual reality tools. The WEBD distance training permits users to experience and interact with a life-like model or environment, in safety and at convenient times, while providing a degree of control over the simulation that is usually not possible in the real-life situation.

Lunar Landing Research Vehicle (LLRV) engine test firing on ramp

NASA Technical Reports Server (NTRS)

1964-01-01

This 1964 NASA Flight Reserch Center photograph shows a ground engine test underway on the Lunar Landing Research Vehicle (LLRV) number 1. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV, in case of jet engine failure, six-500-pounds-of thrust rockets could be used by the pilot to carefully apply lift thrust during the rapid descent to hopefully achieve a controllable landing. The pilot's platform extended forward between two legs while an electronics platform, similarly located, extended rearward. The pilot had a zero-zero ejection seat that would then lift him away to safety. Weight and balance design constraints were among the most challenging to meet for all phases of the program (design, development, operations). The two LLRVs were shipped disassembled from Bell to the FRC in April 1964, with program emphasis placed on vehicle No. 1. The scene then shifted to the old South Base area of Edwards Air Force Base. On the day of the first flight, Oct. 30, 1964, NASA research pilot Joe Walker flew it three times for a total of just under 60 seconds, to a peak altitude of approximately 10 feet. By mid-1966 the NASA Flight Research Center had accumulated enough data from the LLRV flight program to give Bell a contract to deliver three Lunar Landing Training Vehicles (LLTVs) at a cost of $2.5 million each. As 1966 ended, the LLRV #1 had flown 198 flights, and the LLRV #2 was being assembled, instrumented and cockpit modifications made at the South Base. The first flight of the number two LLRV in early January 1967 was quickly followed by five more. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in mid January 1967. When Dryden's LLRVs arrived at Houston they joined the first of the LLTVs to eventually make up the five-vehicle training and simulator fleet. All five vehicles were relied on for simulation and training of moon landings.

A Computer Environment for Beginners' Learning of Sorting Algorithms: Design and Pilot Evaluation

ERIC Educational Resources Information Center

Kordaki, M.; Miatidis, M.; Kapsampelis, G.

2008-01-01

This paper presents the design, features and pilot evaluation study of a web-based environment--the SORTING environment--for the learning of sorting algorithms by secondary level education students. The design of this environment is based on modeling methodology, taking into account modern constructivist and social theories of learning while at…

Shape optimization of tibial prosthesis components

NASA Technical Reports Server (NTRS)

Saravanos, D. A.; Mraz, P. J.; Davy, D. T.

1993-01-01

NASA technology and optimal design methodologies originally developed for the optimization of composite structures (engine blades) are adapted and applied to the optimization of orthopaedic knee implants. A method is developed enabling the shape tailoring of the tibial components of a total knee replacement implant for optimal interaction within the environment of the tibia. The shape of the implant components are optimized such that the stresses in the bone are favorably controlled to minimize bone degradation, to improve the mechanical integrity of the implant/interface/bone system, and to prevent failures of the implant components. A pilot tailoring system is developed and the feasibility of the concept is demonstrated and evaluated. The methodology and evolution of the existing aerospace technology from which this pilot optimization code was developed is also presented and discussed. Both symmetric and unsymmetric in-plane loading conditions are investigated. The results of the optimization process indicate a trend toward wider and tapered posts as well as thicker backing trays. Unique component geometries were obtained for the different load cases.

Integrating causal reasoning at different levels of abstraction. [in problem-solving system functioning as pilot assistant in commercial air transport emergencies

NASA Technical Reports Server (NTRS)

Hudlicka, Eva; Corker, Kevin

1988-01-01

In this paper, a problem-solving system which uses a multilevel causal model of its domain is described. The system functions in the role of a pilot's assistant in the domain of commercial air transport emergencies. The model represents causal relationships among the aircraft subsystems, the effectors (engines, control surfaces), the forces that act on an aircraft in flight (thrust, lift), and the aircraft's flight profile (speed, altitude, etc.). The causal relationships are represented at three levels of abstraction: Boolean, qualitative, and quantitative, and reasoning about causes and effects can take place at each of these levels. Since processing at each level has different characteristics with respect to speed, the type of data required, and the specificity of the results, the problem-solving system can adapt to a wide variety of situations. The system is currently being implemented in the KEE(TM) development environment on a Symbolics Lisp machine.

Application of an integrated flight/propulsion control design methodology to a STOVL aircraft

NASA Technical Reports Server (NTRS)

Garg, Sanjay; Mattern, Duane L.

1991-01-01

Results are presented from the application of an emerging Integrated Flight/Propulsion Control (IFPC) design methodology to a Short Take Off and Vertical Landing (STOVL) aircraft in transition flight. The steps in the methodology consist of designing command shaping prefilters to provide the overall desired response to pilot command inputs. A previously designed centralized controller is first validated for the integrated airframe/engine plant used. This integrated plant is derived from a different model of the engine subsystem than the one used for the centralized controller design. The centralized controller is then partitioned in a decentralized, hierarchical structure comprising of airframe lateral and longitudinal subcontrollers and an engine subcontroller. Command shaping prefilters from the pilot control effector inputs are then designed and time histories of the closed loop IFPC system response to simulated pilot commands are compared to desired responses based on handling qualities requirements. Finally, the propulsion system safety and nonlinear limited protection logic is wrapped around the engine subcontroller and the response of the closed loop integrated system is evaluated for transients that encounter the propulsion surge margin limit.

Engineman stress and fatigue : pilot tests

DOT National Transportation Integrated Search

1992-06-01

In this pilot study, the effects of fatigue on the train handling performance and vigilance of four certified train service locomotive engineers was assessed while they operated the Federal Railroad Administration (FRA), Research and Locomotive Evalu...

CDI Sensitivity and Crosstrack Error on Nonprecision Approaches

DOT National Transportation Integrated Search

1991-01-01

This study was conducted to determine the influence of course deviation : indicator (CDI) sensitivity on pilot tracking error during nonprecision approaches. : Twelve pilots flew an instrumented single-engine airplane on 144 approaches at six : diffe...

STEM Pilot Project Grant Program: Report to the Legislature, June 2016

ERIC Educational Resources Information Center

Noahr, Lorrell; Black, Scott; Rogers, Justin

2016-01-01

The Washington State Legislature established the Science, Technology, Engineering, & Math (STEM) Pilot Program in the 2015-2017 capital budget (Chapter 3, Laws of 2015, 3rd Sp. Session, Section 5026) and provided $12,500,000 for this pilot grant program. Grants awarded under this program constitute the districts' local funding for purposes of…

14 CFR 63.37 - Aeronautical experience requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... flight training in the duties of a flight engineer. (3) A degree in aeronautical, electrical, or... (CONTINUED) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.37 Aeronautical...— (1) On which a flight engineer is required by this chapter; or (2) That has at least three engines...

14 CFR 63.37 - Aeronautical experience requirements.

Code of Federal Regulations, 2011 CFR

2011-01-01

... flight training in the duties of a flight engineer. (3) A degree in aeronautical, electrical, or... (CONTINUED) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.37 Aeronautical...— (1) On which a flight engineer is required by this chapter; or (2) That has at least three engines...

14 CFR 63.37 - Aeronautical experience requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... flight training in the duties of a flight engineer. (3) A degree in aeronautical, electrical, or... (CONTINUED) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.37 Aeronautical...— (1) On which a flight engineer is required by this chapter; or (2) That has at least three engines...

14 CFR 63.37 - Aeronautical experience requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... flight training in the duties of a flight engineer. (3) A degree in aeronautical, electrical, or... (CONTINUED) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.37 Aeronautical...— (1) On which a flight engineer is required by this chapter; or (2) That has at least three engines...

14 CFR 63.37 - Aeronautical experience requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... flight training in the duties of a flight engineer. (3) A degree in aeronautical, electrical, or... (CONTINUED) AIRMEN CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.37 Aeronautical...— (1) On which a flight engineer is required by this chapter; or (2) That has at least three engines...

Pilot Evaluations of Runway Status Light System

NASA Technical Reports Server (NTRS)

Young, Steven D.; Wills, Robert W.; Smith, R. Marshall

1996-01-01

This study focuses on use of the Transport Systems Research Vehicle (TSRV) Simulator at the Langley Research Center to obtain pilot opinion and input on the Federal Aviation Administration's Runway Status Light System (RWSL) prior to installation in an operational airport environment. The RWSL has been designed to reduce the likelihood of runway incursions by visually alerting pilots when a runway is occupied. Demonstrations of the RWSL in the TSRV Simulator allowed pilots to evaluate the system in a realistic cockpit environment.

Development and applications of various optimization algorithms for diesel engine combustion and emissions optimization

NASA Astrophysics Data System (ADS)

Ogren, Ryan M.

For this work, Hybrid PSO-GA and Artificial Bee Colony Optimization (ABC) algorithms are applied to the optimization of experimental diesel engine performance, to meet Environmental Protection Agency, off-road, diesel engine standards. This work is the first to apply ABC optimization to experimental engine testing. All trials were conducted at partial load on a four-cylinder, turbocharged, John Deere engine using neat-Biodiesel for PSO-GA and regular pump diesel for ABC. Key variables were altered throughout the experiments, including, fuel pressure, intake gas temperature, exhaust gas recirculation flow, fuel injection quantity for two injections, pilot injection timing and main injection timing. Both forms of optimization proved effective for optimizing engine operation. The PSO-GA hybrid was able to find a superior solution to that of ABC within fewer engine runs. Both solutions call for high exhaust gas recirculation to reduce oxide of nitrogen (NOx) emissions while also moving pilot and main fuel injections to near top dead center for improved tradeoffs between NOx and particulate matter.

Adaptation of NASA technology for the optimization of orthopedic knee implants

NASA Technical Reports Server (NTRS)

Saravanos, D. A.; Mraz, P. J.; Hopkins, D. A.

1991-01-01

The NASA technology originally developed for the optimization of composite structures (engine blades) is adapted and applied to the optimization of orthopedic knee implants. A method is developed enabling the tailoring of the implant for optimal interaction with the environment of the tibia. The shape of the implant components are optimized, such that the stresses in the bone are favorably controlled to minimize bone degradation and prevent failures. A pilot tailoring system is developed and the feasibility of the concept is elevated. The optimization system is expected to provide the means for improving knee prosthesis and individual implant tailoring for each patient.

Enhanced Engine Control for Emergency Operation

NASA Technical Reports Server (NTRS)

Litt, Jonathan S.

2012-01-01

C-MAPSS40k engine simulation has been developed and is available to the public. The authenticity of the engine performance and controller enabled the development of realistic enhanced control modes through controller modification alone. Use of enhanced control modes improved stability and control of an impaired aircraft. - Fast Response is useful for manual manipulation of the throttles - Use of Fast Response improved stability as part of a yaw rate feedback system. - Use of Overthrust shortened takeoff distance, but was generally useful in flight, too. Initial lack of pilot familiarity resulted in discomfort, especially with yaw rate feedback, but that was the only drawback, overall the pilot found the enhanced modes very helpful.

Variations in Party Line Information Requirements for Flight Crew Situation Awareness in the Datalink Environment

NASA Technical Reports Server (NTRS)

Pritchett, Amy R.; Hansman, R. John

1994-01-01

Current Air Traffic Control communications use shared very high frequency (VHF) voice frequencies from which pilots can obtain 'Party Line' Information (PLI) by overhearing communications addressed to other aircraft. A prior study has shown pilots perceive this PLI to be important. There is concern that some critical PLI may be lost in the proposed datalink environment where communications will be discretely addressed. Different types of flight operations will be, equipped with datalink equipment at different times, generating a 'mixed environment' where some pilots may rely on PLI while others will receive their information by datalink. To research the importance, availability and accuracy of PLI and to query pilots on the information they feel is necessary, a survey was distributed to pilots. The pilots were selected from four flight operation groups to study the variations in PLI requirements in the mixed datalink environment. Pilots perceived PLI to be important overall. Specific information elements pertaining to traffic and weather information were identified as Critical. Most PLI elements followed a pattern of higher perceived importance during terminal area operations, final approach and landing. Pilots from the different flight operation groups identified some elements as particularly important. Pilots perceived PLI to be only moderately available and accurate overall. Several PLI elements received very low availability and accuracy ratings but are perceived as important. In a free response question designed to find the information requirements for global situation awareness, pilots frequently indicated a need for traffic and weather information. These elements were also frequently cited by them as information that could be presented by a datalink system. The results of this survey identify specific concerns to be addressed when implementing datalink communications.

14 CFR 23.901 - Installation.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... maintenance. (c) Engine cowls and nacelles must be easily removable or openable by the pilot to provide adequate access to and exposure of the engine compartment for preflight checks. (d) Each turbine engine...

14 CFR 23.901 - Installation.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... maintenance. (c) Engine cowls and nacelles must be easily removable or openable by the pilot to provide adequate access to and exposure of the engine compartment for preflight checks. (d) Each turbine engine...

14 CFR 23.901 - Installation.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... maintenance. (c) Engine cowls and nacelles must be easily removable or openable by the pilot to provide adequate access to and exposure of the engine compartment for preflight checks. (d) Each turbine engine...

14 CFR 23.901 - Installation.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... maintenance. (c) Engine cowls and nacelles must be easily removable or openable by the pilot to provide adequate access to and exposure of the engine compartment for preflight checks. (d) Each turbine engine...

14 CFR 23.901 - Installation.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... maintenance. (c) Engine cowls and nacelles must be easily removable or openable by the pilot to provide adequate access to and exposure of the engine compartment for preflight checks. (d) Each turbine engine...

PRACA Enhancement Pilot Study Report: Engineering for Complex Systems Program (formerly Design for Safety), DFS-IC-0006

NASA Technical Reports Server (NTRS)

Korsmeyer, David; Schreiner, John

2002-01-01

This technology evaluation report documents the findings and recommendations of the Engineering for Complex Systems Program (formerly Design for Safety) PRACA Enhancement Pilot Study of the Space Shuttle Program's (SSP's) Problem Reporting and Corrective Action (PRACA) System. A team at NASA Ames Research Center (ARC) performed this Study. This Study was initiated as a follow-on to the NASA chartered Shuttle Independent Assessment Team (SIAT) review (performed in the Fall of 1999) which identified deficiencies in the current PRACA implementation. The Pilot Study was launched with an initial qualitative assessment and technical review performed during January 2000 with the quantitative formal Study (the subject of this report) started in March 2000. The goal of the PRACA Enhancement Pilot Study is to evaluate and quantify the technical aspects of the SSP PRACA systems and recommend enhancements to address deficiencies and in preparation for future system upgrades.

Research pilot Mark Pestana

NASA Image and Video Library

2001-04-16

Mark Pestana is a research pilot and project manager at the NASA Dryden Flight Research Center, Edwards, Calif. He is a pilot for the Beech B200 King Air, the T-34C and the Predator B. He flies the F-18 Hornet as a co-pilot and flight test engineer. Pestana has accumulated more than 4,000 hours of military and civilian flight experience. He was also a flight engineer on the NASA DC-8 flying laboratory. Pestana was the project manager and pilot for the Hi–rate Wireless Airborne Network Demonstration flown on the NASA B200 research aircraft. He flew B200 research missions for the X-38 Space Integrated Inertial Navigation Global Positioning System experiment. Pestana also participated in several deployments of the DC-8, including Earth science expeditions ranging from hurricane research over the Caribbean Sea to ozone studies over the North Pole, atmospheric chemistry over the South Pacific, rain forest health in Central America, Rocky Mountain ice pack assessment, and volcanic and tectonic activity around the Pacific Rim. He came to Dryden as a DC-8 mission manager in June 1998 from NASA Johnson Space Center, Houston, where he served as the Earth and Space Science discipline manager for the International Space Station Program at Johnson. Pestana also served as a flight crew operations engineer in the Astronaut Office, developing the controls, displays, tools, crew accommodations and procedures for on-orbit assembly, test, and checkout of the International Space Station. He led the analysis and technical negotiations for modification of the Russian Soyuz spacecraft as an emergency crew return vehicle for space station crews. He joined the U.S. Air Force Reserve in 1991 and held various positions as a research and development engineer, intelligence analyst, and Delta II launch vehicle systems engineer. He retired from the U.S. Air Force Reserve with the rank of colonel in 2005. Prior to 1990, Pestana was on active duty with the U.S. Air Force as the director of mi

Translating Climate Projections for Bridge Engineering

NASA Astrophysics Data System (ADS)

Anderson, C.; Takle, E. S.; Krajewski, W.; Mantilla, R.; Quintero, F.

2015-12-01

A bridge vulnerability pilot study was conducted by Iowa Department of Transportation (IADOT) as one of nineteen pilots supported by the Federal Highway Administration Climate Change Resilience Pilots. Our pilot study team consisted of the IADOT senior bridge engineer who is the preliminary design section leader as well as climate and hydrological scientists. The pilot project culminated in a visual graphic designed by the bridge engineer (Figure 1), and an evaluation framework for bridge engineering design. The framework has four stages. The first two stages evaluate the spatial and temporal resolution needed in climate projection data in order to be suitable for input to a hydrology model. The framework separates streamflow simulation error into errors from the streamflow model and from the coarseness of input weather data series. In the final two stages, the framework evaluates credibility of climate projection streamflow simulations. Using an empirically downscaled data set, projection streamflow is generated. Error is computed in two time frames: the training period of the empirical downscaling methodology, and an out-of-sample period. If large errors in projection streamflow were observed during the training period, it would indicate low accuracy and, therefore, low credibility. If large errors in streamflow were observed during the out-of-sample period, it would mean the approach may not include some causes of change and, therefore, the climate projections would have limited credibility for setting expectations for changes. We address uncertainty with confidence intervals on quantiles of streamflow discharge. The results show the 95% confidence intervals have significant overlap. Nevertheless, the use of confidence intervals enabled engineering judgement. In our discussions, we noted the consistency in direction of change across basins, though the flood mechanism was different across basins, and the high bound of bridge lifetime period quantiles exceeded that of the historical period. This suggested the change was not isolated, and it systemically altered the risk profile. One suggestion to incorporate engineering judgement was to consider degrees of vulnerability using the median discharge of the historical period and the upper bound discharge for the bridge lifetime period.

Army-NASA aircrew/aircraft integration program (A3I) software detailed design document, phase 3

NASA Technical Reports Server (NTRS)

Banda, Carolyn; Chiu, Alex; Helms, Gretchen; Hsieh, Tehming; Lui, Andrew; Murray, Jerry; Shankar, Renuka

1990-01-01

The capabilities and design approach of the MIDAS (Man-machine Integration Design and Analysis System) computer-aided engineering (CAE) workstation under development by the Army-NASA Aircrew/Aircraft Integration Program is detailed. This workstation uses graphic, symbolic, and numeric prototyping tools and human performance models as part of an integrated design/analysis environment for crewstation human engineering. Developed incrementally, the requirements and design for Phase 3 (Dec. 1987 to Jun. 1989) are described. Software tools/models developed or significantly modified during this phase included: an interactive 3-D graphic cockpit design editor; multiple-perspective graphic views to observe simulation scenarios; symbolic methods to model the mission decomposition, equipment functions, pilot tasking and loading, as well as control the simulation; a 3-D dynamic anthropometric model; an intermachine communications package; and a training assessment component. These components were successfully used during Phase 3 to demonstrate the complex interactions and human engineering findings involved with a proposed cockpit communications design change in a simulated AH-64A Apache helicopter/mission that maps to empirical data from a similar study and AH-1 Cobra flight test.

Environmental education and socioresponsive engineering. Report of an educational initiative in Hyderabad, India.

PubMed

Ansari, Ali Uddin; Jafari, Ashfaque; Mirzana, Ishrat Meera; Imtiaz, Zulfia; Lukacs, Heather

2003-07-01

A recent initiative at Muffakham Jah College of Engineering and Technology, Hyderabad, India, has resulted in setting up a program called Centre for Environment Studies and Socioresponsive Engineering which seeks to involve undergraduate students in studying and solving environmental problems in and around the city of Hyderabad, India. Two pilot projects have been undertaken--one focusing on design and construction of an eco-friendly house, The Natural House, and another directed at improving environmental and general living conditions in a slum area. The paper describes our attempts and experience of motivating our students to take interest in such projects. In an interesting development we invited a member of a student-faculty team at Massachusetts Institute of Technology (M.I.T.) that is doing a project in Nepal on safe drinking water. We report in our paper how the presentation by the guest from M.I.T. served as a catalyst for generating interest among civil and mechanical engineering students in our own projects. The paper includes contributions from one of our students and the M.I.T. staff member, reporting on their experiences related to the slum development project. We also discuss the Natural House project and its international and educational significance as a means of inculcating sensitivity and interest in nature among engineering students. We propose a pledge for engineers similar to the Hippocratic Oath for medical professionals.

A simulation investigation of the effects of engine-and thrust-response characteristics on helicopter handling qualities

NASA Technical Reports Server (NTRS)

Corless, L. D.; Blanken, C. L.

1983-01-01

A multi-phase program is being conducted to study, in a generic sense and through ground simulation, the effects of engine response, rotor inertia, rpm control, excess power, and vertical damping on specific maneuvers included in nap-of-the-Earth (NOE) operations. The helicopter configuration with an rpm-governed gas-turbine engine are considered. Handling-qualities-criteria data are considered in light of aspects peculiar to rotary-wing and NOE operations. The results of three moving-based piloted simulation studies are summarized and the frequency, characteristics of the helicopter thrust response which set it apart from other VTOL types are explained. Power-system response is affected by both the engine-governor response and the level of rotor inertia. However, results indicate that with unlimited power, variations in engine response can have a significant effect on pilot rating, whereas changes in rotor inertia, in general, do not. The results also show that any pilot interaction required to maintain proper control can significantly degrade handling qualities. Data for variations in vertical damping and collective sensitivity are compared with existing handling-qualities specifications, MIL-F-83300 and AGARD 577, and show a need for higher minimums for both damping and sensitivity for the bob-up task. Results for cases of limited power are also shown.

Advanced Aircrew Display Symposium (3rd), 19-20 May.

DTIC Science & Technology

1976-01-01

piozea. This was in 1968. ’hS ese3e -2 -12 CE LS 1s desijn a si’mc;,41ed coiimator (movic diamond . fixed line) ot zo jza cy, .mhch v.as mounted on a...typical of electromechanical sights. The tracer sight displays electronic bullets with stadiametric range marks and a diamond at target range when...hackles on the necks of some engineers and pilots, we have become sensitive to the super-engineer/ super- pilot syndrome . It is very desirable to

Ash deposits - Initiating the change from empiricism to generic engineering. Part 1: The generic approach

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

Wagoner, C.L.; Wessel, R.A.

1986-01-01

Empiricism has traditionally been used to relate laboratory and pilot-scale measurements of fuel characteristics with the design, performance, and the slagging and fouling behavior of steam generators. Currently, a new engineering approach is being evaluated. The goal is to develop and use calculations and measurements from several engineering disciplines that exceed the demonstrated limitations of present empirical techniques for predicting slagging/fouling behavior. In Part I of this paper, the generic approach to deposits and boiler performance is defined and a matrix of engineering concepts is described. General relationships are presented for assessing the effects of deposits and sootblowing on themore » real-time performance of heat transfer surfaces in pilot- and commercial-scale steam generators.« less

MD-11 PCA - Research flight team egress

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 has parked on the flightline at NASA's Dryden Flight Research Center, Edwards, California, following its completion of the first and second landings ever performed by a transport aircraft under engine power only (on Aug. 29, 1995). The milestone flight, with NASA research pilot and former astronaut Gordon Fullerton at the controls, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. Coming down the steps from the aircraft are Gordon Fullerton (in front), followed by Bill Burcham, Propulsion Controlled Aircraft (PCA) project engineer at Dryden; NASA Dryden controls engineer John Burken; John Feather of McDonnell Douglas; and Drew Pappas, McDonnell Douglas' project manager for PCA.

ARTIST CONCEPT - APOLLO XI - LUNAR SURFACE

NASA Image and Video Library

1969-07-11

S69-39011 (July 1969) --- TRW Incorporated's artist concept depicting the Apollo 11 Lunar Module (LM) descending to the surface of the moon. Inside the LM will be astronauts Neil A. Armstrong, commander, and Edwin E. Aldrin Jr., lunar module pilot. Astronaut Michael Collins, command module pilot, will remain with the Command and Service Modules (CSM) in lunar orbit. TRW's LM descent engine will brake Apollo 11's descent to the lunar surface. The throttle-able rocket engine will be fired continuously the last 10 miles of the journey to the moon, slowing the LM to a speed of two miles per hour at touchdown. TRW Incorporated designed and built the unique engine at Redondo Beach, California under subcontract to the Grumman Aircraft Engineering Corporation, Bethpage, New York, the LM prime contractor.

MD-11 PCA - First Landing at Edwards

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 transport aircraft approaches its first landing under engine power only on Aug. 29, 1995, at NASA's Dryden Flight Research Center, Edwards, California. The milestone flight, flown by NASA research pilot and former astronaut Gordon Fullerton, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple--for pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

MD-11 PCA - First Landing at Edwards

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 approaches the first landing ever of a transport aircraft under engine power only on Aug. 29, 1995, at NASA's Dryden Flight Research Center, Edwards, California. The milestone flight, flown by NASA research pilot and former astronaut Gordon Fullerton, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when it normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple--for pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

The role of a creative "joint assignment" project in biomedical engineering bachelor degree education.

PubMed

Jiehui Jiang; Yuting Zhang; Mi Zhou; Xiaosong Zheng; Zhuangzhi Yan

2017-07-01

Biomedical Engineering (BME) bachelor education aims to train qualified engineers who devote themselves to addressing biological and medical problems by integrating the technological, medical and biological knowledge. Design thinking and teamwork with other disciplines are necessary for biomedical engineers. In the current biomedical engineering education system of Shanghai University (SHU), however, such design thinking and teamwork through a practical project is lacking. This paper describes a creative "joint assignment" project in Shanghai University, China, which has provided BME bachelor students a two-year practical experience to work with students from multidisciplinary departments including sociology, mechanics, computer sciences, business and art, etc. To test the feasibility of this project, a twenty-month pilot project has been carried out from May 2015 to December 2016. The results showed that this pilot project obviously enhanced competitive power of BME students in Shanghai University, both in the capabilities of design thinking and teamwork.

Emergency Flight Control of a Twin-Jet Commercial Aircraft using Manual Throttle Manipulation

NASA Technical Reports Server (NTRS)

Cole, Jennifer H.; Cogan, Bruce R.; Fullerton, C. Gordon; Burken, John J.; Venti, Michael W.; Burcham, Frank W.

2007-01-01

The Department of Homeland Security (DHS) created the PCAR (Propulsion-Controlled Aircraft Recovery) project in 2005 to mitigate the ManPADS (man-portable air defense systems) threat to the commercial aircraft fleet with near-term, low-cost proven technology. Such an attack could potentially cause a major FCS (flight control system) malfunction or other critical system failure onboard the aircraft, despite the extreme reliability of current systems. For the situations in which nominal flight controls are lost or degraded, engine thrust may be the only remaining means for emergency flight control [ref 1]. A computer-controlled thrust system, known as propulsion-controlled aircraft (PCA), was developed in the mid 1990s with NASA, McDonnell Douglas and Honeywell. PCA's major accomplishment was a demonstration of an automatic landing capability using only engine thrust [ref 11. Despite these promising results, no production aircraft have been equipped with a PCA system, due primarily to the modifications required for implementation. A minimally invasive option is TOC (throttles-only control), which uses the same control principles as PCA, but requires absolutely no hardware, software or other aircraft modifications. TOC is pure piloting technique, and has historically been utilized several times by flight crews, both military and civilian, in emergency situations stemming from a loss of conventional control. Since the 1990s, engineers at NASA Dryden Flight Research Center (DFRC) have studied TOC, in both simulation and flight, for emergency flight control with test pilots in numerous configurations. In general, it was shown that TOC was effective on certain aircraft for making a survivable landing. DHS sponsored both NASA Dryden Flight Research Center (Edwards, CA) and United Airlines (Denver, Colorado) to conduct a flight and simulation study of the TOC characteristics of a twin-jet commercial transport, and assess the ability of a crew to control an aircraft down to a survivable runway landing using TOC. The PCAR project objective was a set of pilot procedures for operation of a specific aircraft without hydraulics that (a) have been validated in both simulation and flight by relevant personnel, and (b) mesh well with existing commercial operations, maintenance, and training at a minimum cost. As a result of this study, a procedure has been developed to assist a crew in making a survivable landing using TOC. In a simulation environment, line pilots with little or no previous TOC experience performed survivable runway landings after a few practice TOC approaches. In-flight evaluations put line pilots in a simulated emergency situation where TOC was used to recover the aircraft, maneuver to a landing site, and perform an approach down to 200 feet AGL. The results of this research, including pilot observations, procedure comments, recommendations, future work and lessons learned, will he discussed. Flight data and video footage of TOC approaches may also be shown.

[Risk of noise-induced hearing loss caused by radio communication? Audiologic findings in helicopter crews and pilots of propeller airplanes].

PubMed

Matschke, R G

1987-12-01

The affects of noise on the human inner ear have been well known for a long time, and measures to prevent occupational noise-induced hearing loss show a clear reduction in the statistics of morbidity. Nevertheless, there are working environments in which the use of ear protection seems to be inapplicable, because communication by speech is indispensable, for example in the cockpit of aircraft. Noise exposure measurements were performed on pilots of helicopters and propeller-machines of the German Federal Navy during realistic flight situations. The ambient noise levels during regular flight service were maintained at levels between 89 dB and 120 dB. Sound protection by flight-helmets and headphones is not only neutralised while using radio and intercom, but the noise during radio-communication is even louder than the noise of the engines. The use of ear protection to avoid excessive noise exposure is only of limited effectiveness. While pilots with normal hearing show only little impairment of speech intelligibility, those with noise-induced hearing loss show substantial impairment that varies in proportion to their hearing loss. Communication abilities may be drastically reduced which may compromise the reliability of radio-communication. The problem may be possibly solved in future by an electronic compensation system for noise.

Why is it Doing That? - Assumptions about the FMS

NASA Technical Reports Server (NTRS)

Feary, Michael; Immanuel, Barshi; Null, Cynthia H. (Technical Monitor)

1998-01-01

In the glass cockpit, it's not uncommon to hear exclamations such as "why is it doing that?". Sometimes pilots ask "what were they thinking when they set it this way?" or "why doesn't it tell me what it's going to do next?". Pilots may hold a conceptual model of the automation that is the result of fleet lore, which may or may not be consistent with what the engineers had in mind. But what did the engineers have in mind? In this study, we present some of the underlying assumptions surrounding the glass cockpit. Engineers and designers make assumptions about the nature of the flight task; at the other end, instructor and line pilots make assumptions about how the automation works and how it was intended to be used. These underlying assumptions are seldom recognized or acknowledged, This study is an attempt to explicitly arti culate such assumptions to better inform design and training developments. This work is part of a larger project to support training strategies for automation.

PRiME: integrating professional responsibility into the engineering curriculum.

PubMed

Moore, Christy; Hart, Hillary; Randall, D'Arcy; Nichols, Steven P

2006-04-01

Engineering educators have long discussed the need to teach professional responsibility and the social context of engineering without adding to overcrowded curricula. One difficulty we face is the lack of appropriate teaching materials that can fit into existing courses. The PRiME (Professional Responsibility Modules for Engineering) Project (http://www.engr.utexas.edu/ethics/primeModules.cfm) described in this paper was initiated at the University of Texas, Austin to provide web-based modules that could be integrated into any undergraduate engineering class. Using HPL (How People Learn) theory, PRiME developed and piloted four modules during the academic year 2004-2005. This article introduces the modules and the pilot, outlines the assessment process, analyzes the results, and describes how the modules are being revised in light of the initial assessment. In its first year of development and testing, PRiME made significant progress towards meeting its objectives. The PRiME Project can strengthen engineering education by providing faculty with an effective system for engaging students in learning about professional responsibility.

SOUTH ELEVATION OF HOT PILOT PLANT (CPP640) LOOKING NORTH. INL ...

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

SOUTH ELEVATION OF HOT PILOT PLANT (CPP-640) LOOKING NORTH. INL PHOTO NUMBER HD-22-3-1. Mike Crane, Photographer, 11/1998 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

Pilot tracking performance during successive in-flight simulated instrument approaches.

DOT National Transportation Integrated Search

1972-02-01

Eight instrument rated pilots with flying experience ranging from 600 to 12,271 hours each flew 10 simulated ILS instrument approaches in a single engine, general aviation aircraft equipped with a primary flight display arranged in a conventional 'T'...

Variations Among Pilots from Different Flight Operations in Party Line Information Requirements for Situation Awareness

NASA Technical Reports Server (NTRS)

Pritchett, Amy; Hansman, John

1997-01-01

Current air traffic control communications use shared VHF voice frequencies from which pilots can obtain 'party line' information (PLI) by overhearing communications addressed to other aircraft. Previous studies have shown that pilots perceive PLI to be important. There is concern that some critical PLI may be lost in the proposed data link environment, where communications will be discretely addressed. Different types of flight operations will be equipped with data link equipment at different times, generating a mixed environment in which some pilots will rely on PLI, while others will receive their information by data link. To research the importance, availability, and accuracy of PLI and to query pilots on the information they feel is necessary for global situation awareness, a survey was distributed to pilots. The pilots were selected from four flight operation groups to study the variations in PLI requirements in the mixed data link environment. Pilots perceived PLI to be important overall, with specific traffic and weather information elements identified as critical. Most PLI elements followed a pattern of higher perceived importance during terminal area operations, final approach, and landing. Pilots from the different flight operation groups identified some elements as particularly important. In a free-response question designed to identify the information requirements for global situation awareness, pilots frequently indicated a need for traffic and weather information. The results of this survey reveal specific concerns to be addressed when implementing data link communications.

This photo shows a head-on view of NASA's SR-71B on the ramp at the Air Force's Plant 42 in Palmdale, California, shortly before delivery to DFRC

NASA Image and Video Library

1991-07-24

This photo shows a head-on view of NASA's SR-71B, used for pilot proficiency and training, on the ramp at the Air Force's Plant 42 in Palmdale, California, shortly before delivery to the Ames-Dryden Flight Research Facility (later, Dryden Flight Research Center) at Edwards, California. NASA operated two of these unique aircraft, an SR-71A, for high-speed, high altitude research, and this SR- 71B pilot trainer for most of the decade of the 1990s. The "B" model is special because of its raised rear cockpit, which provided a second pilot position so a trainer and an experienced pilot could both see what was going on during flights. The SR-71 was designed and built by the Lockheed Skunk Works, now the Lockheed Martin Skunk Works. Studies have shown that less than 20 percent of the total thrust used to fly at Mach 3 is produced by the basic engine itself. The balance of the total thrust is produced by the unique design of the engine inlet and "moveable spike" system at the front of the engine nacelles, and by the ejector nozzles at the exhaust which burn air compressed in the engine bypass system. Data from the SR-71 high speed research program will be used to aid designers of future supersonic/hypersonic aircraft and propulsion systems, including a high speed civil transport.

The GIIDA (Management of the CNR Environmental Data for Interoperability) project

NASA Astrophysics Data System (ADS)

Nativi, S.

2009-04-01

This work presents the GIIDA (Gestione Integrata e Interoperativa dei Dati Ambientali del CNR) inter-departimental project of the Italian National Research Council (CNR). The project is an initiative of the Earth and Environment Department (Dipartimento Terra e Ambiente) of the CNR. GIIDA mission is "To implement the Spatial Information Infrastructure (SII) of CNR for Environmental and Earth Observation data". The project aims to design and develop a multidisciplinary cyber-infrastructure for the management, processing and evaluation of Earth and environmental data. This infrastructure will contribute to the Italian presence in international projects and initiatives, such as: INSPIRE, GMES, GEOSS and SEIS. The main GIIDA goals are: • Networking: To create a network of CNR Institutes for implementing a common information space and sharing spatial resources. • Observation: Re-engineering the environmental observation system of CNR • Modeling: Re-engineering the environmental modeling system del CNR • Processing: Re-engineering the environmental processing system del CNR • Mediation: To define mediation methods and instruments for implementing the international interoperability standards. The project started in July 2008 releasing a specification document of the GIIDA architecture for interoperability and security. Based on these documents, a Call for Proposals was issued in September 2008. GIIDA received 23 proposed pilots from 16 different Institutes belonging to five CNR Departments and from 15 non-CNR Institutions (e.g. three Italian regional administrations, three national research centers, four universities, some SMEs). These pilot were divided into thematic areas. In fact, GIIDA considers seven main thematic areas/domains: • Biodiversity; • Climate Changes; • Air Quality; • Soil and Water Quality; • Risks; • Infrastructures for Research and Public Administrations; • Sea and Marine resources Each of these thematic areas is covered by a Working Group which coordinates the activities and the achievements of the respective pilots. Working Groups are called to develop for each area: 1) a specific Web Portal; 2) a thematic catalog service; 3) a thematic thesaurus service; 4) a thematic Wiki; 5) standard access and view services for thematic resources -such as: datasets, models, and processing services; 6) a couple of significant use scenarios to be demonstrated.

Representation of Cultural Role-Play for Training

NASA Technical Reports Server (NTRS)

Santarelli, Thomas; Pepe, Aaron; Rosenzweiz, Larry; Paulus, John; Yi, Ahn Na

2010-01-01

The Department of Defense (000) has successfully applied a number of methods for cultural familiarization training ranging from stand-up classroom training, to face-to-face live role-play, to so-called smart-cards. Recent interest has turned to the use of single and mUlti-player gaming technologies to augment these traditional methods of cultural familiarization. One such system, termed CulturePad, has been designed as a game-based role-play environment suitable for use in training and experimentation involving cultural roleplay scenarios. This paper describes the initial CulturePad effort focused on a literature review regarding the use of role-play for cultural training and a feasibility assessment of using a game-mediated environment for role-play. A small-scale pilot involving cultural experts was conducted to collect qualitative behavioral data comparing live role-play to game-mediated role-play in a multiplayer gaming engine.

IARC - Illinois Accelerator Research Center | Pilot Program

Science.gov Websites

Toggle navigation Pilot Program Agenda Directions Registration Illinois Accelerator Research Center National Laboratory present Accelerator Stewardship Test Facility Pilot Program Use accelerator technology , energy and environment. With this pilot program, the DOE Office of Science National Laboratories are

14 CFR 63.39 - Skill requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... simulator, or in an approved flight engineer training device, show that he can satisfactorily perform... CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.39 Skill requirements. (a) An applicant for a flight engineer certificate with a class rating must pass a practical test on the duties of...

14 CFR 63.39 - Skill requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... simulator, or in an approved flight engineer training device, show that he can satisfactorily perform... CERTIFICATION: FLIGHT CREWMEMBERS OTHER THAN PILOTS Flight Engineers § 63.39 Skill requirements. (a) An applicant for a flight engineer certificate with a class rating must pass a practical test on the duties of...

Quiet Clean Short-haul Experimental Engine (QCSEE) under-the-wing engine digital control system design report

NASA Technical Reports Server (NTRS)

1978-01-01

A digital electronic control was combined with conventional hydromechanical components to operate the four controlled variables on the under-the-wing engine: fuel flow, fan blade pitch, fan exhaust area, and core compressor stator angles. The engine and control combination offers improvements in noise, pollution, thrust response, operational monitoring, and pilot workload relative to current engines.

Global positioning system supported pilot's display

NASA Technical Reports Server (NTRS)

Scott, Marshall M., Jr.; Erdogan, Temel; Schwalb, Andrew P.; Curley, Charles H.

1991-01-01

The hardware, software, and operation of the Microwave Scanning Beam Landing System (MSBLS) Flight Inspection System Pilot's Display is discussed. The Pilot's Display is used in conjunction with flight inspection tests that certify the Microwave Scanning Beam Landing System used at Space Shuttle landing facilities throughout the world. The Pilot's Display was developed for the pilot of test aircraft to set up and fly a given test flight path determined by the flight inspection test engineers. This display also aids the aircraft pilot when hazy or cloud cover conditions exist that limit the pilot's visibility of the Shuttle runway during the flight inspection. The aircraft position is calculated using the Global Positioning System and displayed in the cockpit on a graphical display.

ECN-448

NASA Image and Video Library

1964-10-30

This 1964 NASA Flight Reserch Center photograph shows a ground engine test underway on the Lunar Landing Research Vehicle (LLRV) number 1. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the Moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on Earth in a simulated Moon environment, one sixth of the Earth's gravity and with totally transparent aerodynamic forces in a "free flight" vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the Moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the Moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw,

14 CFR 121.915 - Continuing qualification curriculum.

Code of Federal Regulations, 2010 CFR

2010-01-01

... in all tasks, procedures and subjects required in accordance with the approved program documentation, as follows: (i) For pilots in command, seconds in command, and flight engineers, First Look in accordance with the certificate holder's FAA-approved program documentation. (ii) For pilots in command...

ARCHITECTURAL WALL SECTIONS OF HOT PILOT PLANT (CPP640). INL DRAWING ...

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

ARCHITECTURAL WALL SECTIONS OF HOT PILOT PLANT (CPP-640). INL DRAWING NUMBER 200-0640-00-279-111682. ALTERNATE ID NUMBER 8952-CPP-640-A-5. - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

MISCELLANEOUS ARCHITECTURAL DETAILS OF HOT PILOT PLANT (CPP640). INL DRAWING ...

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

MISCELLANEOUS ARCHITECTURAL DETAILS OF HOT PILOT PLANT (CPP-640). INL DRAWING NUMBER 200-640-00-279-111684. ALTERNATE ID NUMBER 8952-CPP-640-A-7. - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

Simulating extreme environments: Ergonomic evaluation of Chinese pilot performance and heat stress tolerance.

PubMed

Li, Jing; Tian, Yinsheng; Ding, Li; Zou, Huijuan; Ren, Zhaosheng; Shi, Liyong; Feathers, David; Wang, Ning

2015-06-05

High-temperatures in the cockpit environment can adversely influence pilot behavior and performance. To investigate the impact of high thermal environments on Chinese pilot performance in a simulated cockpit environment. Ten subjects volunteered to participate in the tests under 40°C and 45°C high-temperature simulations in an environmentally controlled chamber. Measures such as grip strength, perception, dexterity, somatic sense reaction, and analytical reasoning were taken. The results were compared to the Combined Index of Heat Stress (CIHS). CIHS exceeded the heat stress safety limit after 45 min under 40°C, grip strength decreased by 12% and somatic perception became 2.89 times larger than the initial value. In the case of 45°C, CIHS exceeded the safety limit after only 20 min, while the grip strength decreased just by 3.2% and somatic perception increased to 4.36 times larger than the initial value. Reaction and finger dexterity were not statistically different from baseline measurements, but the error rate of analytical reasoning test rose remarkably. Somatic perception was the most sensitive index to high-temperature, followed by grip strength. Results of this paper may help to improve environmental control design of new fighter cockpit and for pilot physiology and cockpit environment ergonomics research for Chinese pilots.

NASA/USRA University Advanced Design Program Fifth Annual Summer Conference

NASA Technical Reports Server (NTRS)

1989-01-01

The NASA/USRA University Advanced Design Program is a unique program that brings together NASA engineers, students, and faculty from United States engineering schools by integrating current and future NASA space/aeronautics engineering design projects into the university curriculum. The Program was conceived in the fall of 1984 as a pilot project to foster engineering design education in the universities and to supplement NASA's in-house efforts in advanced planning for space and aeronautics design. Nine universities and five NASA centers participated in the first year of the pilot project. Close cooperation between the NASA centers and the universities, the careful selection of design topics, and the enthusiasm of the students has resulted in a very successful program than now includes forty universities and eight NASA centers. The study topics cover a broad range of potential space and aeronautics projects.

!Claro, se puede! Critical resilience: A critical race perspective on resilience in the baccalaureate achievement of Latino/a engineering and life science students

NASA Astrophysics Data System (ADS)

Cruz, Gary Anthony

An under representation of Latino/as in the fields of science, technology, engineering and math (STEM) still persists. In Rising Above the Gathering Storm, the National Academies sounded an alarm in response to data indicating a "troubling decline" in the number of U.S. citizens trained to become scientists and engineers at a time when the number of technical jobs is outpacing the rate of the U.S. workforce. The shrinking technical talent pipeline threatens the country's future in technology innovation, energy alternatives, national security, and education. This study purported to contextualize resilience and discern the cultural capital and persistence behaviors of STEM Latino/a students succeeding in two adverse environments---higher education and science and engineering. Through a critical race perspective the student cuentos were thematically analyzed. Student narratives were then triangulated with the narrative of the researcher---a Mexican American, first-generation college student, who pursued a life science bachelor's degree through the two institutions in this study. The theoretical framework was guided by Critical Race Theory, Resiliency, Persistence Theory, and Social Construction of Technology. The study consisted of a pilot survey and narrative inquiry. The survey contained pilot questions on the use and perception of information technologies in STEM education. The narrative inquiry was guided by critical race that enabled both positionality and storytelling through narratives and counter-narratives. Twenty-two Latino/a graduating seniors majoring in the biological sciences or engineering/engineering technology at a Hispanic-Serving Institution (HSI) and a Predominantly-White Institution (PWI) in Texas were recruited. The narratives of these students were collected through one-time, semi-structured interviews during the last semester of their studies. Results from the study indicate that these Latino/a STEM students are conscious of their ethnicity; however, they are not critically conscious of the master narrative of what it means to be a Latino/a in a STEM discipline. These students have bought into the master narrative of colorblind science and engineering. The students understood that to succeed in STEM, they had to survive based on their proficiency with institutional norms, practices and cultures and then maintain a sense of self through a respect for their Latino culture.

Understanding the determinants of problem-solving behavior in a complex environment

NASA Technical Reports Server (NTRS)

Casner, Stephen A.

1994-01-01

It is often argued that problem-solving behavior in a complex environment is determined as much by the features of the environment as by the goals of the problem solver. This article explores a technique to determine the extent to which measured features of a complex environment influence problem-solving behavior observed within that environment. In this study, the technique is used to determine how complex flight deck and air traffic control environment influences the strategies used by airline pilots when controlling the flight path of a modern jetliner. Data collected aboard 16 commercial flights are used to measure selected features of the task environment. A record of the pilots' problem-solving behavior is analyzed to determine to what extent behavior is adapted to the environmental features that were measured. The results suggest that the measured features of the environment account for as much as half of the variability in the pilots' problem-solving behavior and provide estimates on the probable effects of each environmental feature.

Thomas C. McMurtry

NASA Technical Reports Server (NTRS)

1982-01-01

Thomas C. McMurtry in November 1982. 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.

14 CFR 27.1305 - Powerplant instruments.

Code of Federal Regulations, 2013 CFR

2013-01-01

... with § 27.955. (n) A gas temperature indicator for each turbine engine. (o) Means to enable the pilot... temperature indicator, for each— (1) Air cooled engine; (2) Rotorcraft with cooling shutters; and (3... condition with respect to cooling. (c) A fuel pressure indicator, for each pump-fed engine. (d) A fuel...

14 CFR 27.1305 - Powerplant instruments.

Code of Federal Regulations, 2014 CFR

2014-01-01

... with § 27.955. (n) A gas temperature indicator for each turbine engine. (o) Means to enable the pilot... temperature indicator, for each— (1) Air cooled engine; (2) Rotorcraft with cooling shutters; and (3... condition with respect to cooling. (c) A fuel pressure indicator, for each pump-fed engine. (d) A fuel...

14 CFR 27.1305 - Powerplant instruments.

Code of Federal Regulations, 2011 CFR

2011-01-01

... with § 27.955. (n) A gas temperature indicator for each turbine engine. (o) Means to enable the pilot... temperature indicator, for each— (1) Air cooled engine; (2) Rotorcraft with cooling shutters; and (3... condition with respect to cooling. (c) A fuel pressure indicator, for each pump-fed engine. (d) A fuel...

14 CFR 27.1305 - Powerplant instruments.

Code of Federal Regulations, 2012 CFR

2012-01-01

... with § 27.955. (n) A gas temperature indicator for each turbine engine. (o) Means to enable the pilot... temperature indicator, for each— (1) Air cooled engine; (2) Rotorcraft with cooling shutters; and (3... condition with respect to cooling. (c) A fuel pressure indicator, for each pump-fed engine. (d) A fuel...

The Optokinetic Cervical Reflex (OKCR) in Pilots of High-Performance Aircraft.

DTIC Science & Technology

1997-04-01

Coupled System virtual reality - the attempt to create a realistic, three-dimensional environment or synthetic immersive environment in which the user ...factors interface between the pilot and the flight environment. The final section is a case study of head- and helmet-mounted displays (HMD) and the impact...themselves as actually moving (flying) through a virtual environment. However, in the studies of Held, et al. (1975) and Young, et al. (1975) the

Microgravity

NASA Image and Video Library

2001-04-26

The first NASA Dropping In a Microgravity Environment (DIME) student competition pilot project came to a conclusion at the Glenn Research Center in April 2001. The competition involved high-school student teams who developed the concept for a microgravity experiment and prepared an experiment proposal. The two student teams - COSI Academy, sponsored by the Columbus Center of Science and Industry, and another team from Cincinnati, Ohio's Sycamore High School, designed a microgravity experiment, fabricated the experimental apparatus, and visited NASA Glenn to operate their experiment in the 2.2 Second Drop Tower. Here, students are briefed by NASA engineer Daniel Dietrich at the top of the drop tower. This image is from a digital still camera; higher resolution is not available.

Applying Ada to Beech Starship avionics

NASA Technical Reports Server (NTRS)

Funk, David W.

1986-01-01

As Ada solidified in its development, it became evident that it offered advantages for avionics systems because of it support for modern software engineering principles and real time applications. An Ada programming support environment was developed for two major avionics subsystems in the Beech Starship. The two subsystems include electronic flight instrument displays and the flight management computer system. Both of these systems use multiple Intel 80186 microprocessors. The flight management computer provides flight planning, navigation displays, primary flight display of checklists and other pilot advisory information. Together these systems represent nearly 80,000 lines of Ada source code and to date approximately 30 man years of effort. The Beech Starship avionics systems are in flight testing.

A Drawing and Multi-Representational Computer Environment for Beginners' Learning of Programming Using C: Design and Pilot Formative Evaluation

ERIC Educational Resources Information Center

Kordaki, Maria

2010-01-01

This paper presents both the design and the pilot formative evaluation study of a computer-based problem-solving environment (named LECGO: Learning Environment for programming using C using Geometrical Objects) for the learning of computer programming using C by beginners. In its design, constructivist and social learning theories were taken into…

Virtual Golden Foods Corporation: Generic Skills in a Virtual Crisis Environment (A Pilot Study)

ERIC Educational Resources Information Center

Godat, Meredith

2007-01-01

Workplace learning in a crisis-rich environment is often difficult if not impossible to integrate into programs so that students are able to experience and apply crisis management practices and principles. This study presents the results of a pilot project that examined the effective use of a virtual reality (VR) environment as a tool to teach…

Kaleri works with the Pilot experiment during Expedition 8

NASA Image and Video Library

2003-10-31

ISS008-E-05179 (31 October 2003) --- Cosmonaut Alexander Y. Kaleri, Expedition 8 flight engineer, works with the Russian biomedical “Pilot” experiment (MBI-15) in the Zvezda Service Module on the International Space Station (ISS). The experiment, which looks at psychological and physiological changes in crew performance during long-duration spaceflight, requires a worktable, ankle restraint system and two control handles for testing piloting skill. Kaleri represents Rosaviakosmos.

Pilot Scott Horowitz fashions cord loop fasteners for a contingency spacewalk

NASA Image and Video Library

1997-02-16

S82-E-5597 (17 Feb. 1997) --- Astronaut Scott J. Horowitz at pilot's station works with a hand-fashioned loop fastener device to be used in support of the additional STS-82 Extravehicular Activity (EVA) to service Hubble Space Telescope (HST). Note sketches overhead which were sent by ground controllers to guide the pilot's engineering of the task. This view was taken with an Electronic Still Camera (ESC).

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.

Level Recession Of Emissions Release By Motor-And-Tractor Diesel Engines Through The Application Of Water-Fuel Emulsions

NASA Astrophysics Data System (ADS)

Ivanov, A.; Chikishev, E.

2017-01-01

The paper is dedicated to a problem of environmental pollution by emissions of hazardous substances with the exhaust gases of internal combustion engines. It is found that application of water-fuel emulsions yields the best results in diesels where production of a qualitative carburetion is the main problem for the organization of working process. During pilot studies the composition of a water-fuel emulsion with the patent held is developed. The developed composition of a water-fuel emulsion provides its stability within 14-18 months depending on mass content of components in it while stability of emulsions’ analogues makes 8-12 months. The mode of operation of pilot unit is described. Methodology and results of pilot study of operation of diesel engine on a water-fuel emulsion are presented. Cutting time of droplet combustion of a water-fuel emulsion improves combustion efficiency and reduces carbon deposition (varnish) on working surfaces. Partial dismantling of the engine after its operating time during 60 engine hours has shown that there is a removal of a carbon deposition in cylinder-piston group which can be observed visually. It is found that for steady operation of the diesel and ensuring decrease in level of emission of hazardous substances the water-fuel emulsion with water concentration of 18-20% is optimal.

Intro to NREL's Thermochemical Pilot Plant

ScienceCinema

Magrini, Kim

2018-02-13

NREL's Thermochemical Pilot Plant converts biomass into higher hydrocarbon fuels and chemicals.NREL is researching biomass pyrolysis. The lab is examining how to upgrade bio-oils via stabilization. Along with this, NREL is developing the engineering system requirements for producing these fuels and chemicals at larger scales.

Pilot heart rate during in-flight simulated instrument approaches in a general aviation aircraft.

DOT National Transportation Integrated Search

1970-04-01

Eight instrument rated pilots with flying experience ranging from 600 to 12,271 hours each flew 10 simulated ILS instrument approaches in a single engine, general aviation aircraft equipped with a primary flight display arranged in conventional 'T' c...

ARCHITECTURAL FLOOR PLAN OF OPERATING AREA HOT PILOT PLANT (CPP640). ...

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

ARCHITECTURAL FLOOR PLAN OF OPERATING AREA HOT PILOT PLANT (CPP-640). INL DRAWING NUMBER 200-0640-00-279-111678. ALTERNATE ID NUMBER 8952-CPP-640-A-1. - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

ARCHITECTURAL DOOR DETAILS AND SCHEDULE OF HOT PILOT PLANT (CPP640). ...

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

ARCHITECTURAL DOOR DETAILS AND SCHEDULE OF HOT PILOT PLANT (CPP-640). INL DRAWING NUMBER 200-640-00-279-111683. ALTERNATE ID NUMBER 8952-CPP-640-A-6. - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

ARCHITECTURAL SECTIONS A, B, C, D, OF HOT PILOT PLANT ...

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

ARCHITECTURAL SECTIONS A, B, C, D, OF HOT PILOT PLANT (CPP-640). INL DRAWING NUMBER 200-0640-00-279-111681. ALTERNATE ID NUMBER 8952-CPP-640-A-5. - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

41 CFR 300-3.1 - What do the following terms mean?

Code of Federal Regulations, 2014 CFR

2014-07-01

... to the operation of the aircraft (e.g., as pilots, co-pilots, flight engineers, navigators) or duties assisting in operation of the aircraft (e.g., as flight directors, crew chiefs, electronics technicians... official travel, including travel planning, authorization, reservations, ticketing, expense reimbursement...

41 CFR 300-3.1 - What do the following terms mean?

Code of Federal Regulations, 2012 CFR

2012-07-01

... to the operation of the aircraft (e.g., as pilots, co-pilots, flight engineers, navigators) or duties assisting in operation of the aircraft (e.g., as flight directors, crew chiefs, electronics technicians... official travel, including travel planning, authorization, reservations, ticketing, expense reimbursement...

41 CFR 300-3.1 - What do the following terms mean?

Code of Federal Regulations, 2013 CFR

2013-07-01

... to the operation of the aircraft (e.g., as pilots, co-pilots, flight engineers, navigators) or duties assisting in operation of the aircraft (e.g., as flight directors, crew chiefs, electronics technicians... official travel, including travel planning, authorization, reservations, ticketing, expense reimbursement...

75 FR 6164 - New Pilot Certification Requirements for Air Carrier Operations

Federal Register 2010, 2011, 2012, 2013, 2014

2010-02-08

... flightcrew eligibility, training, and qualification requirements should be increased for commercial pilots.... House of Representatives passed bill H.R. 3371, the Airline Safety and Pilot Training and Improvement..., practical training/experience, and experience in a crew environment, are also important. A pilot's skills...

Label free cell tracking in 3D tissue engineering constructs with high resolution imaging

NASA Astrophysics Data System (ADS)

Smith, W. A.; Lam, K.-P.; Dempsey, K. P.; Mazzocchi-Jones, D.; Richardson, J. B.; Yang, Y.

2014-02-01

Within the field of tissue engineering there is an emphasis on studying 3-D live tissue structures. Consequently, to investigate and identify cellular activities and phenotypes in a 3-D environment for all in vitro experiments, including shape, migration/proliferation and axon projection, it is necessary to adopt an optical imaging system that enables monitoring 3-D cellular activities and morphology through the thickness of the construct for an extended culture period without cell labeling. This paper describes a new 3-D tracking algorithm developed for Cell-IQ®, an automated cell imaging platform, which has been equipped with an environmental chamber optimized to enable capturing time-lapse sequences of live cell images over a long-term period without cell labeling. As an integral part of the algorithm, a novel auto-focusing procedure was developed for phase contrast microscopy equipped with 20x and 40x objectives, to provide a more accurate estimation of cell growth/trajectories by allowing 3-D voxels to be computed at high spatiotemporal resolution and cell density. A pilot study was carried out in a phantom system consisting of horizontally aligned nanofiber layers (with precise spacing between them), to mimic features well exemplified in cellular activities of neuronal growth in a 3-D environment. This was followed by detailed investigations concerning axonal projections and dendritic circuitry formation in a 3-D tissue engineering construct. Preliminary work on primary animal neuronal cells in response to chemoattractant and topographic cue within the scaffolds has produced encouraging results.

2000 report on the value pricing pilot program

DOT National Transportation Integrated Search

1997-05-01

This document has been written to provide information on how to apply principles of geotechnical earthquake engineering to planning, design, and retrofit of highway facilities. Geotechnical earthquake engineering topics discussed in this document inc...

Searching for a New Way to Reach Patrons: A Search Engine Optimization Pilot Project at Binghamton University Libraries

ERIC Educational Resources Information Center

Rushton, Erin E.; Kelehan, Martha Daisy; Strong, Marcy A.

2008-01-01

Search engine use is one of the most popular online activities. According to a recent OCLC report, nearly all students start their electronic research using a search engine instead of the library Web site. Instead of viewing search engines as competition, however, librarians at Binghamton University Libraries decided to employ search engine…

Modelling decision-making by pilots

NASA Technical Reports Server (NTRS)

Patrick, Nicholas J. M.

1993-01-01

Our scientific goal is to understand the process of human decision-making. Specifically, a model of human decision-making in piloting modern commercial aircraft which prescribes optimal behavior, and against which we can measure human sub-optimality is sought. This model should help us understand such diverse aspects of piloting as strategic decision-making, and the implicit decisions involved in attention allocation. Our engineering goal is to provide design specifications for (1) better computer-based decision-aids, and (2) better training programs for the human pilot (or human decision-maker, DM).

Comparison of in-flight and ground-based simulator derived flying qualities and pilot performance for approach and landing tasks

NASA Technical Reports Server (NTRS)

Grantham, William D.; Williams, Robert H.

1987-01-01

For the case of an approach-and-landing piloting task emphasizing response to the landing flare, pilot opinion and performance parameters derived from jet transport aircraft six-degree-of-freedom ground-based and in-flight simulators were compared in order to derive data for the flight-controls/flying-qualities engineers. The data thus obtained indicate that ground simulation results tend to be conservative, and that the effect of control sensitivity is more pronounced for ground simulation. The pilot also has a greater tendency to generate pilot-induced oscillation in ground-based simulation than in flight.

WEST ELEVATION OF REMOTE ANALYTICAL FACILITY (CPP627) AND HOT PILOT ...

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

WEST ELEVATION OF REMOTE ANALYTICAL FACILITY (CPP-627) AND HOT PILOT PLANT (CPP-640) LOOKING NORTHEAST. INL PHOTO NUMBER HD-22-2-1. Mike Crane, Photographer, 11/1998 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

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

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP640) OVERALL VIEW ...

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

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP-640) OVERALL VIEW LOOKING SOUTHEAST; CONSTRUCTION 34 PERCENT COMPLETE. INL PHOTO NUMBER NRTS-60-3034. Holmes, Photographer, 6/23/1960 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

NORTH ELEVATION OF HOT PILOT PLANT (CPP640) LOOKING SOUTH AFTER ...

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

NORTH ELEVATION OF HOT PILOT PLANT (CPP-640) LOOKING SOUTH AFTER REMOTE ANALYTICAL FACILITY (CPP-627) WAS REMOVED. PHOTO NUMBER HD-54-33-2. Mike Crane, Photographer, 7/2006 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

ARCHITECTURAL ROOF PLAN AND WESTSOUTHEAST ELEVATIONS OF HOT PILOT PLANT ...

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

ARCHITECTURAL ROOF PLAN AND WEST-SOUTHEAST ELEVATIONS OF HOT PILOT PLANT (CPP-640). INL DRAWING NUMBER 200-0640-00-279-111680. ALTERNATE ID NUMBER 8952-CPP-640-A-3. - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

5. PILOTS KNIGHT, RUSHWORTH, ENGLE, THOMPSON, DANA, AND McKAY STANDING ...

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

5. PILOTS KNIGHT, RUSHWORTH, ENGLE, THOMPSON, DANA, AND McKAY STANDING AT THE NOSE OF X-15 NO. 66671. - Edwards Air Force Base, X-15 Engine Test Complex, Rogers Dry Lake, east of runway between North Base & South Base, Boron, Kern County, CA

Private Pilot Ground School Course. Instructor's Guide.

ERIC Educational Resources Information Center

Schlenker, Richard M.

This manual consists of 10 lesson plans for use by instructors teaching a private pilot ground school course. Addressed in the individual lesson plans are the following topics: aerodynamics and principles of flight, flight instruments and systems, operational publications, regulations, airplane operations, engine operations, radio communications,…

NASA X-57 Simulator Prepares Pilots, Engineers for Flight of Electric X-Plane

NASA Image and Video Library

2016-11-29

NASA Administrator Charlie Bolden, a former pilot and astronaut who flew on four shuttle missions, appeared natural at the controls of the X-57 simulator cockpit, and flew a pair of simulations where he landed on the Edwards Air Force Base runway.

MD-11 PCA - View of aircraft on ramp

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 is taxiing to a position on the flightline at NASA's Dryden Flight Research Center, Edwards, California, following its completion of the first and second landings ever performed by a transport aircraft under engine power only (on Aug. 29, 1995). The milestone flight, with NASA research pilot and former astronaut Gordon Fullerton at the controls, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple. For pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

MD-11 PCA - First Landing at Edwards

NASA Technical Reports Server (NTRS)

1995-01-01

A transport aircraft lands for the first time under engine power only, as this McDonnell Douglas MD-11 touches down at 11:38 a.m., Aug. 29, 1995, at NASA's Dryden Flight Research Center, Edwards, California. The milestone flight, flown by NASA research pilot and former astronaut Gordon Fullerton, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple--for pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

MD-11 PCA - Closeup view of aircraft on ramp

NASA Technical Reports Server (NTRS)

1995-01-01

This McDonnell Douglas MD-11 has taxied to a position on the flightline at NASA's Dryden Flight Research Center, Edwards, California, following its completion of the first and second landings ever performed by a transport aircraft under engine power only (on Aug. 29, 1995). The milestone flight, with NASA research pilot and former astronaut Gordon Fullerton at the controls, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple. For pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

MD-11 PCA - First Landing at Edwards

NASA Technical Reports Server (NTRS)

1995-01-01

A transport aircraft lands for the first time under engine power only, as this McDonnell Douglas MD-11 touches down at 11:38 a.m., Aug. 29, 1995, at NASA's Dryden Flight Research Center, Edwards, California. The milestone flight, flown by NASA research pilot and former astronaut Gordon Fullerton, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple--for pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

Correlating Computed and Flight Instructor Assessments of Straight-In Landing Approaches by Novice Pilots on a Flight Simulator

NASA Technical Reports Server (NTRS)

Heath, Bruce E.; Khan, M. Javed; Rossi, Marcia; Ali, Syed Firasat

2005-01-01

The rising cost of flight training and the low cost of powerful computers have resulted in increasing use of PC-based flight simulators. This has prompted FAA standards regulating such use and allowing aspects of training on simulators meeting these standards to be substituted for flight time. However, the FAA regulations require an authorized flight instructor as part of the training environment. Thus, while costs associated with flight time have been reduced, the cost associated with the need for a flight instructor still remains. The obvious area of research, therefore, has been to develop intelligent simulators. However, the two main challenges of such attempts have been training strategies and assessment. The research reported in this paper was conducted to evaluate various performance metrics of a straight-in landing approach by 33 novice pilots flying a light single engine aircraft simulation. These metrics were compared to assessments of these flights by two flight instructors to establish a correlation between the two techniques in an attempt to determine a composite performance metric for this flight maneuver.

Chlamydomonas as a model for biofuels and bio-products production.

PubMed

Scranton, Melissa A; Ostrand, Joseph T; Fields, Francis J; Mayfield, Stephen P

2015-05-01

Developing renewable energy sources is critical to maintaining the economic growth of the planet while protecting the environment. First generation biofuels focused on food crops like corn and sugarcane for ethanol production, and soybean and palm for biodiesel production. Second generation biofuels based on cellulosic ethanol produced from terrestrial plants, has received extensive funding and recently pilot facilities have been commissioned, but to date output of fuels from these sources has fallen well short of what is needed. Recent research and pilot demonstrations have highlighted the potential of algae as one of the most promising sources of sustainable liquid transportation fuels. Algae have also been established as unique biofactories for industrial, therapeutic, and nutraceutical co-products. Chlamydomonas reinhardtii's long established role in the field of basic research in green algae has paved the way for understanding algal metabolism and developing genetic engineering protocols. These tools are now being utilized in C. reinhardtii and in other algal species for the development of strains to maximize biofuels and bio-products yields from the lab to the field. © 2015 The Authors The Plant Journal © 2015 John Wiley & Sons Ltd.

Chlamydomonas as a model for biofuels and bio-products production

PubMed Central

Scranton, Melissa A.; Ostrand, Joseph T.; Fields, Francis J.; Mayfield, Stephen P.

2017-01-01

SUMMARY Developing renewable energy sources is critical to maintaining the economic growth of the planet while protecting the environment. First generation biofuels focused on food crops like corn and sugarcane for ethanol production, and soybean and palm for biodiesel production. Second generation biofuels based on cellulosic ethanol produced from terrestrial plants, has received extensive funding and recently pilot facilities have been commissioned, but to date output of fuels from these sources has fallen well short of what is needed. Recent research and pilot demonstrations have highlighted the potential of algae as one of the most promising sources of sustainable liquid transportation fuels. Algae have also been established as unique biofactories for industrial, therapeutic, and nutraceutical co-products. Chlamydomonas reinhardtii’s long established role in the field of basic research in green algae has paved the way for understanding algal metabolism and developing genetic engineering protocols. These tools are now being utilized in C. reinhardtii and in other algal species for the development of strains to maximize biofuels and bio-products yields from the lab to the field. PMID:25641390

Comparison of a Visual and Head Tactile Display for Soldier Navigation

DTIC Science & Technology

2013-12-01

environments for nuclear power plant operators, air traffic controllers, and pilots are information intensive. These environments usually involve the indirect...queue, correcting aircraft conflicts, giving instruction, clearance and advice to pilots , and assigning aircrafts to other work queues and airports...these dynamic, complex, and multitask environments (1) collect and integrate a plethora of visual information into decisions that are critical for

Proceedings of the 6th Annual Summer Conference: NASA/USRA University Advanced Design Program

NASA Technical Reports Server (NTRS)

1990-01-01

The NASA/USRA University Advanced Design Program is a unique program that brings together NASA engineers, students, and faculty from United States engineering schools by integrating current and future NASA space/aeronautics engineering design projects into the university curriculum. The Program was conceived in the fall of 1984 as a pilot project to foster engineering design education in the universities and to supplement NASA's in-house efforts in advanced planning for space and aeronautics design. Nine universities and five NASA centers participated in the first year of the pilot project. The study topics cover a broad range of potential space and aeronautics projects that could be undertaken during a 20 to 30 year period beginning with the deployment of the Space Station Freedom scheduled for the mid-1990s. Both manned and unmanned endeavors are embraced, and the systems approach to the design problem is emphasized.

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.

What do we mean by Human-Centered Design of Life-Critical Systems?

PubMed

Boy, Guy A

2012-01-01

Human-centered design is not a new approach to design. Aerospace is a good example of a life-critical systems domain where participatory design was fully integrated, involving experimental test pilots and design engineers as well as many other actors of the aerospace engineering community. This paper provides six topics that are currently part of the requirements of the Ph.D. Program in Human-Centered Design of the Florida Institute of Technology (FIT.) This Human-Centered Design program offers principles, methods and tools that support human-centered sustainable products such as mission or process control environments, cockpits and hospital operating rooms. It supports education and training of design thinkers who are natural leaders, and understand complex relationships among technology, organizations and people. We all need to understand what we want to do with technology, how we should organize ourselves to a better life and finally find out whom we are and have become. Human-centered design is being developed for all these reasons and issues.

Project ITCH: Interactive Digital Simulation in Electrical Engineering Education.

ERIC Educational Resources Information Center

Bailey, F. N.; Kain, R. Y.

A two-stage project is investigating the educational potential of a low-cost time-sharing system used as a simulation tool in Electrical Engineering (EE) education. Phase I involves a pilot study and Phase II a full integration. The system employs interactive computer simulation to teach engineering concepts which are not well handled by…

14 CFR 61.109 - Aeronautical experience.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (k) of this section, a person who applies for a private pilot certificate with an airplane category and single-engine...-country flight training in a single-engine airplane; (2) Except as provided in § 61.110 of this part, 3...

14 CFR 61.129 - Aeronautical experience.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (i) of this...-engine class rating must log at least 250 hours of flight time as a pilot that consists of at least: (1... required on instrument training must be in a single engine airplane; (ii) 10 hours of training in an...

14 CFR 61.129 - Aeronautical experience.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (i) of this...-engine class rating must log at least 250 hours of flight time as a pilot that consists of at least: (1... required on instrument training must be in a single engine airplane; (ii) 10 hours of training in an...

14 CFR 61.129 - Aeronautical experience.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (i) of this...-engine class rating must log at least 250 hours of flight time as a pilot that consists of at least: (1... required on instrument training must be in a single engine airplane; (ii) 10 hours of training in an...

14 CFR 61.129 - Aeronautical experience.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (i) of this...-engine class rating must log at least 250 hours of flight time as a pilot that consists of at least: (1... required on instrument training must be in a single engine airplane; (ii) 10 hours of training in an...

14 CFR 61.109 - Aeronautical experience.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (k) of this section, a person who applies for a private pilot certificate with an airplane category and single-engine...-country flight training in a single-engine airplane; (2) Except as provided in § 61.110 of this part, 3...

14 CFR 61.109 - Aeronautical experience.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (k) of this section, a person who applies for a private pilot certificate with an airplane category and single-engine...-country flight training in a single-engine airplane; (2) Except as provided in § 61.110 of this part, 3...

14 CFR 61.129 - Aeronautical experience.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (i) of this...-engine class rating must log at least 250 hours of flight time as a pilot that consists of at least: (1... required on instrument training must be in a single engine airplane; (ii) 10 hours of training in an...

14 CFR 61.109 - Aeronautical experience.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (k) of this section, a person who applies for a private pilot certificate with an airplane category and single-engine...-country flight training in a single-engine airplane; (2) Except as provided in § 61.110 of this part, 3...

14 CFR 61.109 - Aeronautical experience.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Aeronautical experience. (a) For an airplane single-engine rating. Except as provided in paragraph (k) of this section, a person who applies for a private pilot certificate with an airplane category and single-engine...-country flight training in a single-engine airplane; (2) Except as provided in § 61.110 of this part, 3...

STS-47 Pilot Brown on OV-105's flight deck ten minutes after SSME cutoff

NASA Technical Reports Server (NTRS)

1992-01-01

STS-47 Pilot Curtis L. Brown, Jr, is photographed at Endeavour's, Orbiter Vehicle (OV) 105's, pilot station about ten minutes after space shuttle main engine (SSME) cutoff on launch day. Brown smiles from inside the launch and entry suit (LES) and launch and entry helmet (LEH). In the background are the flight mirror assembly silhouetted against forward window W5, control panels, and a checklist.

Summary of the effects of engine throttle response on airplane formation-flying qualities

NASA Technical Reports Server (NTRS)

Walsh, Kevin R.

1993-01-01

A flight evaluation was conducted to determine the effect of engine throttle response characteristics on precision formation-flying qualities. A variable electronic throttle control system was developed and flight-tested on a TF-104G airplane with a J79-11B engine at the NASA Dryden Flight Research Facility. This airplane was chosen because of its known, very favorable thrust response characteristics. Ten research flights were flown to evaluate the effects of throttle gain, time delay, and fuel control rate limiting on engine handling qualities during a demanding precision wing formation task. Handling quality effects of lag filters and lead compensation time delays were also evaluated. The Cooper and Harper Pilot Rating Scale was used to assign levels of handling quality. Data from pilot ratings and comments indicate that throttle control system time delays and rate limits cause significant degradations in handling qualities. Threshold values for satisfactory (level 1) and adequate (level 2) handling qualities of these key variables are presented. These results may provide engine manufacturers with guidelines to assure satisfactory handling qualities in future engine designs.

Piloted Simulation Study of a Dual Thrust-Cutback Procedure for Reducing High-Speed Civil Transport Takeoff Noise Levels

NASA Technical Reports Server (NTRS)

Riley, Donald R.; Glaab, Louis J.; Brandon, Jay M.; Person, Lee H., Jr.; Glaab, Patricia C.

1999-01-01

A piloted simulation study was performed for the purpose of indicating the noise reduction benefits and piloting performance that could occur for a typical 4-engine high-Speed Civil Transport (HSCT) configuration during takeoff when a dual thrust-cutback procedure was employed with throttle operation under direct computer control. Two thrust cutbacks were employed with the first cutback performed while the vehicle was accelerating on the run-way and the second cutback performed at a distance farther downrange. Added vehicle performance improvements included the incorporation of high-lift increments into the aerodynamic database of the vehicle and the use of limited engine oversizing. Four single-stream turbine bypass engines that had no noise suppression of any kind were used with this configuration. This approach permitted establishing the additional noise suppression level that was needed to meet Federal Air Regulation Part 36 Stage 3 noise levels for subsonic commercial jet aircraft. Noise level results were calculated with the jet mixing and shock noise modules of the Aircraft Noise Prediction Program (ANOPP).

A preliminary look at an optimal multivariable design for propulsion-only flight control of jet-transport aircraft

NASA Technical Reports Server (NTRS)

Azzano, Christopher P.

1992-01-01

Control of a large jet transport aircraft without the use of conventional control surfaces was studied. Engine commands were used to attempt to recreate the forces and moments typically provided by the elevator, ailerons, and rudder. Necessary conditions for aircraft controllability were developed pertaining to aircraft configuration such as the number of engines and engine placement. An optimal linear quadratic regulator controller was developed for the Boeing 707-720, in particular, for regulation of its natural dynamic modes. The design used a method of assigning relative weights to the natural modes, i.e., phugoid and dutch roll, for a more intuitive selection of the cost function. A prototype pilot command interface was then integrated into the loop based on pseudorate command of both pitch and roll. Closed loop dynamics were evaluated first with a batch linear simulation and then with a real time high fidelity piloted simulation. The NASA research pilots assisted in evaluation of closed loop handling qualities for typical cruise and landing tasks. Recommendations for improvement on this preliminary study of optimal propulsion only flight control are provided.

Preliminary Flight Deck Observations During Flight in High Ice Water Content Conditions

NASA Technical Reports Server (NTRS)

Ratvasky, Thomas; Duchanoy, Dominque; Bourdinot, Jean-Francois; Harrah, Steven; Strapp, Walter; Schwarzenboeck, Alfons; Dezitter, Fabien; Grandin, Alice

2015-01-01

In 2006, Mason et al. identified common observations that occurred in engine power-loss events attributed to flight in high concentrations of ice crystals. Observations included light to moderate turbulence, precipitation on the windscreen (often reported as rain), aircraft total temperature anomalies, lack of significant airframe icing, and no flight radar echoes at the location and altitude of the engine event. Since 2006, Mason et al. and others have collected information from pilots who experienced engine power-loss events via interviews and questionnaires to substantiate earlier observations and support event analyses. In 2011, Mason and Grzych reported that vertical acceleration data showed increases in turbulence prior to engine events, although the turbulence was usually light to moderate and not unique to high ice water content (HIWC) clouds. Mason concluded that the observation of rain on the windscreen was due to melting of ice high concentrations of ice crystals on the windscreen, coalescing into drops. Mason also reported that these pilot observations of rain on the windscreen were varied. Many pilots indicated no rain was observed, while others observed moderate rain with unique impact sounds. Mason concluded that the variation in the reports may be due to variation in the ice concentration, particle size, and temperature.

Motion Cueing Algorithm Development: Piloted Performance Testing of the Cueing Algorithms

NASA Technical Reports Server (NTRS)

Houck, Jacob A. (Technical Monitor); Telban, Robert J.; Cardullo, Frank M.; Kelly, Lon C.

2005-01-01

The relative effectiveness in simulating aircraft maneuvers with both current and newly developed motion cueing algorithms was assessed with an eleven-subject piloted performance evaluation conducted on the NASA Langley Visual Motion Simulator (VMS). In addition to the current NASA adaptive algorithm, two new cueing algorithms were evaluated: the optimal algorithm and the nonlinear algorithm. The test maneuvers included a straight-in approach with a rotating wind vector, an offset approach with severe turbulence and an on/off lateral gust that occurs as the aircraft approaches the runway threshold, and a takeoff both with and without engine failure after liftoff. The maneuvers were executed with each cueing algorithm with added visual display delay conditions ranging from zero to 200 msec. Two methods, the quasi-objective NASA Task Load Index (TLX), and power spectral density analysis of pilot control, were used to assess pilot workload. Piloted performance parameters for the approach maneuvers, the vertical velocity upon touchdown and the runway touchdown position, were also analyzed but did not show any noticeable difference among the cueing algorithms. TLX analysis reveals, in most cases, less workload and variation among pilots with the nonlinear algorithm. Control input analysis shows pilot-induced oscillations on a straight-in approach were less prevalent compared to the optimal algorithm. The augmented turbulence cues increased workload on an offset approach that the pilots deemed more realistic compared to the NASA adaptive algorithm. The takeoff with engine failure showed the least roll activity for the nonlinear algorithm, with the least rudder pedal activity for the optimal algorithm.

Methodology to Support Dynamic Function Allocation Policies Between Humans and Flight Deck Automation

NASA Technical Reports Server (NTRS)

Johnson, Eric N.

2012-01-01

Function allocation assigns work functions to all agents in a team, both human and automation. Efforts to guide function allocation systematically have been studied in many fields such as engineering, human factors, team and organization design, management science, cognitive systems engineering. Each field focuses on certain aspects of function allocation, but not all; thus, an independent discussion of each does not address all necessary aspects of function allocation. Four distinctive perspectives have emerged from this comprehensive review of literature on those fields: the technology-centered, human-centered, team-oriented, and work-oriented perspectives. Each perspective focuses on different aspects of function allocation: capabilities and characteristics of agents (automation or human), structure and strategy of a team, and work structure and environment. This report offers eight issues with function allocation that can be used to assess the extent to which each of issues exist on a given function allocation. A modeling framework using formal models and simulation was developed to model work as described by the environment, agents, their inherent dynamics, and relationships among them. Finally, to validate the framework and metrics, a case study modeled four different function allocations between a pilot and flight deck automation during the arrival and approach phases of flight.

14 CFR 91.1053 - Crewmember experience.

Code of Federal Regulations, 2010 CFR

2010-01-01

...) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Fractional Ownership... and ratings: (1) Total flight time for all pilots: (i) Pilot in command—A minimum of 1,500 hours. (ii) Second in command—A minimum of 500 hours. (2) For multi-engine turbine-powered fixed-wing and powered...

Academic Coaching: Outcomes from a Pilot Group of Postsecondary STEM Students with Disabilities

ERIC Educational Resources Information Center

Bellman, Scott; Burgstahler, Sheryl; Hinke, Penny

2015-01-01

Faced with poor retention and graduation rates for students with disabilities, postsecondary institutions have experimented with interventions to help students succeed in college. This practice brief describes a pilot initiative in which 41 students with disabilities pursuing science, technology, engineering, and mathematics (STEM) degrees at…

75 FR 81417 - Airworthiness Directives; Piper Aircraft, Inc. Model PA-28-161 Airplanes

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-28

... authority digital engine control (FADEC) backup battery, replacing the supplement pilot's operating handbook... installation of a FADEC backup battery, replacement of the supplement pilot's operating handbook and FAA... backup battery 7 work-hours x $85 per $780 $1,375 Not hour = $595. applicable. Authority for This...

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP640) LOOKING NORTHEAST ...

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

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP-640) LOOKING NORTHEAST SHOWING OVERALL BLOCK EXTERIOR WALLS; CONSTRUCTION 65 PERCENT COMPLETE. INL PHOTO NUMBER NRTS-60-4976. Holmes, Photographer, 9/26/1960 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP640) LOOKING EAST ...

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

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP-640) LOOKING EAST SHOWING EXCAVATION AND FORMING; CONSTRUCTION 6 PERCENT COMPLETE. INL PHOTO NUMBER NRTS-59-4935. J. Anderson, Photographer, 9/21/1959 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

INTERIOR PHOTO OF HOT PILOT PLANT SECOND FLOOR DEPICTING DETAIL ...

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

INTERIOR PHOTO OF HOT PILOT PLANT SECOND FLOOR DEPICTING DETAIL OF SHIELDED CAVE (CPP-640) LOOKING SOUTHWEST. PHOTO TAKEN FROM NORTH. INL PHOTO NUMBER HD-54-40-2. Mike Crane, Photographer, 7/2006 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

INTERIOR PHOTO OF HOT PILOT PLANT SECOND FLOOR WITH SOUTH ...

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

INTERIOR PHOTO OF HOT PILOT PLANT SECOND FLOOR WITH SOUTH SECTION OF SHIELDED CAVE IN FOREGROUND (CPP-640) LOOKING NORTHWEST. INL PHOTO NUMBER HD-54-40-1. Mike Crane, Photographer, 7/2006 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

Water Treatment Pilot Plant Design Manual: Low Flow Conventional/Direct Filtration Water Treatment Plant for Drinking Water Treatment Studies

EPA Science Inventory

This manual highlights the project constraints and concerns, and includes detailed design calculations and system schematics. The plant is based on engineering design principles and practices, previous pilot plant design experiences, and professional experiences and may serve as ...

Aural glide slope cues : their effect on pilot performance during in-flight simulated ILS instrument approaches.

DOT National Transportation Integrated Search

1971-05-01

Forty instrument rated commercial and ATR pilots with 250 to 12,271 flight hours each flew ten simulated ILS approaches in a single engine, general aviation aircraft. Divided into five groups, each group used a different glide slope cue display in co...

The Internet as a Source of Academic Research Information: Findings of Two Pilot Studies.

ERIC Educational Resources Information Center

Kibirige, Harry M.; DePalo, Lisa

2000-01-01

Discussion of information available on the Internet focuses on two pilot studies that investigated how academic users perceive search engines and subject-oriented databases as sources of topical information. Highlights include information seeking behavior of academic users; undergraduate users; graduate users; faculty; and implications for…

Aviation Pilot Training I. Task Analyses: Semester II. Field Review Copy.

ERIC Educational Resources Information Center

Upchurch, Richard

This guide for aviation pilot training begins with a course description, resource information, and a course outline. Tasks/competencies are categorized into 12 concept/duty areas: understanding safe procedures in the flight environment; understanding safe procedures in the airport environment; understanding Federal Aviation Regulations concerning…

Understanding differences in access to water fountains and sugar-sweetened beverages in children׳s environments: a pilot study in high and low deprivation neighbourhoods.

PubMed

Pearson, Amber L; de Latour, Phillip; Kemp, Gabrielle; Findlay, Nohoana; Halim, Angela; Atkinson, Nicola; Chong, Mark; Cameron, Rose; Brown, Courtney; Kim, Grace; Campbell, Paul; Hills, Toby; Jayawant, Aditya; Chae, Matthew; Bhagavan, Chiranth; French, Claire; Jenkin, Gabrielle; Smith, Moira; Signal, Louise

2014-11-01

Access to water fountains and sugar-sweetened beverages (SSBs) in children׳s environments may impact on child obesity and may vary with neighbourhood deprivation. Our pilot analyses of access to water fountains and SSBs in Wellington, New Zealand revealed that water fountain access was high in school environments and low in recreational environments. There were also differences in water fountain and SSB access points by neighbourhood deprivation. The methods piloted in this study could be translated in a larger study, more capable of detecting significant differences in access and allowing for more sophisticated analyses. Such future studies may provide important evidence for the improvement of children׳s health and well-being. Copyright © 2014 Elsevier Ltd. All rights reserved.

Cessna UC–78 Bobcat at the Aircraft Engine Research Laboratory

NASA Image and Video Library

1943-10-21

The Aircraft Engine Research Laboratory acquired the five-seat Cessna UC–78 in March 1943 to maintain the proficiency of its pilots. The UC–78 was referred to as the “Bamboo Bomber” because of its wooden wings and tail and its fabric-covered steel body. The aircraft was produced in 1939 for civilian use, but the military soon began ordering them as training aircraft. The military also began using the aircraft for personnel transport. Cessna produced over 4600 of the aircraft for the military during World War II. The National Advisory Committee for Aeronautics’ (NACA) pilot Howard Lilly flew the UC–78 extensively during its residency in Cleveland. The aircraft was used for ferrying staff members to nearby locations and helping the pilots keep their flying hours up. The UC–78 was transferred in October 1945.

NACA D-558-2 Test Force w/P2B-1S & F-86

NASA Technical Reports Server (NTRS)

1952-01-01

These people and this equipment supported the flight of the NACA D-558-2 Skyrocket at the High-Speed Flight Station at South Base, Edwards AFB. Note the two Sabre chase planes, the P2B-1S launch aircraft, and the profusion of ground support equipment, including communications, tracking, maintenance, and rescue vehicles. Research pilot A. Scott Crossfield stands in front of the Skyrocket. Three D-558-2 'Skyrockets' were built by Douglas Aircraft, Inc. for NACA and the Navy. The mission of the D-558-2 program was to investigate the flight characteristics of a swept-wing aircraft at high supersonic speeds. Particular attention was given to the problem of 'pitch-up,' a phenomenon often encountered with swept-wing configured aircraft. The D-558-2 was a single-place, 35-degree swept-wing aircraft measuring 42 feet in length. It was 12 feet, 8 inches in height and had a wingspan of 25 feet. Fully fueled it weighed from about 10,572 pounds to 15,787 pounds depending on configuration. The first of the three D-558-IIs had a Westinghouse J34-40 jet engine and took off under its own power. The second was equipped with a turbojet engine replaced in 1950 with a Reaction Motors Inc. LR8-RM-6 rocket engine. This aircraft was modified so it could be air-launched from a P2B-1S (Navy designation for the B-29) carrier aircraft. The third Skyrocket had the jet engine and the rocket engine but was also modified so it could be air-launched. The jet engine was for takeoff and climbing to altitude and the four-chambered rocket engine was for reaching supersonic speeds. The rocket engine was rated at 6,000 pounds of thrust. The D-558-2 was first flown on Feb. 4, 1948, by John Martin, a Douglas test pilot. A NACA pilot, Scott Crossfield, became the first person to fly faster than twice the speed of sound when he piloted the D-558-II to its maximum speed of 1,291 miles per hour on Nov. 20, 1953. Its peak altitude, 83,235 feet, a record in its day, was reached with USMC Lt. Col. Marion Carl behind the controls.

Evaluation of advanced displays for engine monitoring and control

NASA Technical Reports Server (NTRS)

Summers, L. G.

1993-01-01

The relative effectiveness of two advanced display concepts for monitoring engine performance for commercial transport aircraft was studied. The concepts were the Engine Monitoring and Control System (EMACS) display developed by NASA Langley and a display by exception design. Both of these concepts were based on the philosophy of providing information that is directly related to the pilot's task. Both concepts used a normalized thrust display. In addition, EMACS used column deviation indicators; i.e., the difference between the actual parameter value and the value predicted by an engine model, for engine health monitoring; while the Display by Exception displayed the engine parameters if the automated system detected a difference between the actual and the predicted values. The results showed that the advanced display concepts had shorter detection and response times. There were no differences in any of the results between manual and auto throttles. There were no effects upon perceived workload or performance on the primary flight task. The majority of pilots preferred the advanced displays and thought they were operationally acceptable. Certification of these concepts depends on the validation of the engine model. Recommendations are made to improve both the EMACS and the display by exception display formats.

Fuel savings with conventional hot water space heating systems by incorporating a natural gas powered heat pump. Preliminary project: Development of heat pump technology

NASA Astrophysics Data System (ADS)

Vanheyden, L.; Evertz, E.

1980-12-01

Compression type air/water heat pumps were developed for domestic heating systems rated at 20 to 150 kW. The heat pump is driven either by a reciprocating piston or rotary piston engine modified to operate on natural gas. Particular features of natural gas engines as prime movers, such as waste heat recovery and variable speed, are stressed. Two systems suitable for heat pump operation were selected from among five different mass produced car engines and were modified to incorporate reciprocating piston compressor pairs. The refrigerants used are R 12 and R 22. Test rig data transferred to field conditions show that the fuel consumption of conventional boilers can be reduced by 50% and more by the installation of engine driven heat pumps. Pilot heat pumps based on a 1,600 cc reciprocating piston engine were built for heating four two-family houses. Pilot pump operation confirms test rig findings. The service life of rotary piston and reciprocating piston engines was investigated. The tests reveal characteristic curves for reciprocating piston engines and include exhaust composition measurements.

Cockpit integration from a pilot's point of view

NASA Technical Reports Server (NTRS)

Green, D. L.

1982-01-01

Extensive experience in both operational and engineering test flight was used to suggest straightforward changes to helicopter cockpit and control system design that would improve pilot performance in marginal and instrument flight conditions. Needed control system improvements considered include: (1) separation of yaw from cyclic force trim; (2) pedal force proportional to displacement rate; and (3) integration of engine controls in collective stick. Display improvements needed include: (1) natural cuing of yaw rate in attitude indicator; (2) collective position indication and radar altimeter placed within primary scan; and (3) omnidirectional display of full range airspeed data.

Procedure Training Aid for the SH-3D/H Normal Start Checklist.

DTIC Science & Technology

1982-02-01

1 Engine .... START Pupoe: To make a Normal Start of No. 1 engine. :4 14. Action Pilot/Copilot verify lite -off by noting rapid rise in T5 and Nq and...Nf increasinq 15. Note Normal starts are characterized by 7 0-75D0 T5 in I seconds after lite -off 16. If T5 is incrasinn too rapidlyv or appears to...Pumps 206 NORMAL START CHECKLIST ITEM NO. 23. No. I Ergine ... TART 14. Action Pilot/Copilot verify lite -off by noting ra ’pid rise in and Ng and Nf

Tuning the cognitive environment: Sound masking with 'natural' sounds in open-plan offices

NASA Astrophysics Data System (ADS)

DeLoach, Alana

With the gain in popularity of open-plan office design and the engineering efforts to achieve acoustical comfort for building occupants, a majority of workers still report dissatisfaction in their workplace environment. Office acoustics influence organizational effectiveness, efficiency, and satisfaction through meeting appropriate requirements for speech privacy and ambient sound levels. Implementing a sound masking system is one tried-and-true method of achieving privacy goals. Although each sound masking system is tuned for its specific environment, the signal -- random steady state electronic noise, has remained the same for decades. This research work explores how `natural' sounds may be used as an alternative to this standard masking signal employed so ubiquitously in sound masking systems in the contemporary office environment. As an unobtrusive background sound, possessing the appropriate spectral characteristics, this proposed use of `natural' sounds for masking challenges the convention that masking sounds should be as meaningless as possible. Through the pilot study presented in this work, we hypothesize that `natural' sounds as sound maskers will be as effective at masking distracting background noise as the conventional masking sound, will enhance cognitive functioning, and increase participant (worker) satisfaction.

Application of the instructional congruence framework: Developing supplemental materials for English language learners

NASA Astrophysics Data System (ADS)

Drews, Tina Skjerping

2009-12-01

This dissertation is a study of the instructional congruence framework as it was used to develop and pilot a supplemental science unit on energy and the environment for sixth grade students in Arizona. With the growing linguistic and cultural diversity of children in American schools, congruent materials are more important now than ever before. The supplemental materials were designed by the researcher and underwent a six person, three educator and three engineer, panel review. The revised materials were then piloted in two sixth grade classrooms in the Southwest with high numbers of English language learners. Classroom observation, teacher interviews, and the classroom observation protocol were utilized to understand the fidelity to the instructional congruence framework. The fidelity of implementation of materials was subject to the realities of varied educational contexts. Piloting materials in urban contexts with diverse students involved additional challenges. The results of the study explore the challenges in creating instructionally congruent materials for diverse students in urban contexts. Recommendations are provided for curriculum developers that undertake the task of creating instructionally congruent materials and emphasize the need to devise innovative methods of creation, while understanding that there is no perfect solution. The education community as a whole could benefit from incorporating and synthesizing the instructional congruence framework in order to provide maximum opportunities in science for all students.

AOPA Survey Summary of AGATE Concepts Demonstration October 17-19, 1996. Volume 1; Basic Report

NASA Technical Reports Server (NTRS)

1997-01-01

An AGATE Concepts Demonstration was conducted at the Annual Aircraft Owners and Pilots Association (AOPA) Convention in 1996. The demonstration consisted of an interactive simulation of a single-pilot, single-engine aircraft in which the participant took off, flew a brief enroute segment and then flew a Global Positioning System (GPS) approach and landing. The participant was provided an advanced 'pathway-in-the-sky' presentation on both a head-up display and a head-down display to follow throughout the flight. A single lever power control and display concept was also provided for control of the engine throughout the flight. A second head-down, multifunction display in the instrument panel provided a moving map display for navigation purposes and monitoring of the status of the aircraft's systems. An estimated 352 people observed or participated in the demonstration, and 144 surveys were collected. The pilot ratings of the participants ranged from student to Air Transport Rating with an average of 1850 hours total flight time. The performance of the participants was surprisingly good, considering the minimal training in a completely new system concept. The overwhelming response was that technologies that simplify piloting tasks are enthusiastically welcomed by pilots of all experience levels. The increase in situation awareness and reduction in pilot workload were universally accepted and lauded as steps in the right direction.

AOPA Survey Summary of AGATE Concepts Demonstration, October 17-19, 1996. Volume 2; Original Survey Data

NASA Technical Reports Server (NTRS)

1997-01-01

An AGATE Concepts Demonstration was conducted at the Annual Aircraft Owners and Pilots Association (AOPA) Convention in 1996. The demonstration consisted of an interactive simulation of a single-pilot, single-engine aircraft in which the participant took off, flew a brief enroute segment and then flew a Global Positioning System (GPS) approach and landing. The participant was provided an advanced 'pathway-in-the-sky' presentation on both a head-up display and a head-down display to follow throughout the flight. A single lever power control and display concept was also provided for control of the engine throughout the flight A second head-down, multifunction display in the instrument panel provided a moving map display for navigation purposes and monitoring of the status of the aircraft's systems. An estimated 352 people observed or participated in the demonstration, and 144 surveys were collected. The pilot ratings of the participants ranged from student to Air Transport Rating with an average of 1850 hours total flight time. The performance of the participants was surprisingly good, considering the minimal training in a completely new system concept. The overwhelming response was that technologies that simplify piloting tasks are enthusiastically welcomed by pilots of all experience levels. The increase in situation awareness and reduction in pilot workload were universally accepted and lauded as steps in the right direction.

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

Aegerter, P.A.

Phillips Petroleum Company scientists and engineers have been operating petroleum refining and separations pilot plants for five years in the Process Development Center. The 26 pilot plants in this building, with one exception, operate under complete computer-control, allowing maximum utilization of limited operating manpower. This centralization and automation of pilot plants has allowed Phillips to more than double the number of operating pilot plants in the petroleum refining area without an increase in manpower. At the same time, the quantity and quality of data has increased correspondingly. This paper discusses Phillips philosophy of operation and management of these pilot plants.more » In addition, details of day-to-day operations and a brief description of the control system are also presented.« less

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.

18. VIEW LOOKING FORWARD FROM ENGINE ROOM INTO GALLEY. STARBOARD ...

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

18. VIEW LOOKING FORWARD FROM ENGINE ROOM INTO GALLEY. STARBOARD ENGINE, FUEL TANK AND BATTERIES SHOWN IN RIGHT SIDE OF IMAGE. OIL-FIRED GALLEY STOVE AND FORWARD COMPANIONWAY LADDER IS IN VIEW THROUGH DOORWAY BEYOND. (HAER FIELD TEAM MEMBER CHRISTOPHER CYZEWSKI IN GALLEY) - Pilot Schooner "Alabama", Moored in harbor at Vineyard Haven, Vineyard Haven, Dukes County, MA

LLRV liftoff from ramp

NASA Technical Reports Server (NTRS)

1960-01-01

This 24-second video clip shows the LLRV pilot strapping in and flying the vehicle. The LLRV's, humorously referred to as 'flying bedsteads,' were created by a predecessor of the NASA Dryden Flight Research Center and Bell Aerosystems Company, Niagra Falls, New York, to study and analyze piloting techniques needed to fly and land the tiny Apollo Lunar Module in the Moon's airless environment. (Dryden was known simply as the NASA Flight Research Center from 1959 to 1976.) Success of the LLRV's led to the building of three Lunar Landing Training Vehicles (LLTV) used by Apollo astronauts at the Manned Spacecraft Center, Houston, Texas, predecessor of the NASA Johnson Space Center. Apollo 11 astronaut, Neil Armstrong -- first human to step onto the Moon's surface -- said the mission would not have been successful without the type of simulation that resulted from the LLRV's. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the Moon's surface. Three concepts developed: an electronic simulator, a tethered device, and the ambitious Flight Research Center (FRC) contribution, a free-flying vehicle. All three became serious projects, but eventually the FRC's LLRV became the most significant one. Hubert Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman the project manager. After conceptual planning and meetings with engineers from Bell Aerosystems, a company with experience in vertical takeoff and landing (VTOL) aircraft, NASA issued Bell a $50,000 study contract in December 1961. Bell had independently conceived a similar, free-flying simulator, and out of this study came the headquarters' endorsement of the LLRV concept, resulting in a $3.6 million production contract awarded to Bell February 1, 1963, for delivery of the first of two vehicles for flight studies at the FRC within 14 months. Built of aluminum alloy trusses and shaped like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in a gimbal, with 4200 pounds of thrust. The engine got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the Moon. Two hydrogen peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal movement. Sixteen smaller hydrogen peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. As safety backups on the LLRV, six 500-pound rockets could take over the lift function and stabilize the craft for a moment if the main jet engine failed. The pilot had a zero-zero ejection seat that would then lift him away to safety. The two LLRV's were shipped from Bell to the FRC in April 1964, with program emphasis on vehicle No. 1. It was first readied for captured flight on a tilt-table affair. The scene then shifted to the old South Base area of Edwards. On the day of the first flight, October 30, 1964, research pilot Joe Walker flew it three times for a total of just under 60 seconds to a peak altitude of ten feet (three meters). Later flights were shared between Walker, another Center pilot named Don Mallick, the Army's Jack Kleuver, NASA Manned Spacecraft Center, Houston, Texas, pilots Joseph Algranti and H.E. 'Bud' Ream. NASA had accumulated enough data from the LLRV flight program at the FRC by mid-1966 to give Bell a contract to deliver three LLTV's at a cost of $2.5 million each. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in January 1967, within weeks of its first flight. Modifications already made to No. 2 had given the pilot a three-axis side control stick and a more restrictive cockpit view, both features of the real Lunar Module that would later be flown by the astronauts down to the Moon's surface. When the LLRV's arrived at Houston, where research pilots would learn how to become LLTV instructor pilots, No. 2 had been flown just seven times while No. 1, the veteran, had a total of 198 flights. In December 1967, the first of the LLTV's joined the FRC's LLRV's to eventually make up the five-vehicle training and simulator fleet. Three of the five vehicles were later destroyed in crashes at Houston - LLRV No. 1 in May 1968 and two LLTVs, in December 1968 and January 1971. The two accidents in 1968, before the first lunar landing, did not deter Apollo program managers who enthusiastically relied on the vehicles for simulation and training. Donald 'Deke' Slayton, then NASA's astronaut chief, said there was no other way to simulate a Moon landing except by flying the LLTV. LLRV No. 2 was eventually returned to Dryden, where it is on display as a silent artifact of the Center's contribution to the Apollo program.

40 CFR 93.129 - Special exemptions from conformity requirements for pilot program areas.

Code of Federal Regulations, 2012 CFR

2012-07-01

... with the conformity requirements of the pilot area's implementation plan revision for § 51.390 of this chapter and all other requirements in 40 CFR parts 51 and 93 that are not covered by the pilot area's... requirements for pilot program areas. 93.129 Section 93.129 Protection of Environment ENVIRONMENTAL PROTECTION...

40 CFR 93.129 - Special exemptions from conformity requirements for pilot program areas.

Code of Federal Regulations, 2010 CFR

2010-07-01

... with the conformity requirements of the pilot area's implementation plan revision for § 51.390 of this chapter and all other requirements in 40 CFR parts 51 and 93 that are not covered by the pilot area's... requirements for pilot program areas. 93.129 Section 93.129 Protection of Environment ENVIRONMENTAL PROTECTION...

40 CFR 93.129 - Special exemptions from conformity requirements for pilot program areas.

Code of Federal Regulations, 2011 CFR

2011-07-01

... with the conformity requirements of the pilot area's implementation plan revision for § 51.390 of this chapter and all other requirements in 40 CFR parts 51 and 93 that are not covered by the pilot area's... requirements for pilot program areas. 93.129 Section 93.129 Protection of Environment ENVIRONMENTAL PROTECTION...

40 CFR 93.129 - Special exemptions from conformity requirements for pilot program areas.

Code of Federal Regulations, 2014 CFR

2014-07-01

... with the conformity requirements of the pilot area's implementation plan revision for § 51.390 of this chapter and all other requirements in 40 CFR parts 51 and 93 that are not covered by the pilot area's... requirements for pilot program areas. 93.129 Section 93.129 Protection of Environment ENVIRONMENTAL PROTECTION...

40 CFR 93.129 - Special exemptions from conformity requirements for pilot program areas.

Code of Federal Regulations, 2013 CFR

2013-07-01

... with the conformity requirements of the pilot area's implementation plan revision for § 51.390 of this chapter and all other requirements in 40 CFR parts 51 and 93 that are not covered by the pilot area's... requirements for pilot program areas. 93.129 Section 93.129 Protection of Environment ENVIRONMENTAL PROTECTION...

Providing Simulated Online and Mobile Learning Experiences in a Prison Education Setting: Lessons Learned from the PLEIADES Pilot Project

ERIC Educational Resources Information Center

Farley, Helen; Murphy, Angela; Bedford, Tasman

2014-01-01

This article reports on the preliminary findings, design criteria and lessons learned while developing and piloting an alternative to traditional print-based education delivery within a prison environment. PLEIADES (Portable Learning Environments for Incarcerated Distance Education Students), was designed to provide incarcerated students with…

Assessing the Flipped Classroom in Operations Management: A Pilot Study

ERIC Educational Resources Information Center

Prashar, Anupama

2015-01-01

The author delved into the results of a flipped classroom pilot conducted for an operations management course module. It assessed students' perception of a flipped learning environment after making them experience it in real time. The classroom environment was construed using a case research approach and students' perceptions were studied using…

Piloted evaluation of an integrated propulsion and flight control simulator

NASA Technical Reports Server (NTRS)

Bright, Michelle M.; Simon, Donald L.

1992-01-01

A piloted evaluation of the integrated flight and propulsion control simulator for advanced integrated propulsion and airframe control design is described. The evaluation will cover control effector gains and deadbands, control effectiveness and control authority, and heads up display functionality. For this evaluation the flight simulator is configured for transition flight using an advanced Short Take-Off and Vertical Landing fighter aircraft model, a simplified high-bypass turbofan engine model, fighter cockpit displays, and pilot effectors. The piloted tasks used for rating displays and control effector gains are described. Pilot comments and simulation results confirm that the display symbology and control gains are very adequate for the transition flight task. Additionally, it is demonstrated that this small-scale, fixed base flight simulator facility can adequately perform a real time, piloted control evaluation.

WATERS - Integrating Science and Education Through the Development of an Education & Outreach Program that Engages Scientists, Students and Citizens

NASA Astrophysics Data System (ADS)

Eschenbach, E. A.; Conklin, M. H.

2007-12-01

The need to train students in hydrologic science and environmental engineering is well established. Likewise, the public requires a raised awareness of the seriousness of water quality and availability problems. The WATERS Network (WATer and Environmental Research Systems Network ) has the potential to significantly change the way students, researchers, citizens, policy makers and industry members learn about environmental problems and solutions regarding water quality, quantity and distribution. This potential can be met if the efforts of water scientists, computer scientists, and educators are integrated appropriately. Successful pilot projects have found that cyberinfrastructure for education and outreach needs to be developed in parallel with research related cyberinfrastructure. We propose further integration of research, education and outreach activities. Through the use of technology that connects students, faculty, researchers, policy makers and others, WATERS Network can provide learning opportunities and teaching efficiencies that can revolutionize environmental science and engineering education. However, there are a plethora of existing environmental science and engineering educational programs. In this environment, WATERS can make a greater impact through careful selection of activities that build upon its unique strengths, that have high potential for engaging the members, and that meet identified needs: (i) modernizing curricula and pedagogy (ii) integrating science and education, (iii) sustainable professional development, and (iv) training the next generation of interdisciplinary water and social scientists and environmental engineers. National and observatory-based education facilities would establish the physical infrastructure necessary to coordinate education and outreach activities. Each observatory would partner with local educators and citizens to develop activities congruent with the scientific mission of the observatory. An unprecedented opportunity exists for educational research of both formal and informal environmental science and engineering education in order to understand how the Network can be efficiently used to create effective technology-based learning environments for all participants.

14 CFR 91.1069 - Flight crew: Instrument proficiency check requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... aircraft under IFR unless, since the beginning of the 6th month before that service, that pilot has passed... command pilot of an aircraft under IFR unless, since the beginning of the 12th month before that service... engine-out speed, propeller and supercharger operations, and hydraulic, mechanical, and electrical...

14 CFR 91.1069 - Flight crew: Instrument proficiency check requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... aircraft under IFR unless, since the beginning of the 6th month before that service, that pilot has passed... command pilot of an aircraft under IFR unless, since the beginning of the 12th month before that service... engine-out speed, propeller and supercharger operations, and hydraulic, mechanical, and electrical...

14 CFR 91.1069 - Flight crew: Instrument proficiency check requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... aircraft under IFR unless, since the beginning of the 6th month before that service, that pilot has passed... command pilot of an aircraft under IFR unless, since the beginning of the 12th month before that service... engine-out speed, propeller and supercharger operations, and hydraulic, mechanical, and electrical...

AeroVironment's Jim Daley, Rik Meininger, Derek Lisoski and Wyatt Sadler (clockwise from bottom left) closely monitor systems testing of the Pathfinder-Plus.

NASA Image and Video Library

2004-09-17

AeroVironment's test director Jim Daley, backup pilot Rik Meininger, stability and controls engineer Derek Lisoski and pilot Wyatt Sadler (clockwise from bottom left) closely monitor systems testing of the Pathfinder-Plus solar aircraft from the control station.

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP640) LOOKING NORTHEAST ...

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

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP-640) LOOKING NORTHEAST SHOWING DECK FORMING FOR SOUTH SECTION OF OPERATING CORRIDOR; CONSTRUCTION 44 PERCENT COMPLETE. INL PHOTO NUMBER NRTS-60-3624. Holmes, Photographer, 7/25/1960 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP640) LOOKING NORTHWEST, ...

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

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CPP-640) LOOKING NORTHWEST, SHOWING FORMING FOR NORTH WALLS OF CELLS 1, 4 AND 5; CONSTRUCTION 21 PERCENT COMPLETE. INL PHOTO NUMBER NRTS-60-1874. Holmes, Photographer, 4/21/1960 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

Women in Science and Technology: A Global Development Leadership Pilot Scheme

ERIC Educational Resources Information Center

Turnbull, Sarah; Howe-Walsh, Liza; Shute, Janis

2014-01-01

In 2012 The University of Portsmouth piloted their first Global Development Leadership program for women in Science and Technology faculties. This was seen to be particularly important because of the wider under-representation of women in Science, Technology, Engineering and Maths (STEM) and the need to encourage more women into senior positions…

Pilot testing model to uncover industrial symbiosis in Brazilian industrial clusters.

PubMed

Saraceni, Adriana Valélia; Resende, Luis Mauricio; de Andrade Júnior, Pedro Paulo; Pontes, Joseane

2017-04-01

The main objective of this study was to create a pilot model to uncover industrial symbiosis practices in Brazilian industrial clusters. For this purpose, a systematic revision was conducted in journals selected from two categories of the ISI Web of Knowledge: Engineering, Environmental and Engineering, Industrial. After an in-depth revision of literature, results allowed the creation of an analysis structure. A methodology based on fuzzy logic was applied and used to attribute the weights of industrial symbiosis variables. It was thus possible to extract the intensity indicators of the interrelations required to analyse the development level of each correlation between the variables. Determination of variables and their weights initially resulted in a framework for the theory of industrial symbiosis assessments. Research results allowed the creation of a pilot model that could precisely identify the loopholes or development levels in each sphere. Ontology charts for data analysis were also generated. This study contributes to science by presenting the foundations for building an instrument that enables application and compilation of the pilot model, in order to identify opportunity to symbiotic development, which derives from "uncovering" existing symbioses.

Fuel control for gas turbine with continuous pilot flame

DOEpatents

Swick, Robert M.

1983-01-01

An improved fuel control for a gas turbine engine having a continuous pilot flame and a fuel distribution system including a pump drawing fuel from a source and supplying a line to the main fuel nozzle of the engine, the improvement being a control loop between the pump outlet and the pump inlet to bypass fuel, an electronically controlled throttle valve to restrict flow in the control loop when main nozzle demand exists and to permit substantially unrestricted flow without main nozzle demand, a minimum flow valve in the control loop downstream of the throttle valve to maintain a minimum pressure in the loop ahead of the flow valve, a branch tube from the pilot flame nozzle to the control loop between the throttle valve and the minimum flow valve, an orifice in the branch tube, and a feedback tube from the branch tube downstream of the orifice to the minimum flow valve, the minimum flow valve being operative to maintain a substantially constant pressure differential across the orifice to maintain constant fuel flow to the pilot flame nozzle.

Direct Air Capture of CO2 - an Overview of Carbon Engineering's Technology and Pilot Plant Development

NASA Astrophysics Data System (ADS)

Holmes, G.; Corless, A.

2014-12-01

At Carbon Engineering, we are developing and commercializing technology to scrub CO2 directly from atmospheric air at industrial scale. By providing atmospheric CO2 for use in fuel production, we can enable production of transportation fuels with ultra-low carbon intensities, which command price premiums in the growing set of constrained fuels markets such as California's LCFS. We are a Calgary based startup founded in 2009 with 10 employees, and we are considered a global leader in the direct air capture (DAC) field. We will review CE's DAC technology, based on a wet-scrubbing "air contactor" which absorbs CO2 into aqueous solution, and a chemical looping "regeneration" component, which liberates pure CO2 from this aqueous solution while re-making the original absorption chemical. CE's DAC tecnology exports purified atmospheric CO2, combined with the combustion CO2 from plant energy usage, as the end product. We will also discuss CE's 2014-2015 end-to-end Pilot Demonstration Unit. This is a $7M technology demonstration plant that CE is building with the help of key industrial partners and equipment vendors. Vendor design and engineering requirements have been used to specify the pilot air contactor, pellet reactor, calciner, and slaker modules, as well as auxiliary systems. These modules will be run for several months to obtain the engineering and performance data needed for subsequent commercial plant design, as well as to test the residual integration risks associated with CE's process. By the time of the AGU conference, the pilot is expected to be in late stages of fabrication or early stages of site installation.

Workstation-Based Simulation for Rapid Prototyping and Piloted Evaluation of Control System Designs

NASA Technical Reports Server (NTRS)

Mansur, M. Hossein; Colbourne, Jason D.; Chang, Yu-Kuang; Aiken, Edwin W. (Technical Monitor)

1998-01-01

The development and optimization of flight control systems for modem fixed- and rotary-. wing aircraft consume a significant portion of the overall time and cost of aircraft development. Substantial savings can be achieved if the time required to develop and flight test the control system, and the cost, is reduced. To bring about such reductions, software tools such as Matlab/Simulink are being used to readily implement block diagrams and rapidly evaluate the expected responses of the completed system. Moreover, tools such as CONDUIT (CONtrol Designer's Unified InTerface) have been developed that enable the controls engineers to optimize their control laws and ensure that all the relevant quantitative criteria are satisfied, all within a fully interactive, user friendly, unified software environment.

Flight evaluation of two segment approaches for jet transport noise abatement

NASA Technical Reports Server (NTRS)

Rogers, R. A.; Wohl, B.; Gale, C. M.

1973-01-01

A 75 flight-hour operational evaluation was conducted with a representative four-engine fan-jet transport in a representative airport environment. The flight instrument systems were modified to automatically provide pilots with smooth and continuous pitch steering command information during two-segment approaches. Considering adverse weather, minimum ceiling and flight crew experience criteria, a transition initiation altitude of approximately 800 feet AFL would have broadest acceptance for initiating two-segment approach procedures in scheduled service. The profile defined by the system gave an upper glidepath of approximately 6 1/2 degrees. This was 1/2 degree greater than inserted into the area navigation system. The glidepath error is apparently due to an erroneous along-track, distance-to-altitude profile.

Assessment of ECG and respiration recordings from simulated emergency landings of ultra light aircraft.

PubMed

Bruna, Ondřej; Levora, Tomáš; Holub, Jan

2018-05-08

Pilots of ultra light aircraft have limited training resources, but with the use of low cost simulators it might be possible to train and test some parts of their training on the ground. The purpose of this paper is to examine possibility of stress inducement on a low cost flight simulator. Stress is assessed from electrocardiogram and respiration. Engine failure during flight served as a stress inducement stimuli. For one flight, pilots had access to an emergency navigation system. There were recorded some statistically significant changes in parameters regarding breathing frequency. Although no significant change was observed in ECG parameters, there appears to be an effect on respiration parameters. Physiological signals processed with analysis of variance suggest, that the moment of engine failure and approach for landing affected average breathing frequency. Presence of navigation interface does not appear to have a significant effect on pilots.

48 CFR 17.106-1 - General.

Code of Federal Regulations, 2012 CFR

2012-10-01

..., preproduction engineering, initial rework, initial spoilage, pilot runs, allocable portions of the costs of... should obtain in-house engineering cost estimates identifying the detailed recurring and nonrecurring... cancellation. For example, consider that the total nonrecurring costs (see 15.408, Table 15-2, Formats for...

48 CFR 17.106-1 - General.

Code of Federal Regulations, 2013 CFR

2013-10-01

..., preproduction engineering, initial rework, initial spoilage, pilot runs, allocable portions of the costs of... should obtain in-house engineering cost estimates identifying the detailed recurring and nonrecurring... cancellation. For example, consider that the total nonrecurring costs (see 15.408, Table 15-2, Formats for...

48 CFR 17.106-1 - General.

Code of Federal Regulations, 2014 CFR

2014-10-01

..., preproduction engineering, initial rework, initial spoilage, pilot runs, allocable portions of the costs of... should obtain in-house engineering cost estimates identifying the detailed recurring and nonrecurring... cancellation. For example, consider that the total nonrecurring costs (see 15.408, Table 15-2, Formats for...

Propulsion controlled aircraft computer

NASA Technical Reports Server (NTRS)

Cogan, Bruce R. (Inventor)

2010-01-01

A low-cost, easily retrofit Propulsion Controlled Aircraft (PCA) system for use on a wide range of commercial and military aircraft consists of an propulsion controlled aircraft computer that reads in aircraft data including aircraft state, pilot commands and other related data, calculates aircraft throttle position for a given maneuver commanded by the pilot, and then displays both current and calculated throttle position on a cockpit display to show the pilot where to move throttles to achieve the commanded maneuver, or is automatically sent digitally to command the engines directly.

Two treatment methods for stormwater sediments--pilot plant and landfarming--and reuse of the treated sediments in civil engineering.

PubMed

Petavy, F; Ruban, V; Conil, P; Viau, J Y; Auriol, J C

2009-07-01

The aim of this research was to present a pilot plant for the treatment of stormwater sediments and to compare the decontamination rate to that obtained by landfarming. The possibilities for reuse of the treated sediments in civil engineering are also studied. Four sediments from retention/infiltration ponds or from street sweeping were studied. In each case organic matter (OM), total hydrocarbons (TH) and polycyclic aromatic hydrocarbons (PAH) were measured. Geotechnical tests were carried out to evaluate the reuse possibilities of the treated sediments. Treatment by means of the pilot plant was efficient at reducing TH and PAH concentrations: THs were reduced by 53-97% and PAHs were decreased by 60-95%. By comparison, a reduction of 45-75% in TH concentration is obtained with landfarming, whereas there is no significant decrease in PAHs. Furthermore, geotechnical tests showed that the treated fractions from the pilot plant can be reused as road embankments and as a capping layer. These results are most encouraging and show that stormwater sediments can valuably be reused after treatment in a pilot plant. Landfarming is less efficient but this technique could be used as a pretreatment in the case of high TH pollution.

Motion-base simulator study of control of an externally blown flap STOL transport aircraft after failure of an outboard engine during landing approach

NASA Technical Reports Server (NTRS)

Middleton, D. B.; Hurt, G. J., Jr.; Bergeron, H. P.; Patton, J. M., Jr.; Deal, P. L.; Champine, R. A.

1975-01-01

A moving-base simulator investigation of the problems of recovery and landing of a STOL aircraft after failure of an outboard engine during final approach was made. The approaches were made at 75 knots along a 6 deg glide slope. The engine was failed at low altitude and the option to go around was not allowed. The aircraft was simulated with each of three control systems, and it had four high-bypass-ratio fan-jet engines exhausting against large triple-slotted wing flaps to produce additional lift. A virtual-image out-the-window television display of a simulated STOL airport was operating during part of the investigation. Also, a simple heads-up flight director display superimposed on the airport landing scene was used by the pilots to make some of the recoveries following an engine failure. The results of the study indicated that the variation in visual cues and/or motion cues had little effect on the outcome of a recovery, but they did have some effect on the pilot's response and control patterns.

Emergency flight control system using one engine and fuel transfer

NASA Technical Reports Server (NTRS)

Burcham, Jr., Frank W. (Inventor); Burken, John J. (Inventor); Le, Jeanette (Inventor)

2000-01-01

A system for emergency aircraft control uses at least one engine and lateral fuel transfer that allows a pilot to regain control over an aircraft under emergency conditions. Where aircraft propulsion is available only through engines on one side of the aircraft, lateral fuel transfer provides means by which the center of gravity of the aircraft can be moved over to the wing associated with the operating engine, thus inducing a moment that balances the moment from the remaining engine, allowing the pilot to regain control over the aircraft. By implementing the present invention in flight control programming associated with a flight control computer (FCC), control of the aircraft under emergency conditions can be linked to the yoke or autopilot knob of the aircraft. Additionally, the center of gravity of the aircraft can be shifted in order to effect maneuvers and turns by spacing such center of gravity either closer to or farther away from the propelling engine or engines. In an alternative embodiment, aircraft having a third engine associated with the tail section or otherwise are accommodated and implemented by the present invention by appropriately shifting the center of gravity of the aircraft. Alternatively, where a four-engine aircraft has suffered loss of engine control on one side of the plane, the lateral fuel transfer may deliver the center of gravity closer to the two remaining engines. Differential thrust between the two can then control the pitch and roll of the aircraft in conjunction with lateral fuel transfer.

Advanced oil recovery technologies for improved recovery from slope basin clastic reservoirs, Nash Draw Brushy Canyon Pool, Eddy County, NM. Second annual technical progress report, October 1, 1996--September 30, 1997

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

NONE

1998-09-01

The Nash Draw Brushy Canyon Pool in Eddy County, New Mexico is a field demonstration in the US Department of Energy Class III Program. Advanced reservoir characterization techniques are being used at the Nash Draw project to develop reservoir management strategies for optimizing oil recovery from this Delaware reservoir. Analysis, interpretation, and integration of recently acquired geological, geophysical, and engineering data revealed that the initial reservoir description was too simplistic to capture the critical features of this complex formation. As a result of the analysis, a proposed pilot area was reconsidered. Comparison of seismic data and engineering data have shownmore » evidence of discontinuities in the area surrounding the proposed injector. Analysis of the 3-D seismic has shown that wells in the proposed pilot are in an area of poor quality amplitude development. The implication is that since amplitude attenuation is a function of porosity, then this is not the best area to be attempting a pilot pressure maintenance project. Because the original pilot area appears to be compartmentalized, the lateral continuity between the pilot wells could be reduced. The 3-D seismic interpretation indicates other areas may be better suited for the initial pilot area. Therefore, the current focus has shifted more to targeted drilling, and the pilot injection will be considered in a more continuous area of the NDP in the future. Results of reservoir simulation studies indicate that pressure maintenance should be started early when reservoir pressure is still high.« less

Design, analysis, and control of a large transport aircraft utilizing selective engine thrust as a backup system for the primary flight control. Ph.D. Thesis

NASA Technical Reports Server (NTRS)

Gerren, Donna S.

1995-01-01

A study has been conducted to determine the capability to control a very large transport airplane with engine thrust. This study consisted of the design of an 800-passenger airplane with a range of 5000 nautical miles design and evaluation of a flight control system, and design and piloted simulation evaluation of a thrust-only backup flight control system. Location of the four wing-mounted engines was varied to optimize the propulsive control capability, and the time constant of the engine response was studied. The goal was to provide level 1 flying qualities. The engine location and engine time constant did not have a large effect on the control capability. The airplane design did meet level 1 flying qualities based on frequencies, damping ratios, and time constants in the longitudinal and lateral-directional modes. Project pilots consistently rated the flying qualities as either level 1 or level 2 based on Cooper-Harper ratings. However, because of the limited control forces and moments, the airplane design fell short of meeting the time required to achieve a 30 deg bank and the time required to respond a control input.

CASH--an innovative approach to sustainable OSH improvement at workplace.

PubMed

Pingle, S; Shanbhag, S

2006-01-01

Occupational health department of a large private enterprise located in India launched Project CASH--Change Agents for Safety and Health, at manufacturing units of the enterprise to bring about a positive change in work environment and improvement in work practices to reduce occupational health risk. Multidisciplinary teams of change agents were constituted and were given intensive training inputs. Reduction in exposure to noise, dust and heat stress were identified as specific objectives after a baseline survey of the work environment. Occupational safety and health knowledge and training was imparted to all field personnel to improve their work practices and attitudes. The focus of the actions was on engineering control measures and process engineering changes necessary for workplace improvement. Noise levels were reduced by an average of more than 9dBA in most of the top ten high noise locations. Out of two locations identified for dust exposure, one was fully eliminated and dust levels at other location were significantly reduced. Heat stress was reduced in all three identified locations with an average reduction of more than 3 degrees C in WBGT levels. Thus, final evaluation of workplace environments revealed significant reduction in exposure to all identified agents, viz noise, dust and heat fulfilling the project objectives. Educating and empowering the team led to reduction of occupational health risks in the work environment. There was positive attitudinal and behavioural change in safety and occupational health awareness & practices among employees. The monetary savings resulting from improvements far outweighed the investments. Success of this pilot project was followed up with further similar projects and their number has grown in geometric proportion for the last three years indicating the sustainability of the project.

40 CFR Appendix - Tables to Subpart B of Part 88

Code of Federal Regulations, 2012 CFR

2012-07-01

... 40 Protection of Environment 21 2012-07-01 2012-07-01 false Tables to Subpart B of Part 88 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CLEAN-FUEL VEHICLES California Pilot Test Program State opt-in for the California Pilot Test Program. Pt. 88, Subpt. B, Tables Tables to Subpart B of Part 88...

40 CFR Appendix - Tables to Subpart B of Part 88

Code of Federal Regulations, 2013 CFR

2013-07-01

... 40 Protection of Environment 21 2013-07-01 2013-07-01 false Tables to Subpart B of Part 88 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CLEAN-FUEL VEHICLES California Pilot Test Program State opt-in for the California Pilot Test Program. Pt. 88, Subpt. B, Tables Tables to Subpart B of Part 88...

40 CFR Appendix - Tables to Subpart B of Part 88

Code of Federal Regulations, 2010 CFR

2010-07-01

... 40 Protection of Environment 20 2010-07-01 2010-07-01 false Tables to Subpart B of Part 88 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CLEAN-FUEL VEHICLES California Pilot Test Program State opt-in for the California Pilot Test Program. Pt. 88, Subpart B, Tables Tables to Subpart B of Part 88...

40 CFR Appendix - Tables to Subpart B of Part 88

Code of Federal Regulations, 2011 CFR

2011-07-01

... 40 Protection of Environment 20 2011-07-01 2011-07-01 false Tables to Subpart B of Part 88 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CLEAN-FUEL VEHICLES California Pilot Test Program State opt-in for the California Pilot Test Program. Pt. 88, Subpart B, Tables Tables to Subpart B of Part 88...

Virtual Collaborative Environments for System of Systems Engineering and Applications for ISAT

NASA Technical Reports Server (NTRS)

Dryer, David A.

2002-01-01

This paper describes an system of systems or metasystems approach and models developed to help prepare engineering organizations for distributed engineering environments. These changes in engineering enterprises include competition in increasingly global environments; new partnering opportunities caused by advances in information and communication technologies, and virtual collaboration issues associated with dispersed teams. To help address challenges and needs in this environment, a framework is proposed that can be customized and adapted for NASA to assist in improved engineering activities conducted in distributed, enhanced engineering environments. The approach is designed to prepare engineers for such distributed collaborative environments by learning and applying e-engineering methods and tools to a real-world engineering development scenario. The approach consists of two phases: an e-engineering basics phase and e-engineering application phase. The e-engineering basics phase addresses skills required for e-engineering. The e-engineering application phase applies these skills in a distributed collaborative environment to system development projects.

Lithium-doped solar cell pilot line fabrication and test programs

NASA Technical Reports Server (NTRS)

Berman, P. A.; Yasui, R. K.

1974-01-01

An investigation was conducted to determine the technology readiness of lithium-doped silicon solar cells with respect to use in space programs. A pilot line fabrication program was established, in which the pilot line cells were evaluated after being exposed to environments ordinarily imposed on nonlithium-doped silicon solar cells. Results indicate that further process improvements are required, particularly with respect to the P/N junction diffusion and the electrical contacting technique (including solder coating). It is concluded that lithium-doped cells can be fabricated to exhibit (1) high efficiencies, (2) uniform cell-to-cell recovery characteristics after exposure to 1-MeV electrons; and (3) good stability in most environments investigated (the only exception being the thermal shock environment).

A Cognitive Engineering Analysis of the Vertical Navigation (VNAV) Function

NASA Technical Reports Server (NTRS)

Sherry, Lance; Feary, Michael; Polson, Peter; Mumaw, Randall; Palmer, Everett

2001-01-01

A cognitive engineering analysis of the Flight Management System (FMS) Vertical Navigation (VNAV) function has identified overloading of the VNAV button and overloading of the Flight Mode Annunciator (FMA) used by the VNAV function. These two types of overloading, resulting in modal input devices and ambiguous feedback, are well known sources of operator confusion, and explain, in part, the operational issues experienced by airline pilots using VNAV in descent and approach. A proposal to modify the existing VNAV design to eliminate the overloading is discussed. The proposed design improves pilot's situational awareness of the VNAV function, and potentially reduces the cost of software development and improves safety.

Performance and Exhaust Emissions in a Natural-Gas Fueled Dual-Fuel Engine

NASA Astrophysics Data System (ADS)

Shioji, Masahiro; Ishiyama, Takuji; Ikegami, Makoto; Mitani, Shinichi; Shibata, Hiroaki

In order to establish the optimum fueling in a natural gas fueled dual fuel engine, experiments were done for some operational parameters on the engine performances and the exhaust emissions. The results show that the pilot fuel quantity should be increased and its injection timing should be advanced to suppress unburned hydrocarbon emission in the middle and low output range, while the quantity should be reduced and the timing retarded to avoid onset of knock at high loads. Unburned hydrocarbon emission and thermal efficiency are improved by avoiding too lean natural gas mixture by restricting intake charge air. However, the improvement is limited because the ignition of pilot fuel deteriorates with excessive throttling. It is concluded that an adequate combination of throttle control and equivalence ratio ensures low hydrocarbon emission and the thermal efficiency comparable to diesel operation.

The Propulsive-Only Flight Control Problem

NASA Technical Reports Server (NTRS)

Blezad, Daniel J.

1996-01-01

Attitude control of aircraft using only the throttles is investigated. The long time constants of both the engines and of the aircraft dynamics, together with the coupling between longitudinal and lateral aircraft modes make piloted flight with failed control surfaces hazardous, especially when attempting to land. This research documents the results of in-flight operation using simulated failed flight controls and ground simulations of piloted propulsive-only control to touchdown. Augmentation control laws to assist the pilot are described using both optimal control and classical feedback methods. Piloted simulation using augmentation shows that simple and effective augmented control can be achieved in a wide variety of failed configurations.

Descriptive analysis of context evaluation instrument for technical oral presentation skills evaluation: A case study in English technical communication course

NASA Astrophysics Data System (ADS)

Mohamed, Abdullah-Adnan; Asmawi, Adelina; Hamid, Mohd Rashid Ab; Mustafa, Zainol bin

2015-02-01

This paper reports a pilot study of Context Evaluation using a self-developed questionnaire distributed among engineering undergraduates at a university under study. The study aims to validate the self-developed questionnaires used in the Context evaluation, a component in the CIPP Model. The Context evaluation assesses background information for needs, assets, problems and opportunities relevant to beneficiaries of the study in a defined environment. Through the questionnaire, background information for the assessment of needs, assets and problems related to the engineering undergraduates' perceptions on the teaching and learning of technical oral presentation skills was collected and analysed. The questionnaire was developed using 5-points Likert scale to measure the constructs under study. They were distributed to 100 respondents with 79 returned. The respondents consisted of engineering undergraduates studied at various faculties at one technical university in Malaysia. The descriptive analysis of data for each item which makes up the construct for Context evaluation is found to be high. This implied that engineering undergraduates showed high interest in teaching and learning of technical oral presentation skills, thus their needs are met. Also, they agreed that assets and facilities are conducive to their learning. In conclusion, the context evaluation involving needs and assets factors are both considerably important; their needs are met and the assets and facilities do support their technical oral presentation skills learning experience.

Can virtual reality be used to conduct mass prophylaxis clinic training? A pilot program.

PubMed

Yellowlees, Peter; Cook, James N; Marks, Shayna L; Wolfe, Daniel; Mangin, Elanor

2008-03-01

To create and evaluate a pilot bioterrorism defense training environment using virtual reality technology. The present pilot project used Second Life, an internet-based virtual world system, to construct a virtual reality environment to mimic an actual setting that might be used as a Strategic National Stockpile (SNS) distribution site for northern California in the event of a bioterrorist attack. Scripted characters were integrated into the system as mock patients to analyze various clinic workflow scenarios. Users tested the virtual environment over two sessions. Thirteen users who toured the environment were asked to complete an evaluation survey. Respondents reported that the virtual reality system was relevant to their practice and had potential as a method of bioterrorism defense training. Computer simulations of bioterrorism defense training scenarios are feasible with existing personal computer technology. The use of internet-connected virtual environments holds promise for bioterrorism defense training. Recommendations are made for public health agencies regarding the implementation and benefits of using virtual reality for mass prophylaxis clinic training.

Medical Handbook for Pilots.

ERIC Educational Resources Information Center

Federal Aviation Administration (DOT), Washington, DC.

This handbook provides information on an airline pilot's physical and mental status and related medical factors which may affect his/her performance. Contents include information on the physical examination for pilots, the flyer's environment, hypoxia, hyperventilation, gas in the body, the ears, alcohol, drugs and flying, carbon monoxide, vision,…

Investigating gender differences under conditions of fatigue in a simulated high G aerial combat environment.

PubMed

Chelette, T L

1997-06-01

Advances in technology have equipped high-performance combat aircraft with the capability of delivering higher and higher sustained acceleration or G-forces on the pilots flying them. While the physiological effects of increased g-forces on the human body continue to be investigated, studies examining the effects of acceleration on the cognitive abilities of high-performance aircraft pilots remain sparse. Additionally, as higher technology is making its way into the cockpit, so are female pilots. With even fewer studies investigating women's physiological and cognitive tolerances to the stressors in the high-performance cockpit and flight environment, Dr. Chelette's study aimed to investigate these issues. Examining pilot workload, flight task abilities, and the effects of sleeplessness on both male and female pilots, Dr. Chelette's results revealed findings that will make their way into the high-performance cockpit of the future.

Children's food store, restaurant, and home food environments and their relationship with body mass index: a pilot study.

PubMed

Holsten, Joanna E; Compher, Charlene W

2012-01-01

This pilot research assessed the feasibility and utility of a study designed to examine the relationship between children's BMI and food store, restaurant, and home food environments. Home visits were conducted with sixth-grade children (N = 12). BMI z-scores were calculated with weight and height measurements. Nutrition Environment Measures Surveys evaluated children's food environments. The study protocol involved a feasible time duration, minimal missing data for primary variables, and participant satisfaction. Potential design problems included the homogeneous store environments and low restaurant exposure of the sample recruited from one school, and the adequacy of a single cross-sectional measure of the home environment.

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.

The use of a tactile interface to convey position and motion perceptions

NASA Technical Reports Server (NTRS)

Rupert, A. H.; Guedry, F. E.; Reschke, M. F.

1994-01-01

Under normal terrestrial conditions, perception of position and motion is determined by central nervous system integration of concordant and redundant information from multiple sensory channels (somatosensory, vestibular, visual), which collectively yield vertical perceptions. In the acceleration environment experienced by the pilots, the somatosensory and vestibular sensors frequently present false information concerning the direction of gravity. When presented with conflicting sensory information, it is normal for pilots to experience episodes of disorientation. We have developed a tactile interface that obtains vertical roll and pitch information from a gyro-stabilized attitude indicator and maps this information in a one-to-one correspondence onto the torso of the body using a matrix of vibrotactors. This enables the pilot to continuously maintain an awareness of aircraft attitude without reference to visual cues, utilizing a sensory channel that normally operates at the subconscious level. Although initially developed to improve pilot spatial awareness, this device has obvious applications to 1) simulation and training, 2) nonvisual tracking of targets, which can reduce the need for pilots to make head movements in the high-G environment of aerial combat, and 3) orientation in environments with minimal somatosensory cues (e.g., underwater) or gravitational cues (e.g., space).

Research Pilot C. Gordon Fullerton in Cockpit of TU-144LL SST Flying Laboratory

NASA Technical Reports Server (NTRS)

1998-01-01

NASA Research pilot C. Gordon Fullerton sits in cockpit of TU-144LL SST Flying Laboratory. Fullerton was one of two NASA pilots who flew the aircraft as part of a joint high speed research program. NASA teamed with American and Russian aerospace industries for an extended period in a joint international research program featuring the Russian-built Tu-144LL supersonic aircraft. The object of the program was to develop technologies for a proposed future second-generation supersonic airliner to be developed in the 21st Century. The aircraft's initial flight phase began in June 1996 and concluded in February 1998 after 19 research flights. A shorter follow-on program involving seven flights began in September 1998 and concluded in April 1999. All flights were conducted in Russia from Tupolev's facility at the Zhukovsky Air Development Center near Moscow. The centerpiece of the research program was the Tu 144LL, a first-generation Russian supersonic jetliner that was modified by its developer/builder, Tupolev ANTK (aviatsionnyy nauchno-tekhnicheskiy kompleks-roughly, aviation technical complex), into a flying laboratory for supersonic research. Using the Tu-144LL to conduct flight research experiments, researchers compared full-scale supersonic aircraft flight data with results from models in wind tunnels, computer-aided techniques, and other flight tests. The experiments provided unique aerodynamic, structures, acoustics, and operating environment data on supersonic passenger aircraft. Data collected from the research program was being used to develop the technology base for a proposed future American-built supersonic jetliner. Although actual development of such an advanced supersonic transport (SST) is currently on hold, commercial aviation experts estimate that a market for up to 500 such aircraft could develop by the third decade of the 21st Century. The Tu-144LL used in the NASA-sponsored research program was a 'D' model with different engines than were used in production-model aircraft. Fifty experiments were proposed for the program and eight were selected, including six flight and two ground (engine) tests. The flight experiments included studies of the aircraft's exterior surface, internal structure, engine temperatures, boundary-layer airflow, the wing's ground-effect characteristics, interior and exterior noise, handling qualities in various flight profiles, and in-flight structural flexibility. The ground tests studied the effect of air inlet structures on airflow entering the engine and the effect on engine performance when supersonic shock waves rapidly change position in the engine air inlet. A second phase of testing further studied the original six in-flight experiments with additional instrumentation installed to assist in data acquisition and analysis. A new experiment aimed at measuring the in-flight deflections of the wing and fuselage was also conducted. American-supplied transducers and sensors were installed to measure nose boom pressures, angle of attack, and sideslip angles with increased accuracy. Two NASA pilots, Robert Rivers of Langley Research Center, Hampton, Virginia, and Gordon Fullerton from Dryden Flight Research Center, Edwards, California, assessed the aircraft's handling at subsonic and supersonic speeds during three flight tests in September 1998. The program concluded after four more data-collection flights in the spring of 1999. The Tu-144LL model had new Kuznetsov NK-321 turbofan engines rated at more than 55,000 pounds of thrust in full afterburner. The aircraft is 215 feet, 6 inches long and 42 feet, 2 inches high with a wingspan of 94 feet, 6 inches. The aircraft is constructed mostly of light aluminum alloy with titanium and stainless steel on the leading edges, elevons, rudder, and the under-surface of the rear fuselage.

Developing Systems Engineering Skills Through NASA Summer Intern Project

NASA Technical Reports Server (NTRS)

Bhasin, Kul; Barritt, Brian; Golden, Bert; Knoblock, Eric; Matthews, Seth; Warner, Joe

2010-01-01

During the Formulation phases of the NASA Project Life Cycle, communication systems engineers are responsible for designing space communication links and analyzing their performance to ensure that the proposed communication architecture is capable of satisfying high-level mission requirements. Senior engineers with extensive experience in communications systems perform these activities. However, the increasing complexity of space systems coupled with the current shortage of communications systems engineers has led to an urgent need for expedited training of new systems engineers. A pilot program, in which college-bound high school and undergraduate students studying various engineering disciplines are immersed in NASA s systems engineering practices, was conceived out of this need. This rapid summerlong training approach is feasible because of the availability of advanced software and technology tools and the students inherent ability to operate such tools. During this pilot internship program, a team of college-level and recently-hired engineers configured and utilized various software applications in the design and analysis of communication links for a plausible lunar sortie mission. The approach taken was to first design the direct-to-Earth communication links for the lunar mission elements, then to design the links between lunar surface and lunar orbital elements. Based on the data obtained from these software applications, an integrated communication system design was realized and the students gained valuable systems engineering knowledge. This paper describes this approach to rapidly training college-bound high school and undergraduate engineering students from various disciplines in NASA s systems engineering practices and tools. A summary of the potential use of NASA s emerging systems engineering internship program in broader applications is also described.

Implementation of Enhanced Propulsion Control Modes for Emergency Flight Operation

NASA Technical Reports Server (NTRS)

Csank, Jeffrey T.; Chin, Jeffrey C.; May, Ryan D.; Litt, Jonathan S.; Guo, Ten-Huei

2011-01-01

Aircraft engines can be effective actuators to help pilots avert or recover from emergency situations. Emergency control modes are being developed to enhance the engines performance to increase the probability of recovery under these circumstances. This paper discusses a proposed implementation of an architecture that requests emergency propulsion control modes, allowing the engines to deliver additional performance in emergency situations while still ensuring a specified safety level. In order to determine the appropriate level of engine performance enhancement, information regarding the current emergency scenario (including severity) and current engine health must be known. This enables the engine to operate beyond its nominal range while minimizing overall risk to the aircraft. In this architecture, the flight controller is responsible for determining the severity of the event and the level of engine risk that is acceptable, while the engine controller is responsible for delivering the desired performance within the specified risk range. A control mode selector specifies an appropriate situation-specific enhanced mode, which the engine controller then implements. The enhanced control modes described in this paper provide additional engine thrust or response capabilities through the modification of gains, limits, and the control algorithm, but increase the risk of engine failure. The modifications made to the engine controller to enable the use of the enhanced control modes are described, as are the interaction between the various subsystems and importantly, the interaction between the flight controller/pilot and the propulsion control system. Simulation results demonstrate how the system responds to requests for enhanced operation and the corresponding increase in performance.

KSC-2012-5023

NASA Image and Video Library

2012-09-12

CAPE CANAVERAL, Fla. - Henry Taylor, from left to right, chief flight engineer on the Shuttle Carrier Aircraft, or SCA, Gary Ash, flight engineer, and Jeff Moultrie, pilot, look ahead to flying space shuttle Endeavour from NASA's Kennedy Space Center in Florida to Los Angeles for public display. Photo credit: NASA/Kim Shiflett

Postgraduate Training in Student Learning and Teaching.

ERIC Educational Resources Information Center

Alpay, E.; Mendes-Tatsis, M. A.

2000-01-01

Presents an experiential postgraduate training program for student learning and supervision involving laboratory and pilot plant supervisions in the chemical engineering field. The program addresses some of the current concerns about non-technical training and the further development of the broad science and engineering knowledge of postgraduate…

The Royal Aircraft Establishment - 100 Years of Research.

DTIC Science & Technology

1981-10-02

Geoffrey de Havilland joined as Chief Engineer, and Designer and Test Pilot respectively. In 1908-14, the poor quality of aero-engines was a serious...which RAE made major contributiotis. In 1954 the Establishment was responsible for the inquiry into the Comet disasters and established new standards

Model-based metrics of human-automation function allocation in complex work environments

NASA Astrophysics Data System (ADS)

Kim, So Young

Function allocation is the design decision which assigns work functions to all agents in a team, both human and automated. Efforts to guide function allocation systematically has been studied in many fields such as engineering, human factors, team and organization design, management science, and cognitive systems engineering. Each field focuses on certain aspects of function allocation, but not all; thus, an independent discussion of each does not address all necessary issues with function allocation. Four distinctive perspectives emerged from a review of these fields: technology-centered, human-centered, team-oriented, and work-oriented. Each perspective focuses on different aspects of function allocation: capabilities and characteristics of agents (automation or human), team structure and processes, and work structure and the work environment. Together, these perspectives identify the following eight issues with function allocation: 1) Workload, 2) Incoherency in function allocations, 3) Mismatches between responsibility and authority, 4) Interruptive automation, 5) Automation boundary conditions, 6) Function allocation preventing human adaptation to context, 7) Function allocation destabilizing the humans' work environment, and 8) Mission Performance. Addressing these issues systematically requires formal models and simulations that include all necessary aspects of human-automation function allocation: the work environment, the dynamics inherent to the work, agents, and relationships among them. Also, addressing these issues requires not only a (static) model, but also a (dynamic) simulation that captures temporal aspects of work such as the timing of actions and their impact on the agent's work. Therefore, with properly modeled work as described by the work environment, the dynamics inherent to the work, agents, and relationships among them, a modeling framework developed by this thesis, which includes static work models and dynamic simulation, can capture the issues with function allocation. Then, based on the eight issues, eight types of metrics are established. The purpose of these metrics is to assess the extent to which each issue exists with a given function allocation. Specifically, the eight types of metrics assess workload, coherency of a function allocation, mismatches between responsibility and authority, interruptive automation, automation boundary conditions, human adaptation to context, stability of the human's work environment, and mission performance. Finally, to validate the modeling framework and the metrics, a case study was conducted modeling four different function allocations between a pilot and flight deck automation during the arrival and approach phases of flight. A range of pilot cognitive control modes and maximum human taskload limits were also included in the model. The metrics were assessed for these four function allocations and analyzed to validate capability of the metrics to identify important issues in given function allocations. In addition, the design insights provided by the metrics are highlighted. This thesis concludes with a discussion of mechanisms for further validating the modeling framework and function allocation metrics developed here, and highlights where these developments can be applied in research and in the design of function allocations in complex work environments such as aviation operations.

40 CFR Appendix - Tables to Subpart B of Part 88

Code of Federal Regulations, 2014 CFR

2014-07-01

... 40 Protection of Environment 20 2014-07-01 2013-07-01 true Tables to Subpart B of Part 88 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CLEAN-FUEL VEHICLES California Pilot Test Program State opt-in for the California Pilot Test Program. Pt. 88, Subpt. B, Tables Tables to Subpart B of Part 88 Tabl...

LLRV in flight and landing on ramp

NASA Technical Reports Server (NTRS)

1960-01-01

This 26-second video clip shows the LLRV flying and landing. The LLRV's, humorously referred to as 'flying bedsteads,' were created by a predecessor of the NASA Dryden Flight Research Center and Bell Aerosystems Company, Niagra Falls, New York, to study and analyze piloting techniques needed to fly and land the tiny Apollo Lunar Module in the Moon's airless environment. (Dryden was known simply as the NASA Flight Research Center from 1959 to 1976.) Success of the LLRV's led to the building of three Lunar Landing Training Vehicles (LLTV) used by Apollo astronauts at the Manned Spacecraft Center, Houston, Texas, predecessor of the NASA Johnson Space Center. Apollo 11 astronaut, Neil Armstrong -- first human to step onto the Moon's surface -- said the mission would not have been successful without the type of simulation that resulted from the LLRV's. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the Moon's surface. Three concepts developed: an electronic simulator, a tethered device, and the ambitious Flight Research Center (FRC) contribution, a free-flying vehicle. All three became serious projects, but eventually the FRC's LLRV became the most significant one. Hubert Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman the project manager. After conceptual planning and meetings with engineers from Bell Aerosystems, a company with experience in vertical takeoff and landing (VTOL) aircraft, NASA issued Bell a $50,000 study contract in December 1961. Bell had independently conceived a similar, free-flying simulator, and out of this study came the headquarters' endorsement of the LLRV concept, resulting in a $3.6 million production contract awarded to Bell February 1, 1963, for delivery of the first of two vehicles for flight studies at the FRC within 14 months. Built of aluminum alloy trusses and shaped like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in a gimbal, with 4200 pounds of thrust. The engine got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the Moon. Two hydrogen peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal movement. Sixteen smaller hydrogen peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. As safety backups on the LLRV, six 500-pound rockets could take over the lift function and stabilize the craft for a moment if the main jet engine failed. The pilot had a zero-zero ejection seat that would then lift him away to safety. The two LLRV's were shipped from Bell to the FRC in April 1964, with program emphasis on vehicle No. 1. It was first readied for captured flight on a tilt-table affair. The scene then shifted to the old South Base area of Edwards. On the day of the first flight, October 30, 1964, research pilot Joe Walker flew it three times for a total of just under 60 seconds to a peak altitude of ten feet (three meters). Later flights were shared between Walker, another Center pilot named Don Mallick, the Army's Jack Kleuver, NASA Manned Spacecraft Center, Houston, Texas, pilots Joseph Algranti and H.E. 'Bud' Ream. NASA had accumulated enough data from the LLRV flight program at the FRC by mid-1966 to give Bell a contract to deliver three LLTVs at a cost of $2.5 million each. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in January 1967, within weeks of its first flight. Modifications already made to No. 2 had given the pilot a three-axis side control stick and a more restrictive cockpit view, both features of the real Lunar Module that would later be flown by the astronauts down to the Moon's surface. When the LLRV's arrived at Houston, where research pilots would learn how to become LLTV instructor pilots, No. 2 had been flown just seven times while No. 1, the veteran, had a total of 198 flights. In December 1967, the first of the LLTV's joined the FRC's LLRV's to eventually make up the five-vehicle training and simulator fleet. Three of the five vehicles were later destroyed in crashes at Houston - LLRV No. 1 in May 1968 and two LLTV's, in December 1968 and January 1971. The two accidents in 1968, before the first lunar landing, did not deter Apollo program managers who enthusiastically relied on the vehicles for simulation and training. Donald 'Deke' Slayton, then NASA's astronaut chief, said there was no other way to simulate a Moon landing except by flying the LLTV. LLRV No. 2 was eventually returned to Dryden, where it is on display as a silent artifact of the Center's contribution to the Apollo program.

Lunar Landing Research Vehicle (LLRV) in flight

NASA Technical Reports Server (NTRS)

1964-01-01

An inflight view from the left side of the Lunar Landing Research Vehicle, is shown in this 1964 NASA Flight Research Center photograph. The photograph was taken in front of the old NACA hangar located at the South Base, Edwards Air Force Base. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV, in case of jet engine failure, six-500-pounds-of thrust rockets could be used by the pilot to carefully apply lift thrust during the rapid descent to hopefully achieve a controllable landing. The pilot's platform extended forward between two legs while an electronics platform, similarly located, extended rearward. The pilot had a zero-zero ejection seat that would then lift him away to safety. Weight and balance design constraints were among the most challenging to meet for all phases of the program (design, development, operations). The two LLRVs were shipped disassembled from Bell to the FRC in April 1964, with program emphasis placed on vehicle No. 1. The scene then shifted to the old South Base area of Edwards Air Force Base. On the day of the first flight, Oct. 30, 1964, NASA research pilot Joe Walker flew it three times for a total of just under 60 seconds, to a peak altitude of approximately 10 feet. By mid-1966 the NASA Flight Research Center had accumulated enough data from the LLRV flight program to give Bell a contract to deliver three Lunar Landing Training Vehicles (LLTVs) at a cost of $2.5 million each. As 1966 ended, the LLRV #1 had flown 198 flights, and the LLRV #2 was being assembled, instrumented and cockpit modifications made at the South Base. The first flight of the number two LLRV in early January 1967 was quickly followed by five more. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in mid January 1967. When Dryden's LLRVs arrived at Houston they joined the first of the LLTVs to eventually make up the five-vehicle training and simulator fleet. All five vehicles were relied on for simulation and training of moon landings.

Lunar Landing Research Vehicle (LLRV) in flight

NASA Technical Reports Server (NTRS)

1965-01-01

In this 1965 NASA Flight Reserch Center photograph the Lunar Landing Research Vehicle (LLRV) is shown at near maximum altitude over the south base at Edwards Air Force Base. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV, in case of jet engine failure, six-500-pounds-of thrust rockets could be used by the pilot to carefully apply lift thrust during the rapid descent to hopefully achieve a controllable landing. The pilot's platform extended forward between two legs while an electronics platform, similarly located, extended rearward. The pilot had a zero-zero ejection seat that would then lift him away to safety. Weight and balance design constraints were among the most challenging to meet for all phases of the program (design, development, operations). The two LLRVs were shipped disassembled from Bell to the FRC in April 1964, with program emphasis placed on vehicle No. 1. The scene then shifted to the old South Base area of Edwards Air Force Base. On the day of the first flight, Oct. 30, 1964, NASA research pilot Joe Walker flew it three times for a total of just under 60 seconds, to a peak altitude of approximately 10 feet. By mid-1966 the NASA Flight Research Center had accumulated enough data from the LLRV flight program to give Bell a contract to deliver three Lunar Landing Training Vehicles (LLTVs) at a cost of $2.5 million each. As 1966 ended, the LLRV #1 had flown 198 flights, and the LLRV #2 was being assembled, instrumented and cockpit modifications made at the South Base. The first flight of the number two LLRV in early January 1967 was quickly followed by five more. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in mid January 1967. When Dryden's LLRVs arrived at Houston they joined the first of the LLTVs to eventually make up the five-vehicle training and simulator fleet. All five vehicles were relied on for simulation and training of moon landings.

Lunar Landing Research Vehicle (LLRV) in flight lifting off from ramp

NASA Technical Reports Server (NTRS)

1964-01-01

This 1964 NASA Flight Reserch Center photograph shows the Lunar Landing Research Vehicle (LLRV) number 1 in flight at the south base of Edwards Air Force Base. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV, in case of jet engine failure, six-500-pounds-of thrust rockets could be used by the pilot to carefully apply lift thrust during the rapid descent to hopefully achieve a controllable landing. The pilot's platform extended forward between two legs while an electronics platform, similarly located, extended rearward. The pilot had a zero-zero ejection seat that would then lift him away to safety. Weight and balance design constraints were among the most challenging to meet for all phases of the program (design, development, operations). The two LLRVs were shipped disassembled from Bell to the FRC in April 1964, with program emphasis placed on vehicle No. 1. The scene then shifted to the old South Base area of Edwards Air Force Base. On the day of the first flight, Oct. 30, 1964, NASA research pilot Joe Walker flew it three times for a total of just under 60 seconds, to a peak altitude of approximately 10 feet. By mid-1966 the NASA Flight Research Center had accumulated enough data from the LLRV flight program to give Bell a contract to deliver three Lunar Landing Training Vehicles (LLTVs) at a cost of $2.5 million each. As 1966 ended, the LLRV #1 had flown 198 flights, and the LLRV #2 was being assembled, instrumented and cockpit modifications made at the South Base. The first flight of the number two LLRV in early January 1967 was quickly followed by five more. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in mid January 1967. When Dryden's LLRVs arrived at Houston they joined the first of the LLTVs to eventually make up the five-vehicle training and simulator fleet. All five vehicles were relied on for simulation and training of moon landings.

Lunar Landing Research Vehicle (LLRV) sitting on ramp

NASA Technical Reports Server (NTRS)

1966-01-01

In this 1966 NASA Flight Reserch Center photograph, the Lunar Landing Research Vehicle (LLRV) number 2 sitting on the ramp. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV, in case of jet engine failure, six-500-pounds-of thrust rockets could be used by the pilot to carefully apply lift thrust during the rapid descent to hopefully achieve a controllable landing. The pilot's platform extended forward between two legs while an electronics platform, similarly located, extended rearward. The pilot had a zero-zero ejection seat that would then lift him away to safety. Weight and balance design constraints were among the most challenging to meet for all phases of the program (design, development, operations). The two LLRVs were shipped disassembled from Bell to the FRC in April 1964, with program emphasis placed on vehicle No. 1. The scene then shifted to the old South Base area of Edwards Air Force Base. On the day of the first flight, Oct. 30, 1964, NASA research pilot Joe Walker flew it three times for a total of just under 60 seconds, to a peak altitude of approximately 10 feet. By mid-1966 the NASA Flight Research Center had accumulated enough data from the LLRV flight program to give Bell a contract to deliver three Lunar Landing Training Vehicles (LLTVs) at a cost of $2.5 million each. As 1966 ended, the LLRV #1 had flown 198 flights, and the LLRV #2 was being assembled, instrumented and cockpit modifications made at the South Base. The first flight of the number two LLRV in early January 1967 was quickly followed by five more. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in mid January 1967. When Dryden's LLRVs arrived at Houston they joined the first of the LLTVs to eventually make up the five-vehicle training and simulator fleet. All five vehicles were relied on for simulation and training of moon landings.

Lunar Landing Research Vehicle (LLRV) in flight

NASA Technical Reports Server (NTRS)

1965-01-01

In this 1965 NASA Flight Reserch Center photograph the Lunar Landing Research Vehicle (LLRV) number 1 is shown in flight. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a 'free flight' vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV, in case of jet engine failure, six-500-pounds-of thrust rockets could be used by the pilot to carefully apply lift thrust during the rapid descent to hopefully achieve a controllable landing. The pilot's platform extended forward between two legs while an electronics platform, similarly located, extended rearward. The pilot had a zero-zero ejection seat that would then lift him away to safety. Weight and balance design constraints were among the most challenging to meet for all phases of the program (design, development, operations). The two LLRVs were shipped disassembled from Bell to the FRC in April 1964, with program emphasis placed on vehicle No. 1. The scene then shifted to the old South Base area of Edwards Air Force Base. On the day of the first flight, Oct. 30, 1964, NASA research pilot Joe Walker flew it three times for a total of just under 60 seconds, to a peak altitude of approximately 10 feet. By mid-1966 the NASA Flight Research Center had accumulated enough data from the LLRV flight program to give Bell a contract to deliver three Lunar Landing Training Vehicles (LLTVs) at a cost of $2.5 million each. As 1966 ended, the LLRV #1 had flown 198 flights, and the LLRV #2 was being assembled, instrumented and cockpit modifications made at the South Base. The first flight of the number two LLRV in early January 1967 was quickly followed by five more. In December 1966 vehicle No. 1 was shipped to Houston, followed by No. 2 in mid January 1967. When Dryden's LLRVs arrived at Houston they joined the first of the LLTVs to eventually make up the five-vehicle training and simulator fleet. All five vehicles were relied on for simulation and training of moon landings.

Effect of Mental Arithmetic on heart rate responses during Parabolic Flights: the Barcelona Zero-G Challenge

NASA Astrophysics Data System (ADS)

Osborne, Jeffrey R.; Alonsopérez Lanza, María Victoria; Desclaux, David Ferrer; Goswami, Nandu; González Alonso, Daniel Ventura; Moser, Maximilian; Grote, Vincent; Garcia-Cuadrado, Gloria; Perez-Poch, Antoni

2014-07-01

When an astronaut transitions from a low to high gravitational environment, fluid shifts from the head towards the feet resulting in orthostatic intolerance and syncope. Ground based experiments have shown that by stimulating the cardiovascular system via simple mental stressors, syncope can be delayed, potentially enabling astronauts to reach assistance before loss of consciousness. However, the effect of mental stressors on the stimulation of the cardiovascular system in gravitational environments different than that of Earth's is unknown. As such, this paper investigates the effects that mental stressors under various gravitational environments. To do this, a pilot study was performed in which two participants were flown on two separate parabolic flights that simulated hyper and hypogravity conditions. The plane used was an Aerobatic Single-Engine Cap-10B plane (twin seater), and each participant executed 11 parabolas. The participants were the winners of the Barcelona Zero-G Challenge 2011 organized by UPC Universitat Politècnica de Catalunya-BarcelonaTech and Aeroclub Barcelona-Sabadell. Measurements were made of the participants' hemodynamic and autonomic response throughout the parabolas, using a Chronocord: high precision HRV monitor. Comparisons of the baseline response without mental stressors, and the response with mental stressors during different gravitational loading conditions were made. It was observed that there is an increase in cardiovascular activity during hypo- and hyper-gravity when performing mental arithmetic. Our results show that the twin seater aerobatic single engine CAP-10B aicraft can provide changing gravitational loading conditions for enough periods to study changes in physiological systems.

ECN-535

NASA Image and Video Library

1964-12-09

In this NASA Flight Reserch Center photograph the Lunar Landing Research Vehicle (LLRV) number 1 is shown in flight. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the Moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on Earth in a simulated Moon environment, one sixth of the Earth's gravity and with totally transparent aerodynamic forces in a "free flight" vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the Moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the Moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal translations. Sixteen smaller hydrogen-peroxide rockets, mounted in pairs, gave the pilot control in pitch, yaw, and roll. On the LLRV,

Literature review: Assessment of DWPF melter and melter off-gas system lifetime

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

Reigel, M. M.

2015-07-30

A glass melter for use in processing radioactive waste is a challenging environment for the materials of construction (MOC) resulting from a combination of high temperatures, chemical attack, and erosion/corrosion; therefore, highly engineered materials must be selected for this application. The focus of this report is to review the testing and evaluations used in the selection of the Defense Waste Processing Facility (DWPF), glass contact MOC specifically the Monofrax ® K-3 refractory and Inconel ® 690 alloy. The degradation or corrosion mechanisms of these materials during pilot scale testing and in-service operation were analyzed over a range of oxidizing andmore » reducing flowsheets; however, DWPF has primarily processed a reducing flowsheet (i.e., Fe 2+/ΣFe of 0.09 to 0.33) since the start of radioactive operations. This report also discusses the materials selection for the DWPF off-gas system and the corrosion evaluation of these materials during pilot scale testing and non-radioactive operations of DWPF Melter #1. Inspection of the off-gas components has not been performed during radioactive operations with the exception of maintenance because of plugging.« less

Literature review: Assessment of DWPF melter and melter off-gas system lifetime

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

Reigel, M.

2015-07-30

A glass melter for use in processing radioactive waste is a challenging environment for the materials of construction (MOC) resulting from a combination of high temperatures, chemical attack, and erosion/corrosion; therefore, highly engineered materials must be selected for this application. The focus of this report is to review the testing and evaluations used in the selection of the Defense Waste Processing Facility (DWPF), glass contact MOC specifically the Monofrax® K-3 refractory and Inconel® 690 alloy. The degradation or corrosion mechanisms of these materials during pilot scale testing and in-service operation were analyzed over a range of oxidizing and reducing flowsheets;more » however, DWPF has primarily processed a reducing flowsheet (i.e., Fe 2+/ΣFe of 0.09 to 0.33) since the start of radioactive operations. This report also discusses the materials selection for the DWPF off-gas system and the corrosion evaluation of these materials during pilot scale testing and non-radioactive operations of DWPF Melter #1. Inspection of the off-gas components has not been performed during radioactive operations with the exception of maintenance because of plugging.« less

Enhancing the Impact of NASA Astrophysics Education and Public Outreach: Community Collaborations

NASA Astrophysics Data System (ADS)

Smith, Denise A.; Lawton, B. L.; Bartolone, L.; Schultz, G. R.; Blair, W. P.; Astrophysics E/PO Community, NASA; NASA Astrophysics Forum Team

2013-01-01

The NASA Astrophysics Science Education and Public Outreach Forum is one of four scientist-educator teams that support NASA's Science Mission Directorate and its nationwide education and public outreach community in increasing the coherence, efficiency, and effectiveness of their education and public outreach efforts. NASA Astrophysics education and outreach teams collaborate with each other through the Astrophysics Forum to place individual programs in context, connect with broader education and public outreach activities, learn and share successful strategies and techniques, and develop new partnerships. This poster highlights examples of collaborative efforts designed to engage youth and adults across the full spectrum of learning environments, from public outreach venues, to centers of informal learning, to K-12 and higher education classrooms. These include coordinated efforts to support major outreach events such as the USA Science and Engineering Festival; pilot "Astro4Girls" activities in public libraries to engage girls and their families in science during Women’s History Month; and a pilot "NASA's Multiwavelength Universe" online professional development course for middle and high school educators. Resources to assist scientists and Astro101 instructors in incorporating NASA Astrophysics discoveries into their education and public outreach efforts are also discussed.

NASA Microgravity Science Competition for High-school-aged Student Teams

NASA Technical Reports Server (NTRS)

DeLombard, Richard; Stocker, Dennis; Hodanbosi, Carol; Baumann, Eric

2002-01-01

NASA participates in a wide variety of educational activities including competitive events. There are competitive events sponsored by NASA and student teams which are mentored by NASA centers. This participation by NASA in public forums serves to bring the excitement of aerospace science to students and educators. A new competition for highschool-aged student teams involving projects in microgravity has completed two pilot years and will have national eligibility for teams during the 2002-2003 school year. A team participating in the Dropping In a Microgravity Environment will research the field of microgravity, develop a hypothesis, and prepare a proposal for an experiment to be conducted in a microgravity drop tower facility. A team of NASA scientists and engineers will select the top proposals and those teams will then design and build their experiment apparatus. When the experiment apparatus are completed, team representatives will visit NASA Glenn in Cleveland, Ohio for operation of their facility and participate in workshops and center tours. Presented in this paper will be a description of DIME, an overview of the planning and execution of such a program, results from the first two pilot years, and a status of the first national competition.

Individual reactions to stress predict performance during a critical aviation incident.

PubMed

Vine, Samuel J; Uiga, Liis; Lavric, Aureliu; Moore, Lee J; Tsaneva-Atanasova, Krasimira; Wilson, Mark R

2015-01-01

Understanding the influence of stress on human performance is of theoretical and practical importance. An individual's reaction to stress predicts their subsequent performance; with a "challenge" response to stress leading to better performance than a "threat" response. However, this contention has not been tested in truly stressful environments with highly skilled individuals. Furthermore, the effect of challenge and threat responses on attentional control during visuomotor tasks is poorly understood. Thus, this study aimed to examine individual reactions to stress and their influence on attentional control, among a cohort of commercial pilots performing a stressful flight assessment. Sixteen pilots performed an "engine failure on take-off" scenario, in a high-fidelity flight simulator. Reactions to stress were indexed via self-report; performance was assessed subjectively (flight instructor assessment) and objectively (simulator metrics); gaze behavior data were captured using a mobile eye tracker, and measures of attentional control were subsequently calculated (search rate, stimulus driven attention, and entropy). Hierarchical regression analyses revealed that a threat response was associated with poorer performance and disrupted attentional control. The findings add to previous research showing that individual reactions to stress influence performance and shed light on the processes through which stress influences performance.

Use of oil shale ash in road construction: results of follow-up environmental monitoring.

PubMed

Reinik, Janek; Irha, Natalya; Koroljova, Arina; Meriste, Tõnis

2018-01-05

Oil shale ash (OSA) was used for road construction in a pristine swamp area in East-Estonia during 2013-2014. OSA was used as a binder both in mass stabilization of soft peat soil and in the upper layer. Use of OSA in civil engineering always raises questions about the environmental safety of such activities. Post-construction environmental monitoring of the pilot section was carried out in 2014 and 2015. The monitoring program involved surface water and soil sampling campaigns. Samples were analyzed for selected constituents and parameters of environmental concern. The paper gives data for assessing the environmental impact and evaluation of potential risks associated with construction of roads using OSA. Leaching of hazardous compounds from the pilot section to surrounding aqueous environment was not observed during the monitoring program. Still, the road construction affected the concentration of sulfates in surrounding surface water. Also, the water-soluble content of barium in surface water correlated significantly with the concentrations of chloride and sulfate ion and electric conductivity of the surface water. Therefore, it is recommended to monitor the electric conductivity, concentrations of sulfates, chlorides, and barium in nearby surface water when OSA is used in road construction.

A Qualitative Piloted Evaluation of the Tupolev Tu-144 Supersonic Transport

NASA Technical Reports Server (NTRS)

Rivers, Robert A.; Jackson, E. Bruce; Fullerton, C. Gordon; Cox, Timothy H.; Princen, Norman H.

2000-01-01

Two U.S. research pilots evaluated the Tupolev Tu-144 supersonic transport aircraft on three dedicated flights: one subsonic and two supersonic profiles. The flight profiles and maneuvers were developed jointly by Tupolev and U.S. engineers. The vehicle was found to have unique operational and flight characteristics that serve as lessons for designers of future supersonic transport aircraft. Vehicle subsystems and observed characteristics are described as are flight test planning and ground monitoring facilities. Maneuver descriptions and extended pilot narratives for each flight are included as appendices.

STS-47 Pilot Brown on OV-105's flight deck ten minutes after SSME cutoff

NASA Image and Video Library

1992-09-12

STS047-28-002 (20 Sept. 1992) --- Astronaut Curtis L. Brown, Jr., STS-47 pilot, is photographed at the Space Shuttle Endeavour's pilot station about ten minutes after main engine cutoff on launch day of the eight-day Spacelab-J mission. Wearing the partial-pressure launch and entry suit, Brown shared the forward cabin with astronaut Robert L. Gibson (out of frame at left), mission commander. Endeavour was beginning its second mission in space, this one devoted to research supporting the Spacelab-J mission.

Biofuel Pilot at St. Juliens Creek and Proposed NAVFAC Policy on Use of Biofuel In Heating Boilers

DTIC Science & Technology

2013-09-01

Engineering and Expeditionary Warfare Center (NAVFAC EXWC) was tasked by NAVFAC HQ with facilitating a pilot study on the use of B20 Biodiesel (20...by NAVFAC HQ with facilitating a pilot study on the use of B20 Biodiesel (20 % biofuel mixed with 80 % fossil fuel oil hereafter referred to as B20...renewable) attributes of B20 as compared to conventional fossil fuel oil, and the ease of boiler and fuel system conversion to the biodiesel fuel

Engineering Education Problems. The Laboratory Equipment Factor.

ERIC Educational Resources Information Center

National Society of Professional Engineers, Washington, DC.

Presented is a pilot study focusing attention on problems of deteriorating physical plants and inadequate/obsolete equipment contributing to the current crisis in engineering education. Data are reported from a survey instrument (included in an appendix) from 26 colleges/universities, representing 168 programs out of a national total of 1212…

Small Internal Combustion Engine Testing for a Hybrid-Electric Remotely-Piloted Aircraft

DTIC Science & Technology

2011-03-01

differential equations (ODEs) were formed and solved for numerically using various solvers in MATLAB . From these solutions, engine performance...program 5. □ Make sure eddy-current absorber and sprockets are free of debris and that no loose materials are close enough to become entangled

Methodology in Seeking Stakeholder Perceptions of Effective Technical Oral Presentations: An Exploratory Pilot Study

ERIC Educational Resources Information Center

Bhattacharyya, Ena; Patil, Arun; Sargunan, Rajeswary Appacutty

2010-01-01

Engineering communication studies indicate the importance of oral presentations as an indispensable component of workplace oral communication activities; however, since there is limited literature regarding stakeholder perceptions of effective presentation skills and attributes in technical oral presentations or final year engineering project…

Engineering a "Contact Zone" through Translanguaging

ERIC Educational Resources Information Center

Helm, Francesca; Dabre, Tejane

2018-01-01

This paper presents a pilot project which uses a translanguaging approach in order to subvert the power dynamics whereby language learners, refugees and migrants are positioned as defective or ineffective communicators of a target language. The project seeks to create a space, an engineered "contact zone" in which the negative,…

Preliminary Airworthiness Evaluation AH-1S Helicopter with OGEE Tip Shape Rotor Blades

DTIC Science & Technology

1980-05-01

ENGINEER PROJECT PILOT HENRY ARNAIZ PROJECT ENGINEER DTIC MAY 1980 ELECTEV SEP 2 I8 Approved for public release; distribution unlimited. A UNITED STATES...compressibility effects between flights. 7. Airspeed and altitude were obtained from a boom-mounted pitot -static probe. Corrections for position error

77 FR 30238 - Living History Flight Experience (LHFE)-Exemptions for Passenger Carrying Operations Conducted...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-05-22

... significant, American- manufactured large, crew-served, piston-powered, multi-engine, World War II bomber... public safety (e.g., older and slower multi-engine which airplanes allow time for appropriate corrective... air show that was piloted by two highly qualified and well-trained flight crewmembers clearly...

The European Framework of Languages: A Piloting Sample of Cross-Curricular Strategy

ERIC Educational Resources Information Center

Mansilla, Paloma Ubeda; Riejos, Ana Maria Roldan

2007-01-01

This paper gives a short overview of the history of the Common European Framework of Reference (CEF) and European Language Portfolio (ELP) and explains their aims and functions. It then provides a summary of the ELP use in Europe and in Spain by showing a pilot study of its implementation carried out at the Schools of Civil Engineering and…

The Influence That Javascript™ Has on the Visibility of a Website to Search Engines--A Pilot Study

ERIC Educational Resources Information Center

Weideman, M.; Schwenke, F.

2006-01-01

Introduction: In this research project, an empirical pilot study on the relationship between JavaScript™ usage and Website visibility was carried out. The main purpose was to establish whether JavaScript™- based hyperlinks attract or repel crawlers, resulting in an increase or decrease in Website visibility. Method: A literature survey has…

A National Partnership-Based Summer Learning Initiative to Engage Underrepresented Students with Science, Technology, Engineering and Mathematics

NASA Technical Reports Server (NTRS)

Melvin, Leland

2010-01-01

In response to the White House Educate to Innovate campaign, NASA developed a new science, technology, engineering, and mathematics (STEM) education program for non-traditional audiences that also focused on public-private partnerships and nationwide participation. NASA recognized that summer break is an often overlooked but opportune time to engage youth in STEM experiences, and elevated its ongoing commitment to the cultivation of diversity. The Summer of Innovation (SoI) is the resulting initiative that uses NASA's unique missions and resources to boost summer learning, particularly for students who are underrepresented, underserved and underperforming in STEM. The SoI pilot, launched in June 2010, is a multi-faceted effort designed to improve STEM teaching and learning through partnership, multi-week summer learning programs, special events, a national concluding event, and teacher development. The SoI pilot features strategic infusion of NASA content and educational resource materials, sustainability through STEM Learning Communities, and assessments of effectiveness of SoI interventions with other pilot efforts. This paper examines the inception and development of the Summer of Innovation pilot project, including achievements and effectiveness, as well as lessons learned for future efforts.

The effects of motion and g-seat cues on pilot simulator performance of three piloting tasks

NASA Technical Reports Server (NTRS)

Showalter, T. W.; Parris, B. L.

1980-01-01

Data are presented that show the effects of motion system cues, g-seat cues, and pilot experience on pilot performance during takeoffs with engine failures, during in-flight precision turns, and during landings with wind shear. Eight groups of USAF pilots flew a simulated KC-135 using four different cueing systems. The basic cueing system was a fixed-base type (no-motion cueing) with visual cueing. The other three systems were produced by the presence of either a motion system or a g-seat, or both. Extensive statistical analysis of the data was performed and representative performance means were examined. These data show that the addition of motion system cueing results in significant improvement in pilot performance for all three tasks; however, the use of g-seat cueing, either alone or in conjunction with the motion system, provides little if any performance improvement for these tasks and for this aircraft type.

Piloted evaluation of an integrated propulsion and flight control simulator

NASA Technical Reports Server (NTRS)

Bright, Michelle M.; Simon, Donald L.

1992-01-01

This paper describes a piloted evaluation of the integrated flight and propulsion control simulator at NASA Lewis Research Center. The purpose of this evaluation is to demonstrate the suitability and effectiveness of this fixed based simulator for advanced integrated propulsion and airframe control design. The evaluation will cover control effector gains and deadbands, control effectiveness and control authority, and heads up display functionality. For this evaluation the flight simulator is configured for transition flight using an advanced Short Take-Off and vertical Landing fighter aircraft model, a simplified high-bypass turbofan engine model, fighter cockpit, displays, and pilot effectors. The paper describes the piloted tasks used for rating displays and control effector gains. Pilot comments and simulation results confirm that the display symbology and control gains are very adequate for the transition flight task. Additionally, it is demonstrated that this small-scale, fixed base flight simulator facility can adequately perform a real time, piloted control evaluation.

Piloted simulation study of an ILS approach of a twin-pusher business/commuter turboprop aircraft configuration

NASA Technical Reports Server (NTRS)

Riley, Donald R.; Brandon, Jay M.; Glaab, Louis J.

1994-01-01

A six-degree-of-freedom nonlinear simulation of a twin-pusher, turboprop business/commuter aircraft configuration representative of the Cessna ATPTB (Advanced turboprop test bed) was developed for use in piloted studies with the Langley General Aviation Simulator. The math models developed are provided, simulation predictions are compared with with Cessna flight-test data for validation purposes, and results of a handling quality study during simulated ILS (instrument landing system) approaches and missed approaches are presented. Simulated flight trajectories, task performance measures, and pilot evaluations are presented for the ILS approach and missed-approach tasks conducted with the vehicle in the presence of moderate turbulence, varying horizontal winds and engine-out conditions. Six test subjects consisting of two research pilots, a Cessna test pilot, and three general aviation pilots participated in the study. This effort was undertaken in cooperation with the Cessna Aircraft Company.

The Design of Large-Scale Complex Engineered Systems: Present Challenges and Future Promise

NASA Technical Reports Server (NTRS)

Bloebaum, Christina L.; McGowan, Anna-Maria Rivas

2012-01-01

Model-Based Systems Engineering techniques are used in the SE community to address the need for managing the development of complex systems. A key feature of the MBSE approach is the use of a model to capture the requirements, architecture, behavior, operating environment and other key aspects of the system. The focus on the model differentiates MBSE from traditional SE techniques that may have a document centric approach. In an effort to assess the benefit of utilizing MBSE on its flight projects, NASA Langley has implemented a pilot program to apply MBSE techniques during the early phase of the Materials International Space Station Experiment-X (MISSE-X). MISSE-X is a Technology Demonstration Mission being developed by the NASA Office of the Chief Technologist i . Designed to be installed on the exterior of the International Space Station (ISS), MISSE-X will host experiments that advance the technology readiness of materials and devices needed for future space exploration. As a follow-on to the highly successful series of previous MISSE experiments on ISS, MISSE-X benefits from a significant interest by the

Evaluating Quality in Educational Spaces: OECD/CELE Pilot Project

ERIC Educational Resources Information Center

von Ahlefeld, Hannah

2009-01-01

CELE's International Pilot Project on Evaluating Quality in Educational Spaces aims to assist education authorities, schools and others to maximise the use of and investment in learning environments. This article provides an update on the pilot project, which is currently being implemented in Brazil, Mexico, New Zealand, Portugal and the United…

Use of virtual reality to promote hand therapy post-stroke

NASA Astrophysics Data System (ADS)

Tsoupikova, Daria; Stoykov, Nikolay; Vick, Randy; Li, Yu; Kamper, Derek; Listenberger, Molly

2013-03-01

A novel artistic virtual reality (VR) environment was developed and tested for use as a rehabilitation protocol for post-stroke hand rehabilitation therapy. The system was developed by an interdisciplinary team of engineers, art therapists, occupational therapists, and VR artists to improve patients' motivation and engagement. Specific exercises were developed to explicitly promote the practice of therapeutic tasks requiring hand and arm coordination for upper extremity rehabilitation. Here we describe system design, development, and user testing for efficiency, subject's satisfaction and clinical feasibility. We report results of the completed qualitative, pre-clinical pilot study of the system effectiveness for therapy. Fourteen stroke survivors with chronic hemiparesis participated in a single training session within the environment to gauge user response to the protocol through a custom survey. Results indicate that users found the system comfortable, enjoyable, tiring; instructions clear, and reported a high level of satisfaction with the VR environment and rehabilitation task variety and difficulty. Most patients reported very positive impressions of the VR environment and rated it highly, appreciating its engagement and motivation. We are currently conducting a longitudinal intervention study over 6 weeks in stroke survivors with chronic hemiparesis. Initial results following use of the system on the first subjects demonstrate that the system is operational and can facilitate therapy for post stroke patients with upper extremity impairment.

AWE: Aviation Weather Data Visualization Environment

NASA Technical Reports Server (NTRS)

Spirkovska, Lilly; Lodha, Suresh K.; Norvig, Peter (Technical Monitor)

2000-01-01

Weather is one of the major causes of aviation accidents. General aviation (GA) flights account for 92% of all the aviation accidents, In spite of all the official and unofficial sources of weather visualization tools available to pilots, there is an urgent need for visualizing several weather related data tailored for general aviation pilots. Our system, Aviation Weather Data Visualization Environment AWE), presents graphical displays of meteorological observations, terminal area forecasts, and winds aloft forecasts onto a cartographic grid specific to the pilot's area of interest. Decisions regarding the graphical display and design are made based on careful consideration of user needs. Integral visual display of these elements of weather reports is designed for the use of GA pilots as a weather briefing and route selection tool. AWE provides linking of the weather information to the flight's path and schedule. The pilot can interact with the system to obtain aviation-specific weather for the entire area or for his specific route to explore what-if scenarios and make "go/no-go" decisions. The system, as evaluated by some pilots at NASA Ames Research Center, was found to be useful.

Economic Impact Forecast System (EIFS). Version 2.0. Users Manual. Supplement II. European Economic Impact Forecast System (EEIFS), Phase 1, (FRG/EIFS Pilot Model).

DTIC Science & Technology

1982-05-01

Chmpip. tL : Construction engineering Research Laboratory ; available from NTIS. 1982. 71 p. (Technical report / Construction Engineering Researsh ...AD-Al17 661 CONSTRUCTION ENGINEERING RESEARCH LAB (ARMY) CHAMPAIGN IL F/G 5/3 ECONOMIC IMPACT FORECAST SYSTEM (EIFS). VERSION 2.0. USERS MANU--ETC(u...CONSTRUCTION ENGINEERING RESEARCH LABORATORY 4A762720A896-C-004 P.O. BOX 4005, CHAMPAIGN, IL 61820 I. CONTROLLING OFFICE NAME AND ADDRESS It. REPORT

STEM Girls Night In at Goddard

NASA Image and Video Library

2016-11-05

Girls Night In was held at Goddard on Nov 4-5, 2016. This is a pilot program which reinvigorates, inspires, and engages high school girls who may be struggling or not fully engaged in STEM (Science, Technology Engineering and Math) education. The program allowed NASA women to share and demonstrate the work they do, provide the girls an opportunity to completely immerse themselves in Goddard science, technology, engineering and math as well as provide them activities that will challenge and promote knowledge and discovery. Goddard invites other NASA centers tolearn from this pilot program and work towards a simultaneous multicenter event in the future. Participating schools were: DuVal, Crossland, Flowers, High Point, Northwestern and Oxon Hill

STEM Girls Night In at Goddard

NASA Image and Video Library

2016-11-04

Girls Night In was held at Goddard on Nov 4-5, 2016. This is a pilot program which reinvigorates, inspires, and engages high school girls who may be struggling or not fully engaged in STEM (Science, Technology Engineering and Math) education. The program allowed NASA women to share and demonstrate the work they do, provide the girls an opportunity to completely immerse themselves in Goddard science, technology, engineering and math as well as provide them activities that will challenge and promote knowledge and discovery. Goddard invites other NASA centers tolearn from this pilot program and work towards a simultaneous multicenter event in the future. Participating schools were: DuVal, Crossland, Flowers, High Point, Northwestern and Oxon Hill

HOPE: An On-Line Piloted Handling Qualities Experiment Data Book

NASA Technical Reports Server (NTRS)

Jackson, E. B.; Proffitt, Melissa S.

2010-01-01

A novel on-line database for capturing most of the information obtained during piloted handling qualities experiments (either flight or simulated) is described. The Hyperlinked Overview of Piloted Evaluations (HOPE) web application is based on an open-source object-oriented Web-based front end (Ruby-on-Rails) that can be used with a variety of back-end relational database engines. The hyperlinked, on-line data book approach allows an easily-traversed way of looking at a variety of collected data, including pilot ratings, pilot information, vehicle and configuration characteristics, test maneuvers, and individual flight test cards and repeat runs. It allows for on-line retrieval of pilot comments, both audio and transcribed, as well as time history data retrieval and video playback. Pilot questionnaires are recorded as are pilot biographies. Simple statistics are calculated for each selected group of pilot ratings, allowing multiple ways to aggregate the data set (by pilot, by task, or by vehicle configuration, for example). Any number of per-run or per-task metrics can be captured in the database. The entire run metrics dataset can be downloaded in comma-separated text for further analysis off-line. It is expected that this tool will be made available upon request

Rocket Engine Nozzle Side Load Transient Analysis Methodology: A Practical Approach

NASA Technical Reports Server (NTRS)

Shi, John J.

2005-01-01

During the development stage, in order to design/to size the rocket engine components and to reduce the risks, the local dynamic environments as well as dynamic interface loads must be defined. There are two kinds of dynamic environment, i.e. shock transients and steady-state random and sinusoidal vibration environments. Usually, the steady-state random and sinusoidal vibration environments are scalable, but the shock environments are not scalable. In other words, based on similarities only random vibration environments can be defined for a new engine. The methodology covered in this paper provides a way to predict the shock environments and the dynamic loads for new engine systems and new engine components in the early stage of new engine development or engine nozzle modifications.

Defense Acquisitions: Assessments of Selected Weapon Programs

DTIC Science & Technology

2016-03-01

Increment 3 81 Indirect Fire Protection Capability Increment 2-Intercept Block 1 (IFPC Inc 2-I Block 1) 83 Improved Turbine Engine Program (ITEP...ITEP Improved Turbine Engine Program JAGM Joint Air-to-Ground Missile JLTV Joint Light Tactical Vehicle JSTARS Recap Joint Surveillance Target...Attack Radar System Recap 09/2017 —-   Improved Turbine Engine Program 06/2018 O O O Amphibious Ship Replacement 09/2018 O O Advanced Pilot

Achieving Helicopter Modernization with Advanced Technology Turbine Engines

DTIC Science & Technology

1999-04-01

computer modeling of compressor and turbine aerody- digital engine control ( FADEC ) with manual backup. namics. Modern directionally solidified and single...controlled by a dual RAH.66A M channel FADEC , and features a very simple installation "" Improved Gross Weight and significantly reduced pilot...air separation efficiencies as an "advanced technology" engine. Technological meas- high as 97.5%. The FADEC improves acceleration, ures include but

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 Model-Based Approach to Engineering Behavior of Complex Aerospace Systems

NASA Technical Reports Server (NTRS)

Ingham, Michel; Day, John; Donahue, Kenneth; Kadesch, Alex; Kennedy, Andrew; Khan, Mohammed Omair; Post, Ethan; Standley, Shaun

2012-01-01

One of the most challenging yet poorly defined aspects of engineering a complex aerospace system is behavior engineering, including definition, specification, design, implementation, and verification and validation of the system's behaviors. This is especially true for behaviors of highly autonomous and intelligent systems. Behavior engineering is more of an art than a science. As a process it is generally ad-hoc, poorly specified, and inconsistently applied from one project to the next. It uses largely informal representations, and results in system behavior being documented in a wide variety of disparate documents. To address this problem, JPL has undertaken a pilot project to apply its institutional capabilities in Model-Based Systems Engineering to the challenge of specifying complex spacecraft system behavior. This paper describes the results of the work in progress on this project. In particular, we discuss our approach to modeling spacecraft behavior including 1) requirements and design flowdown from system-level to subsystem-level, 2) patterns for behavior decomposition, 3) allocation of behaviors to physical elements in the system, and 4) patterns for capturing V&V activities associated with behavioral requirements. We provide examples of interesting behavior specification patterns, and discuss findings from the pilot project.

Engineering flight and guest pilot evaluation report, phase 2. [DC 8 aircraft

NASA Technical Reports Server (NTRS)

Morrison, J. A.; Anderson, E. B.; Brown, G. W.; Schwind, G. K.

1974-01-01

Prior to the flight evaluation, the two-segment profile capabilities of the DC-8-61 were evaluated and flight procedures were developed in a flight simulator at the UA Flight Training Center in Denver, Colorado. The flight evaluation reported was conducted to determine the validity of the simulation results, further develop the procedures and use of the area navigation system in the terminal area, certify the system for line operation, and obtain evaluations of the system and procedures by a number of pilots from the industry. The full area navigation capabilities of the special equipment installed were developed to provide terminal area guidance for two-segment approaches. The objectives of this evaluation were: (1) perform an engineering flight evaluation sufficient to certify the two-segment system for the six-month in-service evaluation; (2) evaluate the suitability of a modified RNAV system for flying two-segment approaches; and (3) provide evaluation of the two-segment approach by management and line pilots.

Vigilance impossible: Diligence, distraction, and daydreaming all lead to failures in a practical monitoring task.

PubMed

Casner, Stephen M; Schooler, Jonathan W

2015-09-01

In laboratory studies of vigilance, participants watch for unusual events in a "sit and stare" fashion as their performance typically declines over time. But watch keepers in practical settings seldom approach monitoring in such simplistic ways and controlled environments. We observed airline pilots performing routine monitoring duties in the cockpit. Unlike laboratory studies, pilots' monitoring did not deteriorate amidst prolonged vigils. Monitoring was frequently interrupted by other pop-up tasks and misses followed. However, when free from these distractions, pilots reported copious mind wandering. Pilots often confined their mind wandering to times in which their monitoring performance would not conspicuously suffer. But when no convenient times were available, pilots mind wandered anyway and misses ensued. Real-world monitors may be caught between a continuous vigilance approach that is doomed to fail, a dynamic environment that cannot be fully controlled, and what may be an irresistible urge to let one's thoughts drift. Published by Elsevier Inc.

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.

Rural Latinos' mental wellbeing: a mixed-methods pilot study of family, environment and social isolation factors.

PubMed

Stacciarini, Jeanne-Marie R; Smith, Rebekah; Garvan, Cynthia Wilson; Wiens, Brenda; Cottler, Linda B

2015-05-01

Upon immigration to the rural areas in the US, Latino families may experience cultural, geographic, linguistic and social isolation, which can detrimentally affect their wellbeing by acting as chronic stressors. Using a community engagement approach, this is a pilot mixed-method study with an embedded design using concurrent qualitative and quantitative data. The purpose of this study is to evaluate family and social environments in terms of protective factors and modifiable risks associated with mental well-being in Latino immigrants living in rural areas of Florida. Latino immigrant mother and adolescent dyads were interviewed by using in-depth ethnographic semistructured interviews and subsequent quantitative assessments, including a demographic questionnaire and three structured instruments: the Family Environment Scale Real Form, the SF-12v2™ Health Survey and the short version (eight items) of PROMIS Health Organization Social Isolation. This mixed-method pilot study highlighted how family, rural, and social environments can protect or impair wellbeing in rural Latino immigrant mother and adolescent dyads.

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.

Students' Pilot Laboratory for Homogeneous Chemical Reactor Analysis and Design in Olive Mill Wastewater Treatment

ERIC Educational Resources Information Center

Ochando-Pulido, J. M.

2017-01-01

The Chemical Engineering Department at the University of Granada have endeavored to make a number of high quality experiments to familiarize our students with our latest research and also scale-up of processes. A pilot-scale wastewater treatment plant was set-up to give students a close practical view of the treatments of effluents by-produced in…

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

14 CFR 23.367 - Unsymmetrical loads due to engine failure.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Unsymmetrical loads due to engine failure. 23.367 Section 23.367 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... may be based on the limit pilot forces specified in § 23.397 except that lower forces may be assumed...

14 CFR 23.367 - Unsymmetrical loads due to engine failure.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Unsymmetrical loads due to engine failure. 23.367 Section 23.367 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... may be based on the limit pilot forces specified in § 23.397 except that lower forces may be assumed...

14 CFR 23.367 - Unsymmetrical loads due to engine failure.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Unsymmetrical loads due to engine failure. 23.367 Section 23.367 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... may be based on the limit pilot forces specified in § 23.397 except that lower forces may be assumed...

An Interdisciplinary Design Studio: How Can Art and Engineering Collaborate to Increase Students' Creativity?

ERIC Educational Resources Information Center

Costantino, Tracie; Kellam, Nadia; Cramond, Bonnie; Crowder, Isabelle

2010-01-01

Creativity often has been associated with the arts, although creativity also is essential for innovative discoveries and applications in science and engineering. In this article, a pilot study is presented about an investigation concerning how creativity is fostered in an art education course in conjunction with an undergraduate engineering…

McNair Scholars' Science, Technology, Engineering, and Mathematics (STEM) Graduate Experience: A Pilot Study

ERIC Educational Resources Information Center

Bancroft, Senetta F.; Benson, Susan Kushner; Johnson-Whitt, Eugenia

2016-01-01

Nationally, racial and gender disparities persist in science, technology, engineering, and mathematics (STEM) disciplines. These disparities are most notable at the doctoral level and are also found in the doctoral outcomes of Ronald E. McNair Postbaccalaureate Achievement Program participants (Scholars) despite opportunities designed to promote…

Elementary Educators' Perceptions of Design, Engineering, and Technology: An Analysis by Ethnicity

ERIC Educational Resources Information Center

Mendoza Diaz, Noemi V.; Cox, Monica F.; Adams, Stephanie G.

2013-01-01

This mixed-methods pilot study extends researchers' understandings about elementary teachers' (K-6) perceptions of design, engineering and technology. In the first phase of the study, a reliable and valid survey was given to thirty-five participants in a teacher professional development academy sponsored by the Institute for P-12 Engineering…

78 FR 65200 - Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) Helicopters

Federal Register 2010, 2011, 2012, 2013, 2014

2013-10-31

... vibrations at certain engine speeds during steady- state operations. These actions are intended to alert... proposed requirements were intended to alert pilots to avoid certain engine speeds during steady-state... the change, and installing a decal as described in Bell Alert Service Bulletin (ASB) No. 407-05-67...

Development and Testing of an Experimental Mobile Instructional Facility for Applied Courses in Engineering Technology.

ERIC Educational Resources Information Center

Kleine, Louis W.

The experimental pilot project was conducted to determine whether students who take the laboratory phase of an engineering technology applied electricity course in a mobile laboratory at branch schools demonstrate proficiency comparable to students who take the applied electricity course in permanent facilities at the parent institution. The…

Podcasting in Engineering Education: A Preliminary Study of Content, Student Attitudes, and Impact

ERIC Educational Resources Information Center

Berger, Edward

2007-01-01

Edward Berger describes a pilot project implemented in an undergraduate engineering mechanics course, entitled Strength of Materials to investigate whether and how students would perceive a benefit from podcasting as a pedagogical tool. Three types of podcasting content were produced: (a) video problem solutions, (b) roundtable discussions, and…

Student Learning Outcomes from a Pilot Medical Innovations Course with Nursing, Engineering, and Biology Undergraduate Students

ERIC Educational Resources Information Center

Ludwig, Patrice M.; Nagel, Jacquelyn K.; Lewis, Erica J.

2017-01-01

Background: Preparing today's undergraduate students from science, technology, engineering, and math (STEM) and related health professions to solve wide-sweeping healthcare challenges is critical. Moreover, it is imperative that educators help students develop the capabilities needed to meet those challenges, including problem solving,…

The implementation and operation of a variable-response electronic throttle control system for a TF-104G aircraft

NASA Technical Reports Server (NTRS)

Neal, Bradford; Sengupta, Upal

1989-01-01

During some flight programs, researchers have encountered problems in the throttle response characteristics of high-performance aircraft. To study and to help solve these problems, the National Aeronautics and Space Administration Ames Research Center's Dryden Flight Research Facility (Ames-Dryden) conducted a study using a TF-104G airplane modified with a variable-response electronic throttle control system. Ames-Dryden investigated the effects of different variables on engine response and handling qualities. The system provided transport delay, lead and lag filters, second-order lags, command rate and position limits, and variable gain between the pilot's throttle command and the engine fuel controller. These variables could be tested individually or in combination. Ten research flights were flown to gather data on engine response and to obtain pilot ratings of the various system configurations. The results should provide design criteria for engine-response characteristics. The variable-response throttle components and how they were installed in the TF-104G aircraft are described. How the variable-response throttle was used in flight and some of the results of using this system are discussed.

Perspective of Micro Process Engineering for Thermal Food Treatment

PubMed Central

Mathys, Alexander

2018-01-01

Micro process engineering as a process synthesis and intensification tool enables an ultra-short thermal treatment of foods within milliseconds (ms) using very high surface-area-to-volume ratios. The innovative application of ultra-short pasteurization and sterilization at high temperatures, but with holding times within the range of ms would allow the preservation of liquid foods with higher qualities, thereby avoiding many unwanted reactions with different temperature–time characteristics. Process challenges, such as fouling, clogging, and potential temperature gradients during such conditions need to be assessed on a case by case basis and optimized accordingly. Owing to the modularity, flexibility, and continuous operation of micro process engineering, thermal processes from the lab to the pilot and industrial scales can be more effectively upscaled. A case study on thermal inactivation demonstrated the feasibility of transferring lab results to the pilot scale. It was shown that micro process engineering applications in thermal food treatment may be relevant to both research and industrial operations. Scaling of micro structured devices is made possible through the use of numbering-up approaches; however, reduced investment costs and a hygienic design must be assured. PMID:29686990

Evaluation of a long-endurance-surveillance remotely-piloted vehicle with and without laminar flow control

NASA Technical Reports Server (NTRS)

Turriziani, R. V.; Lovell, W. A.; Price, J. E.; Quartero, C. B.; Washburn, S. F.

1979-01-01

Two aircraft were evaluated, using a derated TF34-GE-100 turbofan engine one with laminar flow control (LFC) and one without. The mission of the remotely piloted vehicles (RPV) is one of high-altitude loiter at maximum endurance. With the LFC system maximum mission time increased by 6.7 percent, L/D in the loiter phase improved 14.2 percent, and the minimum parasite drag of the wing was reduced by 65 percent resulting in a 37 percent reduction for the total airplane. Except for the minimum parasite drag of the wing, the preceding benefits include the offsetting effects of weight increase, suction power requirements, and drag of the wing-mounted suction pods. In a supplementary study using a scaled-down, rather than derated, version of the engine, on the LFC configuration, a 17.6 percent increase in mission time over the airplane without LFC and an incremental time increase of 10.2 percent over the LFC airplane with derated engine were attained. This improvement was due principally to reductions in both weight and drag of the scaled engine.

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…

Preparing Pilots for Takeoff

ERIC Educational Resources Information Center

Ravage, Barbara

2012-01-01

Why would schools consider partnering with a vendor to operate a pilot? Why not just wait until the final product is released? For starters, pilots provide schools with a golden opportunity to get an early look at the software, take it for a test flight, and ask for changes tailored to their operating environment and business needs. In some cases,…

Piloted Aircraft Environment Simulation Techniques

DTIC Science & Technology

1978-04-01

raS’I.Al. lIIf~iiI~.1 labL. lot. Rolmotion -oft. skylicav - ow d Roll rMotion -oft Skylicape - Off Fig 6 a A Effect of roll motion and akyscape, an msatwntn...greater realism and pilot involvement than ground based simu- lation, it still lacks some of the pilot motivating factors of actual combat. Flight

Sensory Adapted Dental Environments to Enhance Oral Care for Children with Autism Spectrum Disorders: A Randomized Controlled Pilot Study

ERIC Educational Resources Information Center

Cermak, Sharon A.; Stein Duker, Leah I.; Williams, Marian E.; Dawson, Michael E.; Lane, Christianne J.; Polido, José C.

2015-01-01

This pilot and feasibility study examined the impact of a sensory adapted dental environment (SADE) to reduce distress, sensory discomfort, and perception of pain during oral prophylaxis for children with autism spectrum disorder (ASD). Participants were 44 children ages 6-12 (n = 22 typical, n = 22 ASD). In an experimental crossover design, each…

A systematic approach to advanced cockpit warning systems for air transport operations: Line pilot preferences

NASA Technical Reports Server (NTRS)

Williams, D. H.; Simpson, C. A.

1976-01-01

Line pilots (fifty captains, first officers, and flight engineers) from 8 different airlines were administered a structured questionnaire relating to future warning system design and solutions to current warning system problems. This was followed by a semantic differential to obtain a factor analysis of 18 different cockpit warning signals on scales such as informative/distracting, annoying/soothing. Half the pilots received a demonstration of the experimental text and voice synthesizer warning systems before answering the questionnaire and the semantic differential. A control group answered the questionnaire and the semantic differential first, thus providing a check for the stability of pilot preferences with and without actual exposure to experimental systems. Generally, the preference data obtained revealed much consistency and strong agreement among line pilots concerning advance cockpit warning system design.

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.

Measurements to Understand the Flow Mechanisms Contributing to Tandem Rotor Outwash

DTIC Science & Technology

2015-05-23

Directorate —AFDD Aviation & Missile Research, Development & Engineering Center Research, Development & Engineering Command Ames Research Center, Moffett...pilot visibility issues in brownout, dust entrain- ment into engine inlets, blade erosion, and increased air- craft maintenance. Though almost 50 years...Diameter Taylor , 1950 (Ref. 17) S, C, Ta 20 in & 45 in Fradenburgh, 1958 (Ref. 18) S 24 in Bolanovich & Marks, 1959 (Ref. 19) S 75 ft Bryan, 1960 (Ref

2012 Anthropometric Survey of U.S. Army Pilot Personnel: Methods and Summary Statistics

DTIC Science & Technology

2016-05-01

distribution is unlimited U.S. Army Natick Soldier Research, Development and Engineering Center Natick, Massachusetts 01760-2642 REPORT...NAME(S) AND ADDRESS(ES) Natick Soldier Research, Development and Engineering Center ATTN: RDNS-WSH 10 General Greene Avenue, Natick, MA 01760-2642 8...Development and Engineering Center. Goals of the survey were to acquire a large body of data from comparably measured males and females to serve the Army

Research on Building Education & Workforce Capacity in Systems Engineering

DTIC Science & Technology

2011-10-31

product or prototype that addresses a real DoD need. Implemented as pilot courses in eight civilian and six military universities affiliated with...Engineering 1 1.1 Computer Engineering 1 1.1 Operations Research 1 1.1 Product Architecture 1 1.1 Total 93 100.0 Table 7: Breakdown of Student... product specifications, inattention to budget limits and safety issues, inattention to product life cycle, poor implementation of risk management plans

Fuel quantity modulation in pilot ignited engines

DOEpatents

May, Andrew

2006-05-16

An engine system includes a first fuel regulator adapted to control an amount of a first fuel supplied to the engine, a second fuel regulator adapted to control an amount of a second fuel supplied to the engine concurrently with the first fuel being supplied to the engine, and a controller coupled to at least the second fuel regulator. The controller is adapted to determine the amount of the second fuel supplied to the engine in a relationship to the amount of the first fuel supplied to the engine to operate in igniting the first fuel at a specified time in steady state engine operation and adapted to determine the amount of the second fuel supplied to the engine in a manner different from the relationship at steady state engine operation in transient engine operation.

The 10 MWe Solar Thermal Central Receiver Pilot Plant: Solar facilities design integration. Pilot-plant station manual (RADL Item 2-1). Volume 1: System description

NASA Astrophysics Data System (ADS)

1982-09-01

The complete Barstow Solar Pilot Plant is described. The plant requirements and general description are presented, the mechanical, electric power, and control and instrumentation systems as well as civil engineering and structural aspects and the station buildings are described. Included in the mechanical systems are the heliostats, receiver, thermal storage system, beam characterization system, steam, water, nitrogen, and compressed air systems, chemical feed system, fire protection system, drains, sumps and the waste disposal systems, and heating, ventilating, and air conditioning systems.

Proteus DSA control room in Mojave, CA

NASA Image and Video Library

2003-04-03

Proteus DSA control room in Mojave, CA (L to R) Jean-Pierre Soucy; Amphitech International Software engineer Craig Bomben; NASA Dryden Test Pilot Pete Siebold; (with headset, at computer controls) Scaled Composites pilot Bob Roehm; New Mexico State University (NMSU) UAV Technical Analysis Application Center (TAAC) Chuck Coleman; Scaled Composites Pilot Kari Sortland; NMSU TAAC Russell Wolfe; Modern Technology Solutions, Inc. Scaled Composites' unique tandem-wing Proteus was the testbed for a series of UAV collision-avoidance flight demonstrations. An Amphitech 35GHz radar unit installed below Proteus' nose was the primary sensor for the Detect, See and Avoid tests.

Pilot workload and fatigue: A critical survey of concepts and assessment techniques

NASA Technical Reports Server (NTRS)

Gartner, W. B.; Murphy, M. R.

1976-01-01

The principal unresolved issues in conceptualizing and measuring pilot workload and fatigue are discussed. These issues are seen as limiting the development of more useful working concepts and techniques and their application to systems engineering and management activities. A conceptual analysis of pilot workload and fatigue, an overview and critique of approaches to the assessment of these phenomena, and a discussion of current trends in the management of unwanted workload and fatigue effects are presented. Refinements and innovations in assessment methods are recommended for enhancing the practical significance of workload and fatigue studies.

A Flight Training Simulator for Instructing the Helicopter Autorotation Maneuver (Enhanced Version)

NASA Technical Reports Server (NTRS)

Rogers, Steven P.; Asbury, Charles N.

2000-01-01

Autorotation is a maneuver that permits a safe helicopter landing when the engine loses power. A catastrophe may occur if the pilot's control inputs are incorrect, insufficient, excessive, or poorly timed. Due to the danger involved, full-touchdown autorotations are very rarely practiced. Because in-flight autorotation training is risky, time-consuming, and expensive, the objective of the project was to develop the first helicopter flight simulator expressly designed to train students in this critical maneuver. A central feature of the project was the inclusion of an enhanced version of the Pilot-Rotorcraft Intelligent Symbology Management Simulator (PRISMS), a virtual-reality system developed by Anacapa Sciences and Thought Wave. A task analysis was performed to identify the procedural steps in the autorotation, to inventory the information needed to support student task performance, to identify typical errors, and to structure the simulator's practice environment. The system provides immediate knowledge of results, extensive practice of perceptual-motor skills, part-task training, and augmented cueing in a realistic cockpit environment. Additional work, described in this report, extended the capabilities of the simulator in three areas: 1. Incorporation of visual training aids to assist the student in learning the proper appearance of the visual scene when the maneuver is being properly performed; 2. Introduction of the requirement to land at a particular spot, as opposed to the wide, flat open field initially used, and development of appropriate metrics of success; and 3. Inclusion of wind speed and wind direction settings (and random variability settings) to add a more realistic challenge in "hitting the spot."

STS-111 Flight Day 7 Highlights

NASA Technical Reports Server (NTRS)

2002-01-01

On Flight Day 7 of STS-111 (Space Shuttle Endeavour crew includes: Kenneth Cockrell, Commander; Paul Lockhart, Pilot; Franklin Chang-Diaz, Mission Specialist; Philippe Perrin, Mission Specialist; International Space Station (ISS) Expedition 5 crew includes Valery Korzun, Commander; Peggy Whitson, Flight Engineer; Sergei Treschev, Flight Engineer; ISS Expedition 4 crew includes: Yury Onufrienko, Commander; Daniel Bursch, Flight Engineer; Carl Walz, Flight Engineer), this video opens with answers to questions asked by the public via e-mail about the altitude of the space station, the length of its orbit, how astronauts differentiate between up and down in the microgravity environment, and whether they hear wind noise during the shuttle's reentry. In video footage shot from inside the Quest airlock, Perrin is shown exiting the station to perform an extravehicular activity (EVA) with Chang-Diaz. Chang-Diaz is shown, in helmet mounted camera footage, attaching cable protection booties to a fish-stringer device with multiple hooks, and Perrin is seen loosening bolts that hold the replacement unit accomodation in launch position atop the Mobile Base System (MBS). Perrin then mounts a camera atop the mast of the MBS. During this EVA, the astronauts installed the MBS on the Mobile Transporter (MT) to support the Canadarm 2 robotic arm. A camera in the Endeavour's payload bay provides footage of the Pacific Ocean, the Baja Peninsula, and Midwestern United States. Plumes from wildfires in Nevada, Idaho, Yellowstone National Park, Wyoming, and Montana are visible. The station continues over the Great Lakes and the Eastern Provinces of Canada.

STS-111 Flight Day 7 Highlights

NASA Astrophysics Data System (ADS)

2002-06-01

On Flight Day 7 of STS-111 (Space Shuttle Endeavour crew includes: Kenneth Cockrell, Commander; Paul Lockhart, Pilot; Franklin Chang-Diaz, Mission Specialist; Philippe Perrin, Mission Specialist; International Space Station (ISS) Expedition 5 crew includes Valery Korzun, Commander; Peggy Whitson, Flight Engineer; Sergei Treschev, Flight Engineer; ISS Expedition 4 crew includes: Yury Onufrienko, Commander; Daniel Bursch, Flight Engineer; Carl Walz, Flight Engineer), this video opens with answers to questions asked by the public via e-mail about the altitude of the space station, the length of its orbit, how astronauts differentiate between up and down in the microgravity environment, and whether they hear wind noise during the shuttle's reentry. In video footage shot from inside the Quest airlock, Perrin is shown exiting the station to perform an extravehicular activity (EVA) with Chang-Diaz. Chang-Diaz is shown, in helmet mounted camera footage, attaching cable protection booties to a fish-stringer device with multiple hooks, and Perrin is seen loosening bolts that hold the replacement unit accomodation in launch position atop the Mobile Base System (MBS). Perrin then mounts a camera atop the mast of the MBS. During this EVA, the astronauts installed the MBS on the Mobile Transporter (MT) to support the Canadarm 2 robotic arm. A camera in the Endeavour's payload bay provides footage of the Pacific Ocean, the Baja Peninsula, and Midwestern United States. Plumes from wildfires in Nevada, Idaho, Yellowstone National Park, Wyoming, and Montana are visible. The station continues over the Great Lakes and the Eastern Provinces of Canada.

Combining engineered cell-sensors with multi-agent systems to realize smart environment

NASA Astrophysics Data System (ADS)

Chen, Mei

2013-03-01

The connection of everything in a sensory and an intelligent way is a pursuit in smart environment. This paper introduces the engineered cell-sensors into the multi-agent systems to realize the smart environment. The seamless interface with the natural environment and strong information-processing ability of cell with the achievements of synthetic biology make the construction of engineered cell-sensors possible. However, the engineered cell-sensors are only simple-functional and unreliable computational entities. Therefore how to combine engineered cell-sensors with digital device is a key problem in order to realize the smart environment. We give the abstract structure and interaction modes of the engineered cell-sensors in order to introduce engineered cell-sensors into multi-agent systems. We believe that the introduction of engineered cell-sensors will push forward the development of the smart environment.

78 FR 46932 - Notice of Intent to Grant Exclusive Patent License; Safe Environment Engineering

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-02

...; Safe Environment Engineering AGENCY: Department of the Navy, DoD. ACTION: Notice. SUMMARY: The Department of the Navy hereby gives notice of its intent to grant to Safe Environment Engineering a revocable, nonassignable, exclusive license to practice Safe Environment Engineering's proprietary sensor systems for the...

Computer simulation of a single pilot flying a modern high-performance helicopter

NASA Technical Reports Server (NTRS)

Zipf, Mark E.; Vogt, William G.; Mickle, Marlin H.; Hoelzeman, Ronald G.; Kai, Fei; Mihaloew, James R.

1988-01-01

Presented is a computer simulation of a human response pilot model able to execute operational flight maneuvers and vehicle stabilization of a modern high-performance helicopter. Low-order, single-variable, human response mechanisms, integrated to form a multivariable pilot structure, provide a comprehensive operational control over the vehicle. Evaluations of the integrated pilot were performed by direct insertion into a nonlinear, total-force simulation environment provided by NASA Lewis. Comparisons between the integrated pilot structure and single-variable pilot mechanisms are presented. Static and dynamically alterable configurations of the pilot structure are introduced to simulate pilot activities during vehicle maneuvers. These configurations, in conjunction with higher level, decision-making processes, are considered for use where guidance and navigational procedures, operational mode transfers, and resource sharing are required.

Dryden Test Pilots 1990 - Smolka, Fullerton, Schneider, Dana, Ishmael, Smith, and McMurtry

NASA Technical Reports Server (NTRS)

1990-01-01

It was a windy afternoon on Rogers Dry Lake as the research pilots of the National Aeronautics and Space Administration's Ames-Dryden Flight Research Facility gathered for a photo shoot. It was a special day too, the 30th anniversary of the first F-104 flight by research pilot Bill Dana. To celebrate, a fly over of Building 4800, in formation, was made with Bill in a Lockheed F-104 (826), Gordon Fullerton in a Northrop T-38, and Jim Smolka in a McDonnell Douglas F/A-18 (841) on March 23, 1990. The F-18 (841), standing on the NASA ramp is a backdrop for the photo of (Left to Right) James W. (Smoke) Smolka, C. Gordon Fullerton, Edward T. (Ed) Schneider, William H. (Bill) Dana, Stephen D. (Steve) Ishmael, Rogers E. Smith, and Thomas C. (Tom) McMurtry. Smolka joined NASA Ames-Dryden Flight Research Facility in September 1985. He has been the project pilot on the F-15 Advanced Control Technology for Integrated Vehicles (ACTIVE) research and F-15 Aeronautical Research Aircraft programs. He has also flown as a pilot on the NASA B-52 launch aircraft, as a co-project pilot on the F-16XL Supersonic Laminar Flow Control aircraft and the F-18 High Angle-of-Attack Research Vehicle (HARV) aircraft. Other aircraft he has flown in research programs are the F-16, F-111, F-104 and the T-38 as support. Fullerton, joined NASA's Ames-Dryden Flight Research Facility in November 1986. He was project pilot on the NASA/Convair 990 aircraft to test space shuttle landing gear components, project pilot on the F-18 Systems Research Aircraft, and project pilot on the B-52 launch aircraft, where he was involved in six air launches of the commercially developed Pegasus space launch vehicle. Other assignments include a variety of flight research and support activities in multi-engine and high performance aircraft such as, F-15, F-111, F-14, X-29, MD-11 and DC-8. 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), project pilot for the F-15 aeronautical research aircraft, the NASA B-52 launch aircraft, and the SR-71 'Blackbird' aircraft. His past research work at Dryden has included participation in the F-8 Digital Fly-By-Wire, the FAA/NASA 720 Controlled Impact Demonstration, the F-14 Automatic Rudder Interconnect and Laminar Flow programs, and the F-104 Aeronautical Research and Microgravity programs. Dana joined the NASA's High-Speed Flight Station on October 1, 1958. As a research pilot, he was involved in some of the most significant aeronautical programs carried out at the Center. In the late 1960s and in the 1970s Dana was a project pilot on the lifting body program, flying the wingless M2-F1, HL-10, M2-F3, and the X-24B vehicles. He was a project pilot on the hypersonic X-15 research aircraft and flew the rocket-powered vehicle 16 times, reaching a speed of 3,897 mph and an altitude of 310,000 feet. Bill was the pilot on the final (199th) flight of the 10-year program. Other research and support programs Dana participated in were the F-15 Highly Integrated Digital Electronic Control (HIDEC), the F-18 High Angle-of-Attack Research Vehicle (HARV), YF-12, F-104, F-16, PA-30, and T-38. In 1993 Dana became Chief Engineer at NASA's Ames-Dryden Flight Research Facility (soon to be renamed the Dryden Flight Research Center). Ishmael was a research pilot at NASA's Dryden Flight Research Center from January 1977 until the spring of 1995, when he became manager of Dryden's Reusable Launch Vehicle (RLV) programs. In 1996 he became NASA's X-33 Deputy Manager for Flight Test and Operation. As a research pilot he served as the chief project pilot on two major aeronautical research programs, the SR-71 High Speed Research program and the F-16XL Laminar Flow Technology program. He took part in the X-29 Forward-Swept-Wing program, and gave support to other pilots' research flights in a T-38 and F-104 aircraft. Smith became a research pilot at NASA's Ames-Dryden Flight Research Facility in August 1982. In the spring of 1995 he became Chief of the Flight Crew Branch where currently there are 8 other NASA pilots and 2 flight engineers. Smith has also been a co-project pilot on two major aeronautical programs at Dryden. They are the integrated thrust vectoring F-15 ACTIVE and the SR-71 'Blackbird' Research programs. Other research programs that he has been associated with are the F-104 Zero 'G' tests, F-18 HARV, X-29 Forward-Swept-Wing, with support flights being flown in a T-38 and F-104. McMurtry has been a pilot at NASA's Dryden since joining the Flight Research Center in November 1967. In 1981, Tom became Chief Pilot a position he held until February 1986, when he was appointed Chief of the Research Aircraft Operations Division. McMurtry has been project pilot for the AD-1 Oblique Wing program, the F-15 Digital Electronic Engine Control (DEEC) project and the F-8 Supercritical Wing program. He was co- project pilot on the F-15 ACTIVE program, F-8 Digital Fly-By-Wire program and on several remotely piloted research vehicle programs such as the FAA/NASA 720 Controlled Impact Demonstration and the sub-scale F-15 spin research project. He has also been a co-project pilot on the NASA 747 Shuttle Carrier Aircraft.

A spin-recovery parachute system for light general-aviation airplanes

NASA Technical Reports Server (NTRS)

Bradshaw, C.

1980-01-01

A tail mounted spin recovery parachute system was designed and developed for use on light general aviation airplanes. The system was designed for use on typical airplane configurations, including low wing, high wing, single engine and twin engine designs. A mechanically triggered pyrotechnic slug gun is used to forcibly deploy a pilot parachute which extracts a bag that deploys a ring slot spin recovery parachute. The total system weighs 8.2 kg. System design factors included airplane wake effects on parachute deployment, prevention of premature parachute deployment, positive parachute jettison, compact size, low weight, system reliability, and pilot and ground crew safety. Extensive ground tests were conducted to qualify the system. The recovery parachute was used successfully in flight 17 times.

Separation and Conditioning of Mars Atmospheric Gases via TSA

NASA Technical Reports Server (NTRS)

Finn, John E.; Luna, Bernadette (Technical Monitor)

2000-01-01

Space and planetary exploration almost always presents interesting and unusual engineering challenges. Separations engineering for chemical processes that are critical to humans working in space is no exception. The challenges are becoming clearer as we make the transition from concepts and planning to hardware development, and as we understand better the constraints and environments in which the processes must perform. The coming decade will see a robotic Mars exploration program that has recovered from recent setbacks and is building a knowledge and technology base for human exploration. One of the missions will carry a small chemical pilot plant for demonstrating the manufacture of rocket propellants and life support consumables from the low-pressure (0.01 atm) Martian atmosphere. By manufacturing and storing the fuel and consumables needed for human-return missions in situ, launch mass and landed mass are reduced by tons and missions become far less expensive. The front-end to the pilot plant is a solid-state atmosphere acquisition and separation unit based on temperature-swing adsorption (TSA). The unit produces purified and pressurized (to 1.0 atm) carbon dioxide to downstream reactors that will make methane and oxygen. The unit also produces a nitrogen-argon mixture as a valuable by-product for life support, inflatable structures, and propellant pressurization. With nighttime temperatures falling to -100 degrees C, power availability restricted to a few watts, and flawless operation critical to success, the dusty Martian surface is a difficult place to operate a remote plant. This talk will focus on how this TSA separation process is designed and implemented for this application, and how it might be used in the more distant future for human exploration.

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

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

Navigation experience and mental representations of the environment: do pilots build better cognitive maps?

PubMed

Sutton, Jennifer E; Buset, Melanie; Keller, Mikayla

2014-01-01

A number of careers involve tasks that place demands on spatial cognition, but it is still unclear how and whether skills acquired in such applied experiences transfer to other spatial tasks. The current study investigated the association between pilot training and the ability to form a mental survey representation, or cognitive map, of a novel, ground-based, virtual environment. Undergraduate students who were engaged in general aviation pilot training and controls matched to the pilots on gender and video game usage freely explored a virtual town. Subsequently, participants performed a direction estimation task that tested the accuracy of their cognitive map representation of the town. In addition, participants completed the Object Perspective Test and rated their spatial abilities. Pilots were significantly more accurate than controls at estimating directions but did not differ from controls on the Object Perspective Test. Locations in the town were visited at a similar rate by the two groups, indicating that controls' relatively lower accuracy was not due to failure to fully explore the town. Pilots' superior performance is likely due to better online cognitive processing during exploration, suggesting the spatial updating they engage in during flight transfers to a non-aviation context.

Navigation Experience and Mental Representations of the Environment: Do Pilots Build Better Cognitive Maps?

PubMed Central

Sutton, Jennifer E.; Buset, Melanie; Keller, Mikayla

2014-01-01

A number of careers involve tasks that place demands on spatial cognition, but it is still unclear how and whether skills acquired in such applied experiences transfer to other spatial tasks. The current study investigated the association between pilot training and the ability to form a mental survey representation, or cognitive map, of a novel, ground-based, virtual environment. Undergraduate students who were engaged in general aviation pilot training and controls matched to the pilots on gender and video game usage freely explored a virtual town. Subsequently, participants performed a direction estimation task that tested the accuracy of their cognitive map representation of the town. In addition, participants completed the Object Perspective Test and rated their spatial abilities. Pilots were significantly more accurate than controls at estimating directions but did not differ from controls on the Object Perspective Test. Locations in the town were visited at a similar rate by the two groups, indicating that controls' relatively lower accuracy was not due to failure to fully explore the town. Pilots' superior performance is likely due to better online cognitive processing during exploration, suggesting the spatial updating they engage in during flight transfers to a non-aviation context. PMID:24603608

Flight investigation of cockpit-displayed traffic information utilizing coded symbology in an advanced operational environment

NASA Technical Reports Server (NTRS)

Abbott, T. S.; Moen, G. C.; Person, L. H., Jr.; Keyser, G. L., Jr.; Yenni, K. R.; Garren, J. F., Jr.

1980-01-01

Traffic symbology was encoded to provide additional information concerning the traffic, which was displayed on the pilot's electronic horizontal situation indicators (EHSI). A research airplane representing an advanced operational environment was used to assess the benefit of coded traffic symbology in a realistic work-load environment. Traffic scenarios, involving both conflict-free and conflict situations, were employed. Subjective pilot commentary was obtained through the use of a questionnaire and extensive pilot debriefings. These results grouped conveniently under two categories: display factors and task performance. A major item under the display factor category was the problem of display clutter. The primary contributors to clutter were the use of large map-scale factors, the use of traffic data blocks, and the presentation of more than a few airplanes. In terms of task performance, the cockpit-displayed traffic information was found to provide excellent overall situation awareness. Additionally, mile separation prescribed during these tests.

A Distributed Simulation Facility to Support Human Factors Research in Advanced Air Transportation Technology

NASA Technical Reports Server (NTRS)

Amonlirdviman, Keith; Farley, Todd C.; Hansman, R. John, Jr.; Ladik, John F.; Sherer, Dana Z.

1998-01-01

A distributed real-time simulation of the civil air traffic environment developed to support human factors research in advanced air transportation technology is presented. The distributed environment is based on a custom simulation architecture designed for simplicity and flexibility in human experiments. Standard Internet protocols are used to create the distributed environment, linking all advanced cockpit simulator, all Air Traffic Control simulator, and a pseudo-aircraft control and simulation management station. The pseudo-aircraft control station also functions as a scenario design tool for coordinating human factors experiments. This station incorporates a pseudo-pilot interface designed to reduce workload for human operators piloting multiple aircraft simultaneously in real time. The application of this distributed simulation facility to support a study of the effect of shared information (via air-ground datalink) on pilot/controller shared situation awareness and re-route negotiation is also presented.

Alternative Perspectives on Risk: Individual Differences in Problem Structuring

NASA Technical Reports Server (NTRS)

Orasanu, Judith; Fischer, Ute; Connors, Mary M. (Technical Monitor)

1997-01-01

Team decision making involves contributions of multiple players toward a common goal. While much has been written about the importance of developing shared mental models in order for teams to work together effectively, little has been done to determine the value of alternative perspectives on problem solving and decision making. Early studies of expertise contrasted experts with novices and noted that the two groups differ in the way they structure problems and in their selection of information as salient. Little attention has been given to differences among experts who differ in their specializations. A series of experiments was conducted to determine: (1) what dimensions of flight-related problem situations pilots judge to be most important when making flight-relevant decisions; and (2) whether pilots in different crew positions differ in the way they interpret problems relating to flight decisions. A sorting task was used to identify underlying dimensions judged as salient to individual pilots. Captains, first officers, and flight engineers from two major carriers participated in the study. Twenty-two flight scenarios were developed based on ASRS reports. Pilots were required to make judgments about how they would respond in each case and to sort the scenarios on the basis of similarity of decision factors. They were also asked to provide a verbal label that described each of their sorted categories. A second study required a different group of pilots (also captains, first officers and flight engineers) to sort on predetermined bases.

System Engineering Issues for Avionics Survival in the Space Environment

NASA Technical Reports Server (NTRS)

Pavelitz, Steven

1999-01-01

This paper examines how the system engineering process influences the design of a spacecraft's avionics by considering the space environment. Avionics are susceptible to the thermal, radiation, plasma, and meteoroids/orbital debris environments. The environment definitions for various spacecraft mission orbits (LEO/low inclination, LEO/Polar, MEO, HEO, GTO, GEO and High ApogeeElliptical) are discussed. NASA models and commercial software used for environment analysis are reviewed. Applicability of technical references, such as NASA TM-4527 "Natural Orbital Environment Guidelines for Use in Aerospace Vehicle Development" is discussed. System engineering references, such as the MSFC System Engineering Handbook, are reviewed to determine how the environments are accounted for in the system engineering process. Tools and databases to assist the system engineer and avionics designer in addressing space environment effects on avionics are described and usefulness assessed.

Installation Restoration Program Records Search for Bergstrom Air Force Base, Texas.

DTIC Science & Technology

1983-07-01

August 1981. "Pilot Plant Study of Copper , Zinc, and Trivalent Chromium Removal by Adsorbing Colloid Foam Flotation ." M.S. Thesis, Vanderbilt...graduate school and one of his activities included researching the removal of heavy metals, including copper , zinc and trivalent chromium, using a large...scale adsorbing colloid foam flotation pilot plant. Professional Registration Engineer-In-Training, Florida % -7. GREGORY T. MCINTYRE Membership in

KSC-2014-1421

NASA Image and Video Library

2014-01-06

HOUSTON – Engineers for Boeing Space Exploration demonstrate that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford

KSC-2014-1417

NASA Image and Video Library

2014-01-06

HOUSTON – Engineers for Boeing Space Exploration demonstrate that the CST-100 software allows a human pilot to take over control of the spacecraft from the computer during all phases of a mission following separation from the launch vehicle. The pilot-in-the-loop demonstration at the Houston Product Support Center is a milestone under Boeing's Commercial Crew Integrated Capability agreement with the agency and its Commercial Crew Program. Photo credit: NASA/Bill Stafford

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CP640) LOOKING NORTHWEST ...

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

CONSTRUCTION PROGRESS PHOTO OF HOT PILOT PLANT (CP-640) LOOKING NORTHWEST SHOWING FORMING AND PLACEMENT OF REINFORCING STEEL FOR SOUTH WALLS OF CELLS 1, 3, 4 AND 5 AND WEST WALL FOR CELLS 1 AND 2; CONSTRUCTION 13 PERCENT COMPLETE. INL PHOTO NUMBER NRTS 59-6436. J. Anderson, Photographer, 12/18/1959 - Idaho National Engineering Laboratory, Idaho Chemical Processing Plant, Fuel Reprocessing Complex, Scoville, Butte County, ID

Pseudosatellite technologies based on the use of functionally stable complexes of remote-piloted aircrafts

NASA Astrophysics Data System (ADS)

Mashkov, O. A.; Samborskiy, I. I.

2009-10-01

A bundle of papers dealing with functionally stable systems requires the necessity of analyzing of obtained results and their understanding in a general context of cybernetic's development and applications. Description of this field of science, main results and perspectives of the new theory of functionally stability of dynamical systems concerning the problem of remote-piloted aircrafts engineering using pseudosatellite technologies are proposed in the paper.

U.S. Unmanned Aerial Systems

DTIC Science & Technology

2012-01-03

that time, they have been called drones, robot planes, pilotless aircraft, RPVs (remotely piloted vehicles), RPAs (remotely piloted aircraft) and...Paul Jackson, p. 728. OSD. UAS Roadmap 2005-2030. August, 2005, Section 2, p.10. 82 National Journal’s Congress Daily. “ Pilotless Aircraft Makers Seek...Eye Proposed by the Boeing Phantom Works, Phantom Eye would use hydrogen-fueled automobile engines to carry a 3,000-pound payload for ten days.195 A

Global environment facility: Independent evaluation of the pilot phase; Fonds pour l`environnement mondial: evaluation independante de la phase pilote

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

NONE

1994-12-31

This study responds to a request by participants in the Global Environment Facility (GEF) for an independent evaluation of the pilot phase. It profiles the GEF, discusses its policy framework, and reviews project development procedures and the strategies and projects in each of the GEF`s four focal areas. The study concludes that fundamental changes must occur and recommends specific reforms, such as articulating more clearly the GEF`s mandate, objectives, and strategies; addressing deficiencies in meeting its global focus; improving capacities and procedures within implementing agencies for managing the portfolio; and increasing non-government organization (NGO), country and community-level participation.

Physiological training courses for civil aviation pilots.

DOT National Transportation Integrated Search

2003-12-03

Pilots who are knowledge able about physiological phenomena encountered in the aviation environment are better prepared to deal with such potentially fatal in flight events. The FAA Civil Aerospace Medical Institute offers a 1-day training course to ...

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.

Real-time piloted simulation of fully automatic guidance and control for rotorcraft nap-of-the-earth (NOE) flight following planned profiles

NASA Technical Reports Server (NTRS)

Clement, Warren F.; Gorder, Pater J.; Jewell, Wayne F.; Coppenbarger, Richard

1990-01-01

Developing a single-pilot all-weather NOE capability requires fully automatic NOE navigation and flight control. Innovative guidance and control concepts are being investigated to (1) organize the onboard computer-based storage and real-time updating of NOE terrain profiles and obstacles; (2) define a class of automatic anticipative pursuit guidance algorithms to follow the vertical, lateral, and longitudinal guidance commands; (3) automate a decision-making process for unexpected obstacle avoidance; and (4) provide several rapid response maneuvers. Acquired knowledge from the sensed environment is correlated with the recorded environment which is then used to determine an appropriate evasive maneuver if a nonconformity is observed. This research effort has been evaluated in both fixed-base and moving-base real-time piloted simulations thereby evaluating pilot acceptance of the automated concepts, supervisory override, manual operation, and reengagement of the automatic system.

Piloted Ignition to Flaming in Smoldering Fire-Retarded Polyurethane Foam

NASA Technical Reports Server (NTRS)

Putzeys, O.; Fernandez-Pello, A. C.; Urban, D. L.

2007-01-01

Experimental results are presented on the piloted transition from smoldering to flaming in the fire-retarded polyurethane foam Pyrell . The samples are small rectangular blocks with a square cross section, vertically placed in the wall of a vertical wind tunnel. Three of the vertical sample sides are insulated and the fourth side is exposed to an upward oxidizer flow of variable oxygen concentration and to a variable radiant heat flux. The gases emitted from the smoldering reaction pass upwards through a pilot, which consists of a coiled resistance heating wire. In order to compensate for the solid-phase and gas-phase effects of the fire retardants on the piloted transition from smoldering to flaming in Pyrell, it was necessary to assist the process by increasing the power supplied to the smolder igniter and the pilot (compared to that used for non-fire retarded foam). The experiments indicate that the piloted transition from smoldering to flaming occurs when the gaseous mixture at the pilot passes the lean flammability limit. It was found that increasing the oxygen concentration or the external heat flux increases the likelihood of a piloted transition from smoldering to flaming, and generally decreases the time delay to transition. The piloted transition to flaming is observed in oxygen concentrations of 23% and above in both low-density and high-density Pyrell. Comparisons with previous experiments show that the piloted transition from smoldering to flaming is possible under a wider range of external conditions (i.e. lower oxygen concentration) than the spontaneous transition from smoldering to flaming. The results show that the fire retardants in Pyrell are very effective in preventing the piloted transition to flaming in normal air, but Pyrell is susceptible to smoldering and the piloted transition to flaming in oxygen-enriched environments. Therefore, precautions should be taken in the design of applications of Pyrell in oxygen-enriched environments to reduce to the risk of a piloted transition to flaming.

Similarities and Differences in the Academic Education of Software Engineering and Architectural Design Professionals

ERIC Educational Resources Information Center

Hazzan, Orit; Karni, Eyal

2006-01-01

This article focuses on the similarities and differences in the academic education of software engineers and architects. The rationale for this work stems from our observation, each from the perspective of her or his own discipline, that these two professional design and development processes share some similarities. A pilot study was performed,…

E-Readers on Trial: Qualitative Results from an Academic Library Pilot Project

ERIC Educational Resources Information Center

Kemp, Jan; Lutz, Ellen; Nurnberger, Amy L.

2012-01-01

In 2010, the University of Texas at San Antonio Libraries opened a bookless satellite library, the Applied Engineering and Technology (AET) Library. AET librarians wanted to offer a new service: lending e-readers loaded with academic content and other e-books of interest to engineering and science students. Librarians chose three e-readers for the…

The Transformative Potential of Engaging in Science Inquiry-Based Challenges: The ATSE Wonder of Science Challenge

ERIC Educational Resources Information Center

Tomas, Louisa; Jackson, Cliff; Carlisle, Karen

2014-01-01

In 2012, the Australian Academy of Technological Sciences and Engineering (ATSE) piloted the "Wonder of Science Challenge" with a view to enhance school students' interest in Science, Technology, Engineering and Mathematics (STEM). Students in 15 schools across northern Queensland were provided with an inquiry-based research problem and…

Analytical display design for flight tasks conducted under instrument meteorological conditions. [human factors engineering of pilot performance for display device design in instrument landing systems

NASA Technical Reports Server (NTRS)

Hess, R. A.

1976-01-01

Paramount to proper utilization of electronic displays is a method for determining pilot-centered display requirements. Display design should be viewed fundamentally as a guidance and control problem which has interactions with the designer's knowledge of human psychomotor activity. From this standpoint, reliable analytical models of human pilots as information processors and controllers can provide valuable insight into the display design process. A relatively straightforward, nearly algorithmic procedure for deriving model-based, pilot-centered display requirements was developed and is presented. The optimal or control theoretic pilot model serves as the backbone of the design methodology, which is specifically directed toward the synthesis of head-down, electronic, cockpit display formats. Some novel applications of the optimal pilot model are discussed. An analytical design example is offered which defines a format for the electronic display to be used in a UH-1H helicopter in a landing approach task involving longitudinal and lateral degrees of freedom.

An investigation into the vertical axis control power requirements for landing VTOL type aircraft onboard nonaviation ships in various sea states

NASA Technical Reports Server (NTRS)

Stevens, M. E.; Roskam, J.

1985-01-01

The problem of determining the vertical axis control requirements for landing a VTOL aircraft on a moving ship deck in various sea states is examined. Both a fixed-base piloted simulation and a nonpiloted simulation were used to determine the landing performance as influenced by thrust-to-weight ratio, vertical damping, and engine lags. The piloted simulation was run using a fixed-based simulator at Ames Research center. Simplified versions of an existing AV-8A Harrier model and an existing head-up display format were used. The ship model used was that of a DD963 class destroyer. Simplified linear models of the pilot, aircraft, ship motion, and ship air-wake turbulence were developed for the nonpiloted simulation. A unique aspect of the nonpiloted simulation was the development of a model of the piloting strategy used for shipboard landing. This model was refined during the piloted simulation until it provided a reasonably good representation of observed pilot behavior.

[Personnel with poor vision at fighter pilot school].

PubMed

Corbé, C; Menu, J P

1997-10-01

The piloting of fighting aircraft, the navigation of space-shuttle, the piloting of an helicopter in tactical flight at an altitude of 50 metres require the use of all sensorial, ocular, vestibular, proprioceptive ... sensors. So, the selection and the follow-up of these aerial engines' pilots need a very complete study of medical parameters, in particular sensorial and notably visual system. The doctors and the expert researchers in Aeronautical and spatial Medicine of the Army Health Department, which have in charge the medical supervision of flight crew, should study, create, and improve tests of visual sensorial exploration developed from fundamental and applied research. These authenticated tests with military pilots were applied in ophthalmology for the estimation of normal and deficient vision. A proposition to change norms of World Health Organisation applied to the vision has been following these to low visual persons was equally introduced.

Use of Traffic Displays for General Aviation Approach Spacing: A Human Factors Study

DTIC Science & Technology

2007-12-01

engine rated pilots participated. Eight flew approaches in a twin-engine Piper Aztec originating in Sanford, ME, and eight flew approaches in the same...flew approaches in a twin-engine Piper Aztec originating in Sanford, ME, and eight flew approaches in the same aircraft originating in Atlantic City... Aztec . The plane was equipped with a horizontal Situation Indicator (hSI). The Garmin International MX-20™ multifunction traffic display or “Basic

European Hands-on Universe

NASA Astrophysics Data System (ADS)

Doran, Rosa; Ferlet, Roger; Gómez de Castro, Ana I.; Hill, Robert; Horellou, Cathy; Mankiewicz, Lech; Melchior, Anne-Laure; Metaxa, Margarita; Zanazzi, Alessandra

2007-08-01

Hands-on Universe is a project born at UC@Berkeley. A project devoted to enrich the teaching of Astronomy within the classroom environment with a different approach, more connected to the new technologies. Its main goals are not only to promote the use of such technologies but also to reawaken on students the taste for STEM (Science, technologies, engineering and math) related issues and also to increase their scientific culture. Eight countries in Europe decided to adopt the method and, funded by MINERVA, formed the European Hands-on Universe. Several resources were produced and a data reduction software developed http://www.euhou.net/.Other European countries are interested and should join this coordinated effort in the near future. At an international level there are 20 countries using this approach. There are plans to develop scientific cooperation among these countries. Pilot scientific research projects in schools are being tested in EU-HOU schools, Russia and USA. There is also a game being developed to be used as a new tool for teaching scientific content in the classroom environment. An effort to develop an international network of scientific / educational collaboration is the next step.

Linear Aerospike SR-71 Experiment (LASRE): Aerospace Propulsion Hazard Mitigation Systems

NASA Technical Reports Server (NTRS)

Mizukami, Masashi; Corpening, Griffin P.; Ray, Ronald J.; Hass, Neal; Ennix, Kimberly A.; Lazaroff, Scott M.

1998-01-01

A major hazard posed by the propulsion system of hypersonic and space vehicles is the possibility of fire or explosion in the vehicle environment. The hazard is mitigated by minimizing or detecting, in the vehicle environment, the three ingredients essential to producing fire: fuel, oxidizer, and an ignition source. The Linear Aerospike SR-71 Experiment (LASRE) consisted of a linear aerospike rocket engine integrated into one-half of an X-33-like lifting body shape, carried on top of an SR-71 aircraft. Gaseous hydrogen and liquid oxygen were used as propellants. Although LASRE is a one-of-a-kind experimental system, it must be rated for piloted flight, so this test presented a unique challenge. To help meet safety requirements, the following propulsion hazard mitigation systems were incorporated into the experiment: pod inert purge, oxygen sensors, a hydrogen leak detection algorithm, hydrogen sensors, fire detection and pod temperature thermocouples, water misting, and control room displays. These systems are described, and their development discussed. Analyses, ground test, and flight test results are presented, as are findings and lessons learned.

Respiratory Illness and Allergy Related to Work and Home Environment among Commercial Pilots.

PubMed

Fu, Xi; Lindgren, Torsten; Wieslander, Gunilla; Janson, Christer; Norbäck, Dan

2016-01-01

The aim was to study associations between work and home environment and prevalence and incidence of respiratory health and a history of atopy in a 3-y cohort of commercial pilots. A questionnaire was mailed in 1997 to all pilots in a Scandinavian airline company (N = 622); 577 (93%) participated. The same questionnaire was sent to the participants 3 years later, 436 participated (76%). There were questions on asthma, respiratory symptoms and infections, allergies, the cabin environment, psychosocial environment and the home environment. Associations were analyzed by multiple logistic regression, calculating odds ratios (OR) with 95% confidence intervals (95%CI). The incidence of doctors' diagnosed asthma and atopy were 2.4 and 16.6 per 1000 person years, respectively. Pilots changing type of flight during follow-up got more airway infections (OR = 11.27; 95% CI 2.39-53.14). Those reporting decreased work control (OR = 1.85; 95% CI 1.03-3.31 for 1 unit change) and those with environmental tobacco smoke (ETS) at home (OR = 3.73; 95% CI 1.09-12.83) had a higher incidence of atopy during follow up. Dampness or mould at home was associated with a higher prevalence of asthma symptoms (OR = 3.55; 95% CI 1.43-8.82) and airway infections (OR = 3.12 95% CI 1.27-7.68). Window pane condensation in winter at home, reported at baseline, was associated with increased incidence of asthma symptoms (OR = 4.14; 95% CI 1.32-12.97) and pilots living in newer buildings at baseline had a higher incidence of airway infections (OR = 5.23; 95% CI 1.43-19.10). In conclusion, lack of work control and ETS at home can be a risk factors for development of allergic symptoms in pilots. Window pane condensation at home can be a risk factor for incidence of asthma symptoms. Dampness and mould at home can be a risk factor for prevalence of asthma symptoms and airway infections and living in newer buildings can be a risk factor for incidence of airway infections.

Respiratory Illness and Allergy Related to Work and Home Environment among Commercial Pilots

PubMed Central

Fu, Xi; Lindgren, Torsten; Wieslander, Gunilla; Janson, Christer; Norbäck, Dan

2016-01-01

The aim was to study associations between work and home environment and prevalence and incidence of respiratory health and a history of atopy in a 3-y cohort of commercial pilots. A questionnaire was mailed in 1997 to all pilots in a Scandinavian airline company (N = 622); 577 (93%) participated. The same questionnaire was sent to the participants 3 years later, 436 participated (76%). There were questions on asthma, respiratory symptoms and infections, allergies, the cabin environment, psychosocial environment and the home environment. Associations were analyzed by multiple logistic regression, calculating odds ratios (OR) with 95% confidence intervals (95%CI). The incidence of doctors’ diagnosed asthma and atopy were 2.4 and 16.6 per 1000 person years, respectively. Pilots changing type of flight during follow-up got more airway infections (OR = 11.27; 95% CI 2.39–53.14). Those reporting decreased work control (OR = 1.85; 95% CI 1.03–3.31 for 1 unit change) and those with environmental tobacco smoke (ETS) at home (OR = 3.73; 95% CI 1.09–12.83) had a higher incidence of atopy during follow up. Dampness or mould at home was associated with a higher prevalence of asthma symptoms (OR = 3.55; 95% CI 1.43–8.82) and airway infections (OR = 3.12 95% CI 1.27–7.68). Window pane condensation in winter at home, reported at baseline, was associated with increased incidence of asthma symptoms (OR = 4.14; 95% CI 1.32–12.97) and pilots living in newer buildings at baseline had a higher incidence of airway infections (OR = 5.23; 95% CI 1.43–19.10). In conclusion, lack of work control and ETS at home can be a risk factors for development of allergic symptoms in pilots. Window pane condensation at home can be a risk factor for incidence of asthma symptoms. Dampness and mould at home can be a risk factor for prevalence of asthma symptoms and airway infections and living in newer buildings can be a risk factor for incidence of airway infections. PMID:27741314

Propagation effects for land mobile satellite systems: Overview of experimental and modeling results

NASA Technical Reports Server (NTRS)

Goldhirsh, Julius; Vogel, Wolfhard J.

1992-01-01

Models developed and experiments performed to characterize the propagation environment associated with land mobile communication using satellites are discussed. Experiments were carried out with transmitters on stratospheric balloons, remotely piloted aircraft, helicopters, and geostationary satellites. This text is comprised of compiled experimental results for the expressed use of communications engineers, designers of planned Land Mobile Satellite Systems (LMSS), and modelers of propagation effects. The results presented here are mostly derived from systematic studies of propagation effects for LMSS geometries in the United States associated with rural and suburban regions. Where applicable, the authors also draw liberally from the results of other related investigations in Canada, Europe, and Australia. Frequencies near 1500 MHz are emphasized to coincide with frequency bands allocated for LMSS by the International Telecommunication Union, although earlier experimental work at 870 MHz is also included.

gLExec and MyProxy integration in the ATLAS/OSG PanDA workload management system

NASA Astrophysics Data System (ADS)

Caballero, J.; Hover, J.; Litmaath, M.; Maeno, T.; Nilsson, P.; Potekhin, M.; Wenaus, T.; Zhao, X.

2010-04-01

Worker nodes on the grid exhibit great diversity, making it difficult to offer uniform processing resources. A pilot job architecture, which probes the environment on the remote worker node before pulling down a payload job, can help. Pilot jobs become smart wrappers, preparing an appropriate environment for job execution and providing logging and monitoring capabilities. PanDA (Production and Distributed Analysis), an ATLAS and OSG workload management system, follows this design. However, in the simplest (and most efficient) pilot submission approach of identical pilots carrying the same identifying grid proxy, end-user accounting by the site can only be done with application-level information (PanDA maintains its own end-user accounting), and end-user jobs run with the identity and privileges of the proxy carried by the pilots, which may be seen as a security risk. To address these issues, we have enabled PanDA to use gLExec, a tool provided by EGEE which runs payload jobs under an end-user's identity. End-user proxies are pre-staged in a credential caching service, MyProxy, and the information needed by the pilots to access them is stored in the PanDA DB. gLExec then extracts from the user's proxy the proper identity under which to run. We describe the deployment, installation, and configuration of gLExec, and how PanDA components have been augmented to use it. We describe how difficulties were overcome, and how security risks have been mitigated. Results are presented from OSG and EGEE Grid environments performing ATLAS analysis using PanDA and gLExec.

Linear Aerospike SR-71 Experiment (LASRE) dumps water after first in-flight cold flow test

NASA Image and Video Library

1998-03-04

The NASA SR-71A successfully completed its first cold flow flight as part of the NASA/Rocketdyne/Lockheed Martin Linear Aerospike SR-71 Experiment (LASRE) at NASA's Dryden Flight Research Center, Edwards, California on March 4, 1998. During a cold flow flight, gaseous helium and liquid nitrogen are cycled through the linear aerospike engine to check the engine's plumbing system for leaks and to check the engine operating characterisitics. Cold-flow tests must be accomplished successfully before firing the rocket engine experiment in flight. The SR-71 took off at 10:16 a.m. PST. The aircraft flew for one hour and fifty-seven minutes, reaching a maximum speed of Mach 1.58 before landing at Edwards at 12:13 p.m. PST. "I think all in all we had a good mission today," Dryden LASRE Project Manager Dave Lux said. Flight crew member Bob Meyer agreed, saying the crew "thought it was a really good flight." Dryden Research Pilot Ed Schneider piloted the SR-71 during the mission. Lockheed Martin LASRE Project Manager Carl Meade added, "We are extremely pleased with today's results. This will help pave the way for the first in-flight engine data-collection flight of the LASRE."

[Electronic noise compensation for improving speech discrimination in airplane pilots].

PubMed

Matschke, R G; Pösselt, C; Veit, I; Andresen, U

1989-02-01

Noise exposure measurements were performed in pilots of the Federal Navy during realistic flight situations. The ambient noise levels during regular flight service were maintained at levels nearly all the time above 90 dB. To avoid occupational hearing loss, the "Noise Injury Prevention Code" issued by the insurers would demand wearing personal ear protection, e.g. ear plugs. But such equipment in the aircraft cockpit would have precisely the opposite effect, because one of the reasons for possible damage to hearing is radio communication. To be able to understand radio traffic in spite of the noisy environment, headphone volume must be raised above the noise of the engines. The use of ear plugs can be of only limited value. Whereas pilots with normal hearing show only little impairment of speech intelligibility, those with noise-induced hearing loss show substantial impairment that varies in proportion to their hearing loss. Communication abilities may be drastically reduced which may compromise the reliability of radio traffic. Cockpit noise has its maximum intensity around 125 Hz and flight helmets and ear defenders are not very effective in low frequency ranges. Sennheiser electronic KG developed an active noise compensation circuit, which makes use of the "anti noise" principle. Here the outside noises picked up by two microphones integrated into the headset are processed electronically in such a way that they largely neutralise the original noise. It had to be made sure that the radio traffic signal was not also compensated and that the signal to noise ratio was clearly increased.(ABSTRACT TRUNCATED AT 250 WORDS)

Modeling Sources of Teaching Self-Efficacy for Science, Technology, Engineering, and Mathematics Graduate Teaching Assistants.

PubMed

DeChenne, Sue Ellen; Koziol, Natalie; Needham, Mark; Enochs, Larry

2015-01-01

Graduate teaching assistants (GTAs) in science, technology, engineering, and mathematics (STEM) have a large impact on undergraduate instruction but are often poorly prepared to teach. Teaching self-efficacy, an instructor's belief in his or her ability to teach specific student populations a specific subject, is an important predictor of teaching skill and student achievement. A model of sources of teaching self-efficacy is developed from the GTA literature. This model indicates that teaching experience, departmental teaching climate (including peer and supervisor relationships), and GTA professional development (PD) can act as sources of teaching self-efficacy. The model is pilot tested with 128 GTAs from nine different STEM departments at a midsized research university. Structural equation modeling reveals that K-12 teaching experience, hours and perceived quality of GTA PD, and perception of the departmental facilitating environment are significant factors that explain 32% of the variance in the teaching self-efficacy of STEM GTAs. This model highlights the important contributions of the departmental environment and GTA PD in the development of teaching self-efficacy for STEM GTAs. © 2015 S. E. DeChenne et al. CBE—Life Sciences Education © 2015 The American Society for Cell Biology. This article is distributed by The American Society for Cell Biology under license from the author(s). It is available to the public under an Attribution–Noncommercial–Share Alike 3.0 Unported Creative Commons License (http://creativecommons.org/licenses/by-nc-sa/3.0).

An Analysis of En Route Controller-Pilot Voice Communications

DOT National Transportation Integrated Search

1993-03-01

The purposes of this analysis were to examine current pilot-controller communication practices in the en route : environment. Forty-eight hours of voice tapes from eight different Air Route Traffic Control Centers (ARTCCs) were : examined. There were...

The Relationship of a Pilot's Educational Background, Aeronautical Experience and Recency of Experience to Performance In Initial Training at a Regional Airline

NASA Astrophysics Data System (ADS)

Shane, Nancy R.

The purpose of this study was to determine how a pilot's educational background, aeronautical experience and recency of experience relate to their performance during initial training at a regional airline. Results show that variables in pilots' educational background, aeronautical experience and recency of experience do predict performance in training. The most significant predictors include years since graduation from college, multi-engine time, total time and whether or not a pilot had military flying experience. Due to the pilot shortage, the pilots entering regional airline training classes since August 2013 have varied backgrounds, aeronautical experience and recency of experience. As explained by Edward Thorndike's law of exercise and the law of recency, pilots who are actively using their aeronautical knowledge and exercising their flying skills should exhibit strong performance in those areas and pilots who have not been actively using their aeronautical knowledge and exercising their flying skills should exhibit degraded performance in those areas. Through correlation, chi-square and multiple regression analysis, this study tests this theory as it relates to performance in initial training at a regional airline.

Mixed-reality exercise effects on participation of individuals with spinal cord injuries and developmental disabilities: a pilot study.

PubMed

Heyn, Patricia C; Baumgardner, Chad A; McLachlan, Leslie; Bodine, Cathy

2014-01-01

The purpose of this pilot study was to investigate the effectiveness of a mixed-reality (MR) exercise environment on engagement and enjoyment levels of individuals with spinal cord injury (SCI) and intellectual and developmental disabilities (IDD). Six people participated in this cross-sectional, observational pilot study involving one MR exercise trial. The augmented reality environment was based on a first-person perspective video of a scenic biking/walking trail in Colorado. Males and females (mean age, 43.3 ± 13.7 years) were recruited from a research database for their participation in previous clinical studies. Of the 6 participants, 2 had SCI, 2 had IDD, and 2 were without disability. The primary outcome measurement of this pilot study was the self-reported engagement and enjoyment level of each participant after the exercise trial. All participants reported increased levels of engagement, enjoyment, and immersion involving the MR exercise environment as well as positive feedback recommending this type of exercise approach to peers with similar disabilities. All the participants reported higher than normal levels of enjoyment and 66.7% reported higher than normal levels of being on a real trail. Participants' feedback suggested that the MR environment could be entertaining, motivating, and engaging for users with disabilities, resulting in a foundation for further development of this technology for use in individuals with cognitive and physical disabilities.

Creating a school nutrition environment index and pilot testing it in elementary and middle schools in urban South Korea

PubMed Central

Kwon, Kwang-il; Kweon, Soon Ju; Wang, Youfa; Gittelsohn, Joel

2017-01-01

BACKGROUND/OBJECTIVES The role of a school's nutrition environment in explaining students' eating behaviors and weight status has not been examined in an Asian setting. The purpose of this study was to create a school nutrition environment index and to pilot test the index in elementary and middle schools in urban South Korea. SUBJECTS/METHODS This study used a mixed-methods approach. Environment assessment tools were developed based on formative research, which comprised literature reviews, in-depth interviews, and focus group discussions. Key elements from the formative research were included in the assessment tool, which consisted of a structured survey questionnaire for school dietitians. Fifteen school dietitians from 7 elementary and 8 middle schools in Seoul completed the questionnaire. RESULTS The formative research revealed four main sections that guided a summary index to assess a school's nutrition environment: resource availability, education and programs, dietitians' perceptions and characteristics, and school lunch menu. Based on the literature reviews and interviews, an index scoring system was developed. The total possible score from the combined four index sections was 40 points. From the 15 schools participating in the pilot survey, the mean school nutrition-environment index was 22.5 (standard deviation ± 3.2; range 17-28). The majority of the schools did not offer classroom-based nutrition education or nutrition counseling for students and parents. The popular modes of nutrition education were school websites, posters, and newsletters. CONCLUSIONS This paper illustrates the process used to develop an instrument to assess a school's nutrition environment. Moreover, it presents the steps used to develop a scoring system for creation of a school nutrition environment index. As pilot testing indicated the total index score has some variation across schools, we suggest applying this instrument in future studies involving a larger number of schools. Future studies with larger samples will allow investigation of the validity and reliability of this newly developed tool. PMID:28989577

Creating a school nutrition environment index and pilot testing it in elementary and middle schools in urban South Korea.

PubMed

Park, Sohyun; Kwon, Kwang-Il; Kweon, Soon Ju; Wang, Youfa; Gittelsohn, Joel

2017-10-01

The role of a school's nutrition environment in explaining students' eating behaviors and weight status has not been examined in an Asian setting. The purpose of this study was to create a school nutrition environment index and to pilot test the index in elementary and middle schools in urban South Korea. This study used a mixed-methods approach. Environment assessment tools were developed based on formative research, which comprised literature reviews, in-depth interviews, and focus group discussions. Key elements from the formative research were included in the assessment tool, which consisted of a structured survey questionnaire for school dietitians. Fifteen school dietitians from 7 elementary and 8 middle schools in Seoul completed the questionnaire. The formative research revealed four main sections that guided a summary index to assess a school's nutrition environment: resource availability, education and programs, dietitians' perceptions and characteristics, and school lunch menu. Based on the literature reviews and interviews, an index scoring system was developed. The total possible score from the combined four index sections was 40 points. From the 15 schools participating in the pilot survey, the mean school nutrition-environment index was 22.5 (standard deviation ± 3.2; range 17-28). The majority of the schools did not offer classroom-based nutrition education or nutrition counseling for students and parents. The popular modes of nutrition education were school websites, posters, and newsletters. This paper illustrates the process used to develop an instrument to assess a school's nutrition environment. Moreover, it presents the steps used to develop a scoring system for creation of a school nutrition environment index. As pilot testing indicated the total index score has some variation across schools, we suggest applying this instrument in future studies involving a larger number of schools. Future studies with larger samples will allow investigation of the validity and reliability of this newly developed tool.

National Alliance for Advance Biofuels and Bio-Products Final Technical Report Addendum Hydrothermal Processing Pilot System

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

Oyler, James R.

2015-12-21

The main objective of the NAABB was to combine science, technology, and engineering expertise from across the nation to break down critical technical barriers to commercialization of algae-based biofuels. As a part of the consortium, Genifuel’s NAABB goals was to fabricate and demonstrate a pilot-scale system to convert algae into fuels. The purpose of this pilot system was to show that processes developed in the laboratory at bench-scale during the program could be successfully scaled up to a pre-commercial level, and thereby provide visibility into the ultimate viability and cost of algae biofuels. The pilot system has now been completedmore » and tested, and this report documents what has been achieved.« less

Personnel Selection Influences on Remotely Piloted Aircraft Human-System Integration.

PubMed

Carretta, Thomas R; King, Raymond E

2015-08-01

Human-system integration (HSI) is a complex process used to design and develop systems that integrate human capabilities and limitations in an effective and affordable manner. Effective HSI incorporates several domains, including manpower, personnel and training, human factors, environment, safety, occupational health, habitability, survivability, logistics, intelligence, mobility, and command and control. To achieve effective HSI, the relationships among these domains must be considered. Although this integrated approach is well documented, there are many instances where it is not followed. Human factors engineers typically focus on system design with little attention to the skills, abilities, and other characteristics needed by human operators. When problems with fielded systems occur, additional training of personnel is developed and conducted. Personnel selection is seldom considered during the HSI process. Complex systems such as aviation require careful selection of the individuals who will interact with the system. Personnel selection is a two-stage process involving select-in and select-out procedures. Select-in procedures determine which candidates have the aptitude to profit from training and represent the best investment. Select-out procedures focus on medical qualification and determine who should not enter training for medical reasons. The current paper discusses the role of personnel selection in the HSI process in the context of remotely piloted aircraft systems.

Preliminary Engineering Report for the Use of Peracetic Acid at the Oak Ridge National Laboratory Sewage Treatment Plant

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

Taylor, Paul Allen

2017-02-01

The purpose of this report is to identify other disinfection methods to replace the current ozone system and propose a small pilot-scale test. Based on a review of the literature and disinfectants used by other wastewater plants in Tennessee, peracetic acid (PAA) was identified as a leading candidate. This report provides the basis for requesting approval for a pilot-scale study using PAA.

Edible Oil Barriers for Treatment of Perchlorate Contaminated Groundwater

DTIC Science & Technology

2006-02-16

perchlorate is relatively recent. Work performed in soil at Longhorn Army Ammunition Plant in Texas identified chicken manure, cow manure, and...Missile Plant , NC Pilot July-Aug. 2004 Recirculation of emulsion through source area Other DoD Facilities Confidential Site, MD Pilot Oct...G.M. Birk, 2004. A Dash of Oil and Let Marinate. Pollution Engineering, May 2004, pages 30-34. 6.3 End-User Issues Potential end users of the

Helicopter Display Improvement Study

DTIC Science & Technology

1975-05-01

PRESSURE INDICATOR 43 TURN A N D SLIP INDICATOR 21 ENGINE AND SDG OIL IN TEMPERATURE INDICATOR 44 COURSE INDICATOR 22 RADIO MAGNETIC COMPASS INDICATOR... compass seemed to present a problem to several H-l series pilots In that It was poorly located and should be moved. Possible locations Included...the UH-lNs standby compass . Both H/L and L/L pilots agreed that internal, white light was the best system currently in use. INDIVIDUAL DISPLAYS

A Summary of Crew Workload and Situational Awareness Ratings for U.S. Army Aviation Aircraft

DTIC Science & Technology

2014-06-01

Engineering Directorate (ARL/HRED) assesses crewstation design for new and upgraded U.S. Army Aviation aircraft during simulations and operational...crewstation design for new and upgraded Army Aviation aircraft during simulations and operational testing. The assessments are conducted to identify...crewstation design . To date, more than 12,000 pilot workload ratings and 3000 pilot SA ratings have been collected by ARL/HRED for Army aircraft . This report

Race to improve student understanding of uncertainty: Using LEGO race cars in the physics lab

NASA Astrophysics Data System (ADS)

Parappilly, Maria; Hassam, Christopher; Woodman, Richard J.

2018-01-01

Laboratories using LEGO race cars were developed for students in an introductory physics topic with a high early drop-out rate. In a 2014 pilot study, the labs were offered to improve students' confidence with experiments and laboratory skills, especially uncertainty propagation. This intervention was extended into the intro level physics topic the next year, for comparison and evaluation. Considering the pilot study, we subsequently adapted the delivery of the LEGO labs for a large Engineering Mechanics cohort. A qualitative survey of the students was taken to gain insight into their perception of the incorporation of LEGO race cars into physics labs. For Engineering, the findings show that LEGO physics was instrumental in teaching students the measurement and uncertainty, improving their lab reporting skills, and was a key factor in reducing the early attrition rate. This paper briefly recalls the results of the pilot study, and how variations in the delivery yielded better learning outcomes. A novel method is proposed for how LEGO race cars in a physics lab can help students increase their understanding of uncertainty and motivate them towards physics practicals.

Salivary alpha-amylase activity and stress in Japan air self-defense force cargo pilots involved in Iraq reconstruction.

PubMed

Iizuka, Naotaka; Awano, Shuji; Ansai, Toshihiro

2012-01-01

This study aimed to verify whether salivary α-amylase enzyme activity (Amy) is useful as a biomarker of stress in pilots working in a stressful environment. The subjects in this study were nine Japan air self-defense force pilots who participated in Iraq reconstruction support activity in Kuwait. Amy was measured using a portable salivary amylase monitor at preflight, postflight, and on stand-by day. In addition, the state-trait anxiety inventory was administered with state scores (STAI-S) compared to Amy levels. There were greater differences in Amy levels at baseline compared to STAI-S scores between subjects on the stand-by day. Amy levels at preflight tended to increase compared to those on stand-by day as did STAI-S. The change in Amy level at postflight varied among the pilots. The Amy levels of four subjects at postflight were elevated compared to levels at preflight, while the STAI-S scores for all pilots at postflight were lower than at preflight. This study suggests that the Amy level of pilots can reflect subtle individual differences in response to the psychological and physiological stress of a flight task. Thus, monitoring Amy level may be useful for stress evaluation of pilots working in a stressful environment, providing data that might be used as an impetus for addressing stress management for this population. Copyright © 2012 Wiley Periodicals, Inc.

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.

An Analysis of TRACON (Terminal Radar Approach Control) Controller-Pilot Voice Communication

DOT National Transportation Integrated Search

1996-06-01

The purpose of this analysis was to examine pilot-controller communication practices in the TRACONI (Terminal Radar Approach : Control) environment. Forty-eight hours of communications recorded on the voice tapes from eight TRACONs were analyzed. : T...

An Analysis of Tower (Local) Controller - Pilot Voice Communications

DOT National Transportation Integrated Search

1994-06-01

The purposes of this analysis were to examine current pilot-controller communication practices in the terminal environment. Forty-nine hours of voice tapes from local positions in ten Air Traffic Control Towers (ATCTs) were examined. There were 8,444...

Paired peer learning through engineering education outreach

NASA Astrophysics Data System (ADS)

Fogg-Rogers, Laura; Lewis, Fay; Edmonds, Juliet

2017-01-01

Undergraduate education incorporating active learning and vicarious experience through education outreach presents a critical opportunity to influence future engineering teaching and practice capabilities. Engineering education outreach activities have been shown to have multiple benefits; increasing interest and engagement with science and engineering for school children, providing teachers with expert contributions to engineering subject knowledge, and developing professional generic skills for engineers such as communication and teamwork. This pilot intervention paired 10 pre-service teachers and 11 student engineers to enact engineering outreach in primary schools, reaching 269 children. A longitudinal mixed methods design was employed to measure change in attitudes and Education Outreach Self-Efficacy in student engineers; alongside attitudes, Teaching Engineering Self-Efficacy and Engineering Subject Knowledge Confidence in pre-service teachers. Highly significant improvements were noted in the pre-service teachers' confidence and self-efficacy, while both the teachers and engineers qualitatively described benefits arising from the paired peer mentor model.

Lockheed P–38J Lightning at the Aircraft Engine Research Laboratory

NASA Image and Video Library

1945-03-21

The National Advisory Committee for Aeronautics (NACA) Aircraft Engine Research Laboratory acquired two Lockheed P–38J Lightning in October 1944 to augment their burgeoning icing research program. The P–38 was a high-altitude interceptor with a unique twin fuselage configuration. Lockheed designed the aircraft in 1938 and 1939. Its two Allison V–1710 engines carried the aircraft to altitudes up to 40,000 feet. The P–38 was used extensively during World War II in a variety of roles. In August 1943, Lockheed began producing an improved version, the P–38J that included better cockpit heating, engine cooling, and dive flaps. The military loaned the NACA two P–38Js to determine the amount of ice formation on the induction system of the turbosupercharger-equipped engines. In 1944 and 1945 one of the aircraft was subjected to ground tests using an engine blower on the hangar apron. The V–1710 was run over a full range of speeds as different levels of water were injected into the blower and sprayed onto the engine. The other P–38J was flown at 10,000 feet altitude with water sprayed into the engine to simulate rain. The tests confirmed that closing the intercooler flap added protection against the ice by blocking water ingestion and increasing engine heat. NACA pilot Joseph Walker joined the Cleveland laboratory in early 1945 as a physicist. Walker had flown P–38s during World, and later claimed that seeing the NACA’s two P–38Js inspired him to return to his earlier calling as a pilot, this time with the NACA. Walker was particularly active in the icing flight program during his five years of flying in Cleveland.