32 CFR 171.4 - Qualifications.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 1 2014-07-01 2014-07-01 false Qualifications. 171.4 Section 171.4 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.4 Qualifications. The Secretary of Agriculture...

32 CFR 171.2 - Applicability.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 1 2014-07-01 2014-07-01 false Applicability. 171.2 Section 171.2 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.2 Applicability. The regulations in this part...

32 CFR 171.4 - Qualifications.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 1 2013-07-01 2013-07-01 false Qualifications. 171.4 Section 171.4 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.4 Qualifications. The Secretary of Agriculture...

32 CFR 171.7 - Reporting requirements.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 1 2011-07-01 2011-07-01 false Reporting requirements. 171.7 Section 171.7 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.7 Reporting requirements. Not later...

32 CFR 171.4 - Qualifications.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 1 2012-07-01 2012-07-01 false Qualifications. 171.4 Section 171.4 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.4 Qualifications. The Secretary of Agriculture...

32 CFR 171.2 - Applicability.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 1 2010-07-01 2010-07-01 false Applicability. 171.2 Section 171.2 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.2 Applicability. The regulations in this part...

32 CFR 171.2 - Applicability.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 1 2012-07-01 2012-07-01 false Applicability. 171.2 Section 171.2 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.2 Applicability. The regulations in this part...

32 CFR 171.7 - Reporting requirements.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 1 2010-07-01 2010-07-01 false Reporting requirements. 171.7 Section 171.7 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.7 Reporting requirements. Not later...

32 CFR 171.4 - Qualifications.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 1 2011-07-01 2011-07-01 false Qualifications. 171.4 Section 171.4 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.4 Qualifications. The Secretary of Agriculture...

32 CFR 171.2 - Applicability.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 1 2013-07-01 2013-07-01 false Applicability. 171.2 Section 171.2 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.2 Applicability. The regulations in this part...

32 CFR 171.2 - Applicability.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 1 2011-07-01 2011-07-01 false Applicability. 171.2 Section 171.2 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.2 Applicability. The regulations in this part...

32 CFR 171.7 - Reporting requirements.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 1 2014-07-01 2014-07-01 false Reporting requirements. 171.7 Section 171.7 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.7 Reporting requirements. Not later...

Development of Textile Reinforced Composites for Aircraft Structures

NASA Technical Reports Server (NTRS)

Dexter, H. Benson

1998-01-01

NASA has been a leader in development of composite materials for aircraft applications during the past 25 years. In the early 1980's NASA and others conducted research to improve damage tolerance of composite structures through the use of toughened resins but these resins were not cost-effective. The aircraft industry wanted affordable, robust structures that could withstand the rigors of flight service with minimal damage. The cost and damage tolerance barriers of conventional laminated composites led NASA to focus on new concepts in composites which would incorporate the automated manufacturing methods of the textiles industry and which would incorporate through-the-thickness reinforcements. The NASA Advanced Composites Technology (ACT) Program provided the resources to extensively investigate the application of textile processes to next generation aircraft wing and fuselage structures. This paper discusses advanced textile material forms that have been developed, innovative machine concepts and key technology advancements required for future application of textile reinforced composites in commercial transport aircraft. Multiaxial warp knitting, triaxial braiding and through-the-thickness stitching are the three textile processes that have surfaced as the most promising for further development. Textile reinforced composite structural elements that have been developed in the NASA ACT Program are discussed. Included are braided fuselage frames and window-belt reinforcements, woven/stitched lower fuselage side panels, stitched multiaxial warp knit wing skins, and braided wing stiffeners. In addition, low-cost processing concepts such as resin transfer molding (RTM), resin film infusion (RFI), and vacuum-assisted resin transfer molding (VARTM) are discussed. Process modeling concepts to predict resin flow and cure in textile preforms are also discussed.

32 CFR 171.8 - Expiration.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 1 2012-07-01 2012-07-01 false Expiration. 171.8 Section 171.8 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.8 Expiration. This part expires on 30 September 2005. ...

32 CFR 171.8 - Expiration.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 1 2010-07-01 2010-07-01 false Expiration. 171.8 Section 171.8 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.8 Expiration. This part expires on 30 September 2005. ...

32 CFR 171.8 - Expiration.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 1 2011-07-01 2011-07-01 false Expiration. 171.8 Section 171.8 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.8 Expiration. This part expires on 30 September 2005. ...

32 CFR 171.8 - Expiration.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 1 2013-07-01 2013-07-01 false Expiration. 171.8 Section 171.8 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.8 Expiration. This part expires on 30 September 2005. ...

32 CFR 171.8 - Expiration.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 1 2014-07-01 2014-07-01 false Expiration. 171.8 Section 171.8 National Defense Department of Defense OFFICE OF THE SECRETARY OF DEFENSE DEFENSE CONTRACTING IMPLEMENTATION OF WILDFIRE SUPPRESSION AIRCRAFT TRANSFER ACT OF 1996 § 171.8 Expiration. This part expires on 30 September 2005. ...

Validation Tests of Fiber Optic Strain-Based Operational Shape and Load Measurements

NASA Technical Reports Server (NTRS)

Bakalyar, John A.; Jutte, Christine

2012-01-01

Aircraft design has been progressing toward reduced structural weight to improve fuel efficiency, increase performance, and reduce cost. Lightweight aircraft structures are more flexible than conventional designs and require new design considerations. Intelligent sensing allows for enhanced control and monitoring of aircraft, which enables increased structurally efficiency. The NASA Dryden Flight Research Center (DFRC) has developed an instrumentation system and analysis techniques that combine to make distributed structural measurements practical for lightweight vehicles. Dryden's Fiber Optic Strain Sensing (FOSS) technology enables a multitude of lightweight, distributed surface strain measurements. The analysis techniques, referred to as the Displacement Transfer Functions (DTF) and Load Transfer Functions (LTF), use surface strain values to calculate structural deflections and operational loads. The combined system is useful for real-time monitoring of aeroelastic structures, along with many other applications. This paper describes how the capabilities of the measurement system were demonstrated using subscale test articles that represent simple aircraft structures. Empirical FOSS strain data were used within the DTF to calculate the displacement of the article and within the LTF to calculate bending moments due to loads acting on the article. The results of the tests, accuracy of the measurements, and a sensitivity analysis are presented.

Coast Guard Aircraft: Transfer of Fixed-Wing C-27J Aircraft Is Complex and Further Fleet Purchases Should Coincide with Study Results

DTIC Science & Technology

2015-03-01

C-27J to the Coast Guard. This report assesses (1) the status of the transfer and risks the Coast Guard faces in fielding the transferred aircraft...had transferred 2 of the 14 C-27J aircraft it is receiving from the Air Force to its aircraft maintenance facility, with plans to field 14 fully...Coast Guard continues to receive these aircraft in the near term, the capability and cost of the Coast Guard’s fixed-wing fleet runs the risk of being

Second NASA Advanced Composites Technology Conference

NASA Technical Reports Server (NTRS)

Davis, John G., Jr. (Compiler); Bohon, Herman L. (Compiler)

1992-01-01

The conference papers are presented. The Advanced Composite Technology (ACT) Program is a major multi-year research initiative to achieve a national goal of technology readiness before the end of the decade. Conference papers recorded results of research in the ACT Program in the specific areas of automated fiber placement, resin transfer molding, textile preforms, and stitching as these processes influence design, performance, and cost of composites in aircraft structures. These papers will also be included in the Ninth Conference Proceedings to be published by the Federal Aviation Administration as a separate document.

Third NASA Advanced Composites Technology Conference, volume 1, part 1

NASA Technical Reports Server (NTRS)

Davis, John G., Jr. (Compiler); Bohon, Herman L. (Compiler)

1993-01-01

This document is a compilation of papers presented at the Third NASA Advanced Composites Technology (ACT) Conference. The ACT Program is a major multi-year research initiative to achieve a national goal of technology readiness before the end of the decade. Conference papers recorded results of research in the ACT Program in the specific areas of automated fiber placement, resin transfer molding, textile preforms, and stitching as these processes influence design, performance, and cost of composites in aircraft structures. Papers sponsored by the Department of Defense on the Design and Manufacturing of Low Cost Composites (DMLCC) are also included in Volume 2 of this document.

Textile composite fuselage structures development

NASA Technical Reports Server (NTRS)

Jackson, Anthony C.; Barrie, Ronald E.; Chu, Robert L.

1993-01-01

Phase 2 of the NASA ACT Contract (NAS1-18888), Advanced Composite Structural Concepts and Materials Technology for Transport Aircraft Structures, focuses on textile technology, with resin transfer molding or powder coated tows. The use of textiles has the potential for improving damage tolerance, reducing cost and saving weight. This program investigates resin transfer molding (RTM), as a maturing technology for high fiber volume primary structures and powder coated tows as an emerging technology with a high potential for significant cost savings and superior structural properties. Powder coated tow technology has promise for significantly improving the processibility of high temperature resins such as polyimides.

Third NASA Advanced Composites Technology Conference, volume 1, part 2

NASA Technical Reports Server (NTRS)

Davis, John G., Jr. (Compiler); Bohon, Herman L. (Compiler)

1993-01-01

This document is a compilation of papers presented at the Third NASA Advanced Composites Technology (ACT) Conference held at Long Beach, California, 8-11 June 1992. The ACT Program is a major multi-year research initiative to achieve a national goal of technology readiness before the end of the decade. Conference papers recorded results of research in the ACT Program in the specific areas of automated fiber placement, resin transfer molding, textile preforms, and stitching as these processes influence design, performance, and cost of composites in aircraft structures. Papers sponsored by the Department of Defense on the Design and Manufacturing of Low Cost Composites (DMLCC) are also included in Volume 2 of this document.

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.

Analysis and calculation of lightning-induced voltages in aircraft electrical circuits

NASA Technical Reports Server (NTRS)

Plumer, J. A.

1974-01-01

Techniques to calculate the transfer functions relating lightning-induced voltages in aircraft electrical circuits to aircraft physical characteristics and lightning current parameters are discussed. The analytical work was carried out concurrently with an experimental program of measurements of lightning-induced voltages in the electrical circuits of an F89-J aircraft. A computer program, ETCAL, developed earlier to calculate resistive and inductive transfer functions is refined to account for skin effect, providing results more valid over a wider range of lightning waveshapes than formerly possible. A computer program, WING, is derived to calculate the resistive and inductive transfer functions between a basic aircraft wing and a circuit conductor inside it. Good agreement is obtained between transfer inductances calculated by WING and those reduced from measured data by ETCAL. This computer program shows promise of expansion to permit eventual calculation of potential lightning-induced voltages in electrical circuits of complete aircraft in the design stage.

41 CFR 102-33.335 - What are the receiving agency's responsibilities in the transfer or donation of aircraft parts?

Code of Federal Regulations, 2010 CFR

2010-07-01

... 41 Public Contracts and Property Management 3 2010-07-01 2010-07-01 false What are the receiving agency's responsibilities in the transfer or donation of aircraft parts? 102-33.335 Section 102-33.335... agency's responsibilities in the transfer or donation of aircraft parts? An agency that receives...

41 CFR 102-33.335 - What are the receiving agency's responsibilities in the transfer or donation of aircraft parts?

Code of Federal Regulations, 2012 CFR

2012-01-01

... 41 Public Contracts and Property Management 3 2012-01-01 2012-01-01 false What are the receiving agency's responsibilities in the transfer or donation of aircraft parts? 102-33.335 Section 102-33.335... agency's responsibilities in the transfer or donation of aircraft parts? An agency that receives...

41 CFR 102-33.335 - What are the receiving agency's responsibilities in the transfer or donation of aircraft parts?

Code of Federal Regulations, 2013 CFR

2013-07-01

... 41 Public Contracts and Property Management 3 2013-07-01 2013-07-01 false What are the receiving agency's responsibilities in the transfer or donation of aircraft parts? 102-33.335 Section 102-33.335... agency's responsibilities in the transfer or donation of aircraft parts? An agency that receives...

41 CFR 102-33.335 - What are the receiving agency's responsibilities in the transfer or donation of aircraft parts?

Code of Federal Regulations, 2014 CFR

2014-01-01

... 41 Public Contracts and Property Management 3 2014-01-01 2014-01-01 false What are the receiving agency's responsibilities in the transfer or donation of aircraft parts? 102-33.335 Section 102-33.335... agency's responsibilities in the transfer or donation of aircraft parts? An agency that receives...

41 CFR 102-33.335 - What are the receiving agency's responsibilities in the transfer or donation of aircraft parts?

Code of Federal Regulations, 2011 CFR

2011-01-01

... 41 Public Contracts and Property Management 3 2011-01-01 2011-01-01 false What are the receiving agency's responsibilities in the transfer or donation of aircraft parts? 102-33.335 Section 102-33.335... agency's responsibilities in the transfer or donation of aircraft parts? An agency that receives...

Improving Access to Military Aircraft During Civilian Wildfires

DTIC Science & Technology

2015-12-01

Stafford acts ; DOD doctrine and instruction, such as Defense Support to (of) Civil Authorities and Immediate Response Authority; and civilian...civilian wildfires, and that (2) the Economy and Stafford acts be modified to improve the efficiency with which military aircraft respond to civilian...wildfires. 14. SUBJECT TERMS wildfire, aircraft, The Economy Act , The Stafford Act , Department of Defense, National Interagency Fire Center

Aircraft transfer of pediatric patients with intractable cardiac or airway problems – single-institutional experience of a specialty hospital.

PubMed

Ando, Makoto; Takahashi, Yukihiro; Park, In-Sam; Tomoike, Hitonobu

2015-01-01

There is currently a well-established network for the allocation of donor organs for transplantation in Japan, and emergency patients are often transported by the "Doctor Helicopter". However, interhospital transfer of patients, which can require aircraft with specialized equipment, depends on arrangement by each responsible hospital. Since 2009 there were 41 interhospital aviation transfers of pediatric patients with intractable cardiac or airway diseases seeking surgical treatment at Sakakibara Heart Institute. Of these, 22 were newborns, 21 were on continuous drip infusion and 14 on mechanical ventilator support. In 15 cases (36.6%), a commercial airliner was used, with the remaining using chartered emergency aircraft (eg, local fire department helicopter, Self-Defense-Forces of Japan and the Doctor Helicopter). The median transfer time was 239 min for commercial airliners, 51 min for chartered aircraft departing directly from the referring hospital and 120.5 min for chartered aircraft departing from a nearby location. The efficiency of the transfer exemplified by the percentage of the time on board the aircraft was significantly lower for commercial airliners compared with chartered emergency aircraft. Further efforts and cooperation with government are required to obtain geographically uniform availability of carriers with optimal medical equipment to improve pediatric patient outcomes.

Development of stitched/RTM composite primary structures

NASA Technical Reports Server (NTRS)

Kullerd, Susan M.; Dow, Marvin B.

1992-01-01

The goal of the NASA Advanced Composites Technology (ACT) Program is to provide the technology required to gain the full benefit of weight savings and performance offered by composite primary structures. Achieving the goal is dependent on developing composite materials and structures which are damage tolerant and economical to manufacture. Researchers at NASA LaRC and Douglas Aircraft Company are investigating stitching reinforcement combined with resin transfer molding (RTM) to create structures meeting the ACT program goals. The Douglas work is being performed under a NASA contract entitled Innovative Composites Aircraft Primary Structures (ICAPS). The research is aimed at materials, processes and structural concepts for application in both transport wings and fuselages. Empirical guidelines are being established for stitching reinforcement in primary structures. New data are presented in this paper for evaluation tests of thick (90-ply) and thin (16-ply) stitched laminates, and from selection tests of RTM composite resins. Tension strength, compression strength and post-impact compression strength data are reported. Elements of a NASA LaRC program to expand the science base for stitched/RTM composites are discussed.

Satellite communications provisions on NASA Ames instrumented aircraft platforms for Earth science research/applications

NASA Technical Reports Server (NTRS)

Shameson, L.; Brass, J. A.; Hanratty, J. J.; Roberts, A. C.; Wegener, S. S.

1995-01-01

Earth science activities at NASA Ames are research in atmospheric and ecosystem science, development of remote sensing and in situ sampling instruments, and their integration into scientific research platform aircraft. The use of satellite communications can greatly extend the capability of these agency research platform aircraft. Current projects and plans involve satellite links on the Perseus UAV and the ER-2 via TDRSS and a proposed experiment on the NASA Advanced Communications Technology Satellite. Provisions for data links on the Perseus research platform, via TDRSS S-band multiple access service, have been developed and are being tested. Test flights at Dryden are planned to demonstrate successful end-to-end data transfer. A Unisys Corp. airborne satcom STARLink system is being integrated into an Ames ER-2 aircraft. This equipment will support multiple data rates up to 43 Mb/s each via the TDRS S Ku-band single access service. The first flight mission for this high-rate link is planned for August 1995. Ames and JPL have proposed an ACTS experiment to use real-time satellite communications to improve wildfire research campaigns. Researchers and fire management teams making use of instrumented aircraft platforms at a prescribed burn site will be able to communicate with experts at Ames, the U.S. Forest Service, and emergency response agencies.

Transfer of Training with Formation Flight Trainer.

ERIC Educational Resources Information Center

Reid, Gary B.; Cyrus, Michael L.

The present research was conducted to determine transfer of practice from a formation simulator to actual aircraft flight for the wing aircraft component of the formation flying task. Evidence in support of positive transfer was obtained by comparing students trained in the formation simulator with students who were essentially untrained and with…

Observations of Convective and Dynamical Instabilities in Tropopause Folds and their Contribution to Stratosphere-Troposphere Exchange

NASA Technical Reports Server (NTRS)

Cho, John Y. N.; Newell, Reginald E.; Bui, T. Paul; Browell, Edward V.; Fenn, Martha A.; Gary, Bruce L.; Mahoney, Michael J.; Gregory, Gerald L.; Sachse, Glen W.; Vay, Stephanie A.

1999-01-01

With aircraft-mounted in-situ and remote sensing instruments for dynamical, thermal. and chemical measurements, we studied two cases of tropopause folding. In both folds we found Kelvin-Helmholtz billows with horizontal wavelength of about 900 m and thickness of about 120 m. In one case the instability was effectively mixing the bottomside of the fold, leading to the transfer of stratospheric air into the troposphere. Also we discovered in both cases small-scale secondary ozone maxima shortly after the aircraft ascended past the topside of the fold that corresponded to regions of convective instability. We interpreted this phenomenon as convectively breaking gravity waves. Therefore, we posit that convectively breaking gravity waves acting on tropopause folds must be added to the list of important irreversible mixing mechanisms leading to stratosphere-troposphere exchange.

Comparison of VDL Modes in the Aeronautical Telecommunications Network

NASA Technical Reports Server (NTRS)

Bretmersky, Steven; Konangi, Vijay K.; Kerczewski, Robert J.

2002-01-01

VHF Digital Link (VDL) has been identified as a method of communication between aircraft and ground stations in the Aeronautical Telecommunications Network (ATN). Three different modes of VDL have been suggested for implementation. Simulations were conducted to compare the data transfer capabilities of VDL Modes 2, 3, and 4. These simulations focus on up to 50 aircraft communicating with a single VDL ground station. The data traffic is generated by the standard File Transfer Protocol (FTP) and Hyper Text Transfer Protocol (HTTP) applications in the aircraft. Comparisons of the modes are based on the number of files and pages transferred and the response time.

Army PM UAS Spectrum Update

DTIC Science & Technology

2012-07-01

Small Unmanned Aircraft Systems vs. Air Combat Telemetry Systems SUAS - 2 Watts vs. ACTS 100 Watts... SUAS - 25 km normal radius vs. ACTS 200 km normal radius Primary Concerns: Operational Small Unmanned Aircraft Systems ...Std Z39-18 UNCLASSIFIED UNCLASSIFIED Army Unmanned Aircraft Systems 2 Provides the small unit the

An integrated strategy for aircraft/airport noise abatement: A legal-institutional control act section 7 to the noise control act of 1972 and proposals based thereon

NASA Technical Reports Server (NTRS)

Mayo, L. H.

1975-01-01

The development of the aircraft noise control structure since the Griggs case of 1962 was examined. The Noise Control Act of 1972 is described which undertook to establish the legal-institutional framework within which an adequate aircraft/airport noise abatement program might be initiated with concern for full recognition of all the beneficial and detrimental consequences of air transportation and appropriate distribution of benefits and costs.

Using memory for prior aircraft events to detect conflicts under conditions of proactive air traffic control and with concurrent task requirements.

PubMed

Bowden, Vanessa K; Loft, Shayne

2016-06-01

In 2 experiments we examined the impact of memory for prior events on conflict detection in simulated air traffic control under conditions where individuals proactively controlled aircraft and completed concurrent tasks. Individuals were faster to detect conflicts that had repeatedly been presented during training (positive transfer). Bayesian statistics indicated strong evidence for the null hypothesis that conflict detection was not impaired for events that resembled an aircraft pair that had repeatedly come close to conflicting during training. This is likely because aircraft altitude (the feature manipulated between training and test) was attended to by participants when proactively controlling aircraft. In contrast, a minor change to the relative position of a repeated nonconflicting aircraft pair moderately impaired conflict detection (negative transfer). There was strong evidence for the null hypothesis that positive transfer was not impacted by dividing participant attention, which suggests that part of the information retrieved regarding prior aircraft events was perceptual (the new aircraft pair "looked" like a conflict based on familiarity). These findings extend the effects previously reported by Loft, Humphreys, and Neal (2004), answering the recent strong and unanimous calls across the psychological science discipline to formally establish the robustness and generality of previously published effects. (PsycINFO Database Record (c) 2016 APA, all rights reserved).

Firefighting and Emergency Response Study of Advanced Composites Aircraft; Objective 1: Composite Material Damage in Minor Aircraft Fires

DTIC Science & Technology

2013-05-18

26 4.3. 1-D Heat Transfer Model with Pyrolysis and Thermal Damage...Improvements and Added Features ........................................................................31 4.3.4. Pyrolysis Model Calibration... Pyrolysis Model ................................................32 Figure 25. Updated Heat Transfer Algorithm Flow Chart

Jet fuel based high pressure solid oxide fuel cell system

NASA Technical Reports Server (NTRS)

Gummalla, Mallika (Inventor); Yamanis, Jean (Inventor); Olsommer, Benoit (Inventor); Dardas, Zissis (Inventor); Bayt, Robert (Inventor); Srinivasan, Hari (Inventor); Dasgupta, Arindam (Inventor); Hardin, Larry (Inventor)

2013-01-01

A power system for an aircraft includes a solid oxide fuel cell system which generates electric power for the aircraft and an exhaust stream; and a heat exchanger for transferring heat from the exhaust stream of the solid oxide fuel cell to a heat requiring system or component of the aircraft. The heat can be transferred to fuel for the primary engine of the aircraft. Further, the same fuel can be used to power both the primary engine and the SOFC. A heat exchanger is positioned to cool reformate before feeding to the fuel cell. SOFC exhaust is treated and used as inerting gas. Finally, oxidant to the SOFC can be obtained from the aircraft cabin, or exterior, or both.

Jet Fuel Based High Pressure Solid Oxide Fuel Cell System

NASA Technical Reports Server (NTRS)

Srinivasan, Hari (Inventor); Hardin, Larry (Inventor); Gummalla, Mallika (Inventor); Yamanis, Jean (Inventor); Olsommer, Benoit (Inventor); Dardas, Zissis (Inventor); Dasgupta, Arindam (Inventor); Bayt, Robert (Inventor)

2015-01-01

A power system for an aircraft includes a solid oxide fuel cell system which generates electric power for the aircraft and an exhaust stream; and a heat exchanger for transferring heat from the exhaust stream of the solid oxide fuel cell to a heat requiring system or component of the aircraft. The heat can be transferred to fuel for the primary engine of the aircraft. Further, the same fuel can be used to power both the primary engine and the SOFC. A heat exchanger is positioned to cool reformate before feeding to the fuel cell. SOFC exhaust is treated and used as inerting gas. Finally, oxidant to the SOFC can be obtained from the aircraft cabin, or exterior, or both.

Interenvironmental Transfer of Microorganisms on the Exterior Surfaces of Jet Aircraft

PubMed Central

Pfaender, Frederic K.; Swatek, Frank E.

1970-01-01

The likelihood of microorganisms being transferred to new environments by jet aircraft was investigated. Initial random sampling of the aircraft surface revealed the presence of microorganisms in varying numbers on different aerodynamic surfaces. Bacteria of the genus Bacillus were the most common isolates, comprising approximately one-third of the total organisms found. The most frequently isolated fungi were Cladosporium, Alternaria, Penicillium, and several yeasts. Sampling of surfaces before and immediately after a flight demonstrated that microorganisms were collected during flight in areas protected from the airstream and lost in those areas directly exposed to it. These experiments also showed that the majority of the organisms contaminating the aircraft were acquired from the air at ground level. The placement of microorganisms on the aircraft surface before a flight and determination of their survival after flight indicated that the test organisms were most likely to be transported in the areas protected from the airstream. The organisms showing the best chance of being transferred seem to be the sporeforming bacteria, arthrospore-forming fungi, and some yeasts. All phases of this work showed that microorganisms could be carried by jet aircraft to environments they could not reach by natural means of dispersal. PMID:5480099

ACTE Wing Loads Analysis

NASA Technical Reports Server (NTRS)

Horn, Nicholas R.

2015-01-01

The Adaptive Compliant Trailing Edge (ACTE) project modified a Gulfstream III (GIII) aircraft with a new flexible flap that creates a seamless transition between the flap and the wing. As with any new modification, it is crucial to ensure that the aircraft will not become overstressed in flight. To test this, Star CCM a computational fluid dynamics (CFD) software program was used to calculate aerodynamic data for the aircraft at given flight conditions.

Development of stitching reinforcement for transport wing panels

NASA Technical Reports Server (NTRS)

Palmer, Raymond J.; Dow, Marvin B.; Smith, Donald L.

1991-01-01

The NASA Advanced Composites Technology (ACT) program has the objective of providing the technology required to obtain the full benefit of weight savings and performance improvements offered by composite primary aircraft structures. Achieving the objective is dependent upon developing composite materials and structures which are damage tolerant and economical to manufacture. Researchers are investigating stitching reinforcement combined with resin transfer molding to produce materials meeting the ACT program objective. Research is aimed at materials, processes, and structural concepts for application in both transport wings and fuselages, but the emphasis to date has been on wing panels. Empirical guidelines are being established for stitching reinforcement in structures designed for heavy loads. Results are presented from evaluation tests investigating stitching types, threads, and density (penetrations per square inch). Tension strength, compression strength, and compression after impact data are reported.

Fundamental limitations on V/STOL terminal guidance due to aircraft characteristics

NASA Technical Reports Server (NTRS)

Wolkovitch, J.; Lamont, C. W.; Lochtie, D. W.

1971-01-01

A review is given of limitations on approach flight paths of V/STOL aircraft, including limits on descent angle due to maximum drag/lift ratio. A method of calculating maximum drag/lift ratio of tilt-wing and deflected slipstream aircraft is presented. Derivatives and transfer functions for the CL-84 tilt-wing and X-22A tilt-duct aircraft are presented. For the unaugmented CL-84 in steep descents the transfer function relating descent angle to thrust contains a right-half plane zero. Using optimal control theory, it is shown that this zero causes a serious degradation in the accuracy with which steep flight paths can be followed in the presence of gusts.

STS-28 Columbia, OV-102, crewmembers leave KSC O&C Bldg en route to LC Pad 39

NASA Image and Video Library

1989-08-08

STS028-S-001 (8 Aug 1989) --- The five astronaut crewmembers for STS-28 leave the operations and checkout building to board a transfer van en route to Launch Complex 39 for a date with Columbia. Front to back are Brewster H. Shaw Jr., Richard N. Richards, David C. Leestma, James C. Adamson and Mark N. Brown. At the rear of the line are Astronaut Michael L. Coats, acting chief of the astronaut office; and Donald R. Puddy, director of flight crew operations at JSC. Coats later flew a NASA Shuttle training aircraft for pre-launch and launch monitoring activities.

41 CFR 102-33.345 - What are a State agency's responsibilities in the donation of Federal Government aircraft parts?

Code of Federal Regulations, 2010 CFR

2010-07-01

...'s responsibilities in the donation of Federal Government aircraft parts? 102-33.345 Section 102-33... responsibilities in the donation of Federal Government aircraft parts? When a State agency accepts surplus Federal Government aircraft parts for donation, the agency must— (a) Review donation and transfer documents for...

41 CFR 102-33.345 - What are a State agency's responsibilities in the donation of Federal Government aircraft parts?

Code of Federal Regulations, 2011 CFR

2011-01-01

...'s responsibilities in the donation of Federal Government aircraft parts? 102-33.345 Section 102-33... responsibilities in the donation of Federal Government aircraft parts? When a State agency accepts surplus Federal Government aircraft parts for donation, the agency must— (a) Review donation and transfer documents for...

41 CFR 102-33.345 - What are a State agency's responsibilities in the donation of Federal Government aircraft parts?

Code of Federal Regulations, 2013 CFR

2013-07-01

...'s responsibilities in the donation of Federal Government aircraft parts? 102-33.345 Section 102-33... responsibilities in the donation of Federal Government aircraft parts? When a State agency accepts surplus Federal Government aircraft parts for donation, the agency must— (a) Review donation and transfer documents for...

41 CFR 102-33.345 - What are a State agency's responsibilities in the donation of Federal Government aircraft parts?

Code of Federal Regulations, 2014 CFR

2014-01-01

...'s responsibilities in the donation of Federal Government aircraft parts? 102-33.345 Section 102-33... responsibilities in the donation of Federal Government aircraft parts? When a State agency accepts surplus Federal Government aircraft parts for donation, the agency must— (a) Review donation and transfer documents for...

41 CFR 102-33.345 - What are a State agency's responsibilities in the donation of Federal Government aircraft parts?

Code of Federal Regulations, 2012 CFR

2012-01-01

...'s responsibilities in the donation of Federal Government aircraft parts? 102-33.345 Section 102-33... responsibilities in the donation of Federal Government aircraft parts? When a State agency accepts surplus Federal Government aircraft parts for donation, the agency must— (a) Review donation and transfer documents for...

Resin transfer molding for advanced composite primary wing and fuselage structures

NASA Technical Reports Server (NTRS)

Markus, Alan

1992-01-01

The stitching and resin transfer molding (RTM) processes developed at Douglas Aircraft Co. are successfully demonstrating significant cost reductions with good damage tolerance properties. These attributes were identified as critical to application of advanced composite materials to commercial aircraft primary structures. The RTM/stitching developments, cost analyses, and test results are discussed of the NASA Advanced Composites Technology program.

22 CFR 123.8 - Special controls on vessels, aircraft and satellites covered by the U.S. Munitions List.

Code of Federal Regulations, 2014 CFR

2014-04-01

....8 Special controls on vessels, aircraft and satellites covered by the U.S. Munitions List. (a) Transferring registration or control to a foreign person of any aircraft, vessel, or satellite on the U.S... 22 Foreign Relations 1 2014-04-01 2014-04-01 false Special controls on vessels, aircraft and...

22 CFR 123.8 - Special controls on vessels, aircraft and satellites covered by the U.S. Munitions List.

Code of Federal Regulations, 2013 CFR

2013-04-01

... on vessels, aircraft and satellites covered by the U.S. Munitions List. (a) Transferring registration... located in the United States or abroad. (b) The registration in a foreign country of any aircraft, vessel... 22 Foreign Relations 1 2013-04-01 2013-04-01 false Special controls on vessels, aircraft and...

22 CFR 123.8 - Special controls on vessels, aircraft and satellites covered by the U.S. Munitions List.

Code of Federal Regulations, 2012 CFR

2012-04-01

... on vessels, aircraft and satellites covered by the U.S. Munitions List. (a) Transferring registration... located in the United States or abroad. (b) The registration in a foreign country of any aircraft, vessel... 22 Foreign Relations 1 2012-04-01 2012-04-01 false Special controls on vessels, aircraft and...

22 CFR 123.8 - Special controls on vessels, aircraft and satellites covered by the U.S. Munitions List.

Code of Federal Regulations, 2011 CFR

2011-04-01

... on vessels, aircraft and satellites covered by the U.S. Munitions List. (a) Transferring registration... located in the United States or abroad. (b) The registration in a foreign country of any aircraft, vessel... 22 Foreign Relations 1 2011-04-01 2011-04-01 false Special controls on vessels, aircraft and...

22 CFR 123.8 - Special controls on vessels, aircraft and satellites covered by the U.S. Munitions List.

Code of Federal Regulations, 2010 CFR

2010-04-01

... on vessels, aircraft and satellites covered by the U.S. Munitions List. (a) Transferring registration... located in the United States or abroad. (b) The registration in a foreign country of any aircraft, vessel... 22 Foreign Relations 1 2010-04-01 2010-04-01 false Special controls on vessels, aircraft and...

Theoretical linear approach to the combined man-manipulator system in manual control of an aircraft

NASA Technical Reports Server (NTRS)

Brauser, K.

1981-01-01

An approach to the calculation of the dynamic characteristics of the combined man manipulator system in manual aircraft control was derived from a model of the neuromuscular system. This model combines the neuromuscular properties of man with the physical properties of the manipulator system which is introduced as pilot manipulator model into the manual aircraft control. The assumption of man as a quasilinear and time invariant control operator adapted to operating states, depending on the flight phases, of the control system gives rise to interesting solutions of the frequency domain transfer functions of both the man manipulator system and the closed loop pilot aircraft control system. It is shown that it is necessary to introduce the complete precision pilot manipulator model into the closed loop pilot aircraft transfer function in order to understand the well known handling quality criteria, and to derive these criteria directly from human operator properties.

78 FR 1253 - Schweizer Aircraft Corporation, a Subsidiary of Sikorsky Aircraft Corporation, a Division of...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-08

... Sikorsky Military Completion Center, Including On-Site Leased Workers From Adecco, Aerotek, Inc., Aquinas Consulting & Staffing Solutions, Belcan Engineering Group, Butler America, LLC., Cameron Mfg. and Design, Inc... In accordance with Section 223 of the Trade Act of 1974, as amended (``Act''), 19 U.S.C. 2273, the...

19 CFR 10.62b - Aircraft turbine fuel.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 19 Customs Duties 1 2012-04-01 2012-04-01 false Aircraft turbine fuel. 10.62b Section 10.62b... Supplies and Equipment for Vessels § 10.62b Aircraft turbine fuel. (a) General. Unless otherwise provided, aircraft turbine fuel withdrawn from a Customs bonded warehouse for use under section 309, Tariff Act of...

19 CFR 10.62b - Aircraft turbine fuel.

Code of Federal Regulations, 2014 CFR

2014-04-01

... 19 Customs Duties 1 2014-04-01 2014-04-01 false Aircraft turbine fuel. 10.62b Section 10.62b... Supplies and Equipment for Vessels § 10.62b Aircraft turbine fuel. (a) General. Unless otherwise provided, aircraft turbine fuel withdrawn from a Customs bonded warehouse for use under section 309, Tariff Act of...

19 CFR 10.62b - Aircraft turbine fuel.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 19 Customs Duties 1 2013-04-01 2013-04-01 false Aircraft turbine fuel. 10.62b Section 10.62b... Supplies and Equipment for Vessels § 10.62b Aircraft turbine fuel. (a) General. Unless otherwise provided, aircraft turbine fuel withdrawn from a Customs bonded warehouse for use under section 309, Tariff Act of...

19 CFR 10.62b - Aircraft turbine fuel.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 19 Customs Duties 1 2011-04-01 2011-04-01 false Aircraft turbine fuel. 10.62b Section 10.62b... Supplies and Equipment for Vessels § 10.62b Aircraft turbine fuel. (a) General. Unless otherwise provided, aircraft turbine fuel withdrawn from a Customs bonded warehouse for use under section 309, Tariff Act of...

19 CFR 10.62b - Aircraft turbine fuel.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 19 Customs Duties 1 2010-04-01 2010-04-01 false Aircraft turbine fuel. 10.62b Section 10.62b... Supplies and Equipment for Vessels § 10.62b Aircraft turbine fuel. (a) General. Unless otherwise provided, aircraft turbine fuel withdrawn from a Customs bonded warehouse for use under section 309, Tariff Act of...

14 CFR 223.2 - Exemption from section 401 of the Act.

Code of Federal Regulations, 2013 CFR

2013-01-01

... the extent necessary to carry, for purposes of in-flight observation, technical representatives of companies that have been engaged in the manufacture, development, or testing of aircraft or aircraft... persons to the aircraft flight deck. ...

14 CFR 223.2 - Exemption from section 401 of the Act.

Code of Federal Regulations, 2010 CFR

2010-01-01

... the extent necessary to carry, for purposes of in-flight observation, technical representatives of companies that have been engaged in the manufacture, development, or testing of aircraft or aircraft... persons to the aircraft flight deck. ...

14 CFR 223.2 - Exemption from section 401 of the Act.

Code of Federal Regulations, 2014 CFR

2014-01-01

... the extent necessary to carry, for purposes of in-flight observation, technical representatives of companies that have been engaged in the manufacture, development, or testing of aircraft or aircraft... persons to the aircraft flight deck. ...

14 CFR 223.2 - Exemption from section 401 of the Act.

Code of Federal Regulations, 2012 CFR

2012-01-01

... the extent necessary to carry, for purposes of in-flight observation, technical representatives of companies that have been engaged in the manufacture, development, or testing of aircraft or aircraft... persons to the aircraft flight deck. ...

14 CFR 223.2 - Exemption from section 401 of the Act.

Code of Federal Regulations, 2011 CFR

2011-01-01

... the extent necessary to carry, for purposes of in-flight observation, technical representatives of companies that have been engaged in the manufacture, development, or testing of aircraft or aircraft... persons to the aircraft flight deck. ...

The transfer of carbon fibers through a commercial aircraft water separator and air cleaner

NASA Technical Reports Server (NTRS)

Meyers, J. A.

1979-01-01

The fraction of carbon fibers passing through a water separator and an air filter was determined in order to estimate the proportion of fibers outside a closed aircraft that are transmitted to the electronics through the air conditioning system. When both devices were used together and only fibers 3 mm or larger were considered, a transfer function of .001 was obtained.

Research on the aircraft level measurement by laser tracker

NASA Astrophysics Data System (ADS)

Ye, Xiaowen; Tang, Wuzhong; Cao, Chun

2014-09-01

The measuring principle of laser tracking system was introduced. The aircraft level measurement was completed by establish the measurement datum mark, select public sites, set up the aircraft coordinate system and transfer stations. Laser tracking measurement technology improved the work efficiency and ensured the installation precision of key components.

Assessment of risk to Boeing commerical transport aircraft from carbon fibers. [fiber release from graphite/epxoy materials

NASA Technical Reports Server (NTRS)

Clarke, C. A.; Brown, E. L.

1980-01-01

The possible effects of free carbon fibers on aircraft avionic equipment operation, removal costs, and safety were investigated. Possible carbon fiber flow paths, flow rates, and transfer functions into the Boeing 707, 727, 737, 747 aircraft and potentially vulnerable equipment were identified. Probabilities of equipment removal and probabilities of aircraft exposure to carbon fiber were derived.

Criminal Acts against Civil Aviation: 1989

DTIC Science & Technology

1989-01-01

Aviation Security maintains records of aircraft hijackings, bombing attacks, and other significant criminal acts against civil aviation worldwide. These records include actual and attempted hijackings: explosions aboard aircraft, at airports, and at airline offices; and other selected criminal acts against civil aviation. These offenses represent serious threats to the safety of civil aviation and, in those incidents involving U.S. air carriers or facilities outside the United States, are often intended as symbolic attacks against the United States. This edition summarizes

Cost-efficient manufacturing of composite structures

NASA Technical Reports Server (NTRS)

Freeman, W. Tom; Davis, John G.; Johnston, Norman J.

1991-01-01

The Advanced Composites Technology (ACT) program is seeking research breakthroughs that will allow structures made of graphite epoxy materials to replace metals in the wings and fuselages of future aircrafts. NASA's goals are to reduce acquisition cost by 20 to 25 percent, structural weight for a resized aircraft by 40 to 50 percent, and the number of parts by half compared to current production aluminum aircraft. The innovative structural concepts, materials, and fabrication techniques emerging from the ACT program are described, and the relationship between aerospace developments and industrial, commercial, and sporting goods applications are discussed.

Aerodynamic heating rate distributions induced by trailing edge controls on hypersonic aircraft configurations at Mach 8

NASA Technical Reports Server (NTRS)

Kaufman, L. G., II; Johnson, C. B.

1984-01-01

Aerodynamic surface heating rate distributions in three dimensional shock wave boundary layer interaction flow regions are presented for a generic set of model configurations representative of the aft portion of hypersonic aircraft. Heat transfer data were obtained using the phase change coating technique (paint) and, at particular spanwise and streamwise stations for sample cases, by the thin wall transient temperature technique (thermocouples). Surface oil flow patterns are also shown. The good accuracy of the detailed heat transfer data, as attested in part by their repeatability, is attributable partially to the comparatively high temperature potential of the NASA-Langley Mach 8 Variable Density Tunnel. The data are well suited to help guide heating analyses of Mach 8 aircraft, and should be considered in formulating improvements to empiric analytic methods for calculating heat transfer rate coefficient distributions.

A Review of the NASA Textile Composites Research

NASA Technical Reports Server (NTRS)

Poe, C. C., Jr.; Dexter, H. B.; Raju, I. S.

1997-01-01

During the past 15 years NASA has taken the lead role in exploiting the benefits of textile reinforced composite materials for application to aircraft structures. The NASA Advanced Composites Technology (ACT) program was started in 1989 to develop composite primary structures for commercial transport airplanes with costs that are competitive with metal structures. As part of this program, several contractors investigated the cost, weight, and performance attributes of textile reinforced composites. Textile composites made using resin transfer molding type processes were evaluated for numerous applications. Methods were also developed to predict resin infiltration and flow in textile preforms and to predict and measure mechanical properties of the textile composites. This paper describes the salient results of that program.

The aerial relay system: An energy-efficient solution to the airport congestion problem

NASA Technical Reports Server (NTRS)

Kyser, A. C.

1980-01-01

The ability to transfer airline passengers between aircraft in flight, if adequately developed and integrated into the national air transportation system, could provide significant improvements in transportation-system performance, in terms of airport congestion, fuel consumption, and passenger service. The proposed Aerial Relay System concept, which was developed as a means of exploiting inflight transfer, makes use of large 'cruise liner' aircraft which fly continuously along their routes, docking periodically with short-haul feeder aircraft for exchange of payloads. Preliminary vehicle designs for a representative system are described and the operational feasibility of the concept for the United States in the 1990's is discussed.

Charging system using solar panels and a highly resonant wireless power transfer model for small UAS applications

NASA Astrophysics Data System (ADS)

Hallman, Sydney N.; Huck, Robert C.; Sluss, James J.

2016-05-01

The use of a wireless charging system for small, unmanned aircraft system applications is useful for both military and commercial consumers. An efficient way to keep the aircraft's batteries charged without interrupting flight would be highly marketable. While the general concepts behind highly resonant wireless power transfer are discussed in a few publications, the details behind the system designs are not available even in academic journals, especially in relation to avionics. Combining a highly resonant charging system with a solar panel charging system can produce enough power to extend the flight time of a small, unmanned aircraft system without interruption. This paper provides an overview of a few of the wireless-charging technologies currently available and outlines a preliminary design for an aircraft-mounted battery charging system.

Frequency-response identification of XV-15 tilt-rotor aircraft dynamics

NASA Technical Reports Server (NTRS)

Tischler, Mark B.

1987-01-01

The timely design and development of the next generation of tilt-rotor aircraft (JVX) depend heavily on the in-depth understanding of existing XV-15 dynamics and the availability of fully validated simulation models. Previous studies have considered aircraft and simulation trim characteristics, but analyses of basic flight vehicle dynamics were limited to qualitative pilot evaluation. The present study has the following objectives: documentation and evaluation of XV-15 bare-airframe dynamics; comparison of aircraft and simulation responses; and development of a validated transfer-function description of the XV-15 needed for future studies. A nonparametric frequency-response approach is used which does not depend on assumed model order or structure. Transfer-function representations are subsequently derived which fit the frequency responses in the bandwidth of greatest concern for piloted handling-qualities and control-system applications.

Visualization techniques to experimentally model flow and heat transfer in turbine and aircraft flow passages

NASA Technical Reports Server (NTRS)

Russell, Louis M.; Hippensteele, Steven A.

1991-01-01

Increased attention to fuel economy and increased thrust requirements have increased the demand for higher aircraft gas turbine engine efficiency through the use of higher turbine inlet temperatures. These higher temperatures increase the importance of understanding the heat transfer patterns which occur throughout the turbine passages. It is often necessary to use a special coating or some form of cooling to maintain metal temperatures at a level which the metal can withstand for long periods of time. Effective cooling schemes can result in significant fuel savings through higher allowable turbine inlet temperatures and can increase engine life. Before proceeding with the development of any new turbine it is economically desirable to create both mathematical and experimental models to study and predict flow characteristics and temperature distributions. Some of the methods are described used to physically model heat transfer patterns, cooling schemes, and other complex flow patterns associated with turbine and aircraft passages.

Estimation of Handling Qualities Parameters of the Tu-144 Supersonic Transport Aircraft from Flight Test Data

NASA Technical Reports Server (NTRS)

Curry, Timothy J.; Batterson, James G. (Technical Monitor)

2000-01-01

Low order equivalent system (LOES) models for the Tu-144 supersonic transport aircraft were identified from flight test data. The mathematical models were given in terms of transfer functions with a time delay by the military standard MIL-STD-1797A, "Flying Qualities of Piloted Aircraft," and the handling qualities were predicted from the estimated transfer function coefficients. The coefficients and the time delay in the transfer functions were estimated using a nonlinear equation error formulation in the frequency domain. Flight test data from pitch, roll, and yaw frequency sweeps at various flight conditions were used for parameter estimation. Flight test results are presented in terms of the estimated parameter values, their standard errors, and output fits in the time domain. Data from doublet maneuvers at the same flight conditions were used to assess the predictive capabilities of the identified models. The identified transfer function models fit the measured data well and demonstrated good prediction capabilities. The Tu-144 was predicted to be between level 2 and 3 for all longitudinal maneuvers and level I for all lateral maneuvers. High estimates of the equivalent time delay in the transfer function model caused the poor longitudinal rating.

The aircraft as an instrument of self destruction.

DOT National Transportation Integrated Search

1973-03-01

Often the relationship between the pilot and his aircraft is such that the aircraft may be thought of as an extension of the pilot himself during the act of flight. If this pilot accumulates stress in his life with which he can no longer adequately c...

17 CFR 256.310 - Aircraft and airport equipment.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 17 Commodity and Securities Exchanges 3 2011-04-01 2011-04-01 false Aircraft and airport equipment. 256.310 Section 256.310 Commodity and Securities Exchanges SECURITIES AND EXCHANGE COMMISSION... UTILITY HOLDING COMPANY ACT OF 1935 Service Company Property Accounts § 256.310 Aircraft and airport...

17 CFR 256.310 - Aircraft and airport equipment.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 17 Commodity and Securities Exchanges 3 2010-04-01 2010-04-01 false Aircraft and airport equipment. 256.310 Section 256.310 Commodity and Securities Exchanges SECURITIES AND EXCHANGE COMMISSION... UTILITY HOLDING COMPANY ACT OF 1935 Service Company Property Accounts § 256.310 Aircraft and airport...

UAS Integration into the NAS: Unmanned Aircraft System (UAS) Delegation of Separation

NASA Technical Reports Server (NTRS)

Fern, Lisa Carolynn; Kenny, Caitlin Ailis

2012-01-01

FAA Modernization and Reform Act of 2012 mandates UAS integration in the NAS by 2015. Operators must be able to safely maneuver UAS to maintain separation and collision avoidance. Delegated Separation is defined as the transfer of responsibility for maintaining separation between aircraft or vehicles from the air navigation service provider to the relevant flight operator, and will likely begin in sparsely trafficked areas before moving to more heavily populated airspace. As UAS operate primarily in areas with lower traffic density and perform maneuvers routinely that are currently managed through special handling, they have the advantage of becoming an early adopter of delegated separation. This experiment will examine if UAS are capable of performing delegated separation in 5 nm horizontal and 1000 ft vertical distances under two delegation conditions. In Extended Delegation, ATC are in charge of identifying problems and delegating to pilot identification and implementation of the solution and monitoring. In Full Delegation, the pilots are responsible for all tasks related to separation assurance: identification of problems and solutions, implementation and monitoring.

Performance of resin transfer molded multiaxial warp knit composites

NASA Technical Reports Server (NTRS)

Dexter, H. Benson; Hasko, Gregory H.

1993-01-01

Composite materials that are subjected to complex loads have traditionally been fabricated with multidirectionally oriented prepreg tape materials. Some of the problems associated with this type of construction include low delamination resistance, poor out-of-plane strength, and labor intensive fabrication processes. Textile reinforced composites with through-the-thickness reinforcement have the potential to solve some of these problems. Recently, a relatively new class of noncrimp fabrics designated as multiaxial warp knits have been developed to minimize some of the high cost and damage tolerance concerns. Multiple stacks of warp knit fabrics can be knitted or stitched together to reduce layup labor cost. The through-the-thickness reinforcement can provide significant improvements in damage tolerance and out-of-plane strength. Multilayer knitted/stitched preforms, in conjunction with resin transfer molding (RTM), offer potential for significant cost savings in fabrication of primary aircraft structures. The objectives of this investigation were to conduct RTM processing studies and to characterize the mechanical behavior of composites reinforced with three multiaxial warp knit fabrics. The three fabrics investigated were produced by Hexcel and Milliken in the United States, and Saerbeck in Germany. Two resin systems, British Petroleum E9O5L and 3M PR 500, were characterized for RTM processing. The performance of Hexcel and Milliken quasi-isotropic knitted fabrics are compared to conventional prepreg tape laminates. The performance of the Saerbeck fabric is compared to uniweave wing skin layups being investigated by Douglas Aircraft Company in the NASA Advanced Composites Technology (ACT) program. Tests conducted include tension, open hole tension, compression, open hole compression, and compression after impact. The effects of fabric defects, such as misaligned fibers and gaps between tows, on material performance are also discussed. Estimated material and labor cost savings are projected for the Saerbeck fabric as compared to uniweave fabric currently being used by Douglas in the NASA ACT wing development program.

Service life evaluation of rigid explosive transfer lines

NASA Technical Reports Server (NTRS)

Bement, L. J.; Kayser, E. G.; Schimmel, M. L.

1983-01-01

This paper describes a joint Army/NASA-sponsored research program on the service life evaluation of rigid explosive transfer lines. These transfer lines are used to initiate emergency crew escape functions on a wide variety of military and NASA aircraft. The purpose of this program was to determine quantitatively the effects of service, age, and degradation on rigid explosive transfer lines to allow responsible, conservative, service life determination. More than 800 transfer lines were removed from the U.S. Army AH-1G and AH-1S, the U.S. Air Force B-1 and F-111, and the U.S. Navy F-14 aircraft for testing. The results indicated that the lines were not adversely affected by age, service, or a repeat of the thermal qualification tests on full-service lines. Extension of the service life of rigid explosive transfer lines should be considered, since considerable cost savings could be realized with no measurable decrease in system reliability.

Aeromedical transfer of women at risk of preterm delivery in remote and rural Western Australia: why are there no births in flight?

PubMed

Akl, Natalie; Coghlan, Edwina A; Nathan, Elizabeth A; Langford, Stephen A; Newnham, John P

2012-08-01

For more than three decades, women at imminent risk of preterm birth (PTB) in Western Australia have been transferred by small aircraft over long distances to the single tertiary level perinatal centre in Perth, with no known case of birth during the flight. We aimed to review recent experience to understand how aircraft travel may delay PTB. Retrospective observational study of 500 consecutive Royal Flying Doctor Service (RFDS) transfers of women at risk of preterm labour to the tertiary referral centre, from September 2007 to December 31, 2009. In-flight delivery, complications associated with transfer and factors associated with delay in preterm delivery. There were no in-flight deliveries or serious complications associated with the aeromedical transfer of these patients. In a multivariable Cox proportional hazards regression analysis, clinical factors in the presentation that were associated with a shorter time from landing to subsequent delivery included cervical dilatation ≥ 4 cm, ruptured membranes, gestational age > 32 weeks and nulliparity. The aircraft reaching an ambient altitude > 14,000 feet, or cabin altitude above zero (sea level), was associated with a delay in time from landing to delivery for women who were not in spontaneous preterm labour. Our findings add to a 30-year experience that women at risk of preterm labour do not deliver during aeromedical transfer. Ambient and cabin altitude of the aircraft were associated with an extension in the time to delivery after arrival. The mechanisms underpinning this effect warrant further investigation. © 2012 The Authors ANZJOG © 2012 The Royal Australian and New Zealand College of Obstetricians and Gynaecologists.

14 CFR 61.117 - Private pilot privileges and limitations: Second in command of aircraft requiring more than one...

Code of Federal Regulations, 2012 CFR

2012-01-01

...: Second in command of aircraft requiring more than one pilot. 61.117 Section 61.117 Aeronautics and Space... limitations: Second in command of aircraft requiring more than one pilot. Except as provided in § 61.113 of this part, no private pilot may, for compensation or hire, act as second in command of an aircraft that...

14 CFR 61.117 - Private pilot privileges and limitations: Second in command of aircraft requiring more than one...

Code of Federal Regulations, 2014 CFR

2014-01-01

...: Second in command of aircraft requiring more than one pilot. 61.117 Section 61.117 Aeronautics and Space... limitations: Second in command of aircraft requiring more than one pilot. Except as provided in § 61.113 of this part, no private pilot may, for compensation or hire, act as second in command of an aircraft that...

14 CFR 61.117 - Private pilot privileges and limitations: Second in command of aircraft requiring more than one...

Code of Federal Regulations, 2011 CFR

2011-01-01

...: Second in command of aircraft requiring more than one pilot. 61.117 Section 61.117 Aeronautics and Space... limitations: Second in command of aircraft requiring more than one pilot. Except as provided in § 61.113 of this part, no private pilot may, for compensation or hire, act as second in command of an aircraft that...

14 CFR 61.117 - Private pilot privileges and limitations: Second in command of aircraft requiring more than one...

Code of Federal Regulations, 2010 CFR

2010-01-01

...: Second in command of aircraft requiring more than one pilot. 61.117 Section 61.117 Aeronautics and Space... limitations: Second in command of aircraft requiring more than one pilot. Except as provided in § 61.113 of this part, no private pilot may, for compensation or hire, act as second in command of an aircraft that...

14 CFR 61.117 - Private pilot privileges and limitations: Second in command of aircraft requiring more than one...

Code of Federal Regulations, 2013 CFR

2013-01-01

...: Second in command of aircraft requiring more than one pilot. 61.117 Section 61.117 Aeronautics and Space... limitations: Second in command of aircraft requiring more than one pilot. Except as provided in § 61.113 of this part, no private pilot may, for compensation or hire, act as second in command of an aircraft that...

76 FR 58857 - Privacy Act of 1974: System of Records

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-22

... Management, Room W12-140, 1200 New Jersey Ave., SE., Washington, DC 20590. Instructions: All submissions... system of records to the Office of Management and Budget and to Congress. SYSTEM OF RECORDS DOT/ALL-23.... [cir] Aircraft model code. [cir] Aircraft style code. [cir] Aircraft tail number. Attachment: [cir...

14 CFR 13.19 - Certificate action.

Code of Federal Regulations, 2014 CFR

2014-01-01

... any civil airman. Under section 501(e) of the FA Act, any Certificate of Aircraft Registration may be... revoking that certificate. This authority as to aircraft found ineligible for registration is also... Aircraft Registration is affected by an order issued under this section. [Doc. No. 13-14, 44 FR 63723, Nov...

14 CFR 13.19 - Certificate action.

Code of Federal Regulations, 2012 CFR

2012-01-01

... any civil airman. Under section 501(e) of the FA Act, any Certificate of Aircraft Registration may be... revoking that certificate. This authority as to aircraft found ineligible for registration is also... Aircraft Registration is affected by an order issued under this section. [Doc. No. 13-14, 44 FR 63723, Nov...

14 CFR 13.19 - Certificate action.

Code of Federal Regulations, 2013 CFR

2013-01-01

... any civil airman. Under section 501(e) of the FA Act, any Certificate of Aircraft Registration may be... revoking that certificate. This authority as to aircraft found ineligible for registration is also... Aircraft Registration is affected by an order issued under this section. [Doc. No. 13-14, 44 FR 63723, Nov...

Comparison of the Invasion of Crete and the Proposed Invasion in Malta

DTIC Science & Technology

2006-01-01

North Africa for Rommel’s upcoming offensive codenamed “ Theseus .”71 These transfers reflected the strategic and operational focus of the German High... Theseus II Luftflotte transferred 260 aircraft to North Africa. This left 115 aircraft in Sicily to work with the Italians to hinder the British... Theseus was completed. The next day another message was issued saying that Hercules was “suspended until further notice” and “if a deadline for the

Modeling procedures for handling qualities evaluation of flexible aircraft

NASA Technical Reports Server (NTRS)

Govindaraj, K. S.; Eulrich, B. J.; Chalk, C. R.

1981-01-01

This paper presents simplified modeling procedures to evaluate the impact of flexible modes and the unsteady aerodynamic effects on the handling qualities of Supersonic Cruise Aircraft (SCR). The modeling procedures involve obtaining reduced order transfer function models of SCR vehicles, including the important flexible mode responses and unsteady aerodynamic effects, and conversion of the transfer function models to time domain equations for use in simulations. The use of the modeling procedures is illustrated by a simple example.

A study of interior noise levels, noise sources and transmission paths in light aircraft

NASA Technical Reports Server (NTRS)

Hayden, R. E.; Murray, B. S.; Theobald, M. A.

1983-01-01

The interior noise levels and spectral characteristics of 18 single-and twin-engine propeller-driven light aircraft, and source-path diagnosis of a single-engine aircraft which was considered representative of a large part of the fleet were studied. The purpose of the flight surveys was to measure internal noise levels and identify principal noise sources and paths under a carefully controlled and standardized set of flight procedures. The diagnostic tests consisted of flights and ground tests in which various parts of the aircraft, such as engine mounts, the engine compartment, exhaust pipe, individual panels, and the wing strut were instrumented to determine source levels and transmission path strengths using the transfer function technique. Predominant source and path combinations are identified. Experimental techniques are described. Data, transfer function calculations to derive source-path contributions to the cabin acoustic environment, and implications of the findings for noise control design are analyzed.

A study for active control research and validation using the Total In-Flight Simulator (TIFS) aircraft

NASA Technical Reports Server (NTRS)

Chen, R. T. N.; Daughaday, H.; Andrisani, D., II; Till, R. D.; Weingarten, N. C.

1975-01-01

The results of a feasibility study and preliminary design for active control research and validation using the Total In-Flight Simulator (TIFS) aircraft are documented. Active control functions which can be demonstrated on the TIFS aircraft and the cost of preparing, equipping, and operating the TIFS aircraft for active control technology development are determined. It is shown that the TIFS aircraft is as a suitable test bed for inflight research and validation of many ACT concepts.

Benefit and impact of the Arizona land-use experiment: Executive summary

NASA Technical Reports Server (NTRS)

Goodwin, G.

1977-01-01

The benefits and impact of the Arizona Land-Use Experiment on the people of Arizona are examined along with the process of the technology transfer to the political and private sector of the Arizona community. Since the remotely-sensed data in use in Arizona consisted of a blend of spacecraft and aircraft information, it was hoped that the role of the aircraft in the transfer process would be identified and its benefit be determined in a real-world situation. In addition, the role of the institutional arrangements set up in Arizona to facilitate the transfer of remotely-sensed information to the user community was examined.

Future Integrated Systems Concept for Preventing Aircraft Loss-of-Control Accidents

NASA Technical Reports Server (NTRS)

Belcastro, Christine M.; Jacobson, Steven r.

2010-01-01

Loss of control remains one of the largest contributors to aircraft fatal accidents worldwide. Aircraft loss-of-control accidents are highly complex in that they can result from numerous causal and contributing factors acting alone or (more often) in combination. Hence, there is no single intervention strategy to prevent these accidents. This paper presents future system concepts and research directions for preventing aircraft loss-of-control accidents.

Analysis of Asymmetric Aircraft Aerodynamics Due to an Experimental Wing Glove

NASA Technical Reports Server (NTRS)

Hartshorn, Fletcher

2011-01-01

Aerodynamic computational fluid dynamics analysis of a wing glove attached to one wing of a business jet is presented and discussed. A wing glove placed on only one wing will produce asymmetric aerodynamic effects that will result in overall changes in the forces and moments acting on the aircraft. These changes, referred to as deltas, need to be determined and quantified to ensure that the wing glove does not have a significant effect on the aircraft flight characteristics. TRANAIR (Calmar Research Corporation, Cato, New York), a nonlinear full potential solver, and Star-CCM+ (CD-adapco, Melville, New York), a finite volume full Reynolds-averaged Navier-Stokes computational fluid dynamics solver, are used to analyze a full aircraft with and without the glove at a variety of flight conditions, aircraft configurations, and angles of attack and sideslip. Changes in the aircraft lift, drag, and side force along with roll, pitch, and yaw are presented. Span lift and moment distributions are also presented for a more detailed look at the effects of the glove on the aircraft. Aerodynamic flow phenomena due to the addition of the glove are discussed. Results show that the glove produces only small changes in the aerodynamic forces and moments acting on the aircraft, most of which are insignificant.

14 CFR 61.89 - General limitations.

Code of Federal Regulations, 2010 CFR

2010-01-01

... more than one pilot is required by the type certificate of the aircraft or regulations under which the... pilot seeking a sport pilot certificate must comply with the provisions of paragraphs (a) and (b) of this section and may not act as pilot in command— (1) Of an aircraft other than a light-sport aircraft...

78 FR 9789 - Airworthiness Directives; Schweizer Aircraft Corporation

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-12

... Certification Office, Engine & Propeller Directorate, 1600 Stewart Ave., suite 410, Westbury, NY 11590... inspection panel kit and stabilizer mount doublers. The Type Certificate for these helicopters transferred...: Stephen Kowalski, Aviation Safety Engineer, New York Aircraft Certification Office, Engine & Propeller...

Modeling Programs Increase Aircraft Design Safety

NASA Technical Reports Server (NTRS)

2012-01-01

Flutter may sound like a benign word when associated with a flag in a breeze, a butterfly, or seaweed in an ocean current. When used in the context of aerodynamics, however, it describes a highly dangerous, potentially deadly condition. Consider the case of the Lockheed L-188 Electra Turboprop, an airliner that first took to the skies in 1957. Two years later, an Electra plummeted to the ground en route from Houston to Dallas. Within another year, a second Electra crashed. In both cases, all crew and passengers died. Lockheed engineers were at a loss as to why the planes wings were tearing off in midair. For an answer, the company turned to NASA s Transonic Dynamics Tunnel (TDT) at Langley Research Center. At the time, the newly renovated wind tunnel offered engineers the capability of testing aeroelastic qualities in aircraft flying at transonic speeds near or just below the speed of sound. (Aeroelasticity is the interaction between aerodynamic forces and the structural dynamics of an aircraft or other structure.) Through round-the-clock testing in the TDT, NASA and industry researchers discovered the cause: flutter. Flutter occurs when aerodynamic forces acting on a wing cause it to vibrate. As the aircraft moves faster, certain conditions can cause that vibration to multiply and feed off itself, building to greater amplitudes until the flutter causes severe damage or even the destruction of the aircraft. Flutter can impact other structures as well. Famous film footage of the Tacoma Narrows Bridge in Washington in 1940 shows the main span of the bridge collapsing after strong winds generated powerful flutter forces. In the Electra s case, faulty engine mounts allowed a type of flutter known as whirl flutter, generated by the spinning propellers, to transfer to the wings, causing them to vibrate violently enough to tear off. Thanks to the NASA testing, Lockheed was able to correct the Electra s design flaws that led to the flutter conditions and return the aircraft to safe flight. Today, all aircraft must have a flutter boundary 15 percent beyond the aircraft s expected maximum speed to ensure that flutter conditions are not encountered in flight. NASA continues to support research in new aircraft designs to improve knowledge of aeroelasticity and flutter. Through platforms such as Dryden Flight Research Center s Active Aeroelastic Wing (AAW) research aircraft, the Agency researches methods for in-flight validation of predictions and for controlling and taking advantage of aeroelastic conditions to enhance aircraft performance.

A survey of new technology for cockpit application to 1990's transport aircraft simulators

NASA Technical Reports Server (NTRS)

Holt, A. P., Jr.; Noneaker, D. O.; Walthour, L.

1980-01-01

Two problems were investigated: inter-equipment data transfer, both on board the aircraft and between air and ground; and crew equipment communication via the cockpit displays and controls. Inter-equipment data transfer is discussed in terms of data bus and data link requirements. Crew equipment communication is discussed regarding the availability of CRT display systems for use in research simulators to represent flat panel displays of the future, and of software controllable touch panels.

Dynamics of the aircraft in a vortex wake

NASA Astrophysics Data System (ADS)

Gaifullin, A. M.; Sviridenko, Yu N.

2018-03-01

This paper considers the aerodynamics and the dynamics of an aircraft on various modes when the aircraft enters a strongly swirling flow. This is the case when an aircraft purposefully enters the jet-vortex wake of another aircraft in the course of in-flight refuelling, when an aircraft is flying in the trail of an aircraft carrier during landing, or when an aircraft accidentally enters other aircrafts’ vortex wakes. These situations, according to pilots’ evaluation, are the most dangerous and the most difficult modes for piloting. That is why their real time modelling on flight simulators has taken on particular importance. This article provides the algorithms and methodology of mathematical modelling of aerodynamic forces and moments which act upon an aircraft in vortex wakes.

Spectrometry of linear energy transfer and dosimetry measurements onboard spacecrafts and aircrafts

NASA Astrophysics Data System (ADS)

Spurný, F.; Ploc, O.; Jadrníčková, I.

2009-01-01

There are only a few methods of dosimetry which can estimate the contribution of different particles to onboard spacecraft and/or aircraft exposure. This contribution describes an attempt to estimate the contribution of different components to the exposure level using MDU-Liulin energy deposition spectrometer and thermoluminescent detectors (TLD’s), in combination with a spectrometer of linear energy transfer (LET) based on track etch detectors. This equipment was exposed onboard: the International Space Station for a long period and two shorter shuttle missions and a commercial subsonic aircraft for several long-term monitoring periods from 2001 to 2006. The data obtained are analyzed from several points of view and the obtained results are presented, analyzed, and discussed.

Aerodynamics of heat exchangers for high-altitude aircraft

NASA Technical Reports Server (NTRS)

Drela, Mark

1996-01-01

Reduction of convective beat transfer with altitude dictates unusually large beat exchangers for piston- engined high-altitude aircraft The relatively large aircraft drag fraction associated with cooling at high altitudes makes the efficient design of the entire heat exchanger installation an essential part of the aircraft's aerodynamic design. The parameters that directly influence cooling drag are developed in the context of high-altitude flight Candidate wing airfoils that incorporate heat exchangers are examined. Such integrated wing-airfoil/heat-exchanger installations appear to be attractive alternatives to isolated heat.exchanger installations. Examples are drawn from integrated installations on existing or planned high-altitude aircraft.

Air-ground information transfer in the National Airspace System

NASA Technical Reports Server (NTRS)

Lee, Alfred T.; Lozito, Sandra

1989-01-01

This paper reviews NASA's Aviation Safety Reporting System incident data for a two-year period in order to identify the frequency of air-ground information transfer errors and the factors associated with their occurrence. Of the more than 14,000 primary reports received during the 1985 and 1986 reporting period, one out of four reports concerned problems of information transfer between aircraft and ATC. Approximately half of these errors were associated directly or indirectly with aircraft deviations from assigned heading or altitude. The majority of incidents cited some human-system problem such as workload, cockpit distractions, etc., as the primary contributing factor. Improvements in air-ground information transfer using existing and future (e.g., data link) technology are proposed centering on the development and application of user-centered information management principles.

DEVELOPMENT OF A SUPERSONIC TRANSPORT AIRCRAFT ENGINE - PHASE II-A.

DTIC Science & Technology

JET TRANSPORT PLANES, *SUPERSONIC AIRCRAFT ) (U) TURBOJET ENGINES , PERFORMANCE( ENGINEERING ), TURBOFAN ENGINES , AFTERBURNING, SPECIFICATIONS...COMPRESSORS, GEOMETRY, TURBOJET INLETS, COMBUSTION, TEST EQUIPMENT, TURBINE BLADES , HEAT TRANSFER, AIRFOILS , CASCADE STRUCTURES, EVAPOTRANSPIRATION, PLUG NOZZLES, ANECHOIC CHAMBERS, BEARINGS, SEALS, DESIGN, FATIGUE(MECHANICS)

Experimental StudyHigh Altitude Forced Convective Cooling of Electromechanical Actuation Systems

DTIC Science & Technology

2016-01-01

experimental validation at altitudes above 16,000 feet, relevant to commercial and military aircraft. The convective heat transfer coefficient at altitudes...and natural occurring phenomena. Figure 1.3 also shows that a typical flight ceiling for commercial and military air breathing aircraft is about...However, they have not been extensively vetted in atmospheric conditions experienced by commercial and tactical military aircraft. 1.3 Purpose

47 CFR 32.6113 - Aircraft expense.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 47 Telecommunication 2 2010-10-01 2010-10-01 false Aircraft expense. 32.6113 Section 32.6113 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) COMMON CARRIER SERVICES UNIFORM SYSTEM OF ACCOUNTS... account for amounts transferred to Construction and/or to other Plant Specific Operations Expense accounts...

47 CFR 32.6113 - Aircraft expense.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 47 Telecommunication 2 2011-10-01 2011-10-01 false Aircraft expense. 32.6113 Section 32.6113 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) COMMON CARRIER SERVICES UNIFORM SYSTEM OF ACCOUNTS... account for amounts transferred to Construction and/or to other Plant Specific Operations Expense accounts...

Numerical Simulation of Internal Heat Transfer Phenomena Occurring During De-Icing of Aircraft Components

NASA Technical Reports Server (NTRS)

DeWitt, Keneth J.

1996-01-01

An experimental study to determine the convective heat transfer coefficient from castings made from ice-roughened plates is reported. A corresponding topic, 'Measurements of the Convective Heat Transfer Coefficient from Ice Roughened Surfaces in Parallel and Accelerated Flows,' is presented.

15 CFR 740.15 - Aircraft and vessels (AVS).

Code of Federal Regulations, 2011 CFR

2011-01-01

... transfer of technology. No technology is transferred to a national of a destination in Country Group E:1... destination in Country Group E:1 (see supplement No. 1 to this part); (vi) Technology is not transferred to a... destination in Country Group E:1 (see supplement No. 1 to this part); (vi) Technology is not transferred to a...

43 CFR 4740.1 - Use of motor vehicles or aircraft.

Code of Federal Regulations, 2012 CFR

2012-10-01

... administration of the Act, except that no motor vehicle or aircraft, other than helicopters, shall be used for... be conducted in a humane manner. (b) Before using helicopters or motor vehicles in the management of...

43 CFR 4740.1 - Use of motor vehicles or aircraft.

Code of Federal Regulations, 2013 CFR

2013-10-01

... administration of the Act, except that no motor vehicle or aircraft, other than helicopters, shall be used for... be conducted in a humane manner. (b) Before using helicopters or motor vehicles in the management of...

43 CFR 4740.1 - Use of motor vehicles or aircraft.

Code of Federal Regulations, 2011 CFR

2011-10-01

... administration of the Act, except that no motor vehicle or aircraft, other than helicopters, shall be used for... be conducted in a humane manner. (b) Before using helicopters or motor vehicles in the management of...

43 CFR 4740.1 - Use of motor vehicles or aircraft.

Code of Federal Regulations, 2014 CFR

2014-10-01

... administration of the Act, except that no motor vehicle or aircraft, other than helicopters, shall be used for... be conducted in a humane manner. (b) Before using helicopters or motor vehicles in the management of...

14 CFR 375.33 - Transit flights, irregular operations.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Transit flights, irregular operations. 375... Authorized Operations § 375.33 Transit flights, irregular operations. Foreign civil aircraft carrying... mail are transferred to another aircraft. Flights involving stops under such circumstances may, however...

14 CFR 375.33 - Transit flights, irregular operations.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Transit flights, irregular operations. 375... Authorized Operations § 375.33 Transit flights, irregular operations. Foreign civil aircraft carrying... mail are transferred to another aircraft. Flights involving stops under such circumstances may, however...

14 CFR 375.33 - Transit flights, irregular operations.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Transit flights, irregular operations. 375... Authorized Operations § 375.33 Transit flights, irregular operations. Foreign civil aircraft carrying... mail are transferred to another aircraft. Flights involving stops under such circumstances may, however...

14 CFR 375.33 - Transit flights, irregular operations.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Transit flights, irregular operations. 375... Authorized Operations § 375.33 Transit flights, irregular operations. Foreign civil aircraft carrying... mail are transferred to another aircraft. Flights involving stops under such circumstances may, however...

The algorithmic details of polynomials application in the problems of heat and mass transfer control on the hypersonic aircraft permeable surfaces

NASA Astrophysics Data System (ADS)

Bilchenko, G. G.; Bilchenko, N. G.

2018-03-01

The hypersonic aircraft permeable surfaces heat and mass transfer effective control mathematical modeling problems are considered. The analysis of the control (the blowing) constructive and gasdynamical restrictions is carried out for the porous and perforated surfaces. The functions classes allowing realize the controls taking into account the arising types of restrictions are suggested. Estimates of the computational complexity of the W. G. Horner scheme application in the case of using the C. Hermite interpolation polynomial are given.

Transient analysis of energy Transfer Control (ECT) and compressor bleed concepts of remote lift fan control

NASA Technical Reports Server (NTRS)

Sellers, J. F.

1973-01-01

The transient performance of two concepts for control of vertical takeoff aircraft remote lift fans is analyzed and discussed. Both concepts employ flow transfer between pairs of lift fans located in separate parts of the aircraft in order to obtain attitude control moments for hover and low-speed flight. The results presented are from a digital computer, dynamic analysis of the YJ97/LF460 remote drive turbofan. The transient responses of the two systems are presented for step demands in lift and moment.

Conducting Studies of Transfer of Learning: A Practical Guide

DTIC Science & Technology

1982-01-01

X) = percent transfer (If learning C where: Kall aicrage of grades assigned to experimental :.ttmdents for p~erformlanlce in the aircraft. an average...effectiveness. Human Factors. 1971 . 13(6). 561-567. Roscoe, S.N. A little more on incremental transfer effectiveness. Human Factors. 1972, 14(4), 363-364

Unsafe acts and unsafe outcomes in aircraft maintenance

NASA Technical Reports Server (NTRS)

Hobbs, Alan; Williamson, Ann

2002-01-01

Road safety studies using the Driver Behaviour Questionnaire (DBQ) have provided support for a three-way distinction between violations, skill-based errors and mistakes, and have indicated that a tendency to commit driving violations is associated with an increased risk of accident involvement. The aims of this study were to examine whether the three-way distinction of unsafe acts is applicable in the context of aircraft maintenance, and whether involvement in maintenance safety occurrences can be predicted on the basis of self-reported unsafe acts. A Maintenance Behaviour Questionnaire (MBQ) was developed to explore patterns of unsafe acts committed by aircraft maintenance mechanics. The MBQ was completed anonymously by over 1300 Australian aviation mechanics, who also provided information on their involvement in workplace accidents and incidents. Four factors were identified: routine violations, skill-based errors, mistakes and exceptional violations. Violations and mistakes were related significantly to the occurrence of incidents that jeopardized the quality of aircraft maintenance, but were not related to workplace injuries. Skill-based errors, while not related to work quality incidents, were related to workplace injuries. The results are consistent with the three-way typology of unsafe acts described by Reason et al. (1990) and with the DBQ research indicating an association between self-reported violations and accidents. The current findings suggest that interventions addressed at maintenance quality incidents should take into account the role of violations and mistakes, and the factors that promote them. In contrast, interventions directed at reducing workplace injury are likely to require a focus on skill-based errors.

EPA Collaboration on International Air Pollution Standards for Aircraft

EPA Pesticide Factsheets

EPA has collaborated with the United Nation’s International Civil Aviation Organization (ICAO) to set a timeframe for initiating the U.S. domestic regulatory process for addressing greenhouse gas emissions from aircraft under the Clean Air Act.

An Extensible, Interchangeable and Sharable Database Model for Improving Multidisciplinary Aircraft Design

NASA Technical Reports Server (NTRS)

Lin, Risheng; Afjeh, Abdollah A.

2003-01-01

Crucial to an efficient aircraft simulation-based design is a robust data modeling methodology for both recording the information and providing data transfer readily and reliably. To meet this goal, data modeling issues involved in the aircraft multidisciplinary design are first analyzed in this study. Next, an XML-based. extensible data object model for multidisciplinary aircraft design is constructed and implemented. The implementation of the model through aircraft databinding allows the design applications to access and manipulate any disciplinary data with a lightweight and easy-to-use API. In addition, language independent representation of aircraft disciplinary data in the model fosters interoperability amongst heterogeneous systems thereby facilitating data sharing and exchange between various design tools and systems.

Lewis Rodert Receiving a Collier Trophy from President Truman

NASA Image and Video Library

1947-12-21

Lewis Rodert, then of the National Advisory Committee for Aeronautics (NACA) Lewis Flight Propulsion Laboratory, receives the Collier Trophy from President Harry Truman for his work in the design and development of an ice prevention system for aircraft. The accumulation of ice on an aircraft had been a critical issue for years. Rodert developed a method of transferring engine heat to the wings and other vulnerable components to prevent ice buildup. Rodert began his icing investigations at Langley Memorial Aeronautical Laboratory in 1936. The NACA ordered a Lockheed 12A aircraft to be built using Rodert’s deicing system. The aircraft successfully flew through icing conditions during the following winter. Soon thereafter the military incorporated the system into a Consolidated B-24D Liberator and several other military aircraft, including a North American XB-25F. Rodert and the NACA icing program transferred to the Lewis lab in Cleveland in 1946. In Cleveland, the focus turned to the study of cloud composition and the causes of icing. Rodert’s role at Lewis diminished over the ensuing years. Rodert was honored in 1947 for his Collier Trophy at ceremonies at Langley, Ames, and then finally Lewis.

Mission management aircraft operations manual

NASA Technical Reports Server (NTRS)

1992-01-01

This manual prescribes the NASA mission management aircraft program and provides policies and criteria for the safe and economical operation, maintenance, and inspection of NASA mission management aircraft. The operation of NASA mission management aircraft is based on the concept that safety has the highest priority. Operations involving unwarranted risks will not be tolerated. NASA mission management aircraft will be designated by the Associate Administrator for Management Systems and Facilities. NASA mission management aircraft are public aircraft as defined by the Federal Aviation Act of 1958. Maintenance standards, as a minimum, will meet those required for retention of Federal Aviation Administration (FAA) airworthiness certification. Federal Aviation Regulation Part 91, Subparts A and B, will apply except when requirements of this manual are more restrictive.

Navy Nuclear Aircraft Carrier (CVN) Homeporting at Mayport: Background and Issues for Congress

DTIC Science & Technology

2009-09-23

at http://www.defenselink.mil/releases/release.aspx?releaseid= 12600 . 2 The Navy has not identified which specific CVN it would transfer, and a CVN...Determine Aircraft Carrier Homeporting In Mayport,” available online at http://www.defenselink.mil/releases/release.aspx?releaseid= 12600 . 7Although

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.

A survey of heating and turbulent boundary layer characteristics of several hypersonic research aircraft configurations

NASA Technical Reports Server (NTRS)

Lawing, P. L.

1981-01-01

Four of the configurations investigated during a proposed NASA-Langley hypersonic research aircraft program were selected for phase-change-paint heat-transfer testing and forebody boundary layer pitot surveys. In anticipation of future hypersonic aircraft, both published and unpublished data and results are reviewed and presented with the purpose of providing a synoptic heat-transfer data base from the research effort. Engineering heat-transfer predictions are compared with experimental data on both a global and a local basis. The global predictions are shown to be sufficient for purposes of configuration development, and even the local predictions can be adequate when interpreted in light of the proper flow field. In that regard, cross flow in the forebody boundary layers was examined for significant heating and aerodynamic effect on the scramjet engines. A design philosophy which evolved from the research airplane effort is used to design a forebody shape that produces thin, uniform, forebody boundary layers on a hypersonic airbreathing missile. Finally, heating/boundary layer phenomena which are not predictable with state-of-the-art knowledge and techniques are shown and discussed.

Pilot Emergency Tutoring System for F-4 Aircraft Fuel System Malfunction Using Means-Ends Analysis

DTIC Science & Technology

1990-06-01

pulled , and wing transfer pressure is normal. What operator do you choose? For example: type look_at INDICATOR for looked_at(INDICATOR) type set...cb internal wing transfer is pulled , and wing transfer pressure is normal. What operator do you choose? For example: type look_at INDICATOR for...at, external transfer is off, internal wing transfer is stop trans, refuel probe is extended, cb internal wing transfer is pulled ,and wing

27 CFR 28.141 - General.

Code of Federal Regulations, 2012 CFR

2012-04-01

... Exportation, Use as Supplies on Vessels and Aircraft, or Transfer to a Foreign-Trade Zone § 28.141 General. (a...) Transfer to and deposit in a foreign-trade zone for exportation or for storage pending exportation. (b... foreign country; or (2) Transfer to and deposit in a foreign-trade zone for exportation or for storage...

27 CFR 28.141 - General.

Code of Federal Regulations, 2011 CFR

2011-04-01

... Exportation, Use as Supplies on Vessels and Aircraft, or Transfer to a Foreign-Trade Zone § 28.141 General. (a...) Transfer to and deposit in a foreign-trade zone for exportation or for storage pending exportation. (b... foreign country; or (2) Transfer to and deposit in a foreign-trade zone for exportation or for storage...

Technology transfer and other public policy implications of multi-national arrangements for the production of commercial airframes

NASA Technical Reports Server (NTRS)

Gellman, A. J.; Price, J. P.

1978-01-01

A study to examine the question of technology transfer through international arrangements for production of commercial transport aircraft is presented. The likelihood of such transfer under various representative conditions was determined and an understanding of the economic motivations for, effects of, joint venture arrangements was developed. Relevant public policy implications were also assessed. Multinational consortia with U.S. participation were focused upon because they generate the full range of pertinent public issues (including especially technology transfer), and also because of recognized trends toward such arrangements. An extensive search and analysis of existing literature to identify the key issues, and in-person interviews with executives of U.S. and European commercial airframe producers was reviewed. Distinctions were drawn among product-embodied, process, and management technologies in terms of their relative possibilities of transfer and the significance of such transfer. Also included are observations on related issues such as the implications of U.S. antitrust policy with respect to the formation of consortia and the competitive viability of the U.S. aircraft manufacturing industry.

ED11-0072-14

NASA Image and Video Library

2011-03-11

NASA’s Subsonic Research Aircraft Testbed, or SCRAT, is a modified Gulfstream III that operates out of Armstrong Flight Research Center in Edwards, California. SCRAT the test bed aircraft for the ACTE flexible-flap research project, which examines flexible wing flap technology’s benefits to aerodynamic efficiency.

Study of a fail-safe abort system for an actively cooled hypersonic aircraft: Computer program documentation

NASA Technical Reports Server (NTRS)

Haas, L. A., Sr.

1976-01-01

The Fail-Safe Abort System TEMPerature Analysis Program, (FASTEMP), user's manual is presented. This program was used to analyze fail-safe abort systems for an actively cooled hypersonic aircraft. FASTEMP analyzes the steady state or transient temperature response of a thermal model defined in rectangular, cylindrical, conical and/or spherical coordinate system. FASTEMP provides the user with a large selection of subroutines for heat transfer calculations. The various modes of heat transfer available from these subroutines are: heat storage, conduction, radiation, heat addition or generation, convection, and fluid flow.

Scale-model charge-transfer technique for measuring enhancement factors

NASA Technical Reports Server (NTRS)

Kositsky, J.; Nanevicz, J. E.

1991-01-01

Determination of aircraft electric field enhancement factors is crucial when using airborne field mill (ABFM) systems to accurately measure electric fields aloft. SRI used the scale model charge transfer technique to determine enhancement factors of several canonical shapes and a scale model Learjet 36A. The measured values for the canonical shapes agreed with known analytic solutions within about 6 percent. The laboratory determined enhancement factors for the aircraft were compared with those derived from in-flight data gathered by a Learjet 36A outfitted with eight field mills. The values agreed to within experimental error (approx. 15 percent).

EC02-0282-3

NASA Image and Video Library

2002-12-11

A NASA F/A-18 flies over the Dryden Flight Research Center and Rogers Dry Lake on December 11, 2002. The aircraft participated in the Automated Aerial Refueling (AAR) project. The 300-gallon aerial refueling store seen on the belly of the aircraft carries fuel and a refueling drogue. This aircraft acted as a tanker in the study to develop an aerodynamic model for future automated aerial refueling, especially of unmanned vehicles.

EC02-0282-5

NASA Image and Video Library

2002-12-11

A NASA F/A-18 flies over the Dryden Flight Research Center and Rogers Dry Lake on December 11, 2002. The aircraft participated in the Automated Aerial Refueling (AAR) project. The 300-gallon aerial refueling store seen on the belly of the aircraft carries fuel and a refueling drogue. This aircraft acted as a tanker in the study to develop an aerodynamic model for future automated aerial refueling, especially of unmanned vehicles.

EC02-0282-1

NASA Image and Video Library

2002-12-11

A NASA F/A-18 flies over the Dryden Flight Research Center and Rogers Dry Lake on December 11, 2002. The aircraft participated in the Automated Aerial Refueling (AAR) project. The 300-gallon aerial refueling store seen on the belly of the aircraft carries fuel and a refueling drogue. This aircraft acted as a tanker in the study to develop an aerodynamic model for future automated aerial refueling, especially of unmanned vehicles.

Heat transfer in aerospace propulsion

NASA Technical Reports Server (NTRS)

Simoneau, Robert J.; Hendricks, Robert C.; Gladden, Herbert J.

1988-01-01

Presented is an overview of heat transfer related research in support of aerospace propulsion, particularly as seen from the perspective of the NASA Lewis Research Center. Aerospace propulsion is defined to cover the full spectrum from conventional aircraft power plants through the Aerospace Plane to space propulsion. The conventional subsonic/supersonic aircraft arena, whether commercial or military, relies on the turbine engine. A key characteristic of turbine engines is that they involve fundamentally unsteady flows which must be properly treated. Space propulsion is characterized by very demanding performance requirements which frequently push systems to their limits and demand tailored designs. The hypersonic flight propulsion systems are subject to severe heat loads and the engine and airframe are truly one entity. The impact of the special demands of each of these aerospace propulsion systems on heat transfer is explored.

77 FR 55690 - Amendment of Class E Airspace; Dillon, MT

Federal Register 2010, 2011, 2012, 2013, 2014

2012-09-11

... aircraft using new Area Navigation (RNAV) Global positioning System (GPS) standard instrument approach... Airport, Dillon, MT, to accommodate IFR aircraft executing new RNAV (GPS) standard instrument approach.... Steven L. Vale, Acting Manager, Operations Support Group, Western Service Center. [FR Doc. 2012-22269...

76 FR 76686 - Notification and Reporting of Aircraft Accidents or Incidents and Overdue Aircraft, and...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-12-08

...: Regulatory History On January 7, 2010, the NTSB published a final rule entitled, ``Notification and Reporting... submit this certification to the Chief Counsel for Advocacy at the Small Business Administration. This... That Significantly Affect Energy Supply, Distribution, or Use; and the National Technology Transfer and...

41 CFR 102-33.295 - May we exchange or sell an aircraft through reimbursable transfer to another executive agency?

Code of Federal Regulations, 2012 CFR

2012-01-01

... consult with other executive agencies to find out if any agency is interested in taking the aircraft for reimbursement in funds or in kind (as you are directed in part 102-39 of this subchapter B). Note to § 102-33...

41 CFR 102-33.295 - May we exchange or sell an aircraft through reimbursable transfer to another executive agency?

Code of Federal Regulations, 2014 CFR

2014-01-01

... consult with other executive agencies to find out if any agency is interested in taking the aircraft for reimbursement in funds or in kind (as you are directed in part 102-39 of this subchapter B). Note to § 102-33...

41 CFR 102-33.295 - May we exchange or sell an aircraft through reimbursable transfer to another executive agency?

Code of Federal Regulations, 2013 CFR

2013-07-01

... consult with other executive agencies to find out if any agency is interested in taking the aircraft for reimbursement in funds or in kind (as you are directed in part 102-39 of this subchapter B). Note to § 102-33...

41 CFR 102-33.295 - May we exchange or sell an aircraft through reimbursable transfer to another executive agency?

Code of Federal Regulations, 2010 CFR

2010-07-01

... consult with other executive agencies to find out if any agency is interested in taking the aircraft for reimbursement in funds or in kind (as you are directed in part 102-39 of this subchapter B). Note to § 102-33...

41 CFR 102-33.295 - May we exchange or sell an aircraft through reimbursable transfer to another executive agency?

Code of Federal Regulations, 2011 CFR

2011-01-01

... consult with other executive agencies to find out if any agency is interested in taking the aircraft for reimbursement in funds or in kind (as you are directed in part 102-39 of this subchapter B). Note to § 102-33...

Device-Task Fidelity and Transfer of Training: Aircraft Cockpit Procedures Training.

ERIC Educational Resources Information Center

Prophet, Wallace W.; Boyd, H. Alton

An evaluation was made of the training effectiveness of two cockpit procedures training devices, differing greatly in physical fidelity and cost, for use on the ground for a twin-engine, turboprop, fixed-wing aircraft. One group of students received training in cockpit procedures in a relatively expensive, sophisticated, computerized trainer,…

STUDY PROGRAM FOR TURBO-COOLER FOR PRODUCING ENGINE COOLING AIR.

DTIC Science & Technology

VANES , STAGNATION POINT, DECELERATION, ACCELERATION, SUPERSONIC DIFFUSERS, TURBINE BLADES , EVAPOTRANSPIRATION, LIQUID COOLED, HEAT TRANSFER, GAS BEARINGS, SEALS...HYPERSONIC AIRCRAFT , COOLING + VENTILATING EQUIPMENT), (*GAS TURBINES , COOLING + VENTILATING EQUIPMENT), HYPERSONIC FLOW, AIR COOLED, AIRCRAFT ... ENGINES , FEASIBILITY STUDIES, PRESSURE, SUPERSONIC CHARACTERISTICS, DESIGN, HEAT EXCHANGERS, COOLING (U) AXIAL FLOW TURBINES , DUCT INLETS, INLET GUIDE

The lift-fan powered-lift aircraft concept: Lessons learned

NASA Technical Reports Server (NTRS)

Deckert, Wallace H.

1993-01-01

This is one of a series of reports on the lessons learned from past research related to lift-fan aircraft concepts. An extensive review is presented of the many lift-fan aircraft design studies conducted by both government and industry over the past 45 years. Mission applications and design integration including discussions on manifolding hot gas generators, hot gas dusting, and energy transfer control are addressed. Past lift-fan evaluations of the Avrocar are discussed. Lessons learned from these past efforts are identified.

Toward improved durability in advanced aircraft engine hot sections

NASA Technical Reports Server (NTRS)

Sokolowski, Daniel E. (Editor)

1989-01-01

The conference on durability improvement methods for advanced aircraft gas turbine hot-section components discussed NASA's Hot Section Technology (HOST) project, advanced high-temperature instrumentation for hot-section research, the development and application of combustor aerothermal models, and the evaluation of a data base and numerical model for turbine heat transfer. Also discussed are structural analysis methods for gas turbine hot section components, fatigue life-prediction modeling for turbine hot section materials, and the service life modeling of thermal barrier coatings for aircraft gas turbine engines.

Study of a very low cost air combat maneuvering trainer aircraft

NASA Technical Reports Server (NTRS)

Hill, G. C.; Bowles, J. V.

1976-01-01

A very low cost aircraft for performing Air Combat Maneuvering (ACM) training was studied using the BD-5J sport plane as a point of departure. The installation of a larger engine and increased fuel capacity were required to meet the performance and mission objectives. Reduced wing area increased the simulation of the ACM engagement, and a comparison with current tactical aircraft is presented. Other factors affecting the training transfer are considered analytically, but a flight evaluation is recommended to determine the concept utility.

14 CFR 21.314 - Transferability.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Transferability. 21.314 Section 21.314 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS Approval of Materials, Parts, Processes, and Appliances § 21.314...

Conducting Studies of Transfer of Learning: A Practical Guide. Final Report.

ERIC Educational Resources Information Center

Payne, Thomas A.

This document is a guide for use by the practical researcher concerned with conducting studies of transfer of learning from pretraining of pilots in ground-based environments to performance in aircraft. While the material addresses principally transfer of learning of pilots, many of the issues should be applicable to other contexts, to include…

Criminal acts against civil aviation

DOT National Transportation Integrated Search

2001-01-01

Criminal Acts Against Civil Aviation reports on incidents that have taken place against civil aviation aircraft and interests worldwide. Incidents that are recorded are summarized in regional geographic overviews. In addition, one or more feature art...

Department of Defense Financial Management Regulation. Volume 5. Disbursing Policy and Procedures

DTIC Science & Technology

1999-08-01

enable them to recognize fraudulent acts and, thereby, avoid losses. Reports of missing luggage, burglarized automobiles , and unauthorized absence of...for the reward requirement, including the amount needed, will be stated for each request. (e) Lost Aircraft and Lost Target Pilotless Aircraft and

The potential risk of communication media in conveying critical information in the aircraft maintenance organisation: a case study

NASA Astrophysics Data System (ADS)

Shukri, S. Ahmad; Millar, R. M.; Gratton, G.; Garner, M.

2016-10-01

In the world of aircraft maintenance organisation, verbal and written communication plays a pivotal role in transferring critical information in relation to aircraft safety and efficiency. The communication media used to convey the critical information between departments at an aircraft maintenance organisation have potential risk in misunderstanding of the information. In this study, technical and non-technical personnel from five different departments at an aircraft maintenance organisation were interviewed on the communication media they normally utilised to communicate six different work procedures that are closely related to aircraft safety and efficiency. This is to discover which communication media pose higher risk in misunderstanding critical information. The findings reveal that written communication pose higher risk of misinterpretation compared with verbal communication when conveying critical information between departments.

27 CFR 19.607 - Marks on cases.

Code of Federal Regulations, 2010 CFR

2010-04-01

.... Cases removed for export, transfer to customs bonded warehouses or customs manufacturing bonded warehouses, transfer to foreign-trade zones, or for use as supplies on certain vessels and aircraft, shall...; or (6) Labels or data describing the contents for commercial identification or accounting purposes...

Multi-species constraint of anthropogenic and biogenic processes over North America during ACT-America summer 2016 and winter 2017 aircraft campaigns

NASA Astrophysics Data System (ADS)

Parazoo, N.; Bowman, K. W.; Kuai, L.; Liu, J.; Lee, M.; Baker, I. T.; Berry, J. A.; Davis, K. J.; Lauvaux, T.; DiGangi, J. P.; Sweeney, C.

2017-12-01

Multi-species measurements of CO, OCS, and SIF have the potential to attribute CO2 variability to productivity and anthropogenic emissions. ACT-America aircraft campaigns in summer 2016 and winter 2017 collected vertical profiles of these key species close to their sources, providing important constraints on CO2 sources across 3 unique regions in eastern North America. The CMS-Flux carbon cycle assimilation system uses satellite measurements of CO (MOPITT), CO2 (OCO-2), SIF (OCO-2), and OCS (TES) to determine regional CO2 sources due to fossil fuel emissions, biomass burning, and net biome exchange, providing independent flux constraints, and which can be propagated back to the atmosphere for direct comparison to aircraft data. Here, we evaluate tracer-tracer correlations between CO2, CO, and OCS from ACT-America aircraft data during fall and winter campaigns, and compare to posterior signals from CMS-Flux over the same period. To predict atmospheric OCS signals, we leverage mechanistic representations of OCS plant uptake and GPP in the SiB land surface model to determine OCS-GPP linear relationships, then use SIF optimized estimates of GPP to infer OCS fluxes. Our objectives in this study are 3 fold: (1) Determine consistency of regional source attributions from CMS-Flux with aircraft data from ACT-America; (2) Analyze observed (ACT-America) and predicted (CMS-Flux) tracer-tracer correlations across multiple seasons and regions to identify key biogenic and anthropogenic drivers; (3) Determine to what extent SIF and OCS are valid linear predictors of GPP spatial variability. Summertime evaluation of these tracers shows good correlation between OCS/CO2 and OCS/CO in the midwest but poorer correlation in the northeast possibly reflecting biogenic controls on CO2. Comparisons of observed and predicted CO and CO2 in the PBL with CMF-Flux data indicate positively correlated biases that reflect both transport and flux errors. These results are compared with the winter campaign data to better inform biogenic vs anthropogenic sources, and provide ensemble predictions of OCS from SiB and multi-satellite SIF constraints for more robust analysis of GPP variability.

36 CFR 293.6 - Commercial enterprises, roads, motor vehicles, motorized equipment, motorboats, aircraft...

Code of Federal Regulations, 2010 CFR

2010-07-01

..., structures, and cutting of trees. 293.6 Section 293.6 Parks, Forests, and Public Property FOREST SERVICE... trees. Except as provided in the Wilderness Act, subsequent legislation establishing a particular... from aircraft; no structures or installations; and no cutting of trees for nonwilderness purposes. (a...

36 CFR 293.6 - Commercial enterprises, roads, motor vehicles, motorized equipment, motorboats, aircraft...

Code of Federal Regulations, 2014 CFR

2014-07-01

..., structures, and cutting of trees. 293.6 Section 293.6 Parks, Forests, and Public Property FOREST SERVICE... trees. Except as provided in the Wilderness Act, subsequent legislation establishing a particular... from aircraft; no structures or installations; and no cutting of trees for nonwilderness purposes. (a...

36 CFR 293.6 - Commercial enterprises, roads, motor vehicles, motorized equipment, motorboats, aircraft...

Code of Federal Regulations, 2012 CFR

2012-07-01

..., structures, and cutting of trees. 293.6 Section 293.6 Parks, Forests, and Public Property FOREST SERVICE... trees. Except as provided in the Wilderness Act, subsequent legislation establishing a particular... from aircraft; no structures or installations; and no cutting of trees for nonwilderness purposes. (a...

36 CFR 293.6 - Commercial enterprises, roads, motor vehicles, motorized equipment, motorboats, aircraft...

Code of Federal Regulations, 2013 CFR

2013-07-01

..., structures, and cutting of trees. 293.6 Section 293.6 Parks, Forests, and Public Property FOREST SERVICE... trees. Except as provided in the Wilderness Act, subsequent legislation establishing a particular... from aircraft; no structures or installations; and no cutting of trees for nonwilderness purposes. (a...

48 CFR 25.407 - Agreement on Trade in Civil Aircraft.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 48 Federal Acquisition Regulations System 1 2012-10-01 2012-10-01 false Agreement on Trade in... REGULATION SOCIOECONOMIC PROGRAMS FOREIGN ACQUISITION Trade Agreements 25.407 Agreement on Trade in Civil Aircraft. Under the authority of Section 303 of the Trade Agreements Act, the U.S. Trade Representative has...

Aviation security : preliminary observations on TSA's progress and challenges in meeting the statutory mandate for screening air cargo on passenger aircraft.

DOT National Transportation Integrated Search

2009-03-01

The Implementing : Recommendations of the 9/11 : Commission Act of 2007 mandates : the Department of Homeland : Security (DHS) to establish a : system to physically screen 50 : percent of cargo transported on : passenger aircraft by February : 2009 a...

77 FR 58103 - Federal Acquisition Regulation; Submission for OMB Review; Corporate Aircraft Costs

Federal Register 2010, 2011, 2012, 2013, 2014

2012-09-19

... Paperwork Reduction Act, the Regulatory Secretariat will be submitting to the Office of Management and... of the information collection would violate the fundamental purposes of the Paperwork Reduction Act...

Aircraft Loss-of-Control Accident Analysis

NASA Technical Reports Server (NTRS)

Belcastro, Christine M.; Foster, John V.

2010-01-01

Loss of control remains one of the largest contributors to fatal aircraft accidents worldwide. Aircraft loss-of-control accidents are complex in that they can result from numerous causal and contributing factors acting alone or (more often) in combination. Hence, there is no single intervention strategy to prevent these accidents. To gain a better understanding into aircraft loss-of-control events and possible intervention strategies, this paper presents a detailed analysis of loss-of-control accident data (predominantly from Part 121), including worst case combinations of causal and contributing factors and their sequencing. Future potential risks are also considered.

Measurements of ocean wave spectra and modulation transfer function with the airborne two frequency scatterometer

NASA Technical Reports Server (NTRS)

Weissman, D. E.; Johnson, J. W.

1984-01-01

The directional spectrum and the microwave modulation transfer function of ocean waves can be measured with the airborne two frequency scatterometer technique. Similar to tower based observations, the aircraft measurements of the Modulation Transfer Function (MTF) show that it is strongly affected by both wind speed and sea state. Also detected are small differences in the magnitudes of the MTF between downwind and upwind radar look directions, and variations with ocean wavenumber. The MTF inferred from the two frequency radar is larger than that measured using single frequency, wave orbital velocity techniques such as tower based radars or ROWS measurements from low altitude aircraft. Possible reasons for this are discussed. The ability to measure the ocean directional spectrum with the two frequency scatterometer, with supporting MTF data, is demonstrated.

Measurements of ocean wave spectra and modulation transfer function with the airborne two-frequency scatterometer

NASA Technical Reports Server (NTRS)

Weissman, D. E.; Johnson, J. W.

1986-01-01

The directional spectrum and the microwave modulation transfer function of ocean waves can be measured with the airborne two frequency scatterometer technique. Similar to tower based observations, the aircraft measurements of the Modulation Transfer Function (MTF) show that it is strongly affected by both wind speed and sea state. Also detected are small differences in the magnitudes of the MTF between downwind and upwind radar look directions, and variations with ocean wavenumber. The MTF inferred from the two frequency radar is larger than that measured using single frequency, wave orbital velocity techniques such as tower based radars or ROWS measurements from low altitude aircraft. Possible reasons for this are discussed. The ability to measure the ocean directional spectrum with the two frequency scatterometer, with supporting MTF data, is demonstrated.

A flight test facility design for examining digital information transfer

NASA Technical Reports Server (NTRS)

Knox, Charles E.

1990-01-01

Information is given in viewgraph form on a flight test facility design for examining digital information transfer. Information is given on aircraft/ground exchange, data link research activities, data link display format, a data link flight test, and the flight test setup.

Heat transfer in aeropropulsion systems

NASA Astrophysics Data System (ADS)

Simoneau, R. J.

1985-07-01

Aeropropulsion heat transfer is reviewed. A research methodology based on a growing synergism between computations and experiments is examined. The aeropropulsion heat transfer arena is identified as high Reynolds number forced convection in a highly disturbed environment subject to strong gradients, body forces, abrupt geometry changes and high three dimensionality - all in an unsteady flow field. Numerous examples based on heat transfer to the aircraft gas turbine blade are presented to illustrate the types of heat transfer problems which are generic to aeropropulsion systems. The research focus of the near future in aeropropulsion heat transfer is projected.

Heat transfer in aeropropulsion systems

NASA Technical Reports Server (NTRS)

Simoneau, R. J.

1985-01-01

Aeropropulsion heat transfer is reviewed. A research methodology based on a growing synergism between computations and experiments is examined. The aeropropulsion heat transfer arena is identified as high Reynolds number forced convection in a highly disturbed environment subject to strong gradients, body forces, abrupt geometry changes and high three dimensionality - all in an unsteady flow field. Numerous examples based on heat transfer to the aircraft gas turbine blade are presented to illustrate the types of heat transfer problems which are generic to aeropropulsion systems. The research focus of the near future in aeropropulsion heat transfer is projected.

49 CFR 1542.221 - Records of law enforcement response.

Code of Federal Regulations, 2010 CFR

2010-10-01

... each. (2) The number of acts and attempted acts of aircraft piracy. (3) The number of bomb threats received, real and simulated bombs found, and actual detonations on the airport. (4) The number of arrests...

Aerospace and electronic systems - Advanced concepts and pioneering perspectives; Proceedings of the Sixth Symposium, Dayton, OH, November 14, 15, 1984

NASA Astrophysics Data System (ADS)

Among the topics discussed are: the PRAM approach to technology transfer; all-electric aircraft development; and electronic enhancements for the combat aircraft cockpit. Consideration is also given to application of AI systems to military aircraft; ECM and ECCM technology; and the history of monolithic ICs. Developments in the USAF Avionics Integrity Program (AVIP) are reviewed, with emphasis given to: preventive measures for electrostatic discharges; corrosion prevention to increase avionics integrity; and criteria for stress screening temperature levels.

Bob Meyer (right), acting deputy director of NASA Dryden, shakes hands with Les Bordelon, executive

NASA Technical Reports Server (NTRS)

2002-01-01

Bob Meyer (on the right), acting deputy director of NASA's Dryden Flight Research Center, Edwards, California, shakes hands with Les Bordelon, executive director of Edwards Air Force Base. The handshake represents Dryden's acceptance of an Air Force C-20A delivered from Ramstein Air Base, Germany. The aircraft will be modified to carry equipment and experiments in support of both NASA and U.S. Air Force projects. The joint use of this aircraft is a result of the NASA Dryden/Edwards Air Force Base Alliance which shares some resources as cost-cutting measures.

Some Factors Influencing Transfer of Simulator Training.

ERIC Educational Resources Information Center

Caro, Paul W.

Studies of transfer of training may be used to determine whether simulator training improves pilot performance in an aircraft. Some approaches to determining simulator training effectiveness, such as surveys of pilot and instructor opinions, are not considered particularly reliable. Several other approaches have also been suggested. One factor…

Simulation test results for lift/cruise fan research and technology aircraft

NASA Technical Reports Server (NTRS)

Bland, M. P.; Konsewicz, R. K.

1976-01-01

A flight simulation program was conducted on the flight simulator for advanced aircraft (FSAA). The flight simulation was a part of a contracted effort to provide a lift/cruise fan V/STOL aircraft mathematical model for flight simulation. The simulated aircraft is a configuration of the Lift/Cruise Fan V/STOL research technology aircraft (RTA). The aircraft was powered by three gas generators driving three fans. One lift fan was installed in the nose of the aircraft, and two lift/cruise fans at the wing root. The thrust of these fans was modulated to provide pitch and roll control, and vectored to provide yaw, side force control, and longitudinal translation. Two versions of the RTA were defined. One was powered by the GE J97/LF460 propulsion system which was gas-coupled for power transfer between fans for control. The other version was powered by DDA XT701 gas generators driving 62 inch variable pitch fans. The flight control system in both versions of the RTA was the same.

Aircraft Electromagnetic Compatibility.

DTIC Science & Technology

1987-06-01

Human Exposure to Radio Frequency Electromagnetic Fields , 300 KiloHertz to 100 GigaHertz." 6. ARINC 429-8, "Digital Information Transfer System (DITS...142 V EXECUTIVE SUMMARY The Aircraft Electromagnetic Compatibility guidelines document deals with electromagnetic compatibility in a... electromagnetic interference paths (figure EI. TYPE PATH 400 Hz Electrostatic MagneticCharge Electric Field Transients 5 R d t Coupling 150/i 300o Wire

8 CFR 1280.11 - Notice of intention to fine; procedure.

Code of Federal Regulations, 2010 CFR

2010-01-01

... customs for the district in which the vessel or aircraft is located, and the district director of customs... Nationality Act. If the vessel or aircraft is located in a customs district which is outside the jurisdiction of the office of the Service having jurisdiction over the matter, the triplicate copy shall be...

8 CFR 1280.11 - Notice of intention to fine; procedure.

Code of Federal Regulations, 2011 CFR

2011-01-01

... customs for the district in which the vessel or aircraft is located, and the district director of customs... Nationality Act. If the vessel or aircraft is located in a customs district which is outside the jurisdiction of the office of the Service having jurisdiction over the matter, the triplicate copy shall be...

10 CFR 862.1 - Purpose.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 10 Energy 4 2011-01-01 2011-01-01 false Purpose. 862.1 Section 862.1 Energy DEPARTMENT OF ENERGY RESTRICTIONS ON AIRCRAFT LANDING AND AIR DELIVERY AT DEPARTMENT OF ENERGY NUCLEAR SITES § 862.1 Purpose. The... aircraft and air delivery on nuclear sites under the jurisdiction of DOE pursuant to the Atomic Energy Act...

Close Air Support Allocation for Extended Counterinsurgency: Is Our Doctrine Lacking

DTIC Science & Technology

2010-04-01

timely and accurate deconfliction of those aircraft. They act as the primary command and control for all aircraft in the theater and are extremely...only merge the real time CAS control fuctions into a single entity. It is not to eliminate the capacity of the ASOC to participate in land

78 FR 1220 - Agency Information Collection Activities: Guarantee of Payment

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-08

... and approval in accordance with the Paperwork Reduction Act: Guarantee of Payment (CBP Form I-510... forms of information. Title: Guarantee of Payment. OMB Number: 1651-0127. Form Number: CBP Form I-510... master of the vessel or aircraft on CBP Form I-510, Guarantee of Payment. No vessel or aircraft can be...

10 CFR 862.1 - Purpose.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 10 Energy 4 2010-01-01 2010-01-01 false Purpose. 862.1 Section 862.1 Energy DEPARTMENT OF ENERGY RESTRICTIONS ON AIRCRAFT LANDING AND AIR DELIVERY AT DEPARTMENT OF ENERGY NUCLEAR SITES § 862.1 Purpose. The... aircraft and air delivery on nuclear sites under the jurisdiction of DOE pursuant to the Atomic Energy Act...

26 CFR 31.3306(m)-1 - American vessel and aircraft.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 26 Internal Revenue 15 2011-04-01 2011-04-01 false American vessel and aircraft. 31.3306(m)-1 Section 31.3306(m)-1 Internal Revenue INTERNAL REVENUE SERVICE, DEPARTMENT OF THE TREASURY (CONTINUED... SOURCE Federal Unemployment Tax Act (Chapter 23, Internal Revenue Code of 1954) § 31.3306(m)-1 American...

26 CFR 31.3306(m)-1 - American vessel and aircraft.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 26 Internal Revenue 15 2010-04-01 2010-04-01 false American vessel and aircraft. 31.3306(m)-1 Section 31.3306(m)-1 Internal Revenue INTERNAL REVENUE SERVICE, DEPARTMENT OF THE TREASURY (CONTINUED... SOURCE Federal Unemployment Tax Act (Chapter 23, Internal Revenue Code of 1954) § 31.3306(m)-1 American...

Technical evaluation of the Aerospace Medical Panel Specialists Meeting on Escape Problems and Manoeuvres in Combat Aircraft

NASA Technical Reports Server (NTRS)

Jones, W. L.

1974-01-01

A technical evaluation of the papers presented at a conference on escape systems for helicopters and V/STOL aircraft was made. The subjects discussed include the following: (1) bioengineering aspects of spinal injury during ejection, (2) aerodynamic forces acting on crewman during escape, (3) operational practicality of fly away ejection seats, (4) helicopter survivability requirements, (5) ejection experience from V/STOL aircraft, and (6) research projects involving escape and retrieval systems.

The Evolution of the Sonobuoy from World War II to the Cold War

DTIC Science & Technology

2014-01-01

airship , the first aircraft intentionally built for ASW.2 After Wilbur and Orville Wright’s first successful airplane flight in December 1903, the...aircraft had to shut down its engines to use the hydrophone, there was reluctance to use this method for fear the aircraft engine would not start again...the sonobuoy would act as the receiver for the echo from the submarine. This mode became known as “Julie” in 1955, when engineers who worked on the

16 CFR 1101.2. - Scope.

Code of Federal Regulations, 2010 CFR

2010-01-01

... four other acts the Commission administers (transferred acts). These transferred acts are the Flammable... (PPPA); the Federal Hazardous Substances Act, 15 U.S.C. 1261-1276 (FHSA); and the Refrigerator Safety...

The effect of fatigue cracks on fastener flexibility, load distribution, and fatigue crack growth

NASA Astrophysics Data System (ADS)

Whitman, Zachary Layne

Fatigue cracks typically occur at stress risers such as geometry changes and holes. This type of failure has serious safety and economic repercussions affecting structures such as aircraft. The need to prevent catastrophic failure due to fatigue cracks and other discontinuities has led to durability and damage tolerant methodologies influencing the design of aircraft structures. Holes in a plate or sheet filled with a fastener are common fatigue critical locations in aircraft structure requiring damage tolerance analysis (DTA). Often, the fastener is transferring load which leads to a loading condition involving both far-field stresses such as tension and bending, and localized bearing at the hole. The difference between the bearing stress and the tensile field at the hole is known as load transfer. The ratio of load transfer as well as the magnitude of the stresses plays a significant part in how quickly a crack will progress to failure. Unfortunately, the determination of load transfer in a complex joint is far from trivial. Many methods exist in the open literature regarding the analysis of splices, doublers and attachment joints to determine individual fastener loads. These methods work well for static analyses but greater refinement is needed for crack growth analysis. The first fastener in a splice or joint is typically the most critical but different fastener flexibility equations will all give different results. The constraint of the fastener head and shop end, along with the type of fastener, affects the stiffness or flexibility of the fastener. This in turn will determine the load that the fastener will transfer within a given fastener pattern. However, current methods do not account for the change in flexibility at a fastener as the crack develops. It is put forth that a crack does indeed reduce the stiffness of a fastener by changing its constraint, thus lessening the load transfer. A crack growth analysis utilizing reduced load transfer will result in a slower growing crack versus an analysis that ignores the effect.

Lightning induced currents in aircraft wiring using low level injection techniques

NASA Technical Reports Server (NTRS)

Stevens, E. G.; Jordan, D. T.

1991-01-01

Various techniques were studied to predict the transient current induced into aircraft wiring bundles as a result of an aircraft lightning strike. A series of aircraft measurements were carried out together with a theoretical analysis using computer modeling. These tests were applied to various aircraft and also to specially constructed cylinders installed within coaxial return conductor systems. Low level swept frequency CW (carrier waves), low level transient and high level transient injection tests were applied to the aircraft and cylinders. Measurements were made to determine the transfer function between the aircraft drive current and the resulting skin currents and currents induced on the internal wiring. The full threat lightning induced transient currents were extrapolated from the low level data using Fourier transform techniques. The aircraft and cylinders used were constructed from both metallic and CFC (carbon fiber composite) materials. The results show the pulse stretching phenomenon which occurs for CFC materials due to the diffusion of the lightning current through carbon fiber materials. Transmission Line Matrix modeling techniques were used to compare theoretical and measured currents.

Green Flight Challenge

NASA Image and Video Library

2011-10-03

Comparative Aircraft Flight Efficiency (CAFE) Foundation President Brien A. Seeley M.D., left, NASA Acting Chief Technologist Joe Parrish, 2nd from left, and Pipistrel-USA Team Lead Jack Langelaan, center with suit, and the entire Pipistrel-USA, Taurus G4 aircraft team pose for a photograph shortly after winning the 2011 Green Flight Challenge, sponsored by Google, on Monday, Oct. 3, 2011 at the NASA Ames Research Center, Mountain View, Calif. The all electric Taurus G4 aircraft achieved the equivalency of more than 400 miles per gallon. NASA and CAFE held the challenge to advance technologies in fuel efficiency and reduced emissions with cleaner renewable fuels and electric aircraft. Photo Credit: (NASA/Bill Ingalls)

Manufacturing process applications team (MATeam)

NASA Technical Reports Server (NTRS)

Bangs, E. R.

1980-01-01

Progress in the transfer of aerospace technology to solve key problems in the manufacturing sector of the economy is reported. Potential RTOP programs are summarized along with dissemination activities. The impact of transferred NASA manufacturing technology is discussed. Specific areas covered include aircraft production, robot technology, machining of alloys, and electrical switching systems.

Liquid water content variation with altitude in clouds over Europe

NASA Astrophysics Data System (ADS)

Andreea, Boscornea; Sabina, Stefan

2013-04-01

Cloud water content is one of the most fundamental measurements in cloud physics. Knowledge of the vertical variability of cloud microphysical characteristics is important for a variety of reasons. The profile of liquid water content (LWC) partially governs the radiative transfer for cloudy atmospheres, LWC profiles improves our understanding of processes acting to form and maintain cloud systems and may lead to improvements in the representation of clouds in numerical models. Presently, in situ airborne measurements provide the most accurate information about cloud microphysical characteristics. This information can be used for verification of both numerical models and cloud remote sensing techniques. The aim of this paper was to analyze the liquid water content (LWC) measurements in clouds, in time of the aircraft flights. The aircraft and its platform ATMOSLAB - Airborne Laboratory for Environmental Atmospheric Research is property of the National Institute for Aerospace Research "Elie Carafoli" (INCAS), Bucharest, Romania. The airborne laboratory equipped for special research missions is based on a Hawker Beechcraft - King Air C90 GTx aircraft and is equipped with a sensors system CAPS - Cloud, Aerosol and Precipitation Spectrometer (30 bins, 0.51-50 m). The processed and analyzed measurements are acquired during 4 flights from Romania (Bucharest, 44°25'57″N 26°06'14″E) to Germany (Berlin 52°30'2″N 13°23'56″E) above the same region of Europe. The flight path was starting from Bucharest to the western part of Romania above Hungary, Austria at a cruse altitude between 6000-8500 m, and after 5 hours reaching Berlin. In total we acquired data during approximately 20 flight hours and we presented the vertical and horizontal LWC variations for different cloud types. The LWC values are similar for each type of cloud to values from literature. The vertical LWC profiles in the atmosphere measured during takeoff and landing of the aircraft have shown their dependence of the meteorological parameters.

Analysis of an electrohydraulic aircraft control surface servo and comparison with test results

NASA Technical Reports Server (NTRS)

Edwards, J. W.

1972-01-01

An analysis of an electrohydraulic aircraft control-surface system is made in which the system is modeled as a lumped, two-mass, spring-coupled system controlled by a servo valve. Both linear and nonlinear models are developed, and the effects of hinge-moment loading are included. Transfer functions of the system and approximate literal factors of the transfer functions for several cases are presented. The damping action of dynamic pressure feedback is analyzed. Comparisons of the model responses with results from tests made on a highly resonant rudder control-surface servo indicate the adequacy of the model. The effects of variations in hinge-moment loading are illustrated.

Aeroelastic Airworthiness Assesment of the Adaptive Compliant Trailing Edge Flaps

NASA Technical Reports Server (NTRS)

Herrera, Claudia Y.; Spivey, Natalie D.; Lung, Shun-fat; Ervin, Gregory; Flick, Peter

2015-01-01

The Adaptive Compliant Trailing Edge (ACTE) demonstrator is a joint task under the National Aeronautics and Space Administration Environmentally Responsible Aviation Project in partnership with the Air Force Research Laboratory and FlexSys, Inc. (Ann Arbor, Michigan). The project goal is to develop advanced technologies that enable environmentally friendly aircraft, such as adaptive compliant technologies. The ACTE demonstrator flight-test program encompassed replacing the Fowler flaps on the SubsoniC Aircraft Testbed, a modified Gulfstream III (Gulfstream Aerospace, Savannah, Georgia) aircraft, with control surfaces developed by FlexSys. The control surfaces developed by FlexSys are a pair of uniquely-designed unconventional flaps to be used as lifting surfaces during flight-testing to validate their structural effectiveness. The unconventional flaps required a multidisciplinary airworthiness assessment to prove they could withstand the prescribed flight envelope. Several challenges were posed due to the large deflections experienced by the structure, requiring non-linear analysis methods. The aeroelastic assessment necessitated both conventional and extensive testing and analysis methods. A series of ground vibration tests (GVTs) were conducted to provide modal characteristics to validate and update finite element models (FEMs) used for the flutter analyses for a subset of the various flight configurations. Numerous FEMs were developed using data from FlexSys and the ground tests. The flap FEMs were then attached to the aircraft model to generate a combined FEM that could be analyzed for aeroelastic instabilities. The aeroelastic analysis results showed the combined system of aircraft and flaps were predicted to have the required flutter margin to successfully demonstrate the adaptive compliant technology. This paper documents the details of the aeroelastic airworthiness assessment described, including the ground testing and analyses, and subsequent flight-testing performed on the unconventional ACTE flaps.

Comparison of Several Methods of Predicting the Pressure Loss at Altitude Across a Baffled Aircraft-Engine Cylinder

NASA Technical Reports Server (NTRS)

Neustein, Joseph; Schafer, Louis J , Jr

1946-01-01

Several methods of predicting the compressible-flow pressure loss across a baffled aircraft-engine cylinder were analytically related and were experimentally investigated on a typical air-cooled aircraft-engine cylinder. Tests with and without heat transfer covered a wide range of cooling-air flows and simulated altitudes from sea level to 40,000 feet. Both the analysis and the test results showed that the method based on the density determined by the static pressure and the stagnation temperature at the baffle exit gave results comparable with those obtained from methods derived by one-dimensional-flow theory. The method based on a characteristic Mach number, although related analytically to one-dimensional-flow theory, was found impractical in the present tests because of the difficulty encountered in defining the proper characteristic state of the cooling air. Accurate predictions of altitude pressure loss can apparently be made by these methods, provided that they are based on the results of sea-level tests with heat transfer.

Integrated propulsion/energy transfer control systems for lift-fan V/STOL aircraft. [reduction of total propulsion system and control system installation requirements

NASA Technical Reports Server (NTRS)

Deckert, W. H.; Rolls, L. S.

1974-01-01

An integrated propulsion/control system for lift-fan transport aircraft is described. System behavior from full-scale experimental and piloted simulator investigations are reported. The lift-fan transport is a promising concept for short-to-medium haul civil transportation and for other missions. The lift-fan transport concept features high cruise airspeed, favorable ride qualities, small perceived noise footprints, high utilization, transportation system flexibility, and adaptability to VTOL, V/STOL, or STOL configurations. The lift-fan transport has high direct operating costs in comparison to conventional aircraft, primarily because of propulsion system and aircraft low-speed control system installation requirements. An integrated lift-fan propulsion system/aircraft low-speed control system that reduces total propulsion system and control system installation requirements is discussed.

Higher Harmonic Control for Tiltrotor Vibration Reduction

NASA Technical Reports Server (NTRS)

Nixon, Mark W.; Kvaternik, Raymond G.; Settle, T. Ben

1997-01-01

The results of a joint NASA/Army/Bell Helicopter Textron wind-tunnel test to assess the potential of higher harmonic control (HHC) for reducing vibrations in tiltrotor aircraft operating in the airplane mode of flight, and to evaluate the effectiveness of a Bell-developed HHC algorithm called MAVSS (Multipoint Adaptive Vibration Suppression System) are presented. The test was conducted in the Langley Transonic Dynamics Tunnel using an unpowered 1/5- scale semispan aeroelastic model of the V-22 which was modified to incorporate an HHC system employing both the rotor swashplate and the wing flaperon. The effectiveness of the swashplate and the flaperon acting either singly or in combination in reducing 1P and 3P wing vibrations over a wide range of tunnel airspeeds and rotor rotational speeds was demonstrated. The MAVSS algorithm was found to be robust to variations in tunnel airspeed and rotor speed, requiring only occasion-al on-line recalculations of the system transfer matrix.

Establishing confidence in CCV/ACT technology

NASA Technical Reports Server (NTRS)

Holloway, R. B.; Shomber, H. A.

1976-01-01

Despite significant advancements in controls configured vehicles/active controls technology (CCV/ACT) in the past decade, few applications of this promising technology have appeared in recent aircraft designs. The status of CCV/ACT is summarized, and some of the constraints which are retarding its wider application are described. Suggestions toward establishing an increased level of confidence in the technology are given.

22 CFR 126.6 - Foreign-owned military aircraft and naval vessels, and the Foreign Military Sales program.

Code of Federal Regulations, 2011 CFR

2011-04-01

... INTERNATIONAL TRAFFIC IN ARMS REGULATIONS GENERAL POLICIES AND PROVISIONS § 126.6 Foreign-owned military... pursuant to the Arms Export Control Act or the Foreign Assistance Act of 1961, as amended, and (2) The... the Arms Export Control Act pursuant to an Letter of Offer and Acceptance (LOA) authorizing such...

19 CFR 10.60 - Forms of withdrawals; bond.

Code of Federal Regulations, 2011 CFR

2011-04-01

... under section 309 or 317, Tariff Act of 1930, as amended, the port director in his discretion may permit... withdrawal as supplies on aircraft under § 309, Tariff Act of 1930, as amended, when the supplies are to be... 309, Tariff Act of 1930, as amended, and that the value and quantity declared for them are correct. (g...

19 CFR 10.60 - Forms of withdrawals; bond.

Code of Federal Regulations, 2014 CFR

2014-04-01

... under section 309 or 317, Tariff Act of 1930, as amended, the port director in his discretion may permit... withdrawal as supplies on aircraft under § 309, Tariff Act of 1930, as amended, when the supplies are to be... 309, Tariff Act of 1930, as amended, and that the value and quantity declared for them are correct. (g...

19 CFR 10.60 - Forms of withdrawals; bond.

Code of Federal Regulations, 2012 CFR

2012-04-01

... under section 309 or 317, Tariff Act of 1930, as amended, the port director in his discretion may permit... withdrawal as supplies on aircraft under § 309, Tariff Act of 1930, as amended, when the supplies are to be... 309, Tariff Act of 1930, as amended, and that the value and quantity declared for them are correct. (g...

19 CFR 10.60 - Forms of withdrawals; bond.

Code of Federal Regulations, 2013 CFR

2013-04-01

... under section 309 or 317, Tariff Act of 1930, as amended, the port director in his discretion may permit... withdrawal as supplies on aircraft under § 309, Tariff Act of 1930, as amended, when the supplies are to be... 309, Tariff Act of 1930, as amended, and that the value and quantity declared for them are correct. (g...

19 CFR 10.60 - Forms of withdrawals; bond.

Code of Federal Regulations, 2010 CFR

2010-04-01

... under section 309 or 317, Tariff Act of 1930, as amended, the port director in his discretion may permit... withdrawal as supplies on aircraft under § 309, Tariff Act of 1930, as amended, when the supplies are to be... 309, Tariff Act of 1930, as amended, and that the value and quantity declared for them are correct. (g...

75 FR 61485 - Regulatory Training Session With Air Carriers, EPA Regional Partners and Other Interested Parties...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-10-05

... Regional Partners and Other Interested Parties for Implementation of the Aircraft Drinking Water Rule... Agency (EPA) will hold a two-day training session on the regulatory requirements of the Aircraft Drinking... water systems'' under the Safe Drinking Water Act (SDWA) must meet the first set of requirements of the...

Final Rule for Finding That Greenhouse Gas Emissions From Aircraft Cause or Contribute to Air Pollution That May Reasonably Be Anticipated To Endanger Public Health and Welfare

EPA Pesticide Factsheets

The EPA finalized findings that greenhouse gas (GHG) emissions from certain classes of engines used in aircraft contribute to the air pollution that causes climate change endangering public health and welfare under section 231(a) of the Clean Air Act.

Tester for Distress Beacons

NASA Technical Reports Server (NTRS)

Wade, W. R.

1986-01-01

Distress beacons on aircraft and boats checked for proper operation with aid of onboard monitor. Monitor mounted in aircraft cockpit or at wheel of boat. Connected to beacon electronics by cable. Monitor used with interface circuitry in beacon, which acts as buffer so that operation of beacon is not adversely affected if monitor is removed or if connecting cable is accidentally short circuited.

Study of active cooling for supersonic transports

NASA Technical Reports Server (NTRS)

Brewer, G. D.; Morris, R. E.

1975-01-01

The potential benefits of using the fuel heat sink of hydrogen fueled supersonic transports for cooling large portions of the aircraft wing and fuselage are examined. The heat transfer would be accomplished by using an intermediate fluid such as an ethylene glycol-water solution. Some of the advantages of the system are: (1) reduced costs by using aluminum in place of titanium, (2) reduced cabin heat loads, and (3) more favorable environmental conditions for the aircraft systems. A liquid hydrogen fueled, Mach 2.7 supersonic transport aircraft design was used for the reference uncooled vehicle. The cooled aircraft designs were analyzed to determine their heat sink capability, the extent and location of feasible cooled surfaces, and the coolant passage size and spacing.

Comparison of Requirements for Composite Structures for Aircraft and Space Applications

NASA Technical Reports Server (NTRS)

Raju, Ivatury S.; Elliot, Kenny B.; Hampton, Roy W.; Knight, Norman F., Jr.; Aggarwal, Pravin; Engelstad, Stephen P.; Chang, James B.

2010-01-01

In this report, the aircraft and space vehicle requirements for composite structures are compared. It is a valuable exercise to study composite structural design approaches used in the airframe industry and to adopt methodology that is applicable for space vehicles. The missions, environments, analysis methods, analysis validation approaches, testing programs, build quantities, inspection, and maintenance procedures used by the airframe industry, in general, are not transferable to spaceflight hardware. Therefore, while the application of composite design approaches from aircraft and other industries is appealing, many aspects cannot be directly utilized. Nevertheless, experiences and research for composite aircraft structures may be of use in unexpected arenas as space exploration technology develops, and so continued technology exchanges are encouraged.

NASA's aircraft icing technology program

NASA Technical Reports Server (NTRS)

Reinmann, John J.

1991-01-01

NASA' Aircraft Icing Technology program is aimed at developing innovative technologies for safe and efficient flight into forecasted icing. The program addresses the needs of all aircraft classes and supports both commercial and military applications. The program is guided by three key strategic objectives: (1) numerically simulate an aircraft's response to an in-flight icing encounter, (2) provide improved experimental icing simulation facilities and testing techniques, and (3) offer innovative approaches to ice protection. Our research focuses on topics that directly support stated industry needs, and we work closely with industry to assure a rapid and smooth transfer of technology. This paper presents selected results that illustrate progress towards the three strategic objectives, and it provides a comprehensive list of references on the NASA icing program.

Development of fire-resistant, low smoke generating, thermally stable end items for aircraft and spacecraft

NASA Technical Reports Server (NTRS)

Gagliani, J.; Sorathia, U. A. K.; Wilcoxson, A. L.

1977-01-01

Materials were developed to improve aircraft interior materials by modifying existing polymer structures, refining the process parameters, and by the use of mechanical configurations designed to overcome specific deficiencies. The optimization, selection, and fabrication of five fire resistant, low smoke emitting open cell foams are described for five different types of aircraft cabin structures. These include: resilient foams, laminate floor and wall paneling, thermal/acoustical insulation, molded shapes, and coated fabrics. All five have been produced from essentially the same polyimide precursor and have resulted in significant benefits from transfer of technology between the various tasks.

Federal Technology Transfer Act Success Stories

EPA Pesticide Factsheets

Successful Federal Technology Transfer Act (FTTA) partnerships demonstrate the many advantages of technology transfer and collaboration. EPA and partner organizations create valuable and applicable technologies for the marketplace.

Navy Nuclear Aircraft Carrier (CVN) Homeporting at Mayport: Background and Issues for Congress

DTIC Science & Technology

2009-07-17

releaseid= 12600 . 2 The Navy has not identified which specific CVN it would transfer, and a CVN transferred to Mayport could come from any of the...available online at http://www.defenselink.mil/releases/release.aspx?releaseid= 12600 . 7Although the Navy states that the CVN based at Yokosuka is

Relevance of ERTS to the State of Ohio

NASA Technical Reports Server (NTRS)

Sweet, D. C. (Principal Investigator)

1973-01-01

The author has identified the following significant results. A significant result was the fabrication of an image transfer and comparison device. To avoid problems and high costs encountered in manual drafting methods, Battelle staff members have fabricated an inexpensive, yet effective, technique for transferring ERTS-1 analysis displays from the Spatial Data 32-Color Viewer to maps and/or aircraft imagery. In brief, the image transfer-comparison device consists of a 2-way mirror which functions similar to a zoom transfer scope. However, the device permits multiuser viewing and real time photographic recording (35-mm and Polaroid) of enhanced ERTS-1 imagery superimposed over maps and aircraft photography. Thirty-five mm, 70 mm, and 4 in. x 5 in. photographs are taken of 80% of the TV screen of the Spatial Data Density Slicing Viewer. The resulting black and white and color imagery is then used in transparent overlays, viewgraphs, 35-mm and 70-mm transparencies, and paper prints for reports and publications. Annotations can be added on the TV screen or on the finished product.

Miniature Rocket Motor for Aircraft Stall/Spin Recovery

NASA Technical Reports Server (NTRS)

Lucy, M. H.

1985-01-01

Design accommodates different thrust levels and burn times with minimum weight. Different thrust levels achieved by substituting other propellants of different diameter and burn-rate characteristics. Different burn times achieved by simply changing length of grain/tube assembly. Grain bond material also acts as insulator for fiberglass tube. Rocket motor attached to aircraft model and ignited from radio-controlled 4.8-volt power source. Device provides more than twice energy available in previous designs at only 60 percent of weight. Rocket motor used to identify energy requirements for aircraft stall/spin recovery positive propulsion system.

Aircraft Loss-of-Control: Analysis and Requirements for Future Safety-Critical Systems and Their Validation

NASA Technical Reports Server (NTRS)

Belcastro, Christine M.

2011-01-01

Loss of control remains one of the largest contributors to fatal aircraft accidents worldwide. Aircraft loss-of-control accidents are complex, resulting from numerous causal and contributing factors acting alone or more often in combination. Hence, there is no single intervention strategy to prevent these accidents. This paper summarizes recent analysis results in identifying worst-case combinations of loss-of-control accident precursors and their time sequences, a holistic approach to preventing loss-of-control accidents in the future, and key requirements for validating the associated technologies.

CFD analysis of aircraft fuel tanks thermal behaviour

NASA Astrophysics Data System (ADS)

Zilio, C.; Longo, G. A.; Pernigotto, G.; Chiacchio, F.; Borrelli, P.; D'Errico, E.

2017-11-01

This work is carried out within the FP7 European research project TOICA (Thermal Overall Integrated Conception of Aircraft, http://www.toica-fp7.eu/). One of the tasks foreseen for the TOICA project is the analysis of fuel tanks as possible heat sinks for future aircrafts. In particular, in the present paper, commercial regional aircraft is considered as case study and CFD analysis with the commercial code STAR-CCM+ is performed in order to identify the potential capability to use fuel stored in the tanks as a heat sink for waste heat dissipated by other systems. The complex physical phenomena that characterize the heat transfer inside liquid fuel, at the fuel-ullage interface and inside the ullage are outlined. Boundary conditions, including the effect of different ground and flight conditions, are implemented in the numerical simulation approach. The analysis is implemented for a portion of aluminium wing fuel tank, including the leading edge effects. Effect of liquid fuel transfer among different tank compartments and the air flow in the ullage is included. According to Fuel Tank Flammability Assessment Method (FTFAM) proposed by the Federal Aviation Administration, the results are exploited in terms of exponential time constants and fuel temperature difference to the ambient for the different cases investigated.

Modeling Flight Attendants’ Exposures to Pesticide in Disinsected Aircraft Cabins

PubMed Central

Zhang, Yong; Isukapalli, Sastry; Georgopoulos, Panos; Weisel, Clifford

2014-01-01

Aircraft cabin disinsection is required by some countries to kill insects that may pose risks to public health and native ecological systems. A probabilistic model has been developed by considering the microenvironmental dynamics of the pesticide in conjunction with the activity patterns of flight attendants, to assess their exposures and risks to pesticide in disinsected aircraft cabins under three scenarios of pesticide application. Main processes considered in the model are microenvironmental transport and deposition, volatilization, and transfer of pesticide when passengers and flight attendants come in contact with the cabin surfaces. The simulated pesticide airborne mass concentration and surface mass loadings captured measured ranges reported in the literature. The medians (means±standard devitions) of daily total exposures intakes were 0.24 (3.8±10.0), 1.4 (4.2±5.7) and 0.15 (2.1±3.2) μg/(day kg BW) for scenarios of Residual Application, Preflight and Top-of-Descent spraying, respectively. Exposure estimates were sensitive to parameters corresponding to pesticide deposition, body surface area and weight, surface-to-body transfer efficiencies, and efficiency of adherence to skin. Preflight spray posed 2.0 and 3.1 times higher pesticide exposure risk levels for flight attendants in disinsected aircraft cabins than Top-of-Descent spray and Residual Application, respectively. PMID:24251734

78 FR 76114 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-16

... Proposed Issuance of Letter of Offer Pursuant to Section 36(b)(1) of the Arms Export Control Act, as... Articles or Services under Consideration for Purchase: 14 CH-47D Model Aircraft to include T55-GA-714A Turbine Engines, 2 per aircraft (14 ac x 2 = 28 engines) 5 T55-GA-714A Turbine Engines to be used as...

Visual Effects in the High Performance Aircraft Cockpit

DTIC Science & Technology

1988-04-01

The RPE acts in a supportive metabolic role to the photoreceptors and if damaged or artificially aged this...unlimited. 2. Lenses cannot mist and provide minor protection against 4. Provide greater protection against splatter from the firing of MDC and impact...almost opposite requirements: the air combat role and the ground attack role . For the air combat role , the aircraft is used against

Charge control experiments on a CH-53E helicopter in a dusty environment

NASA Technical Reports Server (NTRS)

Moore, C. B.; Jones, J. J.; Hunyady, S. J.

1991-01-01

Charge control tests were carried out on a ground based, Marine Corps helicopter to determine if control of the electric fields acting on the engine exhaust gases could be used to reduce the electrification of the helicopter when it operated in a dusty atmosphere. The test aircraft was flown to a dusty, unpaved area and was then isolated electrically from the earth. When the helicopter engines were operated at ground idle with the rotor locked, the isolated aircraft charged positively, as had been observed previously. However, when the rotor brake was released and the turning rotor created a downdraft that raised dust clouds, the aircraft always became charged more positively, to potentials ranging form +30 to +45 kV. The dust clouds raised by the rotor downwash invariably carried negative space charges with concentrations of up to -100 nC/cu m and caused surface electric fields with strengths of up to 10 kV/m immediately down wind of the aircraft. The natural charging of the helicopter operating in these dust clouds was successfully opposed by control of the electric fields acting on the hot, electrically conductive exhaust gases. The control was achieved by placing electrostatic shield around the exhausts.

Rethinking Import and Export Controls for Defense-Related Goods

DTIC Science & Technology

2013-05-01

restrictions were imposed on the basis of country (Trading with the Enemy Act) or product (Neutrality Act). However, in the post-war environment, a more mixed...described below. • Arms Export Control Act (AECA) of 1976—grants the President the power to control the export of defense products and services. The act...defense-related items and services. The products regulated include weapons systems (e.g., aircraft, tanks, etc.) but also include subsystems or

75 FR 42030 - Amendments to National Emission Standards for Hazardous Air Pollutants: Area Source Standards for...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-20

.... National Technology Transfer Advancement Act J. Executive Order 12898: Federal Actions to Address..., or use of energy. I. National Technology Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995 (``NTTAA''), Public Law 104-113 (15 U.S.C. 272 note) directs...

76 FR 35806 - Amendments to National Emission Standards for Hazardous Air Pollutants for Area Sources: Plating...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-06-20

..., or Use I. National Technology Transfer Advancement Act J. Executive Order 12898: Federal Actions To... action under Executive Order 12866. I. National Technology Transfer Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act (NTTAA) of 1995 (Pub. L. 104-113, section 12(d), 15 U.S.C...

[Monitoring of Crack Propagation in Repaired Structures Based on Characteristics of FBG Sensors Reflecting Spectra].

PubMed

Yuan, Shen-fang; Jin, Xin; Qiu, Lei; Huang, Hong-mei

2015-03-01

In order to improve the security of aircraft repaired structures, a method of crack propagation monitoring in repaired structures is put forward basing on characteristics of Fiber Bragg Grating (FBG) reflecting spectra in this article. With the cyclic loading effecting on repaired structure, cracks propagate, while non-uniform strain field appears nearby the tip of crack which leads to the FBG sensors' reflecting spectra deformations. The crack propagating can be monitored by extracting the characteristics of FBG sensors' reflecting spectral deformations. A finite element model (FEM) of the specimen is established. Meanwhile, the distributions of strains which are under the action of cracks of different angles and lengths are obtained. The characteristics, such as main peak wavelength shift, area of reflecting spectra, second and third peak value and so on, are extracted from the FBGs' reflecting spectral which are calculated by transfer matrix algorithm. An artificial neural network is built to act as the model between the characteristics of the reflecting spectral and the propagation of crack. As a result, the crack propagation of repaired structures is monitored accurately and the error of crack length is less than 0.5 mm, the error of crack angle is less than 5 degree. The accurately monitoring problem of crack propagation of repaired structures is solved by taking use of this method. It has important significance in aircrafts safety improvement and maintenance cost reducing.

Reusable Surface Insulation

NASA Technical Reports Server (NTRS)

1997-01-01

Advanced Flexible Reusable Surface Insulation, developed by Ames Research Center, protects the Space Shuttle from the searing heat that engulfs it on reentry into the Earth's atmosphere. Initially integrated into the Space Shuttle by Rockwell International, production was transferred to Hi-Temp Insulation Inc. in 1974. Over the years, Hi-Temp has created many new technologies to meet the requirements of the Space Shuttle program. This expertise is also used commercially, including insulation blankets to cover aircrafts parts, fire barrier material to protect aircraft engine cowlings and aircraft rescue fire fighter suits. A Fire Protection Division has also been established, offering the first suit designed exclusively by and for aircraft rescue fire fighters. Hi-Temp is a supplier to the Los Angeles City Fire Department as well as other major U.S. civil and military fire departments.

27 CFR 19.531 - Authorized withdrawals without payment of tax.

Code of Federal Regulations, 2010 CFR

2010-04-01

...) Supplies for certain vessels and aircraft, as authorized under 19 U.S.C. 1309; (e) Transfer to customs... authorized under 26 U.S.C. 5373; (g) Transfer to any university, college of learning, or institution of... paragraphs (a) through (e) of this section shall be in accordance with the regulations in 27 CFR part 28; or...

Navy Nuclear Aircraft Carrier (CVN) Homeporting at Mayport: Background and Issues for Congress

DTIC Science & Technology

2009-12-23

releaseid= 12600 . 2 The Navy has not identified which specific CVN it would transfer, and a CVN transferred to Mayport could come from any of the...Mayport,” available online at http://www.defenselink.mil/releases/release.aspx?releaseid= 12600 . 7Although the Navy states that the CVN based at Yokosuka

Ka-band MMIC arrays for ACTS Aero Terminal Experiment

NASA Technical Reports Server (NTRS)

Raquet, C.; Zakrajsek, R.; Lee, R.; Turtle, J.

1992-01-01

An antenna system consisting of three experimental Ka-band active arrays using GaAs MMIC devices at each radiating element for electronic beam steering and distributed power amplification is presented. The MMIC arrays are to be demonstrated in the ACTS Aeronautical Terminal Experiment, planned for early 1994. The experiment is outlined, with emphasis on a description of the antenna system. Attention is given to the way in which proof-of-concept MMIC arrays featuring three different state-of-the-art approaches to Ka-band MMIC insertion are being incorporated into an experimental aircraft terminal for the demonstration of an aircraft-to-satellite link, providing a basis for follow-on MMIC array development.

Carbon/graphite fiber risk analysis and assessment study: An assessment of the risk to Douglas commercial transport aircraft

NASA Technical Reports Server (NTRS)

Schjelderup, H. C.; Cook, C. Q.; Snyder, E.; Henning, B.; Hosford, J.; Gilles, D. L.; Swanstrom, C. W.

1980-01-01

The potential hazard to electrical and electronic devices should there be a release of free carbon fibers due to an aircraft crash and fire was assessed. Exposure and equipment sensitivity data were compiled for a risk analysis. Results are presented in the following areas: DC-9/DC-10 electrical/electronic component characterization; DC-9 and DC-10 fiber transfer functions; potential for transport aircraft equipment exposure to carbon fibers; and equipment vulnerability assessment. Results reflect only a negligible increase in risk for the DC-9 and DC-10 fleets either now or projected to 1993.

NASA KingAir #801 during takeoff

NASA Technical Reports Server (NTRS)

1999-01-01

NASA KingAir N801NA during takeoff. The Beechcraft Beech 200 Super KingAir aircraft N7NA, known as NASA 7, has been a support aircraft for many years, flying 'shuttle' missions to Ames Research Center. It once flew from the Jet Propulsion Laboratory and back each day but now (2001) flies between the Dryden Flight Research Center and Ames. Dryden assumed the mission and aircraft in September 1996. A second Beechcraft Beech 200 Super King Air, N701NA, redesignated N801NA, transferred to Dryden on 3 Oct. 1997 and is used for research missions but substitutes for NASA 7 on shuttle missions when NASA 7 is not available.

Integrated Application of Active Controls (IAAC) Technology to an Advanced Subsonic Transport: Project Plan

NASA Technical Reports Server (NTRS)

1981-01-01

The state of the art of active controls technology (ACT) and a recommended ACT development program plan are reviewed. The performance benefits and cost of ownership of an integrated application of ACT to civil transport aircraft is to be assessed along with the risk and laboratory and/or flight experiments designed to reduce the technical risks to a commercially acceptable level.

NASA aviation safety reporting system

NASA Technical Reports Server (NTRS)

1977-01-01

A decline in reports concerning small aircraft was noted; more reports involved transport aircraft, professional pilots, instrument meteorological conditions, and weather problems. A study of 136 reports of operational problems in terminal radar service areas was made. Pilot, controller, and system factors were found to be associated with these occurrences. Information transfer difficulties were prominent. Misunderstandings by pilots, and in some cases by controllers, of the policies and limitations of terminal radar programs were observed.

Aircraft Lightning Protection Handbook

DTIC Science & Technology

1989-09-01

tape or metal braid . The shield. The effect of leakage through the connector can transfer characteristics can seldom be determined by thus be...62 REFERENCES 66 CHAPTER 4 LIGHTNING EFFECTS ON AIRCRAFT 69 4.1 Introduction 69 4.2 Direct Effects on Metal Structures 70 4.2.1 Pitting and Melt...Certification plans 112 5.8 Test Plans 113 REFERENCES 113 Chapter 6 DIRECT EFFECTS PROTECTION 115 6.1 Introduction 115 6.2 Direct Effects on Metal Structures

A NASA F/A-18, participating in the Automated Aerial Refueling (AAR) project, flies over the Dryden

NASA Technical Reports Server (NTRS)

2002-01-01

A NASA F/A-18 is participating in the Automated Aerial Refueling (AAR) project. The 300-gallon aerial refueling store seen on the belly of the aircraft carries fuel and a refueling drogue. This aircraft acts as a tanker in the study to develop an aerodynamic model for future automated aerial refueling, especially of unmanned vehicles.

76 FR 18957 - Airworthiness Directives; Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701 & 702...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-04-06

... Model CL-600-2D24 (Regional Jet Series 900) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT... referred to Task 05- 51-27-210-801 of Part 2, Volume 1, of the Bombardier CRJ Series Regional Jet Aircraft... Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety...

78 FR 67309 - Earth Stations Aboard Aircraft

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-12

... Communications Act of 1934, as amended, 47 U.S.C. 154(i), 154(j), 157(a), 302(a), 303(c), 303(e), 303(f), 303(g... Commission's Earth Station Aboard Aircraft, Report and Order (Order), which adopted licensing and service...-orbit space stations operating in the 10.95-11.2 GHz, 11.45-11.7 GHz, 11.7-12.2 GHz and 14.0-14.5 GHz...

[Psychophysiological aspects of naval aviation pilots of the Navy in the operation of highly carrier-based aircraft].

PubMed

Mel'nik, S G; Chulaevskiĭ, A O

2011-08-01

The authors have shown that the most difficult elements of the flight deck of the ship are springboard takeoff and aerofinishing landing. An important task is to study the aerodynamic characteristics of the behavior of the aircraft during takeoff different characteristics, forming crews ready to act in particular situations. Adverse factors are the operating conditions of habitability of aircraft (noise, vibration, fumes in the air at work, and aircraft engines, etc.) that have a significant impact on the life of air crew and engineering staff. It is concluded that the development and use of effective means of protecting the organism from the effect of these factors is a priority for specialists in aviation medicine.

Turbulence modeling of free shear layers for high performance aircraft

NASA Technical Reports Server (NTRS)

Sondak, Douglas

1993-01-01

In many flowfield computations, accuracy of the turbulence model employed is frequently a limiting factor in the overall accuracy of the computation. This is particularly true for complex flowfields such as those around full aircraft configurations. Free shear layers such as wakes, impinging jets (in V/STOL applications), and mixing layers over cavities are often part of these flowfields. Although flowfields have been computed for full aircraft, the memory and CPU requirements for these computations are often excessive. Additional computer power is required for multidisciplinary computations such as coupled fluid dynamics and conduction heat transfer analysis. Massively parallel computers show promise in alleviating this situation, and the purpose of this effort was to adapt and optimize CFD codes to these new machines. The objective of this research effort was to compute the flowfield and heat transfer for a two-dimensional jet impinging normally on a cool plate. The results of this research effort were summarized in an AIAA paper titled 'Parallel Implementation of the k-epsilon Turbulence Model'. Appendix A contains the full paper.

76 FR 2860 - National Emission Standards for Hazardous Air Pollutants From the Portland Cement Manufacturing...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-01-18

... action under Executive Order 12866. I. National Technology Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995 (``NTTAA''), Public Law 104-113 (15 U.S.C... of section 12(d) of the National Technology Transfer and Advancement Act of 1995 (15 U.S.C. 272) do...

Training Technology Transfer Act of 1984. Hearing before the Subcommittee on Education, Arts and Humanities of the Committee on Labor and Human Resources, United States Senate, Ninety-Eighth Congress, Second Session on S. 2561. Entitled the "Training Technology Transfer Act of 1984."

ERIC Educational Resources Information Center

Congress of the U.S., Washington, DC. Senate Committee on Labor and Human Resources.

This is a congressional hearing on the Training Technology Transfer Act of 1984, which would establish a mechanism for transferring the Federal Government's investment in computer programming for training systems to those organizations and groups that can use such technology in training the civilian work force. Focus is on refining this bill,…

A Flight Study of the Conversion Maneuver of a Tilt-Duct VTOL Aircraft

NASA Technical Reports Server (NTRS)

Tapscott, Robert J.; Kelley, Henry L.

1960-01-01

Flight records are presented from an early flight test of a wing-tip mounted tilting-ducted-fan, vertical-take-off and landing (VTOL) aircraft configuration. Time histories of the aircraft motions, control positions, and duct pitching-moment variation are presented to illustrate the characteristics of the aircraft in hovering, in conversion from hovering to forward flight, and in conversion from forward flight to hovering. The results indicate that during essentially continuous slow level- flight conversions, this aircraft experiences excessive longitudinal trim changes. Studies have shown that the large trim changes are caused primarily by the variation of aerodynamic moments acting on the duct units. Action of the duct-induced downwash on the horizontal stabilizer during the conversion also contributes to the longitudinal trim variations. Time histories of hovering and slow vertical descent in the final stages of landing in calm air show angular motions of the aircraft as great as +/- 10 deg. about all axes. Stick and pedal displacements required to control the aircraft during the landing maneuver were on the order of 50 to 60 percent of the total travel available.

Graphical and Statistical Analysis of Airplane Passenger Cabin RF Coupling Paths to Avionics

NASA Technical Reports Server (NTRS)

Jafri, Madiha; Ely, Jay; Vahala, Linda

2003-01-01

Portable wireless technology provides many benefits to modern day travelers. Over the years however, numerous reports have cited portable electronic devices (PEDs) as a possible cause of electromagnetic interference (EMI) to aircraft navigation and communication radio systems. PEDs may act as transmitters, both intentional and unintentional, and their signals may be detected by the various radio receiver antennas installed on the aircraft. Measurement of the radiated field coupling between passenger cabin locations and aircraft communication and navigation receivers, via their antennas is defined herein as interference path loss (IPL). IPL data is required for assessing the threat of PEDs to aircraft radios, and is very dependent upon airplane size, the interfering transmitter position within the airplane, and the location of the particular antenna for the aircraft system of concern. NASA Langley Research Center, Eagles Wings Inc., and United Airlines personnel performed extensive IPL measurements on several Boeing 737 airplanes.

Effects of modeling errors on trajectory predictions in air traffic control automation

NASA Technical Reports Server (NTRS)

Jackson, Michael R. C.; Zhao, Yiyuan; Slattery, Rhonda

1996-01-01

Air traffic control automation synthesizes aircraft trajectories for the generation of advisories. Trajectory computation employs models of aircraft performances and weather conditions. In contrast, actual trajectories are flown in real aircraft under actual conditions. Since synthetic trajectories are used in landing scheduling and conflict probing, it is very important to understand the differences between computed trajectories and actual trajectories. This paper examines the effects of aircraft modeling errors on the accuracy of trajectory predictions in air traffic control automation. Three-dimensional point-mass aircraft equations of motion are assumed to be able to generate actual aircraft flight paths. Modeling errors are described as uncertain parameters or uncertain input functions. Pilot or autopilot feedback actions are expressed as equality constraints to satisfy control objectives. A typical trajectory is defined by a series of flight segments with different control objectives for each flight segment and conditions that define segment transitions. A constrained linearization approach is used to analyze trajectory differences caused by various modeling errors by developing a linear time varying system that describes the trajectory errors, with expressions to transfer the trajectory errors across moving segment transitions. A numerical example is presented for a complete commercial aircraft descent trajectory consisting of several flight segments.

Transfer from Audiovisual Pretraining to a Continuous Perceptual Motor Task. Final Report for Period June 1972 - August 1973.

ERIC Educational Resources Information Center

Wood, Milton E.; Gerlach, Vernon S.

A technique was developed for providing transfer-of-training from a form of audiovisual pretraining to an instrument flight task. The continuous flight task was broken into discrete categories of flight; each category combined an instrument configuration with a return-to-criterion aircraft control response. Three methods of sequencing categories…

Development of resins for composites by resin transfer molding

NASA Technical Reports Server (NTRS)

Woo, Edmund P.; Puckett, Paul M.; Maynard, Shawn J.

1991-01-01

Designed to cover a wide range of resin technology and to meet the near-term and long-term needs of the aircraft industry, this research has three objectives: to produce resin transfer molding (RES) resins with improved processability, to produce prepreg systems with high toughness and service temperature, and to produce new resin systems. Progress on reaching the objectives is reported.

Computer Generated Image: Relative Training Effectiveness of Day Versus Night Visual Scenes. Final Report.

ERIC Educational Resources Information Center

Martin, Elizabeth L.; Cataneo, Daniel F.

A study was conducted by the Air Force to determine the extent to which takeoff/landing skills learned in a simulator equipped with a night visual system would transfer to daytime performance in the aircraft. A transfer-of-training design was used to assess the differential effectiveness of simulator training with a day versus a night…

Piloting Changes to Changing Aircraft Dynamics: What Do Pilots Need to Know?

NASA Technical Reports Server (NTRS)

Trujillo, Anna C.; Gregory, Irene M.

2011-01-01

An experiment was conducted to quantify the effects of changing dynamics on a subject s ability to track a signal in order to eventually model a pilot adapting to changing aircraft dynamics. The data will be used to identify primary aircraft dynamics variables that influence changes in pilot s response and produce a simplified pilot model that incorporates this relationship. Each run incorporated a different set of second-order aircraft dynamics representing short period transfer function pitch attitude response: damping ratio, frequency, gain, zero location, and time delay. The subject s ability to conduct the tracking task was the greatest source of root mean square error tracking variability. As for the aircraft dynamics, the factors that affected the subjects ability to conduct the tracking were the time delay, frequency, and zero location. In addition to creating a simplified pilot model, the results of the experiment can be utilized in an advisory capacity. A situation awareness/prediction aid based on the pilot behavior and aircraft dynamics may help tailor pilot s inputs more quickly so that PIO or an upset condition can be avoided.

Application of the H-Mode, a Design and Interaction Concept for Highly Automated Vehicles, to Aircraft

NASA Technical Reports Server (NTRS)

Goodrich, Kenneth H.; Flemisch, Frank O.; Schutte, Paul C.; Williams, Ralph A.

2006-01-01

Driven by increased safety, efficiency, and airspace capacity, automation is playing an increasing role in aircraft operations. As aircraft become increasingly able to autonomously respond to a range of situations with performance surpassing human operators, we are compelled to look for new methods that help us understand their use and guide their design using new forms of automation and interaction. We propose a novel design metaphor to aid the conceptualization, design, and operation of highly-automated aircraft. Design metaphors transfer meaning from common experiences to less familiar applications or functions. A notable example is the "Desktop metaphor" for manipulating files on a computer. This paper describes a metaphor for highly automated vehicles known as the H-metaphor and a specific embodiment of the metaphor known as the H-mode as applied to aircraft. The fundamentals of the H-metaphor are reviewed followed by an overview of an exploratory usability study investigating human-automation interaction issues for a simple H-mode implementation. The envisioned application of the H-mode concept to aircraft is then described as are two planned evaluations.

An engine trade study for a supersonic STOVL fighter-attack aircraft, volume 1

NASA Technical Reports Server (NTRS)

Beard, B. B.; Foley, W. H.

1982-01-01

The best main engine for an advanced STOVL aircraft flight demonstrator was studied. The STOVL aircraft uses ejectors powered by engine bypass flow together with vectored core exhaust to achieve vertical thrust capability. Bypass flow and core flow are exhausted through separate nozzles during wingborne flight. Six near term turbofan engines were examined for suitability for this aircraft concept. Fan pressure ratio, thrust split between bypass and core flow, and total thrust level were used to compare engines. One of the six candidate engines was selected for the flight demonstrator configuration. Propulsion related to this aircraft concept was studied. A preliminary candidate for the aircraft reaction control system for hover attitude control was selected. A mathematical model of transfer of bypass thrust from ejectors to aft directed nozzle during the transition to wingborne flight was developed. An equation to predict ejector secondary air flow rate and ram drag is derived. Additional topics discussed include: nozzle area control, ejector to engine inlet reingestion, bypass/core thrust split variation, and gyroscopic behavior during hover.

U-2 Aircraft at the Lewis Research Center

NASA Image and Video Library

1973-09-21

A National Aeronautics and Space Administration (NASA) Lockheed U-2 aircraft on display at the 1973 Inspection of the Lewis Research Center in Cleveland, Ohio. Lockheed developed the U-2 as a high-altitude reconnaissance aircraft in the early 1950s before satellites were available. The U-2 could cruise over enemy territory at 70,000 feet and remain impervious to ground fire, interceptor aircraft, and even radar. An advanced camera system was designed specifically for the aircraft. The pilot is required to use a pressure suit similar to those worn by astronauts. NASA’s Ames Research Center received two U-2 aircraft in April 1971 to conduct high-altitude research. They were used to study and monitor various Earth resources, celestial bodies, atmospheric chemistry, and oceanic processes. NASA replaced its U-2s with ER-2 aircraft in 1981 and 1989. The ER-2s were designed to carry up to 2600 pounds of scientific equipment. The ER-2 program was transferred to Dryden Flight Research Center in 1997. Since the inaugural flight for this program on August 31, 1971, NASA’s U-2 and ER-2 aircraft have flown more than 4500 data missions and test flights for NASA, other federal agencies, states, universities, and the private sector.

Thermal Management Tools for Propulsion System Trade Studies and Analysis

NASA Technical Reports Server (NTRS)

McCarthy, Kevin; Hodge, Ernie

2011-01-01

Energy-related subsystems in modern aircraft are more tightly coupled with less design margin. These subsystems include thermal management subsystems, vehicle electric power generation and distribution, aircraft engines, and flight control. Tighter coupling, lower design margins, and higher system complexity all make preliminary trade studies difficult. A suite of thermal management analysis tools has been developed to facilitate trade studies during preliminary design of air-vehicle propulsion systems. Simulink blocksets (from MathWorks) for developing quasi-steady-state and transient system models of aircraft thermal management systems and related energy systems have been developed. These blocksets extend the Simulink modeling environment in the thermal sciences and aircraft systems disciplines. The blocksets include blocks for modeling aircraft system heat loads, heat exchangers, pumps, reservoirs, fuel tanks, and other components at varying levels of model fidelity. The blocksets have been applied in a first-principles, physics-based modeling and simulation architecture for rapid prototyping of aircraft thermal management and related systems. They have been applied in representative modern aircraft thermal management system studies. The modeling and simulation architecture has also been used to conduct trade studies in a vehicle level model that incorporates coupling effects among the aircraft mission, engine cycle, fuel, and multi-phase heat-transfer materials.

Contributions of the Transonic Dynamics Tunnel to the Testing of Active Control of Aeroelastic Response

NASA Technical Reports Server (NTRS)

Perry, Boyd, III; Noll, Thomas E.; Scott, Robert C.

2000-01-01

By the 1960s, researchers began to investigate the feasibility of using active controls technology (ACT) for increasing the capabilities of military and commercial aircraft. Since then many researchers, too numerous to mention, have investigated and demonstrated the usefulness of ACT for favorably modifying the aeroelastic response characteristics of flight vehicles. As a result, ACT entered the limelight as a viable tool for answering some very difficult design questions and had the potential for obtaining structural weight reductions optimizing maneuvering performance, and satisfying the multimission requirements being imposed on future military and commercial aircraft designs. Over the past 40 years, the NASA Langley Research Center (LaRC) has played a major role in developing ACT in part by its participation in many wind-tunnel programs conducted in the Transonic Dynamics Tunnel (TDT). These programs were conducted for the purposes of: (1) establishing concept feasibility; (2) demonstrating proof of concept; and (3) providing data for validating new modeling, analysis, and design methods. This paper provides an overview of the ACT investigations conducted in the TDT. For each program discussed herein, the objectives of the effort, the testing techniques, the test results, any, signIficant findings, and the lessons learned with respect to ACT testing are presented.

Task Force Report on Emergency Evacuation of Transport Airplanes. Volume 1. Summary report.

DTIC Science & Technology

1986-07-01

panel was composed of five FAA specialists: Fred Jenkins - Aircraft Certification, Joe Starkel - Aircraft Certification, Rick Cremer - Air Carrier...and Special Projects Officer, Transport Airplane Certification Directorate Chairman, Training and Operations Working Group: Rick L. Cremer , Acting...Washington, D.C. Kirke Comstock ATA - United Airlines Rick Cremer FAA, AFS-220, Washington, D.C. Fred W. Crenshaw FAA, AFS-300, Washington, D.C. Jim

Human factors analysis and classification system applied to civil aircraft accidents in India.

PubMed

Gaur, Deepak

2005-05-01

The Human Factors Analysis and Classification System (HFACS) has gained wide acceptance as a tool to classify human factors in aircraft accidents and incidents. This study on application of HFACS to civil aircraft accident reports at Directorate General Civil of Aviation (DGCA), India, was conducted to ascertain the practicability of applying HFACS to existing investigation reports and to analyze the trends of human factor causes of civil aircraft accidents. Accident investigation reports held at DGCA, New Delhi, for the period 1990--99 were scrutinized. In all, 83 accidents occurred during this period, of which 48 accident reports were evaluated in this study. One or more human factors contributed to 37 of the 48 (77.1%) accidents. The commonest unsafe act was 'skill based errors' followed by 'decision errors.' Violations of laid down rules were contributory in 16 cases (33.3%). 'Preconditions for unsafe acts' were seen in 23 of the 48 cases (47.9%). A fairly large number (52.1%) had 'organizational influences' contributing to the accident. These results are in consonance with larger studies of accidents in the U.S. Navy and general aviation. Such a high percentage of 'organizational influences' has not been reported in other studies. This is a healthy sign for Indian civil aviation, provided effective remedial action for the same is undertaken.

78 FR 5861 - National Plan of Integrated Airport Systems: Clarification of Wildlife Hazard Management...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-28

... Property Act for airport purposes (``Subject Airports''), to conduct Wildlife Hazard Site Visits (WHSVs) or... of land under the Surplus Property Act for airport purposes to identify and mitigate wildlife hazards.... These airports are typically smaller and have less air traffic, more piston-powered aircraft, and...

Virtual Sensor for Failure Detection, Identification and Recovery in the Transition Phase of a Morphing Aircraft

PubMed Central

Heredia, Guillermo; Ollero, Aníbal

2010-01-01

The Helicopter Adaptive Aircraft (HADA) is a morphing aircraft which is able to take-off as a helicopter and, when in forward flight, unfold the wings that are hidden under the fuselage, and transfer the power from the main rotor to a propeller, thus morphing from a helicopter to an airplane. In this process, the reliable folding and unfolding of the wings is critical, since a failure may determine the ability to perform a mission, and may even be catastrophic. This paper proposes a virtual sensor based Fault Detection, Identification and Recovery (FDIR) system to increase the reliability of the HADA aircraft. The virtual sensor is able to capture the nonlinear interaction between the folding/unfolding wings aerodynamics and the HADA airframe using the navigation sensor measurements. The proposed FDIR system has been validated using a simulation model of the HADA aircraft, which includes real phenomena as sensor noise and sampling characteristics and turbulence and wind perturbations. PMID:22294922

Virtual sensor for failure detection, identification and recovery in the transition phase of a morphing aircraft.

PubMed

Heredia, Guillermo; Ollero, Aníbal

2010-01-01

The Helicopter Adaptive Aircraft (HADA) is a morphing aircraft which is able to take-off as a helicopter and, when in forward flight, unfold the wings that are hidden under the fuselage, and transfer the power from the main rotor to a propeller, thus morphing from a helicopter to an airplane. In this process, the reliable folding and unfolding of the wings is critical, since a failure may determine the ability to perform a mission, and may even be catastrophic. This paper proposes a virtual sensor based Fault Detection, Identification and Recovery (FDIR) system to increase the reliability of the HADA aircraft. The virtual sensor is able to capture the nonlinear interaction between the folding/unfolding wings aerodynamics and the HADA airframe using the navigation sensor measurements. The proposed FDIR system has been validated using a simulation model of the HADA aircraft, which includes real phenomena as sensor noise and sampling characteristics and turbulence and wind perturbations.

Criteria for design of integrated flight/propulsion control systems for STOVL fighter aircraft

NASA Technical Reports Server (NTRS)

Franklin, James A.

1993-01-01

As part of NASA's program to develop technology for short takeoff and vertical landing (STOVL) fighter aircraft, control system designs have been developed for a conceptual STOVL aircraft. This aircraft is representative of the class of mixed-flow remote-lift concepts that was identified as the preferred design approach by the U.S./U.K. STOVL Joint Assessment and Ranking Team. The control system designs have been evaluated throughout the powered-lift flight envelope on the Vertical Motion Simulator (VMS) at Ames Research Center. Items assessed in the control system evaluation were: maximum control power used in transition and vertical flight, control system dynamic response associated with thrust transfer for attitude control, thrust margin in the presence of ground effect and hot-gas ingestion, and dynamic thrust response for the engine core. Effects of wind, turbulence, and ship airwake disturbances are incorporated in the evaluation. Results provide the basis for a reassessment of existing flying-qualities design criteria applied to STOVL aircraft.

Design criteria for integrated flight/propulsion control systems for STOVL fighter aircraft

NASA Technical Reports Server (NTRS)

Franklin, James A.

1993-01-01

As part of NASA's program to develop technology for short takeoff and vertical landing (STOVL) fighter aircraft, control system designs have been developed for a conceptual STOVL aircraft. This aircraft is representative of the class of mixed-flow remote-lift concepts that was identified as the preferred design approach by the US/UK STOVL Joint Assessment and Ranking Team. The control system designs have been evaluated throughout the powered-lift flight envelope on Ames Research Center's Vertical Motion Simulator. Items assessed in the control system evaluation were: maximum control power used in transition and vertical flight, control system dynamic response associated with thrust transfer for attitude control, thrust margin in the presence of ground effect and hot gas ingestion, and dynamic thrust response for the engine core. Effects of wind, turbulence, and ship airwake disturbances are incorporated in the evaluation. Results provide the basis for a reassessment of existing flying qualities design criteria applied to STOVL aircraft.

42 CFR 137.96 - Does the Prompt Payment Act apply to funds transferred to a Self-Governance Tribe in a compact or...

Code of Federal Regulations, 2010 CFR

2010-10-01

... transferred to a Self-Governance Tribe in a compact or funding agreement? 137.96 Section 137.96 Public Health... HEALTH AND HUMAN SERVICES TRIBAL SELF-GOVERNANCE Funding Prompt Payment Act § 137.96 Does the Prompt Payment Act apply to funds transferred to a Self-Governance Tribe in a compact or funding agreement? Yes...

Dual towline spin-recovery device

NASA Technical Reports Server (NTRS)

White, W. L. (Inventor)

1985-01-01

A device which corrects aerodynamic spin is described wherein a parachute exerts antispin forces on an aircraft to effect spin recovery. The dual parachute towlines and are each attached to the parachute and are attached to the rear fuselage equidistant to and on opposite sides of the aircraft centerline. As the parachute is deployed during spin, the parachute force acts through only the towing and exerts its force outboard of center on the aircraft. As a result, the parachute exerts not only an antispin torque, but additionally causes the aircraft to roll, creating a gyroscopic antispin rolling moment. The additional antispin rolling moment facilitates spin recovery by permitting a relatively smaller parachute to accomplish spin recovery equivalent to that of a larger parachute attached to the center of the rear fuselage.

Comparison of Requirements for Composite Structures for Aircraft and Space Applications

NASA Technical Reports Server (NTRS)

Raju, Ivatury S.; Elliott, Kenny B.; Hampton, Roy W.; Knight, Norman F., Jr.; Aggarwal, Pravin; Engelstad, Stephen P.; Chang, James B.

2010-01-01

In this paper, the aircraft and space vehicle requirements for composite structures are compared. It is a valuable exercise to study composite structural design approaches used in the airframe industry, and to adopt methodology that is applicable for space vehicles. The missions, environments, analysis methods, analysis validation approaches, testing programs, build quantities, inspection, and maintenance procedures used by the airframe industry, in general, are not transferable to spaceflight hardware. Therefore, while the application of composite design approaches from other industries is appealing, many aspects cannot be directly utilized. Nevertheless, experiences and research for composite aircraft structures may be of use in unexpected arenas as space exploration technology develops, and so continued technology exchanges are encouraged.

General Conformity Training Modules: Appendix A Sample Emissions Calculations

EPA Pesticide Factsheets

Appendix A of the training modules gives example calculations for external and internal combustion sources, construction, fuel storage and transfer, on-road vehicles, aircraft operations, storage piles, and paved roads.

27 CFR 19.605 - Additional marks on portable containers.

Code of Federal Regulations, 2010 CFR

2010-04-01

... manufacturing bonded warehouses, transfer to foreign-trade zones or supplies for certain vessels and aircraft... plant control data. However, marks or attachments shall not conceal, obscure, interfere with or conflict...

Microwave and infrared simulations of an intense convective system and comparison with aircraft observations

NASA Technical Reports Server (NTRS)

Prasad, N.; Yeh, Hwa-Young M.; Adler, Robert F.; Tao, Wei-Kuo

1995-01-01

A three-dimensional cloud model, radiative transfer model-based simulation system is tested and validated against the aircraft-based radiance observations of an intense convective system in southeastern Virginia on 29 June 1986 during the Cooperative Huntsville Meteorological Experiment. NASA's ER-2, a high-altitude research aircraft with a complement of radiometers operating at 11-micrometer infrared channel and 18-, 37-, 92-, and 183-GHz microwave channels provided data for this study. The cloud model successfully simulated the cloud system with regard to aircraft- and radar-observed cloud-top heights and diameters and with regard to radar-observed reflectivity structure. For the simulation time found to correspond best with the aircraft- and radar-observed structure, brightness temperatures T(sub b) are simulated and compared with observations for all the microwave frequencies along with the 11-micrometer infrared channel. Radiance calculations at the various frequencies correspond well with the aircraft observations in the areas of deep convection. The clustering of 37-147-GHz T(sub b) observations and the isolation of the 18-GHz values over the convective cores are well simulated by the model. The radiative transfer model, in general, is able to simulate the observations reasonably well from 18 GHz through 174 GHz within all convective areas of the cloud system. When the aircraft-observed 18- and 37-GHz, and 90- and 174-GHz T(sub b) are plotted against each other, the relationships have a gradual difference in the slope due to the differences in the ice particle size in the convective and more stratiform areas of the cloud. The model is able to capture these differences observed by the aircraft. Brightness temperature-rain rate relationships compare reasonably well with the aircraft observations in terms of the slope of the relationship. The model calculations are also extended to select high-frequency channels at 220, 340, and 400 GHz to simulate the Millimeter-wave Imaging Radiometer aircraft instrument to be flown in the near future. All three of these frequencies are able to discriminate the convective and anvil portions of the system, providing useful information similar to that from the frequencies below 183 GHz but with potentially enhanced spatial resolution from a satellite platform. In thin clouds, the dominant effect of water vapor is seen at 174, 340, and 400 GHz. In thick cloudy areas, the scattering effect is dominant at 90 and 220 GHz, while the overlaying water vapor can attenuate at 174, 340, and 400 GHz. All frequencies (90-400 GHz) show strong signatures in the core.

Assessment of Superstructure Ice Protection as Applied to Offshore Oil Operations Safety: Problems, Hazards, Needs, and Potential Transfer Technologies

DTIC Science & Technology

2008-09-01

thermostats, or materials such as carbon layers, which vary in thickness with location and are self - healing and self - regulating. Ships commonly use heating...aircraft today. Pneumatic deicing systems consist of rubber or other elastomeric boots placed on the leading edge of an aircraft wing or on any surface...by Kenney, two as- semblies consisting of neoprene rubber and urethane-coated Dacron fabric were hung from bulkheads where icing would occur. A timer

Advanced composite vertical stabilizer for DC-10 transport aircraft

NASA Technical Reports Server (NTRS)

Stephens, C. O.

1979-01-01

Structural design, tooling, fabrication, and test activities are reported for a program to develop an advanced composite vertical stabilizer (CVS) for the DC 10 Commercial Transport Aircraft. Structural design details are described and the status of structural and weight analyses are reported. A structural weight reduction of 21.7% is currently predicted. Test results are discussed for sine wave stiffened shear webs containing representative of the CVS spar webs and for lightning current transfer and tests on a panel representative of the CVS skins.

Bridge Busters: The 397th Bombardment Group (Medium) and the B-26 Marauder in World War II

DTIC Science & Technology

2015-06-01

up largely of new pilots from the training pipeline, these established groups transitioned from flying other aircraft. Unfortunately, four fatal...The 322 BG became the first of four initial B-26 groups to join the Eighth AF’s Third Bombardment Wing. With its first aircraft arriving in England...AF refused the suggestion. Marauders continued in the medium bombing role.101 In October 1943, the AAF transferred all four B-26 groups in

14 CFR 21.335 - Responsibilities of exporters.

Code of Federal Regulations, 2010 CFR

2010-01-01

... rigging, alignment, and ground testing is necessary to ensure that the aircraft will conform to the.... registration and airworthiness certificates, giving the date of transfer of title, and the name and address of...

49 CFR 1544.239 - Known shipper program.

Code of Federal Regulations, 2013 CFR

2013-10-01

... a TSA security program approved for transfer of cargo to an aircraft operator with a full program or...) Corrections and updates of this information upon learning of a change to the information specified in...

49 CFR 1544.239 - Known shipper program.

Code of Federal Regulations, 2010 CFR

2010-10-01

... a TSA security program approved for transfer of cargo to an aircraft operator with a full program or...) Corrections and updates of this information upon learning of a change to the information specified in...

49 CFR 1544.239 - Known shipper program.

Code of Federal Regulations, 2014 CFR

2014-10-01

... a TSA security program approved for transfer of cargo to an aircraft operator with a full program or...) Corrections and updates of this information upon learning of a change to the information specified in...

49 CFR 1544.239 - Known shipper program.

Code of Federal Regulations, 2012 CFR

2012-10-01

... a TSA security program approved for transfer of cargo to an aircraft operator with a full program or...) Corrections and updates of this information upon learning of a change to the information specified in...

49 CFR 1544.239 - Known shipper program.

Code of Federal Regulations, 2011 CFR

2011-10-01

... a TSA security program approved for transfer of cargo to an aircraft operator with a full program or...) Corrections and updates of this information upon learning of a change to the information specified in...

Pathogen boosted adoptive cell transfer immunotherapy to treat solid tumors.

PubMed

Xin, Gang; Schauder, David M; Jing, Weiqing; Jiang, Aimin; Joshi, Nikhil S; Johnson, Bryon; Cui, Weiguo

2017-01-24

Because of insufficient migration and antitumor function of transferred T cells, especially inside the immunosuppressive tumor microenvironment (TME), the efficacy of adoptive cell transfer (ACT) is much curtailed in treating solid tumors. To overcome these challenges, we sought to reenergize ACT (ReACT) with a pathogen-based cancer vaccine. To bridge ACT with a pathogen, we genetically engineered tumor-specific CD8 T cells in vitro with a second T-cell receptor (TCR) that recognizes a bacterial antigen. We then transferred these dual-specific T cells in combination with intratumoral bacteria injection to treat solid tumors in mice. The dual-specific CD8 T cells expanded vigorously, migrated to tumor sites, and robustly eradicated primary tumors. The mice cured from ReACT also developed immunological memory against tumor rechallenge. Mechanistically, we have found that this combined approach reverts the immunosuppressive TME and recruits CD8 T cells with an increased number and killing ability to the tumors.

Consequences of Feeder Delays for the Success of A380 Operations

NASA Technical Reports Server (NTRS)

Ruehle, Jens; Goetsch, Bjoern; Koch, Benjamin

2006-01-01

Due to existing slot and infrastructure constraints at international hub-and-spoke airports, an increase in feeder traffic seems only possible if larger feeder aircraft are used. Using a case study of Lufthansa German Airlines at Frankfurt International Airport, three possible A380 routes (Beijing, Tokyo-Narita, Los Angeles) were examined to assess the extent to which delays of feeder traffic may impact the economic performance of very large aircraft. On the basis of today s delays and anticipated traffic growth in the future, we found that between 9.5% and 13.5% of connecting passengers are unable to transfer to their respective intercontinental flights. In addition, the results demonstrate that a further increase in delays can be detrimental to the profitable operation of very large aircraft, as demonstrated by two out of three simulated routes. We suggest options for airlines operating very large aircraft to counteract the negative impacts of feeder delays.

Program for establishing long-time flight service performance of composite materials in the center wing structure of C-130 aircraft. Phase 5: Flight service and inspection

NASA Technical Reports Server (NTRS)

Kizer, J. A.

1981-01-01

Inspections of the C-130 composite-reinforced center wings were conducted over the flight service monitoring period of more than six years. Twelve inspections were conducted on each of the two C-130H airplanes having composite reinforced center wing boxes. Each inspection consisted of visual and ultrasonic inspection of the selective boron-epoxy reinforced center wings which included the inspection of the boron-epoxy laminates and the boron-epoxy reinforcement/aluminum structure adhesive bondlines. During the flight service monitoring period, the two C-130H aircraft accumulated more than 10,000 flight hours and no defects were detected in the inspections over this period. The successful performance of the C-130H aircraft with composite-reinforced center wings allowed the transfer of the responsibilities of inspecting and maintaining these two aircraft to the U. S. Air Force.

Optimal manpower allocation in aircraft line maintenance (Case in GMF AeroAsia)

NASA Astrophysics Data System (ADS)

Puteri, V. E.; Yuniaristanto, Hisjam, M.

2017-11-01

This paper presents a mathematical modeling to find the optimal manpower allocation in an aircraft line maintenance. This research focuses on assigning the number and type of manpower that allocated to each service. This study considers the licenced worker or Aircraft Maintenance Engineer Licence (AMEL) and non licenced worker or Aircraft Maintenance Technician (AMT). In this paper, we also consider the relationship of each station in terms of the possibility to transfer the manpower among them. The optimization model considers the number of manpowers needed for each service and the requirement of AMEL worker. This paper aims to determine the optimal manpower allocation using the mathematical modeling. The objective function of the model is to find the minimum employee expenses. The model was solved using the ILOG CPLEX software. The results show that the manpower allocation can meet the manpower need and the all load can be served.

Gust response of commercial jet aircraft including effects of autopilot operation

NASA Technical Reports Server (NTRS)

Goldberg, J. H.

1982-01-01

A simplified theory of aircraft vertical acceleration gust response based on a model including pitch, vertical displacement and control motions due to autopilot operation is presented. High-order autopilot transfer functions are utilized for improved accuracy in the determination of the overall response characteristics. Four representative commercial jet aircraft were studied over a wide range of operating conditions and comparisons of individual responses are given. It is shown that autopilot operation relative to the controls fixed case causes response attenuation of from 10 percent to approximately 25 percent depending on flight condition and increases in crossing number up to 30 percent, with variations between aircraft of from 5 percent to 10 percent, in general, reflecting the differences in autopilot design. A detailed computer program description and listing of the calculation procedure suitable for the general application of the theory to any airplane autopilot combination is also included.

Progress in Developing Transfer Functions for Surface Scanning Eddy Current Inspections

NASA Astrophysics Data System (ADS)

Shearer, J.; Heebl, J.; Brausch, J.; Lindgren, E.

2009-03-01

As US Air Force (USAF) aircraft continue to age, additional inspections are required for structural components. The validation of new inspections typically requires a capability demonstration of the method using representative structure with representative damage. To minimize the time and cost required to prepare such samples, Electric Discharge machined (EDM) notches are commonly used to represent fatigue cracks in validation studies. However, the sensitivity to damage typically changes as a function of damage type. This requires a mathematical relationship to be developed between the responses from the two different flaw types to enable the use of EDM notched samples to validate new inspections. This paper reviews progress to develop transfer functions for surface scanning eddy current inspections of aluminum and titanium alloys found in structural aircraft components. Multiple samples with well characterized grown fatigue cracks and master gages with EDM notches, both with a range of flaw sizes, were used to collect flaw signals with USAF field inspection equipment. Analysis of this empirical data was used to develop a transfer function between the response from the EDM notches and grown fatigue cracks.

Managing storm water at airports

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

Halm, M.J.

1996-09-01

Airports are active facilities with numerous on-going operations at their sites. The following operations may adversely affect the water quality of nearby aquatic environments: De-icing runways; de-icing taxiways; de-icing and anti-icing aircraft; aircraft maintenance; and salt de-icer application. Until the amendments to the Clean Water Act of 1972, referred to as the Water Quality Act of 1987, were passed by Congress, the majority of storm water discharges in the US were unregulated. The Water Quality Act of 1987 was promulgated as an effort to manage the pollution resulting from storm water runoff. Many industrial facilities, especially airports, were faced withmore » complex problems in attempting to comply with these new federal regulations. National Pollution Discharge Elimination System (NPDES) permits for airports with more than 50,000 flight operations per year require periodic monitoring of receiving waters and storm sewer outfalls. The federal government has given states jurisdiction in issuing NPDES permits for storm water discharges. States may require composite or grab samples.« less

75 FR 68012 - Notice of Intention To Cancel Registrations of Certain Transfer Agents

Federal Register 2010, 2011, 2012, 2013, 2014

2010-11-04

... SECURITIES AND EXCHANGE COMMISSION [Release No. 34-63211] Notice of Intention To Cancel Registrations of Certain Transfer Agents October 29, 2010. Notice is hereby given that the Securities and... Securities Exchange Act of 1934 (``Act''),\\1\\ cancelling the registrations of the transfer agents whose names...

Tracking Student Transfers: The Perils and Pitfalls of Complying with the New Student Right-To-Know Act (PL 101-542).

ERIC Educational Resources Information Center

Lee, Marcia M.

The Student Right-To-Know and Campus Security Act gives community colleges a strong incentive to track transfer students. Westchester Community College (WCC) in New York devised a four-step process to track students who transferred to four-year college before graduating. The method used to track student transfers involved the following steps: (1)…

Requirements of titanium alloys for aeronautical industry

NASA Astrophysics Data System (ADS)

Ghiban, Brânduşa; Bran, Dragoş-Teodor; Elefterie, Cornelia Florina

2018-02-01

The project presents the requirements imposed for aeronatical components made from Titanium based alloys. Asignificant portion of the aircraft pylons are manufactured from Titanium alloys. Strength, weight, and reliability are the primary factors to consider in aircraft structures. These factors determine the requirements to be met by any material used to construct or repair the aircraft. Many forces and structural stresses act on an aircraft when it is flying and when it is static and this thesis describes environmental factors, conditions of external aggression, mechanical characteristics and loadings that must be satisfied simultaneously by a Ti-based alloy, compared to other classes of aviation alloys (as egg. Inconel super alloys, Aluminum alloys). For this alloy class, the requirements are regarding strength to weight ratio, reliability, corrosion resistance, thermal expansion and so on. These characteristics additionally continue to provide new opportunities for advanced manufacturing methods.

Aeronautical Industry Requirements for Titanium Alloys

NASA Astrophysics Data System (ADS)

Bran, D. T.; Elefterie, C. F.; Ghiban, B.

2017-06-01

The project presents the requirements imposed for aviation components made from Titanium based alloys. A significant portion of the aircraft pylons are manufactured from Titanium alloys. Strength, weight, and reliability are the primary factors to consider in aircraft structures. These factors determine the requirements to be met by any material used to construct or repair the aircraft. Many forces and structural stresses act on an aircraft when it is flying and when it is static and this thesis describes environmental factors, conditions of external aggression, mechanical characteristics and loadings that must be satisfied simultaneously by a Ti-based alloy, compared to other classes of aviation alloys (as egg. Inconel super alloys, Aluminum alloys).For this alloy class, the requirements are regarding strength to weight ratio, reliability, corrosion resistance, thermal expansion and so on. These characteristics additionally continue to provide new opportunities for advanced manufacturing methods.

Aeronautics systems technology studies

NASA Technical Reports Server (NTRS)

Bauchspies, J. S.

1983-01-01

Data collection and analysis in the areas of air transportation, aircraft manufacturing and sales, airline operations, market projections, internal trade, and energy consumption; legislation and regulations, technology needs; surveys; decision-making; cost analyses; and technology transfer are discussed.

78 FR 76753 - Standards of Performance for Petroleum Refineries for Which Construction, Reconstruction, or...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-19

..., or Use I. National Technology Transfer and Advancement Act J. Executive Order 12898: Federal Actions... and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995... information claimed to be confidential business information (CBI) or other information whose disclosure is...

System identification methods for aircraft flight control development and validation

NASA Technical Reports Server (NTRS)

Tischler, Mark B.

1995-01-01

System-identification methods compose a mathematical model, or series of models, from measurements of inputs and outputs of dynamic systems. The extracted models allow the characterization of the response of the overall aircraft or component subsystem behavior, such as actuators and on-board signal processing algorithms. This paper discusses the use of frequency-domain system-identification methods for the development and integration of aircraft flight-control systems. The extraction and analysis of models of varying complexity from nonparametric frequency-responses to transfer-functions and high-order state-space representations is illustrated using the Comprehensive Identification from FrEquency Responses (CIFER) system-identification facility. Results are presented for test data of numerous flight and simulation programs at the Ames Research Center including rotorcraft, fixed-wing aircraft, advanced short takeoff and vertical landing (ASTOVL), vertical/short takeoff and landing (V/STOL), tiltrotor aircraft, and rotor experiments in the wind tunnel. Excellent system characterization and dynamic response prediction is achieved for this wide class of systems. Examples illustrate the role of system-identification technology in providing an integrated flow of dynamic response data around the entire life-cycle of aircraft development from initial specifications, through simulation and bench testing, and into flight-test optimization.

Biomechanically Induced and Controller Coupled Oscillations Experienced on the F-16XL Aircraft During Rolling Maneuvers

NASA Technical Reports Server (NTRS)

Smith, John W.; Montgomery, Terry

1996-01-01

During rapid rolling maneuvers, the F-16 XL aircraft exhibits a 2.5 Hz lightly damped roll oscillation, perceived and described as 'roll ratcheting.' This phenomenon is common with fly-by-wire control systems, particularly when primary control is derived through a pedestal-mounted side-arm controller. Analytical studies have been conducted to model the nature of the integrated control characteristics. The analytical results complement the flight observations. A three-degree-of-freedom linearized set of aerodynamic matrices was assembled to simulate the aircraft plant. The lateral-directional control system was modeled as a linear system. A combination of two second-order transfer functions was derived to couple the lateral acceleration feed through effect of the operator's arm and controller to the roll stick force input. From the combined systems, open-loop frequency responses and a time history were derived, describing and predicting an analogous in-flight situation. This report describes the primary control, aircraft angular rate, and position time responses of the F-16 XL-2 aircraft during subsonic and high-dynamic-pressure rolling maneuvers. The analytical description of the pilot's arm and controller can be applied to other aircraft or simulations to assess roll ratcheting susceptibility.

The insertion of human dynamics models in the flight control loops of V/STOL research aircraft. Appendix 2: The optimal control model of a pilot in V/STOL aircraft control loops

NASA Technical Reports Server (NTRS)

Zipf, Mark E.

1989-01-01

An overview is presented of research work focussed on the design and insertion of classical models of human pilot dynamics within the flight control loops of V/STOL aircraft. The pilots were designed and configured for use in integrated control system research and design. The models of human behavior that were considered are: McRuer-Krendel (a single variable transfer function model); and Optimal Control Model (a multi-variable approach based on optimal control and stochastic estimation theory). These models attempt to predict human control response characteristics when confronted with compensatory tracking and state regulation tasks. An overview, mathematical description, and discussion of predictive limitations of the pilot models is presented. Design strategies and closed loop insertion configurations are introduced and considered for various flight control scenarios. Models of aircraft dynamics (both transfer function and state space based) are developed and discussed for their use in pilot design and application. Pilot design and insertion are illustrated for various flight control objectives. Results of pilot insertion within the control loops of two V/STOL research aricraft (Sikorski Black Hawk UH-60A, McDonnell Douglas Harrier II AV-8B) are presented and compared against actual pilot flight data. Conclusions are reached on the ability of the pilot models to adequately predict human behavior when confronted with similar control objectives.

A High Frequency (HF) Inductive Power Transfer Circuit for High Temperature Applications Using SiC Schottky Diodes

NASA Technical Reports Server (NTRS)

Jordan, Jennifer L.; Ponchak, George E.; Spry, David J.; Neudeck, Philip G.

2018-01-01

Wireless sensors placed in high temperature environments, such as aircraft engines, are desirable to reduce the mass and complexity of routing wires. While communication with the sensors is straight forward, providing power wirelessly is still a challenge. This paper introduces an inductive wireless power transfer circuit incorporating SiC Schottky diodes and its operation from room temperature (25 C) to 500 C.

Personal Aircraft Point to the Future of Transportation

NASA Technical Reports Server (NTRS)

2010-01-01

NASA's Small Business Innovation Research (SBIR) and Small Business Technology Transfer (STTR) programs, as well as a number of Agency innovations, have helped Duluth, Minnesota-based Cirrus Design Corporation become one of the world's leading manufacturers of general aviation aircraft. SBIRs with Langley Research Center provided the company with cost-effective composite airframe manufacturing methods, while crashworthiness testing at the Center increased the safety of its airplanes. Other NASA-derived technologies on Cirrus SR20 and SR22 aircraft include synthetic vision systems that help pilots navigate and full-plane parachutes that have saved the lives of more than 30 Cirrus pilots and passengers to date. Today, the SR22 is the world's top-selling Federal Aviation Administration (FAA)-certified single-engine airplane.

A Low LET Radiation Spectrometer for Measuring Particle Doses in Space and Aircraft

NASA Technical Reports Server (NTRS)

Stassinopoulos, E. G.; Stauffer, C. A.; Brucker, G. J.; Dachev, T. P.; Day, John H. (Technical Monitor)

2002-01-01

This paper presents experimental data that demonstrates the feasibility of fabricating a miniature nuclear particle dosimeter for monitoring doses in aircraft and satellites. The basic instrument is a Low Linear-Energy-Transfer (LET) Radiation Spectrometer (LoLRS) that is designed to measure the energy deposited by particles with low LET values. The heart of the instrument is a Silicon-Lithium Drifted Diode (SLDD). Test results show that the LoLRS can be used to monitor the radiation threat to personnel in flights of space- and aircraft and also to generate a comprehensive data base from aviation and satellite measurements that can contribute to the formulation of more accurate environmental radiation models for dose predictions with reduced uncertainty factors.

Numerical simulation of two-dimensional heat transfer in composite bodies with application to de-icing of aircraft components. Ph.D. Thesis. Final Report

NASA Technical Reports Server (NTRS)

Chao, D. F. K.

1983-01-01

Transient, numerical simulations of the de-icing of composite aircraft components by electrothermal heating were performed for a two dimensional rectangular geometry. The implicit Crank-Nicolson formulation was used to insure stability of the finite-difference heat conduction equations and the phase change in the ice layer was simulated using the Enthalpy method. The Gauss-Seidel point iterative method was used to solve the system of difference equations. Numerical solutions illustrating de-icer performance for various composite aircraft structures and environmental conditions are presented. Comparisons are made with previous studies. The simulation can also be used to solve a variety of other heat conduction problems involving composite bodies.

Advanced risk assessment of the effects of graphite fibers on electronic and electric equipment

NASA Technical Reports Server (NTRS)

Pocinki, L.; Cornell, M.; Kaplan, L.

1980-01-01

An assessment of the risk associated with accidents involving aircraft with carbon fiber composite structural components is examined. The individual fiber segments cause electrical and electronic equipment to fail under certain operating conditions. A Monte Carlo simulation model was used to computer the risk. Aircraft accidents with fire, release of carbon fiber material, entrainment of carbon fibers in a smoke plume transport of fibers downwind, transfer of some fibers/into the the interior of buildings, failures of electrical and electronic equipment, and economic impact of failures are discussed. Risk profiles were prepared for individual airports and the Nation. The vulnerability of electrical transmission equipment to carbon fiber incursion and aircraft accident total costs is investigated.

Delay banking for air traffic management

NASA Technical Reports Server (NTRS)

Green, Steven M. (Inventor)

2007-01-01

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

Multivariable control of a forward swept wing aircraft. M.S. Thesis

NASA Technical Reports Server (NTRS)

Quinn, W. W.

1986-01-01

The impact of independent canard and flaperon control of the longitudinal axis of a generic forward swept wing aircraft is examined. The Linear Quadratic Gaussian (LQG)/Loop Transfer Recovery (LTR) method is used to design three compensators: two single-input-single-output (SISO) systems, one with angle of attack as output and canard as control, the other with pitch attitude as output and canard as control, and a two-input-two-output system with both canard and flaperon controlling both the pitch attitude and angle of attack. The performances of the three systems are compared showing the addition of flaperon control allows the aircraft to perform in the precision control modes with very little loss of command following accuracy.

Geometric and radiometric preprocessing of airborne visible/infrared imaging spectrometer (AVIRIS) data in rugged terrain for quantitative data analysis

NASA Technical Reports Server (NTRS)

Meyer, Peter; Green, Robert O.; Staenz, Karl; Itten, Klaus I.

1994-01-01

A geocoding procedure for remotely sensed data of airborne systems in rugged terrain is affected by several factors: buffeting of the aircraft by turbulence, variations in ground speed, changes in altitude, attitude variations, and surface topography. The current investigation was carried out with an Airborne Visible/Infrared Imaging Spectrometer (AVIRIS) scene of central Switzerland (Rigi) from NASA's Multi Aircraft Campaign (MAC) in Europe (1991). The parametric approach reconstructs for every pixel the observation geometry based on the flight line, aircraft attitude, and surface topography. To utilize the data for analysis of materials on the surface, the AVIRIS data are corrected to apparent reflectance using algorithms based on MODTRAN (moderate resolution transfer code).

Ramifications of Illegal U.S. Arms Exports

DTIC Science & Technology

1989-03-01

the military goods may not have known and/or cared where their wares would ultimately be delivered. 5. U.S. v. Ken Park , aka Kwan Park, January 1989 The...revealed that Ken Park , acting as the Export Manager of Universal Technology, was involved in illegal export of aircraft parts to South Korea in August...transshipment to Teheran, Iran. On January 13, 1939, Ken Park admitted illegally exporting aircraft parts purchased from HTL. This case not only shows Iran’s

Criminal Acts Against Civil Aviation. 1993

DTIC Science & Technology

1993-01-01

and the Canadian passenger. The hijacker was injured in the head , the pilot in the leg, and the passenger in the shoulder . It was later determined...er’s "accomplice" would destroy the aircraft unless the demand was met. The hijacker was carrying a shampoo bottle containing a mixture of hydrochloric...hijacker on the head with a whiskey bottle, knocking the man to the floor, and security officers took the hijacker from the aircraft. This was only the

Criminal Acts against Civil Aviation 1987

DTIC Science & Technology

1987-01-01

committea aircraft worldwide. Of the 13, four were U.S.-registered by terrorist groups but by individuals seeking political aircraft and nine were foreign...Moscow/Tallinn, USSR United Kingdom or Norway 07-06-83 Iran Air B-747 Shiraz/Tehran, Iran Iraq/ Political Statement 08-27-83 Air France B-727 Vienna...25-84 CAAC (PRC) Unknown Nanchang/Fuzhou, China Taiwan 06-26-84 Iran Air B-727 Tehran/Bushehr, Iran Baghdad, Iraq/ Political Asylum 07-05-84 Indian

Summary of the National Technology Transfer and Advancement Act

EPA Pesticide Factsheets

Provides a summary of the National Technology Transfer and Advancement Act which pomote economic, environmental, and social well-being by bringing technology and industrial innovation to the marketplace

Aircraft noise prediction

NASA Astrophysics Data System (ADS)

Filippone, Antonio

2014-07-01

This contribution addresses the state-of-the-art in the field of aircraft noise prediction, simulation and minimisation. The point of view taken in this context is that of comprehensive models that couple the various aircraft systems with the acoustic sources, the propagation and the flight trajectories. After an exhaustive review of the present predictive technologies in the relevant fields (airframe, propulsion, propagation, aircraft operations, trajectory optimisation), the paper addresses items for further research and development. Examples are shown for several airplanes, including the Airbus A319-100 (CFM engines), the Bombardier Dash8-Q400 (PW150 engines, Dowty R408 propellers) and the Boeing B737-800 (CFM engines). Predictions are done with the flight mechanics code FLIGHT. The transfer function between flight mechanics and the noise prediction is discussed in some details, along with the numerical procedures for validation and verification. Some code-to-code comparisons are shown. It is contended that the field of aircraft noise prediction has not yet reached a sufficient level of maturity. In particular, some parametric effects cannot be investigated, issues of accuracy are not currently addressed, and validation standards are still lacking.

Views on the impact of HOST

NASA Technical Reports Server (NTRS)

Esgar, J. B.; Sokolowski, Daniel E.

1989-01-01

The Hot Section Technology (HOST) Project, which was initiated by NASA Lewis Research Center in 1980 and concluded in 1987, was aimed at improving advanced aircraft engine hot section durability through better technical understanding and more accurate design analysis capability. The project was a multidisciplinary, multiorganizational, focused research effort that involved 21 organizations and 70 research and technology activities and generated approximately 250 research reports. No major hardware was developed. To evaluate whether HOST had a significant impact on the overall aircraft engine industry in the development of new engines, interviews were conducted with 41 participants in the project to obtain their views. The summarized results of these interviews are presented. Emphasis is placed on results relative to three-dimensional inelastic structural analysis, thermomechanical fatigue testing, constitutive modeling, combustor aerothermal modeling, turbine heat transfer, protective coatings, computer codes, improved engine design capability, reduced engine development costs, and the impacts on technology transfer and the industry-government partnership.

Experiments on the properties of superfluid helium in zero gravity

NASA Technical Reports Server (NTRS)

Mason, P.; Collins, D.; Petrac, D.; Yang, L.; Edeskuty, F.; Williamson, K.

1976-01-01

The paper describes a research program designed to study the behavior of superfluid liquid helium in low and zero gravity in order to determine the properties which are critically important to its use as a stored cryogen for cooling scientific instruments aboard spacecraft for periods up to several months. The experiment program consists of a series of flights of an experiment package on a free-fall trajectory both on an aircraft and on a rocket. The objectives are to study thickness of thin films of helium as a function of acceleration, heat transfer in thin films, heat transfer across copper-liquid helium interfaces, fluid dynamics of bulk helium in high and low accelerations and under various conditions of rotations, alternate methods of separation of liquid and vapor phases and of efficient venting of the vapor, and undesirable thermomechanical oscillations in the vent pipes. Preliminary results from aircraft tests are discussed.

Optimizing an Actuator Array for the Control of Multi-Frequency Noise in Aircraft Interiors

NASA Technical Reports Server (NTRS)

Palumbo, D. L.; Padula, S. L.

1997-01-01

Techniques developed for selecting an optimized actuator array for interior noise reduction at a single frequency are extended to the multi-frequency case. Transfer functions for 64 actuators were obtained at 5 frequencies from ground testing the rear section of a fully trimmed DC-9 fuselage. A single loudspeaker facing the left side of the aircraft was the primary source. A combinatorial search procedure (tabu search) was employed to find optimum actuator subsets of from 2 to 16 actuators. Noise reduction predictions derived from the transfer functions were used as a basis for evaluating actuator subsets during optimization. Results indicate that it is necessary to constrain actuator forces during optimization. Unconstrained optimizations selected actuators which require unrealistically large forces. Two methods of constraint are evaluated. It is shown that a fast, but approximate, method yields results equivalent to an accurate, but computationally expensive, method.

Collaborating with EPA through the Federal Technology Transfer Act

EPA Pesticide Factsheets

Under the Federal Technology Transfer Act (FTTA), EPA can collaborate with external parties on research projects, and share research materials. Learn more about the types of partnerships the EPA offers.

Numerical comparison of convective heat transfer augmentation devices used in cooling channels of hypersonic vehicles

NASA Astrophysics Data System (ADS)

Maldonado, Jaime J.

1994-04-01

Hypersonic vehicles are exposed to extreme thermal conditions compared to subsonic aircraft; therefore, some level of thermal management is required to protect the materials used. Normally, hypersonic vehicles experience the highest temperatures in the nozzle throat, and aircraft and propulsion system leading edges. Convective heat transfer augmentation techniques can be used in the thermal management system to increase heat transfer of the cooling channels in those areas. The techniques studied in this report are pin-fin, offset-fin, ribbed and straight roughened channel. A smooth straight channel is used as the baseline for comparing the techniques. SINDA '85, a lumped parameter finite difference thermal analyzer, is used to model the channels. Subroutines are added to model the fluid flow assuming steady one dimensional compressible flow with heat addition and friction. Correlations for convective heat transfer and friction are used in conjunction with the fluid flow analysis mentioned. As expected, the pin-fin arrangement has the highest heat transfer coefficient and the largest pressure drop. All the other devices fall in between the pin-fin and smooth straight channel. The selection of the best heat augmentation method depends on the design requirements. A good approach may be a channel using a combination of the techniques. For instance, several rows of pin-fins may be located at the region of highest heat flux, surrounded by some of the other techniques. Thus, the heat transfer coefficient is maximized at the region of highest heat flux while the pressure drop is not excessive.

Numerical comparison of convective heat transfer augmentation devices used in cooling channels of hypersonic vehicles

NASA Technical Reports Server (NTRS)

Maldonado, Jaime J.

1994-01-01

Hypersonic vehicles are exposed to extreme thermal conditions compared to subsonic aircraft; therefore, some level of thermal management is required to protect the materials used. Normally, hypersonic vehicles experience the highest temperatures in the nozzle throat, and aircraft and propulsion system leading edges. Convective heat transfer augmentation techniques can be used in the thermal management system to increase heat transfer of the cooling channels in those areas. The techniques studied in this report are pin-fin, offset-fin, ribbed and straight roughened channel. A smooth straight channel is used as the baseline for comparing the techniques. SINDA '85, a lumped parameter finite difference thermal analyzer, is used to model the channels. Subroutines are added to model the fluid flow assuming steady one dimensional compressible flow with heat addition and friction. Correlations for convective heat transfer and friction are used in conjunction with the fluid flow analysis mentioned. As expected, the pin-fin arrangement has the highest heat transfer coefficient and the largest pressure drop. All the other devices fall in between the pin-fin and smooth straight channel. The selection of the best heat augmentation method depends on the design requirements. A good approach may be a channel using a combination of the techniques. For instance, several rows of pin-fins may be located at the region of highest heat flux, surrounded by some of the other techniques. Thus, the heat transfer coefficient is maximized at the region of highest heat flux while the pressure drop is not excessive.

Federal Technology Transfer Act (FTTA)

EPA Pesticide Factsheets

EPA's Federal Technology Transfer Act (FTTA) is a mechanism with which EPA can patent its inventions and license them to companies, through which innovative technologies can enter the marketplace to improve the environment and human health.

Pathogen boosted adoptive cell transfer immunotherapy to treat solid tumors

PubMed Central

Xin, Gang; Schauder, David M.; Jing, Weiqing; Jiang, Aimin; Joshi, Nikhil S.; Johnson, Bryon; Cui, Weiguo

2017-01-01

Because of insufficient migration and antitumor function of transferred T cells, especially inside the immunosuppressive tumor microenvironment (TME), the efficacy of adoptive cell transfer (ACT) is much curtailed in treating solid tumors. To overcome these challenges, we sought to reenergize ACT (ReACT) with a pathogen-based cancer vaccine. To bridge ACT with a pathogen, we genetically engineered tumor-specific CD8 T cells in vitro with a second T-cell receptor (TCR) that recognizes a bacterial antigen. We then transferred these dual-specific T cells in combination with intratumoral bacteria injection to treat solid tumors in mice. The dual-specific CD8 T cells expanded vigorously, migrated to tumor sites, and robustly eradicated primary tumors. The mice cured from ReACT also developed immunological memory against tumor rechallenge. Mechanistically, we have found that this combined approach reverts the immunosuppressive TME and recruits CD8 T cells with an increased number and killing ability to the tumors. PMID:28069963

Space Shuttle Discovery DC Fly-Over

NASA Image and Video Library

2012-04-17

Space shuttle Discovery, mounted atop a NASA 747 Shuttle Carrier Aircraft (SCA), flies over the Washington skyline as seen from a NASA T-38 aircraft, Tuesday, April 17, 2012. Discovery, the first orbiter retired from NASA’s shuttle fleet, completed 39 missions, spent 365 days in space, orbited the Earth 5,830 times, and traveled 148,221,675 miles. NASA will transfer Discovery to the National Air and Space Museum to begin its new mission to commemorate past achievements in space and to educate and inspire future generations of explorers. Photo Credit: (NASA/Robert Markowitz)

Development of stitched/RTM primary structures for transport aircraft

NASA Technical Reports Server (NTRS)

Hawley, Arthur V.

1993-01-01

This report covers work accomplished in the Innovative Composite Aircraft Primary Structure (ICAPS) program. An account is given of the design criteria and philosophy that guides the development. Wing and fuselage components used as a baseline for development are described. The major thrust of the program is to achieve a major cost breakthrough through development of stitched dry preforms and resin transfer molding (RTM), and progress on these processes is reported. A full description is provided on the fabrication of the stitched RTM wing panels. Test data are presented.

The Automated Aircraft Rework System (AARS): A system integration approach

NASA Technical Reports Server (NTRS)

Benoit, Michael J.

1994-01-01

The Mercer Engineering Research Center (MERC), under contract to the United States Air Force (USAF) since 1989, has been actively involved in providing the Warner Robins Air Logistics Center (WR-ALC) with a robotic workcell designed to perform rework automated defastening and hole location/transfer operations on F-15 wings. This paper describes the activities required to develop and implement this workcell, known as the Automated Aircraft Rework System (AARS). AARS is scheduled to be completely installed and in operation at WR-ALC by September 1994.

Investigation of surface tension phenomena using the KC-135 aircraft

NASA Technical Reports Server (NTRS)

Alter, W. S.

1982-01-01

The microgravity environment of the KC-135 aircraft was utilized in three experiments designed to determine the following: (1) the feasibility of measuring critical wetting temperatures; (2) the effectiveness of surface tension as a means of keeping the cushioning heat transfer liquid in the furnace during ampoule translation; and (3) whether a non-wetting fluid would separate from the ampoule wall under low gravity conditions. This trio of investigations concerning surface phenomena demonstrates the effectiveness of the KC-135 as a microgravity research environment for small-scale, hand-held experiments.

Research on flight stability performance of rotor aircraft based on visual servo control method

NASA Astrophysics Data System (ADS)

Yu, Yanan; Chen, Jing

2016-11-01

control method based on visual servo feedback is proposed, which is used to improve the attitude of a quad-rotor aircraft and to enhance its flight stability. Ground target images are obtained by a visual platform fixed on aircraft. Scale invariant feature transform (SIFT) algorism is used to extract image feature information. According to the image characteristic analysis, fast motion estimation is completed and used as an input signal of PID flight control system to realize real-time status adjustment in flight process. Imaging tests and simulation results show that the method proposed acts good performance in terms of flight stability compensation and attitude adjustment. The response speed and control precision meets the requirements of actual use, which is able to reduce or even eliminate the influence of environmental disturbance. So the method proposed has certain research value to solve the problem of aircraft's anti-disturbance.

NASA personnel in a control room during the successful second flight of the X-43A aircraft

NASA Image and Video Library

2004-03-27

NASA personnel in a control room during the successful second flight of the X-43A aircraft. front row, left to right: Randy Voland, LaRC Propulsion; Craig Christy, Boeing Systems; Dave Reubush, NASA Hyper-X Deputy Program Manager; and Vince Rausch, NASA Hyper-X Program Manager. back row, left to right: Bill Talley, DCI/consultant; Pat Stoliker, DFRC Director (Acting) of Research Engineering; John Martin, LaRC G&C; and Dave Bose, AMA/Controls.

Work Domain Analysis of Australia’s Air Power System: Purpose-related Functions of Combat; Transport; and Intelligence, Surveillance, and Reconnaissance Subsystems

DTIC Science & Technology

2015-03-01

of nature (e.g., flooding, drought, cyclone, earthquake, volcanic eruption , disease epidemic) or an act of man (e.g., riots, civil unrest, war...e.g., volcanic eruption ). To militate against these potential dangers, assets contributing to People Rescue (e.g., fixed-wing aircraft, rotary-wing...operating altitude of an aircraft to avoid strong winds or volcanic ash). UNCLASSIFIED DSTO-TR-3085 UNCLASSIFIED 69  “…rescue helicopters and

On two special values of temperature factor in hypersonic flow stagnation point

NASA Astrophysics Data System (ADS)

Bilchenko, G. G.; Bilchenko, N. G.

2018-03-01

The hypersonic aircraft permeable cylindrical and spherical surfaces laminar boundary layer heat and mass transfer control mathematical model properties are investigated. The nonlinear algebraic equations systems are obtained for two special values of temperature factor in the hypersonic flow stagnation point. The mappings bijectivity between heat and mass transfer local parameters and controls is established. The computation experiments results are presented: the domains of allowed values “heat-friction” are obtained.

Damage-mitigating control of aircraft for high performance and life extension

NASA Astrophysics Data System (ADS)

Caplin, Jeffrey

1998-12-01

A methodology is proposed for the synthesis of a Damage-Mitigating Control System for a high-performance fighter aircraft. The design of such a controller involves consideration of damage to critical points of the structure, as well as the performance requirements of the aircraft. This research is interdisciplinary, and brings existing knowledge in the fields of unsteady aerodynamics, structural dynamics, fracture mechanics, and control theory together to formulate a new approach towards aircraft flight controller design. A flexible wing model is formulated using the Finite Element Method, and the important mode shapes and natural frequencies are identified. The Doublet Lattice Method is employed to develop an unsteady flow model for computation of the unsteady aerodynamic loads acting on the wing due to rigid-body maneuvers and structural deformation. These two models are subsequently incorporated into a pre-existing nonlinear rigid-body aircraft flight-dynamic model. A family of robust Damage-Mitigating Controllers is designed using the Hinfinity-optimization and mu-synthesis method. In addition to weighting the error between the ideal performance and the actual performance of the aircraft, weights are also placed on the strain amplitude at the root of each wing. The results show significant savings in fatigue life of the wings while retaining the dynamic performance of the aircraft.

78 FR 12961 - Findings of Failure To Submit a Complete State Implementation Plan for Section 110(a) Pertaining...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-02-26

... Significantly Affect Energy Supply, Distribution or Use I. National Technology Transfer and Advancement Act J... Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995 (NTTAA), Public..., install and utilize technology and systems for the purposes of collecting, validating and verifying...

76 FR 78977 - Real Estate Settlement Procedures Act (Regulation X)

Federal Register 2010, 2011, 2012, 2013, 2014

2011-12-20

...Title X of the Dodd-Frank Wall Street Reform and Consumer Protection Act (Dodd-Frank Act) transferred rulemaking authority for a number of consumer financial protection laws from seven Federal agencies to the Bureau of Consumer Financial Protection (Bureau) as of July 21, 2011. The Bureau is in the process of republishing the regulations implementing those laws with technical and conforming changes to reflect the transfer of authority and certain other changes made by the Dodd-Frank Act. In light of the transfer of the Department of Housing and Urban Development's (HUD's) rulemaking authority for the Real Estate Settlement Procedures Act (RESPA) to the Bureau, the Bureau is publishing for public comment an interim final rule establishing a new Regulation X (Real Estate Settlement Procedures Act). This interim final rule does not impose any new substantive obligations on persons subject to the existing Regulation X, previously published by HUD.

Terrorist Material Support: An Overview of 18 U.S.C. 2339A and 2339B

DTIC Science & Technology

2010-07-19

child (which also is not a violent act), is an ‘act dangerous to human life.’ And it violates ... 18 U.S.C. §2339A(a), which provides that ‘whoever...United States. Giving money to Hamas, like giving a loaded gun to a child (which also is not a violent act), is an ‘act dangerous to human life.’ And...explosive or incendiary devices, or endangerment of human life by means of weapons, on an aircraft within U.S. jurisdiction) 49 U.S.C. 46506 (homicide or

14 CFR 25.445 - Auxiliary aerodynamic surfaces.

Code of Federal Regulations, 2011 CFR

2011-01-01

... AIRCRAFT AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Structure Control Surface and System Loads..., and gusts as specified in § 25.341(a) acting at any orientation at right angles to the flight path. (b...

14 CFR 25.445 - Auxiliary aerodynamic surfaces.

Code of Federal Regulations, 2010 CFR

2010-01-01

... AIRCRAFT AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES Structure Control Surface and System Loads..., and gusts as specified in § 25.341(a) acting at any orientation at right angles to the flight path. (b...

77 FR 59021 - Sunshine Act Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2012-09-25

... ONE item is open to the public. MATTER TO BE CONSIDERED: 8439 Aircraft Accident Report--Crash During Experimental Test Flight, Gulfstream Aerospace Corporation GVI (G650), N652GD, Roswell, New Mexico, April 2...

Drone Aircraft Privacy and Transparency Act of 2013

THOMAS, 113th Congress

Sen. Markey, Edward J. [D-MA

2013-11-04

Senate - 11/04/2013 Read twice and referred to the Committee on Commerce, Science, and Transportation. (All Actions) Tracker: This bill has the status IntroducedHere are the steps for Status of Legislation:

77 FR 27097 - Sunshine Act Meeting

Federal Register 2010, 2011, 2012, 2013, 2014

2012-05-08

... Experimental Amateur-Built Aircraft. NEWS MEDIA CONTACT: Telephone: (202) 314-6100. The press and public may.... The public may view the meeting via a live or archived webcast by accessing a link under ``News...

Aircrew Discourse: Exploring Strategies of Information and Action Management

NASA Technical Reports Server (NTRS)

Irwin, Cheryl M.; Veinott, Elizabeth S.; Shafto, Michael G. (Technical Monitor)

1995-01-01

This paper explores methodology issues encountered in the analysis of flightcrew communications in aviation simulation research. Examples are provided by two recent studies which are compared on three issues: level of analysis, data definition, and interpretation of the results. The data discussed were collected in a study comparing two levels of aircraft automation. The first example is an investigation of how pilots' information transfer strategies differed as a function of automation during low and high-workload flight phases. The second study focuses on how crews managed actions in the two aircraft during a ten minute, high-workload flight segment. Results indicated that crews in the two aircraft differed in their strategies of information and action management. The differences are discussed in terms of their operational and research significance.

Incorporating data link messaging into a multi-function display to support the Small Aircraft Transportation System (SATS) and the self-separation of general aviation aircraft.

PubMed

Adams, Catherine A; Murdoch, Jennifer L; Consiglio, Maria C; Williams, Daniel M

2007-07-01

One objective of the Small Aircraft Transportation System (SATS) Project is to increase the capacity and utilization of small non-towered, non-radar equipped airports by transferring traffic management activities to an automated system and separation responsibilities to general aviation (GA) pilots. This paper describes the development of a research multi-function display (MFD) to support the interaction between pilots and an automated Airport Management Module (AMM). Preliminary results of simulation and flight tests indicate that adding the responsibility of monitoring other traffic for self-separation does not increase pilots' subjective workload levels. Pilots preferred using the enhanced MFD to execute flight procedures, reporting improved situation awareness (SA) over conventional instrument flight rules (IFR) procedures.

A Method for Determining the Rate of Heat Transfer from a Wing or Streamline Body

NASA Technical Reports Server (NTRS)

Frick, Charles W; Mccullough, George B

1945-01-01

A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude. To illustrate the method, the total rate of heat transfer from an airfoil is calculated and compared with the experimental results.

76 FR 47651 - Transfer and Redesignation of Certain Regulations Involving State Savings Associations Pursuant...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-05

...Title III of the Dodd-Frank Wall Street Reform and Consumer Protection Act of 2010 (the Dodd-Frank Act or the Act) provided that the functions, powers, and duties of the Office of Thrift Supervision (OTS) relating to State savings associations will transfer to the FDIC effective one year after July 21, 2010, the date that the Dodd-Frank Act was enacted. The Act also amended section 3 of the Federal Deposit Insurance Act (FDI Act) to designate the FDIC as the ``appropriate Federal banking agency'' for State savings associations. The FDIC is authorized to issue regulations pursuant to the FDI Act and other existing laws as the ``appropriate Federal banking agency'' (or under similar statutory terminology). As a result, pursuant to those laws, the FDIC, the newly-designated ``appropriate Federal banking agency'' for State savings associations, is authorized to issue certain regulations involving State savings associations. Consistent with the authority provided to the FDIC by the Dodd- Frank Act, the FDI Act, and other statutory authorities, the FDIC is reissuing and redesigning certain transferring OTS regulations. In republishing these rules, the FDIC is making only technical changes to existing OTS regulations (such as nomenclature or address changes). The FDIC is not republishing those OTS regulations for which other appropriate Federal banking agencies are authorized to act. In the future, the FDIC may take other actions related to the transferred rules: Incorporating them into other FDIC regulations contained in Title 12, Chapter III, amending them, or rescinding them, as appropriate.

27 CFR 25.282 - Beer lost by fire, theft, casualty, or act of God.

Code of Federal Regulations, 2013 CFR

2013-04-01

... be relieved of liability for the tax if, before transfer of title to the beer to any other person... by fire, casualty, or act of God. The tax liability on excessive losses of beer from transfer between... loss of beer before transfer of title of the beer to another person and who desires to adjust the tax...

27 CFR 25.282 - Beer lost by fire, theft, casualty, or act of God.

Code of Federal Regulations, 2014 CFR

2014-04-01

... be relieved of liability for the tax if, before transfer of title to the beer to any other person... by fire, casualty, or act of God. The tax liability on excessive losses of beer from transfer between... loss of beer before transfer of title of the beer to another person and who desires to adjust the tax...

27 CFR 25.282 - Beer lost by fire, theft, casualty, or act of God.

Code of Federal Regulations, 2012 CFR

2012-04-01

... be relieved of liability for the tax if, before transfer of title to the beer to any other person... by fire, casualty, or act of God. The tax liability on excessive losses of beer from transfer between... loss of beer before transfer of title of the beer to another person and who desires to adjust the tax...

Defining the ATC Controller Interface for Data Link Clearances

NASA Technical Reports Server (NTRS)

Rankin, James

1998-01-01

The Controller Interface (CI) is the primary method for Air Traffic Controllers to communicate with aircraft via Controller-Pilot Data Link Communications (CPDLC). The controller, wearing a microphone/headset, aurally gives instructions to aircraft as he/she would with today's voice radio systems. The CI's voice recognition system converts the instructions to digitized messages that are formatted according to the RTCA DO-219 Operational Performance Standards for ATC Two-Way Data Link Communications. The DO-219 messages are transferred via RS-232 to the ATIDS system for uplink using a Mode-S datalink. Pilot acknowledgments of controller messages are downlinked to the ATIDS system and transferred to the Cl. A computer monitor is used to convey information to the controller. Aircraft data from the ARTS database are displayed on flight strips. The flight strips are electronic versions of the strips currently used in the ATC system. Outgoing controller messages cause the respective strip to change color to indicate an unacknowledged transmission. The message text is shown on the flight strips for reference. When the pilot acknowledges the message, the strip returns to its normal color. A map of the airport can also be displayed on the monitor. In addition to voice recognition, the controller can enter messages using the monitor's touch screen or by mouse/keyboard.

The cost of family-oriented communication before air medical interfacility transport.

PubMed

Macnab, A J; Gagnon, F; George, S; Sun, C

2001-01-01

Family-oriented communication with parents by transport teams eases the stress associated with transferring children to tertiary care. This study was conducted to determine the duration of family-oriented visits and whether the visit contributed significant cost to the mission. Data collection was prospective and double-blind; questions were incorporated into another study. Subjects were infants or children requiring assisted ventilation and air transport to tertiary care. Time from completion of stabilization to departure and reasons for any delay were recorded. Cost of contact time longer than 20 minutes (total acceptable time for family visit and transfer to vehicle) was calculated at paramedic overtime at $0.82/minute and aircraft wait time at $200/hour if incurred. Forty-six patients were enrolled. In 16 cases (35%), time between completing stabilization and hospital departure exceeded 20 minutes, with "family visit" listed as the explanation. Nine of these visits incurred overtime, and two incurred aircraft wait costs. Total costs for providing communication visits more than 10 minutes long were $607 or approximately $13 per patient. The costs for visit time longer than 10 minutes are small compared with the documented benefits of family-oriented communication. However, transport personnel must be mindful of the potential to incur additional cost through overtime, aircraft wait time, or pilot replacement.

Stress training improves performance during a stressful flight.

PubMed

McClernon, Christopher K; McCauley, Michael E; O'Connor, Paul E; Warm, Joel S

2011-06-01

This study investigated whether stress training introduced during the acquisition of simulator-based flight skills enhances pilot performance during subsequent stressful flight operations in an actual aircraft. Despite knowledge that preconditions to aircraft accidents can be strongly influenced by pilot stress, little is known about the effectiveness of stress training and how it transfers to operational flight settings. For this study, 30 participants with no flying experience were assigned at random to a stress-trained treatment group or a control group. Stress training consisted of systematic pairing of skill acquisition in a flight simulator with stress coping mechanisms in the presence of a cold pressor. Control participants received identical flight skill acquisition training but without stress training. Participants then performed a stressful flying task in a Piper Archer aircraft. Stress-trained research participants flew the aircraft more smoothly, as recorded by aircraft telemetry data, and generally better, as recorded by flight instructor evaluations, than did control participants. Introducing stress coping mechanisms during flight training improved performance in a stressful flying task. The results of this study indicate that stress training during the acquisition of flight skills may serve to enhance pilot performance in stressful operational flight and, therefore, might mitigate the contribution of pilot stress to aircraft mishaps.

Stochastic Methods for Aircraft Design

NASA Technical Reports Server (NTRS)

Pelz, Richard B.; Ogot, Madara

1998-01-01

The global stochastic optimization method, simulated annealing (SA), was adapted and applied to various problems in aircraft design. The research was aimed at overcoming the problem of finding an optimal design in a space with multiple minima and roughness ubiquitous to numerically generated nonlinear objective functions. SA was modified to reduce the number of objective function evaluations for an optimal design, historically the main criticism of stochastic methods. SA was applied to many CFD/MDO problems including: low sonic-boom bodies, minimum drag on supersonic fore-bodies, minimum drag on supersonic aeroelastic fore-bodies, minimum drag on HSCT aeroelastic wings, FLOPS preliminary design code, another preliminary aircraft design study with vortex lattice aerodynamics, HSR complete aircraft aerodynamics. In every case, SA provided a simple, robust and reliable optimization method which found optimal designs in order 100 objective function evaluations. Perhaps most importantly, from this academic/industrial project, technology has been successfully transferred; this method is the method of choice for optimization problems at Northrop Grumman.

Solar Radiation Measurements Onboard the Research Aircraft HALO

NASA Astrophysics Data System (ADS)

Lohse, I.; Bohn, B.; Werner, F.; Ehrlich, A.; Wendisch, M.

2014-12-01

Airborne measurements of the separated upward and downward components of solar spectral actinic flux densities for the determination of photolysis frequencies and of upward nadir spectral radiance were performed with the HALO Solar Radiation (HALO-SR) instrument package onboard the High Altitude and Long Range Research Aircraft (HALO). The instrumentation of HALO-SR is characterized and first measurement data from the Next-generation Aircraft Remote-Sensing for Validation Studies (NARVAL) campaigns in 2013 and 2014 are presented. The measured data are analyzed in the context of the retrieved microphysical and optical properties of clouds which were observed underneath the aircraft. Detailed angular sensitivities of the two optical actinic flux receivers were determined in the laboratory. The effects of deviations from the ideal response are investigated using radiative transfer calculations of atmospheric radiance distributions under various atmospheric conditions and different ground albedos. Corresponding correction factors are derived. Example photolysis frequencies are presented, which were sampled in the free troposphere and lower stratosphere over the Atlantic Ocean during the 2013/14 HALO NARVAL campaigns. Dependencies of photolysis frequencies on cloud cover, flight altitude and wavelength range of the photolysis process are investigated. Calculated actinic flux densities in the presence of clouds benefit from the measured spectral radiances. Retrieved cloud optical thicknesses and effective droplet radii are used as model input for the radiative transfer calculations. By comparison with the concurrent measurements of actinic flux densities the retrieval approach is validated. Acknowledgements: Funding by the Deutsche Forschungsgemeinschaft within the priority program HALO (BO 1580/4-1, WE 1900/21-1) is gratefully acknowledged.

Portable air pollution control equipment for the control of toxic particulate emissions

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

Chaurushia, A.; Odabashian, S.; Busch, E.

1997-12-31

Chromium VI (Cr VI) has been identified by the environmental regulatory agencies as a potent carcinogen among eleven heavy metals. A threshold level of 0.0001 lb/year for Cr VI emissions has been established by the California Air Resources Board for reporting under Assembly Bill 2588. A need for an innovative control technology to reduce fugitive emissions of Cr VI was identified during the Air Toxic Emissions Reduction Program at Northrop Grumman Military Aircraft Systems Division (NGMASD). NGMASD operates an aircraft assembly facility in El Segundo, CA. Nearly all of the aircraft components are coated with a protective coating (primer) priormore » to assembly. The primer has Cr VI as a component for its excellent corrosion resistance property. The complex assembly process requires fasteners which also need primer coating. Therefore, NGMASD utilizes High Volume Low Pressure (HVLP) guns for the touch-up spray coating operations. During the touch-up spray coating operations, Cr VI particles are atomized and transferred to the aircraft surface. The South Coast Air Quality Management District (SCAQMD) has determined that the HVLP gun transfers 65% of the paint particles onto the substrate and the remaining 35% are emitted as an overspray if air pollution controls are not applied. NGMASD has developed the Portable Air Pollution Control Equipment (PAPCE) to capture and control the overspray in order to reduce fugitive Cr VI emissions from the touch-up spray coating operations. A source test was performed per SCAQMD guidelines and the final report has been approved by the SCAQMD.« less

Hydrogen embrittlement of structural alloys. A technology survey

NASA Technical Reports Server (NTRS)

Carpenter, J. L., Jr.; Stuhrke, W. F.

1976-01-01

Technical abstracts for about 90 significant documents relating to hydrogen embrittlement of structural metals and alloys are reviewed. Particular note was taken of documents regarding hydrogen effects in rocket propulsion, aircraft propulsion and hydrogen energy systems, including storage and transfer systems.

Survey of aircraft electrical power systems

NASA Technical Reports Server (NTRS)

Lee, C. H.; Brandner, J. J.

1972-01-01

Areas investigated include: (1) load analysis; (2) power distribution, conversion techniques and generation; (3) design criteria and performance capabilities of hydraulic and pneumatic systems; (4) system control and protection methods; (5) component and heat transfer systems cooling; and (6) electrical system reliability.

Some health effects of aircraft noise with special reference to shift work.

PubMed

Rizk, Sanaa A M; Sharaf, Nevin E; Mahdy-Abdallah, Heba; ElGelil, Khalid S Abd

2016-06-01

Aircraft noise is an environmental stressor. A positive relationship exists between noise and high blood pressure. Shift work is an additional hazardous working condition with negative effect on the behavior attitude of workers. This study aimed at investigating some health hazards for shift work on workers at Cairo International Airport (CIA), Egypt, as a strategic work place, with more than one stressor. Assessment of noise effects were carried out in four working sites at the airport besides control sites. The average noise level in the exposure sites was 106.5 dB compared with 54 dB at the control sites. The study comprised a group of 200 male workers exposed to aircraft noise and 110 male workers not exposed to noise as control group. All workers had full general medical examination after filling specially formulated questionnaire. Hearing impairment, raised blood pressure, headaches, disturbed sleep, and symptoms of anxiety were more prominent among the exposed workers than the control. Symptoms of upper respiratory tract were reported among night shifters of both groups with high tendency for smoking. Thus, night-shift workers at CIA work under more than one stressor. Hypertension and smoking might act as intermediate factors on the causal pathway of complaints, making aircraft noise and night shift acting as two synergistic stressors. Airport workers are in need for aggressive hearing conservation programs. Organization of the working hours schedule is mandatory to avoid excessive noise exposure. © The Author(s) 2014.

49 CFR 1522.105 - Adoption and implementation of the security program.

Code of Federal Regulations, 2010 CFR

2010-10-01

..., against acts of criminal violence and air piracy, and against the introduction into aircraft of any... it proposes for the amendment to become effective, unless the designated official allows a shorter...

The Air Force Manufacturing Technology (MANTECH): Technology transfer methodology as exemplified by the radar transmit/receive module program

NASA Technical Reports Server (NTRS)

Houpt, Tracy; Ridgely, Margaret

1991-01-01

The Air Force Manufacturing Technology program is involved with the improvement of radar transmit/receive modules for use in active phased array radars for advanced fighter aircraft. Improvements in all areas of manufacture and test of these modules resulting in order of magnitude improvements in the cost of and the rate of production are addressed, as well as the ongoing transfer of this technology to the Navy.

Analysis of the Hydrodynamics and Heat Transfer Aspects of Microgravity Two-Phase Flows

NASA Technical Reports Server (NTRS)

Rezkallah, Kamiel S.

1996-01-01

Experimental results for void fractions, flow regimes, and heat transfer rates in two-phase, liquid-gas flows are summarized in this paper. The data was collected on-board NASA's KC-135 reduced gravity aircraft in a 9.525 mm circular tube (i.d.), uniformly heated at the outer surface. Water and air flows were examined as well as three glycerol/water solutions and air. Results are reported for the water-air data.

Static aeroelastic analysis of wings using Euler/Navier-Stokes equations coupled with improved wing-box finite element structures

NASA Technical Reports Server (NTRS)

Guruswamy, Guru P.; MacMurdy, Dale E.; Kapania, Rakesh K.

1994-01-01

Strong interactions between flow about an aircraft wing and the wing structure can result in aeroelastic phenomena which significantly impact aircraft performance. Time-accurate methods for solving the unsteady Navier-Stokes equations have matured to the point where reliable results can be obtained with reasonable computational costs for complex non-linear flows with shock waves, vortices and separations. The ability to combine such a flow solver with a general finite element structural model is key to an aeroelastic analysis in these flows. Earlier work involved time-accurate integration of modal structural models based on plate elements. A finite element model was developed to handle three-dimensional wing boxes, and incorporated into the flow solver without the need for modal analysis. Static condensation is performed on the structural model to reduce the structural degrees of freedom for the aeroelastic analysis. Direct incorporation of the finite element wing-box structural model with the flow solver requires finding adequate methods for transferring aerodynamic pressures to the structural grid and returning deflections to the aerodynamic grid. Several schemes were explored for handling the grid-to-grid transfer of information. The complex, built-up nature of the wing-box complicated this transfer. Aeroelastic calculations for a sample wing in transonic flow comparing various simple transfer schemes are presented and discussed.

Estimating short-period dynamics using an extended Kalman filter

NASA Technical Reports Server (NTRS)

Bauer, Jeffrey E.; Andrisani, Dominick

1990-01-01

An extended Kalman filter (EKF) is used to estimate the parameters of a low-order model from aircraft transient response data. The low-order model is a state space model derived from the short-period approximation of the longitudinal aircraft dynamics. The model corresponds to the pitch rate to stick force transfer function currently used in flying qualities analysis. Because of the model chosen, handling qualities information is also obtained. The parameters are estimated from flight data as well as from a six-degree-of-freedom, nonlinear simulation of the aircraft. These two estimates are then compared and the discrepancies noted. The low-order model is able to satisfactorily match both flight data and simulation data from a high-order computer simulation. The parameters obtained from the EKF analysis of flight data are compared to those obtained using frequency response analysis of the flight data. Time delays and damping ratios are compared and are in agreement. This technique demonstrates the potential to determine, in near real time, the extent of differences between computer models and the actual aircraft. Precise knowledge of these differences can help to determine the flying qualities of a test aircraft and lead to more efficient envelope expansion.

Aircraft Lightning Electromagnetic Environment Measurement

NASA Technical Reports Server (NTRS)

Ely, Jay J.; Nguyen, Truong X.; Szatkowski, George N.

2011-01-01

This paper outlines a NASA project plan for demonstrating a prototype lightning strike measurement system that is suitable for installation onto research aircraft that already operate in thunderstorms. This work builds upon past data from the NASA F106, FAA CV-580, and Transall C-180 flight projects, SAE ARP5412, and the European ILDAS Program. The primary focus is to capture airframe current waveforms during attachment, but may also consider pre and post-attachment current, electric field, and radiated field phenomena. New sensor technologies are being developed for this system, including a fiber-optic Faraday polarization sensor that measures lightning current waveforms from DC to over several Megahertz, and has dynamic range covering hundreds-of-volts to tens-of-thousands-of-volts. A study of the electromagnetic emission spectrum of lightning (including radio wave, microwave, optical, X-Rays and Gamma-Rays), and a compilation of aircraft transfer-function data (including composite aircraft) are included, to aid in the development of other new lightning environment sensors, their placement on-board research aircraft, and triggering of the onboard instrumentation system. The instrumentation system will leverage recent advances in high-speed, high dynamic range, deep memory data acquisition equipment, and fiber-optic interconnect.

Light Absorption of Stratospheric Aerosols: Long-Term Trend and Contribution by Aircraft

NASA Technical Reports Server (NTRS)

Pueschel , R. F.; Gore, Waren J. Y. (Technical Monitor)

1997-01-01

Measurements of aerosol light-absorption coefficients are useful for studies of radiative transfer and heating rates. Ogren appears to have published the first light- absorption coefficients in the stratosphere in 1981, followed by Clarke in 1983 and Pueschel in 1992. Because most stratospheric soot appears to be due to aircraft operations, application of an aircraft soot aerosol emission index to projected fuel consumption suggests a threefold increase of soot loading and light absorption by 2025. Together, those four data sets indicate an increase in mid-visible light extinction at a rate of 6 % per year. This trend is similar to the increase per year of sulfuric acid aerosol and of commercial fleet size. The proportionality between stepped-up aircraft operations above the tropopause and increases in stratospheric soot and sulfuric acid aerosol implicate aircraft as a source of stratospheric pollution. Because the strongly light-absorbing soot and the predominantly light-scattering sulfuric acid aerosol increase at similar rates, however, the mid-visible stratospheric aerosol single scatter albedo is expected to remain constant and not approach a critical value of 0.98 at which stratospheric cooling could change to warming.

An Overview of New Technologies Driving Innovation in the Airborne Science Community

NASA Technical Reports Server (NTRS)

Fladeland, Matthew M.

2017-01-01

Following a more than a century of scientific aircraft and ballooning there is a sense that a renaissance of sorts is at hand in the aviation industry. The advent of incredibly miniaturized autopilots, inertial navigation systems, GPS antennae, and payloads has sparked a revolution in manned and unmanned aircraft. Improved SATCOM and onboard computing has enabled realtime data processing and improved transfer of data on and off the aircraft, making flight planning and data collection more efficient and effective. Electric propulsion systems are scaling up to larger and larger vehicles as evidenced by the NASA GL-10, which is leading to a new X-plane and is leading to renewed interest in personal air vehicles. There is also significant private and government investments in the development of High Altitude, Long Endurance (HALE) aircraft. This presentation will explore how such developments are likely to improve our ability to observe earth systems processes from aircraft by providing an overview of current NASA Airborne Science capabilities, followed by a brief discussion of new technologies being applied to Airborne Science missions, and then conclude with an overview of new capabilities on the horizon that are likely to be of interest to the Earth Science community.

A Overview of New Technologies Driving Innovation in the Airborne Science Community

NASA Technical Reports Server (NTRS)

Fladeland, Matthew M.

2017-01-01

Following a more than a century of scientific aircraft and ballooning there is a sense that a renaissance of sorts is at hand in the aviation industry. The advent of incredibly miniaturized autopilots, inertial navigation systems, GPS antennae, and payloads has sparked a revolution in manned and unmanned aircraft. Improved SATCOM and onboard computing has enabled realtime data processing and improved transfer of data on and off the aircraft, making flight planning and data collection more efficient and effective. Electric propulsion systems are scaling up to larger and larger vehicles as evidenced by the NASA GL-10, which is leading to a new X-plane and is leading to renewed interest in personal air vehicles. There is also significant private and government investments in the development of High Altitude, Long Endurance (HALE) aircraft. This presentation will explore how such developments are likely to improve our ability to observe earth systems processes from aircraft by providing an overview of current NASA Airborne Science capabilities, followed by a brief discussion of new technologies being applied to Airborne Science missions, and then conclude with an overview of new capabilities on the horizon that are likely to be of interest to the Earth Science community.

Low cost training aids and devices

NASA Technical Reports Server (NTRS)

Lawver, J.; Lee, A.

1984-01-01

The need for advanced flight simulators for two engine aircraft is discussed. Cost effectiveness is a major requirement. Other training aids available for increased effectiveness are recommended. Training aids include: (1) audio-visual slides; (2) information transfer; (3) programmed instruction; and (4) interactive training systems.

Low temperature fuel behavior studies

NASA Technical Reports Server (NTRS)

Stockemer, F. J.

1980-01-01

Aircraft fuels at low temperatures near the freezing point. The principal objective was an improved understanding of the flowability and pumpability of the fuels in a facility that simulated the heat transfer and temperature profiles encountered during flight in the long range commercial wing tanks.

Desire and the female analyst.

PubMed

Schaverien, J

1996-04-01

The literature on erotic transference and countertransference between female analyst and male patient is reviewed and discussed. It is known that female analysts are less likely than their male colleagues to act out sexually with their patients. It has been claimed that a) male patients do not experience sustained erotic transferences, and b) female analysts do not experience erotic countertransferences with female or male patients. These views are challenged and it is argued that, if there is less sexual acting out by female analysts, it is not because of an absence of eros in the therapeutic relationship. The literature review covers material drawn from psychoanalysis, feminist psychotherapy, Jungian analysis, as well as some sociological and cultural sources. It is organized under the following headings: the gender of the analyst, sexual acting out, erotic transference, maternal and paternal transference, gender and power, countertransference, incest taboo--mothers and sons and sexual themes in the transference.

Aerocrane: A hybrid LTA aircraft for aerial crane applications

NASA Technical Reports Server (NTRS)

Perkins, R. G., Jr.; Doolittle, D. B.

1975-01-01

The Aerocrane, a hybrid aircraft, combines rotor lift with buoyant lift to offer VTOL load capability greatly in excess of helicopter technology while eliminating the airship problem of ballast transfer. In addition, the Aerocrane concept sharply reduces the mooring problem of airships and provides 360 deg vectorable thrust to supply a relatively large force component for control of gust loads. Designed for use in short range, ultra heavy lift missions, the Aerocrane operates in a performance envelope unsuitable for either helicopters or airships. Basic design considerations and potential problem areas of the concept are addressed.

Future Data Communication Architectures for Safety Critical Aircraft Cabin Systems

NASA Astrophysics Data System (ADS)

Berkhahn, Sven-Olaf

2012-05-01

The cabin of modern aircraft is subject to increasing demands for fast reconfiguration and hence flexibility. These demands require studies for new network architectures and technologies of the electronic cabin systems, which consider also weight and cost reductions as well as safety constraints. Two major approaches are in consideration to reduce the complex and heavy wiring harness: the usage of a so called hybrid data bus technology, which enables the common usage of the same data bus for several electronic cabin systems with different safety and security requirements and the application of wireless data transfer technologies for electronic cabin systems.

Airborne interferometer for atmospheric emission and solar absorption.

PubMed

Keith, D W; Dykema, J A; Hu, H; Lapson, L; Anderson, J G

2001-10-20

The interferometer for emission and solar absorption (INTESA) is an infrared spectrometer designed to study radiative transfer in the troposphere and lower stratosphere from a NASA ER-2 aircraft. The Fourier-transform spectrometer (FTS) operates from 0.7 to 50 mum with a resolution of 0.7 cm(-1). The FTS observes atmospheric thermal emission from multiple angles above and below the aircraft. A heliostat permits measurement of solar absorption spectra. INTESA's calibration system includes three blackbodies to permit in-flight assessment of radiometric error. Results suggest that the in-flight radiometric accuracy is ~0.5 K in the mid-infrared.

22 CFR 120.27 - U.S. criminal statutes.

Code of Federal Regulations, 2010 CFR

2010-04-01

... (relating to espionage involving defense or classified information) or § 2339A of such title (relating to... Destructive Weapons Act of 2004, relating to missile systems designed to destroy aircraft (18 U.S.C. 2332g...

Securing Aircraft Cockpits Against Lasers Act of 2011

THOMAS, 112th Congress

Rep. Lungren, Daniel E. [R-CA-3

2011-01-20

Senate - 03/01/2011 Received in the Senate and Read twice and referred to the Committee on the Judiciary. (All Actions) Tracker: This bill has the status Passed HouseHere are the steps for Status of Legislation:

Securing Aircraft Cockpits Against Lasers Act of 2010

THOMAS, 111th Congress

Rep. Lungren, Daniel E. [R-CA-3

2010-07-21

Senate - 07/28/2010 Received in the Senate and Read twice and referred to the Committee on the Judiciary. (All Actions) Tracker: This bill has the status Passed HouseHere are the steps for Status of Legislation:

Full-Scale Turbofan-Engine Turbine-Transfer Function Determination Using Three Internal Sensors

NASA Technical Reports Server (NTRS)

Hultgren, Lennart S.

2011-01-01

Existing NASA/Honeywell EVNERT full-scale static engine test data is analyzed by using source-separation techniques in order to determine the turbine transfer of the currently sub-dominant combustor noise. The results are used to assess the combustor-noise prediction capability of the Aircraft Noise Prediction Program (ANOPP). Time-series data from three sensors internal to the Honeywell TECH977 research engine is used in the analysis. The true combustor-noise turbine-transfer function is educed by utilizing a new three-signal approach. The resulting narrowband gain factors are compared with the corresponding constant values obtained from two empirical acoustic-turbine-loss formulas. It is found that a simplified Pratt & Whitney formula agrees better with the experimental results for frequencies of practical importance. The 130 deg downstream-direction far-field 1/3-octave sound-pressure levels (SPL) results of Hultgren & Miles are reexamined using a post-correction of their ANOPP predictions for both the total noise signature and the combustion-noise component. It is found that replacing the standard ANOPP turbine-attenuation function for combustion noise with the simplified Pratt & Whitney formula clearly improves the predictions. It is recommended that the GECOR combustion-noise module in ANOPP be updated to allow for a user-selectable switch between the current transmission-loss model and the simplified Pratt & Whitney formula. The NASA Fundamental Aeronautics Program has the principal objective of overcoming today's national challenges in air transportation. The Subsonic Fixed Wing Project's Reduce-Perceived-Noise Technical Challenge aims to develop concepts and technologies to dramatically reduce the perceived aircraft noise outside of airport boundaries. The reduction of aircraft noise is critical to enabling the anticipated large increase in future air traffic.

Trace gas retrieval for limb DOAS under changing atmospheric conditions: The X-gas scaling method vs optimal estimation

NASA Astrophysics Data System (ADS)

Hueneke, Tilman; Grossmann, Katja; Knecht, Matthias; Raecke, Rasmus; Stutz, Jochen; Werner, Bodo; Pfeilsticker, Klaus

2016-04-01

Changing atmospheric conditions during DOAS measurements from fast moving aircraft platforms pose a challenge for trace gas retrievals. Traditional inversion techniques to retrieve trace gas concentrations from limb scattered UV/vis spectroscopy, like optimal estimation, require a-priori information on Mie extinction (e.g., aerosol concentration and cloud cover) and albedo, which determine the atmospheric radiative transfer. In contrast to satellite applications, cloud filters can not be applied because they would strongly reduce the usable amount of expensively gathered measurement data. In contrast to ground-based MAX-DOAS applications, an aerosol retrieval based on O4 is not able to constrain the radiative transfer in air-borne applications due to the rapidly decreasing amount of O4 with altitude. Furthermore, the assumption of a constant cloud cover is not valid for fast moving aircrafts, thus requiring 2D or even 3D treatment of the radiative transfer. Therefore, traditional techniques are not applicable for most of the data gathered by fast moving aircraft platforms. In order to circumvent these limitations, we have been developing the so-called X-gas scaling method. By utilising a proxy gas X (e.g. O3, O4, …), whose concentration is either a priori known or simultaneously in-situ measured as well as remotely measured, an effective absorption length for the target gas is inferred. In this presentation, we discuss the strengths and weaknesses of the novel approach along with some sample cases. A particular strength of the X-gas scaling method is its insensitivity towards the aerosol abundance and cloud cover as well as wavelength dependent effects, whereas its sensitivity towards the profiles of both gases requires a priori information on their shapes.

75 FR 52671 - YouthBuild Program

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-27

... required by green building and weatherization industries but are not yet standardized. A full list of the...Build Program AGENCY: Employment and Training Administration, Labor. ACTION: Notice of proposed...Build Transfer Act of 2006 (Transfer Act), which establishes the YouthBuild program in the Department...

Identifying and Mitigating the Impact of the Budget Control Act on High Risk Sectors and Tiers of the Defense Industrial Base: Assessment Approach to Industrial Base Risks

DTIC Science & Technology

2016-04-30

Ü~åÖÉ= - 351 - products, similar to those found in a bill of material. Figure 3 provides an example of the relationship between sectors , sub- sectors ...defense aircraft. Defense aircraft are divided in three main sub- sectors : fixed-wing, rotary wing, and unmanned systems. The fixed-wing sub- sector ...Risk Sectors and Tiers of the Defense Industrial Base: Assessment Approach to Industrial Base Risks Lirio Avilés, Engineer, MIBP, OUSD(AT&L) Sally

Automated fiber placement: Evolution and current demonstrations

NASA Technical Reports Server (NTRS)

Grant, Carroll G.; Benson, Vernon M.

1993-01-01

The automated fiber placement process has been in development at Hercules since 1980. Fiber placement is being developed specifically for aircraft and other high performance structural applications. Several major milestones have been achieved during process development. These milestones are discussed in this paper. The automated fiber placement process is currently being demonstrated on the NASA ACT program. All demonstration projects to date have focused on fiber placement of transport aircraft fuselage structures. Hercules has worked closely with Boeing and Douglas on these demonstration projects. This paper gives a description of demonstration projects and results achieved.

Relationship between nighttime vital sign assessments and acute care transfers in the rehabilitation inpatient.

PubMed

Pellicane, Anthony J

2014-01-01

To investigate the role of nighttime vital sign assessment in predicting acute care transfers (ACT) from inpatient rehabilitation. Retrospective chart review. Fifty patients unexpectedly discharged to acute care underwent chart review to determine details of each ACT. Seven of 50 ACT possessed new vital sign abnormalities at the 11 pm vital sign assessment the night before ACT. None of these seven underwent ACT during the night shift the abnormalities were detected. Two of 50 ACT were transferred between 11 pm and 6:59 am; both demonstrating normal vital sign at the 11 pm assessment. During study period, an estimated 5,607 11 pm vital sign assessments were performed. Nighttime vital sign assessments do not seem to be a good screening tool for clinical instability in the rehabilitation hospital. Eliminating sleep disturbance is important to the rehabilitation inpatient as inadequate sleep hinders physical performance. Tailoring vital sign monitoring to fit patents' clinical presentation may benefit this population. © 2014 Association of Rehabilitation Nurses.

Absorption of Solar Radiation by the Cloudy Atmosphere Interpretations of Collocated Aircraft Measurements

NASA Technical Reports Server (NTRS)

Valero, Francisco P. J.; Cess, Robert D.; Zhang, Minghua; Pope, Shelly K.; Bucholtz, Anthony; Bush, Brett; Vitko, John, Jr.

1997-01-01

As part of the Atmospheric Radiation Measurement (ARM) Enhanced Shortwave Experiment (ARESE), we have obtained and analyzed measurements made from collocated aircraft of the absorption of solar radiation within the atmospheric column between the two aircraft. The measurements were taken during October 1995 at the ARM site in Oklahoma. Relative to a theoretical radiative transfer model, we find no evidence for excess solar absorption in the clear atmosphere and significant evidence for its existence in the cloudy atmosphere. This excess cloud solar absorption appears to occur in both visible (0.224-0.68 microns) and near-infrared (0.68-3.30 microns) spectral regions, although not at 0.5 microns for the visible contribution, and it is shown to be true absorption rather than an artifact of sampling errors caused by measuring three-dimensional clouds.

Perspective on the span-distributed-load concept for application to large cargo aircraft design

NASA Technical Reports Server (NTRS)

Whitehead, A. H., Jr.

1975-01-01

Results of a simplified analysis of the span-distributed-load concept (in which payload is placed within the wing structure) are presented. It is shown that a design based on these principles has a high potential for application to future large air cargo transport. Significant improvements are foreseen in increased payload fraction and productivity and in reduced fuel consumption and operating costs. A review of the efforts in the 1940's to develop all-wing aircraft shows the potential of transferring those early technological developments to current design of distributed-load aircraft. Current market analyses are projected to 1990 to show the future commercial demand for large capacity freighters. Several configuration designs which would serve different market requirements for these large freighters are discussed as are some of the pacing-technology requirements.

Test and analysis results for composite transport fuselage and wing structures

NASA Technical Reports Server (NTRS)

Deaton, Jerry W.; Kullerd, Susan M.; Madan, Ram C.; Chen, Victor L.

1992-01-01

Automated tow placement (ATP) and stitching of dry textile composite preforms followed by resin transfer molding (RTM) are being investigated by researchers at NASA LaRC and Douglas Aircraft Company as cost-effective manufacturing processes for obtaining damage tolerant fuselage and wing structures for transport aircraft. The Douglas work is being performed under a NASA contract entitled 'Innovative Composites Aircraft Primary Structures (ICAPS)'. Data are presented in this paper to assess the damage tolerance of ATP and RTM fuselage elements with stitched-on stiffeners from compression tests of impacted three-J-stiffened panels and from stiffener pull-off tests. Data are also presented to assess the damage tolerance of RTM wing elements which had stitched skin and stiffeners from impacted single stiffener and three blade-stiffened compression tests and stiffener pull-off tests.

Associative charge transfer reactions. Temperature effects and mechanism of the gas-phase polymerization of propene initiated by a benzene radical cation.

PubMed

Ibrahim, Yehia; Meot-Ner Mautner, Michael; El-Shall, M Samy

2006-07-13

In associative charge transfer (ACT) reactions, a core ion activates ligand molecules by partial charge transfer. The activated ligand polymerizes, and the product oligomer takes up the full charge from the core ion. In the present system, benzene(+*) (Bz(+*)) reacts with two propene (Pr) molecules to form a covalently bonded ion, C(6)H(6)(+*) + 2 C(3)H(6) --> C(6)H(12)(+*) + C(6)H(6). The ACT reaction is activated by a partial charge transfer from Bz(+*) to Pr in the complex, and driven to completion by the formation of a covalent bond in the polymerized product. An alternative channel forms a stable association product (Bz.Pr)(+*), with an ACT/association product ratio of 60:40% that is independent of pressure and temperature. In contrast to the Bz(+*)/propene system, ACT polymerization is not observed in the Bz(+*)/ethylene (Et) system since charge transfer in the Bz(+*)(Et) complex is inefficient to activate the reaction. The roles of charge transfer in these complexes are verified by ab initio calculations. The overall reaction of Bz(+*) with Pr follows second-order kinetics with a rate constant of k (304 K) = 2.1 x 10(-12) cm(3) s(-1) and a negative temperature coefficient of k = aT(-5.9) (or an activation energy of -3 kcal/mol). The kinetic behavior is similar to sterically hindered reactions and suggests a [Bz(+*) (Pr)]* activated complex that proceeds to products through a low-entropy transition state. The temperature dependence shows that ACT reactions can reach a unit collision efficiency below 100 K, suggesting that ACT can initiate polymerization in cold astrochemical environments.

Investigation of Nucleate Boiling Mechanisms Under Microgravity Conditions

NASA Technical Reports Server (NTRS)

Dhir, V. K.; Qiu, D. M.; Ramanujapu, N.; Hasan, M. M.

1999-01-01

The present work is aimed at the experimental studies and numerical modeling of the bubble growth mechanisms of a single bubble attached to a heating surface and of a bubble sliding along an inclined heated plate. Single artificial cavity of 10 microns in diameter was made on the polished Silicon wafer which was electrically heated at the back side in order to control the surface nucleation superheat. Experiments with a sliding bubble were conducted at different inclination angles of the downward facing heated surface for the purpose of studying the effect of magnitude of components of gravity acting parallel to and normal to the heat transfer surface. Information on the bubble shape and size, the bubble induced liquid velocities as well as the surface temperature were obtained using the high speed imaging and hydrogen bubble techniques. Analytical/numerical models were developed to describe the heat transfer through the micro-macro layer underneath and around a bubble formed at a nucleation site. In the micro layer model the capillary and disjoining pressures were included. Evolution of the bubble-liquid interface along with induced liquid motion was modeled. As a follow-up to the studies at normal gravity, experiments are being conducted in the KC-135 aircraft to understand the bubble growth/detachment under low gravity conditions. Experiments have been defined to be performed under long duration of microgravity conditions in the space shuttle. The experiment in the space shuttle will provide bubble growth and detachment data at microgravity and will lead to validation of the nucleate boiling heat transfer model developed from the preceding studies conducted at normal and low gravity (KC-135) conditions.

Report for neutral buoyancy simulations of transfer orbit stage contingency extravehicular activities

NASA Technical Reports Server (NTRS)

Sexton, J. D.

1992-01-01

The transfer orbit stage (TOS) will propel the advanced communications technology satellite (ACTS) from the Space Shuttle to an Earth geosynchronous transfer orbit. Two neutral buoyancy test series were conducted at MSFC to validate the extravehicular activities (EVA) contingency operations for the ACTS/TOS/mission. The results of the neutral buoyancy tests are delineated and a brief history of the TOS EVA program is given.

The tropical experiment of the Stratosphere-Troposphere Exchange Project (STEP) - Science objectives, operations, and summary findings

NASA Technical Reports Server (NTRS)

Russell, P. B.; Pfister, L.; Selkirk, H. B.

1993-01-01

An overview is presented of the tropical component of STEP. The STEP cooperative experiments are described and summaries are presented of the STEP tropical ER-2 aircraft flights. STEP tropical results on dehydration and transfer and the mechanisms of upward transfer are summarized. Illustrations show flight paths for each sortie on satellite images and on 100 hPa synoptic flow charts, as well as the timing of flights with respect to overall cloudiness in the Australian region.

Full-Scale Turbofan-Engine Turbine-Transfer Function Determination Using Three Internal Sensors

NASA Technical Reports Server (NTRS)

Hultgren, Lennart S.

2012-01-01

Noise-source separation techniques, using three engine-internal sensors, are applied to existing static-engine test data to determine the turbine transfer function for the currently subdominant combustion noise. The results are used to assess the combustion-noise prediction capability of the Aircraft Noise Prediction Program (ANOPP) and an improvement to the combustion-noise module GECOR is suggested. The work was carried out in response to the NASA Fundamental Aeronautics Subsonic Fixed Wing Program s Reduced-Perceived-Noise Technical Challenge.

Advanced tow placement of composite fuselage structure

NASA Technical Reports Server (NTRS)

Anderson, Robert L.; Grant, Carroll G.

1992-01-01

The Hercules NASA ACT program was established to demonstrate and validate the low cost potential of the automated tow placement process for fabrication of aircraft primary structures. The program is currently being conducted as a cooperative program in collaboration with the Boeing ATCAS Program. The Hercules advanced tow placement process has been in development since 1982 and was developed specifically for composite aircraft structures. The second generation machine, now in operation at Hercules, is a production-ready machine that uses a low cost prepreg tow material form to produce structures with laminate properties equivalent to prepreg tape layup. Current program activities are focused on demonstration of the automated tow placement process for fabrication of subsonic transport aircraft fuselage crown quadrants. We are working with Boeing Commercial Aircraft and Douglas Aircraft during this phase of the program. The Douglas demonstration panels has co-cured skin/stringers, and the Boeing demonstration panel is an intricately bonded part with co-cured skin/stringers and co-bonded frames. Other aircraft structures that were evaluated for the automated tow placement process include engine nacelle components, fuselage pressure bulkheads, and fuselage tail cones. Because of the cylindrical shape of these structures, multiple parts can be fabricated on one two placement tool, thus reducing the cost per pound of the finished part.

Reconfiguration control system for an aircraft wing

NASA Technical Reports Server (NTRS)

Wakayama, Sean R. (Inventor)

2008-01-01

Independently deflectable control surfaces are located on the trailing edge of the wing of a blended wing-body aircraft. The reconfiguration control system of the present invention controls the deflection of each control surface to optimize the spanwise lift distribution across the wing for each of several flight conditions, e.g., cruise, pitch maneuver, and high lift at low speed. The control surfaces are deflected and reconfigured to their predetermined optimal positions when the aircraft is in each of the aforementioned flight conditions. With respect to cruise, the reconfiguration control system will maximize the lift to drag ratio and keep the aircraft trimmed at a stable angle of attack. In a pitch maneuver, the control surfaces are deflected to pitch the aircraft and increase lift. Moreover, this increased lift has its spanwise center of pressure shifted inboard relative to its location for cruise. This inboard shifting reduces the increased bending moment about the aircraft's x-axis occasioned by the increased pitch force acting normal to the wing. To optimize high lift at low speed, during take-off and landing for example, the control surfaces are reconfigured to increase the local maximum coefficient of lift at stall-critical spanwise locations while providing pitch trim with control surfaces that are not stall critical.

Improving the Flow

NASA Technical Reports Server (NTRS)

2004-01-01

In early 1995, NASA s Glenn Research Center (then Lewis Research Center) formed an industry-government team with several jet engine companies to develop the National Combustion Code (NCC), which would help aerospace engineers solve complex aerodynamics and combustion problems in gas turbine, rocket, and hypersonic engines. The original development team consisted of Allison Engine Company (now Rolls-Royce Allison), CFD Research Corporation, GE Aircraft Engines, Pratt and Whitney, and NASA. After the baseline beta version was established in July 1998, the team focused its efforts on consolidation, streamlining, and integration, as well as enhancement, evaluation, validation, and application. These activities, mainly conducted at NASA Glenn, led to the completion of NCC version 1.0 in October 2000. NCC version 1.0 features high-fidelity representation of complex geometry, advanced models for two-phase turbulent combustion, and massively parallel computing. Researchers and engineers at Glenn have been using NCC to provide analysis and design support for various aerospace propulsion technology development projects. NASA transfers NCC technology to external customers using non- exclusive Space Act Agreements. Glenn researchers also communicate research and development results derived from NCC's further development through publications and special sessions at technical conferences.

Tiltrotor Vibration Reduction Through Higher Harmonic Control

NASA Technical Reports Server (NTRS)

Nixon, Mark W.; Kvaternik, Raymond G.; Settle, T. Ben

1997-01-01

The results of a joint NASA/Army/Bell Helicopter Textron wind-tunnel test to assess the potential of higher harmonic control (HHC) for reducing vibrations in tiltrotor aircraft operating in the airplane mode of flight, and to evaluate the effectiveness of a Bell-developed HHC algorithm called MAVSS (Multipoint Adaptive Vibration Suppression System) are presented. The test was conducted in the Langley Transonic Dynamics Tunnel using an unpowered 1/5-scale semispan aeroelastic model of the V-22 which was modified to incorporate an HHC system employing both the rotor swashplate and the wing flaperon. The effectiveness of the swashplate and the flaperon acting either singly or in combination in reducing IP and 3P wing vibrations over a wide range of tunnel airspeeds and rotor rotational speeds was demonstrated. The MAVSS algorithm was found to be robust to variations in tunnel airspeed and rotor speed, requiring only occasional on-line recalculations of the system transfer matrix. HHC had only a small (usually beneficial) effect on blade loads but increased pitch link loads by 25%. No degradation in aeroelastic stability was noted for any of the conditions tested.

Climate impact of anthropogenic aerosols on cirrus clouds

NASA Astrophysics Data System (ADS)

Penner, J.; Zhou, C.

2017-12-01

Cirrus clouds have a net warming effect on the atmosphere and cover about 30% of the Earth's area. Aerosol particles initiate ice formation in the upper troposphere through modes of action that include homogeneous freezing of solution droplets, heterogeneous nucleation on solid particles immersed in a solution, and deposition nucleation of vapor onto solid particles. However, the efficacy with which particles act to form cirrus particles in a model depends on the representation of updrafts. Here, we use a representation of updrafts based on observations of gravity waves, and follow ice formation/evaporation during both updrafts and downdrafts. We examine the possible change in ice number concentration from anthropogenic soot originating from surface sources of fossil fuel and biomass burning and from aircraft particles that have previously formed ice in contrails. Results show that fossil fuel and biomass burning soot aerosols with this version exert a radiative forcing of -0.15±0.02 Wm-2 while aircraft aerosols that have been pre-activated within contrails exert a forcing of -0.20±0.06 Wm-2, but it is possible to decrease these estimates of forcing if a larger fraction of dust particles act as heterogeneous ice nuclei. In addition aircraft aerosols may warm the climate if a large fraction of these particles act as ice nuclei. The magnitude of the forcing in cirrus clouds can be comparable to the forcing exerted by anthropogenic aerosols on warm clouds. This assessment could therefore support climate models with high sensitivity to greenhouse gas forcing, while still allowing the models to fit the overall historical temperature change.

A review of turbine blade tip heat transfer.

PubMed

Bunker, R S

2001-05-01

This paper presents a review of the publicly available knowledge base concerning turbine blade tip heat transfer, from the early fundamental research which laid the foundations of our knowledge, to current experimental and numerical studies utilizing engine-scaled blade cascades and turbine rigs. Focus is placed on high-pressure, high-temperature axial-turbine blade tips, which are prevalent in the majority of today's aircraft engines and power generating turbines. The state of our current understanding of turbine blade tip heat transfer is in the transitional phase between fundamentals supported by engine-based experience, and the ability to a priori correctly predict and efficiently design blade tips for engine service.

Analysis of operational limit of an aircraft: An aeroelastic approach

NASA Astrophysics Data System (ADS)

Hasan, Md. Mehedi; Hassan, M. D. Mehedi; Sarrowar, S. M. Bayazid; Faisal, Kh. Md.; Ahmed, Sheikh Reaz, Dr.

2017-06-01

In classical theory of elasticity, external loading acting on the body is independent of deformation of the body. But, in aeroelasticity, aerodynamic forces depend on the attitude of the body relative to the flow. Aircraft's are subjected to a range of static loads resulting from equilibrium or steady flight maneuvers such as coordinated level turn, steady pitch and bank rate, steady and level flight. Interaction of these loads with elastic forces of aircraft structure creates some aeroelastic phenomena. In this paper, we have summarized recent developments in the area of aeroelasticity. A numerical approach has been applied for finding divergence speed, a static aeroelastic phenomena, of a typical aircraft. This paper also involves graphical representations of constraints on load factor and bank angle during different steady flight maneuvers taking flexibility into account and comparing it with the value without flexibility. Effect of wing skin thickness, spar web thickness and position of flexural axis of wing on this divergence speed as well as load factor and bank angle has also been observed using MATLAB.

7. VIEW WEST OF SCALE ROOM IN FULLSCALE WIND TUNNEL; ...

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

7. VIEW WEST OF SCALE ROOM IN FULL-SCALE WIND TUNNEL; SCALES ARE USED TO MEASURE FORCES ACTING ON MODEL AIRCRAFT SUSPENDED ABOVE. - NASA Langley Research Center, Full-Scale Wind Tunnel, 224 Hunting Avenue, Hampton, Hampton, VA

The Hurricane Rainband and Intensity Change Experiment (RAINEX): Observations and Modeling of Hurricanes Katrina, Ophelia, and Rita (2005)

NASA Astrophysics Data System (ADS)

Houze, R. A.

2006-12-01

The Hurricane Rainband and Intensity Change Experiment (RAINEX) used three P3 aircraft aided by high- resolution numerical modeling and satellite communications to investigate the 2005 Hurricanes Katrina, Ophelia, and Rita. The aim was to increase the understanding of tropical cyclone intensity change by interactions between a tropical cyclone's inner core and rainbands. All three aircraft had dual-Doppler radars, with the ELDORA radar on board the Naval Research Laboratory's P3 aircraft, providing particularly detailed Doppler radar data. Numerical model forecasts helped plan the aircraft missions, and innovative communications and data transfer in real time allowed the flights to be coordinated from a ground-based operations center. The P3 aircraft released approximately 600 dropsondes in locations targeted for optimal coordination with the Doppler radar data, as guided by the operations center. The storms were observed in all stages of development, from Tropical Depression to Category 5 hurricane. The data from RAINEX are readily available through an online Field Catalog and RAINEX Data Archive. The RAINEX dataset is illustrated by a preliminary analysis of Hurricane Rita, which was documented by multi-aircraft flights on five days: 1) while a tropical storm, 2) while rapidly intensifying to a Category 5 hurricane, 3) during an eyewall replacement, 4) when the hurricane became asymmetric upon encountering environmental shear, and 5) just prior to landfall.

Experimental Investigation of Pool Boiling Heat Transfer Enhancement in Microgravity in the Presence of Electric Fields

NASA Technical Reports Server (NTRS)

Herman, Cila

1996-01-01

Boiling is an effective mode of heat transfer since high heat flux levels are possible driven by relatively small temperature differences. The high heat transfer coefficients associated with boiling have made the use of these processes increasingly attractive to aerospace engineering. Applications of this type include compact evaporators in the thermal control of aircraft avionics and spacecraft environments, heat pipes, and use of boiling to cool electronic equipment. In spite of its efficiency, cooling based on liquid-vapor phase change processes has not yet found wide application in aerospace engineering due to specific problems associated with the low gravity environment. After a heated surface has reached the superheat required for the initiation of nucleate boiling, bubbles will start forming at nucleation sites along the solid interface by evaporation of the liquid. Bubbles in contact with the wall will continue growing by this mechanism until they detach. In terrestrial conditions, bubble detachment is determined by the competition between body forces (e.g. buoyancy) and surface tension forces that act to anchor the bubble along the three phase contact line. For a given body force potential and a balance of tensions along the three phase contact line, bubbles must reach a critical size before the body force can cause them to detach from the wall. In a low gravity environment the critical bubble size for detachment is much larger than under terrestrial conditions, since buoyancy is a less effective means of bubble removal. Active techniques of heat transfer enhancement in single phase and phase change processes by utilizing electric fields have been the subject of intensive research during recent years. The field of electrohydrodynamics (EHD) deals with the interactions between electric fields, flow fields and temperature fields. Previous studies indicate that in terrestrial applications nucleate boiling heat transfer can be increased by a factor of 50 as compared to values obtained for the same system without electric fields. Imposing an external electric field holds the promise to improve pool boiling heat transfer in low gravity, since a phase separation force other than gravity is introduced. The goal of our research is to experimentally investigate the potential of EHD and the mechanisms responsible for EHD heat transfer enhancement in boiling in low gravity conditions.

Preservation of Separating, Transferring, or Separated Personnel's Records in Accordance with the Federal Records Act

EPA Pesticide Factsheets

This procedure is designed to ensure that all records as defined in the Federal Records Act, independent of media and format, created or received by EPA employees who are separating, transferring or have separated from an employment relationship with EPA.

12 CFR 1005.3 - Coverage.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Banking BUREAU OF CONSUMER FINANCIAL PROTECTION ELECTRONIC FUND TRANSFERS (REGULATION E) General § 1005.3... Consumer Financial Protection Act of 2010, Title X of the Dodd-Frank Wall Street Reform and Consumer Protection Act, Public Law 111-203, 124 Stat. 1376. (b) Electronic fund transfer. (1) Definition. The term...

Coast Guard Assists with Mapping of Great Lakes Ice

NASA Image and Video Library

1976-11-21

A group of Coast Guard seamen leave their ship to verify ice formations on the Great Lakes as part of an joint effort with the National Aeronautics and Space Administration (NASA) Lewis Research Center and the National Oceanic and Atmospheric Administration. The regular winter freezing of large portions of the Great Lakes stalled the shipping industry. Lewis began working on two complementary systems to monitor the ice. The Side Looking Airborne Radar (SLAR) system used microwaves to measure the ice distribution and electromagnetic systems used noise modulation to determine the thickness of the ice. The images were then transferred via satellite to the Coast Guard station. The Coast Guard then transmitted the pertinent images by VHF to the ship captains to help them select the best route. The Great Lakes ice mapping devices were first tested on NASA aircraft during the winter of 1972 and 1973. The pulsed radar system was transferred to the Coast Guard’s C-130 aircraft for the 1975 and 1976 winter. The SLAR was installed in the rear cargo door, and the small S-band antenna was mounted to the underside of the aircraft. Coast Guard flights began in January 1975 at an altitude of 11,000 feet. Early in the program, teams of guardsmen and NASA researchers frequently set out in boats to take samples and measurements of the ice in order to verify the radar information.

Dynamic Structural Fault Detection and Identification

NASA Technical Reports Server (NTRS)

Smith, Timothy; Reichenbach, Eric; Urnes, James M.

2009-01-01

Aircraft structures are designed to guarantee safety of flight in some required operational envelope. When the aircraft becomes structurally impaired, safety of flight may not be guaranteed within that previously safe operational envelope. In this case the safe operational envelope must be redefined in-flight and a means to prevent excursion from this new envelope must be implemented. A specific structural failure mode that may result in a reduced safe operating envelope, the exceedance of which could lead to catastrophic structural failure of the aircraft, will be addressed. The goal of the DFEAP program is the detection of this failure mode coupled with flight controls adaptation to limit critical loads in the damaged aircraft structure. The DFEAP program is working with an F/A-18 aircraft model. The composite wing skins are bonded to metallic spars in the wing substructure. Over time, it is possible that this bonding can deteriorate due to fatigue. In this case, the ability of the wing spar to transfer loading between the wing skins is reduced. This failure mode can translate to a reduced allowable compressive strain on the wing skin and could lead to catastrophic wing buckling if load limiting of the wing structure is not applied. The DFEAP program will make use of a simplified wing strain model for the healthy aircraft. The outputs of this model will be compared in real-time to onboard strain measurements at several locations on the aircraft wing. A damage condition is declared at a given location when the strain measurements differ sufficiently from the strain model. Parameter identification of the damaged structure wing strain parameters will be employed to provide load limiting control adaptation for the aircraft. This paper will discuss the simplified strain models used in the implementation and their interaction with the strain sensor measurements. Also discussed will be the damage detection and identification schemes employed and the means by which the damaged aircraft parameters will be used to provide load limiting that keeps the aircraft within the safe operational envelope.

27 CFR 28.143 - Containers.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 27 Alcohol, Tobacco Products and Firearms 1 2010-04-01 2010-04-01 false Containers. 28.143 Section....143 Containers. (a) Beer. Beer being exported, used as supplies on vessels and aircraft, or..., or bulk containers. (b) Beer concentrate. Concentrate may not be removed for export, or for transfer...

Evaluation of the Hinge Moment and Normal Force Aerodynamic Loads from a Seamless Adaptive Compliant Trailing Edge Flap in Flight

NASA Technical Reports Server (NTRS)

Miller, Eric J.; Cruz, Josue; Lung, Shun-Fat; Kota, Sridhar; Ervin, Gregory; Lu, Kerr-Jia; Flick, Pete

2016-01-01

A seamless adaptive compliant trailing edge (ACTE) flap was demonstrated in flight on a Gulfstream III aircraft at the NASA Armstrong Flight Research Center. The trailing edge flap was deflected between minus 2 deg up and plus 30 deg down in flight. The safety-of-flight parameters for the ACTE flap experiment require that flap-to-wing interface loads be sensed and monitored in real time to ensure that the structural load limits of the wing are not exceeded. The attachment fittings connecting the flap to the aircraft wing rear spar were instrumented with strain gages and calibrated using known loads for measuring hinge moment and normal force loads in flight. The safety-of-flight parameters for the ACTE flap experiment require that flap-to-wing interface loads be sensed and monitored in real time to ensure that the structural load limits of the wing are not exceeded. The attachment fittings connecting the flap to the aircraft wing rear spar were instrumented with strain gages and calibrated using known loads for measuring hinge moment and normal force loads in flight. The interface hardware instrumentation layout and load calibration are discussed. Twenty-one applied calibration test load cases were developed for each individual fitting. The 2-sigma residual errors for the hinge moment was calculated to be 2.4 percent, and for normal force was calculated to be 7.3 percent. The hinge moment and normal force generated by the ACTE flap with a hinge point located at 26-percent wing chord were measured during steady state and symmetric pitch maneuvers. The loads predicted from analysis were compared to the loads observed in flight. The hinge moment loads showed good agreement with the flight loads while the normal force loads calculated from analysis were over-predicted by approximately 20 percent. Normal force and hinge moment loads calculated from the pressure sensors located on the ACTE showed good agreement with the loads calculated from the installed strain gages.

Water transfer and major environmental provisions of the Central Valley Project Improvement Act: A preliminary economic evaluation

NASA Astrophysics Data System (ADS)

Loomis, John B.

1994-06-01

Increasing block water pricing, water transfer, and wildlife refuge water supply provisions of the Central Valley Project (CVP) Improvement Act are analyzed in terms of likely farmer response and economic efficiency of these provisions. Based on a simplified partial equilibrium analysis, we estimate small, but significant water conservation savings due to pricing reform, the potential for substantial water transfers to non-CVP customers in severe drought years when the water price exceeds 110 per acre foot (1 acre foot equals 1.234 × 103 m3) and positive net benefits for implementation of the wildlife refuge water supply provisions. The high threshold water price is partly a result of requiring farmers to pay full cost on transferred water plus a surcharge of 25 per acre foot if the water is transferred to a non-CVP user. The act also sets an important precedent for water pricing reform, water transfer provisions, and environmental surcharges on water users that may find their way to other Bureau of Reclamation projects.

77 FR 11750 - Idaho: Final Approval of State Underground Storage Tank Program

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-28

... defined under Executive Order 12866. I. National Technology Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995 (``NTTAA''), Public Law 104-113, 12(d... the time needed to review instructions; develop, acquire, install, and utilize technology and systems...

76 FR 57659 - Oregon: Final Approval of State Underground Storage Tank Program

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-16

... defined under Executive Order 12866. I. National Technology Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995 (``NTTAA''), Public Law 104-113, 12(d... instructions; develop, acquire, install, and utilize technology and systems for the purposes of collecting...

16 CFR 1750.2 - Transfer of functions.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Commercial Practices CONSUMER PRODUCT SAFETY COMMISSION REFRIGERATOR SAFETY ACT REGULATIONS STANDARD FOR DEVICES TO PERMIT THE OPENING OF HOUSEHOLD REFRIGERATOR DOORS FROM THE INSIDE § 1750.2 Transfer of functions. Effective May 14, 1973, section 30(c) of the Consumer Product Safety Act (86 Stat. 1231; 15 U.S.C...

16 CFR § 1750.2 - Transfer of functions.

Code of Federal Regulations, 2013 CFR

2013-01-01

...§ 1750.2 Commercial Practices CONSUMER PRODUCT SAFETY COMMISSION REFRIGERATOR SAFETY ACT REGULATIONS STANDARD FOR DEVICES TO PERMIT THE OPENING OF HOUSEHOLD REFRIGERATOR DOORS FROM THE INSIDE § 1750.2 Transfer of functions. Effective May 14, 1973, section 30(c) of the Consumer Product Safety Act (86 Stat...

16 CFR 1750.2 - Transfer of functions.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Commercial Practices CONSUMER PRODUCT SAFETY COMMISSION REFRIGERATOR SAFETY ACT REGULATIONS STANDARD FOR DEVICES TO PERMIT THE OPENING OF HOUSEHOLD REFRIGERATOR DOORS FROM THE INSIDE § 1750.2 Transfer of functions. Effective May 14, 1973, section 30(c) of the Consumer Product Safety Act (86 Stat. 1231; 15 U.S.C...

16 CFR 1750.2 - Transfer of functions.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Commercial Practices CONSUMER PRODUCT SAFETY COMMISSION REFRIGERATOR SAFETY ACT REGULATIONS STANDARD FOR DEVICES TO PERMIT THE OPENING OF HOUSEHOLD REFRIGERATOR DOORS FROM THE INSIDE § 1750.2 Transfer of functions. Effective May 14, 1973, section 30(c) of the Consumer Product Safety Act (86 Stat. 1231; 15 U.S.C...

16 CFR 1750.2 - Transfer of functions.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Commercial Practices CONSUMER PRODUCT SAFETY COMMISSION REFRIGERATOR SAFETY ACT REGULATIONS STANDARD FOR DEVICES TO PERMIT THE OPENING OF HOUSEHOLD REFRIGERATOR DOORS FROM THE INSIDE § 1750.2 Transfer of functions. Effective May 14, 1973, section 30(c) of the Consumer Product Safety Act (86 Stat. 1231; 15 U.S.C...

20 CFR 628.550 - Transfer of funds.

Code of Federal Regulations, 2010 CFR

2010-04-01

... Employees' Benefits EMPLOYMENT AND TRAINING ADMINISTRATION, DEPARTMENT OF LABOR PROGRAMS UNDER TITLE II OF THE JOB TRAINING PARTNERSHIP ACT Program Design Requirements for Programs Under Title II of the Job Training Partnership Act § 628.550 Transfer of funds. If described in the job training plan and approved by...

Identification of aerodynamic models for maneuvering aircraft

NASA Technical Reports Server (NTRS)

Chin, Suei; Lan, C. Edward

1990-01-01

Due to the requirement of increased performance and maneuverability, the flight envelope of a modern fighter is frequently extended to the high angle-of-attack regime. Vehicles maneuvering in this regime are subjected to nonlinear aerodynamic loads. The nonlinearities are due mainly to three-dimensional separated flow and concentrated vortex flow that occur at large angles of attack. Accurate prediction of these nonlinear airloads is of great importance in the analysis of a vehicle's flight motion and in the design of its flight control system. A satisfactory evaluation of the performance envelope of the aircraft may require a large number of coupled computations, one for each change in initial conditions. To avoid the disadvantage of solving the coupled flow-field equations and aircraft's motion equations, an alternate approach is to use a mathematical modeling to describe the steady and unsteady aerodynamics for the aircraft equations of motion. Aerodynamic forces and moments acting on a rapidly maneuvering aircraft are, in general, nonlinear functions of motion variables, their time rate of change, and the history of maneuvering. A numerical method was developed to analyze the nonlinear and time-dependent aerodynamic response to establish the generalized indicial function in terms of motion variables and their time rates of change.

The fiber-optic high-speed data bus for a new generation of military aircraft

NASA Astrophysics Data System (ADS)

Uhlhorn, Roger W.

1991-02-01

The avionic suite for the next generation of military aircraft is being designed with component and module commonality in mind in order to control recurring costs and capitalize on economy of scale. The backbone of the suite fashioned out of these modular building blocks is the fiber-optic bit-serial time-division multiplexed high-speed data bus (HSDB), operating at 50 Mb/s, which provides command and control communications among most of the aircraft subsystems and can be used to provide communications for a fly-by-light flight-control system or for the block transfer of data between mass memories and data processors. The fiber-optic HSDB is examined from the top down, beginning with an overview of the evolution of avionic architectures. A review is given of the standardization activity associated with development of the network, the protocols chosen to implement the desired communication functions, configuration options, and the fiber-optic components used in the bus interfaces or other active nodes of the network. It is believed that the utility of the bus extends beyond aircraft to spacecraft, ships, and land vehicles.

An Experimental Investigation on Bio-inspired Icephobic Coatings for Aircraft Icing Mitigation

NASA Astrophysics Data System (ADS)

Hu, Hui; Li, Haixing; Waldman, Rye

2016-11-01

By leveraging the Icing Research Tunnel available at Iowa State University (ISU-IRT), a series of experimental investigations were conducted to elucidate the underlying physics pertinent to aircraft icing phenomena. A suite of advanced flow diagnostic techniques, which include high-speed photographic imaging, digital image projection (DIP), and infrared (IR) imaging thermometry, were developed and applied to quantify the transient behavior of water droplet impingement, wind-driven surface water runback, unsteady heat transfer and dynamic ice accreting process over the surfaces of airfoil/wing models. The icephobic performance of various bio-inspired superhydrophobic coatings were evaluated quantitatively at different icing conditions. The findings derived from the icing physics studies can be used to improve current icing accretion models for more accurate prediction of ice formation and accretion on aircraft wings and to develop effective anti-/deicing strategies for safer and more efficient operation of aircraft in cold weather. The research work is partially supported by NASA with Grant Number NNX12AC21A and National Science Foundation under Award Numbers of CBET-1064196 and CBET-1435590.

14 CFR 23.471 - General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false General. 23.471 Section 23.471 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... forces that act upon an airplane structure. In each specified ground load condition, the external...

14 CFR 23.471 - General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false General. 23.471 Section 23.471 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... forces that act upon an airplane structure. In each specified ground load condition, the external...

14 CFR 23.471 - General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false General. 23.471 Section 23.471 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... forces that act upon an airplane structure. In each specified ground load condition, the external...

14 CFR 23.471 - General.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false General. 23.471 Section 23.471 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... forces that act upon an airplane structure. In each specified ground load condition, the external...

14 CFR 23.471 - General.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false General. 23.471 Section 23.471 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... forces that act upon an airplane structure. In each specified ground load condition, the external...

40 CFR 124.10 - Public notice of permit actions and public comment period.

Code of Federal Regulations, 2013 CFR

2013-07-01

... issued or is required to issue a RCRA, UIC, PSD (or other permit under the Clean Air Act), NPDES, 404... which may affect aircraft operations or for purposes associated with seaplane operations; (vii) For PSD...

36 CFR 328.5 - Guidelines for seaplane use of project waters.

Code of Federal Regulations, 2014 CFR

2014-07-01

... operations of the aircraft while upon the water shall be in accordance with the marine rules of the road for... the Federal Water Pollution Control Act of 1972 (Pub. L. 92-500). (g) Appropriate signs should be...

36 CFR 328.5 - Guidelines for seaplane use of project waters.

Code of Federal Regulations, 2010 CFR

2010-07-01

... operations of the aircraft while upon the water shall be in accordance with the marine rules of the road for... the Federal Water Pollution Control Act of 1972 (Pub. L. 92-500). (g) Appropriate signs should be...

36 CFR § 328.5 - Guidelines for seaplane use of project waters.

Code of Federal Regulations, 2013 CFR

2013-07-01

... operations of the aircraft while upon the water shall be in accordance with the marine rules of the road for... the Federal Water Pollution Control Act of 1972 (Pub. L. 92-500). (g) Appropriate signs should be...

36 CFR 328.5 - Guidelines for seaplane use of project waters.

Code of Federal Regulations, 2011 CFR

2011-07-01

... operations of the aircraft while upon the water shall be in accordance with the marine rules of the road for... the Federal Water Pollution Control Act of 1972 (Pub. L. 92-500). (g) Appropriate signs should be...

36 CFR 328.5 - Guidelines for seaplane use of project waters.

Code of Federal Regulations, 2012 CFR

2012-07-01

... operations of the aircraft while upon the water shall be in accordance with the marine rules of the road for... the Federal Water Pollution Control Act of 1972 (Pub. L. 92-500). (g) Appropriate signs should be...

Aircraft measurement of ozone turbulent flux in the atmospheric boundary layer

NASA Astrophysics Data System (ADS)

Affre, Ch.; Carrara, A.; Lefebre, F.; Druilhet, A.; Fontan, J.; Lopez, A.

In May 1995, the "Chimie-Creil 95" experiment was undertaken in the north of France. The field data are first used to validate the methodology for airborne measurement of ozone flux. A certain number of methodological problems due to the location of the fast ozone sensor inside the airplane are, furthermore discussed. The paper describes the instrumentation of the ARAT (Avion de Recherche Atmosphérique et de Télédétection), an atmospheric research and remote-sensing aircraft used to perform the airborne measurements, the area flown over, the meteorological conditions and boundary layer stability conditions. These aircraft measurements are then used to determine ozone deposition velocity and values are proposed for aerodynamic, bulk transfer coefficients (ozone and momentum). The paper also establishes the relationship between the normalised standard deviation and stability parameters ( z/ L) for ozone, temperature, humidity and vertical velocity. The laws obtained are then presented.

An approach to the determination of aircraft handling qualities using pilot transfer functions

NASA Technical Reports Server (NTRS)

Adams, J. J.; Hatch, H. G., Jr.

1978-01-01

It was shown that a correlation exists between pilot-aircraft system closed-loop characteristics, determined by using analytical expressions for pilot response along with the analytical expression for the aircraft response, and pilot ratings obtained in many previous flight and simulation studies. Two different levels of preferred pilot response were used. These levels were: (1) a static gain and a second-order lag function with a lag time constant of 0.2 second; and (2) a static gain, a lead time constant of 1 second, and a 0.2-second lag time constant. If a system response with a pitch-angle time constant of 2.6 seconds and a stable oscillatory mode of motion with a period of 2.5 seconds could be achieved with the first-level pilot model, it was shown that the pilot rating will be satisfactory for that vehicle.

Fully unsteady subsonic and supersonic potential aerodynamics for complex aircraft configurations with applications to flutter

NASA Technical Reports Server (NTRS)

Tseng, K.; Morino, L.

1975-01-01

A general formulation is presented for the analysis of steady and unsteady, subsonic and supersonic aerodynamics for complex aircraft configurations. The theoretical formulation, the numerical procedure, the description of the program SOUSSA (steady, oscillatory and unsteady, subsonic and supersonic aerodynamics) and numerical results are included. In particular, generalized forces for fully unsteady (complex frequency) aerodynamics for a wing-body configuration, AGARD wing-tail interference in both subsonic and supersonic flows as well as flutter analysis results are included. The theoretical formulation is based upon an integral equation, which includes completely arbitrary motion. Steady and oscillatory aerodynamic flows are considered. Here small-amplitude, fully transient response in the time domain is considered. This yields the aerodynamic transfer function (Laplace transform of the fully unsteady operator) for frequency domain analysis. This is particularly convenient for the linear systems analysis of the whole aircraft.

Pragmatic Transfer.

ERIC Educational Resources Information Center

Kasper, Gabriele

1992-01-01

Attempting to clarify the concept of pragmatic transfer, this article proposes as a basic distinction Leech/Thomas' dichotomy of sociopragmatics versus pragmalinguistics, presenting evidence for transfer at both levels. Issues discussed include pragmatic universals in speech act realization, conditions for pragmatic transfer, communicative…

Managing acute coronary syndrome during medical air evacuation from a remote location at sea.

PubMed

Westmoreland, Andrew H

2014-01-01

Coronary emergencies at sea requiring air evacuation are not uncommon. On board a Nimitz-class aircraft carrier while in a remote location, an active duty sailor suffered a myocardial infarction. A medical evacuation by helicopter was necessary. Transfer proved difficult due to the ship's location, poor flying conditions, and the patient's deteriorating condition. This case stresses the importance of expeditious diagnosis, treatment, and air transfer to shore-based facilities capable of providing definitive coronary care. A 33-yr-old man recently started on trazodone due to depression complained of chest pain. The patient was hemodynamically unstable and electrocardiogram showed ST segment elevation and Q waves in the anterior, inferior, and lateral leads. He was air-lifted to the nearest accepting facility with cardiac catheterization capabilities, which was over 300 miles away. Poor weather conditions hindered the pilot's ability to fly the original course. The patient remained critical and medication choices were limited. Even with all of these obstacles, everyone involved performed his or her duties admirably. The patient's condition improved by the time the helicopter landed. He was then rushed by ambulance to the hospital's coronary care unit, where he was successfully treated. This case highlights the need to keep a high index of suspicion when patients complain of chest pain, regardless of age. It is of the utmost importance that individuals capable of thinking and acting quickly are assigned to medical evacuation teams, and that they continue to train regularly, as coronary events at sea are not uncommon.

48 CFR 970.2770-3 - Technology transfer and patent rights.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 48 Federal Acquisition Regulations System 5 2013-10-01 2013-10-01 false Technology transfer and....2770-3 Technology transfer and patent rights. The National Competitiveness Technology Transfer Act of 1989 (NCTTA) established technology transfer as a mission for Government-owned, contractor-operated...

48 CFR 970.2770-3 - Technology transfer and patent rights.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 48 Federal Acquisition Regulations System 5 2014-10-01 2014-10-01 false Technology transfer and....2770-3 Technology transfer and patent rights. The National Competitiveness Technology Transfer Act of 1989 (NCTTA) established technology transfer as a mission for Government-owned, contractor-operated...

48 CFR 970.2770-3 - Technology transfer and patent rights.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 48 Federal Acquisition Regulations System 5 2012-10-01 2012-10-01 false Technology transfer and....2770-3 Technology transfer and patent rights. The National Competitiveness Technology Transfer Act of 1989 (NCTTA) established technology transfer as a mission for Government-owned, contractor-operated...

48 CFR 970.2770-3 - Technology transfer and patent rights.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 48 Federal Acquisition Regulations System 5 2011-10-01 2011-10-01 false Technology transfer and....2770-3 Technology transfer and patent rights. The National Competitiveness Technology Transfer Act of 1989 (NCTTA) established technology transfer as a mission for Government-owned, contractor-operated...

48 CFR 970.2770-3 - Technology transfer and patent rights.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 5 2010-10-01 2010-10-01 false Technology transfer and....2770-3 Technology transfer and patent rights. The National Competitiveness Technology Transfer Act of 1989 (NCTTA) established technology transfer as a mission for Government-owned, contractor-operated...

Experimental and computational surface and flow-field results for an all-body hypersonic aircraft

NASA Technical Reports Server (NTRS)

Lockman, William K.; Lawrence, Scott L.; Cleary, Joseph W.

1990-01-01

The objective of the present investigation is to establish a benchmark experimental data base for a generic hypersonic vehicle shape for validation and/or calibration of advanced computational fluid dynamics computer codes. This paper includes results from the comprehensive test program conducted in the NASA/Ames 3.5-foot Hypersonic Wind Tunnel for a generic all-body hypersonic aircraft model. Experimental and computational results on flow visualization, surface pressures, surface convective heat transfer, and pitot-pressure flow-field surveys are presented. Comparisons of the experimental results with computational results from an upwind parabolized Navier-Stokes code developed at Ames demonstrate the capabilities of this code.

NASA Beechcraft KingAir #801 in flight

NASA Technical Reports Server (NTRS)

1998-01-01

NASA 801 Beechcraft Beech Super KingAir in flight. The Beechcraft Beech 200 Super KingAir aircraft N7NA, known as NASA 7, has been a support aircraft for many years, flying 'shuttle' missions to Ames Research Center. It once flew from the Jet Propulsion Laboratory and back each day but now (2001) flies between the Dryden Flight Research Center and Ames. A second Beechcraft Beech 200 Super King Air, N701NA, redesignated N801NA, transferred to Dryden on 3 Oct. 1997 and is used for research missions but substitutes for NASA 7 on shuttle missions when NASA 7 is not available.

NASA #801 and NASA 7 on ramp

NASA Technical Reports Server (NTRS)

1997-01-01

NASA N801NA and NASA 7 together on the NASA Dryden ramp. The Beechcraft Beech 200 Super KingAir aircraft N7NA, known as NASA 7, has been a support aircraft for many years, flying 'shuttle' missions to Ames Research Center. It once flew from the Jet Propulsion Laboratory and back each day but now (2001) flies between the Dryden Flight Research Center and Ames. A second Beechcraft Beech 200 Super King Air, N701NA, redesignated N801NA, transferred to Dryden on 3 Oct. 1997 and is used for research missions but substitutes for NASA 7 on shuttle missions when NASA 7 is not available.

Carbon/graphite fiber risk analysis and assessment study: Assessment of risk to the Lockheed Model L-1011 commercial transport aircraft

NASA Technical Reports Server (NTRS)

Daniledes, J.; Koch, J. R.

1980-01-01

The risk associated with the accidental release of carbon/graphite fibers (CF) from fires on commercial transport aircraft incorporating composite materials was assessed. Data are developed to evaluate the potential for CF damage to electrical and electronic equipment, assess the cost risk, and evaluate the hazard to continued operation. The subjects covered include identification of susceptible equipments, determination of infiltration transfer functions, analysis of airport operations, calculation of probabilities of equipment failures, assessment of the cost risk, and evaluation of the hazard to continued operation. The results show the risks associated with CF contamination are negligible through 1993.

A B-52H, tail number 61-0025, arrives at NASA's Dryden Flight Research Center after landing July 30,

NASA Technical Reports Server (NTRS)

2001-01-01

NASA Dryden Flight Research Center, Edwards, California, received an 'H' model B-52 Stratofortress aircraft on July 30, 2001. The B-52H will be used as an air-launch aircraft supporting NASA's flight research and advanced technology demonstration efforts. Dryden received the B-52H from the U.S. Air Force's (USAF) 23rd Bomb Squadron, 5th Bombardment Wing (Air Combat Command), located at Minot AFB, N.D. A USAF crew flew the aircraft to Dryden. The aircraft, USAF tail number 61-0025, will be loaned initially, then later transferred from the USAF to NASA. The B-52H is scheduled to leave Dryden Aug. 2 for de-militarization and Programmed Depot Maintenance (PDM) at Tinker Air Force Base (AFB), Oklahoma. The depot-level maintenance is scheduled to last about six months and includes a thorough maintenance and inspection process. The newly arrived B-52H is slated to replace Dryden's famous B-52B '008,' in the 2003-2004 timeframe. It will take about one year for the B-52H to be ready for flight research duties. This time includes PDM, construction of the new pylon, installation of the flight research instrumentation equipment, and aircraft envelope clearance flights.

A B-52H, on loan to NASA's Dryden Flight Research Center, makes a pass down the runway prior to land

NASA Technical Reports Server (NTRS)

2001-01-01

NASA Dryden Flight Research Center, Edwards, California, received an 'H' model B-52 Stratofortress aircraft on July 30, 2001. The B-52H will be used as an air-launch aircraft supporting NASA's flight research and advanced technology demonstration efforts. Dryden received the B-52H from the U.S. Air Force's (USAF) 23rd Bomb Squadron, 5th Bombardment Wing (Air Combat Command), located at Minot AFB, N.D. A USAF crew flew the aircraft to Dryden. The aircraft, USAF tail number 61-0025, will be loaned initially, then later transferred from the USAF to NASA. The B-52H is scheduled to leave Dryden Aug. 2 for de-militarization and Programmed Depot Maintenance (PDM) at Tinker Air Force Base (AFB), Oklahoma. The depot-level maintenance is scheduled to last about six months and includes a thorough maintenance and inspection process. The newly arrived B-52H is slated to replace Dryden's famous B-52B '008,' in the 2003-2004 timeframe. It will take about one year for the B-52H to be ready for flight research duties. This time includes PDM, construction of the new pylon, installation of the flight research instrumentation equipment, and aircraft envelope clearance flights.

Department of Defense Program Solicitation 94; Small Business Technology Transfer (STTR) Program; Fiscal Year 1994.

DTIC Science & Technology

1994-01-01

advanced diesel engine components; high-temperature titanium aluminide and Al-Fe alloys for aircraft and missile engines; environmentally compliant...gun-chamber liners and KE penetrator stabilizer fins, tips, and leading edges; low cost, ceramic thermal barrier coatings for gas turbine blades and

Equipment-Device Task Commonality Analysis and Transfer of Training.

ERIC Educational Resources Information Center

Caro, Paul W.

Procedures were developed to enable training personnel systematically and objectively to determine the potential utility of training devices for teaching how to perform missions in operational rotary wing aircraft. These procedures allow comparison of task stimulus and response elements with corresponding elements in synthetic training equipment.…

NASA AERONAUTICS: Impact of Technology Transfer Activities Is Uncertain

DTIC Science & Technology

1993-03-01

agreement, enabled it to make several design changes to its newest commercial aircraft to improve its speed and aerodynamic performance. The changes...made included modifying the overall shape of winglets on the end of both wings and changing the location of fixtures (pylons) that attach the engines

47 CFR 87.25 - Filing of applications.

Code of Federal Regulations, 2011 CFR

2011-10-01

... rules. (c) One application may be submitted for the total number of aircraft stations in the fleet (fleet license). (d) One application for aeronautical land station license may be submitted for the total number of stations in the fleet. (e) One application for modification or transfer of control may be...

47 CFR 87.25 - Filing of applications.

Code of Federal Regulations, 2012 CFR

2012-10-01

... rules. (c) One application may be submitted for the total number of aircraft stations in the fleet (fleet license). (d) One application for aeronautical land station license may be submitted for the total number of stations in the fleet. (e) One application for modification or transfer of control may be...

47 CFR 87.25 - Filing of applications.

Code of Federal Regulations, 2014 CFR

2014-10-01

... rules. (c) One application may be submitted for the total number of aircraft stations in the fleet (fleet license). (d) One application for aeronautical land station license may be submitted for the total number of stations in the fleet. (e) One application for modification or transfer of control may be...

47 CFR 87.25 - Filing of applications.

Code of Federal Regulations, 2013 CFR

2013-10-01

... rules. (c) One application may be submitted for the total number of aircraft stations in the fleet (fleet license). (d) One application for aeronautical land station license may be submitted for the total number of stations in the fleet. (e) One application for modification or transfer of control may be...

Analysis of MMIC arrays for use in the ACTS Aero Experiment

NASA Technical Reports Server (NTRS)

Zimmerman, M.; Lee, R.; Rho, E.; Zaman, Z.

1993-01-01

The Aero Experiment is designed to demonstrate communication from an aircraft to an Earth terminal via the ACTS. This paper describes the link budget and antenna requirements for a 4.8 kbps full-duplex voice link at Ka-Band frequencies. Three arrays, one transmit array developed by TI and two receive arrays developed by GE and Boeing, were analyzed. The predicted performance characteristics of these arrays are presented and discussed in the paper.

Aerospace Safety Advisory Panel report to the NASA acting administrator

NASA Technical Reports Server (NTRS)

1986-01-01

The level of activity of the Aerospace Safety Advisory Panel was increased smewhat during 1985 in concert with the increased mission rate of the National Space Transportation System, the evolutionary changes in management and operation of that program, and the preparation of the Vandenberg Launch Site; the implementation of the Program Definition Phase of the Space Station Program; and the actual flight testing of the X-29 research aircraft. Impending payload STS missions and NASA's overall aircraft operations are reviewed. The safety aspects of the LEASAT salvage mission were assessed. The findings and recommendation of the committee are summerized.

33 CFR 154.1020 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-07-01

... identifying response systems and equipment in a response plan for the applicable operating environment... visibility, and currents within the COTP zone in which the systems or equipment are intended to function... the vessel or aircraft outfitted with the dispersant-application equipment acting as the delivery...

33 CFR 155.1020 - Definitions.

Code of Federal Regulations, 2013 CFR

2013-07-01

... vessel or aircraft outfitted with the dispersant-application equipment acting as the delivery system for...: Adverse weather means the weather conditions that will be considered when identifying response systems and equipment in a response plan for the applicable operating environment. Factors to consider include, but are...

33 CFR 154.1020 - Definitions.

Code of Federal Regulations, 2013 CFR

2013-07-01

... identifying response systems and equipment in a response plan for the applicable operating environment... visibility, and currents within the COTP zone in which the systems or equipment are intended to function... the vessel or aircraft outfitted with the dispersant-application equipment acting as the delivery...

33 CFR 154.1020 - Definitions.

Code of Federal Regulations, 2014 CFR

2014-07-01

... identifying response systems and equipment in a response plan for the applicable operating environment... visibility, and currents within the COTP zone in which the systems or equipment are intended to function... the vessel or aircraft outfitted with the dispersant-application equipment acting as the delivery...

33 CFR 155.1020 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-07-01

... vessel or aircraft outfitted with the dispersant-application equipment acting as the delivery system for...: Adverse weather means the weather conditions that will be considered when identifying response systems and equipment in a response plan for the applicable operating environment. Factors to consider include, but are...

14 CFR 25.321 - General.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false General. 25.321 Section 25.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of...

14 CFR 25.321 - General.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 1 2013-01-01 2013-01-01 false General. 25.321 Section 25.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of...

14 CFR 23.321 - General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false General. 23.321 Section 23.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... General. (a) Flight load factors represent the ratio of the aerodynamic force component (acting normal to...

14 CFR 25.321 - General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false General. 25.321 Section 25.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of...

14 CFR 25.321 - General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false General. 25.321 Section 25.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of...

14 CFR 23.321 - General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false General. 23.321 Section 23.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... General. (a) Flight load factors represent the ratio of the aerodynamic force component (acting normal to...

14 CFR 23.321 - General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false General. 23.321 Section 23.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... General. (a) Flight load factors represent the ratio of the aerodynamic force component (acting normal to...

14 CFR 25.321 - General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false General. 25.321 Section 25.321 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... represent the ratio of the aerodynamic force component (acting normal to the assumed longitudinal axis of...

Ultralight Aircraft Smuggling Prevention Act of 2011

THOMAS, 112th Congress

Sen. Udall, Tom [D-NM

2011-12-08

House - 12/12/2011 Held at the desk. (All Actions) Notes: For further action, see H.R.3801, which became Public Law 112-93 on 2/10/2012. Tracker: This bill has the status Passed SenateHere are the steps for Status of Legislation:

77 FR 35870 - Approval of Air Quality Implementation Plans; Wisconsin; Partial Disapproval of “Infrastructure...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-15

... alignment of the State and Federal definition for ``major modification'' occurs as expeditiously as possible... disapproves a state rule implementing a Federal Standard. National Technology Transfer Advancement Act In..., the requirements of section 12(d) of the National Technology Transfer and Advancement Act of 1995 (15...

76 FR 11404 - Oregon: Tentative Approval of State Underground Storage Tank Program

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-02

... Order 12866. 9. National Technology Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995 (``NTTAA''), Public Law 104-113, section 12(d) (15 U.S.C. 272... Confidential Business Information (CBI) or other information whose disclosure is restricted by statute. Do not...

75 FR 41991 - Amendments to National Emission Standards for Hazardous Air Pollutants: Area Source Standards for...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-20

... Technology Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act... confidential business information (CBI) or other information whose disclosure is restricted by statute. Do not... Concerning Regulations That Significantly Affect Energy Supply, Distribution, or Use I. National Technology...

77 FR 8209 - Quality Assurance Requirements for Continuous Opacity Monitoring Systems at Stationary Sources

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-14

... Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995... Division, Measurement Technology Group (Mail Code: E143-02), Research Triangle Park, NC 27711; telephone... significant economic impact on a substantial number of small entities. Small entities include small businesses...

77 FR 59758 - Idaho: Incorporation by Reference of Approved State Hazardous Waste Management Program

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-01

... defined under Executive Order 12866. 9. National Technology Transfer and Advancement Act Section 12(d) of the National Technology Transfer and Advancement Act of 1995 (``NTTAA''), Public Law 104-113, section..., unless the EPA receives adverse comment on this regulation by the close of business October 31, 2012. If...

76 FR 43180 - Finding of Failure To Submit Section 110 State Implementation Plans for Interstate Transport for...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-07-20

... 12866. J. National Technology Transfer and Advancement Act Section 12(d) of the National Technology... Concerning Regulations That Significantly Affect Energy Supply, Distribution, or Use J. National Technology Transfer and Advancement Act K. Executive Order 12898: Federal Actions To Address Environmental Justice in...

78 FR 18849 - Disapproval of Implementation Plan Revisions; State of California; South Coast VMT Emissions...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-28

... significant regulatory action under Executive Order 12866. I. National Technology Transfer and Advancement Act Section 12 of the National Technology Transfer and Advancement Act (NTTAA) of 1995 requires Federal... business hours with the contact listed in the FOR FURTHER INFORMATION CONTACT section below. FOR FURTHER...

A Study of Korean EFL Learners' Apology Speech Acts: Strategy and Pragmatic Transfer Influenced by Sociolinguistic Variations.

ERIC Educational Resources Information Center

Yang, Tae-Kyoung

2002-01-01

Examines how apology speech act strategies frequently used in daily life are transferred in the framework of interlanguage pragmatics and sociolinguistics and how they are influenced by sociolinguistic variations such as social status, social distance, severity of offense, and formal or private relationships. (Author/VWL)

76 FR 44761 - Remittance Transfers

Federal Register 2010, 2011, 2012, 2013, 2014

2011-07-27

...) (interim final rule); 72 FR 7927 (Feb. 22, 2007) (final rule). Section 1073 of the Dodd-Frank Act added a new Section 919 to the EFTA, entitled ``Remittance Transfers.'' Public Law 111-203, Sec. 1073, 124.... 1693o-1. Paragraph (d) of Section 1073 of Dodd-Frank amended the FCU Act to specify that a remittance...

BOILING HEAT TRANSFER IN ZERO GRAVITY

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

Zara, E.A.

1964-01-01

The preliminary results of a research program to determine the effects of zero and near zero gravity on boiling heat transfer are presented. Zero gravity conditions were obtained on the ASD KC-135 zero gravity test aircraft, capable of providing 30-seconds of zero gravity. Results of the program to date indicate that nucleate (bubble) boiling heat transfer rates are not greatly affected by the absence of gravity forces. However, radical pressure increases were observed that will dictate special design considerations to space vehicle systems utilizing pool boiling processes, such as cryogenic or other fluid storage vessels where thermal input to themore » fluid is used for vessel pressurization. (auth)« less

Determination of lateral-stability derivatives and transfer-function coefficients from frequency-response data for lateral motions

NASA Technical Reports Server (NTRS)

Donegan, James J; Robinson, Samuel W , Jr; Gates, Ordway, B , jr

1955-01-01

A method is presented for determining the lateral-stability derivatives, transfer-function coefficients, and the modes for lateral motion from frequency-response data for a rigid aircraft. The method is based on the application of the vector technique to the equations of lateral motion, so that the three equations of lateral motion can be separated into six equations. The method of least squares is then applied to the data for each of these equations to yield the coefficients of the equations of lateral motion from which the lateral-stability derivatives and lateral transfer-function coefficients are computed. Two numerical examples are given to demonstrate the use of the method.

Rapid, optical measurement of the atmospheric pressure on a fast research aircraft using open-path TDLAS

NASA Astrophysics Data System (ADS)

Buchholz, B.; Afchine, A.; Ebert, V.

2014-05-01

Because of the high travel speed, the complex flow dynamics around an aircraft and the complex dependency of the fluid dynamics on numerous airborne parameters, it is quite difficult to obtain accurate pressure values at a specific instrument location of an aircraft's fuselage. Complex simulations using computational fluid dynamics (CFD) models can in theory computationally "transfer" pressure values from one location to another. However, for long flight patterns, this process is inconvenient and cumbersome. Furthermore these CFD transfer models require a local experimental validation, which is rarely available. In this paper, we describe an integrated approach for a spectroscopic, calibration-free, in-flight pressure determination in an open-path White cell on an aircraft fuselage using ambient, atmospheric water vapour as the "sensor species". The presented measurements are realized with the HAI (Hygrometer for Atmospheric Investigations) instrument, built for multiphase water detection via calibration-free TDLAS (tunable diode laser absorption spectroscopy). The pressure determination is based on raw data used for H2O concentration measurement, but with a different post-flight evaluation method, and can therefore be conducted at deferred time intervals on any desired flight track. The spectroscopic pressure is compared in-flight with the static ambient pressure of the aircraft avionic system and a micro-mechanical pressure sensor, located next to the open-path cell, over a pressure range from 150 hPa to 800 hPa, and a water vapour concentration range of more than three orders of magnitude. The correlation between the micro-mechanical pressure sensor measurements and the spectroscopic pressure measurements show an average deviation from linearity of only 0.14% and a small offset of 9.5 hPa. For the spectroscopic pressure evaluation we derive measurement uncertainties under laboratory conditions of 3.2% and 5.1% during in flight operation on the HALO airplane. Under certain flight conditions we quantified for the first time stalling-induced, dynamic pressure deviations of up to 30% (at 200 hPa) between the avionic sensor and the optical and mechanical pressure sensors integrated in HAI. Such severe local pressure deviations from the usually used avionic pressure are important to take into account for other airborne sensors employed on such fast flying platforms as the HALO aircraft.