Academic literature on the topic 'Aeronautical Board'
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Journal articles on the topic "Aeronautical Board"
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Lord Kings, Norton. "Extract from A Wrack Behind." Aeronautical Journal 103, no. 1022 (April 1999): 214. http://dx.doi.org/10.1017/s000192400009655x.
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In 1943, with the world still at war, a great discussion on the future of aeronautical education was held by the Royal Aeronautical Society. Not only would the war years, however many were still to come, demand more well-qualified aeronautical engineers, but the longed for peace years, with engineers turning swords into ploughshares, would want more. The discussion was in two parts. One took place on 25 June and the other on 23 July. Many of the leading figures in British aeronautics took part and in the chair on both occasions was Dr Roxbee Cox, a vice-president of the society. The discussion culminated in a resolution based on a proposal by Marcus Langley. That resolution and the discussion which led to it resulted in the recommendation by the Aeronautical Research Committee that a post-graduate college of aeronautical science should be established. This was followed by governmental action. Sir Stafford Cripps, then the minister responsible for aircraft production, set up a committee presided over by Sir Roy Fedden to make specific proposals, and the committee recommended in its 1944 report that such a college should be a new and independent establishment. In 1945 the government created the College of Aeronautics board of governors under the chairmanship of Air Chief Marshal Sir Edgar Ludlow-Hewitt to bring the college into existence and govern it. The first meeting of this board took place on 28 June 1945 and there were present: Sir Edgar Ludlow Hewitt, Dr W. Abbot, Mr Hugh Burroughs, Sir Roy Fedden, Mr J. Ferguson, Sir Harold Hartley, Sir William Hil-dred, Sir Melvill Jones, Dr E.B. Moullin, Mr J.D. North, Sir Frederick Handley Page, Mr E.F. Relf, Dr H. Roxbee Cox, Air Marshal Sir Ralph Sovley, Rear Admiral S.H. Troubridge and Mr W.E.P. Ward. Sir William Stanier, who had been appointed, was not present.
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Siabato, Willington, Javier Moya-Honduvilla, and Miguel Ángel Bernabé-Poveda. "Supporting Aeronautical Information Management (AIM) Through Geographic Information Technologies and Spatial Data Infrastructures (SDI)." International Journal of Applied Geospatial Research 7, no. 3 (July 2016): 1–37. http://dx.doi.org/10.4018/ijagr.2016070101.
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The way aeronautical information is managed and disseminated must be modernized. Current aeronautical information services (AIS) methods for storing, publishing, disseminating, querying, and updating the volume of data required for the effective management of air traffic control have become obsolete. This does not contribute to preventing airspace congestion, which turns into a limiting factor for economic growth and generates negative effects on the environment. Owing to this, some work plans for improving AIS and air traffic flow focus on data and services interoperability to allow an efficient and coordinated use and exchange of aeronautical information. Geographic information technologies (GIT) and spatial data infrastructures (SDI) are comprehensive technologies upon which any service that integrates geospatial information can rely. The authors are working on the assumption that the foundations and underlying technologies of GIT and SDI can be applied to support aeronautical data and services, considering that aeronautical information contains a large number of geospatial components. This article presents the design, development, and implementation of a Web-based system architecture to evolve and enhance the use and management of aeronautical information in any context, e.g., in aeronautical charts on board, in control towers, and in aeronautical information services. After conducting a study into the use of aeronautical information, it was found that users demand specific requirements regarding reliability, flexibility, customization, integration, standardization, and cost reduction. These issues are not being addressed with existing systems and methods. A system compliant with geographic standards (OGC, ISO) and aeronautical regulations (ICAO, EUROCONTROL) and supported by a scalable and distributed Web architecture is proposed. This proposal would solve the shortcomings identified in the study and provide aeronautical information management (AIM) with new methods and strategies. In order to seek aeronautical data and services interoperability, a comprehensive aeronautical metadata profile has been defined. This proposal facilitates the use, retrieval, updating, querying, and editing of aeronautical information, as well as its exchange between different private and public institutions. The tests and validations have shown that the proposal is achievable.
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Pereira and Fernandes. "Sandwich Panels Bond with Advanced Adhesive Films." Journal of Composites Science 3, no. 3 (August 1, 2019): 79. http://dx.doi.org/10.3390/jcs3030079.
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Sandwich structures present several advantages, being used in many industries such as the aeronautical industry. In this study, an automated laminating line is employed to manufacture sandwich panels for boards. This work focus on an innovative solution, employing an advanced adhesive film to increase the bonding strength of sandwich structures used for this application. This was used to bond ceramic steel sheets to honeycomb‐cored structures, creating an innovative solution for the board industry. Bending tests were carried to evaluate the performance of the new sandwich solutions and to compare it against a typical one available on the market.
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Guadagno, Liberata, Fabiana Foglia, Roberto Pantani, Maria Dolores Romero-Sanchez, Blanca Calderón, and Luigi Vertuccio. "Low-Voltage Icing Protection Film for Automotive and Aeronautical Industries." Nanomaterials 10, no. 7 (July 9, 2020): 1343. http://dx.doi.org/10.3390/nano10071343.
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High-performance heater films are here proposed. They manifest great applicative potentiality in the de-icing technology of aircraft and motor vehicles. The films are suitable to be integrated into composite structures for the de/anti-icing function, which can be activated if the need arises. The heating is based on the joule effect of the current flowing through the electrically conductive films. Voltage and current parameters have been set based on the generators’ capacities on-board an aircraft and a car, as well as on the energy consumption during the operating conditions and the autonomy in the time. Green processes have been employed through all preparative steps of the films, which are composed of expanded graphite (60% wt/wt) and polyvinyl alcohol (PVA) (40% wt/wt). The results reveal a very significant influence of the aspect ratio of the filler on the heating and de-icing performance and suggest how to enhance the de-icing efficiency saving energy and adapting the current on-board aircraft/car generators for de-icing operations.
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Jenab, Kouroush, Nikita Ottosen, and Saeid Moslehpour. "Application of scenario-driven hazard analysis in the solid rocket booster." International Journal of Engineering & Technology 5, no. 1 (January 7, 2016): 16. http://dx.doi.org/10.14419/ijet.v5i1.4673.
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Bibliographical Notes: Kouroush Jenab is a senior member of IEEE, received the B.Sc. degree from the IE Department at Isfahan University of Technology (1989), the M.Sc. degree from the IE Department at Tehran Polytechnic (1992), and the Ph.D. degree from the Department of Mechanical Engineering at the University of Ottawa (2005). He served as a senior engineer/manager in auto, and high-tech industries for 18 years. He joined the National Research Council Canada as a research officer where he participated in several international research projects. In 2006, he joined the Department of Mechanical and Industrial Engineering at Ryerson University, Toronto as assistant professor. Currently, Dr. Jenab is Faculty of the College of Aeronautics at Embry-riddle Aeronautical University, FL, USA. He has published over 110 papers in international scientific journals based on his experiences in industries.Nikita Ottosen is a current Systems Engineering graduate student at Embry-Riddle Aeronautical University. She received her undergraduate degree from ERAU in Aeronautics and is currently working as an Assistant Campus Director at the Crestview, FL campus. She gained valuable knowledge previously working for the Boeing Company and Seattle-Tacoma International Airport, known as The Port of Seattle, in Seattle, Washington. During her time at The Port of Seattle she worked alongside the Wildlife Management department to conduct a study on effective wildlife management strategies. Her study will become a part of a future Airport Cooperative Research Program (ACRP) publication, sponsored by the FAA’s Transportation Research Board of the National Academies.Saeid Moslehpour is a full professor and department chair in the Electrical and Computer Engineering Department in the College of Engineering, Technology, and Architecture at the University of Hartford. He holds Ph.D. (1993) from Iowa State University and Bachelor of Science (1989) and Master of Science (1990) degrees from University of Central Missouri. His research interests include failure analysis, logic design, CPLDs, FPGAs, Embedded electronic system testing and distance learning.
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Cannarile, F., M. Compare, P. Baraldi, G. Diodati, V. Quaranta, and E. Zio. "Elastic net multinomial logistic regression for fault diagnostics of on-board aeronautical systems." Aerospace Science and Technology 94 (November 2019): 105392. http://dx.doi.org/10.1016/j.ast.2019.105392.
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Page, Frederick. "William John Strang, C.B.E., F.R.Eng., F.R.Ae.S. 29 June 1921 – 14 September 1999." Biographical Memoirs of Fellows of the Royal Society 47 (January 2001): 443–51. http://dx.doi.org/10.1098/rsbm.2001.0026.
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Bill Strang was a dedicated aerospace engineer of great integrity and much respected by all who came into contact with him. He was Technical Director of the Commercial Aircraft Division of British Aerospace until he retired in 1983 to become Chairman of the Airworthiness Requirements Board. All his postgraduate career was spent in the British aerospace industry, mostly at Filton near Bristol, except for a brief spell in the Aeronautical Research Laboratory, Melbourne, Australia, from 1948 to 1951. Dr Strang made the biggest industrial contribution to the aerodynamic design of Concorde and in 1977 was elected a Fellow of The Royal Society as a result; he served on several of the Society's committees from 1977 until 1989. From 1983 until 1990 he was Chairman of the Civil Aviation Airworthiness Requirements Board. He was also a keen sailor and became a Coastal Skipper with The Island Cruising Club at Salcombe before qualifying for his Master's Ticket with the Royal Yachting Association. He loved the countryside and walking. He was awarded a C.B.E. in 1973 and in 1997 he was elected a Fellow of the Royal Academy of Engineering. The Royal Aeronautical Society awarded him the Silver Medal in 1971 and the Gold Medal in 1973. In his later years he suffered from a heart problem that was the cause of his death in 1999.
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Kolobanova, M. S., S. M. Klyushin, V. K. Kozlov, and T. N. Prokopenko. "COMPREHENSIVE APPROACH TO MODELING AND CONSTRUCTION OF FUNCTIONAL DEVICES BASED ON SPACEWIRE CONTROLLERS AND SPACEFIBRE CONTROLLERS OF MULTICOR SERIES." Issues of radio electronics, no. 8 (August 20, 2018): 124–32. http://dx.doi.org/10.21778/2218-5453-2018-8-124-132.
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Proposed is an effective integrated approach to the modelling of functional units (FU), on-board computers and embedded systems at the hardware development phase. It is applicable to enterprises with a complete production cycle of industrial systems, including on-board control and information processing devices, space and aeronautical systems and others. In the traditional approach, the driver and on-board software (BPO) are debugged and verified after the manufacture of the product or computer, which significantly increases the lead time for the finished product. The complex approach to modeling the hardware at the transaction level [1] using the SystemC library [2], encapsulating the work with the driver with SpaceWire and SpaceFibre controllers allows to speed up the development of FU and computers, as well as to detect a number of errors and limitations of the system being designed.
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Newman, S. "Shipborne Aviation: An Introduction." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 5 (May 1, 2005): 363–68. http://dx.doi.org/10.1243/095441005x30324.
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The evolution of air vehicles for use on board a ship spans a period of nearly 150 years. Starting with observation balloons in the American Civil War, the development has moved to the Joint Strike Fighter, an aircraft of immense technical sophistication and a potent weapon. The design requirements of both ship and aircraft spawn conflicts and the two technologies are now required to work in total unison. This paper discusses the evolution and how the various wars have shaped the most demanding of aeronautical disciplines.
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Yevseyev, Arkhip. "Environmental Engineering based Supervision System Design for Highway Construction." Pollution Engineering 51, no. 3 (October 26, 2020): 04–05. http://dx.doi.org/10.17762/pe.v51i3.61.
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Ecological building oversight assumes a significant part during parkway development. There are a great deal of key segments associated with ecological oversight, for example, how to improve the work successfully and productively. In light of distant detecting and Geographic Information System (GIS), this paper presents a plan for natural building oversight framework as far as ecological observing innovation, incorporated administration and public association. The primary segments in the framework incorporate automated aeronautical vehicle based condition screen and condition the board information base and condition observing subsystem.
Dissertations / Theses on the topic "Aeronautical Board"
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Monekosso, Ndedi. "On-board reasoning for an autonomous spacecraft." Thesis, University of Surrey, 1999. http://epubs.surrey.ac.uk/844249/.
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This thesis describes a framework for the high level control of an autonomous unmanned spacecraft. Greater autonomy than currently exist is required for unmanned spacecraft to enable missions to distant planets and bodies. One reason for this is that the signal return time is too long to accommodate real-time control from the ground. A second reason is that spacecraft travelling to bodies where little is known of the environment (e.g. asteroids) must have the capability to respond to unplanned events. In addition, autonomy can help reduce mission operations costs, a very important factor in the current climate where more is expected from space missions at a lower cost. The thesis proposes a novel architecture for an autonomous unmanned spacecraft, based on Distributed Artificial Intelligence (DAI), and more specifically based on the multi-agent paradigm. The proposed model for spacecraft control is decentralised. In this architecture, the spacecraft is made up of agents; the traditional ground-based controller is one agent. The spacecraft is goal-driven; it receives high level goals from the ground. The planning and scheduling of activities to achieve these goals is carried out on-board the spacecraft. The spacecraft is also event-driven; it reacts to events that occur on-board the spacecraft as well as in the environment. A DAI architecture requires a co-ordination mechanism, and a communication structure. Also, distributed versions of algorithms must be provided. In this thesis, co-ordination with and without explicit communication and distributed scheduling were investigated, and a framework proposed for both these issues. An autonomous spacecraft must have inference capability for on-board decision making to enable it to respond to unplanned events. Probabilistic reasoning in the form of Bayesian networks was used to provide the spacecraft with the capability for on-board decision making. Situations may arise where the spacecraft must make decisions with uncertain or incomplete information. The issue of decision making with uncertain or incomplete knowledge (e.g. co-ordination without explicit communication) was investigated using domain specific scenarios. Spacecraft resources are typically very limited in capacity. On-board resource management should result in more efficient use of resources. A framework for an on-board resource manager was defined and implemented using reinforcement learning. A distributed version of the scheduling algorithm using reinforcement learning was developed. Thus, this thesis describes and investigates an architectural framework for a multi-agent approach to spacecraft control.
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Wagner, Elaine Ann. "On-board automatic aid and advisory for pilots of control-impaired aircraft." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/35940.
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Benson, Hewett A. O. "Apparent-mass and on-board circulation of Joukowski airfoils and cascades in severe unsteady motion." Thesis, Massachusetts Institute of Technology, 1989. http://hdl.handle.net/1721.1/14523.
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Lohmeyer, Whitney Quinne. "Space radiation environment impacts on high power amplifiers and solar cells on-board geostationary communications satellites." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/98682.
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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.Cataloged from PDF version of thesis.
Includes bibliographical references (pages 273-292).
Communications satellite operators maintain archives of component telemetry to monitor system function. Operators generally do not typically use the telemetry data for scientific analysis of the space radiation environment effects on component anomalies or performance. We partnered with four geostationary (GEO) operators, acquired >1 million hours of telemetry, and combined these data with space weather observations to investigate relationships between space weather and hardware performance. We focused on the effects of space weather on two component types: solar cells and high power amplifiers. For solar cells, by augmenting >20 years of GEO telemetry with separate GEO space weather measurements, we calculated both on-orbit degradation of Si and GaAs solar cells in an annual average sense, and also quantified the degradation of cells during severe solar proton events (SPEs) of 10 MeV protons > 10,000 pfu. A functional relationship between the amount of degradation and proton fluence is also considered. We used the calculated degradation to evaluate several combinations of space weather environment models with solar cell degradation models and found that predicted performance is within 1% of the observed degradation. These models had not previously been validated using multiple on-orbit GEO datasets. We did not find a model pairing that consistently outperformed the others over all of the datasets. For high power amplifiers, through the use of statistical analysis, simulations, and electron beam experiments we conducted a root-cause analysis of solid state power amplifier (SSPA) anomalies on-board eight GEO satellites. From the statistical analysis, we identified that the occurrence of anomalies was not random with respect to the space weather environment, but that there appeared to be a relationship to high-energy electron fluence for periods of time between 10 - 21 days before the anomalies. From the simulations and electron beam lab tests, we demonstrated that internal charging occurs in the amplifier chain, potentially identifying a cause for the observed anomalies. We substantiated an approach toward understanding space weather effects on space components by obtaining and using long-duration archives of standard commercial telemetry for scientific analysis. The analysis of large telemetry data sets of similar components over long periods of time improves our ability to assess the role of different types of space weather events in causing anomalies and helps to validate models. The findings in this work that relate deep dielectric charging to component anomalies and solar proton events to solar cell degradation make use of only a small fraction of the potentially available commercial geostationary satellite telemetry. Expansion of this work would provide additional insights on the role of space weather to the science community and to the satellite design and operator community.
by Whitney Quinne Lohmeyer.
Ph. D.
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Bilton, Amy M. (Amy Marlou). "Fusion of remote vision and on-board acceleration data for the vibration estimation of large space structures." Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/35580.
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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.Includes bibliographical references (leaves 81-84).
Future space structures such as solar power stations and telescopes are expected to be very large. These structures will require on-orbit construction. Due to the risks and costs of human extravehicular work, teams of robots will be essential for the on-orbit assembly of the large space structures. There are a number of technical challenges presented by such robotic construction. The structures will need to be made of lightweight materials and will be very flexible. Autonomous robots will require information about the vibrations of the flexible structures and their dynamic parameters in order to perform the construction efficiently. Often models of the structures are imperfect, therefore the magnitude of the vibrations of the structure must be estimated on-orbit. This thesis presents a method for estimating the shape and dynamic parameters of a vibrating large space structure. This technique is a cooperative sensing approach using remote free-flying robot observers equipped with vision sensors and structure-mounted accelerometers. This approach exploits the complementary nature of the two types of sensors.
(cont.) Vision sensors are able to measure structure deflections at a high spatial frequency but are bandwidth limited. Accelerometers are able to make measurements at high temporal frequency, but are sparsely located on the structure. The fused estimation occurs in three steps. First, the vision data is condensed in a modal decomposition that results in coarse estimates of modal coefficients. In the second step, the coarse estimates of the modal coefficients obtained from vision data are fused with the accelerometer measurements in a multi-rate nonlinear Kalman filter, resulting in a refined estimate of the modal coefficients and dynamic properties of the structure. In the final step, the estimated modal coefficients are combined with the mode shapes to provide a shape estimate of the entire structure. Simulation and experimental results demonstrate that the performance of this fused estimation approach is superior to the performance achieved when using only a single type of sensor.
by Amy M. Bilton.
S.M.
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Suwatthikul, Jittiwut. "A framework and methods for on-board network level fault diagnostics in automobiles." Thesis, University of Warwick, 2008. http://wrap.warwick.ac.uk/4102/.
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A significant number of electronic control units (ECUs) are nowadays networked in automotive vehicles to help achieve advanced vehicle control and eliminate bulky electrical wiring. This, however, inevitably leads to increased complexity in vehicle fault diagnostics. Traditional off-board fault diagnostics and repair at service centres, by using only diagnostic trouble codes logged by conventional onboard diagnostics, can become unwieldy especially when dealing with intermittent faults in complex networked electronic systems. This can result in inaccurate and time consuming diagnostics due to lack of real-time fault information of the interaction among ECUs in the network-wide perspective. This thesis proposes a new framework for on-board knowledge-based diagnostics focusing on network level faults, and presents an implementation of a real-time in-vehicle network diagnostic system, using case-based reasoning. A newly developed fault detection technique and the results from several practical experiments with the diagnostic system using a network simulation tool, a hardware- in-the- loop simulator, a disturbance simulator, simulated ECUs and real ECUs networked on a test rig are also presented. The results show that the new vehicle diagnostics scheme, based on the proposed new framework, can provide more real-time network level diagnostic data, and more detailed and self-explanatory diagnostic outcomes. This new system can provide increased diagnostic capability when compared with conventional diagnostic methods in terms of detecting message communication faults. In particular, the underlying incipient network problems that are ignored by the conventional on-board diagnostics are picked up for thorough fault diagnostics and prognostics which can be carried out by a whole-vehicle fault management system, contributing to the further development of intelligent and fault-tolerant vehicles.
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Leber, Douglas Eric. "A systems analysis of the impact of navigation instrumentation on-board a Mars rover, based on a covariance analysis of navigation performance." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/42544.
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Letarte, Lyne. "Régime juridique des provisions de bord en droit aérien = Legal status of aircraft stores." Thesis, McGill University, 1987. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=63834.
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Lamy, Christophe A. "The technical boards of aircraft accident investigation in the United States of America & France /." Thesis, McGill University, 2000. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=33065.
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In conformity with the principles laid down in article 26 of the Chicago Convention and its Annex 13 concerning technical aircraft accident investigations, the United States and France respectively set up and developed their own investigation Boards, the NTSB and the BEA, which may be different by their organization and functioning but both aim at the same objective: the promotion of Air Safety.To fulfil their complex mission in the best possible conditions and despite eventual pecuniary constraints, the pressure of the media, or the occasional tensions which may arise in case of concomitance with other investigations, the NTSB and the BEA rely on the renowned professionalism and high technical skills of their employees as well as on the participation in the investigation of members of the aeronautical industry who bring their expertise and contribute to the improvement of air safety.
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Cintosun, Esen. "Analyses expérimentale, numérique et optimisation de traitements acoustiques multicouches à base de matériaux viscoélastiques et poreux pour réduire le bruit à bord de l’avion." Thèse, Université de Sherbrooke, 2011. http://hdl.handle.net/11143/8769.
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Résumé : Ce projet de recherche est composé de trois parties principales : la première comprend l'analyse expérimentale et la simulation des performances vibratoires de matériaux avec amortissement viscoélastique, en tant que traitements acoustiques appliqués aux structures du fuselage d'un avion. La deuxième partie comprend l'analyse expérimentale et le calcul de la performance acoustique de ces matériaux amortissant en comparaison avec l'effet d'une masse équivalente. Enfin, la troisième partie est une étude paramétrique sur les effets de localisation, de la densité et de la taille d'un traitement massique. Les systèmes d'isolation phoniques typiquement employés dans la construction des fuselages d'avions sont composés de matériaux poreux, avec ou sans des matériaux amortissant (matériaux viscoélastiques). La performance et donc l'utilité de ces traitements amortissant, en comparaison avec une couche de masse équivalente, reste une question largement ouverte. Dans ce travail on a comparé numériquement et expérimentalement les performances acoustiques d'un traitement amortissant avec celui d'une masse équivalente tous les deux incorporées dans le traitement phonique et ceci pour plusieurs types d'excitations. Deux structures représentant des fuselages, une en aluminium et la seconde en carbone composite, ont été sélectionnées pour cette étude ainsi que deux matériaux poreux couramment utilisés en aéronautique : une laine en fibre de verre et une mousse à cellules ouvertes. Deux types d'excitations ont été étudiés numériquement et expérimentalement. La première est une excitation acoustique (champ diffus) et la seconde mécanique (forces ponctuelles). Une troisième, excitation par couche limite turbulente a été étudié numériquement. Dans tous les cas, la perte par insertion du traitement acoustique est utilisée comme indicateur principal de la performance. D'autres indicateurs comme le coefficient d'absorption, le coefficient de perte par amortissement et la vitesse quadratique moyenne sont aussi utilisés pour mieux cerner et expliquer l'effet du traitement. Il a été démontré que l'utilisation d'une couche de masse équivalente à un traitement viscoélastique conduit systématiquement à la meilleure performance acoustique et ceci pour les trois types d'excitations étudiées. En particulier, dans le cas classique où le traitement amortissant est appliqué directement au fuselage. Dans ce dernier cas, les effets de doubles parois créés par la couche massique, positionnée judicieusement loin du fuselage, augmentent la performance en moyennes et hautes fréquences. Les performances en basses fréquences restent limitées par la fréquence de résonance double parois. Et même l'effet amortissant des traitements viscoélastiques, théoriquement visible aux résonances et coïncidences du système, se trouve limité par l'amortissement ajouté par le montage et le traitement absorbants. Cependant, l'efficacité de la couche massique est compromise par les difficultés d'installations et en particulier pour les fibreux. Les résultats de cette thèse restent toutefois limités par notre choix de structures et de traitements étudiés.Abstract : The project is made up of three main parts. The first part involves a comprehensive experimental and numerical analysis of viscoelastic damping materials as acoustic treatments to aircraft fuselage structures. The second part involves numerical and experimental acoustic comparison of viscoelastic damping material to equivalent mass. And the third part is a parametric study of equivalent mass for the effects of mass location, density and size. The goal of the project is to identify the vibroacoustic effect of viscoelastic material damping of fuselage skin, and develop possible alternatives to damping. The insulation systems (typically used on aircraft) that are made up of porous materials with or without viscoelastic damping material or equivalent mass were called sound packages throughout this document. The viscoelastic damping material and equivalent mass both incorporated in sound packages were acoustically compared. Fiberglass and open cell foam were used as porous materials. The viscoelastic damping material used in this study is constraining layer damping and abbreviated as CLD. The equivalent mass was an impervious screen. Both representative Aluminum and carbon composite fuselage skin structures were treated with sound packages as part of the comparison. The vibroacoustic performance indicators were used to characterize the sound packages. The indicators were airborne insertion loss (ABIL), structure borne insertion loss (SBIL), turbulent boundary layer insertion loss (TBLIL), average quadratic velocity (AQV), damping loss factor (DLF), absorption coefficient, and radiation efficiency. Diffuse field acoustic excitation was used to obtain the vibroacoustic indicators of ABIL and absorption coefficient. Mechanical excitation was used to obtain SBIL, AQV, DLF, absorption coefficient, and radiation efficiency. Turbulent boundary layer excitation was modeled to obtain TBLIL. The numerical methods of finite element method (FEM) and transfer matrix method (TMM) were used to calculate all of the above vibroacoustic performance indicators. Experimentally, ABIL, SBIL, AQV, DLF and radiation efficiency were measured. Experimental modal analysis was also performed to characterize representative Aluminum and carbon composite fuselage skin structures. Based on the numerical analysis, equivalent mass generated a double or multiple (in case of double wall layer configuration) wall effect and hence became an effective acoustic insulator as part of sound packages at mid to high frequencies. Even at coincidence frequencies (in case of the representative carbon composite fuselage skin), the equivalent mass layer was more effective than viscoelastic damping material. However, the drawback was the occurrence of the double wall resonance at lower frequencies which compromised the effectiveness. Nevertheless, the parametric study of equivalent mass revealed that equivalent mass is superior to viscoelastic damping material at reduced weight in term of vibroacoustic performance indicators of overall ABIL/SBIL/TBLIL in the frequency range of 100 to 6300 Hz and mean ABIL/SBIL/TBLIL in SIL (octave lk, 2k, 4k Hz) frequency range.
Books on the topic "Aeronautical Board"
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Gozon, Felipe L. The Civil Aeronautics Board: Powers, procedures, and regulations. Manila, Philippines: Published & distributed by Rex Book Store, 1993.
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First among equals: The selection of NASA space science experiments. Washington, DC: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.
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Payne, Richard. Stuck on the drawing board: Unbuilt British commercial aircraft since 1945. Stroud [England]: Tempus, 2004.
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Canada, Canada Government of. Final report of the Board of Inquiry into Air Canada Boeing 767 C-GAUN accident - Gimli, Manitoba July 23, 1983. Ottawa: Government of Canada, 1985.
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FEDERAL AVIATION ADMINISTRATION. Guide specification for lifts used to board airline passengers with mobility impairments. Washington, D.C. (800 Independence Ave., S.W. Washington 20591): U.S. Dept. of Transportation, Federal Aviation Administration, 1996.
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GOVERNMENT, US. Compilation of selected aviation laws: Federal Aviation Act of 1958, Civil Aeronautics Board Sunset Act of 1984, Employee Protection Provisions ... Washington: U.S. G.P.O., 1993.
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Board, Canada Treasury. Agreement between the Treasury Board and the Canadian Union of Professional and Technical Employees. Ottawa, Ont: Treasury Board of Canada Secretariat, 1988.
Find full textBook chapters on the topic "Aeronautical Board"
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Siabato, Willington, Javier Moya-Honduvilla, and Miguel Ángel Bernabé-Poveda. "Supporting Aeronautical Information Management (AIM) Through Geographic Information Technologies and Spatial Data Infrastructures (SDI)." In Environmental Information Systems, 306–48. IGI Global, 2019. http://dx.doi.org/10.4018/978-1-5225-7033-2.ch015.
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The way aeronautical information is managed and disseminated must be modernized. Current aeronautical information services (AIS) methods for storing, publishing, disseminating, querying, and updating the volume of data required for the effective management of air traffic control have become obsolete. This does not contribute to preventing airspace congestion, which turns into a limiting factor for economic growth and generates negative effects on the environment. Owing to this, some work plans for improving AIS and air traffic flow focus on data and services interoperability to allow an efficient and coordinated use and exchange of aeronautical information. Geographic information technologies (GIT) and spatial data infrastructures (SDI) are comprehensive technologies upon which any service that integrates geospatial information can rely. The authors are working on the assumption that the foundations and underlying technologies of GIT and SDI can be applied to support aeronautical data and services, considering that aeronautical information contains a large number of geospatial components. This article presents the design, development, and implementation of a Web-based system architecture to evolve and enhance the use and management of aeronautical information in any context, e.g., in aeronautical charts on board, in control towers, and in aeronautical information services. After conducting a study into the use of aeronautical information, it was found that users demand specific requirements regarding reliability, flexibility, customization, integration, standardization, and cost reduction. These issues are not being addressed with existing systems and methods. A system compliant with geographic standards (OGC, ISO) and aeronautical regulations (ICAO, EUROCONTROL) and supported by a scalable and distributed Web architecture is proposed. This proposal would solve the shortcomings identified in the study and provide aeronautical information management (AIM) with new methods and strategies. In order to seek aeronautical data and services interoperability, a comprehensive aeronautical metadata profile has been defined. This proposal facilitates the use, retrieval, updating, querying, and editing of aeronautical information, as well as its exchange between different private and public institutions. The tests and validations have shown that the proposal is achievable.
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Nuñez, Miguel David Ruiz-Cabello, Sergio Fernández Romero, Marc Pous, Enrique Pascual Gil, Luis M. Diaz Angulo, David Poyatos Martínez, Mireya Fernández Chimeno, et al. "Numerical Assessment in Aeronautics for Electromagnetic Environmental Effects." In Electromagnetic Compatibility for Space Systems Design, 153–210. IGI Global, 2018. http://dx.doi.org/10.4018/978-1-5225-5415-8.ch005.
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Electrical and electronic systems on board air vehicles are susceptible to electromagnetic interference (EMI). This has made the topic of electromagnetic compatibility (EMC), a major concern for aircraft safety. The use of composite materials worsens this situation, for their poor shielding and low conductive capabilities. Some of the main experimental E3 certification scenarios used in aeronautics are revisited in this chapter. Guidelines to achieve simple, yet accurate, numerical models of them are provided, with appropriate tradeoffs between computational simplicity and accuracy. The numerical method, endowed with extended capabilities, has been chosen for this task for its ability and efficiency to deal with complex problems of arbitrary materials. The feature selective validation (FSV) IEEE standard procedure, commonly used to quantify the comparison of data in electromagnetic problems, is also revisited. The simulation of three different air vehicles in several certification scenarios is finally described and the numerical results compared to experimental data.
Conference papers on the topic "Aeronautical Board"
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Haynes, Comas. "Preliminary Aeronautical Design Considerations of “High NOS” SOFC/GT Hybrids." In ASME 2004 2nd International Conference on Fuel Cell Science, Engineering and Technology. ASMEDC, 2004. http://dx.doi.org/10.1115/fuelcell2004-2533.
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Aerovehicular application of solid oxide fuel cell/gas turbine (SOFC/GT) auxiliary power units (APUs) is a promising concept that may significantly aid the advent of next-generation, environmentally benign aircrafts. The hybrid concept may not only be a novelty, but a necessity, for viably realizing the benefits of fuel cells on-board. A generic design concept is proposed wherein the strategic integration of the cell stack with a bottoming turbine for APU duty, along with regenerative fuel recirculation, could be used to foster larger reactant “numbers-of-stoichs” (NOS) levels within the stack. This may engender larger gravimetric power densities, capacitance for load following and thermal reliability. Fuel utilization/NOS may then be a significant design degree-of-freedom to include within the design process.
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Harries, Brian, Brandon Smith, Sean Carter, Darris White, and Marc Compere. "Control System Design and Optimization Using LabVIEW for a Plug in Hybrid Electric Vehicle as Part of EcoCar: The NeXt Competition." In ASME 2011 International Mechanical Engineering Congress and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/imece2011-65474.
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Embry Riddle Aeronautical University is part of EcoCar: The NeXt Challenge, an advanced vehicle competition run by Argonne National Labs and sponsored by General Motors and the Department of Energy. The competition tasks 16 schools around the country with designing and implementing the most efficient vehicle architecture. As part of the EcoCar Challenge, Embry Riddle Aeronautical University is working on developing a controls strategy for a Plug in Hybrid Electric Vehicle. The control system is designed to optimize efficiency and consumer acceptability by allowing the EcoEagles to control each of the cars sub-systems. Control is done using CAN bus communication that utilizes National Instruments (NI) single board reconfigurable input / output (sbRIO) real time hardware. The EcoEagles powertrain architecture includes GM’s two-mode hybrid electric transmission which contains two 55kW electric motors, a 1.3 liter turbo diesel engine running on B20 biodiesel, and a 12.8 kWh lithium-ion battery pack produced by A123 Systems. Each component has a control module that interfaces directly with the subsystems and hardware on the vehicle. These controllers are: the Traction Power Inverter Module (TPIM), the Engine Control Module (ECM), and the Battery Pack Control Module (BPCM). Vehicle control and communication between these modules is managed by the EcoEagles, two controllers called the Supervisory Control Unit (SCU) and the Gateway (GW). The purpose of the gateway is to control the flow of CAN communication between modules and to isolate the ECM and BPCM from the vehicle to avoid data interference. Communication is done on two separate CAN buses, the Power Train Expansion Bus (PTEB), and the High Speed Bus (HS). The controls diagram can be seen in Figure 1. The paper will go into detail on shift strategy and engine operation where optimization was used to maintain efficient operation of the engine. The paper will also describe the control strategy that was developed using coupled LabVIEW Statecharts [1] with CAN messaging inputs from all of the control modules in order to maintain safe efficient operation.
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Loh, Kenneth J., and Jerome P. Lynch. "Design and Validation of Carbon Nanotube Thin Film Wireless Sensors for pH and Corrosion Monitoring." In ASME 2008 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2008. http://dx.doi.org/10.1115/smasis2008-569.
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Corrosion damage in civil, aeronautical, and mechanical systems poses significant risks to users and occupants while simultaneously burdening owners with costly repairs and maintenance. Although many different sensing technologies are available to monitor corrosion processes, many cannot be easily implemented in field environments due to requiring expensive data acquisition systems and their destructive and intrusive measurement strategies. In this study, a novel layer-by-layer assembled carbon nanotube and poly(aniline)-based nanocomposite pH sensor is developed for monitoring corrosion of metallic and reinforced concrete structures. First, the electrochemical response of the proposed nanocomposite pH sensor is characterized using time-domain two-point resistance probing measurements to validate its resistance change to different pH buffer solutions (1 to 13). Frequency-domain electrical impedance spectroscopic studies and equivalent circuit analyses confirm changes in film resistance to pH. Upon sensor characterization, these nanocomposites are directly deposited onto printed circuit board coil antennas to realize a miniature passive wireless sensor capable of being embedded within structural materials. Preliminary wireless pH sensing results are presented to demonstrate that the wireless sensor’s bandwidth decreases at 3.9 kHz-pH−1 with increasing pH.
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El Abbazi, Adil, Anas Jaber, Vincent Fontaine, and Christian Marot. "Electromagnetic simulation to predict EMC immunity behavior of an aeronautic board." In 2014 International Symposium on Electromagnetic Compatibility - EMC EUROPE. IEEE, 2014. http://dx.doi.org/10.1109/emceurope.2014.6931073.
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Bruckner, R. J., and C. DellaCorte. "Gas Foil Journal Bearing Power Loss at High Ambient Pressure." In World Tribology Congress III. ASMEDC, 2005. http://dx.doi.org/10.1115/wtc2005-63543.
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The National Aeronautics and Space Administration’s (NASA) Exploration Initiative requires the reliable availability of electrical power, on the order of hundreds of kilowatts, for operating spacecraft electric ion engines, on-board instruments, and communications. Foil gas bearing performance in Helium-Xenon (He-Xe) gas mixtures at high ambient pressures is a critical issue in the design of these power conversion systems. The work describe herein is a combined experimental and analytic approach to predicting bearing power loss at these conditions. A high pressure test chamber is used to test generation III foil journal bearings up to 47 atmospheres (∼700 psig). Data is then calibrated to classic Taylor-Couette flow to determine an appropriate power loss model for these bearings.
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Garcia, Gregory, Ward D. Rummel, Francisco Gonzalez, and Lawrence H. Strouse. "Quantitative Nondestructive Evaluation of Railroad Tank Cars." In 2011 Joint Rail Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/jrc2011-56019.
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A rulemaking issued by the Department of Transportation (DOT) revises Hazardous Materials Regulations (HMR) to replace the hydrostatic pressure test with appropriate nondestructive evaluation (NDE) methods. The rule change is contained in Federal Register 49 Code of Federal Regulations (CFR) Part 180.509, “Requirements for inspection and test of specification tank cars,” paragraph (e) “Structural integrity inspection tests” [1]. The CFR authorizes liquid penetrant (PT), magnetic particle (MT), radiography (RT), ultrasonic (UT), and optically aided visual testing (VT) as allowable NDE methods for structural integrity inspections and tests. Other NDE methods may be allowed under special exemption issued by the Federal Railroad Administration (FRA) Office of Safety. Also included under the requirements of 49 CFR Part 179.7 is the need to qualify not only NDE personnel, but the procedures used to perform NDE reliably. In order to be effective, federal regulations require that the NDE methods have a proven sensitivity and reliability for finding the type and size of flaws likely to cause a tank car failure. In the early 1970s, an internationally accepted quantitative approach that assesses the probability of detection (POD) was developed for the National Aeronautics and Space Association (NASA) and was published in NASA CR-2369, February 1974 [2]. Transportation Technology Center, Inc. (TTCI), under contract with the FRA, and along with industry participation, uses the NASA approach to determine the POD for various NDE methods used in the inspection of railroad tank car circumferential butt welds (girth seam welds), fillet welds, and leak test samples. The emergence of a damage tolerance approach to determine inspection intervals for an engineered structure — in this case a railroad tank car — requires the quantification of the detectable flaw size for the NDE methods used during inspection. Damage tolerance techniques have initiated an evolution in NDE understanding, methods, and requirements. National Transportation Safety Board safety recommendations R-92-21 through R-92-24 address the suggested process of performing reliable inspection of railroad tank cars based on a damage tolerance approach [3]. NDE quantification using the POD approach is a key measure of NDE effectiveness and is integral to damage tolerance requirements. TTCI, working with the FRA, Railroad Tank Car Industry and D&W Enterprises (A NDE consulting company providing expertise in the area of NDE POD), has developed baseline POD curves for the allowed NDE methods. Initial evaluations were performed on the inspection of tank car circumferential butt welds. Subsequent efforts focused on butt welds, longitudinal fillet welds and leak test samples requiring inspection under the CFR. This paper reports quantitative results obtained during this research effort that address system safety and risk analysis during handling and transportation of railroad tank cars carrying hazardous materials.