Journal articles on the topic 'New Zealand electric aircraft'
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1
Fahey, Morgan. "Aircraft Crash Management in Australia and New Zealand." Journal of the World Association for Emergency and Disaster Medicine 1, no. 2 (1985): 139–41. http://dx.doi.org/10.1017/s1049023x00065298.
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In the history of aviation there has never been a period when so much effort has been demonstrated to improve the safety standards of international and national airports. This has come about through the knowledge that aircraft crashes in recent years at some airports have been mismanaged because of bad or non-existent planning for such a disaster, and by poor emergency medical response.We share today a faith in the safety of the aircraft. We share, too, the awareness that more people have survived aircraft crashes than have perished, and that if there are survivors on board, in most cases there will be more survivors than dead (1).The encouragement to improve airport safety and crash management has come largely from the International Civil Aviation Organization (ICAO); from the Club of Mainz Association, who in 1979 set up a consultant committee to investigate and improve international airports; from the Flight Safety Foundation and from the US Airline Pilots Association. All these organizations have rightly questioned the quality of existing emergency medical response to an aircraft crash, and have offered expert advice to improve disaster preparedness and management. This article will report our response to this challenge, particularly in New Zealand, but will also concern our neighboring continent of Australia.New Zealand, set in the Pacific Ocean with its two long islands, has international flight contacts through its three major airports with North America, South East Asia, Japan and the South West Pacific. It has its own national aviation hazards of mountain chains, difficult landing approaches from the sea, made more hazardous with strong winds which are a feature of our capital city airport. Despite this, the safety record of New Zealand airports is extremely high.
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Henderson, Isaac Levi. "Reconciling Registration Policies for Unmanned Aircraft with Unmanned Aircraft Ownership Characteristics." Drones 7, no. 1 (January 16, 2023): 63. http://dx.doi.org/10.3390/drones7010063.
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Registration of unmanned aircraft is a common policy around the world and forms part of the International Civil Aviation Organisation’s model regulations for unmanned aircraft. This study conducts a review of the various registration policies that have been implemented amongst advanced economies to find commonalities and differences. New Zealand is then used as a case study. The country does not currently have registration of unmanned aircraft; however, their Ministry of Transport has put forward the idea of implementing a registration scheme. As part of this case study, the ownership characteristics of 919 New Zealand unmanned aircraft users were collected using an online survey. The results highlight that personally owned aircraft tend to only be used by their owner, with the number of users being lower than the number of aircraft. For organisationally owned aircraft, there are multiple users per aircraft; however, these users tend to only be employees of the organisation. These findings suggest that for New Zealand, the best way to implement a registration scheme would be to register users and organisations rather than individual aircraft. While specific to New Zealand, these findings also prompt the need for future research worldwide to see whether registration schemes reconcile with ownership data.
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Thirukumaran, Sanmugasundaram, Paul Ratnamahilan Polycarp Hoole, Harikrishnan Ramiah, Jeevan Kanesan, Kandasamy Pirapaharan, and Samuel Ratnajeevan Herbert Hoole. "A new electric dipole model for lightning-aircraft electrodynamics." COMPEL: The International Journal for Computation and Mathematics in Electrical and Electronic Engineering 33, no. 1/2 (December 20, 2013): 540–55. http://dx.doi.org/10.1108/compel-12-2012-0385.
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Purpose – As commercial and military aircraft continue to be subject to direct lightning flashes, there is a great need to characterize correctly the electrical currents and electric potential fluctuations on an aircraft to determine alternative design approaches to minimizing the severity of the lightning-aircraft dynamics. Moreover, with the increased severity of thunderstorms due to global warming, the need arises even more to predict and quantify electrical characteristics of the lightning-aircraft electrodynamics, which is normally not measurable, using a reliable electric model of the aircraft. Such a model is advanced here. The paper aims to discuss these issues. Design/methodology/approach – The case considered in this paper is that of an aircraft directly attached to an earth flash lightning channel. The paper develops a new approach to modelling the aircraft using electric dipoles. The model has the power to represent sharp edges such as wings, tail ends and radome for any aircraft with different dimensions by using a number of different sized dipoles. The distributed transmission line model (TLM) of the lightning return stroke incorporating the distributed aircraft model is used to determine aircraft electrical elements and finally the electric current induced on the aircraft body due to lightning's interaction with the aircraft. The model is validated by the waveform method and experimental results. Findings – The dipole model proposed is a very powerful tool for minute representation of the different shapes of aircraft frame and to determine the best geometrical shape and fuselage material to reduce electric stress. This charge simulation method costs less computer storage and faster computing time. Originality/value – The paper for the first time presents a computer-based simulation tool that allows scientists and engineers to study the dynamics of voltage and current along the aircraft surface when the aircraft is attached to a cloud to ground lightning channel.
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Prapotnik Brdnik, Anita, Rok Kamnik, Maršenka Marksel, and Stanislav Božičnik. "Market and Technological Perspectives for the New Generation of Regional Passenger Aircraft." Energies 12, no. 10 (May 16, 2019): 1864. http://dx.doi.org/10.3390/en12101864.
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This article describes the extent to which hybrid aircraft and all-electric aircraft can present a solution for reducing HC, CO, and NO x emissions and noise in the vicinity of airports, in the category of regional passenger aircraft. The goal of the article is to identify, basing on aircraft technical characteristics and market demands, in which sectors of air transport can all-electric or hybrid aircraft be most feasibly introduced. Firstly, a simple theoretical model based on a connection between the aircraft mass and aircraft energy consumption is used to calculate basic technical characteristics and limitations of hybrid and all-electric aircraft. Second, market demands for regional aircraft are presented and discussed, with the intention of recognising the possibilities of replacing conventional aircraft with all-electric and hybrid aircraft models in regional air transport in the near future. Third, quantity of HC, CO, and NO x, CO gas emissions of regional aircraft in Europe was calculated to recognise the possible reduction of gas emissions if hybrid and all-electric aircraft would be implemented.
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Da, Xingya, Huairong Shen, and Lei Hong. "New Electric Field Computation Method for Aircraft." Journal of Aircraft 46, no. 2 (March 2009): 557–61. http://dx.doi.org/10.2514/1.38699.
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Gedye, Nathan. "Use of Aircraft Accident Investigation Evidence in New Zealand." Air and Space Law 25, Issue 4/5 (September 1, 2000): 159–65. http://dx.doi.org/10.54648/276692.
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Walton, Claire Natalie, and Isaac Levi Henderson. "Safety Occurrence Reporting amongst New Zealand Uncrewed Aircraft Users." Eng 4, no. 1 (January 12, 2023): 236–58. http://dx.doi.org/10.3390/eng4010014.
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Safety reporting has long been recognised as critical to reducing safety occurrences by identifying issues early enough that they can be remedied before an adverse outcome. This study examines safety occurrence reporting amongst a sample of 92 New Zealand civilian uncrewed aircraft users. An online survey was created to obtain the types of occurrences that these users have had, how (if at all) these are reported, and why participants did or did not report using particular systems. This study focussed on seven types of occurrences that have been highlighted by the Civil Aviation Authority of New Zealand as being reportable using a CA005RPAS form, the template for reporting to the authority for uncrewed aircraft occurrences. The number of each type of occurrence was recorded, as well as what percentage of occurrences were reported using a CA005RPAS form, an internal reporting system, or were non-reported. Qualitative questions were used to understand why participants did or did not report using particular systems. Categorical and numerical data were analysed using Chi-Squared Tests of Independence, Kruskal–Wallis H Tests, and Mann–Whitney U Tests. Qualitative data were analysed using thematic analysis. The findings reveal that 85.72% of reportable safety occurrences went unreported by pilots, with only 2.74% of occurrences being self-reported by pilots using a CA005RPAS form. The biggest reason for non-reporting was that the user did not perceive the occurrence as serious enough, with not being aware of reporting systems and not being legally required to report also being major themes. Significant differences were observed between user groups, providing policy implications to improve safety occurrence reporting, such as making reporting compulsory, setting minimum training standards, having an anonymous and non-punitive reporting system, and through working with member-based organisations.
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Mieloszyk, Jacek, and Andrzej Tarnowski. "Enhancements in conceptual electric aircraft design." Aircraft Engineering and Aerospace Technology 91, no. 6 (June 10, 2019): 851–56. http://dx.doi.org/10.1108/aeat-07-2018-0192.
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PurposeThis paper aims to describe the enhancement of the numerical method for conceptual phase of electric aircraft design.Design/methodology/approachThe algorithm provides a balance between lift force and weight of the aircraft, together with drag and thrust force equilibrium, while modifying design variables. Wing geometry adjustment, mass correction and performance estimation are performed in an iterative process.FindingsAircraft numerical model, which is most often very simplified, has a number of new improvements. This enables to make more accurate analyses and to show relationships between design parameters and aircraft performance.Practical implicationsThe presented approach can improve design results.Originality/valueThe new methodology, which includes enhanced numerical models for conceptual design, has not been presented before.
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Lents, Charles E. "Hybrid Electric Propulsion." Mechanical Engineering 142, no. 06 (June 1, 2020): 54–55. http://dx.doi.org/10.1115/1.2020-jun5.
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Abstract Electrified propulsion holds the promise of reducing aviation’s CO2 emissions footprint through three means: access to green grid electric energy, improvements in aircraft performance through new airframe and propulsion system architectures and enabling further optimization of the gas turbine cycle. Charging an aircraft battery pack with green electric energy and using this energy to drive electric propulsors results in a zero emissions vehicle. This is practical for light aircraft and short missions. Boosting a Jet-A burning gas turbine with green electric energy (again stored in a ground charged battery), in either a parallel or series turbo-electric architecture can yield a net reduction in CO2 emissions, as long as the fuel burn required to carry the weight of a discharged battery pack does not overcome the reduction in fuel burn afforded by the ground charged battery. Several studies have indicated that a net savings is possible with cell level energy densities approach ∼ 500 whr/kg, a reasonable target for the 2030 time frame. Electrified propulsion can also enable unique aircraft configurations, employing a veryhigh efficiency prime mover (gas turbine) designed for running only a generator at peak efficiency, and/or distributing the propulsors throughout the aircraft, for improvement in L/D and propulsive efficiency.
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Henderson, Isaac Levi. "Examining New Zealand Unmanned Aircraft Users’ Measures for Mitigating Operational Risks." Drones 6, no. 2 (January 20, 2022): 32. http://dx.doi.org/10.3390/drones6020032.
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While the potential risks of unmanned aircraft have received significant attention, there is little in the academic literature that examines how operational risks are mitigated by users. This study examines the prevalence of key operational risk mitigations amongst a sample of 812 unmanned aircraft users in New Zealand, their confidence levels in identifying and complying with airspace requirements, and their ability to read visual navigation charts (VNCs) and use AirShare (a local tool that shows airspace requirements). Significant differences exist between the number and type of mitigations applied, users’ confidence levels in identifying and complying with airspace requirements, and users’ ability to read VNCs and use AirShare based upon user characteristics. Education, practical assessment, membership of a professional body, professional/semi-professional use, and operating for a certificated organisation all improve risk mitigation (greater number and variety of risk mitigations applied). The only risk mitigation employed by almost all users was conducting a pre-flight check of their aircraft, identifying the need for users to view risk mitigation more holistically. The findings support policy directions related to educational requirements, the ability for member-based organisations and professional bodies to self-regulate, and the fitness of the current regulatory system in New Zealand.
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Roe, M. J. "Electric Bo-Bo-Bo locomotives for New Zealand Railways." Proceedings of the Institution of Mechanical Engineers, Part D: Transport Engineering 202, no. 1 (January 1988): 21–31. http://dx.doi.org/10.1243/pime_proc_1988_202_152_02.
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Twenty-two, 3 M W freight locomotives are being supplied to New Zealand Railways Corporation as part of the 25 kV electrification project of the North Island Main Trunk route. The mountainous terrain of this route favours a Bo-Bo-Bo configuration with its good curving performance. Separately excited d.c. traction motors fed from microprocessor-controlled thyristor bridges enable 1000 tonne trains to be started on a I in 50 gradient. The provision of a regenerative brake offers significant energy cost savings.
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Li, AngJun. "Application and design of a new high power and multi propeller hybrid aircraft." SHS Web of Conferences 148 (2022): 01030. http://dx.doi.org/10.1051/shsconf/202214801030.
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This paper describes and explained a new hybrid system that could be used in the multi propeller aircraft. This new hybrid system solved the problems of fuel cost and environmental protection of traditional fuel aircraft, as well as the endurance and load of pure electric aircraft.
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Jones, R. I. "The more electric aircraft—assessing the benefits." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 216, no. 5 (May 1, 2002): 259–69. http://dx.doi.org/10.1243/095441002321028775.
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The concept of the more electric aircraft (MEA), where electrical power is used for at least some of the on-board functions at present powered by hydraulics and pneumatics, has many claimed benefits and is far from new. However, almost all larger aircraft retain hydraulics and pneumatics. Over recent years there has been a great deal of interest in the MEA concept, with developments in relevant technologies and their adoption in other areas of engineering. In support of UK efforts on this and related concepts, the College of Aeronautics has been performing studies since the mid 1980s to assess the benefits of changes. This paper describes the background to these studies and the relationships between them as well as some of their findings, concluding that it is important that such assessment work should be continued in the future.
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Geiß, Ingmar, and Rudolf Voit-Nitschmann. "Sizing of fuel-based energy systems for electric aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (August 4, 2017): 2295–304. http://dx.doi.org/10.1177/0954410017721254.
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Optimized electric motors are lighter and smaller than conventional piston engines. As a result, new airplane configurations are feasible as motors can be placed in unconventional positions. Through careful aircraft design higher aerodynamic efficiencies of airframe, propeller, and propeller integration can be achieved. The energy density of current batteries, however, still limits strongly the range of purely battery powered aircraft. But if the energy is stored in liquid fuel and converted by a generator into electric energy, then the advantages of electric propelled airplanes and conventional combustion engines can be combined. But which combustion engine is optimal for such a serial-hybrid electric aircraft? In this new propulsion chain, other boundary conditions apply to the combustion engine than in conventional aircraft designs. These boundary conditions interact with the characteristics of combustion engines. An example for an engine characteristic is that different kinds of piston engines exist. It can be observed that technologies, which result in lighter piston engines, are associated with lower efficiencies and vice versa. In this paper it will be shown through considerations on aircraft level, that the optimal combustion engine for an electric-hybrid airplane should be heavier and more efficient than the optimal combustion engine for a conventional aircraft.
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Hospodka, Jakub, Helena Bínová, and Stanislav Pleninger. "Assessment of All-Electric General Aviation Aircraft." Energies 13, no. 23 (November 25, 2020): 6206. http://dx.doi.org/10.3390/en13236206.
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The purpose of this paper is to describe the upcoming changes that will bring the transition from piston engines to all-electric aircrafts. The article focuses on the differences in operation of small general aviation aircrafts. This topic is timely, as the first all-electric aircraft was certified by the European Union Aviation Safety Agency (EASA) in 2019. As there are no data concerning this new type of operation available, the data have been derived from other applicable sources. At first, we compared the energy consumption of the same aircraft with the piston engine, and then afterwards with the retrofitted all-electric variant. Our results focus on the difference in fuel price, which is discussed in the context of electricity price comparison with AVGAS prices. Moreover, we discuss the environmental impacts, especially concerning electricity source mix and emissions produced (we estimate both with and without life-cycle assessment). In the discussion, we compare the results and identify the benefits of an all-electric solution. Furthermore, several operational restrictions of all-electric aircrafts are discussed.
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Pinto Leite, José Pedro Soares, and Mark Voskuijl. "Optimal energy management for hybrid-electric aircraft." Aircraft Engineering and Aerospace Technology 92, no. 6 (May 4, 2020): 851–61. http://dx.doi.org/10.1108/aeat-03-2019-0046.
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Purpose In recent years, increased awareness on global warming effects led to a renewed interest in all kinds of green technologies. Among them, some attention has been devoted to hybrid-electric aircraft – aircraft where the propulsion system contains power systems driven by electricity and power systems driven by hydrocarbon-based fuel. Examples of these systems include electric motors and gas turbines, respectively. Despite the fact that several research groups have tried to design such aircraft, in a way, it can actually save fuel with respect to conventional designs, the results hardly approach the required fuel savings to justify a new design. One possible path to improve these designs is to optimize the onboard energy management, in other words, when to use fuel and when to use stored electricity during a mission. The purpose of this paper is to address the topic of energy management applied to hybrid-electric aircraft, including its relevance for the conceptual design of aircraft and present a practical example of optimal energy management. Design/methodology/approach To address this problem the dynamic programming (DP) method for optimal control problems was used and, together with an aircraft performance model, an optimal energy management was obtained for a given aircraft flying a given trajectory. Findings The results show how the energy onboard a hybrid fuel-battery aircraft can be optimally managed during the mission. The optimal results were compared with non-optimal result, and small differences were found. A large sensitivity of the results to the battery charging efficiency was also found. Originality/value The novelty of this work comes from the application of DP for energy management to a variable weight system which includes energy recovery via a propeller.
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Chouhan, Priya, and Nikos J. Mourtos. "Design of a Four-Seat, General Aviation Electric Aircraft." Athens Journal of Τechnology & Engineering 8, no. 2 (April 29, 2021): 139–68. http://dx.doi.org/10.30958/ajte.8-2-2.
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Financial and environmental considerations continue to encourage aircraft manufacturers to consider alternate forms of aircraft propulsion. On the financial end, it is the continued rise in aviation fuel prices, as a result of an increasing demand for air travel, and the depletion of fossil fuel resources; on the environmental end, it is concerns related to air pollution and global warming. New aircraft designs are being proposed using electrical and hybrid propulsion systems, as a way of tackling both the financial and environmental challenges associated with the continued use of fossil fuels. While battery capabilities are evolving rapidly, the current state-of-the-art offers an energy density of ~ 250 Wh/kg. This is sufficient for small, general aviation electric airplanes, with a modest range no more than 200 km. This paper explores the possibility of a medium range (750 km) electric, four-seat, FAR-23 certifiable general aviation aircraft, assuming an energy density of 1500 Wh/kg, projected to be available in 2025. It presents the conceptual and preliminary design of such an aircraft, which includes weight and performance sizing, fuselage design, wing and high-lift system design, empennage design, landing gear design, weight and balance, stability and control analysis, drag polar estimation, environmental impact and final specifications. The results indicate that such an aircraft is indeed feasible, promising greener general aviation fleets around the world. Keywords: general aviation aircraft, electric aircraft, aircraft design
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Zhang, Yijun. "Possibility of Building an Electric Plane: Starting from Existing Designed Models." IOP Conference Series: Earth and Environmental Science 1011, no. 1 (April 1, 2022): 012006. http://dx.doi.org/10.1088/1755-1315/1011/1/012006.
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Abstract Entering the 21st century, searches for alternative energy have become more and more significant to mitigate the gradual deterioration of the environment and the dearth of fossil fuels such as petroleum. As a result, plenty of scientists start resorting to electricity, one kind of clean energy produced by natural power like wind and water. Electricity has recently been applied to vehicles after decades of research, and the technology of the application doesn’t stop progressing. However, the application on vehicles is not just a destination but a starting point for electric aircraft. Nowadays, the research of electric aircraft has been started by several companies. This review begins with the rapid development of new energies, summarizes current existing models of electric aircraft from Airbus, Boeing, and other companies and agencies, considers the possibility of electric aircraft, and provides the prospect of building an electric aircraft in the future. The review concludes that while building electric airplanes is possible, and the size is restricted to be small enough due to the restriction of the energy density of the battery.
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Frosina, Emma, Adolfo Senatore, Luka Palumbo, Giuseppe Di Lorenzo, and Ciro Pascarella. "Development of a Lumped Parameter Model for an Aeronautic Hybrid Electric Propulsion System." Aerospace 5, no. 4 (October 4, 2018): 105. http://dx.doi.org/10.3390/aerospace5040105.
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This paper describes a case study for applying a hybrid electric propulsion system for general aviation aircraft. The work was performed by a joint team from the Centro Italiano Ricerche Aerospaziali (CIRA) and the Department of Industrial Engineering of the University of Naples Federico II. The use of electric and hybrid electric propulsion for aircraft has gained widespread and significant attention over the past decade. The driver of industry interest has principally been the need to reduce the emissions of combustion engine exhaust products and noise; however, studies have revealed the potential for overall improvement in the energy efficiency and mission flexibility of new aircraft types. The goal of the present study was to demonstrate the feasibility of aeronautic parallel hybrid electric propulsion for light aircraft, varying mission profiles and electric configurations. Through the creation and application of a global model with AMESim® software, in which every aspect of the components chosen by the industrial partners can be represented, some interesting studies were carried out. The numerical model used was more complete and more accurate compared to some others available in the literature. In particular, it was confirmed that, for particular missions, integrating state-of-the-art technologies provides notable advantages for aircraft hybrid electric propulsion for light aircraft.
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Mach, D. M. "Technique for Reducing the Effects of Nonlinear Terms on Electric Field Measurements of Electric Field Sensor Arrays on Aircraft Platforms." Journal of Atmospheric and Oceanic Technology 32, no. 5 (May 2015): 993–1003. http://dx.doi.org/10.1175/jtech-d-14-00029.1.
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AbstractA generalized technique has been developed that reduces the contributions of nonlinear effects that occur during measurements of natural electric fields around thunderstorms by an array of field mills on an aircraft. The nonlinear effects can be due to nearby charge emitted by the aircraft as it acquires and sheds charge, but the nonlinear effects are not limited to such sources. The generalized technique uses the multiple independent measurements of the external electric field obtained during flight to determine and remove nonlinear contaminations in the external vector electric field. To demonstrate the technique, a simulated case with nonlinear contaminations was created and then corrected for the nonlinear components. In addition, data from two different field programs utilizing two different aircraft and field mill configurations, each containing observable and different nonlinear effects, were also corrected for the significant nonlinear effects found in the field mill outputs. The expanded independent measurements in this new technique allow for the determination and correction of components in the field mill outputs from almost any measurable source. Alternate utilization of the technique can include removing effects in the aircraft charging such as aircraft altitude, cloud properties, engine power settings, or aircraft flap deployment. This technique provides a way to make more precise measurements of the true external electric field for scientific studies of cloud electrification.
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Ali, Zarqa Shaheen, and Amrita Kondal. "PEOPLE’S ATTITUDES TOWARDS USE OF ELECTRIC CARS IN AOTEAROA NEW ZEALAND." Asia-Pacific - Annual Research Journal of Far East & South East Asia 39 (February 20, 2022): 199–21. http://dx.doi.org/10.47781/asia-pacific.vol39.iss0.4447.
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This study aims to explore the attitudes and perception of people and their intention to use the electric cars based on its cost, usefulness, satisfaction, enjoyment, ease of use and their expectation from government in the form of subsidies to the owners of electric cars, which finally results in their purchase intentions. A descriptive research design is used for this study and the data have been collected from 203 participants from New Zealand. A survey method was used and the questionnaire was developed. The results of the survey indicate that a higher percentage of the respondents are ready to embark on the use of electric cars and the only factor that acts as a constraint in their buying interest is the cost of the car. It is also evident from the results that people are concerned about environmental sustainability and with a little push from the government can convince the people and can initiate their switch to electric cars.
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Zhang, Peng, and Qi Shuang Ma. "A Method of Evaluating Reliability of More-Electric-Aircraft Power System Using Node-Weighted Network." Advanced Materials Research 516-517 (May 2012): 1288–91. http://dx.doi.org/10.4028/www.scientific.net/amr.516-517.1288.
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More-electric-aircraft contains more electric equipment compared with conventional aircraft, which makes it have more complex architecture in power system. It has some characters of complex networks, needs new method to analyze. The method of evaluating reliability of more-electric-aircraft power system mentioned in [1] treats all the power load nodes as the same, which does not exactly match the actual system. In this paper, one type of node-weighted network model is proposed. In the node-weighted model, load nodes with different importance are weighted differently. The given example demonstrates that this approach is feasibly and rational.
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Singleton, John. "Vampires to Skyhawks: Military Aircraft and Frigate Purchases by New Zealand, 1950–70." Australian Economic History Review 42, no. 2 (July 2002): 183–203. http://dx.doi.org/10.1111/1467-8446.t01-1-00029.
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Larsen, H. R., G. W. Fisher, R. A. Knobben, I. S. Lechner, and M. J. Harvey. "An Instrumented Aircraft for Atmospheric Research in New Zealand and the South Pacific." Bulletin of the American Meteorological Society 72, no. 2 (February 1991): 192–200. http://dx.doi.org/10.1175/1520-0477(1991)072<0192:aiafar>2.0.co;2.
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Yang, Zhangang, Junchao Qu, Yingchuan Ma, and Xudong Shi. "Modeling and Simulation of Power Distribution System in More Electric Aircraft." Journal of Electrical and Computer Engineering 2015 (2015): 1–7. http://dx.doi.org/10.1155/2015/847624.
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The More Electric Aircraft concept is a fast-developing trend in modern aircraft industry. With this new concept, the performance of the aircraft can be further optimized and meanwhile the operating and maintenance cost will be decreased effectively. In order to optimize the power system integrity and have the ability to investigate the performance of the overall system in any possible situations, one accurate simulation model of the aircraft power system will be very helpful and necessary. This paper mainly introduces a method to build a simulation model for the power distribution system, which is based on detailed component models. The power distribution system model consists of power generation unit, transformer rectifier unit, DC-DC converter unit, and DC-AC inverter unit. In order to optimize the performance of the power distribution system and improve the quality of the distributed power, a feedback control network is designed based on the characteristics of the power distribution system. The simulation result indicates that this new simulation model is well designed and it works accurately. Moreover, steady state performance and transient state performance of the model can fulfill the requirements of aircraft power distribution system in the realistic application.
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Lin, Yide. "The Development and Challenges of More Electric Aircraft." Highlights in Science, Engineering and Technology 27 (December 27, 2022): 814–19. http://dx.doi.org/10.54097/hset.v27i.3850.
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The development of electrical and electronic engineering makes the replacement of conventional hydraulic, mechanic, and pneumatic system into electrical system become much more possible. That means the secondary power of aircraft will be dominated by electricity, rather than hydraulic oil or bleed air from the engine. The Boeing 787 and Airbus A380 has applied these technologies significantly and their fuel consumption and noise level during flight are also get improved by comparison with their counterpart which has traditional hydraulic and pneumatic system. On the other side, the mass application of electrical driven components on board will lead to various new challenges to aircraft design when concerning the weight and flight safety due to the characteristics of those components. In this paper, technologies implemented, and challenges will be introduced through reviewing literatures. The benefit and drawbacks will be concluded by comparing electrical and hydraulic and pneumatic system.
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da Silva, Francisco Ferreira, João F. P. Fernandes, and Paulo Jose da Costa Branco. "Barriers and Challenges Going from Conventional to Cryogenic Superconducting Propulsion for Hybrid and All-Electric Aircrafts." Energies 14, no. 21 (October 20, 2021): 6861. http://dx.doi.org/10.3390/en14216861.
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The development of electric aircraft is becoming an important technology for achieving the goals set by the European Commission for the reduction of gases emissions by 2050 in the aeronautical transportation system. However, there is a technology gap between the current values of specific power in commercial electric machines and those required for aeronautical applications. Therefore, the search for alternative materials and non-conventional designs is mandatory. One emergent solution is using superconducting machines and systems to overcome the current limits of conventional electrical machines. This work reviews the new hybrid and all-electric aircraft tendencies, complementing it with recent research on the design and development of high specific power superconducting machines. This includes the main topologies for hybrid and all-electric aircraft, with an overview of the ongoing worldwide projects of these aircraft types, systematizing the main characteristics of their propulsion systems. It also includes the research on superconducting machines to achieve high specific power and consider the impact on the redesign of aircraft systems, the electrical, cooling, and fuel source systems.
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Ibrahim, K., S. Sampath, and D. Nalianda. "Voltage synchronisation for hybrid-electric aircraft propulsion systems." Aeronautical Journal 125, no. 1291 (July 22, 2021): 1611–30. http://dx.doi.org/10.1017/aer.2021.56.
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AbstractIncreasing demand for commercial air travel is projected to have additional environmental impact through increased emissions from fuel burn. This has necessitated the improvement of aircraft propulsion technologies and proposal of new concepts to mitigate this impact. The hybrid-electric aircraft propulsion system has been identified as a potential method to achieve this improvement. However, there are many challenges to overcome. One such challenges is the combination of electrical power sources and the best strategy to manage the power available in the propulsion system. Earlier methods reviewed did not quantify the mass and efficiency penalties incurred by each method, especially at system level. This work compares three power management approaches on the basis of feasibility, mass and efficiency. The focus is on voltage synchronisation and adaptation to the load rating. The three methods are the regulated rectification, the generator field flux variation and the buck-boost. This comparison was made using the propulsion system of the propulsive fuselage aircraft concept as the reference electrical configuration. Based on the findings, the generator field flux variation approach appeared to be the most promising, based on a balance of feasibility, mass and efficiency, for a 2.6MW system.
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Sollazzo, Adolfo, Francesco Petrosino, Luciano De Vivo, Antonio Visingardi, and Mattia Barbarino. "Acoustic Impact of Hybrid-Electric DEP Aircraft Configuration at Airport Level." Applied Sciences 11, no. 20 (October 16, 2021): 9664. http://dx.doi.org/10.3390/app11209664.
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The Italian research project PROSIB (PROpulsione e Sistemi IBridi per velivoli ad ala fissa e rotante), is a 30-month initiative funded by the Italian Ministry of University and Scientific Research (MIUR) and coordinated by the Leonardo company. The project is aimed to investigate configurations for regional aircraft and rotary wing platforms and architectures for propulsion systems, and is dedicated to the identification of the best strategy for their use, given different on-board energy sources. The reduced environmental impact is the key for the success of the new hybrid/electric aircraft configurations. This not only considers the chemical pollution introduced in the atmosphere, but also the noise produced on the surrounding area of airports. The present paper describes the acoustic impact assessment resulting from the inclusion of new propulsion technologies and new configurations of regional aircraft (ATR42 pax) in a reference airport area.
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Marksel, M., R. Kamnik, S. Božičnik, and A. B. Prapotnik. "Strategy for 19-seat hybrid-electric short haul air transportation." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012072. http://dx.doi.org/10.1088/1757-899x/1226/1/012072.
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Abstract This paper addresses a way to implement greener aviation technologies, such as hybrid-electric propulsion, into the air transportation network to respond to the increasing environmental challenges posed by growing air traffic. New routes could be established between small airports to ensure better air connectivity in Europe while also connecting disadvantaged areas and relieve congestion at hub airports. Such routes could, for example, be served by micro feeder or 19-seat hybrid-electric aircraft, which produce low or no emissions, have lower operating costs, and are more applicable to environmental constraints. To achieve this and overcome the various challenges posed by the new hybrid-electric technologies, a new strategic roadmap for short-haul air transport is needed to optimize network services with small hybrid-electric aircraft.
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Duke, Mike, Deborah Andrews, and Timothy Anderson. "The feasibility of long range battery electric cars in New Zealand." Energy Policy 37, no. 9 (September 2009): 3455–62. http://dx.doi.org/10.1016/j.enpol.2008.10.047.
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Frost, Frederick A., and Gerardo R. Joson. "Turnaround strategies of electric utilities in New Zealand and the Philippines." Strategic Change 7, no. 5 (August 1998): 289–300. http://dx.doi.org/10.1002/(sici)1099-1697(199808)7:5<289::aid-jsc371>3.0.co;2-h.
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Langston, Lee S. "Old and New." Mechanical Engineering 141, no. 06 (June 1, 2019): 38–43. http://dx.doi.org/10.1115/1.2019-jun2.
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As prime movers go, gas turbines are virtually brand new, compared to, say, wind and water turbines which have been around for millennia. But they have also reached a considerable level of maturity. Gas turbines now dominate both the world’s aircraft propulsion and a good portion of electric power generation. The fortunes of the industry are not uniform, however. The commercial jet engine market is robust and growing; the military jet engine, electric power, and other markets have been relatively flat or declining. But those are the sectors where the possibilities lie. They aren’t new, but they have the potential for renewal. This study delves deeper into the current status and trends in theworldwide gas turbine market.
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Crowder, R., and C. Maxwell. "Simulation of a prototype electrically powered integrated actuator for civil aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 6 (June 1, 1997): 381–94. http://dx.doi.org/10.1243/0954410971532749.
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Developments in the design and proposed operation of large civil aircraft have resulted in aircraft manufacturers and equipment suppliers developing new system concepts, one of which is the all or more electric aircraft. In the all or more electric aircraft the distribution of power for flight actuation will be through the electrical system, as opposed to the currently used bulk hydraulic system. In order to implement power-by-wire, high-performance electrically powered actuators will be required. The paper discusses the design details, and the simulation of an electrohydrostatic actuator suitable for use in primary flight control systems of a civil aircraft. The paper presents experimental and simulation results, and identifies the parameters that will critically affect the performance of an actuator.
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Jia, Yijiang, and Kaushik Rajashekara. "Induction Machine for More Electric Aircraft: Enabling New Electrical Power System Architectures." IEEE Electrification Magazine 5, no. 4 (December 2017): 25–37. http://dx.doi.org/10.1109/mele.2017.2755267.
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Yang, Yuanchao, and Zichen Gao. "Power Management Problem for Civil Aircraft under More Electric Environment." International Journal of Aerospace Engineering 2020 (January 24, 2020): 1–19. http://dx.doi.org/10.1155/2020/8474375.
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The civil aviation industry is moving toward the more electric aircraft (MEA) which is to use electrical power to meet the load demands on multiple aircraft subsystems which are conventionally driven by other power resources. Thus, there will be introduced a large amount of new electrical power demands which are safety-critical for aircraft’s flight and this may lead the challenge for a reliable and efficient power management problem (PMP): the balance between the aircraft power supply and demands while minimizing the operation costs. To cope with the PMP for civil aircraft under more electric environment, in this paper, we explicitly give a detailed and complete modeling of all power supply resources (fuel and battery) and safety-critical electrical loads and cast the PMP as a mixed-integer nonlinear programming problem; we develop a practical solution methodology for the application on the real civil MEA. The proposed formulation and solution algorithm can give an efficient power schedule result with the minimal fuel and battery operation cost through a smart codispatch between the gas turbine generator, storage devices, and all electrical loads of MEA. Numerical testing results based on one real civil aircraft case demonstrate the economic and operational effectiveness.
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Huang, Mingyang, Hong Nie, and Ming Zhang. "Analysis of ground handling characteristic of aircraft with electric taxi system." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 6 (April 11, 2018): 1546–61. http://dx.doi.org/10.1177/0954407018764163.
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Electric landing gear drive equipped with traction motors can provide taxi capability without the use of main engines or tractor. The ground handling characteristic of aircraft with electric taxi system is analyzed. The new mathematic model of aircraft ground maneuver is established, considering the 6-degree-freedom aircraft body and the flexible main strut and the powered wheel. Quasi-steady method is applied to calculate tire side forces and moments, to determine side slip. The simulation for the ground steering response of aircraft with electric taxi system is done by employing ADAMS and Simulink co-simulation platform. The dynamic responses of aircraft ground steering and landing gear spin-up and spring back are simulated. Different taxi conditions including powered nose wheel mode and powered main wheel mode are compared. Four conclusions are obtained: electric taxi system helps the aircraft turn on the spot and the turning radius is smaller than the aircraft using engines; differential powered main wheel mode has the minimum turning radius while turning-circle with uniform velocity, and it has smaller difference between two vertical loads of main landing gear than powered nose wheel mode; in the case of the same steering angle, the extreme velocity of differential powered main wheel mode before side slip is larger than powered nose wheel mode; and pre-rotation of powered main wheel decreases the spin-up drag load and spring back drag load.
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Memmolo, V., A. D. Marano, L. Maio, F. Nicolosi, and F. Marulo. "Aeroelastic assessment of distributed electric propulsion wings." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012066. http://dx.doi.org/10.1088/1757-899x/1226/1/012066.
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Abstract During recent years, aircraft manufacturers focused on environmentally friendly and aerodynamically efficient aircraft concepts that could allow a radical reduction of emissions. The use of a hybrid-electric powertrain is one of the most effective ways to design near-zero-emission aircraft. These aircraft are highly performing and sophisticated so the design process must be extremely accurate. Among the various innovative aspects, the use of distributed engines to improve aerodynamic performance poses new challenges from a structural perspective due to the tip-mounted propeller demanding a complicated design due to reduced flutter performance. This results in higher stiffness requirements and consequently increased mass. Both the weight penalty needed to prevent dynamic instability, and the wing aeroelastic tailoring, crucial to minimize such an additional weight, is of utmost importance. Because of setting up a preliminary approach to estimate the static and dynamic effects of such a non-conventional wing architecture, the present paper shows a comprehensive structural analysis of a wing opportunely designed according to certification specification and equipped with a variable position powertrain. Several different engines are then moved along the wingspan to estimate how it affects the dynamic response using a simplified beam-stick finite element model. The results show that the engine position strongly affects the flutter velocity with a particular band bell curve over the wingspan with the maximum in between 60-70% wingspan. In addition, it is worth noting how the tip propeller may cause a reduction of flutter velocity with respect to the conventional configuration with the turbine mounted in between 30-40% wing-span.
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Pohl, Markus, Jo Köhler, Hagen Kellermann, Michael Lüdemann, Daniel Weintraub, Peter Jeschke, and Mirko Hornung. "Preliminary Design of Integrated Partial Turboelectric Aircraft Propulsion Systems." Journal of the Global Power and Propulsion Society 6 (February 25, 2022): 1–23. http://dx.doi.org/10.33737/jgpps/145907.
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This paper presents a novel tool for the modeling of partial turboelectric propulsion systems together with a corresponding case study for a commercial single-aisle aircraft. In order to reduce the environmental impact of air traffic, radically new aircraft and propulsion concepts with a high market penetration are needed. Partial turboelectric propulsion systems seem to offer a promising option to achieve this. For the development of these propulsion systems, a preliminary design tool with a homogeneous and sufficiently high fidelity, both for turbomachinery and electric components, is needed. To address this, the authors of this publication have developed a tool based on the GasTurb software. The models developed, in particular for the electric components which together form the electric powertrain, are described here. In the case study, which demonstrates the coupling of the developed tool with an aircraft design environment, a conventional turboprop baseline aircraft is compared to a derived aircraft which features a partial turboelectric propulsion system with wingtip propellers. The latter are intended to reduce the induced drag, enabling a reduction of the aircraft's total shaft power demand compared to the conventional baseline aircraft. The comparison between the partial turboelectric aircraft and the baseline aircraft indicates that fuel reduction increases with power split. However, primarily increasing electric powertrain masses and a stagnating drag reduction result in lower additional fuel reductions for higher power splits. Despite these conclusions, the predicted induced drag reductions need further refinement as they were found to be optimistic. In summary, this publication presents a methodology and a set of physics-based component models for the preliminary design of partial turboelectric propulsion systems, so that the electric components can be investigated and optimized at the same high level of detail as the gas turbine.
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Riboldi, Carlo E. D., Lorenzo Trainelli, Luca Mariani, Alberto Rolando, and Francesco Salucci. "Predicting the effect of electric and hybrid-electric aviation on acoustic pollution." Noise Mapping 7, no. 1 (April 13, 2020): 35–56. http://dx.doi.org/10.1515/noise-2020-0004.
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AbstractIn the quest for the reduction of noise pollution, novel hybrid-electric or fully-electric power-trains promise to provide a substantial contribution. Especially closer to airfields, where acceptability issues tend to limit air operations with conventional fuel-burning engines, such novel power-trains allow to fly terminal maneuvers with a dramatically reduced impact on pollution. Considering the General Aviation (GA) field, where such new types of propulsion are more likely to gain a significant market share thanks to their favorable characteristics for this weight category, the reduction of the noise impact on ground may increase the infrastructural value of smaller airfields, often located in densely populated areas. This in turn would help in making novel power-train technologies economically advantageous at a system level. Despite these evident advantages, a methodology to quantify noise emissions of a novel type of power-train has not been identified yet – a fundamental step towards the assessment of the potential contribution of hybrid-electric or fully-electric aircraft to the global scenario of future aviation. This work introduces and discusses a possible procedure to provide such estimation. While mainly focused on the field of propeller-driven GA aircraft, the procedure presented herein can be easily scaled to cope with the specific features of heavier categories.
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Kuprikov, Mikhail, Leonid Ponyaev, and Nikita Kuprikov. "DECREASE OF SOUND PRESSURE LEVEL AND NOISE INSIDE HYBRID ELECTRIC WING BODY PLANES AND DIRIDGABLES." Akustika 34 (November 1, 2019): 170–73. http://dx.doi.org/10.36336/akustika201934170.
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The analysis of the find Optimal Structure of the Large Aircraft and Airship for decrease of Sound/Noise Pressure Level inside and outside the Cabin Saloon are very actually today for Worldwide Ecology Program. The Method of Aircraft layout from the virtual mass center is given, which allows us to obtain the Aircraft layout from the conditions of Infrastructural Constraints in the terminal configurations of the Modern Air Transportation Infrastructure and IATA/ICAO Regulation. A Method is proposed for the synthesis of new circuit solutions for an Aircraft passenger compartment and may be use to any Diridgables Projections future. A Geometrical representation of the concept of LHA with large passenger capacity made with a Drop-Shaped Fuselage in the Aerodynamic balancing Flying Wing Body Scheme is given.The new Body Plane LHA and Lighter-then-Air (LTA) Vehicles with cover of Solar Electro Systems will be more innovation projections for Worldwide Security Air Transportation with reduce Noise and CO Pollution Level.
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Li, Teng, Zhijie Jiao, Lina Wang, and Yong Mu. "A Method of DC Arc Detection in All-Electric Aircraft." Energies 13, no. 16 (August 13, 2020): 4190. http://dx.doi.org/10.3390/en13164190.
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Arc faults in an aircraft’s power distribution system (PDS) often leads to cable and equipment damage, which seriously threatens the personal safety of the passengers and pilots. An accurate and real-time arc fault detection method is needed for the Solid-State Power Controller (SSPC), which is a key protection equipment in a PDS. In this paper, a new arc detection method is proposed based on the improved LeNet5 Convolutional Neural Network (CNN) model after a Time–Frequency Analysis (TFA) of the DC currents was obtained, which makes the arc detection more real-time. The CNN is proposed to detect the DC arc fault for its advantage in recognizing more time–frequency joint details in the signals; the new structure also combines the adaptive and multidimensional advantages of the TFA and image intelligent recognition. It is confirmed by experimental data that the combined TFA–CNN can distinguish arc faults accurately when the whole training database has been repeatedly trained 3 to 5 times. For the TFA, two kinds of methods were compared, the Short-Time Fourier Transform (STFT) and Discrete Wavelet Transform (DWT). The results show that DWT is more suitable for DC arc fault detection. The experimental results demonstrated the effectiveness of the proposed method.
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Wu, Gui Cheng, Yu Hui Liu, Deng Liang Yang, and Jian Hui Deng. "Moment Resisting Performance Analysis and Structure Optimization for Electric Actuator." Key Engineering Materials 522 (August 2012): 686–90. http://dx.doi.org/10.4028/www.scientific.net/kem.522.686.
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The development of altitude and remote control for aircraft requires larger rudder piece pitch angle, and Electric actuator needs to withstand larger bending moment as the attitude control executive mechanism. Traditional bending moment and torsional moment of Electric actuator rely on output shaft bearing which are difficult to meet the requirement of resisting large moment. Based on a particular type of Electric actuator system, this paper analyzes its moment resisting capacity, proposes an idea of seperating bearing objects of bending and torsional moment for aircraft, and designs an innovative actuator structure. Moment test experiments show that moment resisting capacity of the new Electric actuator is enhanced to 150% more than orginal one.
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Selena Sheng, Mingyue, Le Wen, Basil Sharp, Bo Du, Prakash Ranjitkar, and Douglas Wilson. "A spatio-temporal approach to electric vehicle uptake: Evidence from New Zealand." Transportation Research Part D: Transport and Environment 105 (April 2022): 103256. http://dx.doi.org/10.1016/j.trd.2022.103256.
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Hasan, Md Arif, David J. Frame, Ralph Chapman, and Kelli M. Archie. "Costs and emissions: Comparing electric and petrol-powered cars in New Zealand." Transportation Research Part D: Transport and Environment 90 (January 2021): 102671. http://dx.doi.org/10.1016/j.trd.2020.102671.
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Swithinbank, Charles. "Airborne tourism in the Antarctic." Polar Record 29, no. 169 (April 1993): 103–10. http://dx.doi.org/10.1017/s003224740002355x.
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ABSTRACTThere are two classes of airborne tourism in Antarctica: overflights without landing, and fl ights including landing. The earliest overflight was in 1956, but there were no regular flights until 1977, when Qantas and Air New Zealand began overflights with wide-bodied aircraft. A crash on Mount Erebus in 1979 that killed 257 people drew attention to the absence of effective planning, air traffic control, and rescue services. Landings began in the South Shetland Islands in 1982, when C-130 aircraft of Fuerza Aerea de Chile brought passengers from Punta Arenas. Since 1983, tourists have been accommodated in a Chilean government hostel. Flights to the interior began in 1984 when climbers were taken to the Sentinel Range by ski-equipped aircraft. Unmodified transport aircraft have been used since 1987, making wheel landings on naturally occurring bare ice in the Heritage Range. Tourists were taken from this site to the South Pole in 1988 by smaller, ski-equipped aircraft. Owing to the lack of conventional airfields in Antarctica, the future of intercontinental operations may depend on the development of additional airfields on bare ice. There are many possible sites. Most are near the periphery of the continent but some are in high latitudes, one only 300 km from the South Pole. A few of these will allow direct flights of unmodified passenger aircraft from South America, South Africa, Australia, or New Zealand. The possibility of 300 day-trippers stepping onto the ice from a Boeing 747 raises a variety of safety and environmental concerns. The challenge to the Antarctic Treaty System will be to reconcile the interests of governments, scientists, airlines, tour operators, tourists, and environmentalists.
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Zhou, Suying, Hui Lin, and Bingqiang Li. "Research on HILS Technology Applied on Aircraft Electric Braking System." Journal of Electrical and Computer Engineering 2017 (2017): 1–14. http://dx.doi.org/10.1155/2017/3503870.
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On the basis of analyzing the real-time feature of hardware-in-the-loop simulation of aircraft braking system, a new simulation method based on MATLAB/RTW (Real-Time Workshop) and DSP is introduced. The purpose of this research is to develop a digital control unit with antilock brake system control algorithm for aircraft braking system using HILS. DSP is used as simulator. Using this method, a detailed mathematical modeling of system is proposed first. Studies on reducing sampling time with model simplification and modeling for applying to I/O interface of DSP and HILS are conducted. Compared with other methods, this method is low cost and convenient to implement. By using these methods, we can complete HIL simulation of aircraft braking under various experimental conditions, modify its control laws, and test its braking performance. The results have demonstrated that this platform has high reliability. The algorithm is verified by real-time closed loop test with HILS system and the results are presented.
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Bacchini, Alessandro, and Enrico Cestino. "Key aspects of electric vertical take-off and landing conceptual design." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 3 (November 8, 2019): 774–87. http://dx.doi.org/10.1177/0954410019884174.
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The recent advances in battery energy density and electric propulsion systems for automotive applications are enabling the development of the electric vertical take-off and landing (VTOL) aircraft. The electric VTOL is a new means of transport that can fly like an aircraft and take off and land vertically like a helicopter, sometimes called personal aerial vehicle. This paper compares it to the existing vehicles that may compete with it and addresses the estimation of its performances in hover, cruise flight, and the transition phase. The main parameters affecting performances are then discussed. Considerable space is dedicated to the battery mass to total mass ratio.
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Pennell, C. G. L., M. P. Rolston, C. Van Koten, D. E. Hume, and S. D. Card. "Reducing bird numbers at New Zealand airports using a unique endophyte product." New Zealand Plant Protection 70 (July 25, 2017): 224–34. http://dx.doi.org/10.30843/nzpp.2017.70.55.
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Birds are a major issue for airport authorities worldwide creating hazards to operating aircraft. The effect of a species of grass, Schedonorus arundinaceus, colonised by a unique strain of the mutualistic fungal endophyte Epichloé coenophiala on bird abundance was examined during a series of trials at two New Zealand airports between 2007 and 2012. Fewer birds were observed on S. arundinaceus cv. Jackal AR601 plots compared with the original uncultivated ground cover for many months of the year across many years of trials. This corresponds with data collected by airport authorities on the number of bird strikes experienced by these airports before and after the introduction and establishment of S. arundinaceus cv. Jackal AR601. This plant-fungal association was later developed into the product known as Avanex.
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Fioriti, Marco, Silvio Vaschetto, Sabrina Corpino, and Giovanna Premoli. "Design of hybrid electric heavy fuel MALE ISR UAV enabling technologies for military operations." Aircraft Engineering and Aerospace Technology 92, no. 5 (February 29, 2020): 745–55. http://dx.doi.org/10.1108/aeat-05-2019-0109.
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Purpose This paper aims to present the main results achieved in the frame of the TIVANO national-funded project which may anticipate, in a stepped approach, the evolution and the design of the enabling technologies needed for a hybrid/electric medium altitude long endurance (MALE) unmanned aerial vehicle (UAV) to perform persistent intelligence surveillance reconnaissance (ISR) military operations. Design/methodology/approach Different architectures of hybrid-propulsion system are analyzed pointing out their operating modes to select the more suitable architecture for the reference aircraft. The selected architecture is further analyzed together with its electric power plant branch focusing on electric system architecture and the selected electric machine. A final comparison between the hybrid and standard propulsion is given at aircraft level. Findings The use of hybrid propulsion may lead to a reduction of the total aircraft mass and an increase in safety level. However, this result comes together with a reduced performance in climb phase. Practical implications This study can be used as a reference for similar studies and it provides a detailed description of propulsion operating modes, power management, electric system and machine architecture. Originality/value This study presents a novel application of hybrid propulsion focusing on a three tons class MALE UAV for ISR missions. It provides new operating modes of the propulsion system and a detailed electric architecture of its powertrain branch and machine. Some considerations on noise emissions and infra-red traceability of this propulsion, at aircraft level.