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Tsukanov, Ruslan, and Viktor Riabkov. "Transport category airplane flight range calculation accounting center-of-gravity position shift and engine throttling characteristics." Aerospace technic and technology, no. 5 (October 6, 2021): 4–14. http://dx.doi.org/10.32620/aktt.2021.5.01.
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A problem facing world commercial aviation is a provision of the flight range and an increase in the fuel efficiency of transport category airplanes using fuel trim transfer application, which allows for decreasing airplane trim drag at cruise flight. In the existing mathematical models, center-of-gravity position is usually assumed fixed, but with fuel usage, center-of-gravity shifts within the definite range of center-of-gravity positions. Until the fuel trim transfer was not used in airplanes, the center-of-gravity shift range was rather short, that allowed to use the specified assumption without any considerable mistakes. In case of fuel trim transfer use, center-of-gravity shifts can reach 15…20 % of mean aerodynamic chord, that requires considering the center-of-gravity actual position during the flight range calculation. Early made estimated calculations showed the necessity of following mathematical model improvement using accounting the real engine throttling characteristics. The goal of this publication is to develop a method of flight range calculation taking transport category airplane into account actual center-of-gravity position with fuel using and variation in engine-specific fuel consumption according to their throttling characteristics. On the basis of real data from engine maintenance manuals, formulas are obtained for approximation throttling characteristics of turbofan engines in the form of dimensionless specific fuel consumption (related to the specific fuel consumption at full thrust) dependence on the engine throttling coefficient. A mathematical model (algorithm and its program implementation using С language in Power Unit 11.7 R03 system) has been developed to calculate the airplane flight range accounting its actual center-of-gravity position shift with fuel usage and variation in specific fuel consumption according to engine throttling characteristics. Using comparison with known payload-range diagram, adequacy of developed mathematical model is shown. Recommendations to improve the mathematical model are also given.
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Radmanesh, Hamid, Seyed Saeid Heidari Yazdi, G. B. Gharehpetian, and S. H. Fathi. "Modelling and Simulation of Fuel Cell Dynamics for Electrical Energy Usage of Hercules Airplanes." Scientific World Journal 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/593121.
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Dynamics of proton exchange membrane fuel cells (PEMFC) with hydrogen storage system for generating part of Hercules airplanes electrical energy is presented. Feasibility of using fuel cell (FC) for this airplane is evaluated by means of simulations. Temperature change and dual layer capacity effect are considered in all simulations. Using a three-level 3-phase inverter, FC’s output voltage is connected to the essential bus of the airplane. Moreover, it is possible to connect FC’s output voltage to airplane DC bus alternatively. PID controller is presented to control flow of hydrogen and oxygen to FC and improve transient and steady state responses of the output voltage to load disturbances. FC’s output voltage is regulated via an ultracapacitor. Simulations are carried out via MATLAB/SIMULINK and results show that the load tracking and output voltage regulation are acceptable. The proposed system utilizes an electrolyser to generate hydrogen and a tank for storage. Therefore, there is no need for batteries. Moreover, the generated oxygen could be used in other applications in airplane.
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Li, Xiao Gang, Zhou Zhou, Ke Qiang Cao, Chao Xia, and Na Li. "Design of Integrative Testing System for Enclosures in Fuel System of Airplanes." Applied Mechanics and Materials 719-720 (January 2015): 258–61. http://dx.doi.org/10.4028/www.scientific.net/amm.719-720.258.
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In order to start performance testing and experimental research for enclosure of airplanes’ fuel systems, a type of integrative testing system is designed in this paper. This system can accomplish function and performance tests for enclosures in airplanes’ fuel system, and also can execute troubleshooting experiments.
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JAKLIŃSKI, Piotr, Mirosław WENDEKER, Jacek CZARNIGOWSKI, Mariusz DUK, Tomasz ZYSKA, and Jakub KLIMKIEWICZ. "The comparison of the operating parameters in an aircraft radial piston engine fuelled by 100LL and ES95 gasoline." Combustion Engines 136, no. 1 (February 1, 2009): 52–59. http://dx.doi.org/10.19206/ce-117220.
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Small aviation develops very dynamically. This is a result of airplane general availability and their lower prices. At the same time, however, the maintenance costs of airplanes increases. It particularly concerns the operation cost where fuel is its substantial part. At the moment special 100LL gasoline is used to fuel aircraft piston engines. It is about 20% more expensive than ES95 gasoline of comparable properties. The paper shows the results of test-bed research conducted on the radial piston aircraft engine fuelled by aircraft 100LL gasoline and automotive ES95 gasoline. The object of research was ASz-62IR engine by WSK Kalisz fitted with an experimental fuel injection system. The power, fuel consumption and cylinder head temperatures were analysed in the selected typical operating points. The testing was carried out in a steady state. It was proven that it is possible to exchange (replace) fuels with no engine power loss with a miniscule increase of fuel consumption.
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Jurecka, Radek, and Karol Bencalik. "AIRPLANES WITH AN ELECTRIC MOTOR." Aviation 16, no. 3 (October 2, 2012): 63–68. http://dx.doi.org/10.3846/16487788.2012.732304.
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With the decreasing supply of fossil fuel, we can see more and more attempts to substitute combustion engines with other sources of propulsion. This article deals with the possibility of using alternative sources of energy in aviation. Namely, it describes the possibilities of the advantages and disadvantages of using hydrogen fuel cells in aviation.
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Serbezov, Vladimir. "NUMERICAL MODELLING OF TURBOFAN ENGINE DETERIORATION AS A FACTOR IN THE AIRLINES FUEL CONSERVATION." Aviation 23, no. 3 (January 29, 2020): 91–96. http://dx.doi.org/10.3846/aviation.2019.11913.
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The boosting of the fuel efficiency of in-service aircraft is an issue of great commercial and ecological importance. One of the ways to achieve this is by adjusting the flight parameters and flight planning to the particular performance level of every single airplane. Main contributors to the aircraft performance deterioration are the aerodynamic and power plant deterioration. In this paper a mathematical modelling approach for the estimation of the effect of turbofan engine deterioration on passenger aircraft performance is proposed. Based on previous flight models developed by the authors, the present model simulates the deterioration of CFM-56-like turbofans on an Airbus A319-like airplane, and makes possible to compare the performance of airplanes with deteriorated and not deteriorated engines over various flight missions. A representative scenario is explored as an illustration. The model can be further developed to include the aerodynamic deterioration of the aircraft as well as other operational factors.
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., Nithyapathi C. "HYDROGEN AS AN ALTERNATIVE FUEL FOR COMMERCIAL AIRPLANES." International Journal of Research in Engineering and Technology 02, no. 04 (April 25, 2013): 476–80. http://dx.doi.org/10.15623/ijret.2013.0204011.
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de Mattos, Bento Silva, Paulo Jiniche Komatsu, and Jesuíno Takachi Tomita. "Optimal wingtip device design for transport airplane." Aircraft Engineering and Aerospace Technology 90, no. 5 (July 2, 2018): 743–63. http://dx.doi.org/10.1108/aeat-07-2015-0183.
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Purpose The present work aims to analyze the feasibility of wingtip device incorporation into transport airplane configurations considering many aspects such as performance, cost and environmental impact. A design framework encompassing optimization for wing-body configurations with and without winglets is described and application examples are presented and discussed. Design/methodology/approach modeFrontier, an object-oriented optimization design framework, was used to perform optimization tasks of configurations with wingtip devices. A full potential code with viscous effects correction was used to calculate the aerodynamic characteristics of the fuselage–wing–winglet configuration. MATLAB® was also used to perform some computations and was easily integrated into the modeFrontier frameworks. CFD analyses of transport airplanes configurations were also performed with Fluent and CFD++ codes. Findings Winglet provides considerable aerodynamic benefits regarding similar wings without winglets. Drag coefficient reduction in the order of 15 drag counts was achieved in the cruise condition. Winglet also provides a small boost in the clean-wing maximum lift coefficient. In addition, less fuel burn means fewer emissions and contributes toward preserving the environment. Practical implications More efficient transport airplanes, presenting considerable lower fuel burn. Social implications Among other contributions, wingtip devices reduce fuel burn, engine emissions and contribute to a longer engine lifespan, reducing direct operating costs. This way, they are in tune with a greener world. Originality/value The paper provides valuable wind-tunnel data of several winglet configurations, an impact of the incorporation of winglets on airplane design diagram and a direct comparison of two optimizations, one performed with winglets in the configuration and the other without winglets. These simulations showed that their Pareto fronts are clearly apart from each other, with the one from the configuration with winglets placed well above the other without winglets. The present simulations indicate that there are always aerodynamic benefits present regardless the skeptical statements of some engineers. that a well-designed wing does not need any winglet.
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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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Goraj, Zdobyslaw. "Design and Optimisation of Fuel Tanks for BWB Configurations." Archive of Mechanical Engineering 63, no. 4 (December 1, 2016): 605–17. http://dx.doi.org/10.1515/meceng-2016-0034.
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Abstract This paper describes assumptions, goals, methods, results and conclusions related to fuel tank arrangement of a flying wing passenger airplane configuration. A short overview of various fuel tank systems in use today of different types of aircraft is treated as a starting point for designing a fuel tank system to be used on very large passenger airplanes. These systems may be used to move fuel around the aircraft to keep the centre of gravity within acceptable limits, to maintain pitch and lateral balance and stability. With increasing aircraft speed, the centre of lift moves aft, and for trimming the elevator or trimmer must be used thereby increasing aircraft drag. To avoid this, the centre of gravity can be shifted by pumping fuel from forward to aft tanks. The lesson learnt from this is applied to minimise trim drag by moving the fuel along the airplane. Such a task can be done within coming days if we know the minimum drag versus CG position and weight value. The main part of the paper is devoted to wing bending moment distribution. A number of arrangements of fuel in airplane tanks are investigated and a scenario of refuelling - minimising the root bending moments - is presented. These results were obtained under the assumption that aircraft is in long range flight (14 hours), CL is constant and equal to 0.279, Specific Fuel Consumption is also constant and that overall fuel consumption is equal to 20 tons per 1 hour. It was found that the average stress level in wing structure is lower if refuelling starts from fuel tanks located closer to longitudinal plane of symmetry. It can influence the rate of fatigue.
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Young, Trevor M. "Fuel-Sensitivity Analyses for Jet and Piston-Propeller Airplanes." Journal of Aircraft 45, no. 2 (March 2008): 715–19. http://dx.doi.org/10.2514/1.27217.
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Labonté, Gilles. "Formulas for the fuel of climbing propeller driven airplanes." Aircraft Engineering and Aerospace Technology 84, no. 1 (January 20, 2012): 23–36. http://dx.doi.org/10.1108/00022661211194951.
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Zelenika, Saša, Zdenek Hadas, Sebastian Bader, Thomas Becker, Petar Gljušćić, Jiri Hlinka, Ludek Janak, et al. "Energy Harvesting Technologies for Structural Health Monitoring of Airplane Components—A Review." Sensors 20, no. 22 (November 22, 2020): 6685. http://dx.doi.org/10.3390/s20226685.
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With the aim of increasing the efficiency of maintenance and fuel usage in airplanes, structural health monitoring (SHM) of critical composite structures is increasingly expected and required. The optimized usage of this concept is subject of intensive work in the framework of the EU COST Action CA18203 “Optimising Design for Inspection” (ODIN). In this context, a thorough review of a broad range of energy harvesting (EH) technologies to be potentially used as power sources for the acoustic emission and guided wave propagation sensors of the considered SHM systems, as well as for the respective data elaboration and wireless communication modules, is provided in this work. EH devices based on the usage of kinetic energy, thermal gradients, solar radiation, airflow, and other viable energy sources, proposed so far in the literature, are thus described with a critical review of the respective specific power levels, of their potential placement on airplanes, as well as the consequently necessary power management architectures. The guidelines provided for the selection of the most appropriate EH and power management technologies create the preconditions to develop a new class of autonomous sensor nodes for the in-process, non-destructive SHM of airplane components.
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Takahashi, Yasutake, Tohru Ishii, Chiaki Todoroki, Yoichiro Maeda, and Takayuki Nakamura. "Fuzzy Control for a Kite-Based Tethered Flying Robot." Journal of Advanced Computational Intelligence and Intelligent Informatics 19, no. 3 (May 20, 2015): 349–58. http://dx.doi.org/10.20965/jaciii.2015.p0349.
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Observation providing information from above is important in in large-scale or dangerous rescue activity. This has been done from balloons or airplanes. Balloon observation requires a gas such as helium and takes a relatively long time to prepare, and while airplane observation can be prepared in a relatively short time and is highly mobile, flight time depends on the amount of fuel a plane can carry. We have proposed and developed a kite-based tethered flying robot that complements balloon and airplane observation while providing a short preparation time and long flight time [1]. The objective of our research is autonomous flight information gathering consisting of a kite, a flight unit, a tether and a ground control unit with a line-winding machine. We propose fuzzy controllers for our robot that are inspired by kite flying.
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Gogolák, László, Sándor Csikós, Tamás Molnár, Péter Szuchy, István Bíró, and József Sárosi. "Possibilities of optimizing fuel consumption in hybrid and electronic airplanes." Analecta Technica Szegedinensia 13, no. 2 (December 3, 2019): 65–76. http://dx.doi.org/10.14232/analecta.2019.2.65-76.
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The automotive industry was always characterized by innovation and the use of cutting edge technology. Daily we can see vehicles packed with technological advancements. The main focus of the current technological trend is electric drives. With the rise in popularity of electric cars more types of vehicles are adapting electric drives. In the case of airplanes the standards are higher than in the case of cars so the emphasis of research and innovation is greater. This paper presents a list of the challenges electric aircrafts face and their potential solutions. Currently many of these problems currently only have partial solutions if any. There is also a comparison between the properties of materials used and the expectations for hybrid aircraft. A comprehensive model was created taking into account the criteria set for hybrid and electric aircraft. With the aid of the model the effect of the most important components on efficiency can be assessed.
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Labonte, Gilles. "Simple formulas for the fuel of climbing propeller driven airplanes." Advances in aircraft and spacecraft science 2, no. 4 (October 25, 2015): 367–89. http://dx.doi.org/10.12989/aas.2015.2.4.367.
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Долгих, В. С. "АНАЛІЗ ОСОБЛИВОСТЕЙ ПРОЕКТУВАННЯ БЕЗПІЛОТНОГО ТРАНСПОРТНОГО ЛІТАКА ЩОДО ПАЛИВНОЇ ЕФЕКТИВНОСТІ." Open Information and Computer Integrated Technologies, no. 89 (March 23, 2021): 81–90. http://dx.doi.org/10.32620/oikit.2020.89.07.
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The unmanned aircraft systems application is in the initial stage, which is characterized by a significant level of unmanned aircraft development and its elements, and by the lack of the basis of unmanned aircraft application in real technological processes. Resolution of this contradiction requires the solution of diverse problems of conceptual, technical, technological, methodological, organizational and legal – normative character.In general, today the unmanned aircraft systems application in the civil field is practically limited by particular cases of local applications in favor of the solution of current production or economic problems, mainly by the experimental procedure. Therefore, the market growth of the unmanned aircraft systems is expected providing the capability of a number of technical and administrative barriers that restrict the use of unmanned aircraft systems in the national airspace. It should also be noted the increasing prevalence of unmanned systems in general transport.This study was motivated by the globally increasing interest in unmanned cargo drones. It was focused particularly on cargo drones based on existing conventional general aviation airplanes and it should be regarded as a preliminary step towards the complex assessment of unmanned cargo aircraft transport systems. The aim was to estimate the fuel efficiency of such drones and to outline the optimums of some of their key design characteristics. A sample of 26 very light and light aircraft, and motorgliders was examined. The data was taken from open sources. The results outline that for best fuel economy the cargo drone should be a composite structure, piston engine airplane with wing aspect ratio of 10 to 12. Fuel efficiency estimation at distances of 500 to 2500 km shows that such cargo drones would be competitive with large piloted commercial cargo airplanes as well as with the road transport.
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Hariyadi, Setyo, Sutardi Sutardi, Wawan Aries Widodo, and Bambang Juni Pitoyo. "Comparative Study of Forward Wingtip Fence and Rearward Wingtip Fence on Wing Airfoil Eppler E562." Journal of Energy, Mechanical, Material, and Manufacturing Engineering 5, no. 1 (May 31, 2020): 25. http://dx.doi.org/10.22219/jemmme.v5i1.11968.
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The perfect wing is a dream that many airplanes has manufactured have been striving to achieve since the beginning of the airplane design. There are some aspect that most influence in aircraft design lift, drag, thrust, and weight. The combination of these aspects leads to a decrease in fuel consumption, which reduces pollution in our atmosphere and increase in economic revenue. One way to improve aircraft performance is to modify the tip of the wing geometry, which has become a common sight on today’s airplanes. With computational programs, the effects on drag due to wingtip devices can be previewed. This research was done numerically by using turbulence model k-ω SST. Reynolds number in this research was 2,34 x 10 4 with angle of attacks are 0o, 2o, 4o, 6o, 8o, 10o, 12o, 15o, 17o and 19o. The model specimen is wing airfoil Eppler 562 with winglets. Two types of wingtips are used: forward and rearward wingtip fence. From this study, it was found that wingtip fence reduced the strength of vorticity magnitude on the x axis compared to plain wings. The leakage of fluid flow effect at the leading edge corner of the wingtip, giving pressure gradient and slightly shifting towards the trailing edge. this occurs in the plain wing and rearward wingtip fence but does not occur in the forward wingtip fence..
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Krile, Srećko, Marina Krile, and Petr Průša. "NON-LINEAR MINI-MAX PROBLEM OF MULTI-STOP FLIGHT ROUTES." TRANSPORT 30, no. 3 (October 2, 2015): 361–71. http://dx.doi.org/10.3846/16484142.2015.1091984.
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The major change in trends of air transport development is to increase operating efficiency, productivity and profitability. Airline companies (air operators or carriers) can ensure significant fuel savings and better utilization of airplanes capacity. So they need better transport planning tool for costs minimization on a voyage route with multiple loading/unloading airports (multi-stop routes).The existing routes can be re-optimized (improved) or alternative routes can be offered instead. In this research the efficient heuristic algorithm for optimal transportation of N different loads (e.g. passenger contingent) for the airplane with limited capacity is being developed. The main goal of algorithm is to reduce the idle capacity on the route, to decrease expenses and to increase revenue. Through many test examples we can see that such approach functions very good and calculation complexity is under control.
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Ashish, Ankan, and S. B. Chougule. "Wireless Flight Data Recorder (FDR) for Airplanes." Advanced Materials Research 433-440 (January 2012): 6663–68. http://dx.doi.org/10.4028/www.scientific.net/amr.433-440.6663.
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This paper is on the urgent need of today’s Aviation Sector which comes smart materials in airplanes. We have made wireless system i.e. a real time Flight Data Recorder (FDR) in which the data(Parameters like Engine Temperature ,Fuel Level, Speed ,Location (Latitude And Longitude)etc. ) getting stored in real time, in the plane’s FDR(commonly known as Black Box), same data will get transferred to our Personal Computer(PC) which is at ground. The data will be transferred via XBEE-RF Module( long range). Also, the Global Positioning System (GPS) device will send the Position coordinates logged by the micro-controller at periodic intervals. After processing the data, the data will be uploaded to the server via the GPRS/Internet Connection. The program resident on the server will process the data and map the position on a digital map. The digital map view can be accessed through and other PC’s using the Protocol, thus giving real time positioning and different parameters of the plane on ground. “This paper focuses on sufficient data for analyzing the air disasters as short term application, and reduction of air disasters as long term goal.”
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Pratt, Joseph W., Leonard E. Klebanoff, Karina Munoz-Ramos, Abbas A. Akhil, Dita B. Curgus, and Benjamin L. Schenkman. "Proton exchange membrane fuel cells for electrical power generation on-board commercial airplanes." Applied Energy 101 (January 2013): 776–96. http://dx.doi.org/10.1016/j.apenergy.2012.08.003.
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Akbas, Ahmed, and Nor Yuliana Yuhana. "Recycling of Rubber Wastes as Fuel and Its Additives." Recycling 6, no. 4 (December 1, 2021): 78. http://dx.doi.org/10.3390/recycling6040078.
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Economic, social, and urban developments generally require improvements in the transportation sector, which includes automobiles such as trucks, buses, trailers, airplanes, and even bicycles. All these vehicles use rubber tires. After consumption, these tires become waste, leading to enlarged landfill areas for used tires and implying additional harm to the environment. This review summarizes the growth of rubber recycling application and the sustainability of using waste rubber in the construction field. Furthermore, we provide methods to convert rubber waste to fuel or fuel additives by using tire-derived fuel and concentrate to pyrolysis, which are environmentally friendly and efficient ways. The related parameters such as temperature, pressure, and feedstock composition were studied. Most research papers observed that 500 °C is the optimal temperature at atmospheric pressure in the presence of a specific type of catalyst to improve pyrolysis rate, oil yield, and quality.
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Evrin, Reza Alizade, and Ibrahim Dincer. "Development and evaluation of an integrated solid oxide fuel cell system for medium airplanes." International Journal of Energy Research 44, no. 12 (July 6, 2020): 9674–85. http://dx.doi.org/10.1002/er.5525.
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Merkys, Bronius. "THE USE OF ELECTRIC POWER IN A LIGHT AIRCRAFT." Mokslas - Lietuvos ateitis 2, no. 6 (December 31, 2010): 110–15. http://dx.doi.org/10.3846/mla.2010.123.
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The article analyzes a possibility of using electric engines and electric power accumulators in very light and ultra light airplanes, considering the achieved electric power keeping level and predictions of development. First of all, the mass of the engine and accumulator is evaluated. At a later stage, it is compared with the mass of the gas engine and fuel. The last step is to find criterions allowing making a decision on how to choose a powerhouse.
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Ji, Zhixing, Jiang Qin, Kunlin Cheng, Fafu Guo, Silong Zhang, and Peng Dong. "Comparative performance analysis of solid oxide fuel cell turbine-less jet engines for electric propulsion airplanes: Application of alternative fuel." Aerospace Science and Technology 93 (October 2019): 105286. http://dx.doi.org/10.1016/j.ast.2019.07.019.
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Panapakidis, Ioannis, Vasiliki-Marianna Sourtzi, and Athanasios Dagoumas. "Forecasting the Fuel Consumption of Passenger Ships with a Combination of Shallow and Deep Learning." Electronics 9, no. 5 (May 8, 2020): 776. http://dx.doi.org/10.3390/electronics9050776.
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An accurate fuel consumption prediction system for transportation units is the pillar that a more efficient fuel management can rely on. This in turn may eventually lead to cost and emission savings for the unit’s owner. Numerous studies have been conducted for predicting the fuel usage in various means of transportation (i.e., airplanes, trucks, and vehicles). However, there is a limited number of researches that focus on passenger ships. These researches involve traditional machine learning models. There is a lack of literature on deep-learning-based forecasting models. The present paper serves as an initial study for exploring the potential of deep learning in day-ahead fuel consumption on a passenger ship. Firstly, a discussion is provided for the parameters that influence the fuel consumption. Secondly, the day-ahead fuel forecasting problem is formulated. To fully examine the influence of exogenous parameters on the consumption, various scenarios are formulated that differ in the types and number of inputs. The proposed forecasting model combines shallow and deep learning. Several machine learning and time series models were compared, and the results indicate the robustness of the proposed approach.
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Wislicenus, Jan, and Nihad E. Daidzic. "Estimation of Transport-Category Jet Airplane Maximum Range and Airspeed in the Presence of Transonic Wave Drag." Aerospace 9, no. 4 (April 2, 2022): 192. http://dx.doi.org/10.3390/aerospace9040192.
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One of the most difficult steps in estimating the cruise performance characteristics of high-subsonic transport-category turbofan-powered airplanes is the estimation of the transonic wave drag. Modern jet airplanes cruise most efficiently in the vicinity of the drag-divergence or drag-rise Mach numbers. In the initial design phase and later when the preliminary wind-tunnel and/or CFD computations and drag polars are known with increased accuracy, a method of estimating cruise performance is needed. In this study, a new semi-empirical transonic wave drag model using modified Lock’s equation was developed. For maximum range cruise estimations, an optimization criterion based on maximizing specific air range was used. The resulting nonlinear equations are of 12th- and 13th-order. Numerical Newton–Raphson nonlinear solvers were used to find real positive roots of such polynomials. The NR method was first tested for accuracy and convergence using known analytical solutions. A methodology for an initial guess was developed starting with the maximum-range cruise Mach without the wave-drag included. This guess resulted in fast quadratic convergence in all computations. Other novel features of this article include a new semi-empirical fuel-flow law, which was also extensively tested. Additionally, a semi-empirical turbofan thrust model usable for a wide range of bypass ratios and the entire flight envelope was developed. Such physics-based semi-empirical model can be used for a wide range of turbofans. The algorithm can be utilized to identify most beneficial input parameter values and combinations for the cruise flight phase. The model represents a powerful tool to estimate important cruise performance airspeeds located in the transonic regime. An intended application is in the conceptual development stages for early design optimizations of future airplanes. It is possible with additional effort to extend existing model capabilities to deal with supersonic transports optimal cruise parameters.
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Arokiasami, Willson Amalraj, Prahlad Vadakkepat, and Abdullah Al Mamun. "Wingbeat Generation for a 15 DOF Flexible-Wing Aerial Vehicle Using Cosine Wave Functions." Unmanned Systems 05, no. 02 (April 2017): 115–27. http://dx.doi.org/10.1142/s230138501750008x.
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Birds and conventional airplanes control their flight in a different manner. Conventional airplanes maneuver themselves by means of moving surfaces, while birds can bend, twist and deform their wings and adapt to unforeseen conditions such as wind gusts. However, if planes can do exactly as the birds do they can gain agility, more lift, less drag while consuming less fuel. This work aims to address this issue. Therefore, approaches of wingbeat generation for a 15 DOF flexible-wing aerial vehicle are developed in this paper. A computationally cost-effective cosine wave function-based algorithm that computes a set of wingbeats enabling the aerial vehicle to follow a desired trajectory in a realistic manner is discussed. The flexible-wing aerial vehicle is modeled similar to a seagull with an articulated skeleton. Motion of the aerial vehicle is simulated by applying joint torques and aerodynamic forces over a period of time in forward dynamics simulation. Wing and tail feather motions generate lift in the aerial vehicle, which makes it possible for the aerial vehicle to trace predefined paths. The solidworks mechanical design is used as input into Matlab SimMechanics for visualization. The results are promising for the construction of bird-like aerial vehicles.
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Lang, Michael, Corinna Auer, Paul Jentsch, and Tilman Weckesser. "SOFC Stacks for Mobile Applications." Materials Science Forum 638-642 (January 2010): 1170–75. http://dx.doi.org/10.4028/www.scientific.net/msf.638-642.1170.
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Solid Oxide Fuel Cells (SOFCs) are gaining more and more importance as auxiliary power units (APU), e.g. for passenger cars, trucks and airplanes. In this context, the main challenge is the development of SOFC stacks, which fulfill the strong requirements for mobile applications. These are a low weight, a low volume, and a high power density with reformate gases but also low long term degradation rates. The paper presents results of investigations of SOFC short stacks for mobile applications. Therefore, a light weight stack design was developed in an industrial consortium in cooperation with the German Aerospace Center (DLR) in Stuttgart and the Research Center Jülich (FZJ). The SOFC stacks were operated at different temperatures, varying fuel gas compositions and different fuel gas flow rates. The short stacks were electrochemically characterized mainly by long-term measurements, by current-voltage measurements and by impedance spectroscopy. The fuel utilizations and the power densities were determined. In order to analyze the uniformity inside the stacks, the electrochemical behaviour of the individual cassettes were analyzed and compared to each other. Finally, the degradation rates and the degradation mechanisms were determined from the long-term measurements.
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Jarry, Thomas, Fabien Lacressonnière, Amine Jaafar, Christophe Turpin, and Marion Scohy. "Modeling and Sizing of a Fuel Cell—Lithium-Ion Battery Direct Hybridization System for Aeronautical Application." Energies 14, no. 22 (November 16, 2021): 7655. http://dx.doi.org/10.3390/en14227655.
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Nowadays, many aircraft manufacturers are working on new airplanes to reduce the environmental footprint and therefore meet greenhouse gas reduction targets. The concept of more electric aircraft is one of the solutions to achieve this goal. For this aircraft architecture, several electrical devices are used in order to supply propulsive and non-propulsive functions. This paper focuses on the sizing of a direct hybridization system to supply a non-propulsive function in an aircraft. It is composed of a High-Temperature Proton Exchange Membrane Fuel Cell (HT-PEMFC) and a lithium-ion (Li-ion) battery. This sizing is based on a static model of each storage device. The accuracy of these models is compared with dynamic models during a simulation for an aeronautical mission. Static models are implemented in a genetic algorithm to achieve two goals: on the one hand, satisfy the mission profile, and on the other hand, minimize the mass of the system. Other criteria, such as battery and fuel cell aging estimation, are considered. The obtained results show that the direct hybridization system allows protecting the fuel cell against an accelerated aging.
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Hien, Lai Thuy, Pham Thi Hang, Vuong Thi Nga, Hoang Hai, Nobuyasu Yamaguchi, and Katsuji Tani. "MICROBIAL DIVERSITY IN TRACE WATER OF JET FUEL IN VIETNAM." ASEAN Journal on Science and Technology for Development 25, no. 2 (November 22, 2017): 303–12. http://dx.doi.org/10.29037/ajstd.260.
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Microorganisms in petroleum product, including jet fuel, have been found by some English andAmerican authors since the 20’s of the last century. In 1958, after Bakanaukas isolated many microorganisms in jet fuel JP4, this topic was especially concentrated. Most of microorganisms living in jet fuel are able to degrade hydrocarbon of the fuel to obtain energy and carbon source for their growth. The presence of microorganisms in jet fuel not only brings about the lost of fuel in store process, but also briefly changes the component and structure of jet fuel. Moreover, the products of their metabolism, such as organic acids, alcohols, H2S are corrosive. Hence, they cause many problems for fuel reservoirs and tanks, leak plugging pipelines. Besides, filter system and plugging pipeline can become obstructed because of microorganisms’ biomass. This influences the plane safety. Therefore, many countries in the world consider microorganisms criteria as an important standard to estimate the jet fuel quality. From 1985 to 1990, in our country, Vietnam, there were some science projects about microorganisms in TC1 fuel. At the present, as all country in Asia, Vietnam used to utilize and import hundred tons of jet A1. Tropical climate of Vietnam is the suitable condition for growing of microorganisms. With C8-C18 alkane chains, jet fuel is carbon source for a lot of microorganisms, especially bacteria and fungi, which harmfully affect plane safety. Therefore, we aimed Vietnam airlines company to control the number of microorganisms in jet fuel of all Vietnam airplanes, as well as study on the diversity of microorganisms in trace water in fuel samples, looking for the reason why filter is obstructed to contribute to the jet fuel storing and safety in Vietnam.
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Roldan, P. S., I. L. Alcântara, J. C. Rocha, C. C. F. Padilha, and P. M. Padilha. "Determination of Copper, Iron, Nickel and Zinc in fuel kerosene by FAAS after adsorption and pre-concentration on 2-aminothiazole-modified silica gel." Eclética Química 29, no. 2 (2004): 33–40. http://dx.doi.org/10.1590/s0100-46702004000200005.
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Silica gel chemically modified with 2-Aminotiazole groups, abbreviated as SiAT, was used for preconcentration of copper, zinc, nickel and iron from kerosene, normally used as a engine fuel for airplanes. Surface characteristics and surface area of the silica gel were obtained before and after chemical modification using FT-IR, Kjeldhal and surface area analysis (B.E.T.). The retention and recovery of the analyte elements were studied by applying batch and column techniques. The experimental parameters, such as shaking time in batch technique, flow rate and concentration of the eluent (HCl- 0.25-2.00 mol L-1) and the amount of silica, on retention and elution, have been investigated. Detection limits of the method for copper, iron, nickel and zinc are 0.77, 2.92, 1.73 and 0.097 mg L-1, respectively. The sorption-desorption of the studied metal ions made possible the development of a preconcentration method for metal ions at trace level in kerosene using flame AAS for their quantification.
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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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Лось, Александр Васильевич. "ОСОБЛИВОСТІ ОЦІНКИ ПАЛИВНОЇ ЕФЕКТИВНОСТІ МОДИФІКАЦІЙ ЛІТАКІВ З БАГАТОДВИГУНОВИМИ СИЛОВИМИ УСТАНОВКАМИ." Open Information and Computer Integrated Technologies, no. 86 (February 14, 2020): 117–26. http://dx.doi.org/10.32620/oikit.2019.86.08.
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When creating modifications of transport category airplanes, fuel efficiency appears in the structure of their parameters.This indicator is very important, since operating costs largely depend on the amount of fuel consumed per unit of work.The problem of evaluating the fuel efficiency of modifications of transport aircraft with multi-engine power plants is considered. It is noted that multi-engine power plants, used mainly on medium and heavy aircraft, contribute to solving a number of problematic issues:– expanding the ability to operate in hot climates and highlands;– improving operational safety in the event of failure of one or two engines in case of deterioration of take-off/landing conditions, runway conditions, icing conditions and other emergency situations requiring increased thrust-to-weight ratio;– expanding the network of airfields used by reducing the sites of continued or interrupted take-off;– the absence of the need to use on the created modification more powerful engines, domestic or foreign, which do not have forced (emergency) operating modes.– However, the use of forced-mode engines in such power plants leads to a deterioration in fuel efficiency of up to 20 percent.For the preliminary design stage of modifications, a model is proposed for the formation of a fuel efficiency parameter while simultaneously replacing the main engines and changes in the wing geometry, which allows reducing fuel consumption for the flight, and thereby compensating for its losses when using emergency modes.This approach was implemented in the process of development of the An-188 operational tactical military transport aircraft, in which the replacement of 4 theater with 4 turbojet engines was coordinated with the necessary changes in the wing geometry, which allowed the military-technical complex to ensure fuel consumption in horizontal flight mode with maximum payload 154 g/t∙km per unit of useful work, i.e., lower than that of competitors-analogues.
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Khalili, Siavash, Eetu Rantanen, Dmitrii Bogdanov, and Christian Breyer. "Global Transportation Demand Development with Impacts on the Energy Demand and Greenhouse Gas Emissions in a Climate-Constrained World." Energies 12, no. 20 (October 12, 2019): 3870. http://dx.doi.org/10.3390/en12203870.
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The pivotal target of the Paris Agreement is to keep temperature rise well below 2 °C above the pre-industrial level and pursue efforts to limit temperature rise to 1.5 °C. To meet this target, all energy-consuming sectors, including the transport sector, need to be restructured. The transport sector accounted for 19% of the global final energy demand in 2015, of which the vast majority was supplied by fossil fuels (around 31,080 TWh). Fossil-fuel consumption leads to greenhouse gas emissions, which accounted for about 8260 MtCO2eq from the transport sector in 2015. This paper examines the transportation demand that can be expected and how alternative transportation technologies along with new sustainable energy sources can impact the energy demand and emissions trend in the transport sector until 2050. Battery-electric vehicles and fuel-cell electric vehicles are the two most promising technologies for the future on roads. Electric ships and airplanes for shorter distances and hydrogen-based synthetic fuels for longer distances may appear around 2030 onwards to reduce the emissions from the marine and aviation transport modes. The rail mode will remain the least energy-demanding, compared to other transport modes. An ambitious scenario for achieving zero greenhouse gas emissions by 2050 is applied, also demonstrating the very high relevance of direct and indirect electrification of the transport sector. Fossil-fuel demand can be reduced to zero by 2050; however, the electricity demand is projected to rise from 125 TWhel in 2015 to about 51,610 TWhel in 2050, substantially driven by indirect electricity demand for the production of synthetic fuels. While the transportation demand roughly triples from 2015 to 2050, substantial efficiency gains enable an almost stable final energy demand for the transport sector, as a consequence of broad electrification. The overall well-to-wheel efficiency in the transport sector increases from 26% in 2015 to 39% in 2050, resulting in a respective reduction of overall losses from primary energy to mechanical energy in vehicles. Power-to-fuels needed mainly for marine and aviation transport is not a significant burden for overall transport sector efficiency. The primary energy base of the transport sector switches in the next decades from fossil resources to renewable electricity, driven by higher efficiency and sustainability.
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Khan Ankur, Atiquzzaman, Stefan Kraus, Thomas Grube, Rui Castro, and Detlef Stolten. "A Versatile Model for Estimating the Fuel Consumption of a Wide Range of Transport Modes." Energies 15, no. 6 (March 18, 2022): 2232. http://dx.doi.org/10.3390/en15062232.
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The importance of a flexible and comprehensive vehicle fuel consumption model cannot be understated for understanding the implications of the modal changes currently occurring in the transportation sector. In this study, a model is developed to determine the tank-to-wheel energy demand for passenger and freight transportation within Germany for different modes of transport. These modes include light-duty vehicles (LDVs), heavy-duty vehicles (HDVs), airplanes, trains, ships, and unmanned aviation. The model further estimates future development through 2050. Utilizing standard driving cycles, backward-looking longitudinal vehicle models are employed to determine the energy demand for all on-road vehicle modes. For non-road vehicle modes, energy demand from the literature is drawn upon to develop the model. It is found that various vehicle parameters exert different effects on vehicle energy demand, depending on the driving scenario. Public transportation offers the most energy-efficient means of travel in the forms of battery electric buses (33.9 MJ/100 pkm), battery electric coaches (21.3 MJ/100 pkm), fuel cell electric coaches (32.9 MJ/100 pkm), trams (43.3 MJ/100 pkm), and long-distance electric trains (31.8 MJ/100 pkm). International shipping (9.9 MJ/100 tkm) is the most energy-efficient means of freight transport. The electrification of drivetrains and the implementation of regenerative braking show large potential for fuel consumption reduction, especially in urban areas. Occupancy and loading rates for vehicles play a critical role in determining the energy demand per passenger-kilometer for passenger modes, and tonne-kilometer for freight modes.
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Lü, Zhi, Zhan Gao, and Yi Lü. "A Flight Simulator that Grouping Aircrafts Simultaneously Take off and Land in Open Grid Computing Environment." Applied Mechanics and Materials 182-183 (June 2012): 1292–97. http://dx.doi.org/10.4028/www.scientific.net/amm.182-183.1292.
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The performance of airplane in commercial airline environment is determined by, and therefore an indicator of performance measure of, the thermodynamic properties of airplane. The aim of this study was to establish the use of simulators to determine aircraft accident for a flight of airplanes and evaluate the potential of new airspace structure and airport’s runway. This indicates that there is a possibility of obtaining airplane performance from analysis and verification simulating airplane. As compared with AIRBUS Full Flight Simulator, a multiple aircrafts flight simulator that grouping aircrafts simultaneously take off and land was presented, which is basis on a parallel distributed computing in Open Grid Computing Environment (OGCE), and service oriented architecture (SOA) of software in multiple aircraft simulator, the performance of collaborative flight of multiple aircrafts is evaluated.
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Boggero, Luca, Marco Fioriti, and Sabrina Corpino. "Development of a new conceptual design methodology for parallel hybrid aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 3 (December 14, 2017): 1047–58. http://dx.doi.org/10.1177/0954410017745569.
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In this paper, an innovative methodology for the conceptual design of hybrid-powered airplanes is proposed. In particular, this work focuses on parallel hybrid architectures, in which the thermal engine is mechanically coupled to an electric motor, both supplying propulsive power during a limited number of flight phases, e.g. during takeoff and climb. This innovative solution is the subject of several studies being carried out since the current decade. In this paper, a brief overview of the works conducted by other researchers is provided. Then, an overall aircraft design methodology is proposed, which is derived from the most renewed design algorithms. The original contribution of this work is represented by the development of a methodology for the design of hybrid propulsion systems. Moreover, the proposed method is integrated within a global aircraft design methodology. In particular, several effects of the innovative system on the entire aircraft are considered, for instance the variation of the empty mass or the impacts on fuel consumption. The paper ends with some case studies of the proposed design methodology, and a discussion of the obtained results is provided.
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Liu, Yuxin. "Status and prospect of feasibility study on all electric commercial aircraft." Highlights in Science, Engineering and Technology 27 (December 27, 2022): 870–74. http://dx.doi.org/10.54097/hset.v27i.3860.
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Earth’s temperature has risen violently since 1981 which was more than twice before 1980. People believe that human activities increased the concentration of carbon dioxide and other gas in atmosphere resulting in a sharp rise in temperature over the decades which is called Greenhouse Effect. The Greenhouse Effect has become a risk of our survival. Glaciers are melting year by year which leads to flooding of coastal areas and countries like Maldives are under the risk of being submerged. The drought is also one of the consequences, high temperature triggered by Greenhouse throughout whole year especially in summer dries out the sources of water like rivers, lakes. This will lead us some other problems in shipping, irritations, power systems and other industries that are critical to human’s survival. With the development and growth of aviation, the problems tend to be more crucial. Governors have been trying to make plans to use renewable and sustainable fuel on aircrafts. The hard part is still about the electric engines that can be used on the giant airplanes.
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Bloch, Jens Hundevad, Krzysztof Janko, Thomas Thessen, Ole B. Jensen, and Claus Lassen. "Not all hubs are made equal: A case study of airport governance in Europe." European Urban and Regional Studies 28, no. 3 (March 5, 2021): 241–62. http://dx.doi.org/10.1177/0969776421998727.
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The entire aviation industry was severely hit by the COVID-19 pandemic, leaving airplanes stranded and airports empty of the usual hustle. While the full consequences of this crisis are yet unknown, it only adds fuel to the ongoing debates about the future of the aviation sector, including airport capacity and environmental challenges facing many hub airports around Europe. While conventional aviation research describes the development of hub airports as a function of varying geo-economic variables, this research sheds light on the societal underpinnings of the makings of hub airports. From an airport governance perspective, a case study of four European hub airports, representing both expanding and struggling hubs, was conducted. Based on interviews with 31 airport stakeholders from four different countries (i.e. Belgium, Finland, the Netherlands and Switzerland) as well as a review of strategic and policy documents, the authors argue that the development of hub airports and their corresponding governance models is a non-linear process, informed to a great degree by societal and discursive factors. The authors conclude that developing and sustaining a well-functioning hub airport that supports regional development necessitates an active stance from local, regional and national authorities. A clear and strategic governance model is needed, one that is not limited to ownership and regulation questions, but one that guarantees a wide-ranging consensus among airport stakeholders. Finally, the paper provides a perspective on future potentials and challenges facing European hub airports.
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Federico, Cecchini, Cherubini Valeria, Francesco Fabbrocino, and Francesca Nanni. "Novel Approach to The Design of Sound Insulating Composites by Means of a Non-linearly Extrapolated Master Curve." Open Materials Science Journal 12, no. 1 (June 29, 2018): 14–28. http://dx.doi.org/10.2174/1874088x01812010014.
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Background:The increasing use of composite structures with a high stiffness-to-weight ratio in commercial vehicles has brought about a reduction in fuel consumption but, on the other hand, has significantly increased noise transmission particularly in case of thin and lightweight structures. Noise is a primary issue for commercial vehicles, such as airplanes, helicopters and cars. The present research deals with the use of smart materials, as Shear-Thickening Fluids (STF, or dilatants) in view of manufacturing elements with increased sound insulation properties.Methods:The response of a sandwich material with the STF core was investigated both experimentally and numerically, by choosing the Sound Transmission Loss (STL) of the composite structure as the figure of merit.The experimental investigation was focused on the manufacturing of a sandwich structure made of metallic skins and a STF core that was successively characterized by sound insertion loss measurement.The numerical investigation was carried out by using a Generalized Transfer Matrix Method (GTMM) and a Statistical Energy Analysis (SEA) in view of selecting the fluid capable of granting the highest acoustic transmission loss.Results:Finally, the test results were compared to the numerical results, showing a noticeable agreement. The used STF showed increasing viscosity at increasing shear rates.
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Ribeiro, A. L. A., N. Mastelari, and C. A. Cimini. "Low-Cost System to Evaluate Impact Localization in Composite Plates." Key Engineering Materials 627 (September 2014): 17–20. http://dx.doi.org/10.4028/www.scientific.net/kem.627.17.
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The development of composite materials has been following a growing trend, with its use ranging from sporting goods to construction materials and defense. The aerospace industry in particular has observed a minute increase in demand for these materials, since the associated weight reductions promise significant savings in fuel related costs. Composite materials, however, are prone to important and very specific failure modes which are invisible to the naked eye (e.g., delaminations, fiber ruptures, debondings) and occur in response to everyday events such as impacts. Thus, usage of these materials in critical areas of airplanes (e.g. wings and fuselage) is subject to the development of technologies able to continuously and precisely monitor existence, type and extent of failures. Impact localization plays a key role within this paradigm allowing identification of hot spots, that is, areas subjected to potentially damaging phenomena, for further analysis. Several such techniques have already been developed, but anisotropy, precision, robustness and cost are common drawbacks amongst their implementation. The present study was directed to the use of conditioned piezoelectric sensors along with low cost commercial off-the shelf data acquisition system to implement a reliable impact localization method.
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Донець, Олександр Дмитрович, Олександр Іванович Семенець, Євген Тимофійович Василевський, Олександр Григорович Гребеніков, and Андрій Михайлович Гуменний. "КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ РІШЕННЯ ЗАБЕЗПЕЧЕННЯ СТАТИЧНОЇ МІЦНОСТІ ТА РЕСУРСУ РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ." Open Information and Computer Integrated Technologies, no. 82 (December 19, 2018): 4–26. http://dx.doi.org/10.32620/oikit.2018.82.01.
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Ensuring flight safety and aircraft structure lifetime is important today’s problem in development of up-to-date regional passenger aircraft. This paper deals with the aspects of providing static strength and lifetime of regional passenger aircraft. A series of factors and parameters were analyzed, which affect the aircraft static strength, lifetime, such as: fatigue, corrosion, wear, fretting-corrosion, human factor.n To ensure static strength, operational and design loads were determined for the entire range of design speeds and flight altitudes, overloads, aircraft weights and CG positions, fuel weight, cargo weight and various possible combinations of their distribution, taking into account the following: dynamic load and elastic characteristics of the aircraft’s design flying in disturbed air and while landing; dynamic load of the control system structure during maneuvering and under wind gusts; failures and malfunctions of systems that directly affect the strength characteristics. The results of flight tests showed that the An-148 100 / An-158 typical structure under the terms of static strength does not have features and parts that create emergency conditions or are unreliable, and confirmed the correctness of the choice of the established operational limitations presented for inclusion in the Flight Operation Manual. Conditions for operation of the An-148-100 / An-158 family during a design life of 30 years were determined on the basis of a comparative analysis of the corrosion resistance of the aircraft structures, whose service life exceeds 30 years. An-148-100 / An-158 airplanes are designed and manufactured in all-climate version in compliance with all the requirements for anti-corrosion protection. The aircraft used design and technological solutions to protect against loss of strength during operation from weathering, corrosion and abrasion, which allowed to state that the main power elements of the An-148-100 / An-158 aircraft typical structure are protected from reduction or loss of strength in operation for any reason, including weathering, corrosion and abrasion, as well as adequate ventilation and drainage. The provision of static strength and lifetime of regional passenger aircraft is confirmed by static, fatigue and flight tests of airplanes, reflected in technical reports with regard to strength, lifetime and service life of the An-148-100 / An-158 aircraft.
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Tasca, Andrea Luca, Vittorio Cipolla, Karim Abu Salem, and Monica Puccini. "Innovative Box-Wing Aircraft: Emissions and Climate Change." Sustainability 13, no. 6 (March 16, 2021): 3282. http://dx.doi.org/10.3390/su13063282.
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The PARSIFAL project (Prandtlplane ARchitecture for the Sustainable Improvement of Future AirpLanes) aims to promote an innovative box-wing aircraft: the PrandtlPlane. Aircraft developed adopting this configuration are expected to achieve a payload capability higher than common single aisle analogues (e.g., Airbus 320 and Boeing 737 families), without any increase in the overall dimensions. We estimated the exhaust emissions from the PrandtlPlane and compared the corresponding impacts to those of a conventional reference aircraft, in terms of Global Warming Potential (GWP) and Global Temperature Potential (GTP), on two time-horizons and accounted for regional sensitivity. We considered carbon dioxide, carbonaceous and sulphate aerosols, nitrogen oxides and related ozone production, methane degradation and nitrate aerosols formation, contrails, and contrail cirrus. Overall, the introduction of the PrandtlPlane is expected to bring a considerable reduction of climate change in all the source regions considered, on both the time-horizons examined. Moreover, fuel consumption is expected to be reduced by 20%, as confirmed through high-fidelity Computational Fluid Dynamics (CFD) simulations. Sensitivity of data, models, and metrics are detailed. Impact reduction and mitigation strategies are discussed, as well as the gaps to be addressed in order to develop a comprehensive Life Cycle Assessment on aircraft emissions.
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Ciliberti, Danilo, Pierluigi Della Vecchia, Vittorio Memmolo, Fabrizio Nicolosi, Guido Wortmann, and Fabrizio Ricci. "The Enabling Technologies for a Quasi-Zero Emissions Commuter Aircraft." Aerospace 9, no. 6 (June 12, 2022): 319. http://dx.doi.org/10.3390/aerospace9060319.
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The desire for greener aircraft pushes both academic and industrial research into developing technologies, manufacturing, and operational strategies providing emissions abatement. At time of writing, there are no certified electric aircraft for passengers’ transport. This is due to the requirements of lightness, reliability, safety, comfort, and operational capability of the fast air transport, which are not completely met by the state-of-the-art technology. Recent studies have shown that new aero-propulsive technologies do not provide significant fuel burn reduction, unless the operational ranges are limited to short regional routes or the electric storage capability is unrealistically high, and that this little advantage comes at increased gross weight and operational costs. Therefore, a significant impact into aviation emissions reduction can only be obtained with a revolutionary design, which integrates disruptive technologies starting from the preliminary design phase. This paper reviews the recent advances in propulsions, aerodynamics, and structures to present the enabling technologies for a low emissions aircraft, with a focus on the commuter category. In fact, it is the opinion of the European Community, which has financed several projects, that advances on the small air transport will be a fundamental step to assess the results and pave the way for large greener airplanes.
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Kolecki, J., M. Prochaska, Z. Kurczyński, P. Piątek, and J. Baranowski. "DEVELOPING THE STABILIZED MAPPING SYSTEM FOR THE GYROCOPTER – REPORT FROM THE FIRST TESTS." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLI-B1 (June 2, 2016): 31–36. http://dx.doi.org/10.5194/isprsarchives-xli-b1-31-2016.
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The LiDAR mapping carried out using gyrocopters provides a relatively cheap alternative for traditional mapping involving airplanes. The costs of the fuel and the overall maintenance are much lower when compared to planes. At the same time the flight kinematics of the gyrocopter makes it an ideal vehicle for corridor mapping. However a limited payload and a strongly limited space prevent using stabilized platforms dedicated for aerial photogrammetry. As the proper stabilization of the laser scanner during the flight is crucial in order to keep the desirable quality of the LiDAR data, it was decided to develop the prototype of the stabilized, ultra-light mapping platform that can meet the restricted requirements of the gyrocopter. The paper starts with the brief discussion of the legal and practical aspects of the LiDAR data quality, dealing mostly with the influence of the flight imperfections on the point pattern and point density. Afterwards the mapping system prototype is characterized, taking into account three main components: stabilized platform, sensors and control. Subsequently first in-flight tests are described. Though the data are still not perfect mostly due to vibrations, the stabilization provides a substantial improvement of their geometry, reducing both roll and pitch deflections.
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Kolecki, J., M. Prochaska, Z. Kurczyński, P. Piątek, and J. Baranowski. "DEVELOPING THE STABILIZED MAPPING SYSTEM FOR THE GYROCOPTER – REPORT FROM THE FIRST TESTS." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLI-B1 (June 2, 2016): 31–36. http://dx.doi.org/10.5194/isprs-archives-xli-b1-31-2016.
Full textAbstract:
The LiDAR mapping carried out using gyrocopters provides a relatively cheap alternative for traditional mapping involving airplanes. The costs of the fuel and the overall maintenance are much lower when compared to planes. At the same time the flight kinematics of the gyrocopter makes it an ideal vehicle for corridor mapping. However a limited payload and a strongly limited space prevent using stabilized platforms dedicated for aerial photogrammetry. As the proper stabilization of the laser scanner during the flight is crucial in order to keep the desirable quality of the LiDAR data, it was decided to develop the prototype of the stabilized, ultra-light mapping platform that can meet the restricted requirements of the gyrocopter. The paper starts with the brief discussion of the legal and practical aspects of the LiDAR data quality, dealing mostly with the influence of the flight imperfections on the point pattern and point density. Afterwards the mapping system prototype is characterized, taking into account three main components: stabilized platform, sensors and control. Subsequently first in-flight tests are described. Though the data are still not perfect mostly due to vibrations, the stabilization provides a substantial improvement of their geometry, reducing both roll and pitch deflections.
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Kretov, Anatolii, and Dmytro Tiniakov. "EVALUATION OF WING STRUCTURES AT THE CONCEPTUAL STAGE OF TRANSPORT CATEGORY AIRCRAFT PROJECTS." Aviation 26, no. 4 (December 9, 2022): 235–43. http://dx.doi.org/10.3846/aviation.2022.18041.
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The purpose of this research is to improve the approach for evaluating of new design solutions based on sensitivity analysis of takeoff mass (SFM) to initial changes in the basic project. The approach is based on the changes assessment in maximum takeoff mass of a developed project or an already existed basic variant of an aircraft with local design (project) changes, including the aerodynamic ones, that ensure the developing of a more advanced aircraft. In comparison with the existed known approaches based on the mass growth factors, which were considered constant, the proposed approach takes into account more exactly the dependence of the takeoff mass on the initial local change in mass in terms of their functional purpose, as well as the aerodynamic characteristics. This approach allows the designer to calculate more precisely the final maximum takeoff mass changes in the early (preliminary) stages of conceptual design when looking for new design solutions. On numerical examples, carried out on the examples of transport category airplanes, a significant dependence of the wing aspect ratio influence on fuel efficiency is shown. The considered approach using SFM with semi-analytical aerodynamic analysis combination is simple, reliable and convenient in the analysis and synthesis of a new project for the design process based on the base variant.
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Лось, Александр Васильевич, Виктор Иванович Рябков, and Татьяна Николаевна Середа. "ПРОБЛЕМЫ СОЗДАНИЯ САМОЛЕТОВ ТРАНСПОРТНОЙ КАТЕГОРИИ С УЧЕТОМ ЭКОЛОГИЧЕСКИХ ОГРАНИЧЕНИЙ." Aerospace technic and technology, no. 7 (August 31, 2020): 5–11. http://dx.doi.org/10.32620/aktt.2020.7.01.
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With the growth of air transportation on airplanes of the transport category, their negative impact on the environment and humans increases.The environmental impact of civil aviation began to be addressed in the early 70s of the 20th century. There are three critical areas of impact: the surface layer of the atmosphere, where aerodrome emission is important, the upper troposphere at an altitude of about 10 km, where cruise flights of civilian aircraft take place, and not so long ago, the lower stratosphere (10…22 km), where, as expected, must be cruising the flight of supersonic transport of the future. In the first zone, the effect is direct damage to human health. In the second, aviation affects climate change. In the third zone, the ozone layer may be depleted as a result of aviation exposure.ICAO has established strict restrictions on all types of harmful effects, which are stipulated in our country in AP-25 and AP-36. It is noted that these requirements are constantly being tightened, as a result of which the noise level of the world fleet of aircraft over the past half-century has decreased by more than 30 percent.The article discusses the scheme of creating an aircraft taking into account environmental restrictions and economic costs to the level of decision-making on these problematic issues.The implementation of this approach in domestic aircraft construction is the creation of its modification, the An-132D, based on the An-32B aircraft. With an increase in the carrying capacity and range of this modification by re-arranging the wing-tail + tail assembly system of bearing surfaces, as well as replacing the power plant, it was possible to significantly reduce the fuel efficiency of this modification to 222 g / t km, which is the highest indicator for light vehicles airplanes. This means that An-132D has the least impact on greenhouse gas emissions and emissions.Besides, An-132D has several other advantages:- variable revolutions of the propeller Nвв = 850 … 1200 rpm;- “silent taxiing” at Nвв = 850 rpm within the aerodrome;- emergency operation of the main engine in case of failure of one of the two, not only during take-off but also, if necessary, on the route;- significantly better environmental indicators for harmful emissions of the marching engine and noise on the ground.An-132D is an implemented example of creating a transport category aircraft taking into account environmental restrictions.
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Arzu Mustafazade, Arzu Mustafazade. "CLASSIFICATION OF OPTIMIZATION TASKS FOR REFINERIES." PIRETC-Proceeding of The International Research Education & Training Centre 19, no. 02 (May 18, 2022): 04–07. http://dx.doi.org/10.36962/piretc19022022-04.
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Optimizing oil refineries to meet current market and regulatory demands poses significant challenges for today’s oil industry. Environmental standards make new projects more costly and complex. All operations must reduce air pollution emissions (NOX), which means costly upgrades to existing installations. The low sulfur fuel demand increases the value of the hydrogen required for its production. Competitive printing demands high performance with maximum security and production flexibility. 50 % ratio of streams passing through hydro processors for conversion, processing, and pretreatment at US refineries to total streams. Hydrodesulphurization is the largest application of catalytic technology in terms of volume of material processed. Accurate and reliable measurement of crude oil distillation columns; Calculating yield is critical for achieving production goals, planning and programming. The feed rate should be maximized while ensuring that the crude oil mixture meets environmental requirements. Furthermore, errors in measurements can result in costly downtime or out-of-spec products. The purpose of the refining process is to convert crude oil, which is a natural raw material, into salable products. Products from refineries include cars, trucks, airplanes, ships and fuel for other vehicles, fuel for heat and power generation for industrial, and domestic use, raw materials, lubricating oils, waxes, bitumen for the petrochemical and chemical industry. Special products such as energy, heat (steam), also power (electricity) can be grouped as by-products. For the production of petroleum products, raw materials are processed at different distillation plants. crude oil of these processing units, which transform them into products with the help of supporting units and facilities. This combination is called refining. Market demand for the product type, available raw quality and the requirements set by the authorities include the size, configuration, and configuration of a refinery. Affect its complexity. Since these factors vary from region to region, the facility structures of refineries are also different. These are the basic production departments, process units and auxiliary facilities of the refineries.