Relevant bibliographies by topics / Airplanes, fuel

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Airplanes, fuel'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 January 2023

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Journal articles on the topic "Airplanes, fuel"

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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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Dissertations / Theses on the topic "Airplanes, fuel"

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Ciaravino, John S. "Study of hydrogen as an aircraft fuel." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5FCiaravino.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 2003.
Thesis advisor(s): Oscar Biblarz, Garth Hobson. Includes bibliographical references (p. 45-47). Also available online.
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Bradley, Thomas Heenan. "Modeling, design and energy management of fuel cell systems for aircraft." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/26592.

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Thesis (Ph.D)--Mechanical Engineering, Georgia Institute of Technology, 2009.
Committee Chair: Parekh, David; Committee Member: Fuller, Thomas; Committee Member: Joshi, Yogendra; Committee Member: Mavris, Dimitri; Committee Member: Wepfer, William. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Xie, Tieling. "Electrochemical corrosion effects of ethanol based fuel on general aviation aircraft fuel system components." Diss., Mississippi State : Mississippi State University, 2004. http://library.msstate.edu/etd/show.asp?etd=etd-11072004-122317.

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Matherne, Ray P. "Fuel savings through aircraft modification : a cost analysis /." Wright-Patterson Air Force Base, Ohio : Ft. Belvior, VA : Alexandria, Va. : Air Force Institute of Technology, Graduate School of Engineering and Management (AFIT/EN) ; Available to the public through the Defense Technical Information Center ; National Technical Information Service [distributor], 2009. http://www.dtic.mil/dtic/.

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Thesis (M.S. in Logistics)--Department of Operational Sciences, Graduate School of Engineering and Management, Air Force Institute of Technology, Air University, Air Education and Training Command, June 2009.
"June 2009." Thesis advisor: Dr. James T. Moore. Performed by the Air Force Institute of Technology, Graduate School of Engineering and Management (AFIT/EN), Wright-Patterson Air Force Base, Ohio. "Presented to the Faculty Department of Operational Sciences, Graduate School of Engineering and Management, Air Force Institute of Technology, Air University, Air Education and Training Command In Partial Fulfillment of the Requirements for the Degree of Master of Logistics, June 2009."--P. [ii]. "AFIT/IMO/ENS/09-07." Includes bibliographical references. Also available online from the Air University Research Information Management System Web site and the DTIC Online Web site.
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Compton, Timothy James Shauck Maxwell Eustace. "Flight performance testing of ethanol/100LL fuel blends during cruise flight." Waco, Tex. : Baylor University, 2008. http://hdl.handle.net/2104/5150.

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Rawson, Paul Stansfield Christy-Anne. "Field method for detection of metal deactivator additive in jet fuel." Fishermans Bend, Victoria : Defence Science and Technology Organisation, 2009. http://nla.gov.au/nla.arc-24592.

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Kwan, Pok Wang. "Flow management in heat exchanger installations for intercooled turbofan engines." Thesis, University of Oxford, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.711622.

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Davis, James Arthur. "Acoustic-vortical-combustion interaction in a solid fuel ramjet simulator." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12947.

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Jones, James D. "A study of active control techniques for noise reduction in an aircraft fuselage model." Diss., Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/77809.

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A simplified cylindrical model is used to investigate the elementary mechanisms of control of sound transmission into aircraft cabins by two active control techniques: propeller synchrophasing and active vibration control. Propeller synchrophasing involves controlling the relative rotational phase of the engines to achieve maximum cabin noise reduction. Active vibration control involves structurally controlling the vibrational response of the cabin wall to reduce the important modes which transmit their energy into the cabin. Noise reductions for harmonic excitation at acoustic cavity resonance are shown to be in excess of 20 dB throughout most of the cavity whether synchrophasing or active vibration control is used. Off-resonance reductions are substantially less due to increased modal density requiring a larger number of actuators for effective control of the complex sound field. Additional studies were performed using synchrophasing in conjunction with active vibration control to study their joint capabilities in controlling complex sound fields. The dual control system displayed improved control performance with noise reductions on the order of 25-35 dB and a more uniform sound field. Also, the complementary control characteristics of the system clearly demonstrated effective control of orthogonal acoustic modes of the cavity. However, the improved effectiveness of the control system was dependent upon judiciously positioning the actuators for optimal control of the sound field. An independent study was performed to identify the effects of a complex geometry on sound transmission into an aircraft fuselage model interior. For this study, a geometrically scaled cabin floor was installed in the unstiffened test cylinder to investigate the structural and acoustic influence of the simulated cabin floor. Results indicated that the stiffening of the cylindrical model associated with insertion of the floor strongly influenced the structural response of the cylinder but generally had little effect on the coupled pressure response. Conversely, the modification of the interior acoustic cavity tended to have little influence on the cylinder response but substantially reduced the coupled pressure response. Thus, this investigation identified the fundamental mechanisms of control of sound transmission into simplified models of aircraft fuselages by active control techniques.
Ph. D.
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Vasudevan, Gopal. "Fuel optimal rendezvous including a radial constraint." Thesis, Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/94484.

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Fuel-optimal rendezvous in orbit is examined using thrust-impulses and coasting arcs. Necessary conditions for the optimality of fuel-optimal rendezvous with and without radial constraints are derived. These conditions are then used to verify the optimality of trajectories obtained from a parameter-optimization technique. For rendezvous problems with radial constraint, locally optimal trajectories include constrained arcs or touch-point arcs. Numerical procedures to compute the costates and the jumps in the costates at the touch point and at the entry point to the constraint arc are provided. Locally optimal solutions for non-optimal trajectories with a minimum radius-constraint are obtained using criteria due to Lion and Handelsmann. Numerical solutions show that multiple-impulse trajectories almost always result in a lower cost function than the corresponding two impulse trajectories. It is also observed that trajectories comprised of only touch-point arcs can often be improved by using an additional impulse.
M. S.
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Books on the topic "Airplanes, fuel"

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Roy, Langton, ed. Aircraft fuel systems. Reston, VA: American Institute of Aeronautics and Astronautics, 2008.

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Roy, Langton, ed. Aircraft fuel systems. Chichester, West Sussex, U.K: Wiley, 2008.

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FEDERAL AVIATION ADMINISTRATION. Type certification of automobile gasoline in part 23 airplanes with reciprocating engines. Washington, D.C: U.S. Dept. of Transportation, Federal Aviation Administration, 1995.

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Engineers, Society of Automotive, and SAE Historical Committee., eds. Military aviation fuel characteristics, 1917-1945. Warrendale, PA: Society of Automotive Engineers, 1993.

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Green, W. L. Aircraft hydraulic systems: An introduction to the analysis of systems and components. New York: John Wiley & Sons, 1985.

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Vasilenko, V. T. Vlii͡a︡nie ėkspluatat͡s︡ionnykh faktorov na toplivnui͡u︡ sistemu samoletov. Moskva: "Mashinostroenie", 1986.

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Aviation and the emerging use of biofuels: Hearing before the Subcommittee on Space and Aeronautics, Committee on Science and Technology, House of Representatives, One Hundred Eleventh Congress, first session, March 26, 2009. Washington: U.S. G.P.O., 2009.

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Abadie, Olivier. Jet fuel: How high a flyer? : demand, supply, and the endless quest for efficiency. Cambridge, MA: CERA, 2007.

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FEDERAL AVIATION ADMINISTRATION. Protection of airplane fuel systems against fuel vapor ignition due to lightning. Washington, D.C: U.S. Dept. of Transportation, Federal Aviation Administration, 1985.

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National Research Council (U.S.). Air Force Studies Board., ed. Improving the efficiency of engines for large nonfighter aircraft. Washington, D.C: National Academies Press, 2007.

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Book chapters on the topic "Airplanes, fuel"

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Palocz-Andresen, Michael. "Aerodynamics of Vehicles and Airplanes, and Hydrodynamics of Ships." In Decreasing Fuel Consumption and Exhaust Gas Emissions in Transportation, 109–20. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-11976-7_7.

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Palocz-Andresen, Michael. "Airplane Engines." In Decreasing Fuel Consumption and Exhaust Gas Emissions in Transportation, 149–57. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-11976-7_10.

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McConnell, P. M., S. F. Owens, and R. A. Kamin. "Prediction of Fuel Freezing in Airplane Fuel Tanks of Arbitrary Geometry." In Lecture Notes in Engineering, 239–59. Berlin, Heidelberg: Springer Berlin Heidelberg, 1986. http://dx.doi.org/10.1007/978-3-642-82781-5_19.

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Bobkov, A., S. Chepurnykh, and M. Krivenko. "Method of Energy Efficiency Evaluation for Airplane Active Fuel System Pumping Groups." In Lecture Notes in Mechanical Engineering, 347–53. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-54814-8_42.

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"Airplane Fuel Line Support Bracket Failure." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001506.

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"Regulations (Fuel Policy)." In Performance of the Jet Transport Airplane: Analysis Methods, Flight Operations and Regulations, 627–28. Chichester, UK: John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781118534786.app6.

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"Trip Fuel Requirements and Estimation." In Performance of the Jet Transport Airplane: Analysis Methods, Flight Operations and Regulations, 411–38. Chichester, UK: John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781118534786.ch16.

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Salunkhe, Sachin, Vishal Gangadhar Naranje, Jayavelu S., and Atiq Rehman. "Process Optimizations of Direct Metal Laser Melting Using Digital Twin." In Applications of Artificial Intelligence in Additive Manufacturing, 177–93. IGI Global, 2022. http://dx.doi.org/10.4018/978-1-7998-8516-0.ch008.

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Over the past decades, air traffic has increased to such an extent that it has highly impacted (anthropogenic) climate change due to heat, noise, particulates, and gas emissions. With airplane turbines being a pivotal contributor to such adverse developments, there has been an increasing interest in research regarding the optimization of airplane turbines. In line with these efforts, this chapter adopts an innovative approach that bridges the digital and physical through the application of digital twin technology to direct metal laser melting to optimize product development. Specifically, it encompasses a guideline towards how digital twin solutions are created based on all the latest research. A manual approach devises a digital twin interface where the prototype is manufactured used additive manufacturing. This manual can then be applied to optimize airplane turbines regarding their safety, environmental impact, fuel efficiency, and cost.
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Vu, Nam Hai, Minh Le Bui, Hai Thanh Truong, Dat Anh Le, and Ha Pham Hai Nguyen. "Current Challenges and Technological Solutions for Sustainable Aviation." In Digitalization and the Impacts of COVID-19 on the Aviation Industry, 146–61. IGI Global, 2022. http://dx.doi.org/10.4018/978-1-6684-2319-6.ch008.

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This chapter aims to discuss the relevant problems in sustainable aviation development and feature the scientists' solutions addressing these issues. The chapter highlights and discusses the relevant problems in sustainable aviation development; features the scientists' solutions addressing these issues, for instance, by using environmentally friendly aircraft engines, alternative energy sources, and materials; and discusses the likely results in the economy of this practice. The research conceptualizes and contributes to the novel literature on aviation area for supporting Sustainable Development Goals (SDGs) in aviation area. Since the airline shipment continuously grows and is expected to become the fastest means among other modes of transport, it certainly brings environmental problems into view such as noise pollution, discarded fuels and emissions from burning, from both airplane and airport operational activities. These have been underlying issues demanding constant effort for energy, natural, and ecological experts.
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Steel, Duncan G. "Angular Momentum and the Quantum Gyroscope: The Emergence of Spin." In Introduction to Quantum Nanotechnology, 160–80. Oxford University Press, 2021. http://dx.doi.org/10.1093/oso/9780192895073.003.0010.

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Continuing with understanding the implications of the postulates in Chapter 7 and following the approach in Chapter 8 to use operators find solutions to the time independent Schrödinger equation, we return to the subject of angular momentum, of importance to many problems including the quantum gyroscope. Aside from playing a central role in any spherically symmetric quantum system, it plays a central role in inertial guidance systems from airplanes and rockets to autonomous vehicles. Working with only the operators of the angular momentum vector, L^=L^xx̌+L^yy̌+L^zž and L^2 and the corresponding commutation relations, a procedure similar to that used in Chapter 8 for the nano-vibrator is used to completely identify the eigenvectors and eigenvalues. However, in Chapter 6, we required that the magnetic quantum number, m where L^z|l.m〉=mℏ|l.m〉, be integer, because the eigenfunction Yl,m(l,m)∝eimϕ, and we required that a full rotation around the z-axis give the same result requiring, eimϕ=eim(ϕ+2π). In the operator approach, there is no such requirement, but there is still a constraint on m, namely that m is either integer or half integer. The requirements in Chapter 6 hold, so what is the meaning of half-integer? This was one of the first results to indicate the existence of intrinsic (not associated with real space rotation) angular moment known as spin.
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Conference papers on the topic "Airplanes, fuel"

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Sikand, Sharanpal (Paul) S., Sham S. Hariram, and Darsh Aggarwal. "Fuel Tank Safety on Airplanes." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2005. http://dx.doi.org/10.4271/2005-01-3428.

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Young, Trevor. "Fuel Sensitivity Analyses for Jet and Piston-propeller Airplanes." In 6th AIAA Aviation Technology, Integration and Operations Conference (ATIO). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-7708.

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Breit, Joe, and Joanna Szydlo-Moore. "Fuel Cells for Commercial Transport Airplanes - Needs and Opportunities." In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-1390.

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Barufaldi, Guilherme, and ROBERTO GIL ANNES DA SILVA. "Parametric Determination of Fuel Consumption During Cruise Flight for Fuel Cell Powered Airplanes." In 18th Brazilian Congress of Thermal Sciences and Engineering. ABCM, 2020. http://dx.doi.org/10.26678/abcm.encit2020.cit20-0208.

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Thomas Martinsa, Edgard, Isnard Thomas Martinsb, and Marcelo Márcio Soaresa. "Ergonomics and Cognition in Manual and Automated Flight." In Applied Human Factors and Ergonomics Conference (2022). AHFE International, 2022. http://dx.doi.org/10.54941/ahfe1001273.

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Advances in technology have enabled increasingly sophisticated automation to be introduced into the flight decks of modern airplanes. Generally, this automation was added to accomplish worthy objectives such as reducing flightcrew workload, adding additional capability, or increasing fuel economy. To a large extent, these objectives have been achieved. Safety also stood to benefit from the increasing amounts of highly reliable automation. Indeed, the current generation of highly automated transport category airplanes has generally demonstrated an improved safety record relative to the previous generation of airplanes. Vulnerabilities do exist, though, and further safety improvements should be made. To provide a safety target to guide the aviation industry, the Secretary of Transportation and others have expressed the view that the aviation industry should strive for the objective of none accidents. Training standards and currency in manual flying skills may well have deteriorated, but are these changes in proportion to the tasks and situations typical of modern operations, or really at the root of handling related safety concerns.
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Munoz-Ramos, Karina, Joeseph W. Pratt, Abbas A. Akhil, Benjamin L. Schenkman, Lennie E. Klebanoff, and Dita B. Curgus. "Electrical analysis of Proton Exchange Membrane fuel cells for electrical power generation on-board commercial airplanes." In 2012 IEEE Transportation Electrification Conference and Expo (ITEC). IEEE, 2012. http://dx.doi.org/10.1109/itec.2012.6243429.

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7

Nagesh, Athreya, Ola Rashwan, and Ma’moun Abu-Ayyad. "Optimization of the Composite Airplane Fuselage for an Optimum Structural Integrity." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-88215.

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The newly developed airplanes are using composite laminates to replace the metal alloys for different components, such as the fuselage and the wings. The major advantage of the composite materials is to reduce structural weight which results in reducing the fuel consumption. The aim of this project is to investigate the structural integrity of an airplane fuselage, which uses various types of carbon composite laminates under the static loading of the cabin pressurization. The research is performed using the finite element method and the HYPERMESH commercial software with a composite tool to change the thickness and the orientation of carbon fiber laminates used in the facesheet of the sandwich structure. Three different orientations/stacking sequence of the HexPly 8552 AS4 carbon fibers with two honeycomb cores: Hexagonal Al and Nomex. The results show that the composite material using the HexPly 8552 carbon fiber oriented at angle 30 and angle 45 and the Nomex Honeycomb core of a total laminate thickness of 15.875mm outperform all other thicknesses and orientations in regards to the static loading failure.
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Tsang, Wing. "Progress in the Development of Chemical Kinetics Databases for the Combustion of Real Fuels." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-68369.

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Modern Computational Fluid Dynamics codes have increasing capabilities for taking into account detailed chemical kinetics [1, 2]. This opens the possibility of simulating the combustion of real fuels in industrial devices. This will bring combustion technology in line with modern developments in cutting edge science. One could not design VLSI circuits without simulations. Similarly, the design of modern airplanes depends on simulations before final wind tunnel testing. A key to the proper simulation of the chemistry in combustion is the kinetics database. The aim of this paper is to describe the current situation in this area. We will begin by discussing the special problems posed by the nature of the fuel. We will then define the elements in a proper chemical kinetic database. Currently used databases for the simulation of combustion will be critically examined. The importance of a more fundamentally based database will be emphasized. Finally some recent work pertaining to the chemical kinetics of real liquid fuel molecules will be described.
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Ogawa, Toshinori, and Yasuo Kawaguchi. "Performance Testing of 5cc Glow-Ignition Four-Stroke Engine." In ASME/JSME 2007 Thermal Engineering Heat Transfer Summer Conference collocated with the ASME 2007 InterPACK Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/ht2007-32132.

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Although portable electric devices have become increasingly sophisticated and compact, the amount of energy required for their operation has increased and device performance may be restrained by the energy source in the near future. A small power source is also needed for mobile robots for home usage. Small, portable distributed power sources with higher energy density than the conventional battery are required. Since the energy density of hydrocarbon or hydrogen fuel is quite high compared to the battery, combustion micro engines that use these fuels are promising for this purpose. In this research, we focused on the small glow-ignition engine developed for model airplanes. Since the glow engine does not require an auxiliary electric circuit for ignition, it is suitable for lightweight miniature engines. However, unlike the spark-ignition engine, there is no equipment that controls the ignition timing. In the glow-ignition system, heat is supplied by the following three methods for ignition of the air-fuel mixture: (1) Heat produced from the compression of the air-fuel mixture; (2) Heat remaining in the element from the last explosion; and (3) Heat produced by the catalytic action of an ignition element. In such an ignition system, the combustion state may differ between cycles. In order to clarify the combustion process, a miniature pressure sensor was built into the cylinder head, and pressure fluctuation was measured. Analysis was conducted to detect cycle-to-cycle variation. The base engine used was a commercial glow-ignition four-stroke engine with a swept volume of 4.89 cc. This is a high-speed engine with a maximum engine speed exceeding 14,000 rpm. Although the nominal output was 368 W, the value measured by this research was much lower. Fuel consumption was measured by placing a fuel tank on an electronic balance. The fuel used for the experiment consisted of mainly methanol, nitromethane, and lubricant. Weight ratio of these components and air/fuel ratio were changed independently, and the effect on the combustion pressure was evaluated.
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Grönman, Aki, Juha Honkatukia, Petri Sallinen, Jari Backman, Antti Uusitalo, Teemu Turunen-Saaresti, and Ahti Jaatinen-Värri. "Design and Performance Measurements of a 6 kW High-Speed Micro Gas Turbine Prototype." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42620.

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Small portable electricity generating systems are suitable in remote locations where the access by vehicles is restricted or not even possible. These kind of places include for example catastrophic areas after earthquakes or tropical cyclones. Such machines can also be used as auxiliary power units in motor or sail boats. Gas turbine based electricity generation systems offer a good alternative for typical engine-generator units which are characterized by lower specific powers. It is suggested that the power to weight ratio of a 6 kW micro gas turbine can be more than eight times higher than that of the corresponding engine-generator unit. The biggest drawback is the higher specific fuel consumption; however, by introducing a recuperator, the specific fuel consumption can be improved. In this article, the design process and experiments of a 6 kW micro gas turbine prototype are described and discussed in detail. The built non-recuperated prototype is based on a commercial, small jet engine originally designed to give thrust to radio controlled model airplanes. The jet nozzle of the jet engine was replaced by an axial power turbine which was directly connected to a small, high speed permanent magnet generator. The experiments showed the potential of the prototype.
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Reports on the topic "Airplanes, fuel"

1

Pratt, Joesph 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. Office of Scientific and Technical Information (OSTI), May 2011. http://dx.doi.org/10.2172/1219354.

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2

Curgus, Dita Brigitte, Karina Munoz-Ramos, Joseph William Pratt, Abbas Ali Akhil, Leonard E. Klebanoff, and Benjamin L. Schenkman. Proton exchange membrane fuel cells for electrical power generation on-board commercial airplanes. Office of Scientific and Technical Information (OSTI), May 2011. http://dx.doi.org/10.2172/1018476.

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3

Skone, Timothy J. Airplane Combustion of Blended F-T/Conventional Jet Fuel. Office of Scientific and Technical Information (OSTI), May 2012. http://dx.doi.org/10.2172/1509241.

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