Relevant bibliographies by topics / Airplanes Fuel systems

Contents

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

Academic literature on the topic 'Airplanes Fuel systems'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 February 2022

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Journal articles on the topic "Airplanes Fuel systems"

1

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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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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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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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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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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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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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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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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Донець, О. Д., and В. П. Іщук. "КОНЦЕПЦІЯ СТВОРЕННЯ СИЛОВОЇ УСТАНОВКИ СІМЕЙСТВА РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ АН-148/АН-158." Open Information and Computer Integrated Technologies, no. 84 (July 2, 2019): 50–63. http://dx.doi.org/10.32620/oikit.2019.84.02.

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The basic results of calculation and research works carried out in the process of creation of power unit of regional passenger airplanes’ family are given. The design features of the propulsion engines and engine of the auxiliary power plant are described. The aforementioned propulsion system includes propulsion engines D-436-148 and engine AI-450-MS of auxiliary power plant. In order to comply with the requirements of Section 4 of the ICAO standard (noise reduction of the aircraft in site), in part of ensuring the noise reduction of engines, when creating the power plant of the An-148/An-158 aircraft family, a single- and double-layer acoustic filler was used in the structure of the engine nacelle and air intake. The use of electronic system for automatic control of propulsion engines such as FADEC and its integration into the digital airborne aircraft complex ensured the operation of engines, included in the power plant provided with high specific fuel consumption, as well as increased the level of automation of the power plant control and monitoring, and ensured aircraft automation landing in ICAO category 3A. In addition, the use of the aforementioned electronic system, allowed to operate the power plant of the aircraft in accordance with technical status. The use of the AI-450-MS auxiliary power plant with an electronic control system such as FADEC, and the drive of the service compressor from a free turbine, eliminated the effect of changes in power and air takeoff, on the deviation of the engine from optimal mode, which also minimized the fuel consumption. The use of fuel metering system TIS-158, allowed to ensure control of its condition and assemblies, without the use of auxiliary devices, built-in control means. In the fire protection system, the use of the electronic control and monitor unit, as well as the use of digital serial code for the exchange of information between the elements of the system and the aircraft systems, has reduced the number of connections, which increased the reliability of the system and reduced its weight characteristics.
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Liu, Yan, Gou Qing Gou, Hui Chen, Li Jun Wang, Ming Jing Tu, and Jin Peng Yu. "Effects of Fuel Gas on the Microstructure and Mechanical Properties of HVOF Spraying WC-12Co Coating." Advanced Materials Research 602-604 (December 2012): 1710–15. http://dx.doi.org/10.4028/www.scientific.net/amr.602-604.1710.

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In this paper, WC-12Co coating are prepared by two HVOF systems. The biggest difference between these two systems is the fuel gas use. Morphology and mechanical properties of the coatings are analyzed. The results show that the coating sprayed with Airplane Kerosene fuel gas is denser and the WC particles distribute more even than that sprayed with propane fuel gas. And the WC particles melt more fully. The hardness, Young’s Modules and fracture toughness of the coating sprayed with Airplane Kerosene fuel gas is higher than that sprayed with propane fuel gas.
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Dissertations / Theses on the topic "Airplanes Fuel systems"

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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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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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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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Venter, Jeanne Marie. "Autonomous air-to-air refueling : a comparison of control strategies." Thesis, Stellenbosch : Stellenbosch University, 2012. http://hdl.handle.net/10019.1/20239.

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Thesis (MScEng)--Stellenbosch University, 2012.
ENGLISH ABSTRACT: The air-to-air refuelling of large aircraft presents challenges such as a long fuel transfer time, slow aircraft responses and a large distance between the aircraft CG and the receptacle position. This project addresses some of these issues by adding a control system to keep the receiver aircraft in the correct position relative to the tanker to enable fuel transfer. This project investigates different control strategies which are designed to control the A330-300 during refuelling at one trim condition. The controllers are based on a mathematical aircraft model which was derived from a simulation model received from Airbus. The first set of controllers uses the aircraft actuators directly. Controllers that are based on the CG dynamics and the receptacle dynamics are compared. Due to the large distance between the CG and the receptacle it was found to be essential to control the receptacle position, and not only the CG position. Also, a controller that is based on a model of the receptacle dynamics performs better. The second set of controllers uses the aircraft manual control laws as an inner loop controller. This set of controllers and the last direct actuator controller use the same axial controller that uses the engine thrust to control axial position. It was found that both the direct actuator controller and the manual control laws controller are able to keep the receptacle within the disconnect envelope in moderate turbulence. In both sets of controllers the axial controller fails to keep the receptacle reliably within the disconnect envelope in light turbulence. From the results it is concluded that both the direct actuator control and manual control laws can be used to successfully control the receptacle position in the normal and lateral positions as long as the receptacle kinematics are included in the control design. Using only the engine thrust for axial control is insufficient. Several recommendations are made to improve the axial control and also how these results can be used in future work.
AFRIKAANSE OPSOMMING: Die lug-tot-lug brandstof hervulling van groot vliegtuie het uitdagings soos ’n lang hervullingstyd, stadige vliegtuig dinamika en ’n groot afstand tussen die hervullingspoort en die vliegtuig massamiddelpunt. Hierdie projek spreek sommige van hierdie uitdagings aan deur ’n beheerstelsel by te voeg wat die vliegtuig in die korrekte posisie relatief tot die tenker hou vir brandstofoordrag om plaas te vind. Hierdie projek ondersoek verskillende beheerstrategieë wat ontwerp is om die A330- 300 te beheer by ’n enkele gestadigde toestand. Die beheerders is gebaseer op ’n wiskundige vliegtuigmodel wat vanaf ’n simulasiemodel afgelei is. Die simulasiemodel is vanaf Airbus verkry. Die eerste stel beheerders beheer direk die vliegtuig se beheeroppervlakke. Beheerders wat onderskeidelik die massamiddelpunt en die hervullingspoort beheer word vergelyk. Daar is gevind dat dit essensieel is om die hervullingspoort te beheer en nie slegs die massamiddelpunt nie, as gevolg van die groot afstand tussen hierdie twee punte. Die tweede stel beheerders gebruik die vliegtuig se eie beheerwette as ’n binnelusbeheerder en vorm self die buitelus. Albei stelle beheerders gebruik dieselfde aksiale beheerder wat enjin stukrag gebruik om die aksiale posisie te beheer. Daar is gevind dat beide stelle beheerders die hervullingspoort binne die ontkoppelingsbestek kan hou in die normale en laterale rigtings tydens matige turbulensie. In beide stelle beheerders is dit die aksiale beheerder wat faal om die hervullingspoort betroubaar in posisie te hou, selfs in ligte turbulensie. Vanaf die resultate word afgelei dat beide die direkte beheerder en die buitelusbeheerder gepas is om die laterale en normale posisiebeheer toe te pas mits die dinamika van die hervullingspoort in ag geneem word. Om slegs stukrag te gebruik vir aksiale beheer is nie voldoende nie, en verskeie voorstelle word gemaak om die aksiale beheer te verbeter in toekomstige navorsing.
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Aguilar, Cortés Carlos Ezequiel. "Air carrier liability and automation issues." Thesis, McGill University, 2002. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=78196.

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Our intended topic is a general discussion of the basic elements of liability related to airline accidents to which fully automated cockpits have constituted an associated contributory factor. In addition we addressed the liability of air carriers arising from injuries or death caused to passengers traveling on international flights. For this purpose, we reviewed the Warsaw System and the different international instruments that constitute it. We also reviewed principles of common law applicable to aircraft manufacturers and the "Free Flight" as an example of the growing automation environment, which is a general benefit to commercial aviation but also a likely contributory cause for accidents in particular cases. In the last part we briefly discuss a personal view regarding the interplay between manufacturers and airlines under the 1999 Montreal Convention, which is an international treaty unifying the desegregated Warsaw System into one single instrument that is expected to enter into force in a few years.
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Books on the topic "Airplanes Fuel systems"

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

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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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Strauss, Kurt H. Survey of current aircraft engine conditions. Atlanta, Ga. (219 Perimeter Center Pkwy., Atlanta 30346): Aviation Vehicle Fuel, Lubricant, and Equipment Research Committee of the Coordinating Research Council, 1991.

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Aksenov, A. F. Iznosostoĭkostʹ aviat͡s︡ionnykh toplivno-gidravlicheskikh agregatov. Moskva: "Transport", 1986.

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Leshchiner, L. B. Proektirovanie toplivnykh sistem samoletov. 2nd ed. Moskva: "Mashinostroenie", 1991.

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Knox, Charles E. Ground-based time-guidance algorithm for control of airplanes in a time-metered air traffic control environment: A piloted simulation study. Hampton, Va: Langley Research Center, 1986.

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Singh, Jag J. Low-energy gamma ray attenuation characteristics of aviation fuels. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Singh, Jag J. Low-energy gamma ray attenuation characteristics of aviation fuels. Hampton, Va: Langley Research Center, 1990.

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Singh, Jag J. Low-energy gamma ray attenuation characteristics of aviation fuels. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Hui, Timothy H. Y. Investigation of pre-mature ignition of a hypervelocity fuel/air mixture with nitrogen injection. Ottawa: National Library of Canada, 2002.

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Book chapters on the topic "Airplanes Fuel systems"

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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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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 systems"

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Gallagher, Tanya M., Constantin Ciocanel, and Cindy Browder. "Structural Load Bearing Supercapacitors Using a PEGDGE Based Solid Polymer Electrolyte Matrix." In ASME 2011 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2011. http://dx.doi.org/10.1115/smasis2011-5113.

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The interest in developing multifunctional materials has greatly increased in the last decade. Power storage composites are just one class of multifunctional materials that has the potential to lead to significant size and weight reduction. Many electronic devices (i.e. laptops, cellphones, iPods, etc.) and mechanical systems that require or generate electrical power during operation (i.e., hybrid or fully electric cars, wind turbines, airplanes, etc.) could benefit substantially from these materials. While several types of power storage structural composites have been developed to date, i.e. composite batteries and fuel cells, structural load bearing super- and ultra-capacitors appear to be the most promising ones. To date, two classes of structural capacitors have been explored: dielectric and solid electrolyte capacitors; the former are suitable for applications where very high voltage bursts of electrical energy are needed, while the latter are suitable for applications where lower voltage levels are required (i.e. more general power storage/delivery applications). This paper describes the efforts made to develop and characterize electro-mechanically structural supercapacitors. The load-bearing supercapacitors discussed here have been made with carbon fiber weave electrodes and separators of various materials, glued together with a solid polymer electrolyte (SPE) matrix. Electrochemical characterization reported specific capacitances as high as 2.9μF/mm3 and energy densities as high as 4.9 kJ/g.
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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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Jain, Samarth, Soumya Roy, Abhishek Aggarwal, Dhruv Gupta, Vasu Kumar, and Naveen Kumar. "Study on the Parameters Influencing Efficiency of Micro-Gas Turbines: A Review." In ASME 2015 Power Conference collocated with the ASME 2015 9th International Conference on Energy Sustainability, the ASME 2015 13th International Conference on Fuel Cell Science, Engineering and Technology, and the ASME 2015 Nuclear Forum. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/power2015-49417.

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The art and science of gas turbine has traditionally seen a gradual and continuous change over the past few decades. Gas turbines are classified into impulse and reaction types and further into turbojet, turbofan, turboprop, after burning turbojet and micro gas turbine. These turbines find applications in airplanes, large scale industries etc. but these are less suitable for the small scale power generation units due to several factors. Micro gas turbines are set to play a significant role particularly in small-scale power generation using combined heat and power generation among all these types of turbines as the future of power generation lies in decentralised and distributed power generation systems. In the light of making use of the high temperature exhaust of a gas turbine, combined heat and power generation systems are being used to increase the power output and overall efficiency. Micro gas turbines are essentially single-stage, single-shaft and low pressure gas turbines whose capacity ranges from 30–150 KW. In comparison to the conventional turbines, micro gas turbines are compact and have low lubricating oil consumption leading to a simpler lube and sump oil system and because they have fewer rotating parts, this leads to lesser balancing problems. The analysis of micro gas turbines has shown that they are capable of meeting current emission standards of NOx and other pollutants. Even though the installation costs of micro gas turbines are high due to the complexity in adjusting to electrical grid frequency, still these distributed energy systems may prove to be more attractive in a competitive market to those seeking increased reliability as they empower these entities with the capacity of self-generation. The following text reviews the developments in the micro gas turbines with a special focus on the efficiency of its components such as the recuperator, the combustion chamber design and also explores the future prospects of the technology in terms of viability of its application in the automobile sector.
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Uhlár, Erik, and Jozef Čerňan. "System optimization demonstrator for aircraft propulsion technology using fuel cells." In Práce a štúdie. University of Žilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.1.29.

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In order to help accelerate transition to sustainable and eco-friendly personal transportation in a single engine piston aircraft category we’ve developed a simulation software platform of hydrogen powered aircraft for further research and development. Measurements were carried out on a real reference airplane Cessna 172 R and were crosschecked with an airplane flight manual as well as a computer flight simulation. We also focused on a software-based safety and economy optimization by components usage ratio improvement and inflight energy production and transfer limitations.
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Pratt, Joseph W., Lennie Klebanoff, Karina Munoz-Ramos, Abbas A. Akhil, Dita B. Curgus, and Benjamin L. Schenkman. "Proton Exchange Membrane Fuel Cell Systems for Airplane Auxiliary Power." In 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-3679.

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Ghotkar, Rhushikesh, and Ryan J. Milcarek. "Integration of Flame-Assisted Fuel Cells With a Gas Turbine Running Jet-A As Fuel." In ASME 2019 Power Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/power2019-1852.

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Abstract In recent years, the aircraft industry is heading towards the concept of the More Electric Airplane (MEA). Previous research has investigated the possibility of integrating Dual Chamber Solid Oxide Fuel Cells (DC-SOFC) with the auxiliary power unit (APU) of the aircraft. This paper evaluates the merits of integrating the recently proposed Flame-assisted Fuel Cells (FFCs) with the APU gas turbine system. The syngas composition for fuel-rich combustion is studied using chemical equilibrium analysis of Jet-A/air at 8 Bar and 1073 K. The results show the potential for reforming Jet-A fuel to 22% Carbon Monoxide and 18% Hydrogen in the exhaust at an equivalence ratio of 2.4. The paper also reports how the efficiency of power generation changes when FFCs are placed in the combustor of a turbine in the APU. The maximum theoretical electrical efficiency of the FFC/combustor and the area and weight of the fuel cell required to generate the design power is calculated. The FFC offers a viable substitute for the DC-SOFC to be integrated with the APU.
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Knobloch, Karsten, André Fischer, Friedrich Bake, Lars Enghardt, and Stefan Busse-Gerstengarbe. "Full-Scale Tests on APU Noise Reduction." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26803.

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The present paper describes an experimental investigation of the noise emission of a full-scale Garrett (Honeywell) GTCP 36-300 APU as installed on commercial airplanes like the Airbus A320. The APU exhaust noise emissions are measured in a well-controlled environment by 25 ground-based microphones arranged in a polar arc. Comparing a hard-wall reference case with different exhaust mufflers, special attention is given to the assessment of the noise reduction obtained. The performance of a newly designed muffler is compared to the standard device for the most relevant operating states ECS (environmental control system) and MES (main engine start). The paper concludes with a short examination of possibilities to improve the overall noise reduction.
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Pan, Zhen, Chengzhi Chi, and Jingkai Zhang. "A Model of Fuel Consumption Estimation and Abnormality Detection based on Airplane Flight Data Analysis." In 2018 IEEE/AIAA 37th Digital Avionics Systems Conference (DASC). IEEE, 2018. http://dx.doi.org/10.1109/dasc.2018.8569796.

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Hashimoto, Shin-ichi, Ryuichi Miyata, Keiko Kobayashi, Keiji Yashiro, Hitoshi Takamura, Kyosuke Yoshimi, Norito Kijima, et al. "A New Development Strategy of Light Wight Solid Oxide Fuel Cells for Electrified Airplane System." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-4470.

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Ma, Qiuju, Quanyi Liu, Runhe Tian, Junjian Ye, Rui Yang, and Hui Zhang. "The Mass Burning Rate of n-Heptane Pool Fire Under Dynamic Pressure." In ASME 2016 Heat Transfer Summer Conference collocated with the ASME 2016 Fluids Engineering Division Summer Meeting and the ASME 2016 14th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/ht2016-7448.

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Fire safety is critical for safety of airplane operation. During an emergency landing, airplane goes through dramatic external pressure change from cruise altitude to sea level, considering the impact caused by low pressure atmosphere. The objective of this work is to examine the effect of dynamic pressure on the behavior of a horizontally burning diffusion flame over a pool fuel surface based on experimental approach. The experiments were conducted in a large-scale altitude chamber of size 2 m × 3 m × 4.65 m. The pressure rise process was examined under different dynamic pressures from respectively 38 kPa, 64 kPa and 75 kPa to 90 kPa with various pressure rise rates of 100 Pa/s, 150 Pa/s, 200 Pa/s, 250 Pa/s and 300 Pa/s, which is to simulate the airplane landing process from different altitudes. The whole system of the altitude chamber is of unique capability that the pressure in the chamber can be exactly controlled by a powerful pressure controlling system, and the oxygen concentration can maintain at the level about 20%, which are achieved through controlling inlet air flow for oxygen level and outlet gas flow for pressure (static or dynamic) level. A round steel fuel pans of 34 cm in diameter and 15 cm in height were chosen for the pool fire tests. The fuel pan was filled with 99% pure liquid n-Heptane. Cold water is added beneath the fuel layer to cool the pan and minimize the temperature rise in the fuel. Parameters such as mass, mass burning rate, chamber pressure were measured. The results of those tests demonstrated the significant impact to fire behaviors caused by high altitude or low pressure atmosphere.
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