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Relevant bibliographies by topics / Ion engines

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Academic literature on the topic 'Ion engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 12 February 2022

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Journal articles on the topic "Ion engines"

1

Freiherr, Greg. "The Little Rocket Engine That Could." Mechanical Engineering 138, no. 08 (2016): 32–37. http://dx.doi.org/10.1115/1.2016-aug-1.

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This paper highlights advancements of a research team in the field of miniature spacecrafts and development and advantages of CubeStats. CubeSats are space age hitchhikers, that is, miniature spacecraft that fly into orbit aboard rockets whose primary payloads are full-size satellites. Paulo Lozano and his team at MIT’s Space Propulsion Lab have developed a unique kind of rocket engine for these microsatellites. The trick to building a successful ion electrospray propulsion system is to increase thrust density by jamming together as many emitters as possible. Electrospray engines also differ greatly from another form of ion propulsion, plasma ion, which also eschews chemical combustion for the efficiency of the electron. A big advantage, when asking for permission to hitchhike a ride into orbit, is that ion electrospray propulsion engines cannot explode and destroy a rocket’s primary payload. A second advantage of ion engines is their modularity and, consequently, scalability.

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Sorokin, A., X. Vancassel, and P. Mirabel. "Emission of ions and charged soot particles by aircraft engines." Atmospheric Chemistry and Physics Discussions 2, no. 6 (2002): 2045–74. http://dx.doi.org/10.5194/acpd-2-2045-2002.

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Abstract. In this article, a model which examines the formation and evolution of chemiions in an aircraft engine is proposed. This model which includes chemiionisation, electron thermo-emission, electron attachment to soot particles and to neutral molecules, electron-ion and ion-ion recombination, ion-soot interaction, allows the determination of the ion concentration at the exit of the combustor and at the nozzle exit of the engine. It also allows the determination of the charge of the soot particles. A comparison of the model results with the available ground-based experimental data obtained on the ATTAS research aircraft engines during the SULFUR experiments (Schumann, 2002) shows an excellent agreement.

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Sorokin, A., X. Vancassel, and P. Mirabel. "Emission of ions and charged soot particles by aircraft engines." Atmospheric Chemistry and Physics 3, no. 2 (2003): 325–34. http://dx.doi.org/10.5194/acp-3-325-2003.

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Abstract. In this article, a model which examines the formation and evolution of chemiions in an aircraft engine is proposed. This model which includes chemiionisation, electron thermo-emission, electron attachment to soot particles and to neutral molecules, electron-ion and ion-ion recombination, ion-soot interaction, allows the determination of the ion concentration at the exit of the combustor and at the nozzle exit of the engine. It also allows the determination of the charge of the soot particles. For the engine considered, the upper limit for the ion emission index EIi is of the order of (2-5) x1016 ions/kg-fuel if ion-soot interactions are ignored and the introduction of ion-soot interactions lead about to a 50% reduction. The results also show that most of the soot particles are either positively or negatively charged, the remaining neutral particles representing approximately 20% of the total particles. A comparison of the model results with the available ground-based experimental data obtained on the ATTAS research aircraft engines during the SULFUR experiments (Schumann, 2002) shows an excellent agreement.

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Petrov, Nikolay, and Tamara Antonova. "Increasing the specific impulse of the ion engine by zone engineering of the solid-state field cathode." Proceedings of the Russian higher school Academy of sciences, no. 4 (January 20, 2021): 41–50. http://dx.doi.org/10.17212/1727-2769-2020-4-41-50.

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With the rapid development of space technology, the scale of human space exploration is expanding significantly. However, the growing demand for deep space travel cannot be met with conventional chemical engines. Thus, the need for new mechanisms for providing jet thrust, including electric motors, becomes clear. Electric propulsion technology has significant advantages over traditional chemical engines in deep space flight due to its characteristics such as high specific impulse, small size, long service life. A negative feature of electric motors can be called low thrust, however, firstly, in open space this is insignificant and, secondly, the thrust of electric motors can be significantly increased, and for this, there are reserves available at the current level of technology development. Ways to increase the thrust of electric ion thrusters will be detailed and discussed in this work. The increase in the power of ion engines is limited to a large extent by the erosion of the control grids; the ion flow hits the surface of the solid material of the control grid electrode with energetic ions and gradually leads to the failure of this electrode. In this work, the authors will show that the use of field emission as a source of electron beams ionizing the working medium can solve the problem of erosion of control electrodes, due to which it will be possible to significantly increase the strength of the working fields for ion engines, which in turn will increase the specific impulse, efficiency, flow rate and power of the ion engine as a whole.

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Mehresh, P., D. Flowers, and R. W. Dibble. "Experimental and numerical investigation of effect of fuel on ion sensor signal to determine combustion timing in homogeneous charge compression ignition engines." International Journal of Engine Research 6, no. 5 (2005): 465–74. http://dx.doi.org/10.1243/146808705x30404.

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Homogeneous charge compression ignition (HCCI) engines offer promise owing to low emissions and high efficiency. However, the control of the combustion process in HCCI engines, specifically the control of the start of combustion (SOC) or ignition timing, remains a challenge. Piezoelectric pressure transducers are used in research engines for determination of the start of combustion; however, these pressure transducers are too expensive and fragile for applications in commercial engines. Recent work by the authors as well as other investigators has shown the potential of inexpensive ion sensors in HCCI engines fuelled with propane or gasoline. However, the working range of ion sensors is limited in HCCI engines owing, in large part, to the fact that the peak cycle temperature in HCCI combustion is quite low (∼ 1700–1900 K). With the guidance of detailed chemical kinetic modelling it is shown that fuels or additives producing a higher concentration of CH radicals will probably produce higher ion concentrations. Acetylene (HC=CH) is known to produce large concentrations of CH radicals. Hence, various mixtures of propane and acetylene are numerically and experimentally studied. The ion concentration substantially increases with the addition of a small amount of acetylene. This research is an effort to understand the ion generation mechanism in HCCI engines with a view towards improving the ion signal.

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Budko, Artem Yur’evich, M. Yu Medvedev, and Vladimir Vladimirovich Matsiborko. "Improving the Efficiency of Power Generation Plants Based on Internal Combustion Engines." Applied Mechanics and Materials 752-753 (April 2015): 941–45. http://dx.doi.org/10.4028/www.scientific.net/amm.752-753.941.

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This paper describes a method developed by the authors for the detection and estimation of knock intensity in the cylinders of internal combustion engines. The method is based on the spectral analysis of the ion current signal, which is detected within the combustion chamber of the engine. The method allows estimation of the total wave packet energy for different waves speed and frequency. The estimation results of wave’s energy arising in the normal and knock combustion to engine VAZ 2110 are also presented in the paper work.

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Miao, Jian-Guo, Chun-Wang Wu, Wei Wu, and Ping-Xing Chen. "Entropy Exchange and Thermodynamic Properties of the Single Ion Cooling Process." Entropy 21, no. 7 (2019): 650. http://dx.doi.org/10.3390/e21070650.

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A complete quantum cooling cycle may be a useful platform for studying quantum thermodynamics just as the quantum heat engine does. Entropy change is an important feature which can help us to investigate the thermodynamic properties of the single ion cooling process. Here, we analyze the entropy change of the ion and laser field in the single ion cooling cycle by generalizing the idea in Reference (Phys. Rev. Lett. 2015, 114, 043002) to a single ion system. Thermodynamic properties of the single ion cooling process are discussed and it is shown that the Second and Third Laws of Thermodynamics are still strictly held in the quantum cooling process. Our results suggest that quantum cooling cycles are also candidates for the investigation on quantum thermodynamics besides quantum heat engines.

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Fujita, Kazuhisa. "Air Intake Performance of Air Breathing Ion Engines." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 52, no. 610 (2004): 514–21. http://dx.doi.org/10.2322/jjsass.52.514.

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WATANABE, Hiroki, Tomoyuki HATAKEYAMA, Masatoshi IRIE, et al. "Study on Radio Frequency Cathode for Ion Engines." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7, ists26 (2009): Pb_53—Pb_58. http://dx.doi.org/10.2322/tstj.7.pb_53.

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KUNINAKA, Hitoshi. "Microwave Discharge Ion Engines Onboard Hayabusa Asteroid Explorer." Hyomen Kagaku 33, no. 12 (2012): 669–74. http://dx.doi.org/10.1380/jsssj.33.669.

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Dissertations / Theses on the topic "Ion engines"

1

Starling, Dan A. "Propellant feed control for ion engines." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1996. http://handle.dtic.mil/100.2/ADA316748.

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Starling, Dan A. Jr. "Propellant feed control for ion engines." Thesis, Monterey, California. Naval Postgraduate School, 1996. http://hdl.handle.net/10945/8868.

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Approved for public release, distribution is unlimited<br>An overview of space electric propulsion (SEP) is presented. Methods of throttling the power levels of electrostatic and electromagnetic thrusters are discussed. Particular attention is given to the concept of thermally- throttling propellant flow using the temperature-viscosity characteristics of xenon gas. The thermoproperties of xenon gas as a function of temperature are determined, and the flow regimes of the propellant at the mass flow rates of interest are studied. The propellant flow is presented separately as Fanno flow and as Rayleigh flow, and then those combined effects are considered. A method for predicting the performance of thermally-throttled systems is presented. Uncertainties in modeling real-world thermal throttling systems are discussed. The possible use of thermal throttling characteristics as a means of propellant pressure regulation is also examined.

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Gruber, J. R. "A study of erosion due to low-energy sputtering in the discharge chamber of the Kaufman ion thruster." Thesis, University of Oxford, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.249396.

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Panousakis, Dimosthenis. "Ion current sensing for controlled auto ignition in internal combustion engines." Thesis, Loughborough University, 2009. https://dspace.lboro.ac.uk/2134/8145.

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Envirom-nental pollution is a subject that needs urgent addressing. Since the internal combustion engine has its fair share of accountability on this, research on techniques for increasing engine efficiency and emissions is necessary. Controlled Auto Ignition is a promising combustion mode, which increases fuel efficiency while also reducing NOx emissions to negligible levels. This Thesis concentrates on the implementation of this mode through experimental research, on an engine equipped with a fully variable valvetrain. Investigation of the operational window, emissions, fuel consumption, thermodynamic efficiency is carried out and ways to improve on these are discussed. The governing consideration, however, is the control method for this rather intricate combustion mode. As such, experimental data acquisition and analysis of ion current under the whole operating spectrum, from spark ignition to full autoignition is made. It is found that the expected gains in fuel consumption and emissions are realized. In addition, ion current proves to be a very powerful and cost effective tool for engine monitoring, diagnosis and control. The author concludes that Controlled Auto Ignition is a viable proposition for mass production engine designs and that ion current, although not absolutely vital for engine control, considerably increases engine control thus allowing for greater operating window under autoignition, without compromising reliability or cost.

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Holub, Anna, and Jie Liu. "Recognizing Combustion Variability for Control of Gasoline Engine Exhaust Gas Recirculation using Information from the Ion Current." Thesis, Halmstad University, School of Information Science, Computer and Electrical Engineering (IDE), 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:hh:diva-235.

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<p>The ion current measured from the spark plug in a spark ignited combustion engine is used </p><p>as basis for analysis and control of the combustion variability caused by exhaust gas </p><p>recirculation. Methods for extraction of in-cylinder pressure information from the ion </p><p>current are analyzed in terms of reliability and processing efficiency. A model for the </p><p>recognition of combustion variability using this information is selected and tested on both </p><p>simulated and car data.</p>

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Ogunjobi, Taiwo A. "Computational Study of Ring-Cusp Magnet Configurations that Provide Maximum Electron Confinement." Wright State University / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=wright1166226698.

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Botha, Johannes Rudolf. "Design of an RF ion thruster." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/86267.

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Thesis (MEng)--Stellenbosch University, 2014.<br>ENGLISH ABSTRACT: Recent years have seen a decline in the rate of space exploration due to the inefficiency of chemical rockets. Therefore alternative fuel efficient propulsion methods are being sought to enable cost effective deep space exploration. The high fuel efficiency of electric thrusters enable a spacecraft to travel further, faster and cheaper than any other propulsion technology available. Thus electric propulsion has become the propulsion of choice for scientists and engineers. A typically electric thruster contains some sort of electrode to ionise the propellant. Although this is feasible for short space missions, it becomes impractical for more ambitious space missions as electrodes erode over time. The alternative is to ionise the propellant using electromagnetic fields, which eliminates lifespan issues associated with electrode based thrusters. In order to examine methods of improving the lifespan and performance of electric thrusters, this thesis aimed to study the method of microwave discharge ionisation for an electric thruster. This includes the design of an RF Ion Thruster with extraction and acceleration grids to generate thrust. A 600 W 2.45 GHz magnetron (obtained from a conventional microwave oven), coupled to circular TM010 resonant cavity, was used to ionise neutral argon gas. The process of electron cyclotron resonance (ECR) was used to ensure the efficient ionisation of a high density plasma. The thrust was achieved with a three-grid system biased at high voltages to accelerate positively charged argon ions to high exhaust velocities. Results yielded the success of the designed electromagnetic based thruster, measuring approximatively 1.78 mN of thrust with a specific impulse of Isp = 3786 seconds. The ECR process produced a high plasma density with a plasma absorption rate of approximately 77% of the total input microwave power. The final results obtained were found to match the predicted results extremely well and resembled results found in literature. This demonstrates the efficiency of the RF ion thruster that was designed in this project and the future use in space exploration activities. However, future research needs to be undertaken on a controlled feedback system that will ensure optimal operating conditions for maximum performance. In addition, the method of grid-less acceleration needs to be studied to achieve maximum thrust and specific impulse.<br>AFRIKAANSE OPSOMMING: In onlangse jare het ’n afname in die tempo van die verkenning van die ruimte dit te danke aan die ondoeltreffendheid van chemiese vuurpyle. Derhalwe moet alternatiewe brandstof aandrywing metodes ondersoek word, om koste-effektiewe diep ruimte-eksplorasie moontlik te maak. Die hoë brandstof-doeltreffendheid van elektriese ontbranders stel ’n ruimtetuig in staat om verder, vinniger en goedkoper te reis as enige ander aandrywing tegnologie wat tans beskikbaar is. Dus het elektriese aandrywing metodes die aandrywings keuse vir wetenskaplikes en ingenieurs geword. ’n Tipies elektriese vuurpyl/aandrywer bevat ’n vorm van elektrode om die brandstof (argon gas) te ioniseer. Alhoewel hierdie elektrode proses van ionisasie effektief is vir kort ruimte missies, word dit onprakties vir meer ambisieuse ruimte missies as gevolg van verweering van elektrodes met verloop van tyd. ’n Alternatief is om die dryfmiddel/brandstof te ioniseer deur gebruik te maak van elektromagnetiese velde. Die elekromagnetiese velde sal die lewensduur van die vuurpyl vermeerder deur die verweering van elektrodes, wat geassosieer word met tipiese elektrieses vuurpyle, te elimineer. Hierdie tesis se doelwit is om die metode van mikrogolf ontslag ionisasie vir ’n elektriese vuurpyl/aandrywer te bestudeer om ten einde die lewensduur en doeltreffendheid van elektriese vuurpyl/aandrywer te ondersoek. Dit sluit in die ontwerp van ’n radio frekewensie ioon vuurpyl/aandrywer met ’n ontginning en versnelling matriks/rooster om stukrag te genereer. ’n 2,45 GHz magnetron (verkry vanaf ’n konvensionele mikrogolfoond), gekoppel aan ’n TM010 resonante holte, was gebruik om neutrale argon gas te ioniseer. Die proses van elektron siklotron resonansie (ESR) was gebruik om die doeltreffende ionisasie van ’n hoë digtheid plasma te verseker. Die aandrywing/stukrag was behaal met ’n drie-matriks-stelsel, bevoordeel deur hoë spannings om die positief-gelaaide argon ione te versnel. Resultate opgelewer, het die sukses van die ontwerp van ’n elektromagnetiese gebaseerde vuurpyl/aandrywer met ’n benaderde meting van ongeveer 1.78 mN van stukrag/aandrywing met ’n spesifieke impuls van Isp = 3786 sekondes bewys. Die ECR proses het ’n hoë plasma digtheid geproduseer met ’n plasma opname persentasie van ongeveer 77% van die totale inset mikrogolf energie. Die finale uitslae wat verkry was, het bevind dat die voorspelde resultate baie goed inpas met resultate in beskikbare literatuur. Dit dui op die doeltreffendheid van die RF ioon vuurpyl/aandrywer wat ontwerp is in hierdie projek vir die toekomstige gebruik in ruimte eksplorasie-aktiwiteite. Toekomstige navorsing moet op ’n beheerde terugvoer sisteem onderneem word, wat optimale werktoestande verseker vir maksimum prestasie. Daarbenewens moet die metode van matriks-lose versnelling bestudeer word, om maksimum versnelling/stukrag en spesifieke impuls te verseker.

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Rodrigues, Junior Robério. "Avaliação comparativa de recobrimentos superficiais para tuchos de válvula através de ensaios de desgaste." [s.n.], 2010. http://repositorio.unicamp.br/jspui/handle/REPOSIP/263572.

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Orientador: Cecília Amélia de Carvalho Zavaglia<br>Dissertação (mestrado profissional) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica<br>Made available in DSpace on 2018-08-16T19:02:52Z (GMT). No. of bitstreams: 1 RodriguesJunior_Roberio_M.pdf: 3328140 bytes, checksum: d0f2014c71eeb448ae530ee5df6b8479 (MD5) Previous issue date: 2010<br>Resumo: Com o intuito de avaliar a eficiência de diferentes recobrimentos superficiais aplicados a tuchos de válvulas - um componente utilizado em motores à combustão - foram propostos alguns recobrimentos que foram comparados a um recobrimento já utilizado pela indústria. Para as avaliações foram realizados ensaios de microdureza, ensaios de desgaste micro-abrasivo e avaliações da microestrutura dos recobrimentos. Os recobrimentos estudados foram: nitretação a gás convencional, esta já utilizada pela indústria; implantação iônica por imersão em plasma (IIIP) de nitrogênio; IIIP de nitrogênio sobre a camada já existente de nitretação a gás convencional; e confrontada com uma amostra sem nenhuma camada de recobrimento superficial aplicada. Os ensaios de desgaste micro-abrasivo foram realizados em um equipamento do tipo esfera contra bloco, utilizando solução abrasiva de carboneto de silício (SiC), e variando a carga normal aplicada, sendo elas de 1, 2 e 3N. Os resultados mostram que a nitretação a gás convencional obteve o mais elevado nível de microdureza na superfície e também o mais elevado nível de desgaste por micro-abrasão; este resultado prevaleceu nesta amostra para todas as cargas normais aplicadas. Em geral, a amostra que obteve o melhor nível de desgaste, ou seja, o menor volume desgastado foi a amostra que não tinha nenhum tipo de recobrimento<br>Abstract: With the intention to evaluate the efficiency of different coatings applied to valve tappets - a component used in combustion engines - was proposed some coatings that was compared to an coating already known by the industry. For the evaluations were performed micro hardness tests, micro abrasive wear tests and studies of the microstructure of the coatings. The coatings studied were: conventional gas nitriding, this one already used by the industry; ionic implantation by plasma immersion (IIPI) of nitrogen; IIPI of nitrogen over the layer already existing of conventional gas nitriding; against a sample that was tested without any layer of coating. The micro abrasive tests were performed in an equipment named ball-on-block, using abrasive solution of silicon carbide (SiC), and varying the normal load from 1, 2 and 3N. The results showed that the conventional gas nitriding performed the highest level of micro hardness on the surface, and also the highest level of micro abrasion wear; this result prevailed in this sample in all the normal load applied. Generally, the sample that obtained the best level of wear, in other words, the lowest worn volume was the sample whithout any coating<br>Mestrado<br>Materiais<br>Mestre em Engenharia Automobilistica

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Benyo, Theresa L. "Analytical and Computational Investigations of a Magnetohydrodynamic (MHD) Energy-Bypass System for Supersonic Turbojet Engines to Enable Hypersonic Flight." Kent State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=kent1369153719.

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Gustafsson, Karin. "Ion Current Dependence on Operating Condition and Ethanol Ratio." Thesis, Linköping University, Department of Electrical Engineering, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-8053.

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<p>This masters thesis investigates the possibility to estimate the ethanol content in the fuel using ion currents. Flexible fuel cars can be run on gasoline-ethanol blends with an ethanol content from0 to 85 percentage. It is important for the engine control system to have information about the fuel. In todays cars the measurements of the fuel blend are done by a sensor. If it is possible to do this with ion currents this can be used to detect if the sensor is broken, and then estimate the ethanol content until the sensor gets fixed. The benefit</p><p>of using ion currents is that the signal is measured directly from the spark plug and therefore no extra hardware is needed. To be able to see how the ethanol ratio affects the ion currents, the dependencies of the operating point have been investigated. This has been done by a literature review and by measurements in a Saab 9-3. Engine speed, load, ignition timing, lambda and spark plugs effects on the ion currents are especially studied. A black box model for the ion currents dependence on operating point is developed. This model describes the engine speed, load and ignition timing dependencies well, but it can not be used to estimate the ethanol ratio.</p>

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Books on the topic "Ion engines"

1

Starling, Dan A. Propellant feed control for ion engines. Naval Postgraduate School, 1996.

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Foster, John E. Inter-cusp ion and electron transport in a NSTAR-derivative ion thruster. National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Foster, John E. Inter-cusp ion and electron transport in a NSTAR-derivative ion thruster. National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Foster, John E. Inter-cusp ion and electron transport in a NSTAR-derivative ion thruster. National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Foster, John E. Inter-cusp ion and electron transport in a NSTAR-derivative ion thruster. National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Foster, John E. Internal plasma properties and enhanced performance of an 8-cm ion thruster discharge. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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Rawlin, Vincent K. Thermal environmental testing of NSTAR engineering model ion thrusters. National Aeronautics and Space Administration, Lewis Research Center, 1999.

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International Electric Propulsion Conference (24th 1995 Moscow, Russia). Proceedings of the 24th International Electric Propulsion Conference: IEPC. s.n., 1995.

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Stuart, Thomas A. Study of a high voltage ion engine power supply: NASA grant NAG3-1576. National Aeronautics and Space Administration, 1996.

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Foster, John E. Enhanced discharge performance in a ring cusp plasma source. National Aeronautics and Space Administration, Glenn Research Center, 2000.

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Book chapters on the topic "Ion engines"

1

Weißgerber, Tycho, and Gregor Kortendiek. "Spark Control for Ion Current Sensing." In Ignition Systems for Gasoline Engines. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-45504-4_12.

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Sheppard, C. G. W., and E.-S. A. A. Ibrahim. "S. I. Engine Ion Probe Diagnostics." In Instrumentation for Combustion and Flow in Engines. Springer Netherlands, 1989. http://dx.doi.org/10.1007/978-94-009-2241-9_19.

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Li, Ruiguang, Meng Shen, Hao Yu, Chao Li, Pengyu Duan, and Lihuang Zhu. "A Survey on Cyberspace Search Engines." In Communications in Computer and Information Science. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-33-4922-3_15.

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AbstractThis paper introduces the concept of cyberspace search engine, and makes a deep survey on 5 well-known search engines, say Shodan, Censys, BinaryEdge, ZoomEye and Fofa, by querying official websites, analyzing APIs, and making academic research. We discuss the following items in details: Supporting internet protocols, Total amounts of detected devices, Device information, Scanning frequency, System architecture, The third party databases, Probes distribution, etc. We give a comprehensive comparison of the detecting abilities and working principles of the cyberspace search engines.

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Calabretta, Michele, Alessandro Sitta, Salvatore Massimo Oliveri, and Gaetano Sequenzia. "Simulation of Dynamic Stresses on High Performance Engine Valve Spring System Considering Coil Clashing Effect." In Lecture Notes in Mechanical Engineering. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-70566-4_18.

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AbstractThe valve train plays a major role in the performance of internal combustion engines by controlling the combustion process and it is therefore one of the key aspects for increasing the efficiency of combustion engines. Considering the dynamics, the spring force must be high enough to reliably close the valve preventing from seating bouncing due to surge modes after the valve closure. On the other side, the spring force should be kept as low as possible in order to reduce the engine friction losses and consequently the fuel consumption. In the high-performance engines, the valve springs have to be designed and optimized for sustaining higher stresses with compact dimensions leading to critical material and manufacturing processes. This requires a reduction of moving masses and a strong focus on design and process optimization of the coil springs for reducing the mechanical load and the friction losses at low engine speed. At the same time, valve train should be reliable at high engine speed. The calculation of stresses and contact forces for moving parts under dynamic load is essential for durability analysis. A method to calculate the contact of moving masses is described and proposed to justify valve motions experimental results. To fully understand the failure mechanism of test bed reliability trials, the dynamic stresses have been calculated modeling the real springs’ shape. The contact forces have been reproduced considering the coil clash effects and the dynamic behavior of the flexible spring.

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5

Fiedler, Torben, Joachim Rösler, Martin Bäker, et al. "Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_19.

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Abstract To protect the copper liners of liquid-fuel rocket combustion chambers, a thermal barrier coating can be applied. Previously, a new metallic coating system was developed, consisting of a NiCuCrAl bond-coat and a Rene 80 top-coat, applied with high velocity oxyfuel spray (HVOF). The coatings are tested in laser cycling experiments to develop a detailed failure model, and critical loads for coating failure were defined. In this work, a coating system is designed for a generic engine to demonstrate the benefits of TBCs in rocket engines, and the mechanical loads and possible coating failure are analysed. Finally, the coatings are tested in a hypersonic wind tunnel with surface temperatures of 1350 K and above, where no coating failure was observed. Furthermore, cyclic experiments with a subscale combustion chamber were carried out. With a diffusion heat treatment, no large-scale coating delamination was observed, but the coating cracked vertically due to large cooling-induced stresses. These cracks are inevitable in rocket engines due to the very large thermal-strain differences between hot coating and cooled substrate. It is supposed that the cracks can be tolerated in rocket-engine application.

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Itterheim, Steffen, and Andreas Löw. "Physics Engines." In Learn cocos2D Game Development with iOS 5. Apress, 2011. http://dx.doi.org/10.1007/978-1-4302-3814-0_12.

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7

Badescu, Viorel. "Diesel Engines." In Optimal Control in Thermal Engineering. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-52968-4_20.

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8

Badescu, Viorel. "Photochemical Engines." In Optimal Control in Thermal Engineering. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-52968-4_22.

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9

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

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Palocz-Andresen, Michael. "Vehicle Engines." In Decreasing Fuel Consumption and Exhaust Gas Emissions in Transportation. Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-11976-7_9.

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Conference papers on the topic "Ion engines"

1

Janson, S. "Microwave interferometry for ion engines." In 30th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2741.

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2

Kubach, Heiko, Amin Velji, Ulrich Spicher, and Wolfgang Fischer. "Ion Current Measurement in Diesel Engines." In 2004 Powertrain & Fluid Systems Conference & Exhibition. SAE International, 2004. http://dx.doi.org/10.4271/2004-01-2922.

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3

BROPHY, JOHN. "Near-term, 100-kW class ion engines." In Conference on Advanced SEI Technologies. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3566.

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4

Yamamoto, Naoji, Taichi Morita, Ikkoh Funaki, Masakatsu Nakano, and Yasushi Ohkawa. "Demonstration of Wide Throttling Range Ion Engines." In 2018 Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4815.

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5

Fearn, David. "The Future Development of Gridded Ion Engines." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4714.

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6

ZARNITZ, F., K. GROH, H. LOEB, J. FELL, and F. WEBER. "Development status of the RIT ion engines." In 21st International Electric Propulsion Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2671.

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7

Förster, Jürgen, Achim Günther, Markus Ketterer, and Klaus-Jürgen Wald. "Ion Current Sensing for Spark Ignition Engines." In International Congress & Exposition. SAE International, 1999. http://dx.doi.org/10.4271/1999-01-0204.

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8

Mehresh, P., R. W. Dibble, and D. Flowers. "EGR effect on Ion Signal in HCCI Engines." In 2005 SAE Brasil Fuels & Lubricants Meeting. SAE International, 2005. http://dx.doi.org/10.4271/2005-01-2126.

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9

Kuninaka, Hitoshi, and Andrew V. Pakhomov. "Microwave Discharge Ion Engines onboard Hayabusa Asteroid Explorer." In BEAMED ENERGY PROPULSION: Fifth International Symposium on Beamed Energy Propulsion. AIP, 2008. http://dx.doi.org/10.1063/1.2931929.

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Przybylowski, J. N., J. E. Polk, and J. E. Shepherd. "Evidence for ion acceleration by oscillations in the discharge plasma of ion engines." In 2009 IEEE 36th International Conference on Plasma Science (ICOPS). IEEE, 2009. http://dx.doi.org/10.1109/plasma.2009.5227732.

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Reports on the topic "Ion engines"

1

Cheng, Wai, Victor Wong, Michael Plumley, et al. Lubricant Formulations to Enhance Engine Efficiency in Modern Internal Combustion Engines. Office of Scientific and Technical Information (OSTI), 2017. http://dx.doi.org/10.2172/1351980.

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2

Frame, Edwin A., Adam C. Brandt, Ruben Sr A. Alvarez, Allen S. Comfort, and Luis A. Villahermosa. Feasibility of Using Full Synthetic Low Viscosity Engine Oil at High Ambient Temperatures in U.S. Army Engines. Defense Technical Information Center, 2011. http://dx.doi.org/10.21236/ad1007443.

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Sugita, Takayuki. Compressed Air as a Quality and Pollution Free Fuel Substitute in Reciprocating Engines - Effective Solutions to Improve Engine Performance. SAE International, 2011. http://dx.doi.org/10.4271/2011-32-0509.

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Tubman, Michael, and Timothy Welp. Evaluation Tests of Select Fuel Additives for Potential Use in U.S. Army Corps of Engineers Diesel Engines. Defense Technical Information Center, 2016. http://dx.doi.org/10.21236/ad1013242.

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Eidler, Phillip. Dueco Plug-In Hybrid Engines. Office of Scientific and Technical Information (OSTI), 2011. http://dx.doi.org/10.2172/1055765.

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Xu, Hongming, Trevor Wilson, Stan Wallace, et al. Progress in FORESIGHT Homogeneous Autoignition Engines. SAE International, 2005. http://dx.doi.org/10.4271/2005-08-0221.

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Allen, Jr, and John J. Air Force Civil Engineers in Joint Engineer Operations: Validating the Concept and Incorporating Lessons Learned. Defense Technical Information Center, 2009. http://dx.doi.org/10.21236/ada513943.

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Dodge, L., and D. Naegeli. Combustion Characterization of Methylal in Reciprocating Engines. Office of Scientific and Technical Information (OSTI), 1994. http://dx.doi.org/10.2172/10157045.

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Dodge, L., and D. Naegeli. Hydrogen-air mixing evaluation in reciprocating engines. Office of Scientific and Technical Information (OSTI), 1994. http://dx.doi.org/10.2172/10156770.

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Failla, Charles C., and Andrew A. Pouring. Kerosene Base Fuels in Small Gasoline Engines. Defense Technical Information Center, 1991. http://dx.doi.org/10.21236/ada244846.

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