Relevant bibliographies by topics / Electric Propellant

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

Academic literature on the topic 'Electric Propellant'

Author: Grafiati
Published: 4 June 2021
Last updated: 5 February 2022

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Journal articles on the topic "Electric Propellant"

1

Glascock, Matthew S., Joshua L. Rovey, and Kurt A. Polzin. "Impulse and Performance Measurements of Electric Solid Propellant in a Laboratory Electrothermal Ablation-Fed Pulsed Plasma Thruster." Aerospace 7, no. 6 (May 30, 2020): 70. http://dx.doi.org/10.3390/aerospace7060070.

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Electric solid propellants are advanced solid chemical rocket propellants that can be controlled (ignited, throttled and extinguished) through the application and removal of an electric current. This behavior may enable the propellant to be used in multimode propulsion systems utilizing the ablative pulsed plasma thruster. The performance of an electric solid propellant operating in an electrothermal ablation-fed pulsed plasma thruster was investigated using an inverted pendulum micro-newton thrust stand. The impulse bit and specific impulse of the device using the electric solid propellant were measured for short-duration test runs of 100 pulses and longer-duration runs to end-of-life, at energy levels of 5, 10, 15 and 20 J. Also, the device was operated using the current state-of-the-art ablation-fed pulsed plasma thruster propellant, polytetrafluoroethylene (PTFE). Impulse bit measurements for PTFE indicate 100 ± 20 µN-s at an initial energy level of 5 J, which increases linearly with energy by approximately 30 µN-s/J. Within the error of the experiment, measurements of the impulse bit for the electric solid propellant are identical to PTFE. Specific impulse when operating on PTFE is calculated to be about 450 s. It is demonstrated that a surface layer in the hygroscopic electric solid propellant is rapidly ablated over the first few discharges of the device, which decreases the average specific impulse relative to the traditional polytetrafluoroethylene propellant. Correcting these data by subtracting the early discharge ablation mass loss measurements yields a corrected electric solid propellant specific impulse of approximately 300 s.
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Mukhtar, Amir, Habib Nasir, and Hizba Waheed. "Pressure-Time Study of Slow Burning Rate Ap/HTPB Based Composite Propellant by Using Closed Vessel Test (CVT)." Key Engineering Materials 778 (September 2018): 268–74. http://dx.doi.org/10.4028/www.scientific.net/kem.778.268.

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The Closed vessel (CV) is an equipment used to study the ballistic parameters by recording burning time history, pressure buildup during the process and vivacity of the propellants. It is an apparatus which consists of strong pressure vessel, piezo-electric pressure transducers, sensors and dedicated software. To save time and resources this method is employed instead of dynamic firing while doing research and development of propellants. A measured amount of propellant charge is loaded in the vessel and fired remotely. Ignition is provided by the filament which ignites the black powder charge. In this study, we have used Closed Vessel Tests (CVT) for the first time for recording the ballistic parameters of slow burning composite rocket propellant. We developed a set of composite solid propellant samples containing a mixture of bimodal Ammonium Perchlorate (AP) as an oxidizer, Hydroxy-terminated Polybutadiene (HTPB) as a binder as well as fuel, Dioctyl Sebacate (DOS) as plasticizer, 1-(2-methyl) Aziridinyl Phosphine Oxide (MAPO) as bonding agent and Toluene Diisocyanate (TDI) as curator. Samples were developed by changing the solid loading percentage of bimodal AP particles. By increasing the percentage of AP, the oxidizer-fuel ratio (O/F) increases which effects the ballistic parameters. It is observed that maximum pressure and vivacity increases with increase in solid filler in the propellants. As quantity of AP increases, rate of rise of pressure also increases. CVT firing of each sample was done three times to obtain average burning time and pressure buildup history to evaluate the effect of oxidizer loadings on ballistic parameters of the composite propellant.
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М. М. Челтонов, С. А. Опарин, Е. Ю. Нестерова, А. Л. Кириченко, and Е. Б. Устименко. "ПОЛУЧЕНИЕ МОДИФИЦИРОВАННЫХ НИТРАМИНОВ ДЛЯ ПРИМЕНЕНИЯ В НЕЭЛЕКТРИЧЕСКИХ СИСТЕМАХ ИНИЦИИРОВАНИЯ." World Science 1, no. 10(50) (October 31, 2019): 26–29. http://dx.doi.org/10.31435/rsglobal_ws/31102019/6716.

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In present-day conditions of Ukraine the setup of domestic production of non-electric initiation systems (NEIS) is an important issue. The main component of NEIS consisting of mixture of nitramine (octogen or hexogen) and aluminum. The deficiency of the above nitramines may be solved through applying the resource-recovery technologies of disposal of solid propellant (SP) and ammunition, which are further unusable as intended. However, when applying the mentioned technologies, the nitramine extracted from solid propellant and ammunition does not conform to the requirements on quality of commercial product for NEIS production. The purpose of this research is to obtain nitramine extracted from solid propellants by crystallization in dimethyl sulphoxide (DMSO) aqueous solution to obtain a product usable in manufacturing NEIS shock tubes.
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Rachov, P. A. Pavlov, H. Tacca, and D. Lentini. "Electric Feed Systems for Liquid-Propellant Rockets." Journal of Propulsion and Power 29, no. 5 (September 2013): 1171–80. http://dx.doi.org/10.2514/1.b34714.

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Schuster, J. R., C. T. Huynh, and G. E. Williams. "Electric orbit transfer vehicle cryogenic propellant system." Cryogenics 33, no. 4 (April 1993): 423–28. http://dx.doi.org/10.1016/0011-2275(93)90171-j.

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Glascock, Matthew S., Joshua L. Rovey, Shae Williams, and Jason Thrasher. "Plume Characterization of Electric Solid Propellant Pulsed Microthrusters." Journal of Propulsion and Power 33, no. 4 (July 2017): 870–80. http://dx.doi.org/10.2514/1.b36271.

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7

Glascock, Matthew S., Joshua L. Rovey, and Kurt A. Polzin. "Electric Solid Propellant Ablation in an Arc Discharge." Journal of Propulsion and Power 35, no. 5 (September 2019): 984–93. http://dx.doi.org/10.2514/1.b37517.

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NAKAYAMA, Yoshinori. "Propellant Flow Analysis within Electric Propulsion Test Facility." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 17, no. 3 (2019): 276–81. http://dx.doi.org/10.2322/tastj.17.276.

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Kang, Xiaoming, Lei Dong, and Wansheng Zhao. "Performance of propellant for ultrasonically aided electric propulsion." Acta Astronautica 98 (May 2014): 1–8. http://dx.doi.org/10.1016/j.actaastro.2014.01.003.

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10

Saravia, Manuel Martín, Luca Bernazzani, Alessio Ceccarini, Alfio Emanuele Vinci, and Fabrizio Paganucci. "Modeling and Characterization of a Thermally Controlled Iodine Feeding System for Electric Propulsion Applications." Aerospace 7, no. 2 (January 23, 2020): 10. http://dx.doi.org/10.3390/aerospace7020010.

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Iodine is considered as a feasible alternative to xenon as a propellant for electric propulsion systems, thanks to its good propulsive performance, high availability, and high storage density. However, as iodine is stored in solid state at ambient temperature, current state-of-the-art propellant management systems are not suitable to be used with it. Moreover, due to its high reactivity, iodine imposes requirements on material-compatibility, hindering the use of mass flow measurement and control systems typically used with other propellants. The architecture of a controlled iodine feeding system for low power (200 W class) ion and Hall effect thrusters is presented and the resulting prototype is described. It consists of a sublimation assembly whose temperature is used to control the tank pressure, a normally-closed ON-OFF valve, and a thermal throttle to perform the fine control of the mass flow rate. A 1D thermal-fluid model concerning the vapor generation in the tank, and its evolution along the different components is detailed. The thermal throttle model has been experimentally verified using air as a working fluid. The model results agree with the measurements of the verification tests in the hypothesis of the presence of an extended region at the entrance of the pipe where the laminar flow velocity and temperature profiles are not fully developed (known as entry flow region). Finally, the system is experimentally characterized and the model of the full system is calibrated using experimental measurements. The calibration shows that the thermal throttle flow presents an entry flow region, that the viscosity is correctly modeled, and that there is a difference between the measured tank temperature and the effective sublimation temperature.
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Dissertations / Theses on the topic "Electric Propellant"

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Singh, Lake Austin. "Very low earth orbit propellant collection feasibility assessment." Diss., Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/53039.

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This work focuses on the concept of sustainable propellant collection. The concept consists of gathering ambient gas while on-orbit and using it as propellant. Propellant collection could potentially enable operation in very-low Earth orbits without compromising spacecraft lifetime. This work conducts a detailed analysis of propellant collection from a physics perspective in order to test the assertions of previous researchers that propellant collection can dramatically reduce the cost of propellant on-orbit. Major design factors for propellant collection are identified from the fundamental propellant collection equations, which are derived in this work from first principles. A sensitivity analysis on the parameters in these equations determines the relative importance of each parameter to the overall performance of a propellant-collecting vehicle. The propellant collection equations enable the study of where propellant collection is technically feasible as a function of orbit and vehicle performance parameters. Two case studies conducted for a very-low Earth orbit science mission and a propellant depot-type mission serve to demonstrate the application of the propellant collection equations derived in this work. The results of this work show where propellant collection is technically feasible for a wide range of orbit and vehicle performance parameters. Propellant collection can support very-low Earth operation with presently available technology, and a number of research developments can further extend propellant-collecting concepts' ability to operate at low altitudes. However, propellant collection is not presently suitable for propellant depot applications due to limitations in power.
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Conley, Buford Ray. "Utilization of ambient gas as a propellant for low earth orbit electric propulsion." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/31061.

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Jain, Prachi Lalit. "Characterization of a Low Current LaB6 Heaterless Hollow Cathode with Krypton Propellant." Thesis, Virginia Tech, 2020. http://hdl.handle.net/10919/99141.

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A first-generation LaB6 heaterless hollow cathode with a flat-plate anode is experimentally investigated. The cathode is characterized using krypton as propellant at varying flow rates, discharge currents and cathode-anode distances. Voltage probes, used to make direct voltage measurements in the ignition circuit, are the only diagnostic tool used experimentally. A plasma model is used to infer plasma parameters in the cathode emitter region. The cathode characterization results are consistent with those obtained during previous investigations of 1 A-class LaB6 hollow cathode with krypton. A peak-to-peak anode voltage criterion is used to identify the discharge modes and the occurrence of mode transition. Fourier analysis of the keeper and anode voltage waveforms carried out to study the discharge mode behavior reveals resonant frequencies ranging from 40 to 150 kHz. Lastly, post-test visual observations of the cathode components show signs of emitter poisoning and keeper erosion.
Master of Science
Recent years have seen rapid growth in the development of both stand-alone satellites and satellite constellations. A critical component of these satellites is the on-board propulsion system, which is responsible for controlling their orientation with respect to the object of interest and keeping the spacecraft in the assigned orbit. Generally, electric propulsion systems are used for this purpose. These types of propulsion systems use electrical power to change the velocity of satellite, providing a small thrust for a long duration of time as compared to chemical propulsion systems. Certain types of electric thrusters utilize a hollow cathode device as an electron source to start-off and support the thruster operation. In this research, a non-conventional hollow cathode for low power applications is developed and tested. The main characteristic of the developed cathode is the heaterless configuration, which eliminates the heater module used in conventional cathodes to enable the cathode to reach its operational temperature. The absence of a heater reduces the complexity of the cathode and the electrical power system. The cathode utilizes an electron emitter material which is insensitive to impurities and air exposure. Additionally, unlike typical electric thrusters which use xenon as the fuel, this cathode uses krypton which is similar to xenon but is less expensive. The presented work includes an overview of electric propulsion and the hollow cathode operation, followed by a detailed discussion of the heaterless hollow cathode design, the experimental setup and the test results. Several noteworthy findings regarding cathode operation are included as well. This research shows that the non-conventional heaterless hollow cathode and its operation with krypton have the potential to improve the overall thruster performance by reducing the weight and the cost, thus contributing to an integral aspect of satellite on-board propulsion.
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Barizuddin, Syed. "Mesoporous iron oxide energetic composites with slow burn rate, sustained pressure and reduced ESD sensitivity for propellant applications." Diss., Columbia, Mo. : University of Missouri-Columbia, 2006. http://hdl.handle.net/10355/4571.

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Thesis (M.S.)--University of Missouri-Columbia, 2006.
The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on May 7, 2009) Includes bibliographical references.
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Marmuse, Florian. "Iodine plasmas : experimental and numerical studies. Application to electric propulsion." Thesis, Sorbonne université, 2020. http://www.theses.fr/2020SORUS110.

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L'iode est un carburant alternatif pour la propulsion électrique des satellites, avec des performances comparables à celles du xénon. En 2020, de tels systèmes de propulsion à l’iode sont déjà sur le marché. Ces bonnes performances sont liées à la très basse énergie de dissociation de I2, produisant un plasma similaire à un plasma de xénon. À quel point peut-on négliger la nature moléculaire et électronégative des plasmas d’iode? Un modèle global de plasma d’iode est amélioré et recodé en python, permettant des analyses paramétriques rapides, la quantification des incertitudes, et intégrant des effets électronégatifs. Des outils et procédures sont mis en place pour la pérennité des installations durant les expériences à l’iode. Quatre diagnostics optiques sont développés et installés sur la chambre d’ionisation du propulseur PÉGASES. Ils mènent, pour la première fois, à la température de I, ainsi qu’à la densité de I et I2: spectroscopie d’émission, spectroscopie d’absorption laser et absorption saturée à 10969 cm−1 et 11036 cm−1, absorption laser à 7603 cm−1, et absorption large-bande de 480nm à 500nm. Confronter ces données et celles issues d’une sonde de Langmuir au modèle global montre que le modèle surestime la dissociation de I2 et la densité électronique. Ces écarts peuvent être partiellement expliqués par des pertes de puissance sous-estimées dans le plasma, possiblement liées à sa nature moléculaire et électronégative. Ce travail donne des pistes pour de nouvelles études théoriques et de nouveaux diagnostics sur les plasmas d’iode. Il propose un modèle mis à jour et un panel de nouveaux diagnostics, utiles pour le développement de nouveaux systèmes de propulsion
Iodine is an alternative propellant for the electric propulsion of satellites, offering performances comparable to xenon. As of 2020, propulsion systems running on iodine are already on the market. These good performances are linked to the very low dissociation energy of I2, leading to a plasma similar to an atomic xenon plasma. To which extent can the molecular and electronegative nature of iodine plasmas be neglected? An existing global model for I2 plasmas is further developed and fully recoded in python, to enable fast parametric studies, uncertainty quantification, and integrate electronegative effects. Tools and processes are developed to ensure the safety of operators and experimental setups during iodine experiments. Four optical diagnostics are developed and installed on the ionization chamber of the PEGASES thruster. They lead for the first time to the density and temperature of I, and the density of I2: emission spectroscopy, laser absorption coupled to Doppler-free saturated absorption spectroscopy at 10969 cm−1 and 11036 cm−1, laser absorption spectroscopy at 7603 cm−1, and broadband absorption spectroscopy from 480nm to 500nm. Langmuir probe measurements yield the electron density and temperature. Confronting this data to the model shows that the model overestimates the molecular dissociation and the electron density. These discrepancies can be partly explained by underestimated power losses phenomena in the plasma, possibly linked to its molecular and electronegative nature. This work gives leads for future theoretical work and diagnostics on I2 plasmas. It proposes an updated model and a set of new diagnostics for use to further develop propulsion systems
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Taillefer, Zachary R. "Characterization of the Near Plume Region of Hexaboride and Barium Oxide Hollow Cathodes operating on Xenon and Iodine." Digital WPI, 2018. https://digitalcommons.wpi.edu/etd-dissertations/44.

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The use of electric propulsion for spacecraft primary propulsion, attitude control and station-keeping is ever-increasing as the technology matures and is qualified for flight. In addition, alternative propellants are under investigation, which have the potential to offer systems-level benefits that can enable particular classes of missions. Condensable propellants, particularly iodine, have the potential to significantly reduce the propellant storage system volume and mass. Some of the most widely used electric thrusters are electrostatic thrusters, which require a thermionic hollow cathode electron source to ionize the propellant for the main discharge and for beam neutralization. Failure of the hollow cathode, which often needs to operate for thousands of hours, is one of the main life-limiting factors of an electrostatic propulsion system. Common failure modes for hollow cathodes include poisoning or evaporation of the thermionic emitter material and erosion of electrodes due to sputtering. The mechanism responsible for the high energy ion production resulting in sputtering is not well understood, nor is the compatibility of traditional thermionic hollow cathodes with alternative propellants such as iodine. This work uses both an emissive probe and Langmuir probe to characterize the near-plume of several hollow cathodes operating on both xenon and iodine by measuring the plasma potential, plasma density, electron temperature and electron energy distribution function (EEDF). Using the EEDF the reaction rate coefficients for relevant collisional processes are calculated. A low current (< 5 A discharge current) hollow cathode with two different hexaboride emitters, lanthanum hexaboride (LaB6) and cerium hexaboride (CeB6), was operated on xenon propellant. The plasma potential, plasma density, electron temperature, EEDF and reaction rate coefficients were measured for both hexaboride emitter materials at a single cathode orifice diameter. The time-resolved plasma potential measurements showed low frequency oscillations (<100 kHz) of the plasma potential at low cathode flow rates (<4 SCCM) and spot mode operation between approximately 5 SCCM and 7 SCCM. The CeB6 and LaB6 emitters behave similarly in terms of discharge power (keeper and anode voltage) and plasma potential, based on results from a cathode with a 0.020�-diameter. Both emitters show almost identical operating conditions corresponding to the spot mode regime, reaction rates, as well as mean and RMS plasma potentials for the 0.020� orifice diameter at a flow rate of 6 SCCM and the same discharge current. The near-keeper region plasma was also characterized for several cathode orifice diameters using the CeB6 emitter over a range of propellant flow rates. The spot-plume mode transition appears to occur at lower flow rates as orifice size is increased, but has a minimum flow rate for stable operation. For two orifice diameters, the EEDF was measured in the near-plume region and reaction rate coefficients calculated for several electron- driven collisional processes. For the cathode with the larger orifice diameter (0.040�), the EEDFs show higher electron temperatures and drift velocities. The data for these cathodes also show lower reaction rate coefficients for specific electron transitions and ionization. To investigate the compatibility of a traditional thermionic emitter with iodine propellant, a low-power barium oxide (BaO) cathode was operated on xenon and iodine propellants. This required the construction and demonstration of a low flow rate iodine feed system. The cathode operating conditions are reported for both propellants. The emitter surface was inspected using a scanning electron microscope after various exposures to xenon and iodine propellants. The results of the inspection of the emitter surface are presented. Another low current (< 5 A), BaO hollow cathode was operated on xenon and iodine propellants. Its discharge current and voltage, and plume properties are reported for xenon and iodine with the cathode at similar operating conditions for each. The overall performance of the BaO cathode on iodine was comparable to xenon. The cathode operating on iodine required slightly higher power for ignition and discharge maintenance compared to xenon, as evident by the higher keeper and anode potentials. Plasma properties in the near- plume region were measured using an emissive probe and single Langmuir probe. For both propellants, the plasma density, electron energy distribution function (EEDF), electron temperature, select reaction rate coefficients and time-resolved plasma potentials are reported. For both propellants the cathode operated the same keeper (0.25 A) and discharge current (3.1 A), but the keeper and anode potentials were higher with iodine; 27 V and 51 V for xenon, and 30 V and 65 V for iodine, respectively. For xenon, the mean electron energy and electron temperature were 7.5 eV and 0.7 eV, with bulk drift energy of 6.6 eV. For iodine, the mean electron energy and electron temperature were 6.3 eV and 1.3 eV, with a bulk drift energy of 4.2 eV. A literature review of relevant collisional processes and associated cross sections for an iodine plasma is also presented.
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Gantt, Lynn Rupert. "Energy Losses for Propelling and Braking Conditions of an Electric Vehicle." Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/32879.

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The market segment of hybrid-electric and full function electric vehicles is growing within the automotive transportation sector. While many papers exist concerning fuel economy or fuel consumption and the limitations of conventional powertrains, little published work is available for vehicles which use grid electricity as an energy source for propulsion. Generally, the emphasis is put solely on the average drive cycle efficiency for the vehicle with very little thought given to propelling and braking powertrain losses for individual components. The modeling section of this paper will take basic energy loss equations for vehicle speed and acceleration, along with component efficiency information to predict the grid energy consumption in AC Wh/km for a given drive cycle. This paper explains how to calculate the forces experienced by a vehicle while completing a drive cycle in three different ways: using vehicle characteristics, United States Environmental Protection Agencyâ s (EPA) Dynamometer â targetâ coefficients, and an adaptation of the Sovran parameters. Once the vehicle forces are determined, power and energy demands at the wheels are determined. The vehicle power demands are split into propelling, braking, and idle to aide in the understanding of what it takes to move a vehicle and to identify possible areas for improvement. Then, using component efficiency data for various parameters of interest, the energy consumption of the vehicle as a pure EV is supplied in both DC (at the battery terminals) and AC (from the electric grid) Wh/km. The energy that flows into and out of each component while the vehicle is driving along with the losses at each step along the way of the energy path are detailed and explained. The final goal is to make the results of the model match the vehicle for any driving schedule. Validation work is performed in order to take the model estimates for efficiencies and correlate them against real world data. By using the Virginia Tech Range Extended Crossover (VTREX) and collecting data from testing, the parameters that the model is based on will be correlated with real world test data. The paper presents a propelling, braking, and net energy weighted drive cycle averaged efficiency that can be used to calculate the losses for a given cycle. In understanding the losses at each component, not just the individual efficiency, areas for future vehicle improvement can be identified to reduce petroleum energy use and greenhouse gases. The electric range of the vehicle factors heavily into the Utility Weighted fuel economy of a plug-in hybrid electric vehicle, which will also be addressed.
Master of Science
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8

Lee, Yeaw-Lip. "Particle-sizing system fro scanning electron microscope images of solid-propellant combustion exhaust." Thesis, Monterey, California. Naval Postgraduate School, 1991. http://hdl.handle.net/10945/28440.

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Tiffin, Daniel Joseph. "Orbital Fueling Architectures Leveraging Commercial Launch Vehicles for More Affordable Human Exploration." Case Western Reserve University School of Graduate Studies / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=case1575590285930015.

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Edwards, Clive Henderson. "Discharge characteristics and instabilities in the UK-25 ion thruster operating on inert gas propellants." Thesis, University of Southampton, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.242761.

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Books on the topic "Electric Propellant"

1

Zurawski, Robert L. Catalytic ignition of hydrogen and oxygen propellants. [Washington, DC: National Aeronautics and Space Administration, 1988.

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Whalen, Margaret V. Compatibility of grain-stabilized platinum with candidate propellants for resistojets. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Whalen, Margaret V. Compatibility of grain-stabilized platinum with candidate propellants for resistojets. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Whalen, Margaret V. Compatibility of grain-stabilized platinum with candidate propellants for resistojets. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Yiming, Li, ed. Ye ti yun zai huo jian xi tong dian ci jian rong xing wen ji. Beijing Shi: Yu hang chu ban she, 2002.

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Low power dc arcjet operation with hydrogen/nitrogen propellant mixtures. [Washington, DC]: National Aeronautics and Space Administration, 1986.

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Center, NASA Glenn Research, ed. Advanced electric propulsion for space solar power satellites. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

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M, Nelms R., Shepherd Michael T, and United States. National Aeronautics and Space Administration., eds. Design of a ZVS PWM inverter for a brushless DC motor in an EMA application. [Washington, DC: National Aeronautics and Space Administration, 1993.

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Numerical simulation of cylindrical, self-field MPD thrusters with multiple propellants. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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United States. National Aeronautics and Space Administration., ed. Numerical simulation of cylindrical, self-field MPD thrusters with multiple propellants. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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Book chapters on the topic "Electric Propellant"

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Shorikov, A. F., and V. I. Kalev. "Propellant Consumption Optimal Adaptive Terminal Control of Launch Vehicle." In Lecture Notes in Electrical Engineering, 107–19. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-39225-3_13.

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Li, Jinfei, Weidong Huang, Kai Qu, Wenshuang Wang, and Ming Yang. "Experimental Research on Fatigue Damage of Composite Solid Propellant with Constant Constrain." In Lecture Notes in Electrical Engineering, 315–22. Berlin, Heidelberg: Springer Berlin Heidelberg, 2016. http://dx.doi.org/10.1007/978-3-662-48768-6_36.

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Kim, Nak-Hwe, and Jun-Ho Huh. "A Method of Propelling with Many Whirlpools Used by Inland Birds." In Lecture Notes in Electrical Engineering, 805–10. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-1328-8_105.

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Kim, Nak-Hwe, and Jun-Ho Huh. "A Study on the Method of Propelling by Analyzing the Form of Bird’s Movement." In Lecture Notes in Electrical Engineering, 799–804. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-1328-8_104.

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Kondamudi, Srichandan, and Sandhya Thotakura. "Design of Multi-Stage Dodecapole Electrical Propelling System (DEPS) and Its Possible Use in the Hyperloop Transportation." In Algorithms for Intelligent Systems, 499–511. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-2109-3_46.

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Palaszewski, Bryan. "Martian Moons and Space Transportation Using Chemical and Electric Propulsion Options." In Solar Planets and Exoplanets [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.96717.

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Using chemical and nuclear electric propulsion for the exploration of the Martian moons will be investigated. Both oxygen/hydrogen chemical propulsion and nuclear electric propulsion with 500 kilowatt electric (kWe) to 10 megawatt electric (MWe) reactors will be assessed. The initial masses, propellant masses, and trip times for a variety of space vehicle payload masses will be compared. For high energy orbital transfer, the nuclear electric propulsion vehicles required a small fraction of the propellant mass over oxygen/hydrogen orbital transfer vehicles (OTVs). The moons, Phobos and Deimos, may hold resources for refueling future space vehicles. In-situ resource utilization (ISRU) can be a powerful method of reducing Earth dependence on space vehicle propellants, liquid water, and breathing gases. Historical studies have identified the potential of water in carbonaceous chondrites on the moons. The moon-derived propellants OTVs that move payloads between the moons and to other important operational Mars orbits. Also, the propellants have been suggested to support reusable Mars landers. To extract the water, the mined mass, its volume and the mining time were estimated. The water mass fraction may be as low as 2x10−4. Very large masses were needed to be extracted for up to 100 MT of water.
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Yarovenko, V. A. "DYNAMICS OF PROPELLING ELECTRIC POWER PLANTS OF ELECTRIC SHIPS’ PROPULSIVE COMPLEXES." In Development of Scientific Schools of Odessa National Maritime University, 139–63. Izdevnieciba “Baltija Publishing”, 2020. http://dx.doi.org/10.30525/978-9934-588-86-0.08.

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D. B., Vishwas, Gowtham M., Gururaj H. L., and Sam Goundar. "Industrial Internet of Things 4.0." In Advances in Computer and Electrical Engineering, 172–91. IGI Global, 2021. http://dx.doi.org/10.4018/978-1-7998-3375-8.ch012.

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In the era of mechanical digitalization, organizations are progressively putting resources into apparatuses and arrangements that permit their procedures, machines, workers, and even the products themselves to be incorporated into a solitary coordinated system for information assortment, information examination, the assessment of organization advancement, and execution improvement. This chapter presents a reference guide and review for propelling an Industry 4.0 venture from plan to execution, according to base on the economic and scientific policy of European parliament, applying increasingly effective creation forms, and accomplishing better profitability and economies of scale may likewise bring about expanded financial manageability. This chapter present the contextual analysis of a few Industry 4.0 applications. Authors give suggestions coordinating the progression of Industry 4.0. This section briefly portrays the advancement of IIoT 4.0. The change of ubiquitous computing through the internet of things has numerous difficulties related with it.
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Mosanako, Seamogano. "Broadcasting Policy in Botswana." In Advances in Electronic Government, Digital Divide, and Regional Development, 217–30. IGI Global, 2017. http://dx.doi.org/10.4018/978-1-5225-1859-4.ch014.

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The media has been considered an essential tool in propelling social change. Nonetheless, in Botswana, while the media is expected to play a role in the country's development, there exists a broadcasting policy vacuum in that there is no formal media policy to guide the operations of the media. A national television service, Botswana Television (Btv), is used as a case study in this chapter to demonstrate that the lack of media policy in Botswana and possibly other developing countries is generally responsible for poor performance of the broadcast media regarding its role in national development. Such poor performance of the media is reflected by domination of government originated content, domination of foreign content on local television, state control of the media as well as increasing pressure on the media to be more accessible to opposition political parties.
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Odetti, Angelo, Marco Altosole, Marco Bibuli, Gabriele Bruzzone, Massimo Caccia, and Michele Viviani. "Advance Speed-Hull-Pump-Jet Interactions in Small ASV." In Progress in Marine Science and Technology. IOS Press, 2020. http://dx.doi.org/10.3233/pmst200043.

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This paper is related to the technological development of an innovative small-size Autonomous Surface Vehicle designed to meet the requirement of accessing, monitoring and protecting the shallow waters peculiar of the Wetlands. The first prototype of a fully electric, modular, portable, lightweight, and highly-controllable Autonomous Surface Vehicle (ASV) for extremely shallow water and remote areas, namely SWAMP, was developed by CNR-INM and DITEN-Unige. This catamaran is equipped with four azimuth Pump-Jet Modular (PJM) actuators designed for small-size (1 to 1.5 m long) ASV. The main advantage of Pump-Jet thrusters is that they are flush with the hull, thus minimizing the risks of damages due to possible grounding. This system is used to increase the manoeuvrability in narrow spaces and to increase the spacial resolution by allowing the access also in extremely shallow waters with smaller risk of loosing manoeuvrability. The knowledge of the hydrodynamic characteristics of the thruster and of the vessel allows to partly or fully identifying the vessel for a better controllability. With this aim a series of tests have been conducted in the DITEN towing tank. In particular advance resistance on the SWAMP hull in deep and shallow water, bollard pull and self-propelling tests with the Pump-Jet Module working have been carried out. The results of the tests with the effects of advance speed on the PJM performance is reported in this paper together with the description of the modelling of the thruster itself.
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Conference papers on the topic "Electric Propellant"

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Anderson, John, and Dennis Fitzgerald. "Fullerene propellant research for electric propulsion." In 32nd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-3211.

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Glascock, Matthew S., and Joshua Rovey. "Electric Solid Propellant Ablation in a Pulsed Electric Thruster." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4818.

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KELLY, A., and R. JAHN. "MPD thruster performance - Propellant distribution and species effects." In International Electric Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-2022.

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PACCANI, G. "Non-steady solid propellant MPD thruster experimental analysis concepts." In 21st International Electric Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2674.

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PACCANI, G. "A coaxial non-steady solid propellant MPD thruster experimental analysis." In 19th International Electric Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1095.

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Toki, Kyoichiro, Norihiro Asakura, Tomohiro Ohtsuka, and Taku Akazawa. "Experiments on a Propellant-less Electric Propulsion Using Photon Pressure." In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-4819.

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Frisbee, Robert, James Polk, Alec Gallimore, and Colleen Marrese. "Oxygen-propellant plasma thrusters for cis-lunar electric propulsion missions." In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3994.

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BERG, H. P., and H. BASSNER. "Propellant storage and feed system for the radiofrequency ion propulsion assembly RITA." In 21st International Electric Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2592.

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Tverdokhlebov, O., and A. Semenkin. "Iodine propellant for electric propulsion - To be or not to be." In 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3350.

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Glascock, Matthew S., Joshua Rovey, Shae Williams, and Jason Thrasher. "Plasma Plume Characterization of Electric Solid Propellant Micro Pulsed Plasma Thrusters." In 51st AIAA/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-4185.

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Reports on the topic "Electric Propellant"

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Burton, Rodney L. Pulsed Electric Microthrusters With Solid Propellant for Microsats and Nanosats. Fort Belvoir, VA: Defense Technical Information Center, April 2002. http://dx.doi.org/10.21236/ada401337.

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Klingenberg, G., H. J. Frieske, and H. Rockstroh. Electrical Ignition of Han-Based Liquid Propellants. Fort Belvoir, VA: Defense Technical Information Center, January 1990. http://dx.doi.org/10.21236/ada223272.

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