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Journal articles on the topic 'Hall effect thruster'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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1

Hopping, Ethan P., Wensheng Huang, and Kunning G. Xu. "Small Hall Effect Thruster with 3D Printed Discharge Channel: Design and Thrust Measurements." Aerospace 8, no. 8 (2021): 227. http://dx.doi.org/10.3390/aerospace8080227.

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This paper presents the design and performance of the UAH-78AM, a low-power small Hall effect thruster. The goal of this work is to assess the feasibility of using low-cost 3D printing to create functioning Hall thrusters, and study how 3D printing can expand the design space. The thruster features a 3D printed discharge channel with embedded propellant distributor. Multiple materials were tested including ABS, ULTEM, and glazed ceramic. Thrust measurements were obtained at the NASA Glenn Research Center. Measured thrust ranged from 17.2–30.4 mN over a discharge power of 280 W to 520 W with an anode ISP range of 870–1450 s. The thruster has a similar performance range to conventional thrusters at the same power levels. However, the polymer ABS and ULTEM materials have low temperature limits which made sustained operation difficult.

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2

Baird, Matthew, Thomas Kerber, Ron McGee-Sinclair, and Kristina Lemmer. "Plume Divergence and Discharge Oscillations of an Accessible Low-Power Hall Effect Thruster." Applied Sciences 11, no. 4 (2021): 1973. http://dx.doi.org/10.3390/app11041973.

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Hall effect thrusters (HETs) are an increasingly utilized proportion of electric propulsion devices due to their high thrust-to-power ratio. To enable an accessible research thruster, our team used inexpensive materials and simplified structures to fabricate the 44-mm-diameter Western Hall Thruster (WHT44). Anode flow, discharge voltage, magnet current, and cathode flow fraction (CFF) were independently swept while keeping all other parameters constant. Simultaneously, a Faraday probe was used to test plume properties at a variety of polar coordinate distances, and an oscilloscope was used to capture discharge oscillation behavior. Plasma plume divergence angle at a fixed probe distance of 4.5 thruster diameters increased with increasing anode flow, varying from 36.7° to 37.4°. Moreover, divergence angle decreased with increasing discharge voltage, magnet current, and CFF, by 0.3°, 0.2°, and 8°, respectively, over the span of the swept parameters. Generally, the thruster exhibited a strong oscillation near 90 kHz, which is higher than a similarly sized HET (20–60 kHz). The WHT44 noise frequency spectra became more broadband and the amplitude increased at a CFF of less than 1.5% and greater than 26%. Only the low flow and low voltage operating conditions showed a quiescent sinusoidal discharge current; otherwise, the discharge current probability distribution was Gaussian. This work demonstrates that the WHT44 thruster, designed for simplicity of fabrication, is a viable tool for research and academic purposes.

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3

Yan, Li, Ping-Yang Wang, Yang-Hua Ou, and Xiao-Lu Kang. "Numerical Study of Hall Thruster Plume and Sputtering Erosion." Journal of Applied Mathematics 2012 (2012): 1–16. http://dx.doi.org/10.1155/2012/327021.

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Potential sputtering erosion caused by the interactions between spacecraft and plasma plume of Hall thrusters is a concern for electric propulsion. In this study, calculation model of Hall thruster’s plume and sputtering erosion is presented. The model is based on three dimensional hybrid particle-in-cell and direct simulation Monte Carlo method (PIC/DSMC method) which is integrated with plume-wall sputtering yield model. For low-energy heavy-ion sputtering in Hall thruster plume, the Matsunami formula for the normal incidence sputtering yield and the Yamamura angular dependence of sputtering yield are used. The validation of the simulation model is realized through comparing plume results with the measured data. Then, SPT-70’s sputtering erosion on satellite surfaces is assessed and effect of mass flow rate on sputtering erosion is analyzed.

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4

Zidar, David G., and Joshua L. Rovey. "Hall-Effect Thruster Channel Surface Properties Investigation." Journal of Propulsion and Power 28, no. 2 (2012): 334–43. http://dx.doi.org/10.2514/1.b34312.

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5

Boniface, C., G. J. M. Hagelaar, L. Garrigues, J. P. Boeuf, and M. Prioul. "Modeling of double stage Hall effect thruster." IEEE Transactions on Plasma Science 33, no. 2 (2005): 522–23. http://dx.doi.org/10.1109/tps.2005.845117.

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6

Kurzyna, Jacek, Maciej Jakubczak, Agnieszka Szelecka, and Käthe Dannenmayer. "Performance tests of IPPLM's krypton Hall thruster." Laser and Particle Beams 36, no. 1 (2018): 105–14. http://dx.doi.org/10.1017/s0263034618000046.

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AbstractThe Institute of Plasma Physics and Laser Microfusion's (IPPLM) Hall effect thruster (Krypton Large IMpulse Thruster, KLIMT) is a 500 W class plasma engine with a mean diameter of discharge channel of 42 mm. KLIMT was developed within ESA/PECS project aiming to provide relatively small thruster for satellites that would be able to effectively operate with krypton propellant. Being several times less expensive than xenon, which is regarded as a propellant of choice for electric propulsion of electrostatic type, krypton since years has been suggested as an attractive alternative. In this paper, a design as well as performance tests of the laboratory model of KLIMT are discussed. It is shown that precise adjustment of magnetic field topography results in the stable operation of the thruster in wide range of operating conditions providing similar thrust and specific impulse production for both propellants. Maximum thrust produced with the use of xenon and krypton reached about 16–17 mN for mass flow rate of 1.15–1.2 mg/s resulting in specific impulse in the range of 1300–1500 s (13–15 km/s). However, for krypton the anode efficiency drops by ~10% in comparison with xenon. For krypton plasma beam divergence as measured by an average half-angle with respect to the beam axis was found to remain within the range of 19–23° for the whole set of the examined operating conditions. The reported characteristics are reasonable for Hall thruster of the discussed size and power.

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7

Langendorf, S., K. Xu, and M. Walker. "Effects of wall electrodes on Hall effect thruster plasma." Physics of Plasmas 22, no. 2 (2015): 023508. http://dx.doi.org/10.1063/1.4908273.

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8

Szelecka, Agnieszka, Jacek Kurzyna, and Loic Bourdain. "Thermal stability of the krypton Hall effect thruster." Nukleonika 62, no. 1 (2017): 9–15. http://dx.doi.org/10.1515/nuka-2017-0002.

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Abstract The Krypton Large IMpulse Thruster (KLIMT) ESA/PECS project, which has been implemented in the Institute of Plasma Physics and Laser Microfusion (IPPLM) and now is approaching its final phase, was aimed at incremental development of a ~500 W class Hall effect thruster (HET). Xenon, predominantly used as a propellant in the state-of-the-art HETs, is extremely expensive. Krypton has been considered as a cheaper alternative since more than fifteen years; however, to the best knowledge of the authors, there has not been a HET model especially designed for this noble gas. To address this issue, KLIMT has been geared towards operation primarily with krypton. During the project, three subsequent prototype versions of the thruster were designed, manufactured and tested, aimed at gradual improvement of each next exemplar. In the current paper, the heat loads in new engine have been discussed. It has been shown that thermal equilibrium of the thruster is gained within the safety limits of the materials used. Extensive testing with both gases was performed to compare KLIMT’s thermal behaviour when supplied with krypton and xenon propellants.

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9

Szelecka, Agnieszka. "Advanced laboratory for testing plasma thrusters and Hall thruster measurement campaign." Nukleonika 61, no. 2 (2016): 213–18. http://dx.doi.org/10.1515/nuka-2016-0036.

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Abstract Plasma engines are used for space propulsion as an alternative to chemical thrusters. Due to the high exhaust velocity of the propellant, they are more efficient for long-distance interplanetary space missions than their conventional counterparts. An advanced laboratory of plasma space propulsion (PlaNS) at the Institute of Plasma Physics and Laser Microfusion (IPPLM) specializes in designing and testing various electric propulsion devices. Inside of a special vacuum chamber with three performance pumps, an environment similar to the one that prevails in space is created. An innovative Micro Pulsed Plasma Thruster (LμPPT) with liquid propellant was built at the laboratory. Now it is used to test the second prototype of Hall effect thruster (HET) operating on krypton propellant. Meantime, an improved prototype of krypton Hall thruster is constructed.

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10

Mullins, Carl R., Casey C. Farnell, Cody C. Farnell, et al. "Non-invasive Hall current distribution measurement in a Hall effect thruster." Review of Scientific Instruments 88, no. 1 (2017): 013507. http://dx.doi.org/10.1063/1.4974098.

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11

Book, Carl F., and Mitchell L. R. Walker. "Effect of Anode Temperature on Hall Thruster Performance." Journal of Propulsion and Power 26, no. 5 (2010): 1036–44. http://dx.doi.org/10.2514/1.48028.

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12

Garrigues, L., G. J. M. Hagelaar, C. Boniface, and J. P. Boeuf. "Optimized atom injection in a Hall effect thruster." Applied Physics Letters 85, no. 22 (2004): 5460–62. http://dx.doi.org/10.1063/1.1829137.

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13

Jiang, Yiwei, Haibin Tang, Junxue Ren, Min Li, and Jinbin Cao. "Magnetic mirror effect in a cylindrical Hall thruster." Journal of Physics D: Applied Physics 51, no. 3 (2017): 035201. http://dx.doi.org/10.1088/1361-6463/aa9e3e.

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14

Guo, Zongshuai. "Radial distribution of electrons rotation moment in hall effect and plasma-ion thrusters." Aerospace technic and technology, no. 4 (August 27, 2021): 28–34. http://dx.doi.org/10.32620/aktt.2021.4.04.

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The subject matter of the article is the radial distribution of electrons movement parameters inside electric propulsion thrusters with closed electrons drift. The radial magnetic field in Hall effect thrusters is the limits the axial flow of electrons because of interaction with azimuth electron current. In turn, this azimuth current exists as a result of rivalry between the attempt of the magnetic field to transform electrons current completely closed one and the loss of electrons rotation moment in collisions. Similar processes take place in the ionization chamber of plasma-ion thrusters with the radial magnetic field. The attempts to estimate electrons parameters through only collisions with ions and atoms inside volume have given the value of axial electrons current much lower than really being. This phenomenon is called anomalous electrons conductivity, which was tried to be explained as a consequence of various effects including "near-the-wall-conductivity", which was explained as a result of non-mirror reflection of electrons from the Langmuir layer near the walls of the thruster channel. The disadvantage of this name is the fact that the reflection of the electron occurs before reaching the surface from the potential barrier at the plasma boundary with any environment: the wall, but also with the environment vacuum. The potential distribution in the Langmuir layer is non-stationary and inhomogeneous due to the presence of so-called plasma oscillations. The definition of "conductivity" is just as unfortunate in this name, because the collisions are always not a factor of conductivity, but on the contrary – of resistance. The goal is to solve the task of electrons rotation moment distribution in the thruster channel. The methods used are the formulation of the kinetic equation for electrons distribution function over the velocities, radius, and projections of the coordinates of the instantaneous center of cyclotron rotation; solution of this equation and finding with its use the distribution of the gas-dynamic parameters of electrons along the cross-section of the channel. Conclusions. A mathematical model of electrons rotation moment dynamics is proposed, which allows using plasma-dynamics equations to analyze its distribution along the cross-section of thruster channel and to estimate the effect of "near-the-wall-conductivity" using appropriate boundary conditions.

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15

Désangles, Victor, Sergey Shcherbanev, Thomas Charoy, et al. "Fast Camera Analysis of Plasma Instabilities in Hall Effect Thrusters Using a POD Method under Different Operating Regimes." Atmosphere 11, no. 5 (2020): 518. http://dx.doi.org/10.3390/atmos11050518.

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Even after half a century of development, many phenomena in Hall Effect Thrusters are still not well-understood. While numerical studies are now widely used to study this highly non-linear system, experimental diagnostics are needed to validate their results and identify specific oscillations. By varying the cathode heating current, its emissivity is efficiently controlled and a transition between two functioning regimes of a low power thruster is observed. This transition implies a modification of the axial electric field and of the plasma plume shape. High-speed camera imaging is performed and the data are analysed using a Proper Orthogonal Decomposition method to isolate the different types of plasma fluctuations occurring simultaneously. The low-frequency breathing mode is observed, along with higher frequency rotating modes that can be associated to rotating spokes or gradient-induced instabilities. These rotating modes are observed while propagating outside the thruster channel. The reduction of the cathode emissivity beyond the transition comes along with a disappearance of the breathing mode, which could improve the thruster performance and stability.

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16

Panelli, Mario, Davide Morfei, Beniamino Milo, Francesco D’Aniello, and Francesco Battista. "Axisymmetric Hybrid Plasma Model for Hall Effect Thrusters." Particles 4, no. 2 (2021): 296–324. http://dx.doi.org/10.3390/particles4020026.

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Hall Effect Thrusters (HETs) are nowadays widely used for satellite applications because of their efficiency and robustness compared to other electric propulsion devices. Computational modelling of plasma in HETs is interesting for several reasons: it can be used to predict thrusters’ operative life; moreover, it provides a better understanding of the physical behaviour of this device and can be used to optimize the next generation of thrusters. In this work, the discharge within the accelerating channel and near-plume of HETs has been modelled by means of an axisymmetric hybrid approach: a set of fluid equations for electrons has been solved to get electron temperatures, plasma potential and the discharge current, whereas a Particle-In-Cell (PIC) sub-model has been developed to capture the behaviour of neutrals and ions. A two-region electron mobility model has been incorporated. It includes electron–neutral/ion collisions and uses empirical constants, that vary as a continuous function of axial coordinates, to take into account electron–wall collisions and Bohm diffusion/SEE effects. An SPT-100 thruster has been selected for the verification of the model because of the availability of reliable numerical and experimental data. The results of the presented simulations show that the code is able to describe plasma discharge reproducing, with consistency, the physics within the accelerating channel of HETs. A small discrepancy in the experimental magnitude of ions’ expansion, due probably to boundary condition effects, has been found.

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17

Makela, Jason M., Robert L. Washeleski, Dean R. Massey, Lyon B. King, and Mark A. Hopkins. "Development of a Magnesium and Zinc Hall-Effect Thruster." Journal of Propulsion and Power 26, no. 5 (2010): 1029–35. http://dx.doi.org/10.2514/1.47410.

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18

Dragnea, Horatiu C., Alejandro Lopez Ortega, Hani Kamhawi, and Iain D. Boyd. "Simulation of a Hall Effect Thruster Using Krypton Propellant." Journal of Propulsion and Power 36, no. 3 (2020): 335–45. http://dx.doi.org/10.2514/1.b37499.

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19

Dorf, L., Y. Raitses, N. J. Fisch, and V. Semenov. "Effect of anode dielectric coating on Hall thruster operation." Applied Physics Letters 84, no. 7 (2004): 1070–72. http://dx.doi.org/10.1063/1.1646727.

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20

ROSSI, Alberto, Frédéric MESSINE, and Carole HENAUX. "Parametric Optimization of a Hall Effect Thruster Magnetic Circuit." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14, ists30 (2016): Pb_197—Pb_202. http://dx.doi.org/10.2322/tastj.14.pb_197.

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21

Frieman, Jason D., Nathan P. Brown, Connie Y. Liu, et al. "Impact of Propellant Species on Hall Effect Thruster Electrical Facility Effects." Journal of Propulsion and Power 34, no. 3 (2018): 600–613. http://dx.doi.org/10.2514/1.b36566.

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22

Cichocki, Filippo, Adrián Domínguez-Vázquez, Mario Merino, Pablo Fajardo, and Eduardo Ahedo. "Three-dimensional neutralizer effects on a Hall-effect thruster near plume." Acta Astronautica 187 (October 2021): 498–510. http://dx.doi.org/10.1016/j.actaastro.2021.06.042.

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23

ROY, SUBRATA, and B. P. PANDEY. "Plasma–wall interaction inside a Hall thruster." Journal of Plasma Physics 68, no. 4 (2002): 305–19. http://dx.doi.org/10.1017/s0022377802002027.

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The dynamics of a Hall thruster is investigated numerically in the presence of a plasma–wall interaction. The plasma–wall interaction is a function of the wall potential, which in turn is determined by the secondary electron emission and sputtering yield. In the present work, the effect of secondary electron emission and sputter yield have been considered simultaneously. Owing to disparate temporal scales, ions and neutrals have been described by a set of time-dependent equations while electrons are considered in a steady state. Based on the experimental observations, a third-order polynomial in electron temperature is used to calculate the ionization rate. The changes in the plasma density, potential and azimuthal electron velocity due to the sputter yield are significant in the acceleration region. The change in ion and electron velocity and temperature is small. The neutral velocity, which decreases initially, starts increasing towards the exit consistent with the computed neutral density profile. The results are qualitatively compared with the experiments.

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24

Passaro, A., A. Vicini, F. Nania, and L. Biagioni. "Numerical Rebuilding of SMART-1 Hall Effect Thruster Plasma Plume." Journal of Propulsion and Power 26, no. 1 (2010): 149–58. http://dx.doi.org/10.2514/1.36821.

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25

Hause, Michael L., Benjamin D. Prince, and Raymond J. Bemish. "Krypton charge exchange cross sections for Hall effect thruster models." Journal of Applied Physics 113, no. 16 (2013): 163301. http://dx.doi.org/10.1063/1.4802432.

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26

Boniface, C., L. Garrigues, G. J. M. Hagelaar, J. P. Boeuf, D. Gawron, and S. Mazouffre. "Anomalous cross field electron transport in a Hall effect thruster." Applied Physics Letters 89, no. 16 (2006): 161503. http://dx.doi.org/10.1063/1.2360182.

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27

Garrigues, L., J. Pérez-Luna, J. Lo, G. J. M. Hagelaar, J. P. Boeuf, and S. Mazouffre. "Empirical electron cross-field mobility in a Hall effect thruster." Applied Physics Letters 95, no. 14 (2009): 141501. http://dx.doi.org/10.1063/1.3242336.

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28

Kwon, Kybeom, Mitchell L. R. Walker, and Dimitri N. Mavris. "Self-consistent, one-dimensional analysis of the Hall effect thruster." Plasma Sources Science and Technology 20, no. 4 (2011): 045021. http://dx.doi.org/10.1088/0963-0252/20/4/045021.

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29

Li, Lai, Xi Lu, Hulin Huang, Xidong Zhang, and Guiping Zhu. "The Numerical Simulation of a High Power Hall Effect Thruster." IOP Conference Series: Earth and Environmental Science 192 (November 5, 2018): 012008. http://dx.doi.org/10.1088/1755-1315/192/1/012008.

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30

Kwon, Kybeom, Mitchell L. R. Walker, and Dimitri N. Mavris. "Study on Anomalous Electron Diffusion in the Hall Effect Thruster." International Journal of Aeronautical and Space Sciences 15, no. 3 (2014): 320–34. http://dx.doi.org/10.5139/ijass.2014.15.3.320.

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31

Kim, Eun-Hyouek, Youn-Ho Kim, Jong-Soo Park, Dong-Wook Koh, Yun-Hwang Jeong, and Hyun-Woo Lee. "Orbit Evolution Analysis of DubaiSat-2 using Hall-effect Thruster." Journal of the Korean Society for Aeronautical & Space Sciences 43, no. 4 (2015): 377–86. http://dx.doi.org/10.5139/jksas.2015.43.4.377.

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32

Langendorf, S., and M. L. R. Walker. "Characterization of Hall effect thruster propellant distributors with flame visualization." Review of Scientific Instruments 84, no. 1 (2013): 013302. http://dx.doi.org/10.1063/1.4774049.

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33

Loyan, A. V., S. Yu Nesterenko, Guo Zongshuai та Huang Zhihao. "КВАЗІОДНОВИМІРНА МАТЕМАТИЧНА МОДЕЛЬ ПРОЦЕСІВ В ХОЛЛІВСЬКОМУ ТА ПЛАЗМОВО-ІОННОМУ ДВИГУНІ". Open Information and Computer Integrated Technologies, № 92 (6 вересня 2021): 41–54. http://dx.doi.org/10.32620/oikit.2021.92.04.

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Plasma-ion thrusters with a radial magnetic field in ionization chamber and Hall effect thrusters are electrostatic electric propulsion thrusters with closed electron drift. Axial symmetry in the dynamics of the components of propellant in these thrusters allows to write the equations of plasma-dynamics for electrons, ions and neutral atoms in two-dimensional axial-radial form. Attempts to reduce the equations to simpler one-dimensional form by simply removing the components with radius differentiation lead to the loss in the description of important effects, responsible for values of thruster performance. At the same time, a significant disadvantage of gas dynamics equation set is its fundamental openness – the correspondence between the number of unknown variables and equations is achieved approximately basing on some assumptions. In traditional form of gas dynamics, such closeness is made under the assumption of thermodynamic equilibrium with velocity distribution functions of components close to Maxwell one, which is the limit result of collisions. The use of such approximation to plasma components dynamics in electric propulsion thrusters is impossible due to the rarefaction of the substance in them. A mathematical model of two-component plasma-dynamics is represented in stationary form to describe the processes in the Hall effect thruster channel and the ionization chamber of plasma-ion thruster with radial magnetic field. Due to the impossibility of using the method of local thermodynamic equilibrium to describe the rarefied substance in electric propulsion thruster, a more advanced form of equations is used. A more reliable means of approximate closure of the set of equations is proposed in the description of the rarified gas. An approach to the description of the specifics of electrons energy transfer from the plasma to the walls of the channel, as well as the non-mirror reflection of electrons from the potential barrier within the Langmuir layer is shown. A method of averaging the parameters over the cross section of the channel is proposed, which allows to convert the equation into a quasi-one-dimensional form with the preservation of charge, momentum and energy losses on the channel walls.

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34

Xu, Kunning G., and Mitchell L. R. Walker. "Technique to Collimate Ions in a Hall-Effect Thruster Discharge Chamber." Journal of Propulsion and Power 27, no. 3 (2011): 564–72. http://dx.doi.org/10.2514/1.49171.

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35

Cho, Shinatora, Hiroki Watanabe, Kenichi Kubota, and Ikkoh Funaki. "Numerical Sensitivity Analysis of Chamber Backpressure Effect in Hall Thruster Experiment." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 66, no. 3 (2018): 61–68. http://dx.doi.org/10.2322/jjsass.66.61.

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36

Martinez, Rafael A., Hoang Dao, and Mitchell L. R. Walker. "Power Deposition into the Discharge Channel of a Hall Effect Thruster." Journal of Propulsion and Power 30, no. 1 (2014): 209–20. http://dx.doi.org/10.2514/1.b34897.

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37

Frieman, Jason D., Thomas M. Liu, and Mitchell L. R. Walker. "Background Flow Model Validation with a Six-Kilowatt Hall Effect Thruster." Journal of Propulsion and Power 36, no. 2 (2020): 308–11. http://dx.doi.org/10.2514/1.b37512.

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38

Hargus, William A. "Laser-Induced-Fluorescence-Derived Hall Effect Thruster Ion Velocity Distribution Visualization." IEEE Transactions on Plasma Science 39, no. 11 (2011): 2918–19. http://dx.doi.org/10.1109/tps.2011.2132149.

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39

Kwon, Ky-Beom. "Design Space Exploration of the Hall Effect Thruster for Conceptual Design." Journal of the Korean Society for Aeronautical & Space Sciences 39, no. 12 (2011): 1133–40. http://dx.doi.org/10.5139/jksas.2011.39.12.1133.

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40

Xu, Zhang, Wei Liqiu, Han Liang, Ding Yongjie, and Yu Daren. "Effect of azimuthal diversion rail on an ATON-type Hall thruster." Journal of Physics D: Applied Physics 50, no. 9 (2017): 095202. http://dx.doi.org/10.1088/1361-6463/aa5622.

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41

Ding, Yongjie, Boyang Jia, Yu Xu, et al. "Effect of vortex inlet mode on low-power cylindrical Hall thruster." Physics of Plasmas 24, no. 8 (2017): 080703. http://dx.doi.org/10.1063/1.4986007.

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42

Balika, L., C. Focsa, S. Gurlui, et al. "Laser ablation in a running hall effect thruster for space propulsion." Applied Physics A 112, no. 1 (2012): 123–27. http://dx.doi.org/10.1007/s00339-012-7211-0.

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43

Xu, Kunning G., and Mitchell L. R. Walker. "Effect of External Cathode Azimuthal Position on Hall-Effect Thruster Plume and Diagnostics." Journal of Propulsion and Power 30, no. 2 (2014): 506–13. http://dx.doi.org/10.2514/1.b34980.

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44

Chernyshev, Timofey, Eduard Son, and Oleg Gorshkov. "2D3V kinetic simulation of Hall effect thruster, including azimuthal waves and diamagnetic effect." Journal of Physics D: Applied Physics 52, no. 44 (2019): 444002. http://dx.doi.org/10.1088/1361-6463/ab35cb.

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45

Yuge, Seiro, Atsushi Shirasaki, and Hirokazu Tahara. "Effect of Magnetic Field Characteristics on Thrust Efficiency and Internal Efficiency of a Hall Thruster." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 55, no. 636 (2007): 8–16. http://dx.doi.org/10.2322/jjsass.55.8.

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46

Kwon, Kybeom, Gregory Lantoine, Ryan P. Russell, and Dimitri N. Mavris. "A study on simultaneous design of a Hall Effect Thruster and its low-thrust trajectory." Acta Astronautica 119 (February 2016): 34–47. http://dx.doi.org/10.1016/j.actaastro.2015.11.002.

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47

Szelecka, Agnieszka, Maciej Jakubczak, and Jacek Kurzyna. "Plasma beam structure diagnostics in krypton Hall thruster." Laser and Particle Beams 36, no. 2 (2018): 219–25. http://dx.doi.org/10.1017/s0263034618000198.

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AbstractKrypton Large Impulse Thruster (KLIMT) project was aimed at incremental development and optimization of a 0.5 kW-class plasma Hall Effect Thruster in which, as a propellant, krypton could be used. The final thermally stable version of the thruster (the third one) was tested in the Plasma Propulsion Satellites (PlaNS) laboratory in the Institute of Plasma Physics and Laser Microfusion (IPPLM) in Warsaw as well as in the European Space Agency (ESA) propulsion laboratory in the European Space Research and Technology Centre (ESTEC).During final measurement campaign, a wide spectrum of parameters was tested. The plasma potential, electron temperature, electron concentration, and electron energy probability function in the far-field plume of the thruster were measured with a single cylindrical Langmuir probe. Faraday probes were used for recording local values of ion current. Using several collectors in different locations and moving them on the surface of a sphere, the angular distribution of the expelled particles was reconstructed which was a local measure of beam divergence. Angular distribution of ion flux as measured with a central Faraday probe was parameterized with krypton mass flow rate, voltage, coil current ratio, and the cathode mass flow rate. Beam divergence measurements with Faraday probes as well as plasma parameters derived from Langmuir probe seem to be consistent with our understanding of the operating envelope. Obtained results will serve as a baseline in the design of plasma beam structure diagnostics system for the PlaNS laboratory.

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48

Walker, Jonathan A., Jason D. Frieman, Mitchell L. R. Walker, Vadim Khayms, David King, and Peter Y. Peterson. "Electrical Facility Effects on Hall-Effect-Thruster Cathode Coupling: Discharge Oscillations and Facility Coupling." Journal of Propulsion and Power 32, no. 4 (2016): 844–55. http://dx.doi.org/10.2514/1.b35835.

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49

Wu, Zhi Wen, Shu Shu, Da Ren Yu, Xiang Yang Liu, and Ning Fei Wang. "Numerical Simulation for the Effect of Wall Material on Near Wall Conductivity in Hall Thrusters." Applied Mechanics and Materials 29-32 (August 2010): 519–24. http://dx.doi.org/10.4028/www.scientific.net/amm.29-32.519.

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The wall material plays an important role for the electron current due to near wall conductivity in Hall Thrusters. A Monte Carlo method combined with a one dimensional steady sheath model is presented and is applied to simulate the electron conductive current due to near wall conductivity for the different channel wall materials of Hall thruster. The simulation results show that the higher the secondary electron emission (SEE) coefficient of the channel wall material is, the greater the electron conductive current is. Based on the simulation, a physical explanation is given from the viewpoint of near wall conductivity. For the channel wall material with low SEE coefficient, the secondary electrons taking part in the near wall conductivity becomes less. In addition, the absolute potential drop in the sheath near the wall increases, which means that the sheath can stop more electrons from colliding with the channel wall. And consequently the electron conductive current due to near wall conductivity is much less. The situation is vice verse for the channel wall material with high SEE coefficient. The simulation results are qualitatively in accordance with the experiments. The results can help to choose and design the wall material of the Hall Thrusters with a high performance.

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50

Walker, Mitchell L. R., Allen L. Victor, Richard R. Hofer, and Alec D. Gallimore. "Effect of Backpressure on Ion Current Density Measurements in Hall Thruster Plumes." Journal of Propulsion and Power 21, no. 3 (2005): 408–15. http://dx.doi.org/10.2514/1.7713.

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