Pub Date : 2024-01-01Epub Date: 2024-12-02DOI: 10.1007/s44205-024-00088-9
David R Jovel, Janice D Cabrera, Mitchell L R Walker
Hall effect thrusters (HETs) are typically regarded as DC electric propulsion devices as they are operated with isolated DC power supplies. However, it is well known that the HET's discharge current possesses oscillations of varying magnitudes and frequencies and is thus a function of time with AC characteristics. The observed oscillations are caused by plasma processes associated with ion, electron, and neutral particle dynamics that occur inside the HET's discharge channel and in the plume as the HET electrically interacts with its local operating environment. The extent to which plasma oscillations impact HET discharge dynamics is difficult to quantify due to the complexity of analyzing AC signals, given that the HET is a nonlinear, time-variant electrical load. In this work, we overcome the challenge of nonlinearity and time-variance of HETs by conducting a small-signal impedance analysis to characterize the effective resistance and reactance of the HET discharge with a novel and versatile impedance measurement diagnostic. The impedance magnitude and phase of a 7-kW class HET were measured from 100 Hz to 300 kHz with an excitation signal of ± 2 Vpk for two discharge operating conditions on krypton: 4.5 kW, 15 A and 6 kW, 20 A. The results were used to quantify resistive, capacitive, and inducive characteristics present within the HET discharge signature. For the 4.5 kW, 15 A thruster operating condition, the breathing mode capacitance was estimated to be 12.6 µF with an inductance of 15.3 µH. Furthermore, the impedance characteristics of the breathing mode are within ± 2.4 kHz of the power spectral density plots independently generated by time-resolved oscilloscope traces indicating good agreement in the frequency domain. Thus, the impedance measurement tool is a new diagnostic for characterizing the impedance and associated AC characteristics of HETs.
{"title":"Hall effect thruster impedance characterization in ground-based vacuum test facilities.","authors":"David R Jovel, Janice D Cabrera, Mitchell L R Walker","doi":"10.1007/s44205-024-00088-9","DOIUrl":"10.1007/s44205-024-00088-9","url":null,"abstract":"<p><p>Hall effect thrusters (HETs) are typically regarded as DC electric propulsion devices as they are operated with isolated DC power supplies. However, it is well known that the HET's discharge current possesses oscillations of varying magnitudes and frequencies and is thus a function of time with AC characteristics. The observed oscillations are caused by plasma processes associated with ion, electron, and neutral particle dynamics that occur inside the HET's discharge channel and in the plume as the HET electrically interacts with its local operating environment. The extent to which plasma oscillations impact HET discharge dynamics is difficult to quantify due to the complexity of analyzing AC signals, given that the HET is a nonlinear, time-variant electrical load. In this work, we overcome the challenge of nonlinearity and time-variance of HETs by conducting a small-signal impedance analysis to characterize the effective resistance and reactance of the HET discharge with a novel and versatile impedance measurement diagnostic. The impedance magnitude and phase of a 7-kW class HET were measured from 100 Hz to 300 kHz with an excitation signal of ± 2 <i>V</i> <sub><i>pk</i></sub> for two discharge operating conditions on krypton: 4.5 kW, 15 A and 6 kW, 20 A. The results were used to quantify resistive, capacitive, and inducive characteristics present within the HET discharge signature. For the 4.5 kW, 15 A thruster operating condition, the breathing mode capacitance was estimated to be 12.6 <i>µ</i>F with an inductance of 15.3 <i>µ</i>H. Furthermore, the impedance characteristics of the breathing mode are within ± 2.4 kHz of the power spectral density plots independently generated by time-resolved oscilloscope traces indicating good agreement in the frequency domain. Thus, the impedance measurement tool is a new diagnostic for characterizing the impedance and associated AC characteristics of HETs.</p>","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":"3 1","pages":"31"},"PeriodicalIF":0.0,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.ncbi.nlm.nih.gov/pmc/articles/PMC11611958/pdf/","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142782021","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-12-01DOI: 10.1007/s44205-023-00061-y
C. Drobny, Martin Tajmar
{"title":"Characterization of a C12A7 electride plasma-based cathode using different keeper orifice sizes","authors":"C. Drobny, Martin Tajmar","doi":"10.1007/s44205-023-00061-y","DOIUrl":"https://doi.org/10.1007/s44205-023-00061-y","url":null,"abstract":"","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":"131 4","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138622486","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-12-01DOI: 10.1007/s44205-023-00060-z
Chris Acheson, Jakub Glowacki, Ryota Nakano, Daiki Maeshima, Dominik Saile, B. Pavri, Ryohei Takagi, Ryoyu Mori, Randy Pollock, Jamal R. Olatunji, Max Goddard-Winchester, Nicholas M. Strickland, Daisuke Ichihara, Stuart C. Wimbush, Kiyoshi Kinefuchi
{"title":"Operational demonstration and experimental characterisation of a central cathode electrostatic thruster equipped with a high temperature superconducting magnet","authors":"Chris Acheson, Jakub Glowacki, Ryota Nakano, Daiki Maeshima, Dominik Saile, B. Pavri, Ryohei Takagi, Ryoyu Mori, Randy Pollock, Jamal R. Olatunji, Max Goddard-Winchester, Nicholas M. Strickland, Daisuke Ichihara, Stuart C. Wimbush, Kiyoshi Kinefuchi","doi":"10.1007/s44205-023-00060-z","DOIUrl":"https://doi.org/10.1007/s44205-023-00060-z","url":null,"abstract":"","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":" 17","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138615720","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-11-16DOI: 10.1007/s44205-023-00059-6
André Nyberg Borrfors, Dan J. Harding, Jonas Weissenrieder, Simone Ciaralli, Ashley Hallock, Tore Brinck
{"title":"Aromatic hydrocarbons as Molecular Propellants for Electric Propulsion Thrusters","authors":"André Nyberg Borrfors, Dan J. Harding, Jonas Weissenrieder, Simone Ciaralli, Ashley Hallock, Tore Brinck","doi":"10.1007/s44205-023-00059-6","DOIUrl":"https://doi.org/10.1007/s44205-023-00059-6","url":null,"abstract":"","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":"30 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139266988","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-19DOI: 10.1007/s44205-023-00057-8
Koki Matsukawa, Yuiko Nakashima, Momoko Naemura, Yoshinori Takao
Abstract An externally wetted emitter array with longitudinally grooved structures for ionic liquid electrospray thrusters was fabricated to improve ionic liquid transport to the emitter tips. Two grooved emitter shapes with different groove depths were successfully fabricated using microelectromechanical system processing techniques. We evaluated the current–voltage characteristics, measured the mass spectra using time-of-flight (ToF) spectrometry, and conducted in-situ observations using a high-speed microscope. The experimental results of ion emission show that the absolute emission current increases compared with that of our previous emitter without grooves. This tendency is strengthened with deeper grooves. Moreover, the slope of the current–voltage curve for the grooved emitters does not decrease even when high voltages are applied, indicating that the grooved structure improves the ionic liquid transport to the emitter tips. This improvement is attributed to the low hydraulic impedance of the emitter structure. However, deeper grooving also increases the percentage of current intercepted by the extractor electrode, and electrochemical reactions are not avoided at an alternation frequency of 1 Hz. Although the first current–voltage measurement tended to have unstable characteristics, the ToF results indicated that the emission in the center line was in the pure-ion regime, composed mostly of monomer and dimer ions, under all the measured conditions. High-speed microscope observations showed that too much ionic liquid deposited on the extractor causes ion emission from the extractor to the emitter, known as backspray, and implies that no large droplets are emitted for either grooved emitter structure, which is consistent with the ToF results.
{"title":"Emission measurements and in-situ observation of ionic liquid electrospray thrusters with longitudinally grooved emitters","authors":"Koki Matsukawa, Yuiko Nakashima, Momoko Naemura, Yoshinori Takao","doi":"10.1007/s44205-023-00057-8","DOIUrl":"https://doi.org/10.1007/s44205-023-00057-8","url":null,"abstract":"Abstract An externally wetted emitter array with longitudinally grooved structures for ionic liquid electrospray thrusters was fabricated to improve ionic liquid transport to the emitter tips. Two grooved emitter shapes with different groove depths were successfully fabricated using microelectromechanical system processing techniques. We evaluated the current–voltage characteristics, measured the mass spectra using time-of-flight (ToF) spectrometry, and conducted in-situ observations using a high-speed microscope. The experimental results of ion emission show that the absolute emission current increases compared with that of our previous emitter without grooves. This tendency is strengthened with deeper grooves. Moreover, the slope of the current–voltage curve for the grooved emitters does not decrease even when high voltages are applied, indicating that the grooved structure improves the ionic liquid transport to the emitter tips. This improvement is attributed to the low hydraulic impedance of the emitter structure. However, deeper grooving also increases the percentage of current intercepted by the extractor electrode, and electrochemical reactions are not avoided at an alternation frequency of 1 Hz. Although the first current–voltage measurement tended to have unstable characteristics, the ToF results indicated that the emission in the center line was in the pure-ion regime, composed mostly of monomer and dimer ions, under all the measured conditions. High-speed microscope observations showed that too much ionic liquid deposited on the extractor causes ion emission from the extractor to the emitter, known as backspray, and implies that no large droplets are emitted for either grooved emitter structure, which is consistent with the ToF results.","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":"80 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135730524","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-13DOI: 10.1007/s44205-023-00055-w
Kevin D. Sampson, Mark W. Crofton
Abstract This study sought to characterize the behavior of exhausted electric thruster xenon ions in the near-Earth magnetospheric environment as functions of various trajectory and particle attributes, neglecting effects of electric fields, plasma waves and particle collisions. This was done via simulation using the AeroTracer program, a software tool which computes ion trajectories within the magnetosphere by applying an adaptive step-size Runge-Kutta technique to the fully relativistic Lorentz equation. Over 3,800 independent simulations were performed, with variables including release position, release energy and direction, ion charge, and orbital phase. Initial release altitude was a major driver in determining whether the ion eventually fell to Earth (“Below Minimum Altitude” or BMA), remained trapped by the simulation’s end (“Maximum Number of Steps” or MNS), or traveled beyond the magnetosphere (“Lost to Space” or LTS). Ions expelled at the highest altitudes investigated - 60,000 km and above - almost invariably were lost to space. Like altitude, increasing inclination and energy were important factors that reduced trapping, affecting the outcome probabilities. Higher charge state produced strong improvement of trapping capability. Effects of orbital phase, day of year and solar cycle phase were also apparent. A transition region was found in the 20,000 km to 60,000 km altitude range, within which the sensitivity of outcomes to parameter variation increased. The ordered sequence MNS> BMA> LTS was found to be consistent with decreasing confinement capability, and it was manifested consistently as parameters were varied.
{"title":"Simulations of xenon beam ions emitted from electric thrusters in Earth’s magnetosphere","authors":"Kevin D. Sampson, Mark W. Crofton","doi":"10.1007/s44205-023-00055-w","DOIUrl":"https://doi.org/10.1007/s44205-023-00055-w","url":null,"abstract":"Abstract This study sought to characterize the behavior of exhausted electric thruster xenon ions in the near-Earth magnetospheric environment as functions of various trajectory and particle attributes, neglecting effects of electric fields, plasma waves and particle collisions. This was done via simulation using the AeroTracer program, a software tool which computes ion trajectories within the magnetosphere by applying an adaptive step-size Runge-Kutta technique to the fully relativistic Lorentz equation. Over 3,800 independent simulations were performed, with variables including release position, release energy and direction, ion charge, and orbital phase. Initial release altitude was a major driver in determining whether the ion eventually fell to Earth (“Below Minimum Altitude” or BMA), remained trapped by the simulation’s end (“Maximum Number of Steps” or MNS), or traveled beyond the magnetosphere (“Lost to Space” or LTS). Ions expelled at the highest altitudes investigated - 60,000 km and above - almost invariably were lost to space. Like altitude, increasing inclination and energy were important factors that reduced trapping, affecting the outcome probabilities. Higher charge state produced strong improvement of trapping capability. Effects of orbital phase, day of year and solar cycle phase were also apparent. A transition region was found in the 20,000 km to 60,000 km altitude range, within which the sensitivity of outcomes to parameter variation increased. The ordered sequence MNS> BMA> LTS was found to be consistent with decreasing confinement capability, and it was manifested consistently as parameters were varied.","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135855635","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-12DOI: 10.1007/s44205-023-00058-7
Anmol Taploo, Vikas Soni, Halen Solomon, Marshall McCraw, Li Lin, Jake Spinelli, Steven P. Shepard, Santiago D. Solares, Michael Keidar
Abstract The paper presents an enhanced version of an arc electron source designed for air ionization applications in a self-neutralizing air-breathing plasma thruster. The arc electron source is specifically suited for the air-breathing plasma thruster, as it allows precise control of mean electron energy levels. This paper focuses on the ionization aspects of air-breathing thrusters through the development of axially magnetized arc electron sources. The sources consist of a circular and coaxial configuration of a metallic arc plasma source coupled with a positively biased grid to extract electrons and control mean electron energy. The average mean electron energy of electrons in the arc electron source is regulated by adjusting the bias voltage of the grid within the range of 0 V – 300 V. To investigate the behavior of ion current density and electron density concerning pressure and mean electron energy, the current probe and magnetic filter were utilized. It was demonstrated that the circular electron source leads to enhanced ionization of airflow by achieving plasma densities greater than 10 18 m −3 . By utilizing a high-speed camera for the circular arc electron source, the arc spot was seen to move azimuthally due to the magnetic field. Furthermore, scanning electron microscopy and a conductance measurement system were employed for the coaxial arc electron source to examine the deposition and conductance of the electron extraction grid. While the grid underwent deposition of about 600 microns, the conductance was observed to increase/saturate with time and bias voltage, indicating an electrically “self-healing material”.
摘要:本文介绍了一种用于自中和空气呼吸等离子体推力器中空气电离应用的增强型电弧电子源。电弧电子源特别适合于空气呼吸等离子体推进器，因为它允许精确控制平均电子能量水平。本文通过研制轴向磁化电弧电子源，重点研究了吸气式推进器的电离问题。该源由金属弧等离子体源的圆形和同轴结构组成，并与正偏置栅格耦合以提取电子并控制平均电子能量。通过调节栅极的偏置电压，在0 V ~ 300 V范围内调节电弧电子源中电子的平均电子能。为了研究离子电流密度和电子密度随压力和平均电子能的变化规律，采用了电流探针和磁滤波器。结果表明，当等离子体密度大于10 18 m−3时，圆形电子源会导致气流的电离增强。利用高速摄像机作为圆弧电子源，观察到圆弧光斑在磁场作用下的方位运动。此外，利用扫描电镜和电导测量系统对同轴电弧电子源的沉积和电导进行了检测。当栅格进行约600微米的沉积时，观察到电导随着时间和偏置电压的增加而增加/饱和，表明电“自愈材料”。
{"title":"Characterization of a circular arc electron source for a self-neutralizing air-breathing plasma thruster","authors":"Anmol Taploo, Vikas Soni, Halen Solomon, Marshall McCraw, Li Lin, Jake Spinelli, Steven P. Shepard, Santiago D. Solares, Michael Keidar","doi":"10.1007/s44205-023-00058-7","DOIUrl":"https://doi.org/10.1007/s44205-023-00058-7","url":null,"abstract":"Abstract The paper presents an enhanced version of an arc electron source designed for air ionization applications in a self-neutralizing air-breathing plasma thruster. The arc electron source is specifically suited for the air-breathing plasma thruster, as it allows precise control of mean electron energy levels. This paper focuses on the ionization aspects of air-breathing thrusters through the development of axially magnetized arc electron sources. The sources consist of a circular and coaxial configuration of a metallic arc plasma source coupled with a positively biased grid to extract electrons and control mean electron energy. The average mean electron energy of electrons in the arc electron source is regulated by adjusting the bias voltage of the grid within the range of 0 V – 300 V. To investigate the behavior of ion current density and electron density concerning pressure and mean electron energy, the current probe and magnetic filter were utilized. It was demonstrated that the circular electron source leads to enhanced ionization of airflow by achieving plasma densities greater than 10 18 m −3 . By utilizing a high-speed camera for the circular arc electron source, the arc spot was seen to move azimuthally due to the magnetic field. Furthermore, scanning electron microscopy and a conductance measurement system were employed for the coaxial arc electron source to examine the deposition and conductance of the electron extraction grid. While the grid underwent deposition of about 600 microns, the conductance was observed to increase/saturate with time and bias voltage, indicating an electrically “self-healing material”.","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135969000","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-09-11DOI: 10.1007/s44205-023-00056-9
Ninad Joshi, Christian Heiliger
Abstract A hybrid Fluid-Kinetic model based on a polymorphic Particle-in-Cell method is developed for the simulation of plasmas in ion thruster. The numerical scheme is suited for scenarios in which thermal ions or electrons undergo strong acceleration. The polymorphic PIC model is tested for the extraction region of an ion thruster. In this paper, we report the results achieved by implementing the scheme on a single extraction orifice and compare our results with the simulation from known IGUN software for ion extraction.
{"title":"Fluid-Kinetic-hybrid simulation for ion thruster using polymorphic particles","authors":"Ninad Joshi, Christian Heiliger","doi":"10.1007/s44205-023-00056-9","DOIUrl":"https://doi.org/10.1007/s44205-023-00056-9","url":null,"abstract":"Abstract A hybrid Fluid-Kinetic model based on a polymorphic Particle-in-Cell method is developed for the simulation of plasmas in ion thruster. The numerical scheme is suited for scenarios in which thermal ions or electrons undergo strong acceleration. The polymorphic PIC model is tested for the extraction region of an ion thruster. In this paper, we report the results achieved by implementing the scheme on a single extraction orifice and compare our results with the simulation from known IGUN software for ion extraction.","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135980773","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-08-24DOI: 10.1007/s44205-023-00054-x
Oliver Jia-Richards, Y. Marzouk, P. Lozano
{"title":"A method for direct in-space thrust estimation from low-acceleration orbital maneuvers","authors":"Oliver Jia-Richards, Y. Marzouk, P. Lozano","doi":"10.1007/s44205-023-00054-x","DOIUrl":"https://doi.org/10.1007/s44205-023-00054-x","url":null,"abstract":"","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47517645","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-07-21DOI: 10.1007/s44205-023-00053-y
D. Lev, Daniel Katz Franco, R. Zimmerman, Moshe Tordjman, Boaz Auslender, Oren Epstein
{"title":"96 kN-sec endurance test of the R-200 low power hall thruster","authors":"D. Lev, Daniel Katz Franco, R. Zimmerman, Moshe Tordjman, Boaz Auslender, Oren Epstein","doi":"10.1007/s44205-023-00053-y","DOIUrl":"https://doi.org/10.1007/s44205-023-00053-y","url":null,"abstract":"","PeriodicalId":73724,"journal":{"name":"Journal of electric propulsion","volume":" ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2023-07-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44712707","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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