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Title: Effects of magnetic field strength in the discharge channel on the performance of a multi-cusped field thruster

Abstract

The performance characteristics of a Multi-cusped Field Thruster depending on the magnetic field strength in the discharge channel were investigated. Four thrusters with different outer diameters of the magnet rings were designed to change the magnetic field strength in the discharge channel. It is found that increasing the magnetic field strength could restrain the radial cross-field electron current and decrease the radial width of main ionization region, which gives rise to the reduction of propellant utilization and thruster performance. The test results in different anode voltage conditions indicate that both the thrust and anode efficiency are higher for the weaker magnetic field in the discharge channel.

Authors:
; ; ;  [1]
  1. Lab of Plasma Propulsion, Harbin Institute of Technology, Harbin, 150001 (China)
Publication Date:
OSTI Identifier:
22611365
Resource Type:
Journal Article
Resource Relation:
Journal Name: AIP Advances; Journal Volume: 6; Journal Issue: 9; Other Information: (c) 2016 Author(s); Country of input: International Atomic Energy Agency (IAEA)
Country of Publication:
United States
Language:
English
Subject:
75 CONDENSED MATTER PHYSICS, SUPERCONDUCTIVITY AND SUPERFLUIDITY; ANODES; CURRENTS; EFFICIENCY; ELECTRIC DISCHARGES; ELECTRIC POTENTIAL; ELECTRONS; EXPLOSIVES; FUELS; IONIZATION; MAGNETIC FIELDS; MAGNETS; REDUCTION; THRUSTERS

Citation Formats

Hu, Peng, Liu, Hui, Gao, Yuanyuan, and Yu, Daren, E-mail: yudaren@hit.edu.cn. Effects of magnetic field strength in the discharge channel on the performance of a multi-cusped field thruster. United States: N. p., 2016. Web. doi:10.1063/1.4962548.
Hu, Peng, Liu, Hui, Gao, Yuanyuan, & Yu, Daren, E-mail: yudaren@hit.edu.cn. Effects of magnetic field strength in the discharge channel on the performance of a multi-cusped field thruster. United States. doi:10.1063/1.4962548.
Hu, Peng, Liu, Hui, Gao, Yuanyuan, and Yu, Daren, E-mail: yudaren@hit.edu.cn. 2016. "Effects of magnetic field strength in the discharge channel on the performance of a multi-cusped field thruster". United States. doi:10.1063/1.4962548.
@article{osti_22611365,
title = {Effects of magnetic field strength in the discharge channel on the performance of a multi-cusped field thruster},
author = {Hu, Peng and Liu, Hui and Gao, Yuanyuan and Yu, Daren, E-mail: yudaren@hit.edu.cn},
abstractNote = {The performance characteristics of a Multi-cusped Field Thruster depending on the magnetic field strength in the discharge channel were investigated. Four thrusters with different outer diameters of the magnet rings were designed to change the magnetic field strength in the discharge channel. It is found that increasing the magnetic field strength could restrain the radial cross-field electron current and decrease the radial width of main ionization region, which gives rise to the reduction of propellant utilization and thruster performance. The test results in different anode voltage conditions indicate that both the thrust and anode efficiency are higher for the weaker magnetic field in the discharge channel.},
doi = {10.1063/1.4962548},
journal = {AIP Advances},
number = 9,
volume = 6,
place = {United States},
year = 2016,
month = 9
}
  • The performance characteristics of a Multi-cusped Field Thruster depending on the magnetic field in the plume region were investigated. Five magnetic field shielding rings were separately mounted near the exit of discharge channel to decrease the strength of magnetic field in the plume region in different levels, while the magnetic field in the upstream was well maintained. The test results show that the electron current increases with the decrease of magnetic field strength in the plume region, which gives rise to higher propellant utilization and lower current utilization. On the other hand, the stronger magnetic field in the plume regionmore » improves the performance at low voltages (high current mode) while lower magnetic field improves the performance at high voltages (low current mode). This work can provide some optimal design ideas of the magnetic strength in the plume region to improve the performance of thruster.« less
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  • Measurements of the most probable time-averaged axial ion velocities and plasma potential within the acceleration channel and in the plume of a straight-channeled cylindrical cusped field thruster operating on xenon are presented. Ion velocities for the thruster are derived from laser-induced fluorescence measurements of the 5d[4]{sub 7/2}-6p[3]{sub 5/2} xenon ion excited state transition centered at {lambda}=834.72nm. Plasma potential measurements are made using a floating emissive probe with a thoriated-tungsten filament. The thruster is operated in a power matched condition with 300 V applied anode potential for comparison to previous krypton plasma potential measurements, and a low power condition with 150more » V applied anode potential. Correlations are seen between the plasma potential drop outside of the thruster and kinetic energy contours of the accelerating ions.« less
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  • It is futile for a double stage Hall thruster to design a special ionization stage if the ionized ions cannot enter the acceleration stage. Based on this viewpoint, the ion transport under different magnetic field strengths in the ionization stage is investigated, and the physical mechanisms affecting the ion transport are analyzed in this paper. With a combined experimental and particle-in-cell simulation study, it is found that the ion transport between two stages is chiefly affected by the potential well, the potential barrier, and the potential drop at the bottom of potential well. With the increase of magnetic field strengthmore » in the ionization stage, there is larger plasma density caused by larger potential well. Furthermore, the potential barrier near the intermediate electrode declines first and then rises up while the potential drop at the bottom of potential well rises up first and then declines as the magnetic field strength increases in the ionization stage. Consequently, both the ion current entering the acceleration stage and the total ion current ejected from the thruster rise up first and then decline as the magnetic field strength increases in the ionization stage. Therefore, there is an optimal magnetic field strength in the ionization stage to guide the ion transport between two stages.« less