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Title: Performance characteristics according to the radial position of gas distributor holes in a low-power cylindrical Hall thruster

Abstract

The effect of radial position of gas holes in the distributor on the performance of cylindrical Hall thruster was investigated. A series of gas distributors with different radial positions (R{sub g}) of holes were designed in the experiment. The results show that the larger R{sub g} leads to the higher ion current and electron current; meanwhile, the beam angle in plume is narrowed. Nevertheless, the peak energy in ion energy distribution function increases, together with the narrowing of ion energy distribution function. As a result, the overall performance is enhanced. It is suggested that the growing of R{sub g} could lead to the movement of the main ionization region towards anode, which could promote ion velocity and the clearer separation of acceleration region from ionization region. This work can provide some optimal design ideas to improve the performance of the thruster.

Authors:
; ; ; ;  [1]
  1. Lab of Plasma Propulsion, Harbin Institute of Technology, Harbin 150001 (China)
Publication Date:
OSTI Identifier:
22599956
Resource Type:
Journal Article
Resource Relation:
Journal Name: Physics of Plasmas; Journal Volume: 23; Journal Issue: 8; Other Information: (c) 2016 Author(s); Country of input: International Atomic Energy Agency (IAEA)
Country of Publication:
United States
Language:
English
Subject:
70 PLASMA PHYSICS AND FUSION TECHNOLOGY; 71 CLASSICAL AND QUANTUM MECHANICS, GENERAL PHYSICS; ACCELERATION; ANODES; BEAMS; CYLINDRICAL CONFIGURATION; DISTRIBUTION FUNCTIONS; ELECTRONS; ENERGY SPECTRA; HALL EFFECT; HOLES; IONIZATION; PEAKS; PERFORMANCE; PLUMES; THRUSTERS; VELOCITY

Citation Formats

Gao, Yuanyuan, Liu, Hui, Hu, Peng, Huang, Hongyan, and Yu, Daren, E-mail: yudaren@hit.edu.cn. Performance characteristics according to the radial position of gas distributor holes in a low-power cylindrical Hall thruster. United States: N. p., 2016. Web. doi:10.1063/1.4960663.
Gao, Yuanyuan, Liu, Hui, Hu, Peng, Huang, Hongyan, & Yu, Daren, E-mail: yudaren@hit.edu.cn. Performance characteristics according to the radial position of gas distributor holes in a low-power cylindrical Hall thruster. United States. doi:10.1063/1.4960663.
Gao, Yuanyuan, Liu, Hui, Hu, Peng, Huang, Hongyan, and Yu, Daren, E-mail: yudaren@hit.edu.cn. 2016. "Performance characteristics according to the radial position of gas distributor holes in a low-power cylindrical Hall thruster". United States. doi:10.1063/1.4960663.
@article{osti_22599956,
title = {Performance characteristics according to the radial position of gas distributor holes in a low-power cylindrical Hall thruster},
author = {Gao, Yuanyuan and Liu, Hui and Hu, Peng and Huang, Hongyan and Yu, Daren, E-mail: yudaren@hit.edu.cn},
abstractNote = {The effect of radial position of gas holes in the distributor on the performance of cylindrical Hall thruster was investigated. A series of gas distributors with different radial positions (R{sub g}) of holes were designed in the experiment. The results show that the larger R{sub g} leads to the higher ion current and electron current; meanwhile, the beam angle in plume is narrowed. Nevertheless, the peak energy in ion energy distribution function increases, together with the narrowing of ion energy distribution function. As a result, the overall performance is enhanced. It is suggested that the growing of R{sub g} could lead to the movement of the main ionization region towards anode, which could promote ion velocity and the clearer separation of acceleration region from ionization region. This work can provide some optimal design ideas to improve the performance of the thruster.},
doi = {10.1063/1.4960663},
journal = {Physics of Plasmas},
number = 8,
volume = 23,
place = {United States},
year = 2016,
month = 8
}
  • Plasma plume and thruster performance characteristics associated with multiply charged ions in a cylindrical type Hall thruster (CHT) and an annular type Hall thruster are compared under identical conditions such as channel diameter, channel depth, propellant mass flow rate. A high propellant utilization in a CHT is caused by a high ionization rate, which brings about large multiply charged ions. Ion currents and utilizations are much different due to the presence of multiply charged ions. A high multiply charged ion fraction and a high ionization rate in the CHT result in a higher specific impulse, thrust, and discharge current.
  • Investigation of the radial scale effect on low-power cylindrical Hall thrusters has been undertaken by comparing the thrusters with three different channel diameters of 28, 40, and 50 mm. The investigation found that both the anode efficiency and the thrust of the larger thruster are higher as the anode power is raised. On the other hand, higher current and propellant utilizations are achieved for the smaller thruster, which is due to higher neutral density and better electron confinement. The large plume angle of the small cylindrical Hall thruster causes thrust loss, resulting in the reduction of anode efficiency.
  • Performance characteristics of a cylindrical Hall thruster depending on the depth of the annular region (L{sub a}) in front of the anode were investigated. The effect of the annular region was examined by operating thrusters corresponding to four different values of L{sub a} (0, 4, 6, and 10 mm) and a fixed length of the cylindrical region (25 mm). Various measurements such as electron and ion currents, thrust, anode efficiency, current and propellant utilizations, and ion energy distribution functions were performed. Such measurements lead to an interpretation that (1) a considerable potential difference may exist between the anode and themore » ionization region, which is presumably located near the end of the annular region where magnetic field lines converge; (2) this potential difference increases with respect to increasing L{sub a}; and (3) the presence of the annular region near the anode reduces the specific impulse and anode efficiency for the examined thrusters.« less
  • Electron transport across a magnetic field in a magnetic-layer-type Hall thruster was numerically investigated for the future predictive modeling of Hall thrusters. The discharge of a 1-kW-class magnetic-layer-type Hall thruster designed for high-specific-impulse operation was modeled using an r-z two-dimensional fully kinetic particle code with and without artificial electron-diffusion models. The thruster performance results showed that both electron transport models captured the experimental result within discrepancies less than 20% in thrust and discharge current for all the simulated operation conditions. The electron cross-field transport mechanism of the so-called anomalous diffusion was self-consistently observed in the simulation without artificial diffusion models;more » the effective electron mobility was two orders of magnitude higher than the value obtained using the classical diffusion theory. To account for the self-consistently observed anomalous transport, the oscillation of plasma properties was speculated. It was suggested that the enhanced random-walk diffusion due to the velocity oscillation of low-frequency electron flow could explain the observed anomalous diffusion within an order of magnitude. The dominant oscillation mode of the electron flow velocity was found to be 20 kHz, which was coupled to electrostatic oscillation excited by global ionization instability.« less
  • An investigation of a fully cylindrical Hall thruster was performed using laser induced fluorescence (LIF) to measure ion velocity profiles in the plume. The measurements confirm a previously reported 9% increase in the exhaust energy when the cathode keeper draws an excess current (overrun mode). Furthermore, the velocity directions in the plume remain relatively unchanged for the cusped and direct magnetic field configuration in both overrun and nonoverrun modes. Previously reported plume narrowing in the overrun mode was confirmed and found to be due to the shift of the acceleration and ionization regions toward the anode. The electric field inferredmore » from the LIF measurements allowed calculation of the electron ExB drift. Close to the centerline of the thruster, electrons drift azimuthally with velocity decreasing away from the centerline, thus creating shear. This shear can be a source of plasma instabilities and influence electron transport. Further away from the centerline, electrons drift in the opposite direction with their velocity increasing with increasing radius. In that region, electrons rotate without shear.« less