Space Electric Propulsion Technology

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Astronautics & Space Science".

Deadline for manuscript submissions: closed (15 March 2024) | Viewed by 2496

Special Issue Editors


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Guest Editor
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China
Interests: space electric propulsion technology; gas discharge; high voltage technology

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Guest Editor
School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
Interests: electric propulsion technology; new concept space propulsion technology

Special Issue Information

Dear Colleagues,

Space electric propulsion, due to its main characteristics of high specific impulse and micro thrust, is playing an increasingly prominent role in space engineering such as long-life satellites, deep space exploration, and non-drag control, becoming the forefront of space propulsion technology and receiving attention from countries around the world. The successful applications of the Smart-1, Hayabusa, Deep Space 1, and Shijian satellites mark the gradual maturity of electric propulsion technology and the increasing importance in the future of the aerospace field. Space Electric Propulsion Technology has gone through a long period of development and reserve, and has made solid progress in ion thruster, Hall thruster, Arcjet, Pulse Plasma Propulsion, Magneto Plasma Dynamic (MPD) thruster, Colloid and electrospray thrusters, and other aspects. Electric propulsion is currently considered by all space actors as a key and revolutionary technology for the new generations of commercial and scientific satellites. Initiatives in this field all over the world are aimed at the development of competitive new generations of electric propulsion systems for the different types of markets and applications. We hope this Special Issue on the topic of Space Electric Propulsion Technology can expand the latest research achievements in electric propulsion technology and its applications.

Prof. Dr. Liqiu Wei
Prof. Dr. Zhiwen Wu
Guest Editors

Manuscript Submission Information

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Keywords

  • electric propulsion device
  • electric propulsion physics
  • electric propulsion application
  • electric propulsion progress

Published Papers (2 papers)

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Research

12 pages, 3156 KiB  
Article
Time-of-Flight Measurements in the Jet of a High-Current Vacuum Arc Thruster
by Etienne Michaux and Stéphane Mazouffre
Aerospace 2023, 10(12), 1011; https://doi.org/10.3390/aerospace10121011 - 30 Nov 2023
Viewed by 889
Abstract
Measurements of ion speed in the plume of a pulsed high-current vacuum arc thruster were performed by means of electrostatic probes. The probes were designed to provide direct speed measurements with minimum disturbance on the plasma jet. Typical mean values of vi [...] Read more.
Measurements of ion speed in the plume of a pulsed high-current vacuum arc thruster were performed by means of electrostatic probes. The probes were designed to provide direct speed measurements with minimum disturbance on the plasma jet. Typical mean values of vi for Ti and Cu cathodes are determined at different locations downstream of the electrodes, in the far field region. From one VAT discharge to another, the mean ion speed strongly varies which leads to a large statistical dispersion. Single-shot analysis allows the observation of the plume anisotropy and its high divergence as well as the existence of several ion groups of different speeds throughout a discharge. Full article
(This article belongs to the Special Issue Space Electric Propulsion Technology)
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15 pages, 10782 KiB  
Article
Effects of Magnetic Field Gradient on the Performance of a Magnetically Shielded Hall Thruster
by Qi Liu, Yong Li, Yanlin Hu and Wei Mao
Aerospace 2023, 10(11), 942; https://doi.org/10.3390/aerospace10110942 - 05 Nov 2023
Viewed by 1192
Abstract
The objective of this study is to investigate the effects of a magnetic field gradient on the performance of a magnetically shielded Hall thruster. The Particle-in-cell with Monte Carlo collision method (PIC-MCC) is used to simulate the discharge process of the thruster. The [...] Read more.
The objective of this study is to investigate the effects of a magnetic field gradient on the performance of a magnetically shielded Hall thruster. The Particle-in-cell with Monte Carlo collision method (PIC-MCC) is used to simulate the discharge process of the thruster. The performance and plasma characteristics are obtained in conditions with different magnetic field gradients by numerical simulations. As the maximum of the gradient is increased from 1.2 to 3.33 T/m, the electron number density near the channel exit decreases, which leads to less ionization and a weaker radial electric field. As a result, the thrust and specific impulse are decreased, while the plume divergence angle is reduced. Full article
(This article belongs to the Special Issue Space Electric Propulsion Technology)
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