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High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes
ESCI SJR: 0.176 SNIP: 0.48 CiteScore™: 1.3

ISSN Печать: 1093-3611
ISSN Онлайн: 1940-4360

Выпуски:
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High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes

DOI: 10.1615/HighTempMatProc.2015015355
pages 83-90

DESIGN OPTIMIZATION OF A MAGNETOPLASMADYNAMIC THRUSTER BY NUMERICAL METHODS

M. Li
School of Astronautics, Beihang University, Beijing, China
H. Liu
Plasma Propulsion Laboratory, Harbin Institute of Technology, Harbin, China
Z. Ning
Plasma Propulsion Laboratory, Harbin Institute of Technology, Harbin, China
J. Ren
School of Astronautics, Beihang University, Beijing, China
H. Tang
School of Astronautics, Beihang University, Beijing, China
D. Yu
Plasma Propulsion Laboratory, Harbin Institute of Technology, Harbin, China
Stepan I. Eliseev
St. Petersburg State University, St. Petersburg, 199034, Russia; ITMO University, 49 Kronverkskiy Ave., St. Petersburg, 197101, Russia
Anatoly A. Kudryavtsev
St. Petersburg State University, St. Petersburg, 199034, Russia; ITMO University, 49 Kronverkskiy Ave., St. Petersburg, 197101, Russia

Краткое описание

In this work a 2D model for simulating an applied-field magnetoplasmadynamic (AF-MPD) thruster with a hollow cathode made of thoriated tungsten was constructed using Comsol Multiphysics. The model allowed for self-consistent description of plasma processes inside an ionization chamber in the thruster and heating of the cathode due to ion bombardment. The distribution of such discharge parameters as charged and excited particle densities, charged particles' mean energies and temperatures, gas temperature, cathode temperature, and electric potential were obtained. Numerical experiments were carried out for different geometries and optimal configuration of AFMPD thruster with a hollow cathode was obtained.


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