Application of a microwave cathode to a 200-W Hall thruster with comparison to a hollow cathode

Takato Morishita, Ryudo Tsukizaki, Naoji Yamamoto, Kiyoshi Kinefuchi, Kazutaka Nishiyama

研究成果: Contribution to journalArticle査読

抄録

A hollow cathode is an efficient electron source in the self-heating mode utilizing the discharge power. However, in sub-ampere currents, it needs keeper power to maintain the thermionic electron discharge, which could decrease the thrust efficiency. To address this problem, we propose using a microwave cathode, which is based on the flight model of a microwave ion thruster neutralizer cathode, as an alternative to a hollow cathode. First, we redesigned the magnetic field of a microwave cathode discharge chamber and tested it in the diode mode configuration. The electron emission current is doubled compared to the original performance. Next, we coupled the improved microwave cathode with a 200-W class Hall thruster and compared the characteristics and performance with a hollow cathode. We confirmed that the magnetic field polarity affects the ignition characteristics. We measured the thrust by an inverted thrust stand, the ion energy distribution functions by a retarding potential analyzer, and the beam profiles by an ion collector. The thrust and thrust efficiency are equivalent for both types of cathode. The specific impulse is 10% higher in the case of the microwave cathode. Since the potential difference between the microwave cathode and ground rapidly increased at currents above 600 mA, this could be taken to be the trade-off point against the hollow cathode.

本文言語英語
ページ(範囲)413-423
ページ数11
ジャーナルActa Astronautica
176
DOI
出版ステータス出版済み - 11 2020

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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