TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
Online ISSN : 1884-0485
Operation Characteristics of Applied-Field Magnetoplasmadynamics Thruster Using Hollow Cathode
Hayato KASUGAJeohun JEONGKeisuke MIZUTANIAkira IWAKAWAAkihiro SASOHKohei KOJIMATatsuya KIMURAYoshihiro KAWAMATAMasaaki YASUI
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2018 Volume 16 Issue 1 Pages 69-74

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Abstract

The thrust performance of a steady-state, applied-field magnetoplasmadynamics (MPD) thruster has been improved by increasing a discharge current was increased from 20 A to 60 A using a lanthanum hexaboride (LaB6) hollow cathode. The experimentally obtained thrust characteristics were consistent with that of electromagnetic acceleration. Using argon as the propellant, a thrust efficiency of 25.5% and a thrust/power ratio of 17.0 mN/kW were obtained with an applied magnetic field of 265 mT, discharge current of 30 A, propellant mass flow rate of 2.1 mg/s and discharge voltage was 121 V.

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© 2018 The Japan Society for Aeronautical and Space Sciences
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