Operation Characteristics of Applied-Field Magnetoplasmadynamics Thruster Using Hollow Cathode

Hayato KASUGA; Jeohun JEONG; Keisuke MIZUTANI; Akira IWAKAWA; Akihiro SASOH; Kohei KOJIMA; Tatsuya KIMURA; Yoshihiro KAWAMATA; Masaaki YASUI

doi:10.2322/tastj.16.69

Hayato KASUGA, Jeohun JEONG, Keisuke MIZUTANI, Akira IWAKAWA, Akihiro SASOH, Kohei KOJIMA, Tatsuya KIMURA, Yoshihiro KAWAMATA, Masaaki YASUI

著者情報

キーワード: Space Engineering, MPD Thruster, LaB₆ Hollow Cathode

ジャーナルフリー

2018 年 16 巻 1 号 p. 69-74

DOI https://doi.org/10.2322/tastj.16.69

詳細

抄録

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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