MPDスラスタ内の放電電流経路と推進性能に関する数値的検討

カテゴリ: 論文誌(論文単位)

グループ名: 【A】基礎・材料・共通部門

発行日: 2016/03/01

タイトル(英語): Numerical Study on Discharge Current Path and Performance of a Magnetoplasmadynamic Thruster

著者名: 川崎　央（東京工業大学 大学院総合理工学研究科 創造エネルギー専攻），窪田　健一（宇宙航空研究開発機構 航空技術部門），船木　一幸（宇宙航空研究開発機構 宇宙科学研究所），奥野　喜裕（東京工業大学 大学院総合理工学研究科 創造エネルギー専攻）

著者名(英語): Akira Kawasaki (Department of Energy Sciences, Tokyo Institute of Technology), Kenichi Kubota (Japan Aerospace Exploration Agency), Ikkoh Funaki (Japan Aerospace Exploration Agency), Yoshihiro Okuno (Department of Energy Sciences, Tokyo Institute of Technology)

キーワード: 電気推進，MPDスラスタ，電磁流体シミュレーション，放電電流経路，電極シース　　electric propulsion，MPD thruster，MHD flow simulation，discharge current path，electrode sheath

要約(英語): The discharge current path and performance of a steady-state, self-field magnetoplasmadynamic (MPD) thruster using argon propellant have been examined under the assumption of temperature distributions on the cathode by axisymmetry two-dimensional magnetohydrodynamic (MHD) flow simulation with electrode sheath model as the boundary condition. The discharge current path in the thruster is affected not only by the Hall effect but also by the distribution of thermionic emission from the cathode. When the cathode temperature is decreased from the tip to the root, the discharge current shifts to the cathode tip, which mitigates the current concentration toward the cathode root due to the Hall effect. Then, the thrust is increased as well as the input power, and the thrust efficiency is almost the same as that under the constant temperature distribution on the cathode.

本誌: 電気学会論文誌A（基礎・材料・共通部門誌） Vol.136 No.3 （2016）

本誌掲載ページ: 135-140 p

原稿種別: 論文／日本語

電子版へのリンク: https://www.jstage.jst.go.jp/article/ieejfms/136/3/136_135/_article/-char/ja/