@inproceedings{oai:jaxa.repo.nii.ac.jp:00003867,
 author = {川崎, 央 and 窪田, 健一 and 船木, 一幸 and 奥野, 喜裕 and Kawasaki, Akira and Kubota, Kenichi and Funaki, Ikkoh and Okuno, Yoshihiro},
 book = {宇宙航空研究開発機構特別資料: 第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県, 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan, For a steady-state self-field magnetiplasmadynamic (MPD) thruster (ZT3 thruster, which was investigated experimentally at the Institute of Space System of the University of Stuttgart), a magnetohydrodynamic (MHD) simulation of a plasma flow is conducted under consideration for electrode phenomena by incorporating a theoretical cathode sheath/presheath model into an MHD fluid model as a boundary condition. The influence of the incorporation of the cathode sheath/presheath model on numerical performance prediction is discussed for the operation in a propellant (argon) flow rate of 2.0 g/s and a discharge current of 10 kA. By incorporating the cathode sheath/presheath model, the predicted discharge voltage (21.0 V) agreed well with the experimental result (ca. 20 V). Estimated averagevoltage drop within the cathode sheath/presheath accounts for 31% of the discharge voltage. It was therefore confirmed by numerical simulation that the existence of the cathode sheath significantly affects the operation of the MPD thruster., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530023032, レポート番号: JAXA-SP-14-010},
 pages = {179--184},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {電極現象を考慮した電磁流体シミュレーションによるMPDスラスタの性能予測},
 volume = {JAXA-SP-14-010},
 year = {2015}
}