MHD Simulation and Thermal Design of an MPD Thruster

• KAWASAKI Akira

  Department of Energy Sciences, Tokyo Institute of Technology

• KUBOTA Kenichi

  Institute of Aeronautical Technology, Japan Aerospace Exploration Agency

• FUNAKI Ikkoh

  Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

• OKUNO Yoshihiro

  Department of Energy Sciences, Tokyo Institute of Technology

抄録

For a 500-to-900-kW-class steady-state self-field magnetoplasmadynamic (MPD) thruster, the thermal design is conducted with a combination of magnetohydrodynamic (MHD) and thermal analyses, where a heat flux evaluated from the MHD analysis is imposed on the electrode as a boundary condition in the thermal analysis. The increase in anode-to-cathode radius ratio improves the thrust performance, but can simultaneously raise the temperature locally at the anode exit edge and the cathode tip due to the concentration of the discharge current and/or the insufficient heat removal. It is suggested, however, that a thruster without electrode melting should be realizable even at such a high input power by setting an appropriate cathode radius and enhancing heat removal from the electrodes by means of heat pipe, although the achievable performance of the thruster depends on the assumption of the temperature of cathode root.

収録刊行物

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12 (ists29), Pb_19-Pb_25, 2014

  一般社団法人 日本航空宇宙学会

キーワード

• Electric Propulsion
• MPD Thruster
• Self Field
• MHD Simulation
• Thermal Design

詳細情報

• CRID: 1390001205318993280
• NII論文ID: 130003395407
• DOI: 10.2322/tastj.12.pb_19
• ISSN: 18840485
• Web Site: https://www.jstage.jst.go.jp/article/tastj/12/ists29/12_Pb_19/_pdf
• 本文言語コード: en
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