Feasibility Study on C 60 Plasma Application to Ion Thruster

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概要

• 論文の詳細を見る

• The application of C60 to an ion thruster will improve thrust generation without increasing electric power consumption, because this molecule has a lower ionization potential and larger molecular weight than the conventional/typical ion thruster propellant. However, the application requires a sublimation device for the gaseous feed as ion thruster propellant, and control of the discharge for prevention of fragmentation and multi-ionization. Considering the advantages and disadvantages of this molecule, an electron bombardment ion thruster was designed and fabricated. Using this thruster, it was confirmed that the flow rate of the sublimated C60 was 4.9 sccm (2.6 mg/s), which was comparable to that of a typical ion thruster, and the thrust was 4.1 mN, which was the largest obtained in several laboratories. In order to advance this study, however, improvements of the propellant utilization efficiency and ion production cost may be necessary.

• Publication Office, Japanese Journal of Applied Physics, Faculty of Science, University of Tokyoの論文
• 1997-06-15

著者

• Takegahara Haruki

  Department of Aerospace Engineering

• Nakayama Yoshinori

  Department of Aerospace Engineering, Tokyo Metropolitan Institute of Technology

関連論文

• Study on C_60 Application to Ion Thruster : Fundmental Processes of Ion Production and Extraction
• Experimental Approach to Improve Ion Thruster Performance: Part 2 Effects of Magnetic Field
• Experimental Approach to Improve Ion Thruster Performance: Part 1 Effects of the Propellant Delivery Method
• Numerical Study of Beam Extraction Phenomena in an Ion Thruster
• Feasibility Study on C 60 Plasma Application to Ion Thruster

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