ジメチルエーテルを用いたパルス型プラズマ推進機の性能 Performance of a Pulsed Plasma Thruster Using Dimethyl Ether Propellant

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The current paper describes experimental results for a pulsed plasma thruster (PPT) using dimethyl ether (DME) as a propellant. DME is an ether compound, which is neither toxic nor reactive and is stored in the liquid form in tanks because of 6 atm vapor pressure. A coaxial type DME-PPT was designed to evaluate the performance. Main discharges were successfully initiated by an igniter or spontaneous discharge induced by DME injection. The igniter was used in the case that propellant mass was so low that the spontaneous discharge was not initiated by DME feeding. Thrust measurement using a thrust target yielded a specific impulse of 1200s for an igniter type DME-PPT with 1.5μg mass shot and 5J capacitor stored energy, and 620s for spontaneous discharge type with 8.8μg and 13J.

収録刊行物

  • 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 59(693), 266-272, 2011-10-05

    一般社団法人 日本航空宇宙学会

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各種コード

  • NII論文ID(NAID)
    10030274934
  • NII書誌ID(NCID)
    AA11307372
  • 本文言語コード
    JPN
  • 資料種別
    ART
  • ISSN
    13446460
  • NDL 記事登録ID
    11277284
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z74-B503
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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