書誌事項
- タイトル別名
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- Nozzle Shape Optimization for an MPD Thruster Using a Two-Dimensional Axisymmetric Flow Model
- オウトウ キョクメンホウ オ モチイタ 2ジゲン ドウジク ケイジョウ ジコ ユウキ ジバガタ MPD スラスタ ノ サイテキ ケイジョウ タンサク
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The mathematical optimization of the nozzle configuration of self-field magneto-plasma-dynamic thrusters (MPDT) is quite difficult because of the calculation cost. In this paper, we proposed an optimization method based on a response surface method and optimized the shape of the discharge chamber of a self-field MPDT, using a 2-dimensional axially symmetric model of plasma flow. We searched the optimum shape with maximum thrust efficiency under the condition of 8,000A of discharge current, and discussed optimum shape changes when input power was changed. As a result, we could get the optimum shape with only about 100 CFD calculations, and found out that the optimum configuration had a flared anode and a long cathode in about 200 to 400kW region.
収録刊行物
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- 日本航空宇宙学会論文集
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日本航空宇宙学会論文集 59 (687), 90-96, 2011
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390001204470556800
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- NII論文ID
- 10028049207
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- NII書誌ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL書誌ID
- 11086162
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可