抄録
A thrust model for a Lissajous method has shown that a competitive performance compared with the rockets using, e.g., ion engines or Hall thrusters, can be achieved by electrodeless method which can be a long lived thruster. Previous experiments showed a slight increase of plasma flow velocity by this method, however, experimental conditions were not optimized and the thrust was not measured. In this study, two experiments are reported in order to develop helicon plasma sources and a thrust measurement method by using Ar gas propellant. The first experiment is measurements of thermal thrust in order to characterize thruster performance 26 mm and 50 mm diameter helicon plasma thrusters without Lissajous acceleration. Maximum specific impulse (390 ± 130 s) is observed at a parameter set: the mass flow rate of 0.24 mg/s, the magnetic field: BZ = 0.054 T and RF (radio frequency) input power of 2.0 kW when a 50 mm diameter thruster is used. It is found that the thrust and efficiency is proportional to absorbed power by the plasma. The second experiment is preliminary measurements of Lissajous acceleration by using a laboratory model of 50 mm diameter. Preliminary thrust measurements by using the laboratory model show clear plasma acceleration by applying acceleration power. The observed thrust with acceleration power of 130 W is 3.3±0.3 mN with a specific impulse of 380±40 s and efficiency
| 元の言語 | 英語 |
|---|---|
| ホスト出版物のタイトル | 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 |
| 出版物ステータス | 出版済み - 12 1 2012 |
| イベント | 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 - Atlanta, GA, 米国 継続期間: 7 30 2012 → 8 1 2012 |
出版物シリーズ
| 名前 | 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 |
|---|
その他
| その他 | 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 |
|---|---|
| 国 | 米国 |
| 市 | Atlanta, GA |
| 期間 | 7/30/12 → 8/1/12 |
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All Science Journal Classification (ASJC) codes
- Energy Engineering and Power Technology
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
- Mechanical Engineering
これを引用
Laboratory model development of Lissajous acceleration for electrodeless helicon plasma thruster. / Matsuoka, Takeshi; Funaki, Ikkoh; Satoh, Syuhei; Fujino, Takayasu; Iwabuchi, Shota; Nakamura, Takahiro; Nishida, Hiroyuki; Shinohara, Shunjiro; Tanikawa, Takao; Hada, Tohru; Shamrai, Konstantin P.
48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012. 2012. (48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012).研究成果: 著書/レポートタイプへの貢献 › 会議での発言
}
TY - GEN
T1 - Laboratory model development of Lissajous acceleration for electrodeless helicon plasma thruster
AU - Matsuoka, Takeshi
AU - Funaki, Ikkoh
AU - Satoh, Syuhei
AU - Fujino, Takayasu
AU - Iwabuchi, Shota
AU - Nakamura, Takahiro
AU - Nishida, Hiroyuki
AU - Shinohara, Shunjiro
AU - Tanikawa, Takao
AU - Hada, Tohru
AU - Shamrai, Konstantin P.
PY - 2012/12/1
Y1 - 2012/12/1
N2 - A thrust model for a Lissajous method has shown that a competitive performance compared with the rockets using, e.g., ion engines or Hall thrusters, can be achieved by electrodeless method which can be a long lived thruster. Previous experiments showed a slight increase of plasma flow velocity by this method, however, experimental conditions were not optimized and the thrust was not measured. In this study, two experiments are reported in order to develop helicon plasma sources and a thrust measurement method by using Ar gas propellant. The first experiment is measurements of thermal thrust in order to characterize thruster performance 26 mm and 50 mm diameter helicon plasma thrusters without Lissajous acceleration. Maximum specific impulse (390 ± 130 s) is observed at a parameter set: the mass flow rate of 0.24 mg/s, the magnetic field: BZ = 0.054 T and RF (radio frequency) input power of 2.0 kW when a 50 mm diameter thruster is used. It is found that the thrust and efficiency is proportional to absorbed power by the plasma. The second experiment is preliminary measurements of Lissajous acceleration by using a laboratory model of 50 mm diameter. Preliminary thrust measurements by using the laboratory model show clear plasma acceleration by applying acceleration power. The observed thrust with acceleration power of 130 W is 3.3±0.3 mN with a specific impulse of 380±40 s and efficiency
AB - A thrust model for a Lissajous method has shown that a competitive performance compared with the rockets using, e.g., ion engines or Hall thrusters, can be achieved by electrodeless method which can be a long lived thruster. Previous experiments showed a slight increase of plasma flow velocity by this method, however, experimental conditions were not optimized and the thrust was not measured. In this study, two experiments are reported in order to develop helicon plasma sources and a thrust measurement method by using Ar gas propellant. The first experiment is measurements of thermal thrust in order to characterize thruster performance 26 mm and 50 mm diameter helicon plasma thrusters without Lissajous acceleration. Maximum specific impulse (390 ± 130 s) is observed at a parameter set: the mass flow rate of 0.24 mg/s, the magnetic field: BZ = 0.054 T and RF (radio frequency) input power of 2.0 kW when a 50 mm diameter thruster is used. It is found that the thrust and efficiency is proportional to absorbed power by the plasma. The second experiment is preliminary measurements of Lissajous acceleration by using a laboratory model of 50 mm diameter. Preliminary thrust measurements by using the laboratory model show clear plasma acceleration by applying acceleration power. The observed thrust with acceleration power of 130 W is 3.3±0.3 mN with a specific impulse of 380±40 s and efficiency
UR - http://www.scopus.com/inward/record.url?scp=84880795318&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84880795318&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84880795318
SN - 9781600869358
T3 - 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012
BT - 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012
ER -