High-Specific-Impulse Electrostatic Thruster with Argon Propellant
説明
In this study, an electrostatic thruster was newly developed, in which a diverging magnetic field with a cusp around a cathode was applied by using two solenoid coils. The effects of the magnetic field strength on thrust performance under a similar applied-magnetic-field configuration were investigated. Because of its light weight and lower price, argon was used as a propellant. By increasing the magnetic field strength, the thrust efficiency was improved owing to the suppression of the discharge current while an almost constant thrust was maintained. A specific impulse of 3800 s with thrust efficiency greater than 30% was obtained; the corresponding mass-averaged exhaust velocity exceeded the value by full-potential electrostatic acceleration of singly charged ions. From the thrust performance, ion beam current, and ion energy distribution function that were experimentally measured under the representative operation condition, 32% of the ion beam current and 43% of the total thrust were evaluated as the contribution of doubly charged ions.
収録刊行物
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- Journal of Propulsion and Power
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Journal of Propulsion and Power 36 (2), 256-263, 2020-03
American Institute of Aeronautics and Astronautics
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詳細情報 詳細情報について
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- CRID
- 1050566774745491456
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- NII論文ID
- 120006845847
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- DOI
- 10.2514/1.b37675
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- HANDLE
- 2237/00032258
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- ISSN
- 15333876
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- 本文言語コード
- en
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- 資料種別
- journal article
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- データソース種別
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- IRDB
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- CiNii Articles
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