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Ion ejection from a permanent-magnet mini-helicon thruster
| Content Provider | Semantic Scholar |
|---|---|
| Author | Chen, F. F. |
| Copyright Year | 2014 |
| Abstract | A small helicon source, 5 cm in diameter and 5 cm long, using a permanent magnet (PM) to create the DC magnetic field B, is investigated for its possible use as an ion spacecraft thruster. Such ambipolar thrusters do not require a separate electron source for neutralization. The discharge is placed in the far-field of the annular PM, where B is fairly uniform. The plasma is ejected into a large chamber, where the ion energy distribution is measured with a retarding-field energy analyzer. The resulting specific impulse is lower than that of Hall thrusters but can easily be increased to relevant values by applying to the endplate of the discharge a small voltage relative to spacecraft ground. VC 2014 AIP Publishing LLC. [http://dx.doi.org/10.1063/1.4896238] |
| File Format | PDF HTM / HTML |
| Alternate Webpage(s) | http://www.seas.ucla.edu/~ffchen/Publs/Chen242.pdf |
| Language | English |
| Access Restriction | Open |
| Subject Keyword | Acetaminophen 500 MG / Diphenhydramine Hydrochloride 25 MG Oral Tablet Adaptive Internet Protocol Analyzer, device Dental Permanent Fillings Diameter (qualifier value) Discharger Electron Fractional quantum Hall effect Hall-effect thruster Ions Lunar Lander Challenge Magnet |
| Content Type | Text |
| Resource Type | Article |
