Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency

Abstract Development of a magnetic nozzle radiofrequency (rf) plasma thruster has been one of challenging topics in space electric propulsion technologies. The thruster typically consists of an rf plasma source and a magnetic nozzle, where the plasma produced inside the source is transported along t...

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Autor principal:	Kazunori Takahashi
Formato:	article
Lenguaje:	EN
Publicado:	Nature Portfolio 2021
Materias:	Medicine R Science Q
Acceso en línea:	https://doaj.org/article/c2d6cc35c9ca4dec88f26f36097f93bb
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spelling	oai:doaj.org-article:c2d6cc35c9ca4dec88f26f36097f93bb2021-12-02T14:06:56ZMagnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency10.1038/s41598-021-82471-22045-2322https://doaj.org/article/c2d6cc35c9ca4dec88f26f36097f93bb2021-02-01T00:00:00Zhttps://doi.org/10.1038/s41598-021-82471-2https://doaj.org/toc/2045-2322Abstract Development of a magnetic nozzle radiofrequency (rf) plasma thruster has been one of challenging topics in space electric propulsion technologies. The thruster typically consists of an rf plasma source and a magnetic nozzle, where the plasma produced inside the source is transported along the magnetic field and expands in the magnetic nozzle. An imparted thrust is significantly affected by the rf power coupling for the plasma production, the plasma transport, the plasma loss to the wall, and the plasma acceleration process in the magnetic nozzle. The rf power transfer efficiency and the imparted thrust are assessed for two types of rf antennas exciting azimuthal mode number of $$m=+1$$ m = + 1 and $$m=0$$ m = 0 , where propellant argon gas is introduced from the upstream of the thruster source tube. The rf power transfer efficiency and the density measured at the radial center for the $$m=+1$$ m = + 1 mode antenna are higher than those for the $$m=0$$ m = 0 mode antenna, while a larger thrust is obtained for the $$m=0$$ m = 0 mode antenna. Two-dimensional plume characterization suggests that the lowered performance for the $$m=+1$$ m = + 1 mode case is due to the plasma production at the radial center, where contribution on a thrust exerted to the magnetic nozzle is weak due to the absence of the radial magnetic field. Subsequently, the configuration is modified so as to introduce the propellant gas near the thruster exit for the $$m=0$$ m = 0 mode configuration and the thruster efficiency approaching twenty percent is successfully obtained, being highest to date in the kW-class magnetic nozzle rf plasma thrusters.Kazunori TakahashiNature PortfolioarticleMedicineRScienceQENScientific Reports, Vol 11, Iss 1, Pp 1-12 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	Medicine R Science Q
spellingShingle	Medicine R Science Q Kazunori Takahashi Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency
description	Abstract Development of a magnetic nozzle radiofrequency (rf) plasma thruster has been one of challenging topics in space electric propulsion technologies. The thruster typically consists of an rf plasma source and a magnetic nozzle, where the plasma produced inside the source is transported along the magnetic field and expands in the magnetic nozzle. An imparted thrust is significantly affected by the rf power coupling for the plasma production, the plasma transport, the plasma loss to the wall, and the plasma acceleration process in the magnetic nozzle. The rf power transfer efficiency and the imparted thrust are assessed for two types of rf antennas exciting azimuthal mode number of $$m=+1$$ m = + 1 and $$m=0$$ m = 0 , where propellant argon gas is introduced from the upstream of the thruster source tube. The rf power transfer efficiency and the density measured at the radial center for the $$m=+1$$ m = + 1 mode antenna are higher than those for the $$m=0$$ m = 0 mode antenna, while a larger thrust is obtained for the $$m=0$$ m = 0 mode antenna. Two-dimensional plume characterization suggests that the lowered performance for the $$m=+1$$ m = + 1 mode case is due to the plasma production at the radial center, where contribution on a thrust exerted to the magnetic nozzle is weak due to the absence of the radial magnetic field. Subsequently, the configuration is modified so as to introduce the propellant gas near the thruster exit for the $$m=0$$ m = 0 mode configuration and the thruster efficiency approaching twenty percent is successfully obtained, being highest to date in the kW-class magnetic nozzle rf plasma thrusters.
format	article
author	Kazunori Takahashi
author_facet	Kazunori Takahashi
author_sort	Kazunori Takahashi
title	Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency
title_short	Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency
title_full	Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency
title_fullStr	Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency
title_full_unstemmed	Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency
title_sort	magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency
publisher	Nature Portfolio
publishDate	2021
url	https://doaj.org/article/c2d6cc35c9ca4dec88f26f36097f93bb
work_keys_str_mv	AT kazunoritakahashi magneticnozzleradiofrequencyplasmathrusterapproachingtwentypercentthrusterefficiency
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Magnetic nozzle radiofrequency plasma thruster approaching twenty percent thruster efficiency

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