@inproceedings{acheson_integration_2023,
	title = {Integration and testing of a high temperature superconductor magnet with a central cathode electrostatic thruster},
	shorttitle = {Proc. {Aerospace} {Europe} {Conference} ‑ {EUCASS} ‑ {CEAS}},
	url = {/publications/10.13009/EUCASS2023-261.pdf},
	doi = {10.13009/EUCASS2023-261},
	abstract = {Superconductor magnets generate high magnetic fields which can increase the performance of electric propulsion devices, but many such thruster operational regimes remain unexplored. In this work, a superconductor magnet and electrostatic thruster were integrated on a thrust measurement stand. Thruster performance was characterised at applied fields of up to 0.8 T, representing a significant advance for applied-field plasma thrusters. Thermal behaviour of the cryogenic magnet was assessed. A convex anode enabled ignition at high magnetic fields, and in this configuration thruster performance was measured in the range of 1 kW to 2.5 kW and 0.6 T to 0.8 T.},
	language = {en},
	booktitle = {Proceedings of the {Aerospace} {Europe} {Conference} - {EUCASS} - {CEAS}},
	author = {Acheson, Chris R. and Głowacki, Jakub and Nakano, Ryota and Maeshima, Daiki and Saile, Dominik and Pavri, Bettina and Mori, Ryoyu and Takagi, Ryohei and Pollock, Randy and Olatunji, Jamal R. and Goddard Winchester, Max and Strickland, Nick and Ichihara, Daisuke and Wimbush, Stuart C. and Kinefuchi, Kiyoshi},
	year = {2023},
	keywords = {CC-EST, ELECTRIC PROPULSION, MAGNET, PLASMA, SUPERCONDUCTOR, THRUSTER},
	file = {Acheson et al. - 2023 - Integration and testing of a high temperature supe.pdf:C\:\\Users\\scwim\\OneDrive\\Work\\Zotero Library\\Acheson et al. - 2023 - Integration and testing of a high temperature supe.pdf:application/pdf},
}

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In this work, a superconductor magnet and electrostatic thruster were integrated on a thrust measurement stand. Thruster performance was characterised at applied fields of up to 0.8 T, representing a significant advance for applied-field plasma thrusters. Thermal behaviour of the cryogenic magnet was assessed. A convex anode enabled ignition at high magnetic fields, and in this configuration thruster performance was measured in the range of 1 kW to 2.5 kW and 0.6 T to 0.8 T.","language":"en","booktitle":"Proceedings of the Aerospace Europe Conference - EUCASS - CEAS","author":[{"propositions":[],"lastnames":["Acheson"],"firstnames":["Chris","R."],"suffixes":[]},{"propositions":[],"lastnames":["Głowacki"],"firstnames":["Jakub"],"suffixes":[]},{"propositions":[],"lastnames":["Nakano"],"firstnames":["Ryota"],"suffixes":[]},{"propositions":[],"lastnames":["Maeshima"],"firstnames":["Daiki"],"suffixes":[]},{"propositions":[],"lastnames":["Saile"],"firstnames":["Dominik"],"suffixes":[]},{"propositions":[],"lastnames":["Pavri"],"firstnames":["Bettina"],"suffixes":[]},{"propositions":[],"lastnames":["Mori"],"firstnames":["Ryoyu"],"suffixes":[]},{"propositions":[],"lastnames":["Takagi"],"firstnames":["Ryohei"],"suffixes":[]},{"propositions":[],"lastnames":["Pollock"],"firstnames":["Randy"],"suffixes":[]},{"propositions":[],"lastnames":["Olatunji"],"firstnames":["Jamal","R."],"suffixes":[]},{"propositions":[],"lastnames":["Goddard","Winchester"],"firstnames":["Max"],"suffixes":[]},{"propositions":[],"lastnames":["Strickland"],"firstnames":["Nick"],"suffixes":[]},{"propositions":[],"lastnames":["Ichihara"],"firstnames":["Daisuke"],"suffixes":[]},{"propositions":[],"lastnames":["Wimbush"],"firstnames":["Stuart","C."],"suffixes":[]},{"propositions":[],"lastnames":["Kinefuchi"],"firstnames":["Kiyoshi"],"suffixes":[]}],"year":"2023","keywords":"CC-EST, ELECTRIC PROPULSION, MAGNET, PLASMA, SUPERCONDUCTOR, THRUSTER","file":"Acheson et al. - 2023 - Integration and testing of a high temperature supe.pdf:C\\:\\\\Users\\\\scwim\\ØneDrive\\\\Work\\\\Zotero Library\\\\Acheson et al. - 2023 - Integration and testing of a high temperature supe.pdf:application/pdf","bibtex":"@inproceedings{acheson_integration_2023,\n\ttitle = {Integration and testing of a high temperature superconductor magnet with a central cathode electrostatic thruster},\n\tshorttitle = {Proc. {Aerospace} {Europe} {Conference} ‑ {EUCASS} ‑ {CEAS}},\n\turl = {/publications/10.13009/EUCASS2023-261.pdf},\n\tdoi = {10.13009/EUCASS2023-261},\n\tabstract = {Superconductor magnets generate high magnetic fields which can increase the performance of electric propulsion devices, but many such thruster operational regimes remain unexplored. In this work, a superconductor magnet and electrostatic thruster were integrated on a thrust measurement stand. Thruster performance was characterised at applied fields of up to 0.8 T, representing a significant advance for applied-field plasma thrusters. Thermal behaviour of the cryogenic magnet was assessed. A convex anode enabled ignition at high magnetic fields, and in this configuration thruster performance was measured in the range of 1 kW to 2.5 kW and 0.6 T to 0.8 T.},\n\tlanguage = {en},\n\tbooktitle = {Proceedings of the {Aerospace} {Europe} {Conference} - {EUCASS} - {CEAS}},\n\tauthor = {Acheson, Chris R. and Głowacki, Jakub and Nakano, Ryota and Maeshima, Daiki and Saile, Dominik and Pavri, Bettina and Mori, Ryoyu and Takagi, Ryohei and Pollock, Randy and Olatunji, Jamal R. and Goddard Winchester, Max and Strickland, Nick and Ichihara, Daisuke and Wimbush, Stuart C. and Kinefuchi, Kiyoshi},\n\tyear = {2023},\n\tkeywords = {CC-EST, ELECTRIC PROPULSION, MAGNET, PLASMA, SUPERCONDUCTOR, THRUSTER},\n\tfile = {Acheson et al. - 2023 - Integration and testing of a high temperature supe.pdf:C\\:\\\\Users\\\\scwim\\\\OneDrive\\\\Work\\\\Zotero Library\\\\Acheson et al. - 2023 - Integration and testing of a high temperature supe.pdf:application/pdf},\n}\n\n","author_short":["Acheson, C. 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