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Impact of dielectric separation on transition point and accessible flow enthalpy of inductive plasmas

Impact of dielectric separation on transition point and accessible flow enthalpy of inductive plasmas
Impact of dielectric separation on transition point and accessible flow enthalpy of inductive plasmas
In order to develop inductive electric propulsion systems towards flight-ready status, an investigation into the influence of the dielectric separation between plasma and inductive coil has been conducted. This was completed by varying the wall thickness of the thruster discharge tube. The investigation assessed discharges of argon and an argon-nitrogen mixture. Additionally, results of a similar investigation utilising air have been included for comparison. The sum of these investigations showed two contrasting trends. The argon condition exhibited a preference for thicker walls, with transitions to the higher inductive regime occurring at lower input powers with increasing wall thickness. Results for Ar:N2 and air showed the opposite, with system thermal power increasing with decreasing wall thicknesses. This behaviour has been proposed to include contributions of both the mechanical dielectric separation caused by the choice of chamber wall thickness, and the gasdynamic dielectric separation owing to the discharge thermal boundary layer
Chadwick, Ashley R.
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Herdrich, Georg
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Kim, Min Kwan
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Dally, Bassam
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Hertel, Johanna
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Chadwick, Ashley R.
5a40e88e-e42a-45e9-8a6d-da46334ade01
Herdrich, Georg
c871e6e4-243b-46a8-843f-28c4770e08e3
Kim, Min Kwan
18ed9a6f-484f-4a7c-bf24-b630938c1acc
Dally, Bassam
fc96eccc-bf96-4fed-a947-7bccc80a985c
Hertel, Johanna
b4b965c2-0b04-406e-b813-d4773e2fa49a

Chadwick, Ashley R., Herdrich, Georg, Kim, Min Kwan, Dally, Bassam and Hertel, Johanna (2016) Impact of dielectric separation on transition point and accessible flow enthalpy of inductive plasmas. Space Propulsion 2016, Italy. 02 - 06 Mar 2016.

Record type: Conference or Workshop Item (Paper)

Abstract

In order to develop inductive electric propulsion systems towards flight-ready status, an investigation into the influence of the dielectric separation between plasma and inductive coil has been conducted. This was completed by varying the wall thickness of the thruster discharge tube. The investigation assessed discharges of argon and an argon-nitrogen mixture. Additionally, results of a similar investigation utilising air have been included for comparison. The sum of these investigations showed two contrasting trends. The argon condition exhibited a preference for thicker walls, with transitions to the higher inductive regime occurring at lower input powers with increasing wall thickness. Results for Ar:N2 and air showed the opposite, with system thermal power increasing with decreasing wall thicknesses. This behaviour has been proposed to include contributions of both the mechanical dielectric separation caused by the choice of chamber wall thickness, and the gasdynamic dielectric separation owing to the discharge thermal boundary layer

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SP2016_3125078_DielectricSeparation.pdf - Accepted Manuscript
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More information

Accepted/In Press date: 15 January 2016
e-pub ahead of print date: 2 May 2016
Venue - Dates: Space Propulsion 2016, Italy, 2016-03-02 - 2016-03-06
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 405041
URI: https://eprints.soton.ac.uk/id/eprint/405041
PURE UUID: 971d7ec6-74e5-40ba-9da7-8e1dae752c10

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Date deposited: 26 Jan 2017 11:44
Last modified: 09 Jan 2018 17:35

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