Modelling small hollow cathode discharges for ion microthrusters
Modelling small hollow cathode discharges for ion microthrusters
A hybrid Direct Simulation Monte Carlo (DSMC), Particle in Cell (PIC) code has been developed to model plasma dynamics within the components of ion thrusters. The hollow cathode can be used as either an electron or ion source for various types of ion thruster. Several experimental ion thrusters, including standard geometry, micron scale geometry, and 'hollow cathode as thruster' (developed alongside the code) provide valuable validation sources for the code, as well as a good range of subjects for modelling. The work is aimed at aiding the understanding of the experimental results to improve the performance of hollow cathodes across the envelope of operation required for spacecraft propulsion purposes. A discussion of the plasma scaling factors involved for the hollow cathode discharge (HCD) is followed by an examination of the hollow cathode neutral flow predicted by the DSMC model.
Crawford, F.
b3ee50ce-be31-414d-8f54-89d49ee85c5f
Gabriel, S.
ac76976d-74fd-40a0-808d-c9f68a38f259
2002
Crawford, F.
b3ee50ce-be31-414d-8f54-89d49ee85c5f
Gabriel, S.
ac76976d-74fd-40a0-808d-c9f68a38f259
Crawford, F. and Gabriel, S.
(2002)
Modelling small hollow cathode discharges for ion microthrusters.
33rd Plasmadynamics and Lasers Conference, Hawaii, USA.
19 - 22 May 2002.
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Conference or Workshop Item
(Paper)
Abstract
A hybrid Direct Simulation Monte Carlo (DSMC), Particle in Cell (PIC) code has been developed to model plasma dynamics within the components of ion thrusters. The hollow cathode can be used as either an electron or ion source for various types of ion thruster. Several experimental ion thrusters, including standard geometry, micron scale geometry, and 'hollow cathode as thruster' (developed alongside the code) provide valuable validation sources for the code, as well as a good range of subjects for modelling. The work is aimed at aiding the understanding of the experimental results to improve the performance of hollow cathodes across the envelope of operation required for spacecraft propulsion purposes. A discussion of the plasma scaling factors involved for the hollow cathode discharge (HCD) is followed by an examination of the hollow cathode neutral flow predicted by the DSMC model.
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Published date: 2002
Additional Information:
AIAA-2002-2101
Venue - Dates:
33rd Plasmadynamics and Lasers Conference, Hawaii, USA, 2002-05-19 - 2002-05-22
Identifiers
Local EPrints ID: 22306
URI: http://eprints.soton.ac.uk/id/eprint/22306
PURE UUID: a5b51d5b-d291-44fb-b9f1-d0a1d4083138
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Date deposited: 05 Jun 2006
Last modified: 11 Dec 2021 14:37
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Contributors
Author:
F. Crawford
Author:
S. Gabriel
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