Preliminary thrust characterization of a T5 hollow cathode
Preliminary thrust characterization of a T5 hollow cathode
Previous testing of conventional T6 hollow cathodes has shown performance sufficient to consider displacing dual chemical/ion thruster propulsion systems with a common hollow cathode thruster (HCT)/ion thruster system. Future design optimization requires a detailed understanding of the influence of terminal parameters on all thrust generation mechanisms. As the next step in this process, this paper presents a preliminary thrust characterization of the T5 hollow cathode with argon using a pendulum thrust balance as a laser optical lever with a position sensitive photo-detector. Influence of terminal parameters such as geometry, flow rate and discharge current are discussed with respect to thrust parameters. This work identifies the possibility of using a T5 HCT as part of an all-electric propulsion system for the proposed European Student Moon Orbiter (ESMO). The all-electric spacecraft presents significant mass savings over conventional configurations while the preferable electrical characteristics of the hollow cathode discharge also make standalone thruster a candidate for micro satellite applications.
Hollow cathode, micro thruster, electric propulsion, plasma, ion
Grubisic, A.N.
94e5f6ea-9b65-4c81-bfa1-f0e29e8bbaf4
Gabriel, S.B
ac76976d-74fd-40a0-808d-c9f68a38f259
Grubisic, A.N.
94e5f6ea-9b65-4c81-bfa1-f0e29e8bbaf4
Gabriel, S.B
ac76976d-74fd-40a0-808d-c9f68a38f259
Grubisic, A.N. and Gabriel, S.B
(2007)
Preliminary thrust characterization of a T5 hollow cathode.
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cincinnati, United States.
08 - 11 Jul 2007.
16 pp
.
(Submitted)
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Conference or Workshop Item
(Paper)
Abstract
Previous testing of conventional T6 hollow cathodes has shown performance sufficient to consider displacing dual chemical/ion thruster propulsion systems with a common hollow cathode thruster (HCT)/ion thruster system. Future design optimization requires a detailed understanding of the influence of terminal parameters on all thrust generation mechanisms. As the next step in this process, this paper presents a preliminary thrust characterization of the T5 hollow cathode with argon using a pendulum thrust balance as a laser optical lever with a position sensitive photo-detector. Influence of terminal parameters such as geometry, flow rate and discharge current are discussed with respect to thrust parameters. This work identifies the possibility of using a T5 HCT as part of an all-electric propulsion system for the proposed European Student Moon Orbiter (ESMO). The all-electric spacecraft presents significant mass savings over conventional configurations while the preferable electrical characteristics of the hollow cathode discharge also make standalone thruster a candidate for micro satellite applications.
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Submitted date: 8 June 2007
Venue - Dates:
43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Cincinnati, United States, 2007-07-08 - 2007-07-11
Keywords:
Hollow cathode, micro thruster, electric propulsion, plasma, ion
Organisations:
Astronautics Group
Identifiers
Local EPrints ID: 48315
URI: http://eprints.soton.ac.uk/id/eprint/48315
PURE UUID: e983b2b8-7bd5-40b4-8649-07ba1930b7d2
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Date deposited: 11 Sep 2007
Last modified: 15 Mar 2024 09:44
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Contributors
Author:
A.N. Grubisic
Author:
S.B Gabriel
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