Performance testing and evaluation of a high temperature xenon resistojet prototype manufactured by selective laser melting
Performance testing and evaluation of a high temperature xenon resistojet prototype manufactured by selective laser melting
This paper presents performance testing and evaluation of the AMR-X-0, the first additively manufactured breadboard model resistojet thruster with a novel design of heat exchanger. Testing is performed within the David Fearn Electric Propulsion Laboratory at the University of Southampton. The thruster is characterized at constant flow rates with argon, in both cold gas mode and at a range of electrical power inputs with current regulation. Thrust measurements demonstrate an improvement in ISP of 50% and thus validating the concept and providing insight into the thermal inertia of the AMR-X thruster. The presence of a gas leak caused by a ceramic component is discussed.
Romei, Federico
2c01d8c3-430b-49f8-9c8c-e30d0d135f89
Grubisic, Angelo
a4cab763-bbc0-4130-af65-229ae674e8c8
Gibbon, Dave
e60476ec-e06b-418d-a71f-bf3a6ae2ecc2
12 October 2017
Romei, Federico
2c01d8c3-430b-49f8-9c8c-e30d0d135f89
Grubisic, Angelo
a4cab763-bbc0-4130-af65-229ae674e8c8
Gibbon, Dave
e60476ec-e06b-418d-a71f-bf3a6ae2ecc2
Romei, Federico, Grubisic, Angelo and Gibbon, Dave
(2017)
Performance testing and evaluation of a high temperature xenon resistojet prototype manufactured by selective laser melting.
In 35th International Electric Propulsion Conference.
IEPC Conference.
12 pp
.
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Conference or Workshop Item
(Paper)
Abstract
This paper presents performance testing and evaluation of the AMR-X-0, the first additively manufactured breadboard model resistojet thruster with a novel design of heat exchanger. Testing is performed within the David Fearn Electric Propulsion Laboratory at the University of Southampton. The thruster is characterized at constant flow rates with argon, in both cold gas mode and at a range of electrical power inputs with current regulation. Thrust measurements demonstrate an improvement in ISP of 50% and thus validating the concept and providing insight into the thermal inertia of the AMR-X thruster. The presence of a gas leak caused by a ceramic component is discussed.
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In preparation date: 23 December 2016
Accepted/In Press date: 30 September 2017
Published date: 12 October 2017
Venue - Dates:
35th International Electric Propulsion Conference, Georgia Institute of Technology, Atlanta, United States, 2017-10-08 - 2017-10-12
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Local EPrints ID: 415095
URI: http://eprints.soton.ac.uk/id/eprint/415095
PURE UUID: d96fdc0d-7253-49b4-b421-ea4033e1009f
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Date deposited: 26 Oct 2017 16:30
Last modified: 29 Nov 2024 15:30
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Author:
Dave Gibbon
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