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| Naji, M. |
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| Motta, Antonella |
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| Aletan, Dirar |
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| Mohamed, Tarek |
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| Ertürk, Emre |
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| Taccardi, Nicola |
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| Kononenko, Denys |
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| Petrov, R. H. | Madrid |
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| Alshaaer, Mazen | Brussels |
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| Bih, L. |
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| Casati, R. |
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| Muller, Hermance |
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| Kočí, Jan | Prague |
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| Šuljagić, Marija |
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| Kalteremidou, Kalliopi-Artemi | Brussels |
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| Azam, Siraj |
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| Ospanova, Alyiya |
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| Blanpain, Bart |
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| Ali, M. A. |
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| Popa, V. |
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| Rančić, M. |
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| Ollier, Nadège |
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| Azevedo, Nuno Monteiro |
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| Landes, Michael |
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| Rignanese, Gian-Marco |
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Romei, Federico
University of Southampton
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (8/8 displayed)
- 2024Initial performance assessment of 3D printed thin walled structures for spacecraft applicationscitations
- 2019Endurance testing of the additively manufactured STAR resistojetcitations
- 2018Novel non-destructive inspection of the STAR additively manufactured resistojet
- 2018Novel non-destructive inspection of the STAR additively manufactured resistojet
- 2018Endurance testing of the STAR additively manufactured resistojet
- 2017Manufacturing of a high-temperature resistojet heat exchanger by selective laser meltingcitations
- 2017Performance testing and evaluation of a high temperature xenon resistojet prototype manufactured by selective laser melting
- 2016Selective laser melting for production of a novel high temperature electrothermal propulsion system
Places of action
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conferencepaper
Performance testing and evaluation of a high temperature xenon resistojet prototype manufactured by selective laser melting
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.