Liquid micro pulsed plasma thruster
Abstract
A new type of pulsed plasma thruster (PPT) for small satellite propulsion is investigated, of which the most innovative aspect is the use of a non-volatile liquid propellant. The thruster is based on an open capillary design. The thruster achieved a thrust-to-power ratio above 45 μN/W, which constitutes a 5-fold improvement over the water-propelled pulsed plasma thruster, and which is also slightly above the performance of a similarly sized PPT with a solid propellant.
Language: English
Page range: 257 - 261
Submitted on: Nov 27, 2014
Accepted on: Mar 24, 2015
Published on: Jun 22, 2015
Published by: Institute of Nuclear Chemistry and Technology
In partnership with: Paradigm Publishing Services
Publication frequency: 4 issues per year
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© 2015 Agnieszka Szelecka, Jacek Kurzyna, Dariusz Daniłko, Serge Barral, published by Institute of Nuclear Chemistry and Technology
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.