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Czasopismo
2015 | 60 | 2 | 257-261
Tytuł artykułu

Liquid micro pulsed plasma thruster

Treść / Zawartość
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
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.
Wydawca

Czasopismo
Rocznik
Tom
60
Numer
2
Strony
257-261
Opis fizyczny
Daty
wydano
2015-06-01
otrzymano
2014-11-27
zaakceptowano
2015-03-24
online
2015-06-22
Twórcy
  • Institute of Plasma Physics and Laser Microfusion (IPPLM), 23 Hery Str., 01-497 Warsaw, Poland, Tel.: +48 22 638 1460, Fax: +48 22 666 8372, agnieszka.szelecka@ifpilm.pl
  • Institute of Plasma Physics and Laser Microfusion (IPPLM), 23 Hery Str., 01-497 Warsaw, Poland, Tel.: +48 22 638 1460, Fax: +48 22 666 8372
  • Institute of Plasma Physics and Laser Microfusion (IPPLM), 23 Hery Str., 01-497 Warsaw, Poland, Tel.: +48 22 638 1460, Fax: +48 22 666 8372
autor
  • QuinteScience SERGE BARRAL, 31/33 Rozbrat Str., 00-429 Warsaw, Poland
Bibliografia
  • 1. Barral, S., Kurzyna, J., Szelecka, A., Rachubiński, H., Remírez, E., Martín, R., Ortiz, P., Alonso, J., Bottinelli, S., Mabillard, Y., Zaldívar, A., Rangsten, P., & Koppel, C. (2014). First experimental characterization of a pulsed plasma thruster with non-volatile liquid propellant. In Proceedings of Space Propulsion Conference, 19–22 May 2014. Cologne, Germany.
  • 2. Rezaeiha, A., & Schönherr, T. (2013). Overview of alternative propellants for use in PPT. In 29th International Symposium on Space Technology and Science ISTS, 2–9 June 2013. Nagoya, Japan.
  • 3. Barral, S., Kurzyna, J., Remírez, E., Martín, R., Ortiz, P., Alonso, J., Bottinelli, S., Mabillard, Y., Zaldívar, A., Rangsten, P., & Koppel, C. R. (2013). Development status of an open capillary pulsed plasma thruster with non-volatile liquid propellant. In Proceedings of the 33rd International Electric Propulsion Conference, 6–10 October 2013 (paper IEPC-2013-291). Worthington, OH: The Electric Rocket Propulsion Society.
  • 4. Koizumi, H., Kakami, A., Furuta, Y., Komurasaki, K., & Arakawa, Y. (2003). Liquid propellant pulsed plasma thruster. In Proceedings of 28th International Electric Propulsion Conference, Toulouse, France (no. 2003-87). Worthington, OH: The Electric Rocket Propulsion Society.
  • 5. Koizumi, H., Kawazoe, Y., Komurasaki, K., & Arakawa, Y. (2005). Performance improvement of a liquid propellant pulsed plasma thruster. In Proceedings of 29th International Electric Propulsion Conference, Princeton, NJ (no. 2005-69). Worthington, OH: The Electric Rocket Propulsion Society.
  • 6. Scharlemann, C. (2003). Investigation of thrust mechanism in a water fed pulsed plasma thruster. Ph. D. dissertation, The Ohio State University.
  • 7. Krejci, D., Seifert, B., & Scharleman, C. (2013). Endurance testing of pulsed plasma thruster for nanosatellites. Acta Astronomica, 91, 187–193.
  • 8. Haag, T. (1997). Thrust stand for pulsed plasma thrusters. Rev. Sci. Instrum., 68, 2060–2067.
Typ dokumentu
Bibliografia
Identyfikatory
Identyfikator YADDA
bwmeta1.element.-psjd-doi-10_1515_nuka-2015-0057
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