Experimental Investigations of a Krypton Stationary Plasma Thruster
Stationary plasma thrusters are attractive electric propulsion systems for spacecrafts. The usual propellant is xenon. Among the other suggested propellants, krypton could be one of the best candidates. Most studies have been carried out with a Hall effect thruster previously designed for xenon. The...
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| Format: | Article |
| Language: | English |
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Wiley
2013-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2013/686132 |
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| author | A. I. Bugrova A. M. Bishaev A. V. Desyatskov M. V. Kozintseva A. S. Lipatov M. Dudeck |
| author_facet | A. I. Bugrova A. M. Bishaev A. V. Desyatskov M. V. Kozintseva A. S. Lipatov M. Dudeck |
| author_sort | A. I. Bugrova |
| collection | DOAJ |
| description | Stationary plasma thrusters are attractive electric propulsion systems for spacecrafts. The usual propellant is xenon. Among the other suggested propellants, krypton could be one of the best candidates. Most studies have been carried out with a Hall effect thruster previously designed for xenon. The ATON A-3 developed by MSTU MIREA (Moscow) initially defined for xenon has been optimized for krypton. The stable high-performance ATON A-3 operation in Kr has been achieved after optimization of its magnetic field configuration and its optimization in different parameters: length and width of the channel, buffer volume dimensions, mode of the cathode operation, and input parameters. For a voltage of 400 V and the anode mass flow rate of 2.5 mg/s the anode efficiency reaches 60% and the specific impulse reaches 2900 s under A-3 operating with Kr. The achieved performances under operation A-3 with Kr are presented and compared with performances obtained with Xe. |
| format | Article |
| id | doaj-art-fffd14f73a11472ebe345090a8cc2e43 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2013-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-fffd14f73a11472ebe345090a8cc2e432025-02-03T05:53:49ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742013-01-01201310.1155/2013/686132686132Experimental Investigations of a Krypton Stationary Plasma ThrusterA. I. Bugrova0A. M. Bishaev1A. V. Desyatskov2M. V. Kozintseva3A. S. Lipatov4M. Dudeck5Laboratory of Plasmadynamics, Sub-Faculty of Physics, Moscow State Technical University of Radio Engineering, Electronics and Automation (MSTU MIREA), 119454 Moscow, RussiaLaboratory of Plasmadynamics, Sub-Faculty of Physics, Moscow State Technical University of Radio Engineering, Electronics and Automation (MSTU MIREA), 119454 Moscow, RussiaLaboratory of Plasmadynamics, Sub-Faculty of Physics, Moscow State Technical University of Radio Engineering, Electronics and Automation (MSTU MIREA), 119454 Moscow, RussiaLaboratory of Plasmadynamics, Sub-Faculty of Physics, Moscow State Technical University of Radio Engineering, Electronics and Automation (MSTU MIREA), 119454 Moscow, RussiaLaboratory of Plasmadynamics, Sub-Faculty of Physics, Moscow State Technical University of Radio Engineering, Electronics and Automation (MSTU MIREA), 119454 Moscow, RussiaInstitut Jean le Rond d'Alembert, Université Pierre et Marie Curie (Paris 6), 75252 Paris Cedex, FranceStationary plasma thrusters are attractive electric propulsion systems for spacecrafts. The usual propellant is xenon. Among the other suggested propellants, krypton could be one of the best candidates. Most studies have been carried out with a Hall effect thruster previously designed for xenon. The ATON A-3 developed by MSTU MIREA (Moscow) initially defined for xenon has been optimized for krypton. The stable high-performance ATON A-3 operation in Kr has been achieved after optimization of its magnetic field configuration and its optimization in different parameters: length and width of the channel, buffer volume dimensions, mode of the cathode operation, and input parameters. For a voltage of 400 V and the anode mass flow rate of 2.5 mg/s the anode efficiency reaches 60% and the specific impulse reaches 2900 s under A-3 operating with Kr. The achieved performances under operation A-3 with Kr are presented and compared with performances obtained with Xe.http://dx.doi.org/10.1155/2013/686132 |
| spellingShingle | A. I. Bugrova A. M. Bishaev A. V. Desyatskov M. V. Kozintseva A. S. Lipatov M. Dudeck Experimental Investigations of a Krypton Stationary Plasma Thruster International Journal of Aerospace Engineering |
| title | Experimental Investigations of a Krypton Stationary Plasma Thruster |
| title_full | Experimental Investigations of a Krypton Stationary Plasma Thruster |
| title_fullStr | Experimental Investigations of a Krypton Stationary Plasma Thruster |
| title_full_unstemmed | Experimental Investigations of a Krypton Stationary Plasma Thruster |
| title_short | Experimental Investigations of a Krypton Stationary Plasma Thruster |
| title_sort | experimental investigations of a krypton stationary plasma thruster |
| url | http://dx.doi.org/10.1155/2013/686132 |
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