| Autor: |
Acheson, Chris R., Glowacki, Jakub, Nakano, Ryota, Maeshima, Daiki, Saile, Dominik, Pavri, Betina, Takagi, Ryohei, Mori, Ryoyu, Pollock, Randy, Olatunji, Jamal R., Goddard-Winchester, Max, Strickland, Nicholas M., Ichihara, Daisuke, Wimbush, Stuart C., Kinefuchi, Kiyoshi |
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| Zdroj: |
Journal of Electric Propulsion; 12/11/2023, Vol. 2 Issue 1, p1-22, 22p |
| Abstrakt: |
Interplanetary transport of payloads of unprecedented mass, as envisaged beyond the lunar gateway, will require thrusters with high specific impulse as well as high thrust. To achieve this, innovations in propulsion are critical. Many classes of electric thruster utilise a magnetic applied field module to accelerate charged particles. Magnetoplasmadynamic thrusters exhibit improved performance with increasing field, at least up to the limit of around 0.5 T able to be provided by permanent magnets or copper electromagnets. However, superconducting magnets can generate much stronger magnetic fields. In this study, we utilised a space-relevant cryocooled high temperature superconducting magnet as the applied field module for a central cathode electrostatic thruster (CC-EST). A convex anode enabled ignition at high magnetic fields, and in this configuration the thruster's performance was characterised in the power range of 1 kW to 2.5 kW and at steady applied fields ranging from 0.6 T to 0.8 T, representing a significant advance in achievable field strength. In combination, these operating parameters enabled the achievement of a magnet-inclusive thruster efficiency of 19%, while the cryocooled magnet was demonstrated to be thermally stable in the presence of the kW-scale plasma, demonstrating the viability of such a design for space flight applications. [ABSTRACT FROM AUTHOR] |
| Databáze: |
Complementary Index |
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