Development of a 50,000-s, Lithium-fueled, Gridded Ion Thruster
Development of a 50,000-s, Lithium-fueled, Gridded Ion Thruster
- Neue Suche nach: Goebel, Dan M.
- Neue Suche nach: Polk, James E.
- Neue Suche nach: Brophy, John R.
- Neue Suche nach: Goebel, Dan M.
- Neue Suche nach: Polk, James E.
- Neue Suche nach: Brophy, John R.
The ion propulsion system on NASA’s Dawn mission provided over 11 km/s delta-V to the spacecraft. There is potential interest in missions that have delta-V’s an order of magnitude greater than this, i.e., 100 km/s to 200 km/s. To perform such missions would require a thruster that can produce a specific impulse roughly an order of magnitude greater than the 3100 s of the Dawn ion propulsion system. A 50-kW gridded ion thruster is being developed for operation with lithium propellant to produce a specific impulse of 50,000 s. The resulting thruster design requires a net accelerating voltage of 9 kV and a beam current of 5.5 A. Discharge chamber modeling is used to design a 35-cm diameter ring-cusp discharge chamber with six magnet rings. The discharge chamber is masked down to produce an active grid area that is ~25 cm diameter. Modeling suggests that the unique ionization characteristics of lithium may enable discharge chamber operation at a propellant efficiency of 99%. Operation at such a high propellant efficiency could significantly reduce the production of charge-exchange ions and thereby significantly reduce erosion of the accelerator grid.
Dokumentinformationen
Development of a 50,000-s, Lithium-fueled, Gridded Ion Thruster
2017-10-09
Preprint
Keine Angabe
Englisch