Spacecraft propulsion applications for field emission cathodes

Author

Marrese-Reading, Colleen M. ; Polk, James E.

Author_Institution

Jet Propulsion Lab., California Inst. of Technol., Pasadena, CA, USA

fYear

2001

fDate

2001

Firstpage

123

Lastpage

124

Abstract

Many small-scale spacecraft propulsion systems under development could benefit from a compatible FE cathode. These thrusters challenge the performance of FE cathodes because of the plasma environment they create could significantly limit the cathode lifetime if it does not have the proper configuration and materials. The thruster current requirements and cathode integration challenges are discussed in this article. Cathode configurations are recommended to improve the cathode and thruster compatibility. Preliminary results are presented from the first successful test of an electric thruster with a Spindt-type FEA cathode neutralizer

Keywords

aerospace propulsion; cathodes; electric propulsion; electron field emission; vacuum microelectronics; Spindt-type FEA cathode neutralizer; cathode integration; electric propulsion; field emission cathode; plasma environment; spacecraft propulsion; thruster current; Aircraft manufacture; Cathodes; Control systems; Ion beams; Iron; Laboratories; Plasma materials processing; Propulsion; Space technology; Space vehicles;

fLanguage

English

Publisher

ieee

Conference_Titel

Vacuum Microelectronics Conference, 2001. IVMC 2001. Proceedings of the 14th International

Conference_Location

Davis, CA

Print_ISBN

0-7803-7197-6

Type

conf

DOI

10.1109/IVMC.2001.939684

Filename

939684