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An 8-cm ion thruster characterization

Author
Hancock, D. J.
Published
Oct 1, 1987.
Physical Description
1 electronic document
Additional Creators
Williamson, W. S., Wessel, F. J., and Dulgeroff, C. R.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The performance of the Ion Auxiliary Propulsion System (IAPS) thruster was increased to thrust T = 32 mN, specific impulse I sub sp = 4062 s, and thrust-to-power ratio T/P = 33 mN/kW. This performance was obtained by increasing the discharge power, accelerating voltage, propellant flow rate, and chamber magnetic field. Adding a plenum and main vaporizer for propellant distribution was the only major change required in the thruster. The modified thruster characterization is presented. A cathode magnet assembly did not improve performance. A simplified power processing unit was designed and evaluated. This unit decreased the parts count of the IAPS power processing unit by a factor of ten.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19880000724.
Accession ID: 88N10106.
NAS 1.26:180819.
HAC-E7324.
NASA-CR-180819.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15697130