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A Hall Thruster Performance Model Incorporating the Effects of a Multiply-Charged Plasma

Author:
Hofer, Richard R.
Published:
January 2002.
Physical Description:
1 electronic document
Additional Creators:
Jankovsky, Robert S.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary:
A Hall thruster performance model that predicts anode specific impulse, anode efficiency, and thrust is discussed. The model is derived as a function of a voltage loss parameter, an electron loss parameter, and the charge state of the plasma. Experimental data from SPT and TAL type thrusters up to discharge powers of 21.6 kW are used to determine the best fit for model parameters. General values for the model parameters are found, applicable to high power thrusters and irrespective of thruster type. Performance of a 50 kW thruster is calculated for an anode specific impulse of 2500 seconds or a discharge current of 100 A.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 20020038543.
NASA/TM-2002-211214.
NAS 1.15:211214.
E-13066.
AIAA Paper 2001-3322.
37th Joint Propulsion Conference and Exhibit; 8-11 Jul. 2001; Salt Lake City, UT; United States.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15638424