Actions for Performance of a magnetic multipole line-cusp argon ion thruster

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Performance of a magnetic multipole line-cusp argon ion thruster

Author
Sovey, J. S.
Published
JAN 1, 1981.
Physical Description
1 electronic document
Online Version

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Summary
A 17 cm diameter line cusp ion thruster was evaluated with inert gases which are candidate propellants for on orbit and orbit transfer propulsion functions for Large Space Systems. A semiempirical relationship was generated to predict thruster beam current in terms of plasma parameters which would allow initial thruster optimization without ion extraction and the associated large vacuum facilities. The sensitivity of performance to changes in discharge electrode configurations and magnetic circuit was evaluated and is presented. After final optimization a propellant utilization efficiency of 0.9 at a discharge chamber power expenditure of about 260 w per beam ampere was obtained. These performance parameters are the highest yet achieved with argon propellant.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19810010692.
Accession ID: 81N19219.
E-729.
NASA-TM-81703.
Intern. Elec. Propulsion Conf.; 21-23 Apr. 1981; Las Vegas, NV; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15719905