NDLI: Electric thruster research (Document No: 19820016409)

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Electric thruster research (Document No: 19820016409)

Content Provider	NASA Technical Reports Server (NTRS)
Author	Kaufman, H. R. Robinson, R. S.
Copyright Year	1981
Description	The multipole discharge chamber of an electrostatic ion thruster is discussed. No reductions in discharge losses were obtained, despite repeated demonstration of anode potentials more positive than the bulk of the discharge plasma. The penalty associated with biased anode operation was reduced as the magnetic integral above the biased anodes was increased. The hollow cathode is discussed. The experimental configuration of the Hall current thruster had a uniform field throughout the ion generation and acceleration regions. To obtain reliable ion generation, it was necessary to reduce the magnetic field strength, to the point where excessive electron backflow was required to establish ion acceleration. The theoretical study of ion acceleration with closed electron drift paths resulted in two classes of solutions. One class has the continuous potential variation in the acceleration region that is normally associated with a Hall current accelerator. The other class has an almost discontinuous potential step near the anode end of the acceleration region. This step includes a significant fraction of the total acceleration potential difference.
File Size	5044499
Page Count	162
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19820016409
Archival Resource Key	ark:/13960/t8cg4j75x
Language	English
Publisher Date	1981-12-01
Access Restriction	Open
Subject Keyword	Spacecraft Propulsion And Power Magnetic Flux Hollow Cathodes Electrostatic Engines Discharge Coefficient Ion Engines Hall Effect Plasma Acceleration Electric Current Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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