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15 cm mercury multipole thrusterA 15 cm multipole ion thruster was adapted for use with mercury propellant. During the optimization process three separable functions of magnetic fields within the discharge chamber were identified: (1) they define the region where the bulk of ionization takes place, (2) they influence the magnitudes and gradients in plasma properties in this region, and (3) they control impedance between the cathode and main discharge plasmas in hollow cathode thrusters. The mechanisms for these functions are discussed. Data from SERT II and cusped magnetic field thrusters are compared with those measured in the multipole thruster. The performance of this thruster is shown to be similar to that of the other two thrusters. Means of achieving further improvement in the performance of the multipole thruster are suggested.
Document ID
19780048848
Document Type
Conference Paper
Authors
Longhurst, G. R. (Colorado State Univ. Fort Collins, CO, United States)
Wilbur, P. J. (Colorado State University Fort Collins, Colo., United States)
Date Acquired
August 9, 2013
Publication Date
April 1, 1978
Subject Category
SPACECRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 78-682
Meeting Information
International Electric Propulsion Conference(San Diego, CA)
Funding Number(s)
CONTRACT_GRANT: NGR-06-002-112
Distribution Limits
Public
Copyright
Other