A comparison of experimental and computer model results on the charge-exchange plasma flow from a 30 cm mercury ion thrusterIon thrusters can be used in a variety of primary and auxiliary space-propulsion applications. A thruster produces a charge-exchange plasma which can interact with various systems on the spacecraft. The propagation of the charge-exchange plasma is crucial in determining the interaction of that plasma with the spacecraft. This paper compares experimental measurements with computer model predictions of the propagation of the charge-exchange plasma from a 30 cm mercury ion thruster. The plasma potentials, and ion densities, and directed energies are discussed. Good agreement is found in a region upstream of, and close to, the ion thruster optics. Outside of this region the agreement is reasonable in view of the modeling difficulties.
Document ID
19830031287
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gabriel, S. B. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Kaufman, H. R. (Colorado State University Fort Collins, CO, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1982
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1946
Meeting Information
Meeting: Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference