Development of a large inert gas ion thrusterA 30 cm inert gas electrostatic ion thruster has been developed, exhibiting excellent performance. In the development, the effective anode area was reduced by altering the magnetic field geometry to improve plasma containment, consistent with operational stability. The propellant introduction scheme has the effect of 'folding' the discharge chamber without the increased wall loss penalty associated with a longer chamber. These features contribute to a low discharge cost (eV/ion) versus mass utilization characteristic which remains relatively flat even to high mass utilizations.
Document ID
19830031278
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Steiner, G. (Xerox Electro-Optical Systems Pasadena, CA, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1982
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1927
Meeting Information
Meeting: Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference