Performance of a magnetic multipole line-cusp argon ion thruster

Abstract

A 17-cm diameter line-cusp ion thruster was evaluated with inert gases which arc candidate propellants for on-orbit and orbit transfer propulsion functions for Large Space Systems. A semi-empirical relationshio 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 obt;,ined. These performance parameters are the highest yet achieved with argon propellant.

Improved ion containment using a ring-cusp ion thruster

“…The neutralizer was located 10 cm axially and 10 cm radially from the last row of grid holes (ref. 2).…”