In this paper we review recent results obtained for segmented electrode and cylindrical Hall thrusters. A low sputtering graphite segmented electrode, placed at the exit of the annular thruster, is shown to affect the plasma potential distribution in the ceramic channel. This effect appears to be correlated with an observed plume reduction compared to a conventional, nonsegmented thruster. In preliminary experiments a 3 cm thruster was operated in the 50-200 W power range. Two operating regimes, stable and oscillating, were observed and investigated. © 2001 by the American Institute of Aeronautics and Astronautics Inc. All rights reserved.