author={Mark A. Hopkins},
..................................................................................................................... xiv Chapter 
1 Citations
Effect of Channel Shape on Hall thruster Performance Using Argon and Xenon propellant
Recently, alternative propellant is required because xenon price is increasing yearly. Argon which is the cheapest gas to use EPs, have not been a strong candidate because of its poor performance.


Light Metal Propellant Hall Thrusters
The feasibility of using magnesium (Mg) and zinc (Zn) vapor as Hall Effect Thruster propellant was proven. Mg and Zn are plentiful, non-toxic, low cost alternatives to xenon and krypton. Because Zn
Internal plasma potential measurements of a Hall thruster using xenon and krypton propellant (10 pages)
For krypton to become a realistic option for Hall thruster operation, it is necessary to understand the performance gap between xenon and krypton and what can be done to reduce it. A floating
Development of a Magnesium and Zinc Hall-effect Thruster
§This paper describes what are believed to be the first demonstrations of Hall-effect thrusters operating on magnesium and zinc propellant. Pathfinding experiments were performed using consumable
Effect of Anode Temperature on Hall Thruster Performance
The effects of anode temperature on the performance of a 5-kW Hall-effect thruster are investigated. The performance characteristics of the P5 Hall-effect thruster are measured with and without
Performance Evaluation of an Iodine-Vapor Hall Thruster
The performance of a nominal 200 W Hall effect thruster fueled by iodine vapor was evaluated. The system included a laboratory propellant feed system, a flight-model Hall thruster, and breadboard
Thrust stand for high‐power electric propulsion devices
A thrust stand for use with magnetoplasmadynamic (MPD) thrusters operated at powers up to 250 kW steady state has been built and tested. The stand was based on an inverted pendulum configuration
Characterizing Vacuum Facility Backpressure Effects on the Performance of a Hall Thruster
* Presented as Paper IEPC-01-045 at the 27 International Electric Propulsion Conference, Pasadena, CA, 15-19 October 2001. † Copyright © 2001 by the Electric Rocket Propulsion Society. All rights
Development and Testing of a Prototype Bismuth Cathode for Hall Thrusters
Using bismuth in place of gases such as xenon for Hall thruster propellant could potentially offer both physical and economical gains. As research continues to develop Hall thrusters that are fueled
Progress on the Development of a Direct Evaporation Bismuth Hall Thruster
It has been demonstrated that using segmented anodes for thermal regulation of anodes is possible by controlling where the discharge current attaches to. Thrust, Isp and efficiency measurements were
Magnetic shielding of a laboratory Hall thruster. I. Theory and validation
We demonstrate a technique by which erosion of the acceleration channel in Hall thrusters can be reduced by at least a few orders of magnitude. The first principles of the technique, now known as