Comparison of Hall-Effect Thrusters vs Electrostatic Ion Thrusters

Communication satellites often use electric propulsion systems. These satellites orbit the earth at specific altitudes to record data and transmit it to stations on earth. This requires onboard propulsion systems to make necessary corrections, keeping the device within an acceptable altitude and position. Two very common propulsion systems used are the Hall-effect Thruster and the Electrostatic Ion Thruster. Both systems were analyzed to view the benefits of each and contrast them. Both propulsion systems most commonly use xenon as their fuel, and therefore make comparison of their performances easier by eliminating the effects of using different fuel sources. Comparing these two thrusters we can analyse their suitability with respect to fuel usage, weight, thrust provided, and maneuverability. This allows for a detailed comparison of the two propulsion systems to detail the benefits and detriments each system's usage may bring, and determine which system may be more suitable in a given situation. This will allow for better decisions to be made when designing spacecraft depending on the device's purpose.

Description

Poster and abstract presented at the FYRE in STEM Showcase, 2024.
Research project completed at the Department of Aerospace Engineering.

Publisher

Wichita State University

Series

FYRE in STEM 2024

URI

https://hdl.handle.net/10057/27774

Collections

FYRE in STEM 2024