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Characterizing Electrical Arc Behavior in Ion EnginesGridded ion engines represent a class of electric thrusters characterized by high propulsive efficiency and high total impulse capabilities. These engines operate by applying high voltage to multi-aperture electrodes, thereby electrostatically accelerating plasma to generate thrust. Within the course of normal operations, periodic occurrences of high voltage breakdowns manifest within the thruster. These breakdowns constitute an inherent aspect of operation, with observations indicating a diminishing frequency and total count over the thruster's operational lifespan. To safeguard the propulsion system during such occurrences, the power processing unit (PPU) employs an automated arc extinction sequence, termed "recycle," which is triggered upon detection of an over-current condition. The initial phase of this sequence involves momentarily deactivating the high voltage and reducing the discharge current to a predetermined level, minimizing plasma impingement as the ion beam is defocused. The high voltage is subsequently reapplied, and the discharge current is returned to its nominal value. The entire sequence typically spans approximately 800 milliseconds. Throughout a recycle event, the propulsion system experiences various current and voltage transients as the arc current traverses the system and different power supplies are toggled on and off.
Document ID
20240006356
Acquisition Source
Glenn Research Center
Document Type
Extended Abstract
Authors
Robert E. Thomas
(Glenn Research Center Cleveland, United States)
Rittu S. Raju
(HX5, LLC)
Keith D. Goodfellow
(Aerojet Rocketdyne Rancho Cordova, California, United States)
Chayse A. Aubuchon
(Aerojet Rocketdyne Rancho Cordova, California, United States)
James J. Bontempo
(ZIN Technologies (United States) Cleveland, United States)
Date Acquired
May 16, 2024
Subject Category
Spacecraft Propulsion and Power
Meeting Information
Meeting: AIAA SciTech Forum and Exposition
Location: Orlando, FL
Country: US
Start Date: January 6, 2025
End Date: January 10, 2025
Sponsors: American Institute of Aeronautics and Astronautics, Lockheed Martin (United States)
Funding Number(s)
WBS: 966826.02.03.1724.24
CONTRACT_GRANT: SpaceDoc SAA3-1711
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
Keywords
electric propulsion
gridded ion engines
spacecraft interactions
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