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Development Status and Performance Metrics of the Advanced NEXT Ion Propulsion SystemThe Advanced NEXT ion propulsion system is a derivative of the NEXT-C flight design, incorporating modifications that support increased thrust-to-power ratios without significantly altering the system’s mass or volume. The primary design modifications are described, which include changes to the discharge cathode assembly, ion optics, and the power processing unit (PPU) architecture. A system integration test, conducted using an engineering model thruster and a prototype model PPU, verified functionality across the entire throttle range, assessed steady-state efficiencies, and evaluated fault management. The thruster demonstrated efficiencies comparable to those of the NEXT-C system, while maintaining adequate performance margins at all test conditions. A thrust of 330 mN was demonstrated, which represents a 40% increase over the NEXT-C maximum. The PPU operated stably at all ten throttle levels, effectively managed arc faults, and maintained an efficiency between 92% and 95%. Ongoing and future work includes detailed evaluation of ion optics performance, subcomponent life testing, and environmental qualification of the PPU.
Document ID
20250008168
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Robert E Thomas
(Glenn Research Center Cleveland, United States)
Marcelo C Gonzalez
(Glenn Research Center Cleveland, United States)
Rittu R Samuel
(HX5, LLC)
James J Bontempo
(Voyager Technologies)
Keith D Goodfellow
(L3Harris (United States) Melbourne, United States)
Chayse A Aubuchon
(L3Harris (United States) Melbourne, United States)
Michael J Patterson
(Desert Works Propulsion)
Date Acquired
August 7, 2025
Subject Category
Spacecraft Propulsion and Power
Report/Patent Number
IEPC-2025-133
Meeting Information
Meeting: 39th International Electric Propulsion Conference (IEPC)
Location: London
Country: GB
Start Date: September 14, 2025
End Date: September 19, 2025
Sponsors: Electric Rocket Propulsion Society, American Institute of Aeronautics and Astronautics, Imperial College London
Funding Number(s)
WBS: 966826.02.03.1786.25
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
in space propulsion
gridded ion thruster
plasma physics
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