NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Development of a High-Propellant Throughput Small Spacecraft Electric Propulsion System (HT-SSEP) to Enable Lower Cost NASA Science MissionsDiscusses progress at the NASA Glenn Research Center (GRC) in the development and demonstration of an integrated high-propellant throughput small spacecraft electric propulsion (HT-SSEP) system based on a Hall-effect thruster. A center-mounted cathode and an innovative magnetic circuit topology were implemented in the design of the Hall-effect thruster to achieve high-propellant throughput, high performance, and efficient packaging. To minimize technical risk, the HT-SSEP development approach sought to limit design features and materials to those with a clear path-to-flight. A propellant throughput capability of greater than 100 kilograms at a minimum thruster efficiency of 50 percent was targeted. The proof-of-concept NASA-H64M laboratory model (LM) thruster was designed, fabricated, and tested at GRC in fiscal year 2018. The thruster development leveraged heritage Hall-effect thruster design and manufacturing processes wherever appropriate. Recent NASA advances in Hall-effect thruster technology were also leveraged. A scalable discharge power supply (DPS) capable of powering the H64M-LM was developed, then demonstrated as part of an integrated system test. The DPS uses commercial off-the-shelf components with spaceflight equivalents. A keeper supply with DC ignitor was breadboarded, then demonstrated with a laboratory cathode. Finally, feed system trade studies were performed to ascertain what feed system architecture might be appropriate for an HT-SSEP system. This paper details the motivations for the project, the development approach, the chosen sub-system architectures, design considerations, and test results.
Document ID
20190030680
Document Type
Presentation
Authors
Benavides, Gabriel (NASA Glenn Research Center Cleveland, OH, United States)
Kamhaw, Hani (NASA Glenn Research Center Cleveland, OH, United States)
Liu, Thomas (NASA Glenn Research Center Cleveland, OH, United States)
Pinero, Luis (NASA Glenn Research Center Cleveland, OH, United States)
Sarver-Verhey, Timothy (NASA Glenn Research Center Cleveland, OH, United States)
Rhodes, Corey (NASA Glenn Research Center Cleveland, OH, United States)
Yim, John (NASA Glenn Research Center Cleveland, OH, United States)
Mackey, Jon (NASA Glenn Research Center Cleveland, OH, United States)
Gray, Timothy (NASA Glenn Research Center Cleveland, OH, United States)
Butler-Craig, Naia (NASA Glenn Research Center Cleveland, OH, United States)
Myers, James (Vantage Partners, LLC Brook Park, OH, United States)
Birchenough, Arthur (Vantage Partners, LLC Brook Park, OH, United States)
Date Acquired
September 9, 2019
Publication Date
August 21, 2019
Subject Category
Spacecraft Propulsion and Power
Report/Patent Number
AIAA 2019-4162
GRC-E-DAA-TN72297
Meeting Information
AIAA/SAE/ASEE Joint Propulsion and Energy Forum and Exposition 2019(Indianapolis, IN)
Funding Number(s)
WBS: 469947.04.22.22
CONTRACT_GRANT: NNC12BA01B
Distribution Limits
Public
Copyright
Public Use Permitted.
Technical Review
Single Expert

Available Downloads

NameType 20190030680.pdf STI