Development of a High-Propellant Throughput Small Spacecraft Electric Propulsion System (HT-SSEP) to Enable Lower Cost NASA Science Missions

Benavides, Gabriel ; Kamhaw, Hani ; Liu, Thomas ; Pinero, Luis ; Sarver-Verhey, Timothy ; Rhodes, Corey ; Yim, John ; Mackey, Jon ; Gray, Timothy ; Butler-Craig, Naia(NASA Glenn Research Center, Cleveland, OH, United States)

关键词: HALL EFFECT THRUSTERS (HET);    ELECTRIC PROPULSION;    SPACECRAFT PROPULSION;    LOW THRUST PROPULSION;    SMALL SCIENTIFIC SATELLITES;    SMALL SATELLITE TECHNOLOGY;    PROPELLANTS;    POWER CONDITIONING;    MAGNETIC CIRCUITS;    CATHODES;    FEED SYSTEMS;    POWER EFFICIENCY;    HIGH IMPULSE;    PERFORMANCE TESTS;    DESIGN ANALYSIS;    MODELS;    COST REDUCTION;    NASA SPACE PROGRAMS;   

RP-ID  :  AIAA 2019-4162,GRC-E-DAA-TN72297

学科分类：航空航天科学

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来源: NASA Technical Reports Server

【 摘 要 】

Discusses 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 50percent 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.