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High-Propellant Throughput Sub-kW Electric Propulsion System for Deep Space Science and Exploration The National Aeronautics and Space Administration (NASA) is maturing high-propellant throughput sub-kilowatt electric propulsion technologies to enable small spacecraft deep space science and exploration missions with high delta-v requirements. The pathfinder model (PM) propulsion system consists of the H71M-PM Hall-effect thruster, a breadboard 1-kW power processing unit (PPU), and a propellant flow control system. The propulsion system requirements balance the needs of various high delta-v NASA and commercial industry mission concepts to achieve a design that both enables a variety of NASA small spacecraft deep space missions, while remaining viable for select commercial applications. The H71M-PM thruster has completed performance characterization and three 500-h short duration wear tests (SDWT). The propulsion system provides stable thrust generation over a wide range of operating conditions from 200 W to 1 kW, and 200 V to 400 V. The thruster has demonstrated a thrust as high as 68 mN at 300 V and 1 kW. The thruster has similarly demonstrated a specific impulse of 1850 s at 400 V and 1 kW. Key surfaces were machined between each SDWT to simulate accelerated discharge channel and pole cover erosion. Profilometry scans across masked pole cover surfaces were conducted to determine erosion rates. SDWT results support that a target thruster lifetime of 14 kh with 50% margin is achievable. Component testing has demonstrated propellant azimuthal flow uniformity better than ± 2 percent of the nominal value, azimuthal magnetic field uniformity better than ± 0.5 percent of the nominal value, and cathode heater cycle testing to greater than 30,000 cycles. Propulsion system integrated system testing is planned to use the H71M-PM and a breadboard 1-kW PPU. Pathfinder model test results are now supporting the design of the H71M-EM engineering model thruster. A second-generation breadboard PPU has been fabricated and is currently under test. NASA has made these technologies available to U.S. industry through a no cost, nonexclusive license agreement.
Document ID
20220009248
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Gabriel F. Benavides
(Glenn Research Center Cleveland, Ohio, United States)
Hani Kamhawi
(Glenn Research Center Cleveland, Ohio, United States)
Timothy R. Sarver-Verhey
(Glenn Research Center Cleveland, Ohio, United States)
Corey R. Rhodes
(Glenn Research Center Cleveland, Ohio, United States)
Matthew J. Baird
(Glenn Research Center Cleveland, Ohio, United States)
Jonathan A. Mackey
(Glenn Research Center Cleveland, Ohio, United States)
Date Acquired
June 13, 2022
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
IEPC-2022-343
Meeting Information
Meeting: 37th International Electric Propulsion Conference (IEPC)
Location: Boston, MA
Country: US
Start Date: June 19, 2022
End Date: June 23, 2022
Sponsors: Accion International, Enpulsion
Funding Number(s)
WBS: 571232.04.46.22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert
Keywords
Hall
Thruster
Propulsion
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