NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Wear Trends of the HERMeS Thruster as a Function of Throttle PointA series of short-duration (200 hour) wear tests were conducted with two Hall Effect Rocket with Magnetic Shielding (HERMeS) technology demonstration units (TDU). Front pole covers, cathode keeper, and discharge channel wear were characterized as a function of discharge voltage, magnetic field strength, and chamber pressure. No discharge channel erosion was observed. Inner pole cover erosion was shown to be a weak function of discharge voltage with most erosion occurring at the lowest value, 300 volts. The TDU-3 keeper electrode eroded with each operating condition, with high magnetic field yielding the greatest erosion rate. The TDU-1 keeper electrode exhibited net deposition suggesting its configuration is more consistent with meeting overall HERMeS service life requirements. Ratios of molybdenum to graphite erosion rates suggests, with high uncertainty, that the sputtering ions are originating downstream of the thruster exit plane, striking the surface with small angles of incidence.
Document ID
20170009070
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Williams, George J., Jr. (NASA Glenn Research Center Cleveland, OH United States)
Kamhawi, Hani (NASA Glenn Research Center Cleveland, OH United States)
Choi, Maria (NASA Glenn Research Center Cleveland, OH United States)
Haag, Thomas (NASA Glenn Research Center Cleveland, OH United States)
Huang, Wensheng (NASA Glenn Research Center Cleveland, OH United States)
Herman, Daniel A. (NASA Glenn Research Center Cleveland, OH United States)
Gilland, James H. (Ohio Aerospace Inst. Cleveland, OH, United States)
Peterson, Peter Y. (Vantage Partners, LLC Cleveland, OH, United States)
Date Acquired
September 26, 2017
Publication Date
October 8, 2017
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
GRC-E-DAA-TN45507
Meeting Information
Meeting: International Electric Propulsion Conference
Location: Atlanta, GA
Country: United States
Start Date: October 8, 2017
End Date: October 12, 2017
Sponsors: NASA Headquarters
Funding Number(s)
WBS: WBS 729200.06.03.05.01
CONTRACT_GRANT: NNC12BA01B
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
life (durability)
ion engines
hollow cathodes

Related Records

There are no records associated with this record.
No Preview Available