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Effects of anode material on arcjet performanceAnodes fabricated from four different materials were tested in a modular arcjet thruster at 1 kW power level on nitrogen/hydrogen mixtures. A two-percent thoriated tungsten anode served as the control. Graphite was chosen for its ease in fabrication, but experienced severe erosion in the constrictor and diverging side. Hafnium carbide and lanthanum hexaboride were chosen for their low work functions but failed due to thermal stress and reacted with the propellant. When compared to the thoriated tungsten nozzle, thruster performance was significantly lower for the lanthanum hexaboride insert and the graphite nozzle, but was slightly higher for the hafnium carbide nozzle. Both the lanthanum hexaboride and hafnium carbide nozzle operated at higher voltages. An attempt was made to duplicate higher performance hafnium carbide results, but repeated attempts at machining a second anode insert were unsuccessful. Graphite, hafnium carbide, and lanthanum hexaboride do not appear viable anode materials for low power arcjet thrusters.
Document ID
19930001009
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sankovic, John M. (NASA Lewis Research Center Cleveland, OH, United States)
Curran, Frank M. (NASA Lewis Research Center Cleveland, OH, United States)
Larson, C. A. (Air Force Academy CO., United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-105799
E-6873
NAS 1.15:105799
Meeting Information
Meeting: 1992 JANNAF Propulsion Meeting
Location: Indianapolis, IN
Country: United States
Start Date: February 24, 1992
End Date: February 28, 1992
Accession Number
93N10197
Funding Number(s)
PROJECT: RTOP 506-42-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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