Electrode Erosion Processes in Pulsed Plasma Thrusters.
Abstract
During the course of this program it was determined that material melting is the primary physical phenomenon leading to erosion of the anode electrode. Experimentation with various materials indicated that minimum erosion of the anode was obtainable using Poco Graphite but significant impulse bit reduction due to the high resistivity of this material would be incurred if this material were used. The material yielding the next least amount of anode erosion was shown to be copper (OHFC). Various modifications to the thruster propellant/electrode configurations were attempted using Graphite in attempting to recover the loss in thruster performance associated with the use of this material as an anode electrode. These attempts were unsuccessful, and the decision was made about midway through the program to concentrate on minimizing the effects of the arc heat load on a copper anode surface by reconfiguring the electrodes and/or propellant rods. This approach to the problem not only led to a successful solution of the anode erosion problem, but also resulted in improved thruster performance and the capability of storing sufficient propellant to meet a total impulse requirement far in excess of the program goal using the original helical rod storage system with modified propellant rod width. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1979
- Accession Number
- ADA069276
Entities
People
- Dominic J. Palumbo
- Martin Begun
- William J. Guman