Flow Study of a Novel Ionizer Configuration with Testing Apparatus
Abstract
Micro-satellites require a propulsion system that minimizes mass and size while maximizing performance. Ion propulsion engines may be the most scalable pending reductions in ionizer size. This work explores a new ionization chamber concept. This thesis reports on the ionization of Argon, an alternative propellant to Xenon, which has been achieved at relatively low voltages with locally designed and manufactured Micro-Structured Electrode (MSE) Arrays. Testing was done with the gas flowing through the array holes, simulating the actual space environment as in an operating ion thruster. With argon flowing, breakdown has been achieved at voltages between 230 and 350 volts depending on chamber pressure, and array insulation thickness and hole size. The breakdown voltage in argon gas was higher (between 15 and 100 volts) with the flow than that without for the same wafer, and always higher for the smaller (0.127 mm vs. 0.381 mm) insulation thickness tested. No breakdown was observed when the cathode was located upstream.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 2008
- Accession Number
- ADA479818
Entities
People
- John D. Armstrong
Organizations
- Naval Postgraduate School