Micro-Discharge Micro-Thruster
Abstract
This paper summarizes the experiments and analysis of the micro-discharge microthruster developed jointly by Ewing Technology Associates and the University of Washington. The key experimental result has been the demonstration of a sustained discharge in a very simple micro-discharge type of structure (aperture ^300 microns) under demanding flow conditions. The micro-discharge provides for power addition to the neutral gas in discharges that transition from relatively high pressure (^10-30 Torr) to vacuum on the supersonic flow side of the limiting aperture "nozzle" separating the discharge region from the vacuum region. The fact that a fairly stable discharge is maintained on the downstream side suggests that the fairly hot plasma (^2 eV) deposits power into the neutral gas (Argon) in a manner that produces a neutral flow of similar energy, much like an arcjet but at very low power (1-5 W). A crude measurement of the power deposition into the gas via an energy balance approach was obtained from thermocouple measurements, which also imply that the gas temperature may be as high as 1-2 eV. Thrust measurements as well as characterization of discharge and plasma properties are an integral part of the current experimental work. Concurrently, a numerical model is being developed to explain the gas and plasma dynamics involved in the device. A description of the device and the experimental setup, as well as results from the experiments, will be presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2005
- Accession Number
- ADA437433
Entities
People
- J. J. Ewing
- John Slough
- Samuel Andreason
- Timothy Ziemba
Organizations
- University of Washington