Computational Investigations of Novel Micro-Glow Discharges for Potential Nanosatellite Thruster Applications
Final rept., 15 Jan 2003-31 Aug 2005
TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS
Pagination or Media Count:
The objective of this project was the development and application of a computational modeling approach for a fundamental understanding of the direct-current micro-discharge phenomena. A detailed, two-dimensional plasma simulation tool has been developed and implemented for the study of micro-discharges in the context of small-satellite electro-thermal propulsion. The special features of the model are a full self-consistent, multi-species, multi-temperature, treatment of plasma phenomena along with the effect of a net bulk flow in the system. The particular geometry of the micro-discharge based micropropulsion device defined the features of the computational model.
- Numerical Mathematics
- Electricity and Magnetism
- Unmanned Spacecraft