Development of a Hollow Cathode Micro-Thruster for Small Satellites
- Paper number
IAC-06-C4.P.4.01
- Author
Mr. Angelo Grubisic, University of Southampton, United Kingdom
- Year
2006
- Abstract
Conventional low cost propulsion systems for small satellites, such as cold gas and resistojets, are robust and capable of providing basic attitude control functions. When considering increasing capabilities however, these systems lack the specific impulse and flexibility offered by more advanced propulsion. On the other hand small satellites are not generally able to accommodate high performance systems without significant increases in complexity, which limit their use. Few intermediate solutions exist between these extremes. This paper therefore presents initial results on the development of a cost effective stand-alone microthruster to fill the performance gap in the thruster spectrum. Operating hollow cathodes in specific geometries has been found to give heavy particle exit temperatures approaching 6,000K with wall temperature 1,400-1,600K making a simple but promising electrothermal thruster. Operating at low powers between 20-100W, the hollow cathode microthruster will operate with minimal conditioning and avoid scaling issues associated with magnetic confinement. Optimizing cathode geometry is shown to enable usable thrusts and moderate specific impulse at low fall voltages. By exploring plasma formation and acceleration processes, the influence of terminal parameters is assessed.
- Abstract document
- Manuscript document
IAC-06-C4.P.4.01.pdf (🔒 authorized access only).
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