Hollow cathodes as a plasma propulsion device
Grubisic, Angelo N. and Gabriel, Stephen B. (2008) Hollow cathodes as a plasma propulsion device. In, Proceedings of the 46th AIAA Aerospace Sciences Meeting and Exhibition. 46th AIAA Aerospace Sciences Meeting and Exhibition Reston, USA, American Institute of Aeronautics and Astronautics. (AIAA 2008-1082).
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Testing of T5 and T6 ion thruster derived hollow cathode thrusters (HCT) at the University of Southampton has demonstrated impressive propulsive performance showing potential for a number of new applications. Ongoing studies also indicate that the hollow cathode thruster concept can be scaled down to a micro-electro-mechanical-systems (MEMs) level device with improving thrust efficiencies. Initial results indicate 3 forms of HCT propulsion device are possible. The first is a high power <1kW device which evokes MPD (magneto-plasma-dynamic) principles to deliver very high specific impulses >1200s with inert propellants such as xenon and argon; essentially a low current (<30A) MPD-HCT thruster. The second form of device operates in an electrothermal mode at lower powers and currents (<100W, <3.2A) and is capable of delivering at least 427s with argon. More recently HCTs have also been proposed in a third form as an on-chip MEMs device for applications at very low power (<5W) with theoretical specific impulse up to 180s for xenon. This paper describes the current findings in HCT technology research and the proposed the possibility of extending this to MEMs scale
|Item Type:||Book Section|
|Keywords:||hollow cathode, thruster, plasma|
|Subjects:||U Military Science > U Military Science (General)
T Technology > TL Motor vehicles. Aeronautics. Astronautics
Q Science > QC Physics
|Divisions:||University Structure - Pre August 2011 > School of Engineering Sciences > Astronautics
|Date Deposited:||15 Feb 2010|
|Last Modified:||15 May 2012 11:15|
|Publisher:||American Institute of Aeronautics and Astronautics|
|RDF:||RDF+N-Triples, RDF+N3, RDF+XML, Browse.|
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