62nd Annual Gaseous Electronics Conference
Volume 54, Number 12
Tuesday–Friday, October 20–23, 2009;
Saratoga Springs, New York
Session FT2: Plasma Thrusters
8:00 AM–9:30 AM,
Tuesday, October 20, 2009
Saratoga Hilton
Room: Ballroom 2
Chair: Ane Aanesland, CNRS - Ecole Polytechnique
Abstract ID: BAPS.2009.GEC.FT2.5
Abstract: FT2.00005 : Microdischarge plasma thrusters for small satellite propulsion
9:00 AM–9:30 AM
Preview Abstract
Abstract
Author:
Laxminarayan Raja
(The University of Texas at Austin)
Small satellites weighing less than 100 kg are gaining importance in the
defense and commercial satellite community owing to advantages of low costs
to build and operate, simplicity of design, rapid integration and testing,
formation flying, and multi-vehicle operations. The principal challenge in
the design and development of small satellite subsystems is the severe mass,
volume, and power constraints posed by the overall size of the satellite.
The propulsion system in particular is hard to down scale and as such poses
a major stumbling block for small satellite technology.\textbf{
}Microdischarge-based miniaturized plasma thrusters are potentially a novel
solution to this problem.
In its most basic form a microdischarge plasma thruster is a simple
extension of a cold gas micronozzle propulsion device, where a direct or
alternating current microdischarge is used to preheat the gas stream to
improve to specific impulse of the device. We study a prototypical thruster
device using a detailed, self-consistent coupled plasma and fluid flow
computational model. The model describes the microdischarge power
deposition, plasma dynamics, gas-phase chemical kinetics, coupling of the
plasma phenomena with high-speed flow, and overall propulsion system
performance. Unique computational challenges associated with microdischarge
modeling in the presence of high-speed flows are addressed. Compared to a
cold gas micronozzle, a significant increase in specific impulse (50 to 100
{\%}) is obtained from the power deposition in the diverging supersonic
section of the thruster nozzle. The microdischarge remains mostly confined
inside the micronozzle and operates in an abnormal glow discharge regime.
Gas heating, primarily due to ion Joule heating, is found to have a strong
influence on the overall discharge behavior. The study provides a validation
of the concept as simple and effective approach to realizing a relatively
high-specific impulse thruster device at small geometric scales.
To cite this abstract, use the following reference: http://meetings.aps.org/link/BAPS.2009.GEC.FT2.5