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Title: Computational simulation of coupled nonequilibrium discharge and compressible flow phenomena in a microplasma thruster

Journal Article · · Journal of Applied Physics
DOI:https://doi.org/10.1063/1.3224863· OSTI ID:21361825
; ;  [1]
  1. Department of Aerospace Engineering and Engineering Mechanics, University of Texas at Austin, Austin, Texas 78712 (United States)

The microplasma thruster (MPT) concept is a simple extension of a cold gas micronozzle propulsion device, where a direct-current microdischarge is used to preheat the gas stream to improve the specific impulse of the device. Here we study a prototypical MPT device using a detailed, self-consistently coupled plasma and 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. Compared to a cold gas micronozzle, a significant increase in specific impulse is obtained from the power deposition in the diverging section of the MPT nozzle. For a discharge voltage of 750 V, a power input of 650 mW, and an argon mass flow rate of 5 SCCM (SCCM denotes cubic centimeter per minute at STP), the specific impulse of the device is increased by a factor of approx1.5 to about 74 s. 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 MPT concept as a simple and effective approach to improve the performance of micronozzle cold gas propulsion devices.

OSTI ID:
21361825
Journal Information:
Journal of Applied Physics, Vol. 106, Issue 6; Other Information: DOI: 10.1063/1.3224863; (c) 2009 American Institute of Physics; ISSN 0021-8979
Country of Publication:
United States
Language:
English