Experimental and Computational Investigation of a RF Plasma Micro-Thruster

Journal Article · Wed Dec 31 04:00:00 EST 2008 · AIP Conference Proceedings

DOI:https://doi.org/10.1063/1.3076596· OSTI ID:21254965

Olliges, J D ^[1]; Ketsdever, A D ^[2]; Stein, W B; Alexeenko, A A; Hrbud, I ^[3]

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1. University of Southern California, Aerospace and Mechanical Engineering, Los Angeles, CA 90089 (United States)
2. Air Force Research Laboratory, Edwards AFB, CA 93524 (United States)
3. Purdue University, School of Aeronautical and Astronautical Engineering, West Lafayette, IN 47907 (United States)

A prototype RF plasma micro-thruster has been investigated numerically and experimentally. The experimental results were obtained on a thrust stand capable of micro-Newton resolution. Thrust and mass flow (hence specific impulse) were measured for an argon propellant at mass flows ranging from 0.4 to 5.5 mg/s. An increase over the cold gas thrust of up to 20% was observed for a discharge frequency of 100 MHz and an input power of 77 W. Propulsive efficiency was seen to increase both experimentally and numerically for increasing mass flow and decreasing discharge frequency.

• OSTI ID: 21254965
• Journal Information: AIP Conference Proceedings, Journal Name: AIP Conference Proceedings Journal Issue: 1 Vol. 1084; ISSN 0094-243X; ISSN APCPCS
• Country of Publication: United States
• Language: English

Related Subjects

71 CLASSICAL AND QUANTUM MECHANICS
GENERAL PHYSICS
ARGON
MASS
MHZ RANGE
MONTE CARLO METHOD
PLASMA
PLASMA INSTABILITY
PULSES
THRUSTERS