Performance and probe measurements of a radio-frequency plasma thruster
The performance of a radio-frequency plasma thruster is evaluated using a displacement-type, inverted-pendulum thrust stand in the Large Vacuum Test Facility at the University of Michigan. A radio-frequency generator supplies up to 2000 W to the radio-frequency plasma thruster at a fixed frequency of 13.56 MHz. The matching network is placed inside the vacuum chamber at the thruster, and the radio-frequency power is measured at the matching network input port with a dual-directional coupler. A Faraday probe measures the current density in the far-field exhaust of the thruster, a retarding potential analyzer characterizes the ion voltage distribution, and a Langmuir probe measures the plasma potential. The radio-frequency plasma thruster is operated with argon propellant at mass flow rates of 2.4-7.6 mg/s, at corresponding corrected facility pressures of 1.5 × 10-6-4.6 × 10-6 torr. The maximum thrust observed is 10.8 mN, and the maximum specific impulse is 303 s. Thrust efficiency is below1%at all conditions. Faraday probe results show that the propellant utilization efficiency is below 15% and that the ionized exhaust has an effective divergence half-angle of 48 deg. Thrust is negatively correlated with the ion beam most probable voltage, showing that retarding potential analyzer results alone may not accurately characterize thruster performance. Charge-exchange collisions likely have a significant influence on radio-frequency plasma thruster operation. Copyright © 2012 by Adam Shabshelowitz.
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- 4001 Aerospace engineering
- 0913 Mechanical Engineering
- 0901 Aerospace Engineering
- 0202 Atomic, Molecular, Nuclear, Particle and Plasma Physics
Citation
Published In
DOI
EISSN
ISSN
Publication Date
Volume
Issue
Start / End Page
Related Subject Headings
- Aerospace & Aeronautics
- 4001 Aerospace engineering
- 0913 Mechanical Engineering
- 0901 Aerospace Engineering
- 0202 Atomic, Molecular, Nuclear, Particle and Plasma Physics