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EASIER VX-200 Operation at 200 kW and Plume Measurements: Future Plans and an ISS EP Test Platform IEPC-2011-154 Presented at the 32nd International Electric Propulsion Conference, Wiesbaden Germany

Houston, Texas, 77023, USA Thomas P. DeBakey11 Department of Electrical and Computer Engineering, University of Houston, Houston, Texas, 77023, USA Christopher R. Miley12 Department of Electrical and Computer Engineering, University of Texas, Austin, TX, 78753, USA George L. Miller12 University of California — Riverside, Riverside, California, 92503, USA Michael B. Moore13 School of Aerospace Engineering, University of California — Davis, Davis, California, 95616, USA Present at IEEE Spring Symposium on “Electric Propulsion and Electric Vehicle Power Systems, May 2013 Abstract: The concept of a plasma thruster is that a charged-particle accelerator can produce plasma for electric thrust applications. Plasma thrusters are considered to be more efficient if they can create large plumes of ionized gases to produce thrust. The current generation of plasma thrusters has three operational modes (i.e., linear, turbo or turbo pump). In all three, plasma is produced and ejected through a single injection nozzle, or alternatively, plasmids (plasma particles) are ejected from either one or two injection nozzles. This review focuses on the plasma thruster as the most practical propulsion system to date for Earth observation and space missions. The advantages of a plasma thruster include: simplicity, operation at high speeds, high operating pressures, large plumes and low propellant consumption. The current plasma thruster system, the VX-200, has demonstrated several operational modes at approximately 20 kilowatts of thrust. This thruster can produce plasma plumes that are comparable to those produced by ion drives (i.e., 30 kW) on Earth. This paper assesses the overall performance of the VX-200 as well as provides some discussion about the development of future plasma thrusters based on the technology being available today. Aerospace craft Propulsion: Current Status and Technology Assessment IAEA-2010-633 Presented at the IEEASI-2010 International Electric Propulsion Conference, Onside, The Netherlands March 10 – 12 2009 Patrick O. McGovern2 University of Minnesota, Minneapolis, Minnesota, 55402, USA Paul E. Wiehe2 University of Colorado — Boulder, Boulder, Colorado, 80309, USA Mark J. Biederman1 University of Washington, Seattle, Washington, 98195, USA Eric D.

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