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Ion Thruster Plasma Generators 157 500 450 400 350 300 250 200 150 100 50 0 B=0G B=5G B = 10 G 0.70 0.75 0.80 Mass Utilization Efficiency Fig. 4-34. rf ion thruster discharge loss versus mass utilization efficiency for three values of the induced magnetic field in the discharge chamber. 0.85 0.90 0.95 230 eV/ion if 10 G is induced in the chamber. This is a significant reduction in the calculated loss and is the key to rf ion thruster discharge performance. To produce the 2-A beam in our 20-cm thruster example at 230 eV/ion, a total input power to the antenna of 460 W is required to be absorbed by the plasma. Since the rf power supplies are typically 90% efficient in this frequency range, the input power to the thruster PPU would be about 511 W. This predicted performance is in good agreement with the data about this size of rf thruster found in the literature [50], suggesting that a 0-D particle and energy balance model can provide reasonably accurate performance predictions. One advantage of rf ion thrusters is that they have only Maxwellian electrons and ambipolar ion and electron loss rates, which simplifies the discharge loss expressions and makes it easy to analyze the few geometric parameters to optimize the discharge loss. An example of the process is as follows: First, specifying the required beam current and current density determines the grid diameter in any ion thruster. Ion optics codes then determine the grid transparency. Once the grid design is set, a Monte-Carlo gas code is used to evaluate the Clausing factor introduced in Eq. (4.3-33). Assuming a conical or cylindrical discharge chamber shape of a given length immediately specifies the loss areas and plasma volume. Then, specifying the mass utilization efficiency gives the neutral density, and the electron temperature can be found from Eq. (4.5-17) with an initial confinement factor assumption. These values are the input parameters to the discharge loss given by Eq. (4.5-15), which provides the Discharge Loss (eV/ion)PDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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