Fundamentals of Electric Propulsion: Ion and Hall Thrusters

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Fundamentals of Electric Propulsion: Ion and Hall Thrusters ( fundamentals-electric-propulsion-ion-and-hall-thrusters )

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294 Chapter 6 at 553.5 nm excited in the plasma. Since the emission intensity depends on the amount of Ba present in the plasma and the electron density and temperature, the plasma parameters were monitored with a probe and the Ba-I signal was normalized to a neutral xenon line to account for any variations in plasma parameters during the measurements. Figure 6-38 shows the barium loss rate measured at 725 ̊C versus the ion bombardment energy. Increasing the ion bombardment energy from 10 to 30 eV increases the barium loss rate by an order of magnitude. Figure 6-39 shows the barium loss rate as a function of temperature for two cathode bias energies. For the case of the cathode floating relative to the plasma, the ion bombardment energy is only a few eV and the barium loss rate is determined solely by thermal evaporation. For a bias energy of 15 eV, the barium loss rate is found to be the same as for thermal evaporation for cathode temperatures in excess of about 800 ̊C. Since the hollow cathodes in most thrusters operate at insert temperatures in excess of 1000 ̊C, these data show that the barium loss rate is determined by thermal evaporation rates. A model of the enhancement of barium evaporation for a surface under energetic ion bombardment was developed by Doerner, et al. [49] to explain this behavior. At elevated surface temperatures, two classes of surface particles must be considered at the surface: (a) those particles that are bound to the material lattice structure (denoted here as “lattice atoms”) and (b) atoms that have been liberated from the lattice structure, but which are still bound to the Fig. 6-38. Variation of barium loss rate from the cathode surface at 725 ̊C with cathode bias voltage (redrawn from [48]).

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