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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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310 Chapter 6 Fig. 6-53. The xenon ions gain most of their kinetic energy in the sheath and the potential well on axis (from [65]). plate to the keeper can be sufficient to ignite a discharge once gas is introduced. The plasma then penetrates the orifice, extending the anode potential into the insert region and the discharge transitions directly to the insert. The orifice plate is subject to sputter erosion by the ions in the discharge, and the barium layer is removed and has to be reestablished if the cathode is turned off in order to restart [68]. For cathodes with larger orifices (typically 2-mm diameter or larger), a sufficient keeper voltage (typically 100 to 500 V) will cause the applied positive potential to penetrate inside the insert region with levels in excess of the ionization potential of the propellant gas. The electrons from the insert then can be accelerated locally inside the insert and cause ionization, which ignites the discharge through the orifice to the keeper or anode. This is the mechanism used in most of the LaB6 cathodes developed by the authors to strike the discharge. For hollow cathodes with smaller orifices or inhibited orifice-plate emission (due to surface impurities, barium depletion, etc.), an arc-initiation technique typically is used. In this case, the applied keeper voltage is pulsed to a high positive value (typically >500 V). The discharge starts due to either field emission of electrons from the orifice plate ionizing the injected cathode gas or Paschen breakdown occurring at the relatively high pressure in the cathode-to- keeper gap generating plasma that penetrates the orifice into the insert region. To ensure reliable thruster ignition over life, it is standard to apply both a DC keeper voltage in the 50- to 150-V range and a pulsed keeper voltage in the

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