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>Pulse ignition characterization of mercury ion thruster hollow cathode using an improved pulse ignitor
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Pulse ignition characterization of mercury ion thruster hollow cathode using an improved pulse ignitor
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机译：使用改进的脉冲点火器对汞离子推进器空心阴极进行脉冲点火表征
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摘要
An investigation of the high voltage pulse ignition characteristics of the 8 cm mercury ion thruster neutralizer cathode identified a low rate of voltage rise and long pulse duration as desirable factors for reliable cathode starting. Cathode starting breakdown voltages were measured over a range of mercury flow rates and tip heater powers for pulses with five different rates of voltage rise. Breakdown voltage requirements for the fastest rising pulse (2.5 to 3.0 kV/micro sec) were substantially higher (2 kV or more) than for the slowest rising pulse (0.3 to 0.5 kV/micro sec) for the same starting conditions. Also described is an improved, low impedance pulse ignitor circuit which reduces power losses and eliminates problems with control and packaging associated with earlier designs.
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