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Ion and Hall Thruster Plumes 417 Thruster Plume Plasma +15 V Hollow Cathode Cathode Common Fig. 8-15. The thruster neutralizer hollow cathode generates a plasma typically 10 to 20 V above the cathode common. 0V Spacecraft Fig. 8-16. The cathode common would float on the order of 10 V negative on a spacecraft with a conducting surface. Thruster Plume Plasma +15 V −10 V Cathode Common Hollow 0 V Cathode about 10V negative with respect to the thruster plume plasma, cathode common would be 90-V positive compared to spacecraft ground, as illustrated in Fig. 8-17. On operational spacecraft, cathode common will float somewhere between the two extremes, –15 V to 90 V, depending on the array construction, and may vary with orientation and season. Cathode common potential can be held at a fixed potential with respect to spacecraft chassis ground by tying the electric propulsion system circuit ground to spacecraft ground with a resistor. Plasma currents collected by exposed spacecraft surfaces will flow through the resistor. These currents can be limited by reducing the exposed conducting area in the thruster plumes. The plasma currents are usually quite small. For example, if the charge-exchange plasma plume density 1 meter from the thruster axis isPDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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