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416 Chapter 8 1.0 μm −1.0 −3.0 −5.0 −7.0 −9.0 Fig. 8-14. Contours of the erosion (negative numbers) and deposition depths (positive numbers) due to sputtering during operation of the SPT-100 Hall thruster onboard the Express-A spacecraft. The calculation was performed with EPIC [6]. Chapter 6, the sheath drop internal to a hollow cathode and orifice resistive heating produce energetic electrons that ionize the propellant gas and generate plasma. The combined insert and orifice potential drops are typically between 10 and 15 V, causing the external plasma to be about the same value above cathode common, as illustrated in Fig. 8-15. The hollow cathode–generated plasma has an electron temperature of about 2 eV, typical of many laboratory plasmas. The spacecraft acts as a Langmuir probe in the thruster plume plasma and will float to a potential where the ion and electron currents from the plasma cancel. As discussed in Chapter 3, plasma electron velocities are much higher than ion velocities, so current balance is achieved by repelling most of the plasma electrons. This balance occurs when the surface is a few times the electron temperature negative of the local plasma potential. If the electric propulsion system were isolated from spacecraft ground by a very high impedance, cathode common would float around 10 V negative with respect to spacecraft ground, as illustrated in Fig. 8-16. When the spacecraft has exposed surfaces at different voltages, predicting the cathode common floating potential is more difficult. An extreme case would be if the spacecraft solar arrays had a large area at high positive voltage immersed in the thruster plume. Then, to achieve current balance, the high-voltage area would be close in potential to the thruster plume plasma. For example, assume that the spacecraft had 100-V solar arrays. Since the cathode common is onlyPDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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