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Hollow Cathodes 297 employs a stepper-motor-driven sapphire fiber-optic probe that is scanned along the insert inside diameter and collects the light radiated by the insert surface. Ratio pyrometry is used to determine the axial temperature profile of the insert from the fiber-optic probe data. Thermocouples attached on the outside of the cathode on the orifice plate provide additional temperature data during operation and are used to calibrate the pyrometer system in situ with a small oven inserted over the cathode to equilibrate the temperature. Figure 6-41 shows temperature profiles measured for a nominal Space Station Contactor (SSC) cathode [50] operating at four different discharge currents. The peak temperature of the insert at the full 12-A current level is about 1200 ̊C. The insert also has approximately a 10% to 15% temperature gradient along its length. The change in the insert temperature with the xenon flow rate for the cathode producing 12 A of discharge current is shown in Fig. 6-42. High flow rates through the cathode reduce the insert temperature, although the effect is small. A direct comparison of the insert temperature profile for the NSTAR discharge cathode and the SSC cathode at identical discharge currents of 12 A and xenon flow rates of 6 sccm is shown in Fig. 6-43. The NSTAR insert temperature is higher than the SSC all along the insert. It also appears that the temperatures of the inserts tend to converge near the orifice plate. The high insert temperature for the NSTAR cathode is likely because the plasma contact area is significantly larger at the roughly 50% lower internal pressure as compared with the SSC. In addition, thermocouple measurements on the orifice plate show that the smaller-diameter SSC orifice plate is significantly hotter than the NSTAR orifice plate, consistent with orifice heating effects described in Section 6.5 for smaller orifice diameters. Fig. 6-41. Insert temperature profile measured for a SSC hollow cathode for several different discharge currents (from [50]).PDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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