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Flight Ion and Hall Thrusters 435 thruster in station keeping applications [13] is shown in Table 9-4. A schematic of a generic Kaufman thruster was shown in Chapter 4, and a photograph of the T5 thruster is shown in Fig. 9-5. The T5 thruster generates an 1100-V, 0.329-A xenon ion beam that produces about 18 mN of thrust at a nominal Isp of 3200 s with a total efficiency of about 55%. The RITA system uses a RIT-10 rf ion thruster originally developed [14] at the University of Giessen in Germany and manufactured [15] for Artemis by Astrium in Germany. The performance of the RIT-10 thruster in the station keeping application [15] is shown in Table 9-5. A schematic of a generic rf thruster was shown in Chapter 4, and a photograph of the RIT-10 rf ion thruster from [16] is shown in Fig.9-6. The RIT-10 thruster generates a 1500-V, 0.234-A xenon ion beam that produces 15 mN of thrust at an Isp of 3400 s and a total efficiency in excess of 51%. The Institute of Space and Astronautical Science of the Japan Aerospace Exploration Agency (JAXA) launched four of the 10 ECR ion thrusters on the Hayabusa (formerly Muses-C) spacecraft [17] in 2003. These 10-cm grid- diameter thrusters are successfully providing primary propulsion for an asteroid sample return mission that will return to Earth in 2010. The thruster [18,19] uses 4.2-GHz microwaves to produce the main plasma in the thruster and drive the electron neutralizer. A schematic drawing of the thruster was shown in Chapter 4. The performance of the 10-cm ECR thruster is shown in Table 9-6, and a photograph of the thruster from Ref. 20 is shown in Fig. 9-7. The 10-cm ECR ion thruster generates a 1500-V, 0.136-A xenon ion beam that produces 8.1 mN of thrust at an Isp of 3090 s and a total efficiency of 36%. The most recent launch of a new ion thruster was by the Japan Aerospace Exploration Agency (JAXA), who launched four 20mN-class Kaufman ion thrusters developed by Mitsubishi Electric Corporation on the Engineering Test Satellite VIII (ETS-VIII) [21] in 2006. The 12-cm grid-diameter Kaufman thrusters provide north-south station keeping for this large geosynchronous communications satellite. The performance of the 12-cm Kaufman thruster [22] is shown in Table 9-7, and a photograph of the thruster from [23] is shown in Figure 9-8. At its nominal operating condition, the thruster generates a 996-V, 0.432 to 0.480-A xenon ion beam that produces 20.9 to 23.2 mN of thrust at an Isp of 2402 to 2665 sec and a total efficiency of about 46 to 50%. There are a significant number of new ion thrusters in development world-wide for prime propulsion and satellite station keeping applications. Since these thrusters have not flown as of this date, they will not be covered in detail and only mentioned here. NASA Glenn Research Center (GRC) is leading thePDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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