Fundamentals of Electric Propulsion: Ion and Hall Thrusters

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Fundamentals of Electric Propulsion: Ion and Hall Thrusters ( fundamentals-electric-propulsion-ion-and-hall-thrusters )

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Chapter 9 Flight Ion and Hall Thrusters 9.1 Introduction Ion and Hall thruster technology development programs continue to improve the performance of these engines. However, it is worthwhile to survey the state- of-the-art thrusters that have been flown to date. In this brief look, we are covering modern thrusters that have flown in the last ten to fifteen years in satellite station-keeping and spacecraft prime-propulsion applications. These thrusters are ion thruster and Hall thruster systems that use xenon as the propellant. The parameters given for the thrusters include the neutralizer or external cathode flow rates, since that is required for flight operation on satellites and spacecraft. 9.2 Ion Thrusters The first of the modern ion thrusters flown were intended for station-keeping applications on geosynchronous satellites and developed by Mitsubishi Electric Corporation (MELCO) for use on the Japanese “Engineering Test Satellite (ETS-6)” in 1994 [1,2]. These 13-cm Kaufman thrusters produced nominally 20 mN of thrust at an Isp of about 2400 s. Despite launch vehicle problems that caused the satellite to fail to reach its planned orbit, the thrusters were successfully operated in orbit. The same electric propulsion subsystem was launched on the COMETS satellite in 1996, which also failed to reach its planned orbit. Development of Kaufman ion thrusters for communications satellite station-keeping applications is continuing at MELCO. The first successful use of ion thrusters in commercial station keeping applications was the Hughes 13-cm Xenon Ion Propulsion System (XIPS) [3,4], which was launched into orbit in 1997 on the Hughes PAS-5 satellite. The XIPS system utilizes two fully redundant subsystems, each consisting of two thrusters, a power supply, and a xenon gas supply. The performance parameters 429

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