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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Flight Ion and Hall Thrusters 431 Fig. 9-2. Photograph of the 13-cm XIPS ion thruster (photo courtesy of L-3 Communications, Electron Technologies, Inc.). diameter of 28.6 cm. NSTAR was developed and manufactured by a team of NASA GRC, JPL and Hughes/Boeing and launched in 1998 on the Deep Space 1 spacecraft. This ion engine has arguably been the most analyzed and tested ion thruster in history, with over 16,000 hours of operation in space, over 40,000 hours of life testing, and hundreds of papers published on its design and performance. NSTAR was operated over a wide throttle range in the DS1 application from a minimum input power to the power processing unit (PPU) of 580 W to a maximum power of over 2550 W. The Extended Life Test of this thruster at JPL demonstrated 30,252 hours of operation distributed across several of the throttle levels and was terminated with the engine still running in order to provide life status and data for the subsequent DAWN mission [7]. The throttle table used on DS1 with parameters for the NSTAR thruster from a review by Brophy [6] is shown in Table 9-2. A photograph of the NSTAR engine manufactured by L-3 Communications, Electron Technologies, Inc. is shown in Fig. 9-3. The next ion thruster technology launched was designed for both orbit raising and station keeping applications on a commercial communications satellite. The 25-cm XIPS thruster was first launched in 1999 on a Hughes/Boeing 702 satellite. Although the 25-cm XIPS ion thruster was developed [9] at Hughes Research Laboratories in the same time frame as the NSTAR engine and has a similar basic design as the 13-cm XIPS shown in Fig. 9-1, the 25-cm thruster entered production after the 13-cm version and incorporated sufficient

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