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434 Chapter 9 is completed, each of the four thrusters is fired once daily for an average of about 45 minutes in a “low power,” 2.3-kW mode for station keeping. In this mode, the beam voltage is kept the same, and the discharge current and gas flow are reduced to generate a 1.2-kV, 1.5-A beam that produces nominally 79 mN of thrust at an Isp of 3400 s. The thruster performance parameters are shown in Table 9-3. Recently, tests by the manufacturer L-3 Communications Electron Technologies Inc. have demonstrated that the XIPS engine and PPU can be throttled from a PPU input power level of 400 W to over 5 kW. Over this range, the performance significantly exceeds the NSTAR thruster performance [11]. The next flight of ion thrusters was on the European Space Agency Artemis spacecraft launched in 2001. Artemis carried four ion thruster assemblies, two EITA (Electron-bombardment Ion Thruster Assembly) systems manufactured by Astrium UK, and two RITA (Radio-frequency Ion Thruster Assembly) systems developed by Astrium Germany. The EITA system, also called the UK-10 system, used copies of the T5 thruster [12,13], and the RITA system used RIT-10 ion thrusters [14,15]. Artemis was intended to be launched into a geosynchronous orbit, but a malfunction of the launcher’s upper stage placed the satellite into a lower orbit. The ion thrusters were used in an unplanned orbit-raising role to rescue the spacecraft from the lower 31,000-km parking orbit and raise the spacecraft to the proper geosynchronous orbit. The thrusters then successfully performed standard EP station keeping activities. The EITA/UK-10/T5 thruster is a 10-cm Kaufman thruster [13] presently manufactured by Qinetiq in England. The performance of the T5 Kaufman Parameter Active grid diameter (cm) Thruster input power (kW) Average Isp (s) Thrust (mN) Total efficiency (%) Mass utilization efficiency (%) Electrical efficiency (%) Beam voltage (V) Beam current (A) Low-Power Station Keeping 25 2 3420 80 67 80 87 1215 1.45 High-Power Orbit Raising 25 4.3 3550 166 68.8 82.5 87.5 1215 3.05 Table 9-3. 25-cm XIPS performance parameters.PDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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