DocumentCode :
2207156
Title :
Extending ion engine technology to NEXT and beyond
Author :
Domonkos, M.T. ; Patterson, M.J. ; Foster, J.E. ; Rawlin, V.K. ; Soulas, G.C. ; Sovey, J.S. ; Kovaleski, S.D. ; Roman, R.F. ; Williams, G.J., Jr.
Author_Institution :
NASA John H. Glenn Res. Center, Cleveland, OH, USA
fYear :
2002
fDate :
26-30 May 2002
Firstpage :
173
Abstract :
Summary form only given. Extending ion engine technology beyond the current state-of-the-art primary interplanetary electric propulsion system, the 2.3-kW NASA Solar Electric Propulsion Technology and Applications Readiness (NSTAR) system, will require thrusters with improved propellant throughput and total impulse capability. Many of the design choices that culminated in the NSTAR thrusters must be revisited, and their application to next generation ion engine technology must be evaluated. The concept of derating, which was successfully employed in NSTAR, has been applied to the 40cm NASA Evolutionary Xenon Thruster (NEXT) currently under development at NASA Glenn Research Center (GRC). At 5-kW, NEXT operates with the same average beam current density as NSTAR, and at 10-kW, the peak beam current density is only ten percent greater than NSTAR. The result is that similar ion optics technology is expected to yield comparable lifetimes. Thick-accelerator-grid ion optics are also being tested to realize additional lifetime benefits. A 40-A discharge cathode is being developed for NEXT based on scaling the NSTAR design. Nevertheless, the experiences of the NSTAR ground tests and the thruster on the Deep Space One spacecraft indicate that the discharge cathode wear must be studied experimentally and theoretically to ensure that it meets the lifetime requirements. Although NEXT is in its infancy, investigations have already begun to examine possible modifications to engine design for even higher-power and higher-specific impulse engines. Ion optics using alternate materials such as titanium, graphite, or carbon-carbon composite are currently being investigated due to their low sputter yields at high voltage.
Keywords :
aerospace engines; aerospace propulsion; current density; electric propulsion; ion engines; ion optics; space vehicles; 10 kW; 2.3 kW; 40 A; 40 cm; 5 kW; C-C composite; Deep Space One spacecraft; NASA Evolutionary Xenon Thruster; NASA Glenn Research Center; NASA Solar Electric Propulsion Technology and Applications Readiness system; NEXT; NSTAR; NSTAR design; NSTAR ground tests; NSTAR thrusters; Ti; Xe; alternative propellants; average beam current density; derating; design choices; discharge cathode; discharge cathode wear; engine design; graphite; high-power engines; high-power ion thruster systems; impulse engines; ion engine technology; ion optics; ion thruster technology; lifetime benefits; lifetime requirements; microwave-based ion thruster; next generation ion engine technology; peak beam current density; power handling capabilities; primary interplanetary electric propulsion system; propellant; state-of-the-art; testing requirements; thick-accelerator-grid ion optics; thrusters; total impulse capability; Cathodes; Current density; Engines; Life testing; NASA; Particle beam optics; Propulsion; Space technology; Throughput; Xenon;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Plasma Science, 2002. ICOPS 2002. IEEE Conference Record - Abstracts. The 29th IEEE International Conference on
Conference_Location :
Banff, Alberta, Canada
Print_ISBN :
0-7803-7407-X
Type :
conf
DOI :
10.1109/PLASMA.2002.1030383
Filename :
1030383
Link To Document :
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