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Conceptual Design of the Nuclear Electronic Xenon Ion System (NEXIS)In support of the NEXIS program, Aerojet-Redmond Operations, with review and input from the JPL and Boeing, has completed the design for a development model (DM) discharge chamber assembly and main discharge cathode assembly. These efforts along with the work by JPL to develop the carbon-carbon-composite ion optics assembly have resulted in a complete ion engine design. The goal of the NEXIS program is to significantly advance the current state of the art by developing an ion engine capable of operating at an input power of 20kW, an Isp of 7500 sec and have a total xenon through put capability of 2000 kg. In this paper we will describe the methodology used to design the discharge chamber and cathode assemblies and describe the resulting final design. Specifics will include the concepts used for the mounting of the ion optics along with the concepts used for the gimbal mounts. In addition, we will present results of a vibrational analysis showing how the engine will respond to a typical Delta IV heavy vibration spectrum.
Document ID
20110015989
Acquisition Source
Jet Propulsion Laboratory
Document Type
Conference Paper
External Source(s)
Authors
Monheiser, Jeff
(Aerojet-General Corp. Redmond, WA, United States)
Polk, Jay
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Randolph, Tom
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
August 25, 2013
Publication Date
July 12, 2004
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA Paper 2004-3264
Meeting Information
Meeting: Joint Propulsion Conference
Location: Fort Lauderale, FL
Country: United States
Start Date: July 12, 2004
End Date: July 14, 2004
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other
Keywords
ion truster

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