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Performance Evaluation of a 50kW Hall ThrusterAn experimental investigation was conducted on a laboratory model Hall thruster designed to operate at power levels up to 50 kW. During this investigation the engine's performance was characterized over a range of discharge currents from 10 to 36 A and a range of discharge voltages from 200 to 800 V Operating on the Russian cathode a maximum thrust of 966 mN was measured at 35.6 A and 713.0 V. This corresponded to a specific impulse of 3325 s and an efficiency of 62%. The maximum power the engine was operated at was 25 kW. Additional testing was conducted using a NASA cathode designed for higher current operation. During this testing, thrust over 1 N was measured at 40.2 A and 548.9 V. Several issues related to operation of Hall thrusters at these high powers were encountered.
Document ID
20000021551
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Jacobson, David T.
(DYNACS Engineering Co., Inc. Brook Park, OH United States)
Jankovsky, Robert S.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 1999
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA Paper 99-0457
NAS 1.15:209447
NASA/TM-1999-209447
E-11939
Meeting Information
Meeting: 37th Aerospace Sciences Meeting
Location: Reno, NV
Country: United States
Start Date: January 11, 1999
End Date: January 19, 1999
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 632-1B-1B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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