NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
High Voltage SPT PerformanceA 2.3 kW stationary plasma thruster designed to operate at high voltage was tested at discharge voltages between 300 and 1250 V. Discharge specific impulses between 1600 and 3700 sec were demonstrated with thrust between 40 and 145 mN. Test data indicated that discharge voltage can be optimized for maximum discharge efficiency. The optimum discharge voltage was between 500 and 700 V for the various anode mass flow rates considered. The effect of operating voltage on optimal magnet field strength was investigated. The effect of cathode flow rate on thruster efficiency was considered for an 800 V discharge.
Document ID
20020012540
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Manzella, David (Toledo Univ. OH United States)
Jacobson, David (NASA Glenn Research Center Cleveland, OH United States)
Jankovsky, Robert (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
November 1, 2001
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-12983
NASA/TM-2001-211135
NAS 1.15:211135
AIAA Paper 2001-3774
Report Number: E-12983
Report Number: NASA/TM-2001-211135
Report Number: NAS 1.15:211135
Report Number: AIAA Paper 2001-3774
Meeting Information
Meeting: 37th Joint Propulsion Conference and Exhibit
Location: Salt Lake City, UT
Country: United States
Start Date: July 8, 2001
End Date: July 11, 2001
Sponsors: American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc., American Society of Mechanical Engineers, American Inst. of Chemical Engineers
Funding Number(s)
PROJECT: RTOP 755-B4-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available