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Preliminary tests of the electrostatic plasma acceleratorThis report describes the results of a program to verify an electrostatic plasma acceleration concept and to identify those parameters most important in optimizing an Electrostatic Plasma Accelerator (EPA) thruster based upon this thrust mechanism. Preliminary performance measurements of thrust, specific impulse and efficiency were obtained using a unique plasma exhaust momentum probe. Reliable EPA thruster operation was achieved using one power supply.
Document ID
19960011787
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Aston, G.
(Electric Propulsion Lab., Inc. Tehachapi, CA, United States)
Acker, T.
(Electric Propulsion Lab., Inc. Tehachapi, CA, United States)
Date Acquired
August 17, 2013
Publication Date
November 2, 1990
Publication Information
Publication: Center for Advanced Space Propulsion, Tullahoma, TN, Center for Advanced Space Propulsion Second Annual Technical Symposium Proceedings
Subject Category
Spacecraft Propulsion And Power
Accession Number
96N70672
Funding Number(s)
CONTRACT_GRANT: CAR/EPL 89-01
Distribution Limits
Public
Copyright
Public Use Permitted.
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