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Pulse ignition characterization of mercury ion thruster hollow cathode using an improved pulse ignitorAn investigation of the high voltage pulse ignition characteristics of the 8 cm mercury ion thruster neutralizer cathode identified a low rate of voltage rise and long pulse duration as desirable factors for reliable cathode starting. Cathode starting breakdown voltages were measured over a range of mercury flow rates and tip heater powers for pulses with five different rates of voltage rise. Breakdown voltage requirements for the fastest rising pulse (2.5 to 3.0 kV/micro sec) were substantially higher (2 kV or more) than for the slowest rising pulse (0.3 to 0.5 kV/micro sec) for the same starting conditions. Also described is an improved, low impedance pulse ignitor circuit which reduces power losses and eliminates problems with control and packaging associated with earlier designs.
Document ID
19780013260
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wintucky, E. G.
(NASA Lewis Research Center Cleveland, OH, United States)
Gruber, R. P.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-78858
E-9592
Meeting Information
Meeting: Intern. Elec. Propulsion Conf.
Location: San Diego, CA
Country: United States
Start Date: April 25, 1978
End Date: April 27, 1978
Sponsors: AIAA, DGLR
Accession Number
78N21203
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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