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Eight cm technology thruster developmentA structural integrated ion thruster with 8-cm beam diameter (SIT-8) was developed for attitude control and stationkeeping of synchronous satellites. As optimized, the system demonstrates a thrust T=1.14 mlb (not corrected for beam V sub B = 1200 V (I sub sp = 2200 sec) total propellant utilization efficiency nu sub u = 59.8% (is approximately 72% without auxiliary pulse-igniter electrode), and electrical efficiency n sub E 61.9%. The thruster incorporates a wire-mesh anode and tantalum cover surfaces to control discharge chamber flake formation and employs an auxiliary pulse-igniter electrode for hollow-cathode ignition. When the SIT-8 is integrated with the compatible SIT-5 propellant tankage, the system envelope is 35 cm long by 13 cm flange bolt circle with a mass of 9.8 kg including 6.8 kg of mercury propellant. Two thrust vectoring systems which generate beam deflections in two orthogonal directions were also developed under the program and tested with the 8-cm thruster. One system vectors the beam over + or - 10 degrees by gimbaling of the entire thruster (not including tankage), while the other system vectors the beam over + or - 7 degrees by translating the accel electrode relative to the screen electrode.
Document ID
19740025114
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hyman, J., Jr. (Hughes Research Labs. Malibu, CA, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-134685
Accession Number
74N33227
Funding Number(s)
CONTRACT_GRANT: NAS3-17791
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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