Satellite control mercury ion thrusterProgram status is reviewed for development of an 8-cm structurally integrated ion thruster for application to attitude control and stationkeeping of synchronous satellites. The system is designed to achieve a thrust level of 1 and 2 mlb at a beam voltage of 1200 V, a propellant-utilization efficiency of 85%, and electrical efficiency of 75%. Thrust vectoring will be implemented by a dished-gird roll misalignment system. Design features are incorporated which ensure thruster life of 20,000 hours, with 10,000 thruster-start cycles and 100,000 beam-deflection cycles.
Document ID
19740029500
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hyman, J., Jr.
Poeschel, R. L. (Hughes Research Laboratories Malibu, Calif., United States)
Date Acquired
August 7, 2013
Publication Date
October 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
AIAA PAPER 73-1132
Meeting Information
Meeting: Electric Propulsion Conference
Location: Lake Tahoe, NV
Start Date: October 31, 1973
End Date: November 2, 1973
Sponsors: American Institute of Aeronautics and Astronautics