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Engineering Model 8-cm Thruster SystemDevelopment of an Engineering Model 8-cm Mercury Ion Thruster System for Satellite Control has been successfully completed. This system operates at a specific impulse in excess of 2600 sec, produces a thrust of 5 mN with a total input power of 165 W; it has a dry mass of 16.6 kg and a mercury-propellant-reservoir capacity of 8.75 kg. This paper summarizes the development work, the system characteristics and performance, and the testing undertaken to verify the design.
Document ID
19780053525
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Herron, B. G. (Hughes Aircraft Co., Technology Div., El Segundo Calif., United States)
Hyman, J., Jr. (Hughes Aircraft Co. El Segundo, CA, United States)
Hopper, D. J. (Hughes Aircraft Co. El Segundo, CA, United States)
Williamson, W. S. (Hughes Aircraft Co. El Segundo, CA, United States)
Dulgeroff, C. R. (Hughes Aircraft Co. El Segundo, CA, United States)
Collett, C. R. (Hughes Research Laboratories Malibu, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
April 1, 1978
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 78-646
Report Number: AIAA PAPER 78-646
Meeting Information
Meeting: International Electric Propulsion Conference
Location: San Diego, CA
Country: US
Start Date: April 25, 1978
End Date: April 27, 1978
Sponsors: Deutsche Gesellschaft fuer Luft- und Raumfahrt, American Institute of Aeronautics and Astronautics
Accession Number
78A37434
Funding Number(s)
CONTRACT_GRANT: NAS3-18917
CONTRACT_GRANT: NAS3-21023
Distribution Limits
Public
Copyright
Other

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