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Extended performance solar electric propulsion thrust system designA thrust system design has been established for an extended performance technology, 6.4 kW, 4800 sec specific impulse ion thruster. The configuration is comprised of ten thrusters configured with a power management and control subsystem in a modular thrust system design. The system design approach is an adaptation of that previously established for the baseline technology 2.7 kW, 3000 sec specific impulse ion thruster. The power management and control subsystem design includes a combination of individual electronics for each thruster and a set of electronics with redundancy that are common to all thrusters. The thermal dissipation from all electronics is removed with a common heat pipe/radiator assembly.
Document ID
19780053521
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cake, J. E.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Hawthorne, E. I.
(Hughes Aircraft Co., Space and Communications Group, Los Angeles Calif., United States)
Poeschel, R. L.
(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 78-643
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
78A37430
Funding Number(s)
CONTRACT_GRANT: NAS3-20395
Distribution Limits
Public
Copyright
Other

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