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Advances in series resonant inverter technology and its effect on spacecraft employing electric propulsionThe efficiency of transistorized Series Resonant Inverters (SRIs), which is higher than that of silicon-controlled rectifier alternatives, reduces spacecraft radiator requirements by 40% and may eliminate the need for heat pipes on 30-cm ion thruster systems. Recently developed 10- and 25-kW inverters have potential applications in gas thrusters, and represent the first spaceborne SRI designs for such power levels. Attention is given to the design and control system approaches employed in these inverter designs to improve efficiency and reduce weight, along with the impact of such improved parameters on electric propulsion systems.
Document ID
19830031248
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Robson, R. R.
(Hughes Research Laboratories Malibu, CA, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1982
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1881
Meeting Information
Meeting: Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference
Location: New Orleans, LA
Start Date: November 17, 1982
End Date: November 19, 1982
Sponsors: AIAA
Accession Number
83A12466
Funding Number(s)
CONTRACT_GRANT: NAS3-22471
CONTRACT_GRANT: NAS3-23159
Distribution Limits
Public
Copyright
Other

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