The 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.
Advances in series resonant inverter technology and its effect on spacecraft employing electric propulsion
Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference ; 1982 ; New Orleans, LA
1982-11-01
Conference paper
No indication
English
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