The requirements for auxiliary and primary propulsion systems were investigated in order to define the requirements for the field emission electric propulsion power conditioning unit (PCU). Emphasis was placed on simplifying the PCU design and improving weight. The PCU consists of a central power and control module (CPCM) connected to several thruster dedicated power supply modules (TDPDM). The connections between the CPCM and the TDPDM the command and control philosophy, and the power cmponents and power circuits are considered. The use of high inverter frequencies and optical fiber data transmission to aleviate high voltage insulation problems are addressed.
Field Emission Electric Propulsion Power Conditioning Unit Design Concept, Volume 1
1981
183 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Unmanned Spacecraft , Field emission , Ion propulsion , Power conditioning , Power modules (Sts) , Spacecraft power supplies , Command and control , Data links , Fiber optics , Optical relay systems , Satellite attitude control , Stationkeeping , Temperature control , Foreign technology
Measurement of the Microthrust of the Field Emission Electric Propulsion Unit
British Library Conference Proceedings | 1997
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