The electrical power subsystem (EPS) of high-orbit satellites, including geosynchronous Earth orbit (GEO) satellites, have been designed to meet the requirements of power (4-6 kWe), lifetime (7-10 yr) and solar eclipse periods. Additional requirements imposed upon the EPS include fault-tolerant operation with autonomous control and fault correction. A description is given of overall design of such a satellite's EPS including its power source, power conditioning, control, distribution and energy storage equipment, and operational characteristics. Emphasis is placed on the fault-tolerance aspects of the design.
Electrical power system design of high orbit satellites
Auslegung von Stromversorgungssystemen für Satelliten mit hoher Umlaufbahn
1989
5 Seiten, 10 Quellen
Conference paper
English
Combined chemical/electrical orbit control system for advances communication satellites
Tema Archive | 1975
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