A regulated high voltage solar array/battery system using large area silicon solar cells and a group of Ni-H energy storage cells meets the requirements of a multikilowatt geosynchronous orbit application. The electrical power bus operates at approximately 50 Vdc, minimizing unbalanced magnetic torques and distribution harness weight. The program design goal of 12 years of operation on station, including up to 2 years of orbital storage, represents a significant extension of total mission life.
An Electrical Power System for a Mobile Communications Spacecraft
Sae Technical Papers
27th Intersociety Energy Conversion Engineering Conference (1992) ; 1992
1992-08-03
Aufsatz (Konferenz)
Englisch
SERT 2 spacecraft electrical power system
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