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Abstract ▼ AI-Helper

The major goal of this research is to use as a baseline guide for a flight model design of power system of next domestic communication satellite. For this purpose, the EPS(Electrical Power Subsystem) is designed to compliance performance requirements specified in EPS subsystem specification during a...

The major goal of this research is to use as a baseline guide for a flight model design of power system of next domestic communication satellite. For this purpose, the EPS(Electrical Power Subsystem) is designed to compliance performance requirements specified in EPS subsystem specification during all expected spacecraft operations. The regulated electrical power bus gives 42.5V to the various spacecraft loads from PCDU(Power Control & Distribution Unit) and the solar arrays are composed of 6 panel, each panel has 3 circuits including 7 string. The battery system is comprised of two batteries consisting of 26 IPV(Individual-Pressure-Vessel) NiH2 cells. Each battery can be capable of delivering 2878Watt-hours at a 80% maximum DOD(Depth of Discharge) based on the nameplate capacity of 150 amper-hours.

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