Battery tied bus being the simplest power system configurations, has been selected for its minimal complexity.
A lithium ion battery in 2S2P configuration, with a nominal voltage of 7.4V and 5.2Ah capacity is used to meet the energy storage requirements of the satellite. Battery decides the operating point of the solar array.
Solar array generates on an average 11 W of power. Load end converters are used to provide the regulated power for various subsystems of the spacecraft.
The enable / disable function of the DC DCs are used to meet the under voltage protection of the battery. Built-in soft start circuitry is enabled to reduce the start – up current to avoid loading of solar panels.
Two numbers of 8.7V, 5W, low leakage current zeners in parallel provides the overvoltage protection for the battery.