Electrical Power System (EPS) is an important component of a satellite. The design and implementation of EPS to cater to the power demand of all the subsystems of the satellite is a challenging task. This work details the design and simulation of an efficient Electrical Power System for a 3U CubeSat. The objective is to build and launch a student satellite in Low Earth Orbit and perform on-orbit operations to demonstrate the imaging of the Earth’s surface, high altitude operations, and de-orbiting maneuver. The EPS was designed taking into consideration the power requirement from all the subsystems of the satellite. The system design includes a battery tied bus consisting of surface mounted and deployable solar panels, Lithium-ion batteries with over-voltage and under-voltage control. The EPS also involves the design of a highly efficient controllable power distribution system consisting DC–DC Converters which are capable to provide 3.3 V and 5 V regulated DC supply as well as unregulated supply.


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