3. Design and implementation of electrical power system for ISRA1cube sattelite

Author: Moutaman Mirghani*, Mohammed Bek Omar Elssadig and Hind Mahmoud Elhaj


Cube satellites are miniaturized nanosatellites that are used as educational and scientific platforms. CubeSats are of about a liter size and launched to low Earth orbits of hundreds of kilometers altitude. The Electrical Power System (EPS) of a cube satellite is responsible for providing the adequate electric voltages and currents to the different subsystems onboard. The primary source of power is the Sunlight that energizes solar cells to generate electric current used to charge the onboard batteries. The main electrical power source for a satellite are the solar panels that collect the sunlight and transform it to electricity, which is stored in the onboard batteries. Because of the motion of the satellite along its orbit, the direction of the solar panels towards the Sun varies continuously and hence the voltage generated is varying accordingly. A critical factor that limits the useful lifetime of a satellite is the battery lifetime. For longer battery lifetime, the charging current should be precisely controlled. EPS is in charge to regulate the batteries charging currents as well as the diverse voltages required by all subsystems and protect them from over voltages and currents. A big challenge for EPS of a cube satellite is the limitation of the size and mass of the components used to implement it. Other challenges facing design of EPS for CubeSat is the limitation of power budget. In this paper, the design and implementation of the EPS of ISRASAT1 cube satellite will be highlighted, summarizing work done by the EPS research team and the satisfying results of 4.66 W total power that were achieved by this design and implementation.

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