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The paper describes a computational program developed in MatLab Simulink, that performs calculation of electric power generated by photoconverters for various missions of nanosatellites in low Earth orbit (LEO). Electric power generated by nanosatellite’s solar panels was estimated for polar LEO of 450 km altitude for two versions of the satellite’s static orientation. The results show how orientation maneuver at the Earth’s surface point affects power generated by the satellite’s solar panels.

Calculating electric power generated by 3U CubeSat’s photoconverters depending the orbit and orientation parameters