Design and implementation of the electrical power subsystem for a small satellite

Abstract

Design, implementation and test of a small satellite electrical power subsystem is purposed in this paper. This subsystem has been designed for the orbital status of its mission at 375 Km apogee and 250 Km perigee and 40 days of lifetime. It includes GaAs solar panels with 28 percent efficiency to obtain solar energy as power resource. Also a 6.4 Ah Li-ion battery pack has been used as power storage. The power control unit consists of five electronic boards including battery charger board, two DC-DC power converter boards and a power distribution board which are installed in the EBOX. All ECSS environmental tests have been accomplished at Iranian Space Research Institute of Iran for the implemented electrical power subsystem components and integrated in the satellite. The satellite is in the waiting list for launch.