Preliminary Design Electronic Power System (EPS) Low Earth Orbit (LEO) Communication Microsatellite

Abstract

The development of satellite technology provides great benefits in various fields, one of which is eliminating the distance limit in communication between human beings inside the hemisphere. Satellite technology's role is not simple in the telecommunications sector, in almost all fields such as the defense, marine, plantation, and agriculture sectors. Electronic Power System (EPS) is a crucial part of a satellite system that can generate, store and distribute power to all satellite electronic devices. If the EPS fails, the power supply to all electronic devices in the satellite device may be disrupted and result in a loss of mission. This paper describes the preliminary design of EPS for LEO micro-communication satellites based on basic satellite-level parameters such as orbital altitude, orbital slope, mission operation, and mission duration. The results of this study are an EPS for satellites with 28 V bus voltage, which distributes current and voltage on each channel used at 3.3 V, 5 V, and 12 V and can control the current and voltage when overloaded. This EPS also provides a minimum of 4 Automatic Fuses (AF), a minimum of 13 Fuses (FS), and a minimum of 25 switches (S) to control each device in the satellite system.