Design of Electrical Power Systems for Satellites

Abstract

An integral subsystem of a satellite is its Electrical Power System (EPS). Spacecraft power systems have undergone significant new developments in the last decade and will continue to do so even at a faster rate in the current decade. The EPS functions to supply continuous power during the satellite mission life, control and distribute power, support power requirements for peak and average electrical load, and protect payload operations against failures within the EPS. The design of the solar panels and batteries depends on the payload/s power demand and the mission lifetime. This paper studies the design, management and characteristics of the power subsystem of small satellites. The EPS for small satellites is required to have high efficiencies and low masses because of volume and weight constraints. Based on the power utilized by onboard equipment and devices, this paper proposes an efficient and durable power system.