Micro-Satellite Electrical Power System Design

Abstract

Micro-Satellites with a total system mass below 50 kg must prioritise efficiency and reliability within all subsystems due to the minimal scope for inbuilt redundancies and non-essential equipment. By designing a Micro-Satellite Electrical Power System (EPS) that is highly efficient at generating, regulating, storing and distributing the power required by a satellite, the chance of successfully completing a complex space mission is improved. This paper discusses the preliminary design stages of an EPS tailored to meet the demands of the Micro-gravity Experiment Recovery Satellite (MERS) re-entry concept mission. This paper also discusses an EPS design solution that utilises commercial off the shelf (COTS) products tailored to the power profile of the craft. Utilising proven COTS products decreases the chance of failure in what is an already complex mission. A range of candidate orbital and craft configurations are discussed in order to increase the flexibility of the mission, outlining the effects these choices have on maximum peak power, the beta angle of the orbit and the overall ability of the EPS to handle the crafts power needs. The report culminates with an EPS preliminary design architecture that is capable of operating in a wide variety of orbits, primarily the 47 and 98 degree inclination orbit with a minimum solar panel surface area of 0.24m^2.