Speaker
Description
3U CubeSats typically achieve maximum power levels of around 30 W, having the on-board power generation capacity constrained by the surface area available for mounting solar panels. However, through advancements in the area of high-capacity batteries, some satellite platform developers provide solutions of up to one order of magnitude higher in payload power. But as the external surface area of the satellite remains constant, its thermal regulation capacity may not accommodate the increased heat dissipation required for maintaining it within nominal temperature limits. Our study explores the influence high-power payloads and their duty cycle have on a 3U CubeSat payload’s temperature profile. The results demonstrate that even short durations of payload activity can cause temperature spikes beyond operational values, calling for the implementation of thermal control methods. We then assess the satellite’s thermal response to common passive thermal control strategies by carrying out individual sensitivity analyses on their parameters, namely: (i) heat storages’ mass; (ii) external faces optical surface properties’ values; and (iii) thermal couplings’ values across components. The results demonstrate how the satellite’s temperature outputs are influenced by each distinct change brought to its thermal design, helping identify the most influential parameters, and facilitating a more informed decision-making regarding the parameters’ values in the design process.