On-orbit Thermal Analysis of CubeSat with CFRP Using Patterned Graphite Sheet and Stitching Method

Abstract

Satellites operate in a space thermal environment and can suffer from extreme temperature variations. To survive and perform missions within the mission period, a thermal control system must be applied. These thermal control systems quickly disperse heat and evenly distribute heat between components to keep the temperature of the satellite's internal components within the allowable temperature range. Aluminum, which is predominantly used in satellite frames for its excellent thermal conductivity, serves as an efficient thermal transfer path with advantageous thermal conductivity. However, its relatively high density increases the satellite's overall weight and makes it hard to meet the recent demand for miniaturization and weight reduction in artificial satellites. Alternatively, carbon fiber composites can potentially be used in the space environment, replacing aluminum to achieve weight reduction. However, such composites have relatively low thermal conductivity, making them unsuitable for use as a heat transfer path. In this study, to solve this problem, a carbon fiber composite material with improved thermal performance was produced using a patterned graphite sheet and stitching method, and thermal properties were measured. The implemented composite was applied to a solar panel of a 3U cube satellite model, which was designed using a Thermal Desktop, weighing approximately 3.7 kg. Orbital thermal analysis was performed with SINDA/FLUINT to analyze its thermal performance in space environments, and the analysis results were compared and analyzed. This study proposes a new carbon fiber composite material capable of weight reduction and effective heat control.