CubeSat thermal analysis: evaluating models for thermal contact conductance

Abstract

In thermal design of space applications, calculating thermal contact conductance present a challenge. The absence of convective heat transfer necessitates the essential requirement for a comprehensive of thermal contact conductance and the pivotal physical factors that influence it. This article explores a thermal management for 3U CubeSat in LEO. It covers the space thermal environment, thermal analysis methodology, and the determination of thermal contact conductance using both elastic and plastic models. The study also outlines CubeSat design considerations and the assumptions made for simulations using Comsol Multiphysics software. Experimental results from thermal balance tests are presented and compared to simulations results. The research concludes that the CMY method is the best suited for CubeSat applications to identify the thermal contact conductance, but notes the need for further refinement when dealing with materials that have high roughness or less-than-ideal contact conditions.