A Thermal solution proposal for small satellites

Abstract

This article presents the design of a suitable Thermal Control solution for nanosatellites’ and microsatellites’ external surfaces and onboard equipment. Each of the designed components and the analysis that have been made is shown throughout the report. In addition, orbital Mechanics concepts are introduced. Finally, the author’s proposal is explained to be implemented in a CubeSat satellite, characterized by its low manufacturing cost, simple construction and reduced development time.