ESEO satellite thermal model design analysis and validation of thermal solutions

Document Type : Original Article

Authors

1 M.Sc., Space Technology Center, Cairo, Egypt.

2 PhD., Astronautics Engineering Department, Military Technical College, Egypt.

10.1088/1742-6596/3070/1/012023

Abstract

This paper focuses on the analysis and investigating the design of thermal control subsystem for a small satellite operating in low Earth orbit (LEO). The European Student Earth Orbiter (ESEO) satellite was selected as the subject of this study. The primary goal of the thermal control subsystem is to guarantee the proper operation against the hard conditions of environment in space. The goal is to certify that the maximum and minimum temperatures of the panel’s lower sheet remain within the specified design range. Thermal analysis was implemented using commercially available tools. The comparison between the results showed that maximum Hot Case (1) temperature difference is 2.12 ℃ in panel (3), maximum Hot Case (2) temperature difference is 2.61 ℃ AMSAT. maximum cold Case (3) temperature difference is 1.68 ℃ in SOLAR PANEL (+Z). maximum cold Case (4) temperature difference is 2.05 ℃ in SOLAR PANEL (+X).

Keywords

International Conference on Aerospace Sciences and Aviation Technology
Volume 21, Issue 21
21st International Conference on Aerospace Sciences & Aviation Technology, ASAT 21, 2025.
September 2025
Pages 1-20

Files

Share

How to cite

Statistics