A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites

Anwar Ali, Jijun Tong*, Haider Ali, Muhammad Rizwan Mughal, Leonardo M. Reyneri

*Corresponding author for this work

Research output: Contribution to journalArticleScientificpeer-review

5 Citations (Scopus)
46 Downloads (Pure)


In space thermal environment, satellites are exposed to multiple heat sources which can deteriorate structural and equipment integrity over long periods of time. Normally radiators are used to release heat, but due to space and weight constraints, it is impossible to mount radiators on small satellites. This problem signifies the importance of thermal analysis of a satellite in every development stage, such as design, manufacturing and testing. The ultimate goal of this work is to analyze a small spacecraft in space thermal environment by considering the effect of various heat sources. Thermal equilibrium equation is achieved which is applied to spacecraft with different shapes and dimensions and temperature is measured for a range of absorption co-efficient values (i.e. 0.5 similar to 0.9). Through an experimental setup a method is devised to measure the absorption co-efficient of small satellites that can be used for exact temperature measurement. Secondly, the paper presents a preliminary analysis of induced spin produced by small satellites due to asymmetrical colors (different absorptance) of satellite outer surface. The substantial contributors for induced spin are considered and the estimated spin is measured.

Original languageEnglish
Article number9160911
Pages (from-to)146196-146207
Number of pages12
JournalIEEE Access
Publication statusPublished - 1 Jan 2020
MoE publication typeA1 Journal article-refereed


  • absorption
  • Satellites
  • temperature
  • thermal analysis


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