Abstract In this paper, we present the process and the results of the thermal analysis applied to a nanosatellite developed at Politecnico di Torino. First, main mission parameters and the spacecraft design are presented, in order to fix the boundary conditions and the thermal environment used for the analysis. Then, the thermal model built to solve the thermal balance problem is described into details, and the numerical simulation code is presented. Finally, results are given and discussed in depth. The tool developed provides excellent modelling capabilities and temperature distributions have been validated through commercial software. The analysis has been used to refine the spacecraft configuration and to set the requirements applicable to the thermal control system of the satellite. The results showed that a basically passive control is sufficient to maintain most spacecraft׳s components within their temperature range when appropriate thermal coatings and/or tapes are provided. However, heaters to warm up batteries are recommended to survive coldest conditions.

    Highlights We carried out the thermal analysis of a nanosatellite in LEO. A numerical simulation code has been developed to solve the thermal energy balance. The method is based on the finite difference numerical approach. The model predicts temperature profiles of the satellite under dynamic conditions. Technical solutions are proposed to meet thermal requirements of critical equipment.


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    Title :

    Thermal design and analysis of a nanosatellite in low earth orbit


    Contributors:
    Corpino, S. (author) / Caldera, M. (author) / Nichele, F. (author) / Masoero, M. (author) / Viola, N. (author)

    Published in:

    Acta Astronautica ; 115 ; 247-261


    Publication date :

    2015-05-07


    Size :

    15 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English