A preliminary thermal design was proposed by determining all the possible combinations of solar absorptivity and infrared emissivity on the panel surfaces of Earth-pointing satellites deployed from Japan’s experimental module small-satellite orbital deployer. The three most common internal panel configurations in a 50 kg satellite with body-mounted solar cells and dimensions of 550 × 350 × 550    mm were considered. Conductive insulation was applied between the inner and outer structures to decrease the temperature change of inner components. The worst hot- and cold case conditions were estimated based on the beta angle of the orbit and the Earth’s distance from the sun. The analyses were carried out using a simple tool created in MATLAB©. The tool output combinations of optical properties that satisfied the predefined allowable temperature range of structures and components. These optical properties were subsequently verified using Thermal Desktop©’s SINDA/FLUINT with the RadCAD module. Using these combinations, the thermal design for microsatellites in a low Earth and non-sun-synchronous orbit may be shortened.


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    Titel :

    Preliminary Thermal Design for Microsatellites Deployed from International Space Station’s Kibo Module


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.07.2018




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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