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 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.
Preliminary Thermal Design for Microsatellites Deployed from International Space Station’s Kibo Module
Journal of Thermophysics and Heat Transfer ; 32 , 3 ; 789-798
01.07.2018
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Modification of the KIBO Passive Thermal Control
British Library Conference Proceedings | 2002
|Design of 'KIBO' structure and verification
AIAA | 2010
|SAE Technical Papers | 2003
|