Transient heat transfer analysis on a satellite in an orbit

Abstract

A parametric study has been carried out on emissivities of the surfaces, shell thicknesses and materials of a satellite structure in order to obtain useful information for satellite thermal engineering design. This is done through a three-dimensional finite element transient heat transfer model on a simple satellite structure using the commercial software ANSYS. The satellite is subjected to several heat loadings in an orbit of sun-tracking mode. Using actual empirically available data, a numerical model is developed and the temperature distribution in the satellite structure predicted. The numerical results of the thermal analysis are analyzed and discussed.