Thermal state simulation of radioelectronic components as a part of space vehicle with regard to internal heat and external heat exchange

Abstract

This article describes the conditions of the spacecraft (SC) heat transfer at the stages of its operation. A methodical approach is developed, and algorithm for calculation of external and internal heat transfer of spacecraft is proposed. The calculations of the thermal modes and computer experiment to assess the possibility of placing electronic components on the surface of the plate inside nonhermetic SC are carried out. Modeling was carried out taking into account heat liberation of functioning equipment and requirements for the maintenance of a specified temperature range with passive temperature control means. Obtained using a mathematical model results could be used as input parameters for reproducing the calculated external heat loads on the SS irradiated surface during the thermal vacuum tests. The methods of model verification and confirmation of the adequacy of ground tests during the flight test are proposed.