Estimation of Maximum Temperature Deformations of Solar Panels of Earth Remote Sensing Small Satellite “Aist-2D”

Abstract

This article evaluates the temperature deformations of a solar battery panel of a small satellite “Aist-2D” designed for the Earth remote sensing as a result of a thermal shock. Such an assessment is necessary for successful performance of the target tasks of remote sensing of the Earth by a small spacecraft. As a result of the temperature shock, the orientation requirements of the spacecraft may be violated. This is especially true for the angular velocity requirements. The maximum deflection of solar panel is estimated using a one-dimensional thermoelasticity model. The incident heat flux is assumed to be perpendicular to the surface of the solar panel. The panel itself has a flat, non-deformed shape at the time of the temperature shock. This situation makes it possible to estimate the maximum effect of the thermal shock. In this case, the solar panel heating will be maximal. Significance of perturbations from temperature shock leads to the need to take it into account in the analysis of orbital motion of the spacecraft. The stress-strain state of the solar panel has been investigated. The dependences of the deflection of the solar panel points during the temperature shock are obtained. The results of the estimation can be used to assess the impact of thermal shock on the task execution of “Aist-2D”.