Thermally Induced Satellite Vibrations: Rigid-Flexible-Thermal Coupling in LEO, GEO, and DRO

Abstract Thermally induced vibrations in communication satellites equipped with Solar Array Drive Assemblies (SADA) and laser communication terminals have garnered increasing attention. However, existing research has predominantly focused on the coupling between flexibility and rotation caused by such vibrations, critical factors such as the SADA stiffness matrix in flexible coupling and translational coupling between the solar array and the satellite body have been overlooked. To address these gaps, this study develops a comprehensive rigid-flexible-thermal coupling model for satellites. Utilizing this model, the external heat flux, thermal analysis, and thermally induced vibrations are systematically examined across various orbits, including Low Earth Orbit (LEO), Geostationary Orbit (GEO), and Distant Retrograde Orbit (DRO). The findings demonstrate that incorporating the SADA stiffness matrix significantly improves the accuracy of modeling attitude perturbations caused by thermally induced vibrations on the satellite’s rotational dynamics. Additionally, including translational coupling terms provides a more realistic assessment of disturbances affecting the satellite’s translational motion, particularly in dual-wing configurations. Further analysis reveals that the higher temperature fluctuation rates in LEO lead to more pronounced thermally induced vibrations in the solar arrays. Finally, the study highlights that thermal vibrations exert a greater impact on the attitude angular velocity of single-wing satellites with asymmetrical layouts compared to symmetrically configured dual-wing satellites.