The bending thermoelastic vibrations of thin-walled rod with a circular cross-section connected to the spacecraft (SC) and exposed to solar heat are considered. Transient temperature of the rod is determined by the heat equation, taking into account changes of the incidence angles of sunlight on the surface of the rod due to its bending and turns of the spacecraft.
To solve the related problem of non-stationary thermoelasticity, and thermal conductivity of thin-walled rod the finite element method (FEM) is used. The calculations of vibrations
of the system due to exit of the shadow and turning the spacecraft are conducted.