Abstract
Thermally induced vibrations of flexible spacecraft appendages, which are subjected to incident solar heat flux during the orbital eclipse transitions, have been typical failure of modern spacecrafts since 1960’s. For example, this failure was observed on the Voyager space explorer [1], the Hubble Space Telescope [1] and the UARS satellite [2] etc. When the thermally-induced vibration is unstable, it is called thermal flutter, which is due to the coupling effect between structural deformations and the incident normal solar heat flux. Owing to the existence of the coupling effect and the transient heat conduction problem involving heat transfer by radiation, it is really a highly nonlinear problem.
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