Influence Of Mast's Material Property On Thermally Induced Vibration Of Flexible Solar Wing

Flexible solar wings(FSW) are widely used on the power system of large space stations, which are spread out in orbit by the mid-mast. When space station keeps going into and out of the Earth shadow area, periodic thermal radiation, which can cause time-varying temperature load and further lead to thermal deformation and even thermal induced vibration(TIV), is applied on the FSW system. Among all these parts of FSW, the mast's thermal deformation greatly affects the TIV of flexible solar array(FSA). The thermal deformation of mast must not exceed acceptable limits in order to maintain the normal work of FSA. In this paper influence of the material properties of mast on the FSA's TIV is investigated mainly.Various subjects, such as thermal conduction, thermal elastic mechanics and dynamics are involved in study of this problem. The temperature load of FSW is transformed into thermal excitation under the uncoupled thermal-structural assumption. Based on this theory, sequential couple engineering method is used to calculate the thermal load and TIV respectively. First, temperature load was obtained using the finite element software NX I-deas, then vibration response is calculated by ABAQUS.In order to compare the influence of material properties on TIV, the study was carried out mainly in two aspects. First, three kinds of thermal control coating material, such as electrodeposited coating, white paint coating, and none coating, are studied and the corresponding responses of FSW are compared. Afterwards, model FRONTIER in combination with ABAQUS are employed to perform the optimizations for three kinds of metal masts-aluminum alloy, titanium alloy and stainless steel respectively. Obtained results can be used as reference for design of FSW.