月基望远镜反射镜转台的热-结构耦合分析及验证

Abstract

To improve the work performance of a 2;d mirror gimbal for the lunar;based telescope, the thermal;structural coupled analysis was carried out, and the analysis results were verified by thermal and onboard tests. according to the given input conditions, thermal loads and the thermal boundary, the finite element model was established to calculate the temperature fields of the mirror gimbal and main heating components. through inputting the temperature loads, preloads and the boundary conditions into the finite element model, the thermal deformation and stress of the u;shape structure, precision moving shafting systems and the worm gears were obtained. then, the expressions of friction moment were derived, and analytical data were used to the expressions to achieve the friction moment of shafting systems. on the basis of the friction moment, a proper moment motor was chosen. after calculation, the results show that the left shafting system has a larger friction moment at the low temperature condition of ;25, and the maximal one is up to 14.163 n·mm; while the friction moment is smaller under high temperature condition 55, and the maximal one is 4.796 n·mm. the results also show friction moment of the azimuth shafting systems at a low temperature condition of ;25 is 16.45 n·mm. moreover, the vertical shaft system shows its friction moment to be 16.45 n·mm at the low temperature condition of ;25, while it is zero at the high temperature condition because of shafting system unloading. the results indicate the reflection mirror gimbal works well between ;25 to 55. finally, the thermal and onboard tests were carried out to demonstrate the rationality and validity of the analysis results. © 2016, science press. all right reserved.