Abstract: Using the method of simulation analysis, the influence of honeycomb area and pressing bushing area on thermal deformation of upper skin on solar wing honeycomb sandwich structure was studied. The results show that the direction of the carbon fiber layer in the honeycomb area had some influence on the deformation of the upper skin. In the pressing bushing area of the honeycomb sandwich structure, the maximum deformation of the upper skin was located at the junction of the foam and aluminum honeycomb, which had an obvious effect on the deformation of the upper skin. When the temperature of the autoclave decreased from 130 ℃ to 20 ℃, the difference between the measured deformation of 0° carbon fiber and 90° carbon fiber of the skin on the honeycomb area and the pressing bushing area and the simulation results were 11. 1%, 12. 0%, 14. 1% and 14. 9% respectively, which proved that the simulation analysis results were reliable.