采用仿真分析的方法,研究了蜂窝区域和压紧衬套区域对太阳翼蜂窝夹层结构上蒙皮热变形的影响。结果表明:蜂窝区域碳纤维的铺层方向对上蒙皮变形有一定影响;在蜂窝夹层结构的压紧衬套区域中,上蒙皮的最大变形位于发泡胶与铝蜂窝交界处,该处对上蒙皮变形影响明显;当热压罐温度由130 ℃降为20 ℃时,蜂窝区域以及压紧衬套区域上蒙皮0°碳纤维与90°碳纤维经试验测得的变形量与仿真计算结果的差值分别为11. 1%,12. 0%,14. 1%和14. 9%,证明仿真分析结果可靠。

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.