Analysis of the influence of carbon fiber placement patterns on the thermal expansion performance of structural panels

Carbon fiber skin honeycomb sandwich structural panels are widely used in aviation, aerospace, and other fields due to their characteristics of light weight, high strength, and small deformation. The deformation of structural panels under high and low temperature environments during service is a key factor affecting the success of missions. How to ensure the overall performance of the structure while effectively optimizing and improving its thermal stability is a bottleneck problem in the development of such structures. Existing research on the manufacturing and forming process technologies of structural panels mainly focuses on materials and forming processes, but there is a lack of technical research on the influence of carbon fiber layup methods on the thermal expansion rate of the final formed structure. In response to the above situation, this paper conducts a comparative analysis of the thermal expansion performance of sandwich structures formed by two typical fiber layup methods (vertical cross method and X-type cross method), and analyzes the influence relationship between different placement patterns and the thermal deformation performance of the structure.