Study on the Properties of 120℃ Curing Toughened Epoxy Carbon Fiber Fabric Composites

The 120℃ curing toughened epoxy carbon fiber fabric composites are the main structural materials used in aviation at present. In view of the urgent need of using 120℃ curing toughened epoxy carbon fiber fabric composites for typical structures such as skin, partition, rib and fairing of large-scale composite materials, and relying on the research foundation and accumulated experience of domestic earlier composites, In this paper, 120℃ curing toughened epoxy carbon fiber fabric composites were prepared by two-step hot-melt method, the typical curing process parameters were determined, the DSC characteristics, IR spectra and rheological properties of toughened resin system were studied, the heat resistance and curing process adaptability were verified, and the physical properties, room temperature mechanical properties of the composites, the properties of toughness and high and low temperature mechanical properties were evaluated, and established relatively complete performance data. The results show that the prepreg prepared by curing toughened epoxy carbon fiber fabric at 120℃ has good technicality, the precision of resin content reaches±2% and the precision of fiber surface density reaches±5%. It can be applied to the forming process of hot-pressing pot, and meets the control requirements of the prepreg by the large-scale aeronautical molding. The glass transition temperature of the material is high, the properties of the composite meet the requirements of the index, the mechanical properties are excellent, the tensile properties and interlaminar shear properties are maintained at high temperature and humidity, the resistance to heat and humidity is good, and the comprehensive properties are excellent.