Analysis Of Composite Material Autoclave Curing Deformation And Compaction Process

Large area molding technology with overall composite used in reinforced wall structure of aircraft can significantly reduce the number of parts or fasteners and achieve efficient production of composite structures. Autoclave curing process is an important approach in overall composite molding technology and curing deformation is the key.In this paper, temperature and curing degree distribution in the composite material component were obtained by coupling heat conduction equation and the curing kinetics equation of resin-based composite in certain boundary conditions, and with the experimental comparison, simulation results were proved correct; Program was written to forecast composite effective elastic modulus, shrinkage strain, thermal expansion coefficient and to analyze the residual stress and deformation of the model in certain boundary conditions. The thickness effect, resin volume shrinkage ratio effect on curing temperature, curing degree field and residual stress after curing were analyzedResin layer thickness was calculated for given viscosity values, and several characteristics were obtained; Compaction procedure was built using APDL language, suitable viscosity value was calculated according to the design fiber volume fraction to meet the technical design requirements. Pressure applying time was obtained by fitting the experimental viscosity-temperature equation of epoxy resin, and experimental results proved the feasibility of theoretical predictions.Effect of pressure to composite laminates of different thickness on temperature and curing degree field distribution in curing process was analyzed.