Study On Civil Aircraft Composite Heat Curing Molding Tooling Thermal Analysis

In order to solve the aircraft composite component mold selection and autoclave moulding process of poor mold thermal uniformity caused problems caused uneven curing, the traditional test repair method of high cost, low efficiency and can not effectively control the deformation analysis, aiming at the influence law of the model complexity, mold curing deformation of members is not clear, mould heat distribution test design is not mature in the research difficulties analysis finite element simulation analysis of the autoclave molding composite component mold heat based on actual design work, in this paper, and the finite element analysis method based on the thermal analysis of the component selection mould hot pressing composite component forming tooling and molding composite cans made a thorough study.One of the design elements of the composite component molding tooling: necessity of composite parts molding tooling thermal uniformity requirements eliciting tooling distributed heat testing and heat distribution under different circumstances of the theoretical parameters model.Based on the finite element simulation, the local temperature distribution through the analysis of the composite material parts and tooling, fixture to determine the relationship between temperature and component temperature hysteresis, and discussed on tooling for the impact of complex temperature distribution of material parts.Taking a certain type of aircraft laminate parts extended box laminate rib as example, detailed analysis by finite element simulation temperature parts- tooling lead region and the hysteresis region, puts forward relevant thermocouple layout scheme according to the simulation results, and through the test of corresponding. Compiled related process documents for actual production and manufacture and use.