Analysis And Control On Cured Deformation Of Composite Structure

Recently, more and more aircraft designers pay attention to integrated molding technology which can reduce weight and cost by reduction of fastening pieces. However, the autoclave-process cured deformation is unavoidable if stacking design only satisfy the requirement of structure. Forced assemblage may lead to lots of problems, such as assemble stress, seal failure and so on. So the control methods of cured deformation become a key technology during the composite structure design.The approach to reduce cost is to find a suit of cured deformation analysis and control methods. The prediction and control of cured deformation by numerical simulation of autoclave process and structural optimization design is the economy method. Now the cured deformation is mostly calculated by 3D model and 2D plane strain model. The efficiency of 3D model is low, and the 2D plane strain model require a conversion of material parameters. The chapter two, present a equivalent plane strain model. There are many control methods about cured deformation by optimization of process parameters and dimension, but little about stacking sequence. The chapter three present a stacking sequence optimization method based on the composite materials cured deformation by the agent model of stacking sequence. The chapter four, the cured deformation of integral wing panel is calculated and controlled based on the method of prediction and optimization, then a new control method about the stiffened panel cured deformation is presented based on the cured deformation characteristic of stiffened panel and anti-symmetry laminates.