Study On Finite-element Modeling And Experiment Of Carbon Fibermetal Laminates And Prediction Of Fatigue Life

CFMLs is the abbreviation of Carbon Fiber metal laminates. Fiber metal laminates (FMLs) in the good performance has been extensively used in the 777 and the airbus A380 wing and the body structure, the the region and how much aircraft structure of plane advanced composite materials used in have become one of the important indexes of advancement. Our country has a research for early fiber metal laminates structural design and manufacturing process to a certain extent, but is in the infancy for the new generation FMLs structure research, to satisfy the need of our large planes independent design and manufacture, research must be canrried out for new generation FMLs structure design and manufacturing technology. Fiber metal laminates is generally consisted of hot-pressed alternating layers , heat residual stress will be generated in this process, and thermal residual stress size and distribution of the fibers metal laminates have an important effect on the mechanical properties. The finite element method is comparatively mature numerical method currently in practice, a high-precision results will be gained by appropriate use of finite element method. It is common that theory method has a precise description of results in numerical, experimental method can reflect the real results;in other espect ,finite element method is rather simple and practical ,and the laboursaving. In brief research using finite element method for thermal residual stress, tensile strength, fatigue life of carbon fibre metal laminates has an important theoretical and practical significance.In this paper, adhesive interface is simulated by interface element unit materials ,tensile model is establed in ABAQUS/Standar, both a study of the impacts on the tensile strength from garge length and knuckle of the tensile specimen is conducted and a research for effects on fracture position of specimen from gauge length and knuckle is carried out. model is established in ABAQUS/ Explicit , hot forming process has been simulated and thermal residual stress distribution in spcimen is analyzed. Based on damage theory, empirical formula to estimate fatigue life of laminates at different stress ratio is established by combinaton of theory add experimental results fitting, and the formula has a good perfomance.