Composite Multiple Bolted Joints Laminates Failure Analysis And Fatigue Life Estimation

With the development of aircraft structure technology, composite materials aregradually are widely used in various industrial fields due to high strength and highstiffness. For composite laminates usually applied in main force-bearing components,mechanical joints are mainly used. Since the structure specialty for composites,influencing factors of joint strength are much more complex than those in metals. Thestrength analysis and life estimation of connection area for the interference fit ofcomposite laminated plate is the main difficulties for the current structural design.Numerical simulations and experimental observation in the area of compositelaminate mechanical joints researched by foreign and domestic scholars are analyzed inthis paper, using the finite element analysis software ANSYS, through establish threedimensional model of composite laminates, considering the interference fit and theinfluence of the contact problem and researching the fatigue characteristics of the holeside.First, briefly introduces the present researching situation of the composite multiplelaminated joints laminates and the basic information of composite connection failure,and then points out that the purpose of the research. This paper analyzes the hole sidestress distribution characteristics of composite laminate mechanical joints ininterference fit, comparing the condition of load distribution of different connectionmodel and interference ratio, discussed the selection of failure criteria and thedistribution of different failure layers for Hashin failure criterion.Secondly, researching the fatigue strength of composite laminates double shear andinterference fit model. Contrasting stress and strain of different interference ratiomodels under alternating load. Using the fatigue life prediction software FE-safe onestimation for the composite laminates life and the holes edge safety coefficient, andhave a further understanding for the fatigue failure over alternating load.Finally, all the information that were given and all conclusions based on theanalysis were summarized, and the observation of composite joints was made.