A Composite Bolted Connections Force Numerical Analysis Method

Along with the composite materialis gradually extensive in the application of the aviation realm ,a lot of inevitable joint problems appear. The joint of composite laminate can be sort into bonding joint and bolt joint. There are disadvantage and advantage on the bonding and bolted. Mechanical joint provide the primary means for transferring load among components in the construction of aircraft structures. However, they are associated with high stress concentration arising from bolt holes leading to failure. Therefore, assessment of the stress in bolted composite joints is essential for the design of reliable components. The stress state in a bolted composite joint is significantly influenced by loading condition, degree of anisotropy ,plate dimensions,bolt flexibility and the clearance between a bolt and the hole boundary.This study concerns the determination of the contact stress and contact region around bolt hole and the bolt load distribution in single-and double lap joints of uniform composite laminates with arbitrarily located bolted under general mechanical loading conditions. The method in this study is an analytical/numerical method.The complex potential functions suggested by Lekhnitskii in the form of series,automatically satisfies the in-plane stress equilibrium equations and compatibility conditions. The stress and displacement around bolt holes can be expressed as functions of potential function. The contact forces and the force arising from displacement constraints are also assumed in the form of series.Each of the bolt and laminate equilibrium equation and the boundary condition are satisfied by minimizing the total potential energy, i.e. the first variation of the total potential energy vanish.Based on the equilibrium equations in laminates and bolts derived from first variation of the total potential energy, we obtain a humongous matrix equation. Solving the equation vectors permits calculation of the stress and displacement...