The Strength Of The Composite Plate Buckling And Mechanical Connection Analysis

At first, this paper introduces history and development of composite detailedly, composite is used in the field of industry and agriculture and so on widely. This paper summaries the researches and developments of some study fields, points out some problems about the researches. Finally, some suggestions are put forward for about the direction of this area in the future and the works need to done.The paper can be divided in five chapters:The first one is the summaries of theory analysis and fern analysis. This chapter shows some laminate theories such as The Classical Plate Theory and The First Order Shear Deformation Theory and The High Order Shear Deformation Theory and it's simple forms firstly. Some plate(shell) and solid elements that can be used for composite analysis of the commercial software are presented in the paper in order to make foundation for analysis and calculation of theory and method.The second one is experimental research of the moderately thick composite laminates. Due to the analysis of moderately thick composite laminates focus on the theory calculation and numerical simulation, the experimental data are absence. In this paper, three kinds of laminates are tested and simulated numerically. The result indicates that the elastic behavior of experimental point is explicit and the data are coincident with simulation.The third one is the buckling analysis of the moderately thick composite laminates. This chapter indicates buckling modes, critical load and equilibrium path of plate under axial compression and shear load. Some results can be obtained from this chapter. The plate's deformation keep linear relationship with load before buckling and plate's capability of standing load descends immediately. From the figures we can conclude the results that the plate is not buckling even more load.The fourth one is the FEM analysis of composite structure with ply drop-off. The studies we have performed show that the deformation, strain and stress distributes unequally in structure due to the ply cut-off. This can induce interlaminar stress and danger zone especially in the zone nearby transition, so the structure's strength can be degraded.The fifth one is the study of three-dimensional stress distribution of compositelaminate with bolted joint. A composite laminate with bolted joint was established to determine the stress distribution on the contact surface. The effects of clamping torque, friction and bolt elasticity on the contact stress and interlaminar normal stress are considered seriously. Contact stress is bearing mainly by the 0° layer. The distribution and magnitude of contact stress are conducted by friction and stiffness of bolt; The effect of clamping torque on interlaminar normal stress is very strong, when there has no clamping torque, the interlaminate normal stress reach the peak value at the region near contact edge, there is prone to failure. At application, the interlaminar compress stress can be induced by impose enough clamping torque on laminate help to avoid failure of structure.