Analysis On Temperature Influence Of The Mechanical Properties Of GLARE Laminates Single-Bolt Joints

The GLARE(Glass Laminate Aluminum Reinforced Epoxy)laminate is a new type of fiber-reinforced metal laminate,which is made of aluminum alloy and glass fiber resin.It not only has the advantages of composite materials,such as high specific stiffness,high specific strength and designability,but also has the advantages of good ductility and impact resistance of aluminum alloy.It is widely used in the aviation field.In the process of aircraft flying,a seri es of temperature changes are often experienced.In this process,aluminum alloy,glass fiber and resin base will show different physical,chemical and mechanical properties.Therefore,their combination-GLARE laminate will have more complex mechanical properties.In the past research work,the temperature effect of mechanical properties of aluminum alloy mechanical connection structure and pure composite mechanical connection structure has been studied more,however,there is little research on the temperature effect of the mechanical properties of the mechanical connection structure of flare laminate.Therefore,Therefore,it is very important to study the effect of temperature on the mechanical properties of GLARE laminate.In this paper,the mechanical properties of single lap and single bolt connection structure with GLARE laminate under tensile load are studied by means of simulation analysis.The influence rules of temperature,end distance/pin diameter(E/D)and hole diameter(D)on its ultimate tensile load and failure mode are studied.Firstly,the equivalent modulus and Poisson’s ratio of GLARE laminates at different temperatures are calculated by using the calculation method of composite mechanics,which provides some reference for the following res earch.Secondly,the failure analysis model of GLARE laminate components is established,and the finite element simulation analysis of GLARE laminate bolted connection structure under tensile load is carried out by using ABAQUS software.The failure of the connection structure and the load displacement response of the connection structure under tensile load are analyzed under different temperature,end distance/pin diameter(E/D)and hole diameter(D)The influence of these factors on the ultimate tensile load and failure mode of the structure.with the same structural model and boundary conditions,it is compared with the experimental results of previous researchers to verify the effectiveness of the model.Furthermore,the preset experiments are introduced briefly,and the test methods for determining the material parameters of glass fiber prepreg at different temperature s are described.The preparation and tensile test methods of the test pieces are introduced in detail.The finite element model established in this paper can simulate the tension of the test piece very well,and provide some reference for the optimization design of GLARE laminates mechanical joint structure performance in the future aviation field.