Thermal-mechanical Coupling Of Glass Fiber Composite Laminates Strength And Performance

Fiber reinforced composite laminates have been widely used in aerospace,aviation,wind power and other cutting-edge fields in recent years due to their high specific strength,high specific modulus and low manufacturing cost.Workpiece is susceptible to external temperature load during operation,which causes damage to material structure,accelerates the propagation of macro damage cracks,and then affects the strength performance of the whole structure.In addition,there are many factors affecting the failure of composite laminates,such as complex failure modes,scattered experimental data and difficult theoretical prediction.Therefore,it is very important to use finite element method to effectively predict the failure load of composite structures under high temperature and to simulate the generation and expansion of local damage.Aiming at the strength failure of composite laminates under different loads,this paper firstly considers that the basic component of composite laminates is single-ply,and the strength of single-ply directly affects the strength of composite laminates.The macro-mechanics research of composite laminates is the basis of analysis of composite laminates.It is necessary to carry out basic static load tests on single-ply laminates in order to obtain composite laminates.Secondly,based on the classical laminate theory,Hashin damage failure criterion and material stiffness degradation mode are selected.According to the different loading conditions and laying sequence of laminates,different laminate models are established for comparative analysis,and then different laminate thickness,laying sequence,aperture size and other factors are obtained for composite materials.At the same time,the finite element analysis software is used to predict the damage evolution of each layer of the laminate with holes,and the results show that the damage failure trend of each layer is quite different.Finally,considering that the difference of composite material performance is susceptible to the influence of temperature external load,the strength performance of material structure under temperature load is tested,and the simulation analysis isobtained.The damage evolution trend of each layer of composite structures under different temperatures.By referring to a large number of documents and experiments done by predecessors,it is found that the geometric model and progressive damage analysis method of composite laminates established by finite element analysis software in this paper are correct.In this paper,the ultimate bearing capacity of composite structures under different influencing factors is discussed.At the same time,the distribution of local and global stress and damage,the redistribution of load and the way of damage extension after damage can be clearly understood.It is proposed for the ultimate bearing capacity analysis,design,maintenance and performance optimization of composite laminates based on finite element method.For some reference.