Structure Design And Optimization Of Fiber Reinforced Composite Airfoil

Compared with manned aircraft,UAV can achieve miniaturization and miniaturization,which is of great significance to the development of various industries.Uav made of traditional metal materials has large structure weight,poor flexibility and short flight time.Now lightweight has become the basic requirement of UAV design.Due to its advantages of low density,high specific strength and stiffness,composite material has become the preferred material in lightweight design of UAV,which can not only greatly reduce the structural weight but also have excellent overall performance.As the main force transfer and bearing components of UAV,the wing undertakes about 70% of the aerodynamic load,which is the key link in the research and development of UAV and directly determines the quality and performance of the whole machine.Based on the "Intelligent Small Cruise" project of Fanrui Yi Hui Composite Material Co.,LTD.,this paper adopts composite material wings to achieve significant weight reduction and improve the overall performance of wing structure according to the engineering needs and the existing wing design experience.In order to reduce the weight of the wing structure and meet the design requirements of strength and stiffness,a complete study is made on the optimization and preparation of the composite wing structure.The main research work and achievements of this paper are as follows:(1)Study the influence of layering mode on the properties of composite laminates.Through the sample test of laminates with different layering schemes,study the influence law of layering sequence and layering Angle on the tensile and shear properties of composite laminates,and analyze the design theory of laminates and strength failure criteria.(2)Through the analysis of the design characteristics of the composite material structure,the structure form of the wing,the wing design principle and the design requirements,the selection of the wing wing profile and the determination of the initial design parameters and the establishment of the wing model.The finite element analysis of the wing was carried out on ANSYS Workbench platform,and the initial finite element model of the wing was established.(3)The cladding material of wing skin was optimized by finite element analysis,and M40 J carbon fiber prepreg was selected as the cladding material of wing skin.The genetic algorithm was used to optimize the wing skin layup sequence,and the optimal layup scheme was obtained as[45°,0°,-45°,0°,0°]s.By optimizing the layup thickness,the wing skin layup thickness was obtained as 2mm.The maximum displacement of the wing slightly decreased from 114 mm before optimization to 54.136 mm,meeting the design requirements.The maximum Tsai-Wu failure factor of the wing was less than 1,and no failure occurred.(4)The statics test of the wing verifies the simulation optimization results.The statics test results show that the maximum displacement of the wing wing slightly is 46 mm under the action of 280 N force,and the result of finite element simulation analysis is 54.136 mm,with an error of14.1%,which meets the requirements of engineering design.The optimized wing fully meets the design requirements of strength and stiffness,and also effectively reduces the weight of the wing,providing a reliable reference for engineering applications.