Stiffness Analysis And Optimization Design Of Press In Intelligent Forging Production Line

Forging industry as an important part of China’s traditional industry,its products are all over the automobile manufacturing,aerospace and other important fields,the realization of forging intelligence is of great significance to the domestic economic development and technological breakthroughs in key areas.As the core equipment of intelligent forging production line,the forging press has a complex structure,and the key bearing parts are in the harsh environment for a long time,which is prone to deformation and precision degradation.Therefore,it is important to study how to improve the stiffness performance of the machine under different working conditions by carrying out optimal design of the press structure.In this paper,we take JH31-250 forging press as the research object,analyze and study the influence of the press structure on the stiffness and accuracy under the working condition,and explore the optimization design method of the press body structure under different working conditions.Based on the technical parameters of JH31-250 press,a three-dimensional solid model of the fuselage is established,and the static analysis,modal analysis and explicit dynamic analysis of the original fuselage are carried out based on Abaqus software to obtain the stress and deformation of the fuselage under the action of nominal force,the inherent frequencies and vibration patterns of the first six sections of the fuselage and the dynamic response under transient impact force.The results of the numerical analysis of the fuselage are used to determine the structural design area of the fuselage and provide reference for the subsequent static and dynamic structural optimization.The topology optimization method is used to optimize the design of the support structure on both sides of the frame to improve the static stiffness of the frame.With the minimum flexibility as the optimization objective function and the volume fraction as the constraint,a topology optimization mathematical model is established to obtain the topological concept configuration of the fuselage.According to the optimal configuration,the fuselage is regularized,and the maximum relative displacement of the fuselage is used as the optimization parameter to establish the response surface model.After optimization,the maximum relative displacement of the fuselage is 0.2548 mm,which is 40.03% lower than the deformation of the original model,and the static stiffness of the fuselage has been improved.The hybrid cellular automata algorithm(HCA)based on the hybrid cellular automata algorithm(HCA)is used to optimize the design of the body structure to improve the dynamic stiffness of the body.In view of the complexity of transient dynamic analysis,it is creatively proposed to convert the complex 3D structure of the machine tool into a 2D mechanical model,and use physical quantities such as cell density and thickness to describe the finite element unit of the structural design.According to the simplified model,the strain energy distribution of the cells in the structure is calculated,and the cell information is updated using the HCA method to form a definite structural image and obtain a topological conceptual configuration.After that,the 3D fuselage structure is reconstructed and regularized according to the conceptual configuration,and the structural geometric parameters are fine-tuned by combining response surface and particle swarm methods to complete the transient dynamic structural optimization of the fuselage.The maximum relative displacement of the optimized fuselage is 0.4896 mm,which is 31.02% lower than the deformation of the original model,and the dynamic stiffness of the fuselage has been improved.Tensile tests were designed to verify the optimized fuselage structure.The numerical simulation and tensile test of the specimen were used to verify the correctness of the material parameters.The solid resin models of the original and optimized fuselage were printed in equal scale by using light-curing technology,and the relative deformation and displacement of the fuselage models before and after the optimization were compared in the tensile test and numerical simulation,which proved the rationality and effectiveness of the optimization scheme of the fuselage structure and provided a reference for the design of high stiffness structures of similar forging and pressing equipment.