Optimization Design Of Mechanism And Frame Structure Of High-speed Press

High-speed presses are highly efficient and precise,and are widely used in the production of functional stamping parts(such as lead frames,connectors,silicon steel sheets,etc.).As the market demand for stamping parts has soared,the press has become more competitive and has been paid more attention to equipment performance and cost.Using reasonable methods to reduce the operating cost and production cost of high-speed presses to a minimum and at the same time improve the kinematic characteristics and structural performance of the press,and enhance the market competitiveness of the press has become the focus of press equipment development.Therefore,it is important to study the force-increasing characteristics,kinematic characteristics and lightweight structure of the high-speed press.This paper takes the double-slider six-bar press as the research object,uses theoretical analysis and numerical calculation methods to optimize the design of the movement scale of the punching mechanism,and enhances the force-increasing characteristics of the mechanism and the punching movement characteristics;using finite element simulation and multi-objective topology optimization methods,The lightweight design of the fuselage is carried out on the premise of ensuring the structural performance requirements.The main contents are as follows:(1)The functional principle,basic movement and selected mechanism of each component of the mechanical system of the high-speed press are introduced.Taking the dual-slider and six-bar mechanism as the research object,the kinematics and dynamics calculations are carried out to obtain the movement characteristic curve of the slider,and the mechanical gain analysis of the mechanism is carried out,and the mechanism movement scale based on the mechanical gain and stamping movement characteristics is proposed.Target optimization design method,according to different target weight distribution to obtain two optimization plans,compare the optimization plan and the original plan's force-increasing characteristics,punching motion characteristics,and test the rationality of the method.(2)Combine the dynamic calculation with the analysis of the local force of the crankshaft,analyze the load of each member in the punching mechanism at each contact position of the fuselage,and carry out the theoretical design of the pre-tightening force,and extract all the loads and pre-tightening forces under the stamping conditions Establish a finite element model of the fuselage for static structural analysis and dynamic characteristics analysis,and obtain the deformation and stress of the fuselage under dangerous conditions,as well as the first six natural frequencies and mode shapes of the fuselage.Analyze the weak position of the fuselage,and extract the maximum deformation,maximum stress and low-order frequency values of the fuselage as a comparison plan for subsequent optimization.(3)Using topology optimization method to carry out lightweight design for the upper beam and base with larger mass.The optimization comprehensively considers the multi-condition stiffness of the upper beam and the base and the low-order frequency of the fuselage.The compromise planning method is used to define the multi-condition stiffness target,and the average frequency formula is used to define the low-order frequency target,thereby establishing a multi-objective topology optimization model.The optimal topological structure of the fuselage is satisfied,and its reasonable structural layout is determined.According to the topological optimization results,the fuselage is conceptually modeled,and the preliminary plan design of the fuselage is carried out based on the casting requirements and reserved space.(4)Based on the topological optimization results and the preliminary design plan of the fuselage,the main structural parameters of the fuselage were optimized.After the preliminary selection of parameters and the correlation analysis of the parameters,eight pairs of state variables(deformation,stress,frequency,total mass)were determined.The parameters with greater correlation are the design variables for subsequent optimization.Minimizing the mass is our goal,and the structural performance parameters of the original plan are used as constraints.The goal-driven optimization is carried out to obtain three optimization plans,which are selected after comprehensive consideration of various aspects of performance.best plan.The structural performance of the fuselage of the optimized scheme is better than that of the original scheme,and the weight of the fuselage is reduced by 14.2%,and the lightweight effect is significant.