Structure Optimization Of Feeder Body Of 15000 Mine Directional Drilling Rig

The drilling rig is not only used in the production of exploration and drainage,pipeline laying,geological exploration,but also widely used in coal mine gas drainage operation,which is the key equipment for gas mining.Feeder body is the direct bearing mechanism when the power head of directional drilling rig feeds and pulls up,and its structural strength is directly related to the accuracy and stability of the drilling rig.In order to ensure the stable and reliable operation of the drilling rig,the economy and flexibility of the drilling rig are poor,and the safety factor of structural design is too high and the amount of product is too large,resulting in waste of resources.Therefore,this paper takes the feed fuselage of 15000 mine directional drilling rig as the research object to optimize the structure and realize the lightweight design of the feed fuselage.The main research contents are as follows:(1)Analysis of the static and dynamic characteristics of the feed body.According to the working principle and stress condition of the drilling rig,the dangerous working conditions of the drilling rig are determined.The static strength analysis of the six typical positions of lifting0 ° and 20 °,the front position,the middle position and the last position of the feed are carried out,and the dynamic characteristics of the feed body are analyzed.The results show that the maximum stress position is the front position of lifting 20°.Under this position,the maximum stress of the fuselage is 103.2 MPa,which is located at the bottom of the connecting bolt hole of the feed fuselage and the fixed seat of the feed mechanism.Co MPared with the allowable stress of 230 MPa of the material,the structural strength is sufficient.From the results of dynamic characteristics,the dynamic dangerous position of the fuselage is located near the upper end of the left and right side plates.(2)Multi-objective size optimization design of feed fuselage.The multi-objective size optimization design of the feed fuselage was carried out by using Hyper Study software.Based on the sensitivity analysis,the bottom plate,the front plate,the rear plate,the left plate and the right plate were selected as the design objects.Under the premise of meeting the static and dynamic characteristics of the structure,the weight of the original fuselage was reduced by 9 %after the plate thickness optimization.(3)Topology optimization of feed fuselage after multi-objective size optimization.On the premise of meeting the static and dynamic characteristics of the structure,the topology optimization of the feed fuselage was carried out.After the optimization,the first-order frequency changed,and the maximum stress of 129.7 MPa changed little co MPared with that before the optimization.Through the topology optimization,the maximum weight loss of the feed fuselage was 70.88 kg,and the weight loss was 41.4 %.