航空钛合金ti6al4v的高速铣削表面完整性模拟研究分析-simulation research and analysis of surface integrity of ti 6 al 4v aviation titanium alloy in high speed milling.docxVIP

AbstractWith the advances in aerospace technology, titanium alloy Ti6Al4V due to its heat resistance, corrosion resistance, strength and good plasticity, is widely applied to high temperature, high pressure and high speed and other special conditions, and the requirement to meet better fitting accuracy, fatigue strength and wear resistance, surface integrity of higher standards. Mainly in the surface residual stress, surface hardening and surface roughness on the surface of the integrity of research.The rapid development of computer technology makes the application of the finite element method more and more on high-speed machining surface integrity. This paper describes some of the key technologies of the finite element method in high-speed machining, the overall control equation of the finite element method for high-speed cutting, the geometry model of the finite element, the constitutive equation of the material, the friction model, chip separation criteria, chip fracture criterion, cutting process in heat transfer and dissipation. Explore the finite element model, combined with Ti6Al4V in the actual processing of the feed per tooth and axial depth of cut small, reasonable simplification oblique cutting model. SHPB test measured at different strain rates, the various temperature stress-strain curve, the software Matlab fitting out of the Power-law material constitutive model.Based on Oxley cutting model, combined with Power-law material constitutive modeling established the prediction model of residual stress. Designing an orthogonal experiment, using the finite element software Third Wave AdvantEdge researched surface residual stress distribution range on cutting parameters and tool parameters and analysis to identify the optimal combination of parameters of the minimum surface residual tensile stress.Explore the formation mechanism of the surface work-hardening, that the depth strained layer of workpiece corresponding to the depth of hardened layer of workpiece,