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<p>In the field of aerospace manufacturing, the demand for fastening assembly has led to the increasing application of CFRP/Ti-6Al-4&#xa0;V laminated structures in aircraft load-bearing structural parts, and the quality of single-pass hole-making is crucial to the connection performance of aircraft structural parts. However, the machinability of CFRP and Ti-6Al-4&#xa0;V is poor, and the rapid wear of the tool is considered to be the main factor restricting the hole quality. To improve the hole-making quality of CFRP/Ti-6Al-4&#xa0;V laminated material, the tool wear test of CFRP/Ti-6Al-4&#xa0;V laminated material was carried out by using a corner-radius end mill. The wear mechanism of the cutting edge was analyzed. The influence of spindle speed on wear and the change rule of tool wear on cutting temperature, cutting force and hole-making quality were studied. The results show that the tool wear area of gyroscopic milling is mainly concentrated in the bottom cutting edge area and the arc transition edge area. The wear bands are long spoon-shaped and triangular, respectively, and the wear of the arc transition edge area is relatively serious. The tool wear process of gyroscopic milling goes through the coating wear stage dominated by abrasive wear, the coating shedding stage dominated by adhesive wear and the sharp wear stage of cutting edge mixed with various wear mechanisms. With the increase in spindle speed, the boundary between the various stages of tool wear becomes not obvious, and the wear mechanism becomes more complex. With the increase of tool wear, the surface morphology of the CFRP hole wall, the tear factor of the CFRP outlet and the burr height of the Ti-6Al-4&#xa0;V outlet all decreased significantly.</p>

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Study on the Wear Mechanism and Cutting Performance of Corner-Radius End Mill in Gyroscopic Milling of CFRP/Ti-6Al-4 V Laminated Material

  • 期刊论文

  • 发表日期：

    2025年10月21日

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  • Hui Xiao,
  • Tao Chen,
  • Chunhui Li,
  • Guangyue Wang,
  • Zhilong Yu

摘要

In the field of aerospace manufacturing, the demand for fastening assembly has led to the increasing application of CFRP/Ti-6Al-4 V laminated structures in aircraft load-bearing structural parts, and the quality of single-pass hole-making is crucial to the connection performance of aircraft structural parts. However, the machinability of CFRP and Ti-6Al-4 V is poor, and the rapid wear of the tool is considered to be the main factor restricting the hole quality. To improve the hole-making quality of CFRP/Ti-6Al-4 V laminated material, the tool wear test of CFRP/Ti-6Al-4 V laminated material was carried out by using a corner-radius end mill. The wear mechanism of the cutting edge was analyzed. The influence of spindle speed on wear and the change rule of tool wear on cutting temperature, cutting force and hole-making quality were studied. The results show that the tool wear area of gyroscopic milling is mainly concentrated in the bottom cutting edge area and the arc transition edge area. The wear bands are long spoon-shaped and triangular, respectively, and the wear of the arc transition edge area is relatively serious. The tool wear process of gyroscopic milling goes through the coating wear stage dominated by abrasive wear, the coating shedding stage dominated by adhesive wear and the sharp wear stage of cutting edge mixed with various wear mechanisms. With the increase in spindle speed, the boundary between the various stages of tool wear becomes not obvious, and the wear mechanism becomes more complex. With the increase of tool wear, the surface morphology of the CFRP hole wall, the tear factor of the CFRP outlet and the burr height of the Ti-6Al-4 V outlet all decreased significantly.