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A method for planning the machining trajectory of a laminated material hole

A technology of laminated materials and trajectory planning, applied in the direction of manufacturing tools, metal processing equipment, milling machine equipment, etc., can solve the problems of dividing processing stages, reducing the revolution speed of terminal hole-making actuators, and not significantly improving processing defects, etc., to achieve The effects of reducing hole diameter deviation and roundness, improving overall processing quality, and improving overall hole-making accuracy

Active Publication Date: 2021-02-09
LANZHOU UNIVERSITY OF TECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Patent document CN 105728811A discloses a method and system for robotized spiral hole-making of aircraft fuselage laminated materials, which improves the hole-making efficiency of fuselage laminated materials by increasing the axial feed pitch; While the small axial feed pitch is efficient for spiral hole making, the revolution speed of the terminal hole making actuator is reduced to suppress the excitation force caused by the mass eccentricity of the terminal hole making actuator; it does not depend on the composition of the laminated material Therefore, the above-mentioned patent documents only improve the efficiency of processing holes, but do not significantly improve the processing defects of each component material of the laminated material at the exit, entrance and interface.

Method used

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  • A method for planning the machining trajectory of a laminated material hole
  • A method for planning the machining trajectory of a laminated material hole
  • A method for planning the machining trajectory of a laminated material hole

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Embodiment 1

[0050] According to the composition of the laminated material, determine the thickness of the workpiece material and the aperture range: the double-layered laminated material is composed of the upper layer of CFRP composite material and the lower layer of titanium alloy, wherein the thickness of the titanium alloy material layer ranges from 5-10mm, and the thickness of the CFRP composite material layer is titanium alloy 2 times the thickness of the layer, the diameter range of the machining hole is 10-20mm, and the ratio of the hole diameter to the tool diameter is 1.5.

[0051] Using a traditional end mill, combined with the helical milling hole end effector under the industrial robot platform, the hole making process of double-layer laminated materials is implemented. The helical milling hole end effector used in the present invention is the prior art, which generally includes a tool The rotation unit, the tool revolution unit, the tool radial offset unit, the axial feed unit...

Embodiment 2

[0062] According to the composition of laminated materials, the thickness and aperture range of workpiece materials are determined: sandwich laminated materials are composed of upper layer CFRP composite material, middle layer titanium alloy and lower layer CFRP composite material. Among them, the thickness range of the titanium alloy material layer is 5-7mm, and the thickness of the CFRP composite material layer is twice the thickness of the titanium alloy layer. The diameter range of the machined hole is 15-30mm, and the ratio of hole diameter to tool diameter is 1.3.

[0063] Using a traditional end mill, combined with the helical milling hole end effector under the platform of the industrial numerical control machine tool to implement the hole making process to the sandwich laminated material, the helical milling hole end effector used in the present invention is the prior art, which generally includes The tool rotation unit, the tool revolution unit, the tool radial offse...

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Abstract

The invention discloses a method for planning a hole-making process trajectory of a laminated material, which comprises the following steps: 1) dividing the processing process of the laminated material into processing stages such as entry, stabilization, interface, and exit along the axial direction; 2) measuring and sorting out the hole-making accuracy 3) Analyze the variation law of the hole making precision at each stage, and establish the fitting relationship between the hole diameter deviation, roundness and the characteristic parameters of the spiral trajectory; 4) The average value of the axial cutting force is the smallest, and the peak value of the circumferential cutting force is the smallest As the goal, the optimal value of the characteristic parameters of the spiral trajectory is obtained. The invention provides a way to solve the problem of "inverted cone" in the through-hole processing of laminated materials. By analyzing the variation law of the hole-making precision in the key stage of the single-hole processing process, the core goal is to meet the precision level requirements of the export stage, and the spiral movement is carried out. Trajectory planning, and finally realize the optimization of process parameters, which can not only improve the overall hole-making accuracy of the single-hole machining process, but also help reduce the overall cutting force level to prolong the tool life.

Description

technical field [0001] The invention relates to an advanced hole-making technology in the field of aviation manufacturing, in particular to a method for planning a hole-making process trajectory of laminated materials. Background technique [0002] With the advancement and development of aviation advanced manufacturing technology, typical aviation high-performance materials represented by aviation aluminum alloys, titanium alloys, and carbon fiber composite materials (CFRP) have highlighted advantages in terms of overall aircraft structure lightweight, low energy consumption, and high reliability. , and the laminated material composed of the above aerospace difficult-to-machine materials is superior to any single material in terms of material performance. Therefore, in the laminated materials of aircraft wings, composite materials are selected for wing panels, and aluminum and titanium alloys for the skeleton have been used in engineering applications, and the use of titaniu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23C3/00
CPCB23C3/00
Inventor 周兰安国升李文生冯力郑敏
Owner LANZHOU UNIVERSITY OF TECHNOLOGY
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