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Method for machining high-precision holes of carbon fiber sandwich-aluminum alloy laminated materials

A processing method and technology of aluminum alloy layer, applied in the field of mechanical processing, can solve the problems of low efficiency, reduced hole quality and precision, prone to flutter, etc., and achieve the effects of reducing manufacturing cost, ensuring processing quality, and reducing scrap rate

Inactive Publication Date: 2019-04-12
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the traditional method has the following deficiencies: First, when the hole is made by the robot assembly system, due to the poor rigidity of the robot end actuator, chattering is prone to occur during the hole making, which reduces the quality and accuracy of the hole; the manual hole making is not only inefficient, but also And affected by factors such as the proficiency of workers, it is difficult to guarantee the quality requirements of the holes
Secondly, in the process of processing, problems such as tearing and damage of the orifice of the carbon fiber sandwich layer are prone to occur, resulting in the scrapping of the parts, increasing the manufacturing cost of the parts, affecting the processing efficiency of the parts, and thus affecting the development cycle of the entire aviation equipment

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  • Method for machining high-precision holes of carbon fiber sandwich-aluminum alloy laminated materials

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Effect test

Embodiment 1

[0024] The present invention is realized through the following technical solutions, as figure 1 As shown, a carbon fiber sandwich-aluminum alloy laminated material high-precision hole processing method, the carbon fiber sandwich and the aluminum alloy joint are assembled together through a tooling frame, and then layered drilling is performed according to different materials, and the same material Different tool combinations are selected in the area, and the method of step drilling and reaming is adopted to realize the processing of high-precision holes in carbon fiber sandwich-aluminum alloy laminated materials.

[0025] It should be noted that, through the above improvements, the limitation of drilling from the carbon fiber sandwich layer 1 due to the processing conditions has been broken through the method of layering and step drilling and reaming, and the tearing of the carbon fiber sandwich layer 1 hole has been avoided. Quality problems such as damage and out-of-toleranc...

Embodiment 2

[0028] This embodiment is further optimized on the basis of the above embodiments, such as figure 1 As shown, it specifically includes the following steps:

[0029] Step S1: Assemble the carbon fiber sandwich material and the aluminum alloy joint through the tooling frame, and fix it on the machine tool table;

[0030] Step S2: Select the drill bit 3 to make the initial hole of the carbon fiber sandwich layer in the carbon fiber sandwich layer 1; the initial hole of the carbon fiber sandwich layer is a blind hole; the diameter of the initial hole is D C , the diameter of the final hole formed after processing is D Z .

[0031] Step S3: According to the size of the final hole of the carbon fiber sandwich layer 1, different tool combinations are selected, and the hole of the aluminum alloy layer is processed to the same diameter as the initial hole of the carbon fiber sandwich layer by step drilling;

[0032] Step S4: The carbon fiber sandwich layer 1 and the aluminum alloy l...

Embodiment 3

[0042] This embodiment is the best embodiment of the present invention, as figure 1 As shown, a carbon fiber sandwich-aluminum alloy laminated material high-precision hole processing method specifically includes the following steps:

[0043] Step S1: Assemble the carbon fiber sandwich material and the aluminum alloy joint through the tooling frame, and fix it on the machine tool table;

[0044] Step S2: Select the drill bit 3 to make the initial hole of the carbon fiber sandwich layer in the carbon fiber sandwich layer 1; the initial hole of the carbon fiber sandwich layer is a blind hole; the diameter of the initial hole is D C , the diameter of the final hole formed after processing is D Z .

[0045]The step S2 specifically refers to: in the drilling of the initial hole of the carbon fiber sandwich layer, the initial hole diameter D C and end hole diameter D Z Satisfy between: 0.6mm≤(D Z -D C )≤1mm; and the depth L at the drill shoulder P and the thickness d of the ca...

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Abstract

The invention discloses a method for machining high-precision holes of carbon fiber sandwich-aluminum alloy laminated materials. Carbon fiber sandwiches and aluminum alloy connectors are assembled together through a tool fixture, then layered drilling is carried out according to different materials, different cutter combinations are selected and used in the same material region, and by the adoption of broaching and reaming of a stepped drill, the high-precision holes of the carbon fiber sandwich-aluminum alloy laminated materials are machined. The quality problems that carbon fiber sandwich layer orifices are torn and broken and are super-poor are avoided, the machining quality of parts is guaranteed, the rejection rate of the parts is reduced, and therefore the manufacturing cost of the parts is reduced.

Description

technical field [0001] The invention relates to the technical field of mechanical processing, in particular to a high-precision hole processing method for a carbon fiber sandwich-aluminum alloy laminated material. Background technique [0002] With the continuous development of aviation technology, the new generation of aviation equipment has higher and higher requirements for material performance, especially composite materials. [0003] It is a carbon fiber composite material that has been widely used for its unique properties. As an integral part of the new generation of aviation equipment, carbon fiber sandwich parts play a vital role in the development of the entire aviation equipment, especially the Airbus A350XWB series, most of which are made of composite materials, and the amount of composite materials accounts for The ratio is as high as 53%. At present, carbon fiber sandwich composite parts are mostly used in important positions such as aircraft wings and rudder...

Claims

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Application Information

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IPC IPC(8): B23B35/00B23P13/02
CPCB23B35/00B23P13/02
Inventor 张也王鹏程韩雄罗育果王伟
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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