Production method for assembling hole of composite material part

A composite material and assembly hole technology, applied in metal processing and other directions, can solve the problems of uncoordinated tooling positioning holes, large shape, large thermal expansion coefficient, etc., and achieve the effect of large practical application value, improved assembly accuracy, and large economic benefits.

Inactive Publication Date: 2016-07-06
HARBIN
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  • Claims
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Problems solved by technology

However, since most forming molds are made of metal, and the thermal expansion coefficient of metal molds is larger than that of composite materials, the formed parts are larger than the theoretical shape, so stress will be generated at the position of the positioning pin
In this case, the positioning pin is pulled out, and the stress of the part is released, causing the formed assembly hole to deviate from the theoretical po

Method used

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  • Production method for assembling hole of composite material part

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Embodiment Construction

[0011] The present invention will be described in further detail below.

[0012] The hole making method of the assembly hole of the composite material part of the present invention directly drills on the composite material to make the assembly hole, and the specific process is as follows:

[0013] Step 1: Composite Part Molding

[0014] After the composite material part is solidified under high temperature and pressure, it is cooled to normal temperature (room temperature) to avoid the deviation of the hole diameter during drilling;

[0015] Step 2: Positioning and pressing

[0016] There is no need to disassemble the composite material parts, and the drilling mold is fitted on the forming mold, wherein the drilling mold 3 is divided into an integrated bottom and a drilling part, wherein the bottom is fixed to the surface of the forming mold, and the drilling area is located at above the part, and set the drill sleeve for drilling;

[0017] Step 3: Drill Holes

[0018] Whe...

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Abstract

The invention belongs to an assembling technology of a composite material and relates to a production method for an assembling hole of a composite material part. The production method for the assembling hole of the composite material part is characterized in that after the composite material part is pressurized and cured at high temperature, and when a mold to be formed and the composite material part restore to normal temperature, a drilling jig is positioned and pressured. The drilling jig is divided into a bottom and a drilling part which are integrated; the bottom and a molded surface of a forming mold are attached and fixed; a drilling area is positioned above the part; and a drilling bushing sleeves the drilling area for drilling. The assembling hole of the composite material part, produced by the production method disclosed by the invention, is free of influence from curvature and overall dimension of products, is accurate in position and can be coordinated with a positioning hole in an assembling workshop; and the demand of actual assembly is met, and the assembling precision of an airplane is effectively improved.

Description

technical field [0001] The invention belongs to composite material assembly technology, and relates to a hole-making method for assembly holes of composite material parts. Background technique [0002] When composite parts are assembled in the assembly workshop, the assembly holes outside the cutting line are usually used to position and compress the parts, and the assembly holes are made by the molding workshop. [0003] The existing hole-making method in the molding workshop is usually to use polytetrafluoroethylene positioning pins to insert into the positioning holes of the forming mold before laying the layers, and then pull them out to form assembly holes after curing under high temperature and pressure. However, since most forming molds are made of metal, and the thermal expansion coefficient of metal molds is larger than that of composite materials, the formed parts are larger than the theoretical shape, so stress will be generated at the position of the positioning ...

Claims

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Application Information

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IPC IPC(8): B29C70/54B26F1/16
CPCB29C70/545B26F1/16
Inventor 孙有赵立兵刘胜
Owner HARBIN
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