A kind of inner cavity web processing method

A processing method and web technology, applied in the field of aerospace metal cutting, can solve the problems of cumbersome processing process and poor processing accuracy, achieve the effect of no manual intervention, improve processing efficiency and processing accuracy, and meet processing requirements

Active Publication Date: 2022-05-10
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the entire processing process is still relatively cumbersome, and the processing accuracy is not good.

Method used

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  • A kind of inner cavity web processing method
  • A kind of inner cavity web processing method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] see Figure 1-Figure 2 , a method for processing an inner cavity web, comprising the steps of:

[0039] a. Position and clamp the part 1 to be processed through the process boss 2;

[0040] b. Find the processing coordinate system 3 of the part 1 to be processed;

[0041] c. Rough machining the front side 6 of the inner cavity web and the reverse side 7 of the inner cavity web of the part 1 to be processed, leaving a part of the margin as the remaining material area of ​​the inner cavity web;

[0042] d. Finishing the reverse side 7 of the inner cavity web of the part 1 to be processed to the preset size;

[0043] e. After processing the reverse side 7 of the inner cavity web of the part 1 to be processed to the preset size, then process the front side 4 of the inner cavity web verification area and the reverse side 5 of the inner cavity web verification area;

[0044] f. Call the probe on the machine tool to measure the actual thickness of the front side 4 of the in...

Embodiment 2

[0048] see Figure 1-Figure 2 , a method for processing an inner cavity web, comprising the steps of:

[0049] a. Position and clamp the part 1 to be processed through the process boss 2;

[0050] b. Find the processing coordinate system 3 of the part 1 to be processed;

[0051] c. Rough machining the front side 6 of the inner cavity web and the reverse side 7 of the inner cavity web of the part 1 to be processed, leaving a part of the margin as the remaining material area of ​​the inner cavity web;

[0052] d. Finishing the reverse side 7 of the inner cavity web of the part 1 to be processed to the preset size;

[0053] e. After processing the reverse side 7 of the inner cavity web of the part 1 to be processed to the preset size, then process the front side 4 of the inner cavity web verification area and the reverse side 5 of the inner cavity web verification area;

[0054] f. Call the probe on the machine tool to measure the actual thickness of the front side 4 of the in...

Embodiment 3

[0058] see Figure 1-Figure 2 , a method for processing an inner cavity web, comprising the steps of:

[0059] a. Position and clamp the part 1 to be processed through the process boss 2;

[0060] b. Find the processing coordinate system 3 of the part 1 to be processed;

[0061] c. Rough machining the front side 6 of the inner cavity web and the reverse side 7 of the inner cavity web of the part 1 to be processed, leaving a part of the margin as the remaining material area of ​​the inner cavity web;

[0062] d. Finishing the reverse side 7 of the inner cavity web of the part 1 to be processed to the preset size;

[0063] e. After processing the reverse side 7 of the inner cavity web of the part 1 to be processed to the preset size, then process the front side 4 of the inner cavity web verification area and the reverse side 5 of the inner cavity web verification area;

[0064] f. Call the probe on the machine tool to measure the actual thickness of the front side 4 of the in...

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PUM

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Abstract

The invention discloses a method for processing an inner cavity web, which belongs to the technical field of aviation metal cutting and processing. The machining coordinate system of the part; c. Rough machining the front side of the inner cavity web and the reverse side of the inner cavity web of the part to be processed; d. Finishing the reverse side of the inner cavity web of the part to be processed to the preset size; e. Machining the inner cavity web The front side of the verification area and the back side of the inner cavity web verification area; f. Measure the actual thickness of the front side of the inner cavity web verification area and the back side of the inner cavity web verification area, calculate the difference between the actual value and the theoretical value, and then calculate the difference Compensate to the program of finishing the front side of the inner cavity web; g. Finally finish machining the front side of the inner cavity web of the part to be processed to the preset size, and complete the processing of the inner cavity web. The invention can not only meet the processing requirements of the inner cavity web, realize no manual intervention in the processing process, but also improve processing efficiency and processing precision.

Description

technical field [0001] The invention relates to the technical field of aviation metal cutting, in particular to a method for processing an inner cavity web. Background technique [0002] With the rapid development of the aviation manufacturing industry, in order to adapt to the development trend of intelligent manufacturing technology of aircraft structural parts based on digitalization, aviation main engine manufacturers are gradually changing the existing manufacturing mode of aircraft structural parts, and implementing flexible manufacturing based on digitalization and informationization. The construction of production lines and digital workshops can improve the automation level of aircraft structural parts processing, meet the needs of production flexibility and automation, and realize the improvement of manufacturing technology with aviation manufacturing technology as a breakthrough. [0003] With the development of aircraft structural composite design technology, the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/00
CPCB23P15/00
Inventor 黄景康王琪张杨尚江阮超高锦焜郭国彬
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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