Method for machining a reverse hole of large sandwich blind hole structure of aircraft

A processing method and hole structure technology, which is applied in the direction of drilling dies for workpieces, boring/drilling, metal processing equipment, etc. wide range of effects

Inactive Publication Date: 2018-11-27
AVIC SAC COMML AIRCRAFT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

First of all, limited by the minimum thickness of the hole wall of the drill sleeve, a cutting allowance of at least 3mm in diameter is left in the first cut before the final hole. Hole operation, since there is no guiding device on the side of the structure that needs to be reversed, it is easy to cause the reversed hole to be non-vertical and not in the same axis as the original hole on the structure

Method used

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  • Method for machining a reverse hole of large sandwich blind hole structure of aircraft
  • Method for machining a reverse hole of large sandwich blind hole structure of aircraft
  • Method for machining a reverse hole of large sandwich blind hole structure of aircraft

Examples

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Embodiment

[0016] Example: 1) Use the original final hole in the structure to drill the initial hole of 3.26mm into the product structure that needs to be reversed through the guide pin 5 with the initial hole of φ3.26mm;

[0017] 2) Use the step pin 4 to locate the drill template 2 for the reverse hole on the side of the product structure where the hole needs to be reversed to realize the precise positioning of the drill template 2 so that the drill template 2 is coaxial with the original final hole on the structure to ensure the reverse hole The rear end hole is coaxial with the original end hole. The positioning process of the drill template 2 is to place the drill template 2 and the drill sleeve 3 on the side of the product structure that needs to be reversed, and then insert the stepped pin 4. The front end of the stepped pin 4 has a diameter of 3.26mm and is matched with the guide pin 5. The diameter of the rear end is φ4.1mm, which is matched with the drill sleeve 3. By continuously...

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Abstract

The invention relates to a processing method for a large sandwich blind hole structure reverse hole of an aircraft. The reverse hole processing is carried out through the steps of making an initial hole, positioning a drill template, reaming, making a final hole and inspecting, etc. After the operation of the large sandwich blind hole reverse hole, the coaxiality and the hole diameter of the holemeet the engineering requirements.

Description

Technical field [0001] The invention relates to a processing method, in particular to a processing method for reverse holes of a large sandwich blind hole structure of an aircraft, belonging to an aircraft processing method. Background technique [0002] In the process of aircraft assembly, the blind hole reverse hole operation is often encountered. The traditional reverse hole method is to drill and ream the structure without holes through the existing final hole in the structure and use the drill sleeve to drill and ream the structure without holes. Drill sleeve, use the final hole drill reamer to the final hole. Using this method to counter holes will bring two risks. First of all, limited by the minimum thickness of the drill sleeve hole wall, a cutting allowance of at least 3mm in diameter is left before the final hole, which will cause the last cut to be too large, causing the hole diameter to be easily out of tolerance. Finally, for the large thickness of the sandwich Fo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23B41/00B23B47/28
CPCB23B41/00B23B47/287
Inventor 王铁林韩文强刘振山杨继光李论李艳军贾晓亮
Owner AVIC SAC COMML AIRCRAFT
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