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A positioning method and a processing method for an aircraft skin assembly hole

A technology of aircraft skinning and positioning method, which is applied in the direction of metal processing equipment, metal processing machine parts, manufacturing tools, etc. It can solve the problems of poor efficiency of manual marking, frequent design changes, and long change cycle, so as to reduce the difficulty of design, Improve display clarity, reduce design difficulty and cost

Active Publication Date: 2021-09-03
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in the initial stage of aircraft model development, the design changes frequently, and the corresponding skin molds also need to be redesigned and manufactured, which is costly and takes a long time to change.
[0005] The assembly hole positioning method of manual scribing is a relatively original hole positioning method, but the efficiency of manual scribing is poor and the precision is low, so it is gradually replaced by other assembly positioning methods

Method used

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  • A positioning method and a processing method for an aircraft skin assembly hole
  • A positioning method and a processing method for an aircraft skin assembly hole
  • A positioning method and a processing method for an aircraft skin assembly hole

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Embodiment 1

[0037] see figure 1 As shown, the positioning method of the aircraft skin assembly hole provided by the embodiment of the present invention, the chordwise length of the aircraft skin is 2m, the spanwise length is 10m, and a fixing hole 21 is respectively set at the corners of the aircraft skin 2, totally four The four fixing holes 21 are used to install the aircraft skin 2 on the assembly frame 1 through the four fixing holes 21 . A positioning hole is respectively set at the assembly holes of the four corners of the aircraft skin 2 and the internal rib and the beam, four positioning holes are arranged at the center of the aircraft skin, and the target 3 is set at the eight positioning holes. The eight targets 3 realize the connection of the spatial position of the aircraft skin 2 with the laser projection system. The position coordinates of the target 3 are collected, and a projection file is prepared by using a computer according to the position coordinates of the target 3,...

Embodiment 2

[0052] The second embodiment is basically the same as the first embodiment, and the similarities will not be described in detail. The difference is that the aircraft skin has a chord length of 6m and a span length of 15m, at the four corners of the aircraft skin 2 and the internal ribs and beams. One positioning hole is arranged at each assembly hole of the aircraft skin 2, and eleven positioning holes are arranged in the center of the aircraft skin 2. Targets 3 are set at the fifteen positioning holes, and the aircraft skin 2 is realized through the fifteen targets 3. The spatial location is connected with the laser projection system. For an aircraft skin of this size class, the laser projection system consists of eight laser projectors 4, see image 3 As shown, eight laser projectors 4 are arranged in two rows in the chord upward, and the number of laser projectors 4 in each row is the same as four, and each row of laser projectors 4 is arranged at equal intervals to realize...

Embodiment 3

[0056] Present embodiment three is basically the same as embodiment one, and the similarities will not be described in detail. The difference is that the aircraft skin 2 has a chord length of 2m and a span length of 6m. One positioning hole is set at each assembly hole in the corner, two positioning holes are arranged in the center of the aircraft skin, and targets 3 are set at the six positioning holes, and the spatial position of the aircraft skin 2 is realized through the six targets 3 Interface with laser projection system. For the aircraft skin 2 of this size class, the laser projection system includes two laser projectors 4, and the two laser projectors 4 are arranged at equidistant intervals and arranged in a row.

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Abstract

The invention relates to the technical field of aircraft skin assembly, in particular to a positioning method and a processing method for an aircraft skin assembly hole. This positioning method adopts the digital positioning method of laser projection, and does not need to manufacture a special drilling template for drilling positioning, which saves costs, especially in the early stage of development when the aircraft skin structure design needs to be changed frequently. When the design is changed, only the laser It is easy to change and implement the assembly hole position by changing the projection file, effectively improving the positioning efficiency and reducing the design difficulty and cost. The processing method adopts a digital positioning method, which can efficiently and accurately process positioning holes, especially for the early stage of development when the aircraft skin structure design needs to be changed frequently, and can quickly locate and process, effectively improving efficiency and reducing costs.

Description

technical field [0001] The invention relates to the technical field of aircraft skin assembly, in particular to a positioning method and a processing method for an aircraft skin assembly hole. Background technique [0002] The connection between the aircraft skin and the internal ribs and beams of the aircraft is generally carried out on the assembly frame, and the locators set on the assembly frame are used to fix the skin and internal beams and ribs on the frame. Then determine the position of the assembly hole by setting the drilling template, manual scribing or mold scribing, etc. [0003] In practical engineering applications, it is an efficient way to locate the assembly holes through the drilling template for products whose design has been finalized. However, in the early stage of aircraft model development, the design changes frequently, and the corresponding drilling template also needs to be redesigned. , manufacturing, high cost and long change cycle. [0004] F...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23B41/00B23B47/00B23Q17/24
CPCB23B41/00B23B47/00B23Q17/2423
Inventor 缪伟民路建军张铁夫唐中华
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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