Process joint for aircraft panel component assembly, and assembly method

A technology for process joints and aircraft wall panels, applied in aircraft parts, thin plate connections, connecting components, etc., can solve the problems of low efficiency, low assembly accuracy, low repeatability, etc., and achieve accurate position, improve production efficiency, and high product accuracy. Effect

Inactive Publication Date: 2016-06-22
HARBIN
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The products assembled in this way have low assembly accuracy and inaccurate positions, which will cause misalignment of the shape of the skin and the shape of the skeleton, coupled with the shape error of the skin itself, resulting in large riveting

Method used

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  • Process joint for aircraft panel component assembly, and assembly method
  • Process joint for aircraft panel component assembly, and assembly method
  • Process joint for aircraft panel component assembly, and assembly method

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Embodiment Construction

[0015] A process joint used for the assembly of aircraft wall panels, which is fixedly connected by a connecting plate 3 and a positioning plate 4, wherein on the connecting plate 3 there is a connecting hole 6 that can be connected to the aircraft wall panel, and on the positioning plate 4 There is a positioning hole 7 that can be connected with the locator 2, and the process joint is positioned and connected on the aircraft wall by adjusting the locator 2. There is also a reinforcing rib 5 between the connecting plate 3 and the positioning plate 4 .

[0016] A method for positioning and assembling aircraft panel parts, using the above-mentioned process joints, first setting four process joints at the determined positions of the aircraft panel parts through the locator 2, and passing through the connecting holes on the connecting plate 3 of the process joints Drill holes on the aircraft panel parts; secondly, connect the connecting plate of the process joint with the aircraft...

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Abstract

The invention belongs to the technical field of aircraft manufacturing, relates to assembly for aircraft body panel components, and specifically relates to a process joint for aircraft panel component assembly, and an assembly method. An aircraft body is generally formed by carrying out riveting assembly on a plurality of panel components, the aerodynamic shapes of modern aircrafts are mainly complex hyperboloids, and the shapes of surface covering parts, that is, skin panels, of the modern aircrafts, are also mostly hyperboloids, thus difficulty is brought to assembly location. The invention designs a process joint for aircraft panel component assembly, and an assembly method, for keeping accurate riveting assembly positions of the panel components and increasing the assembly efficiency. Assembly location among the panel components is carried out by virtue of the method, a digitized assembly method is realized, allowance reservation is not required for the panel components, and field manual repair is not needed any more; the assembled products are high in accuracy and accurate in position; and the production efficiency is also greatly improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft manufacturing and is used for the assembly of aircraft fuselage panel components, in particular to a process joint and an assembly method of aircraft panel components. Background technique [0002] Aircraft fuselages are generally assembled by riveting multiple panel parts. The aerodynamic shape of modern aircraft is mainly a complex hyperboloid. difficult. There is no reliable positioning of the aircraft panel parts on the assembly tooling, only the shape of the skin, the shape of the skeleton and the positioning clamps are used, and the skin of the wall panel also needs to leave a margin. The operator adjusts the position of the skin based on experience, and uses the clamps , rubber rope and C-shaped pliers to tighten the skin and the frame beam skeleton of the fuselage, drill out the rivet holes, insert the spring pin, manually draw the edge line, determine the skin margin to be removed, and ...

Claims

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Application Information

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IPC IPC(8): B23P19/00F16B5/00
CPCB23P19/00B23P2700/01F16B5/0004
Inventor 张岩曲才王明凯
Owner HARBIN
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