Composite material skin net edge coordination tools and assembling method for skins

A composite material and side coordinator technology, applied in aircraft assembly, ground installation, transportation and packaging, etc., can solve problems such as difficulty in shortening assembly cycle, low assembly efficiency, and inconvenient operation, so as to reduce individual operation errors and improve assembly Efficiency, avoiding time-consuming and labor-intensive effects

Active Publication Date: 2015-11-11
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to its material characteristics, the processing and assembly of composite skin is somewhat different from that of metal skin, and it is even more complicated. It is impossible to use the previous processing and assembly process of metal skin to determine the net edge of composite skin.
[0003] The existing technology has the following problems: First, since the composite material skin is integrally formed, the shape accuracy of the part determines the aerodynamic shape accuracy of the aircraft to a large extent, but the existing composite material skin will produce certain deformation after molding Therefore, it is impossible to accurately determine the accuracy of the position of the net edge in the state of the part; second, composite materials are difficult-to-machine materials. Compared with metal materials, it is time-consuming and labor-intensive to repair and grind t

Method used

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  • Composite material skin net edge coordination tools and assembling method for skins
  • Composite material skin net edge coordination tools and assembling method for skins
  • Composite material skin net edge coordination tools and assembling method for skins

Examples

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Example Embodiment

[0035] Composite upper skin assembly tooling, including upper skin assembly tooling 16, including upper skin outer shape card board 3, upper skin inner shape card board, frame 5, upper skin clean edge drawing template 1, upper skin clean edge coordinator 2;

[0036] There are multiple upper skin shape clips 3, and the inner surface of the upper skin shape clip 3 is matched with the upper surface of the aircraft; the upper skin inner shape clip is used to press the skin to the upper skin The outer shape card board 3, the upper skin outer shape card board 3 and the upper skin inner shape card board are fixed on the frame;

[0037] The inner-shaped card plate of the upper skin can be compressed by using a commonly used inner card plate.

[0038] see figure 1 , the upper skin clear edge drawing template 1 is a flat plate structure, the upper skin clear edge drawing template 1 and the end face of the contact end of the skin match the outer surface of the skin, and the upper skin ...

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PUM

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Abstract

The invention relates to composite material skin net edge coordination tools and an assembling method for skins. The method comprises following steps: 1) arranging coordinators on the skin assembling tools, wherein the coordinators are provided with coordination holes; 2) mounting the skins on corresponding assembling racks, and prepositioning and clamping the skins; 3) drilling technologic holes in the skins through the coordination holes in the net edge coordinators; 4) positioning and fixing the skins on the corresponding racks through the coordination holes in the skins; 5) drawing net edge lines on the surfaces of the skins by the use of line drawing templates; 6) performing trimming based on the net edge lines after the skins are disassembled; and 7) assembling and positioning the different skins on an assembly frame through butt joint coordination holes. According to the invention, the net edge size of the skins are determined through the cooperation of the net edge coordinators and the line drawing templates, and the skins are positioned through the butt joint coordination holes in an assembling process, so that the accuracy of the net edge size of the composite material skins is improved, the structure of the frame is simplified, the operation is easy and visual, and the assembling efficiency is improved.

Description

technical field [0001] The invention relates to a composite material skin clean edge coordination tooling and assembly method suitable for aircraft and other products, which is suitable for high-quality assembly of composite material aircraft skin, improves the processing and assembly efficiency of composite material skin clean edge, and the seam gap between skins precision, etc., which belong to the technical field of composite material component processing and assembly. Background technique [0002] With the continuous improvement of aerodynamic shape, strength and other performance requirements of aircraft and other products, composite materials have also been more and more widely used. A large number of composite material structures are used in the fuselage, wings and other parts, especially the shape of the airframe is composed of several large-scale overall composite skins. As a key part of the aerodynamic shape, its shape is complex, its size range varies greatly, an...

Claims

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Application Information

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IPC IPC(8): B64F5/00B64F5/10
Inventor 王新张毅王绍强张鹏王爱春刘宏涛王新星
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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