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A positioning structure and positioning method of a surface insert

A technology of positioning structure and positioning method, which is applied in the field of preparation of composite materials with surface inserts, can solve the problems of inability to achieve accurate positioning of inserts, increase in weight of composite materials, and inaccurate compensation effects, and achieve good promotion and application value and improve Production efficiency and the effect of improving the pass rate

Active Publication Date: 2021-10-15
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, for the positioning of surface metal inserts in composite structural parts, conventional mold positioning pins are used, and it is impossible to adjust the position deviation of inserts during mold loading; especially for multiple inserts, accurate positioning is required from different normal directions During operation, this method cannot achieve accurate positioning of the insert, and deviations are prone to occur
In order to make up for the position deviation in the molding process, the size of the metal parts is generally increased in the existing process, and the compensation effect is not accurate enough. However, increasing the size of the metal parts will increase the weight of the composite material, which cannot meet the existing weight reduction, Design Requirements for Precise Positioning

Method used

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  • A positioning structure and positioning method of a surface insert
  • A positioning structure and positioning method of a surface insert
  • A positioning structure and positioning method of a surface insert

Examples

Experimental program
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Effect test

Embodiment

[0052] Carry out accurate positioning of 10 outer layer metal inserts 3 in an L-shaped cross-section composite quilted beam structure 2. The length of the L-shaped cross-section quilted beam structure is 1000 mm, and each side of the L-shaped cross-section has 5 metal inserts on the outer layer.

[0053] Manually lay carbon fiber plies layer by layer in the lower half-mold 1 of the forming mold to prepare an L-shaped cross-section quilted beam prefabricated body. The fiber plies whose outer layer needs to be embedded with metal inserts need to be pre-drilled according to the designed position (10 holes in total) ;

[0054] After the fiber layup is complete, metal inserts are placed in the openings of the layup;

[0055] Assemble the upper half-molds 1 and 4, align the upper and lower half-molds and insert the positioning pin 5, install the fastening bolts to ensure that the upper and lower half-molds are closed in place, and the gap between the joint surfaces is less than 0.05...

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Abstract

The invention provides a positioning structure and a positioning method for a surface insert, including a surface insert, a central positioning pin, a tapered hole structure, a tapered positioning pin, an outer pressure plate structure and a top plate structure. The invention can maximize the realization of the goal of reducing the weight of the structure, and can realize the deviation adjustment and accurate positioning of the inserts in different normal directions one by one during the one-time forming process of the components.

Description

technical field [0001] The invention relates to a positioning structure and a positioning method of a surface insert, and belongs to the technical field of preparation of composite materials containing surface inserts. Background technique [0002] Due to its outstanding features of light weight, high strength and strong designability, composite materials have been widely used in military and civilian fields since their appearance in the mid-1960s, such as aerospace, weaponry, sports and leisure, infrastructure facilities, automobile and shipbuilding industries , biological engineering, etc., especially in various weapons and equipment (such as military aircraft, missiles, etc.), it plays a vital role in promoting lightweight and high performance. The use of advanced composite materials in aerospace structures can reduce weight by 20-30%, which is an effect that other advanced technologies cannot achieve. Therefore, composite materials are increasingly used in the aerospace ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/68B29C33/12B29K705/00
CPCB29C33/126B29C70/681B29K2705/00
Inventor 田正刚王国勇柳晓辉朱八一狄海笑
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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