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A method and device for positioning and assembling parts and composite material skeleton skin structure

A composite material and assembly method technology, applied in the field of resin-based structural composite material molding, can solve the problems of inability to guarantee the shape and surface accuracy, inability to determine the installation datum, etc., to ensure the aerodynamic shape requirements, improve the interface bonding quality and the shape and dimension accuracy. , to avoid the effect of debonding of the contact surface

Active Publication Date: 2021-04-13
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

[0005] The purpose of the present invention is to provide a method and device for positioning and assembling parts and composite skeleton skin structures, which can quickly find the precise installation position of parts and skeletons, and avoid problems due to inability to The problem that the installation datum cannot be determined due to the guarantee of shape and surface accuracy

Method used

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  • A method and device for positioning and assembling parts and composite material skeleton skin structure
  • A method and device for positioning and assembling parts and composite material skeleton skin structure
  • A method and device for positioning and assembling parts and composite material skeleton skin structure

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Embodiment 1

[0065] Such as figure 1 As shown, the present embodiment provides a composite skeleton skin structure for aircraft empennage, comprising an integral skeleton, a metal rudder shaft and a lower skin 200, and the skeleton structure consists of an upper frame, a lower frame, and a plurality of groups of different heights. The upper frame is composed of a plurality of first frame bars to form a multi-grid structure, and the lower frame is surrounded by a plurality of second frame bars 2 to form a multi-grid structure. The first frame bars and the second frame bars 2 are in one-to-one correspondence , a vertical plate 3 is arranged between the corresponding first frame bar and the second frame bar 2, and forms a structure with an I-shaped vertical section, the upper surface of the upper frame and the lower surface of the lower frame are double-curvature surfaces, Correspondingly, the lower skin 200 is also a double-curvature surface, and the skeleton skin structure is made of carbon...

Embodiment 2

[0083] Such as Figure 6 As shown, the present embodiment provides a composite skeleton skin structure for aircraft wings, including an integral skeleton and a lower skin 200, and the skeleton structure is composed of an upper frame, a lower frame and multiple sets of vertical plates 3 with different heights , wherein the upper frame is surrounded by a plurality of first frame bars to form a multi-grid structure, and the lower frame is surrounded by a plurality of second frame bars 2 to form a multi-grid structure. The first frame bars and the second frame bars 2 correspond one-to-one. A vertical plate 3 is provided between the corresponding first frame bar and the second frame bar 2, and forms a structure with an I-shaped vertical section. The upper surface of the upper frame and the lower surface of the lower frame are both double-curvature surfaces, correspondingly , the lower skin 200 is also a double-curvature surface, and the skeleton skin structure is made of carbon fib...

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Abstract

The present invention discloses a positioning and assembly method and device for the skin structure of parts and composite materials, which belongs to the formation technology of resin base structure composite materials.The method includes: first stack the skin and skeleton on the working surface of the shape mold in turn, and fix it tightly.The parts are fixed through the positioning department, and the relative position of the fixed seat and the positioning surface is adjusted until the fixed parts should be adapted to the skeleton, and then the described part is installed on the skeleton, demolishedThe parts positioner and shape mold of the parts are completed to complete the positioning assembly of the parts and the skeleton.The present invention can quickly find the precise installation position of the parts and skeleton, and avoid the problem that the installation benchmark cannot be determined when the skin cannot be determined when the skin cannot ensure that the surface accuracy cannot be determined when the skin is not guaranteed.

Description

technical field [0001] The invention belongs to the molding technology of resin-based structural composite materials, and in particular relates to a method for assembling and positioning a part and a double-curvature frame skin structure of a high-temperature-resistant resin-based composite material. Background technique [0002] With the rapid development of aerospace structural composite materials and the further requirements of new models for structural weight reduction and high efficiency, the overall molding technology of structural composite materials has become the focus, and the resulting assembly technology of the overall skeleton and skin has become the focus. As the key supporting technology of my country's transportation system, material technology is an important factor determining the performance, quality and reliability of aerospace products. Its performance and level have a very important impact on the development of aerospace technology and the development pro...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/54
CPCB29C70/342B29C70/54
Inventor 赵锐霞王新张大海何析峻张毅
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH