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Bonding method and bonding mold of variable thickness composite skeleton and skin

A composite material and bonding method technology, which is applied in the field of resin-based structural composite material molding, can solve the problems of inability to guarantee the quality of the bonding interface and the aerodynamic shape requirements, the debonding shape dimensions, and the tolerance, and achieve the guarantee of the aerodynamic shape requirements, Improve the quality of bonding and the effect of accurate positioning

Active Publication Date: 2020-11-20
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

[0004] For the conventional skeleton-skin structure, the skeleton is usually made of metal, and the fixed connection between the skeleton and the skin is generally realized by fasteners, while for figure 1 In the skeleton-skin structure shown, both the skeleton and the skin are composite materials. From the perspective of weight reduction, it is preferable to choose the fixed combination of the two in the form of bonding. Since the contact surface between the skeleton and the skin is a double-curvature surface, Moreover, during the molding process of the two, there is a certain deformation of the contact surface, which cannot guarantee the quality of the bonding interface and the requirements of the aerodynamic shape. If the bonding glue is directly coated on the contact surface for bonding, it is prone to debonding and out-of-tolerance dimensions question

Method used

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  • Bonding method and bonding mold of variable thickness composite skeleton and skin
  • Bonding method and bonding mold of variable thickness composite skeleton and skin
  • Bonding method and bonding mold of variable thickness composite skeleton and skin

Examples

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Embodiment 1

[0073] Such as figure 1 As shown, the present embodiment provides a composite skeleton skin structure for aircraft wings, including a whole skeleton 100, an upper skin 300 and a lower skin 200, and the skeleton structure consists of an upper frame, a lower frame and multiple sets of heights Different vertical plates 3 are formed, wherein the upper frame is surrounded by a plurality of first frame bars 11 to form a multi-grid structure, and the lower frame is surrounded by a plurality of second frame bars 22 to form a multi-grid structure. The first frame bars 11 and the second frame bars The frame bars 21 correspond one-to-one, and a vertical plate 3 is arranged between the corresponding first frame bar 11 and the second frame bar 21, and forms a structure with an I-shaped vertical section. The upper surface of the upper frame and the lower frame of the lower frame The surfaces are all double-curvature surfaces, and accordingly, the upper skin 300 and the lower skin 200 are al...

Embodiment 2

[0089] Such as Figure 4 As shown, the present embodiment provides a kind of composite skeleton skin structure that is used for aircraft empennage, comprises integral skeleton 100, upper skin 300 and lower skin 200, and skeleton structure is made of upper frame, lower frame and multiple sets of different heights. The vertical plate 3 is formed, wherein the upper frame is surrounded by a plurality of first frame bars 11 to form a multi-grid structure, and the lower frame is surrounded by a plurality of second frame bars 22 to form a multi-grid structure. The first frame bars 11 and the second frame The bars 21 correspond one-to-one, and a vertical plate 3 is arranged between the corresponding first frame bar 11 and the second frame bar 21, 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 Both are double-curvature surfaces. Correspondingly, the upper skin 300 and the lower skin 200 are also dou...

Embodiment 3

[0105] Such as Figure 5 As shown, the present embodiment provides a composite skeleton skin structure of an aircraft wing test piece, comprising a whole skeleton 100, an upper skin 300 and a lower skin 200, and the skeleton structure consists of an upper frame, a lower frame and multiple sets of heights Different vertical plates 3 are formed, wherein the upper frame is surrounded by a plurality of first frame bars 11 to form a multi-grid structure, and the lower frame is surrounded by a plurality of second frame bars 22 to form a multi-grid structure. The first frame bars 11 and the second frame bars The frame bars 21 correspond one-to-one, and a vertical plate 3 is arranged between the corresponding first frame bar 11 and the second frame bar 21, and forms a structure with an I-shaped vertical section. The upper surface of the upper frame and the lower frame of the lower frame The surfaces are all double-curvature surfaces, and accordingly, the upper skin 300 and the lower s...

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Abstract

The invention discloses a variable-thickness composite material framework and skin bonding method and a bonding mold, and belongs to a resin-based structural composite material forming technology. Thebonding method comprises the following steps of processing a second surface of the framework and a first surface of the skin, the first surface and the second surface are opposite in orientation, anda hot-melt prepreg is adopted, the surface of the adhesive film is paved on the framework to obtain a first to-be-adhered framework; and a first side baffle is arranged on the periphery of a first appearance mold, a cavity of the framework and the skin bonding piece is formed, the skin is placed in the cavity, so that the second surface of the skin and the upper surface of the first profile moldare aligned and attached, then the first to-be-bonded framework is stacked on the skin, finally the elastic layer of a first cover plate is buckled with the first surface of the framework, the first side baffle plate is fixed to the first cover plate, curing is carried out, and bonding is completed. According to the variable-thickness composite material framework and skin bonding method, the framework skin structure can be bonded and formed, the bonding quality is high, and the pneumatic appearance of the product is effectively guaranteed.

Description

technical field [0001] The invention belongs to the molding technology of resin-based structural composite materials, and in particular relates to a high-temperature-resistant resin-based composite material double-curvature frame-skin structure bonding mold and a molding method. 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 molding technology of structural composite materials has become the focus. Structural composite material technology is the key supporting technology of my country's transportation system. An important factor of quality and reliability, its performance and level have a very important impact on the development of aerospace technology and the development process of aerospace products. [0003] As my country's reusable aircraft proposes lightweight, integrated, and high-temperature-resistant requirements, co...

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 赵锐霞张大海何析峻唐占文张毅孙宏杰
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH