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Used for aircraft composite materials, fonts, tendon wall boards, co -adhesive processing methods

A composite material and reinforced wall panel technology, which is applied in the field of composite material manufacturing, can solve the problems of difficulty in ensuring thickness uniformity, film and resin flow, and long truss axis offset, etc. The effect of uniform force and guarantee of correctness

Active Publication Date: 2021-10-15
COMAC +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a process method for co-gluing and forming of I-shaped reinforced wall panels of aircraft composite materials. Problems that seriously affect the quality of the parts, such as truss sag, long truss axis deviation, adhesive film and resin flowing around in the skin surface, and difficulty in ensuring uniform thickness, can also ensure the formation of a better quality of the glued surface

Method used

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  • Used for aircraft composite materials, fonts, tendon wall boards, co -adhesive processing methods
  • Used for aircraft composite materials, fonts, tendon wall boards, co -adhesive processing methods
  • Used for aircraft composite materials, fonts, tendon wall boards, co -adhesive processing methods

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Embodiment Construction

[0030] The implementation and use of the preferred embodiments of the present invention will be discussed in detail below in conjunction with the accompanying drawings. It should be understood, however, that the specific embodiments discussed are merely illustrative of specific ways to make and use the invention and do not limit the scope of the invention. The expression of the structural position of each component such as up, down, left, right, top, bottom, etc. in the description is not absolute but relative. These directional expressions are appropriate when the various components are arranged as shown in the drawings, and when the positions of the various components in the drawings are changed, these directional expressions are also changed accordingly.

[0031] Such as Figure 1 to Figure 5 Shown in, according to the processing method of composite I-shaped reinforced wall panel of the present invention co-glued forming is realized through the following steps:

[0032] (...

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Abstract

The invention provides a process method for the co-gluing and forming of I-shaped reinforced wall panels of aircraft composite materials, which comprises the steps of: paving the skin; placing the process cover plate: placing the process cover plate on the paved skin Above, the process cover plate has a plurality of reserved slots for placing I-shaped stringers; stringer preparation; stringer pre-assembly; stringer and skin bonding combination; stringer mandrel filling; Vacuum bagging; curing; demoulding.

Description

technical field [0001] The invention belongs to the field of composite material manufacturing, and in particular relates to a process method for co-gluing forming of I-shaped reinforced wall panels of aircraft composite materials. Background technique [0002] The composite material reinforced panel structure is composed of skin and I-shaped long trusses, which can obtain greater structural rigidity and buckling resistance, and improve structural efficiency. The co-gluing process is used to manufacture composite material reinforced wall panels, and the I-shaped stringer is bonded to the skin through the adhesive film, which simplifies the traditional riveting connection method, reduces the number of fasteners, and has better performance. Great reduction of assembly cost and weight reduction effect. Compared with the process of co-curing, co-gluing can not only reduce the difficulty of mold design and manufacturing, but also reduce the risk of overall scrapping of parts; com...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/54B29L31/30
CPCB29C70/342B29C70/545B29L2031/3076
Inventor 刘卫平卢鑫姜丽萍李志远张冬梅王健
Owner COMAC
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