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Large-thickness honeycomb sandwich structure and forming anti-slip process method

A technology of honeycomb interlayer and process method, which is applied in the field of aerospace composite material manufacturing, can solve the problems of restricting the application of large-thickness honeycomb sandwich structure, honeycomb collapse, deformation, etc., and achieve the effect of large practical application value, low cost and strong rigidity

Inactive Publication Date: 2021-11-09
THE RES INST FOR SPECIAL STRUCTURES OF AERONAUTICAL COMPOSITE AVIC
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Problems solved by technology

[0003] However, since the lateral compressive strength of the honeycomb is lower than the curing pressure of the prepreg when the sandwich structure is formed, during the forming process of the large-thickness honeycomb sandwich structure, the honeycomb in the slope area will collapse, deform, shrink and slip, which seriously limits the large thickness. Application of honeycomb sandwich structure

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  • Large-thickness honeycomb sandwich structure and forming anti-slip process method

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Embodiment Construction

[0032] This part is the embodiment of the present invention, which is used to explain and illustrate the technical solution of the present invention.

[0033] An anti-slip process method for forming a large-thickness honeycomb sandwich structure. In the manufacture of a large-thickness honeycomb sandwich structure, a pre-laying and curing step is added, and the adhesive layer and prepreg are laid on the slope area of ​​the honeycomb and cured first, and then partially cured The honeycomb with good adhesive layer and prepreg is used as the sandwich material to prepare the honeycomb sandwich structure.

[0034] Further, it specifically includes the following steps:

[0035] Step 1, according to the size requirements of the honeycomb core material of the large-thickness honeycomb sandwich structure, the honeycomb is chamfered to generate a honeycomb slope;

[0036] Step 2, deforming the large-thickness honeycomb according to the requirements of the honeycomb profile;

[0037] S...

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Abstract

The invention belongs to the technical field of aviation composite material manufacturing, and discloses a large-thickness honeycomb sandwich structure and a forming anti-slip process method. In the manufacturing process of the large-thickness honeycomb sandwich structure, the step of pre-laying and curing is added, an adhesive layer and prepreg are laid in the bevel area of a honeycomb and cured firstly, and then the honeycomb sandwich structure is prepared by taking the partially cured honeycomb of the adhesive layer and the prepreg as a sandwich material. According to the structure and the method, the problems of collapse, deformation and shrinkage of honeycombs in the preparation process of the large-thickness honeycomb sandwich structure are solved, the preparation process level of the large-thickness honeycomb sandwich structure is improved, a large practical application value is achieved, new tools and machined parts are not added, implementation is easy, and the cost is low; The honeycomb structure manufactured by the structure and the method disclosed by the invention has stronger rigidity in an easily-deformed area of the inclined plane.

Description

technical field [0001] The invention belongs to the technical field of aviation composite material manufacturing, and relates to a fixing process method of a honeycomb sandwich structure, in particular to a large-thickness honeycomb sandwich structure and a molding anti-slip process method. Background technique [0002] In the application process of aircraft composite materials, because the honeycomb sandwich structure has the characteristics of high specific strength, high specific modulus, and light weight, it is an important structural form in the manufacture of aircraft composite materials. With the improvement of strength and weight reduction requirements, aircraft wing-body fairings need to be designed in the form of a large-thickness honeycomb sandwich, and this structure has been applied in Boeing aircraft. [0003] However, since the lateral compressive strength of the honeycomb is lower than the curing pressure of the prepreg when the sandwich structure is formed, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/54B29C35/02
CPCB29C70/34B29C70/54B29C70/545B29C35/02
Inventor 杨茂伟贾顺利郝磊
Owner THE RES INST FOR SPECIAL STRUCTURES OF AERONAUTICAL COMPOSITE AVIC
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