Forming method of composite material of ultra-large size special honeycomb structure

A composite material and honeycomb structure technology, applied in the field of composite material manufacturing and molding, can solve the problems of unusable, pressurized, and untransportable large structural parts

Active Publication Date: 2009-05-06
BEIJING AVIATION MATERIAL INST NO 1 GRP CORP CHINA AVIATION IND
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  • Application Information

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Problems solved by technology

[0002] There are many forms of molding process for composite materials, such as: autoclave heating and pressure molding, compression molding, RTM injection molding, vacuum-assisted injection molding, pultrusion molding, winding molding, etc., temperature, pressure, time, working space Limitation is the main parameter of this type of equipment, but these formi...

Method used

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Embodiment

[0007] The size of the product is 36 meters long, 14 meters wide, 20 mm thick, with a total area of ​​504 square meters and a total weight of 1.6 tons. The honeycomb unit size is 2.4×1.2 meters, and a total of 180 honeycomb units are required.

[0008] (1) According to the size of the composite material forming part, trim the honeycomb unit member of 2.4 × 14 meters respectively, glue a layer of nylon gauze on the end face of the honeycomb unit member, change the original linear and hollow surface, and enhance the bonding strength of the honeycomb end face; (2), glue the skin on the upper and lower surfaces of each honeycomb unit component and reserve skin overlapping parts and honeycomb overlapping parts on both sides of the honeycomb unit component, on the upper surface side of the honeycomb unit component Reserving a skin overlapping part, reserve a skin overlapping part on the opposite side of the lower surface of the honeycomb unit component and the upper surface skin over...

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Abstract

The invention belongs to the technical field of composite material manufacturing and shaping and relates to a shaping method of an oversize composite material part with special honeycomb cellular structure. The method includes the following steps of: (1) prefabricating a honeycomb cell component according to the size of a composite material shaping part; (2) cementing a coating on the upper surface and the lower surface of each honeycomb cell component and reserving a coating overlapping part and a honeycomb overlapping part respectively at two sides of each honeycomb cell component; (3) cementing a nylon gauze on the upper surface and the lower surface of the split joint seam in each honeycomb cell component; (4) encapsulating the honeycomb cell component after adhesion in a vacuum bag to be pressurized and solidified; and (5) continuing connection on the encapsulated vacuum bag to extend the size so as to encapsulate and pressurize the honeycomb cell component after adhesion in the vacuum bag. The invention separately prepares the honeycomb cell components, uses an oversize vacuum bag to block up the integral shaping of pressurization, satisfies the overall rigidity and flexibility, has no unrecoverable fold or crack in the cementing seam in bending and achieves the cementation and solidification requirements in normal temperature.

Description

technical field [0001] The invention belongs to the technical field of composite material manufacturing and molding, and relates to a molding method for super-large special honeycomb structure composite material parts. Background technique [0002] There are many forms of molding process for composite materials, such as: autoclave heating and pressure molding, compression molding, RTM injection molding, vacuum-assisted injection molding, pultrusion molding, winding molding, etc., temperature, pressure, time, working space Limitation is the main parameter of this type of equipment, but these forming processes and equipment cannot be used for large structural parts. There is no corresponding large-scale equipment, and such super-sized parts cannot be heated, pressurized, and solidified in the equipment, and cannot be transported. In the case of exceeding the size of the existing equipment and the special oversized parts cannot be transported, it can only be made on site. Co...

Claims

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Application Information

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IPC IPC(8): B29C70/00B29C70/44
Inventor 刘京林白树成何鲁林梁滨温磊张华
Owner BEIJING AVIATION MATERIAL INST NO 1 GRP CORP CHINA AVIATION IND
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