Manufacturing method of wing-body integrated honeycomb sandwiched composite material skin

A composite material and wing-body fusion technology, which is applied in the field of composite material molding in the aviation industry, can solve the problems of complex skin shape, difficult control of honeycomb edge, and high cost, so as to shorten the curing cycle, eliminate the offset defect of honeycomb sandwich core, reduce the The effect of solidifying costs

Inactive Publication Date: 2014-07-16
NORTHWESTERN POLYTECHNICAL UNIV
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AI Technical Summary

Problems solved by technology

However, the skin shape of the wing-body fusion honeycomb sandwich composite material is relatively complex, and the cost of secondary curing and tertiary curing is high, and the cycle is long; when co-curing, the position of the honeycomb and the edge of the honeycomb are not easy to control, and the honeycomb core will shift. Defects

Method used

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  • Manufacturing method of wing-body integrated honeycomb sandwiched composite material skin
  • Manufacturing method of wing-body integrated honeycomb sandwiched composite material skin
  • Manufacturing method of wing-body integrated honeycomb sandwiched composite material skin

Examples

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Embodiment Construction

[0030] The present invention is a process method for integral solidification and molding of wing-body fusion honeycomb sandwich composite materials. The process method will be further explained in conjunction with an example of a wing-body fusion skin engineering example of a certain model.

[0031] Step 1: Prepare a hot-pressing mold for the skin of the wing-body fused honeycomb sandwich composite material, and the mold includes a frame-type support structure and a mold surface. In practical engineering applications, before the hot-pressing mold is prepared, the design of the mold, the honeycomb anti-slip rib and the stiffness and strength analysis of the mold are carried out by CAD three-dimensional software and CAE finite element software: the honeycomb sandwich composite skin is designed by UG software parts mold, such as figure 1 As shown, 32 anti-slip positioning holes 1 with a diameter of 0.5 mm are designed on the mold surface. The frame structure is mainly to meet the...

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Abstract

The invention provides a manufacturing method of a wing-body integrated honeycomb sandwiched composite material skin. The manufacturing method comprises the steps of preparing a hot-pressing die of the wing-body integrated honeycomb sandwich composite material skin, laying and hot-pressing, wherein a plurality of antiskid positioning holes having the diameter of 0.5mm are formed in the profile of the die along honeycomb mounting edges. Flexible honeycomb antiskid positioning ribs are mounted on the profile of the die and a beneficial solidification process in a hot-pressing tank is obtained by virtue of lots of tests, so that shortcomings caused by the deviation of a honeycomb sandwich in a co-solidification process are eliminated thoroughly, the solidification period is shortened and the solidification cost is reduced.

Description

technical field [0001] The invention relates to the technical field of composite material forming in the aviation industry, in particular to a method for manufacturing a skin of a wing-body fused honeycomb sandwich composite material. Background technique [0002] Advanced composite materials have excellent properties such as high specific strength, high specific modulus, fatigue resistance, multi-functionality, anisotropy, designability, identity of material and structure, etc. Since their advent in the 1960s, advanced composite materials have been very It will soon be widely used and become one of the four major aerospace materials. [0003] There are many forms of composite molding process, such as hand lay-up molding, winding molding, extrusion molding, RTM molding, VARI molding, autoclave molding, compression molding, etc. In the aviation field, relatively more autoclave molding is used. craft. At present, the autoclave curing process is divided into secondary curing,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34
CPCB29C70/342B29C70/38
Inventor 王海丞薛小平邱飞周世平张雅丹张磊
Owner NORTHWESTERN POLYTECHNICAL UNIV
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