Integrated co-curing forming technology method for composite material multi-beam box section

A technology of composite materials and curing molding, which is applied in the field of overall co-curing molding technology of composite multi-beam box sections, can solve the problems of unguaranteed quality of the whole box section, difficulty in calculating the expansion amount, and unusability, etc., to achieve the benefit of heat Conduction and temperature uniformity, easy assurance of internal quality, reproducible results

Active Publication Date: 2013-08-28
COMAC +1
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AI Technical Summary

Problems solved by technology

Since the RTM process requires high resin fluidity, it can only be applied to a specific resin system, and the resin content of the molded parts is high and unstable, so it cannot be used for the manufacture of aircraft load-bearing box sections
However, the rubber airbag is inflated and pressurized by the rubber airbag. Because the airb

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  • Integrated co-curing forming technology method for composite material multi-beam box section
  • Integrated co-curing forming technology method for composite material multi-beam box section
  • Integrated co-curing forming technology method for composite material multi-beam box section

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Embodiment Construction

[0044] The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0045] According to a preferred embodiment of the present invention, the overall co-curing molding process method of composite multi-beam box segments includes the steps:

[0046] (1) Laying of beam slab: using automatic tape laying technology or manual paving technique, lay beam slab 1 on the beam slab tooling.

[0047] (2) Pre-forming of beam flat plate: such as figure 1 As shown in the figure, using hot diaphragm technology or manual bending technology, the beam plate 1 is preformed into a "C"-shaped beam in the beam preforming tool 2.

[0048] (3) Vacuum: such as Figure 2a-2b As shown in the figure, in order from the inside to the outside, the core mold 3, the isolation material 4, the tubular vacuum bag 5, the air felt 6, and the tubular non-porous isolation film 7 are pasted into the vacuum bag. A vacuum nozzle 8 is set on the outside of 7,...

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Abstract

The invention provides an integrated co-curing forming technology method for a composite material multi-beam box section. The integrated co-curing forming technology method comprises the following steps of: arranging a beam flat plate; pre-forming the beam flat plate; vacuumizing; premounting a beam; arranging an upper wall plate and a lower wall plate; combining the beam; arranging spilling bars; closing the upper wall plate; vacuumizing; extracting a core die; curing the core die; and demolding the core die. The technology method is easy to operate and high in repeatability. In a curing process, the core die is pulled out; the openness of a manufactured piece is high; heat conduction and temperature uniformity are facilitated; and the inner quality of the manufactured piece is easy to guarantee.

Description

Technical field [0001] The invention relates to the technical field of solidification molding, in particular to a method for integral co-solidification molding of composite material multi-beam box sections. Background technique [0002] Composite materials have many excellent characteristics such as high specific strength and specific modulus, designable performance and easy overall forming. The application of composite materials has become the development trend of civil aircraft. With the development of composite material design and application technology, the integral multi-beam box section structure is more and more widely used in civil aircraft, which is similar to the traditional multi-rib structure (composed of upper and lower wall panels, front and rear beams and multiple ribs) In comparison, the integral multi-beam box section reduces the number of parts from multiple to one, which simplifies the assembly process of the box section, reduces the number of fasteners and the...

Claims

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Application Information

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IPC IPC(8): B29C70/44
Inventor 刘卫平张冬梅刘军马晓星王健庄桂增杨洋黄春泉
Owner COMAC
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