Sandwich structure composite material and OOA preparation method thereof

A composite material and sandwich structure technology, applied in chemical instruments and methods, lamination, lamination devices, etc., can solve the problems of strict structural weight requirements, inability to meet low-cost manufacturing and structural lightweight, application limitations, etc. Reduced material cost, low comprehensive manufacturing cost, and small equipment investment

Active Publication Date: 2020-04-17
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The application of the above two methods is limited in fields with strict structural weight requirements and extremely high low-cost requirements, and cannot meet the requirements of low-cost manufacturing and lightweight structures.

Method used

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  • Sandwich structure composite material and OOA preparation method thereof
  • Sandwich structure composite material and OOA preparation method thereof
  • Sandwich structure composite material and OOA preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0058] Prepreg:

[0059]

[0060] Adopt this example prepreg to prepare PMI foam sandwich structure composite material, PMI foam (density 71kg / m 3 ) thickness 2mm.

[0061] The OOA process is adopted as follows:

[0062] 1. Prepare 3068 medium temperature curing epoxy resin for prepreg.

[0063] Weigh a certain amount of carbon nanotubes and 3068 medium-temperature curing epoxy resin, mix them with a mixer until there is no dry powder, pour them into a three-roll mill and grind them for 3-5 times to obtain a carbon nanofiber masterbatch. According to the resin process requirements for prepreg production and the nanofiber content requirements in the resin, add curing agent, accelerator, and nanofiber masterbatch to the reaction kettle in proportion, stir evenly and degas to obtain the resin for prepreg.

[0064] 2. Prepare T300-3000-40B twill carbon cloth / 3068 resin prepreg.

[0065] The carbon nanotube-containing 3068 resin content in the prepreg is 35-38 wt%. When com...

Embodiment 2

[0078] Prepreg:

[0079]

[0080] The preparation process of the foam sandwich structure composite material is the same as that of Example 1, and the flat tensile strength and surface density of the PMI foam sandwich structure composite material are shown in Table 1.

Embodiment 3

[0082] Prepreg:

[0083]

[0084] Aramid paper honeycomb sandwich structure composite material adopts aramid honeycomb density (29kg / m 3 ) thickness 2mm, aramid paper honeycomb sandwich structure composite material preparation process is the same as embodiment 1, and the difference between this embodiment and embodiment 1 is:

[0085] Step 5, the honeycomb sandwich structure composite material is pre-compacted.

[0086] Vacuumize the encapsulated sandwich structure composite material assembly at room temperature for 2 hours to further discharge the gas entrapped in the prepreg and the air in the interlayer of the sandwich structure,

[0087] Step 6, pre-curing.

[0088] Keep warm at 90°C for 4 hours to gradually impregnate the continuous fibers and fabrics in the prepreg with low viscosity, so that the composite panel will be densified. Under the effect, the resin wets and spreads on the surface of the core material to form glue bumps, and the nanofibers in the resin are...

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Abstract

The invention provides a sandwich structure composite material and an OOA preparation method thereof. The composite material comprises a panel and a core layer, the panel is prepared from a partially-infiltrated prepreg by adopting OOA, the partially-infiltrated prepreg is prepared from a nanofiber-containing resin matrix and a fiber by adopting a hot melting process, the partially-infiltrated prepreg is composed of an upper infiltrated layer, a lower infiltrated layer and a middle partially-infiltrated layer, and the middle partially-infiltrated layer is composed of a non-infiltrated fiber area and an infiltrated fiber area which are discontinuous; and the addition amount of the nanofiber is not less than 0.5% of the mass of the resin matrix. The prepreg with self-adhesion capability is used for preparing the sandwich material, so the weight reduction efficiency is high, and the material cost is saved; and the sandwich structure composite material with high bonding strength can be obtained by only adopting the prepreg with normal resin content without adding a structural adhesive film or increasing the resin content of the prepreg between the panel and the core material of the composite material, so that an adhesive film can be saved or the consumption of resin can be reduced, the material cost can be reduced, and the product weight can be further reduced.

Description

technical field [0001] The invention relates to a sandwich structure composite material and an OOA preparation method thereof, belonging to the technical field of composite material preparation. Background technique [0002] The characteristics of high specific strength and specific modulus of resin-based composite materials make it widely used in aerospace. With the gradual increase in the amount of composite materials and product size, the traditional autoclave and molding-based molding processes, The shortcomings of high equipment investment, expensive process cost and unfavorable integrated integral molding are becoming increasingly apparent, which cannot meet the needs of low-cost manufacturing and integrated integral molding of high-performance composite materials, hindering the further expansion of composite materials. application. Liquid molding represented by VARI has great advantages in low-cost manufacturing and integrated overall molding, but the composite produc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B33/00B32B37/00B32B37/06B32B37/10B32B38/00B32B5/24B32B5/02B32B3/12
CPCB32B37/1018B32B37/06B32B37/00B32B38/00B32B5/02B32B5/245B32B3/12B32B33/00
Inventor 欧秋仁唐中华董大为张帅陈哲明
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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