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Composite material combustion barrier structure and composite material thereof

A structured, flame-retardant material technology, applied in the direction of coating, layered products, etc., can solve problems affecting the mechanical properties of composite materials, achieve the effects of inhibiting combustion, reducing the amount of flame retardants, and inhibiting air diffusion

Active Publication Date: 2017-05-10
AVIC BASIC TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

But it still has the following disadvantages: the flame-retardant intercalation is continuously distributed in the entire interlayer, and has a certain thickness, and the relatively tough interlayer with a lower modulus will definitely affect the mechanical properties of the composite material, especially is the flexural modulus of the composite

Method used

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  • Composite material combustion barrier structure and composite material thereof

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Effect test

Embodiment 1

[0028] The implementation process of the technical solution of the present invention is as follows:

[0029] (1-1) Disperse 3g of silica nanoparticles or nano-layered silicate clay or halloysite nanotubes in N,N-dimethylformamide or tetrahydrofuran, and the diameters or layer thicknesses of the three are respectively 50nm, 70nm and 35nm, then take 75g of phenolphthalein-modified polyaryletherketone (PEK-C) or polyepoxyphenoxy resin (PKHH) and 25g of polyphenylsulfone diphenylphosphonate, and dissolve them uniformly in In the dispersion liquid, ultrasonic dispersion can obtain a uniform dispersion liquid;

[0030](1-2) Take epoxy resin prepreg, carbon fiber T300, 3K or T800, 12K, epoxy resin 5228 (product of AVIC Composite Material Co., Ltd.) or epoxy resin QY9611 (product of AVIC Composite Material Co., Ltd.), Print the solution onto the surface of the prepreg by screen printing, control the final film thickness at 18 μm or 32 μm by the amount of the solution, and control the...

Embodiment 2

[0036] The implementation process of the technical solution of the present invention is as follows:

[0037] (2-1) Dissolve 17g of phenolphthalein-modified polyarylether ketone or phenolphthalein-modified polyarylether sulfone or polyethylene terephthalate into 83g of N,N-dimethylformamide, with a mass percent concentration of 17 %, then add 0.35g of multi-walled carbon nanotubes with a diameter of 25nm and 0.5g of carbon-60, add 0.1g of polyvinylpyrrolidone to improve the dispersion of carbon nanomaterials, and then add nitrogen-containing heterocyclic triphenylphosphine oxide poly Aryl ether 5g, after adding, ultrasonically mix evenly, set aside. Spray or print the solution on a flat plate, control the amount of spraying, so that the final film thickness is 22 μm or 38 μm, and control the screen density, so that the single width of the printed diamond-shaped mesh structure is 2.3m, and the side length of the grid is 6.2mm. Blast drying at 80°C for 1 hour, then vacuum drying...

Embodiment 3

[0041] The implementation process of the technical solution of the present invention is as follows:

[0042] (3-1) Heat and dissolve 18g of polyetherimide or 17g of polyphenylene sulfide in 60g of bismaleimide resin to form a solution with a concentration of 18% or 17% by mass, and add 13g or 20g of it to polymerize The polymer flame retardant is polyphenylsulfone diphenyl phosphonate or nitrogen-containing heterocyclic triphenylphosphine oxide polyarylether or tribromophenol-modified novolac resin, hot-melt and stirred evenly ;

[0043] (3-2) Take unidirectional continuous carbon fiber reinforced bimaleimide resin-based prepreg, carbon fiber CCF300, 3K, bismaleimide resin 6421 (product of AVIC Composites Co., Ltd.), and use (3-1) The resin is coated on the surface of the prepreg while it is hot, and the amount of spraying is controlled so that the final film thickness is about 15 μm or 27 μm. The screen density is controlled so that the single width of the printed rectangula...

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Abstract

The invention belongs to the technical field of preparation of structure-function integrated composite materials, and relates to a composite material combustion barrier structure and a composite material thereof. A carbon fiber prepreg of a prefabricated structured interlayer combustion barrier structure is developed, and the prefabricated structured interlayer combustion barrier structure is distributed on the surface of the prepreg, has a certain thickness and is in mesh distribution. The prepreg comprises resin, a thermoplastic toughening agent which is thermally dissolved into the resin, and fire retardants and / or nanoparticles which are evenly distributed into the thermoplastic toughening agent. After the prepreg is prepared into the composite material, a continuous combustion barrier layer is formed between layers and diffused into the layer with high carbon fiber content to play a cooperative barrier role, so that the composite material combustion barrier structure plays a good flame-retardant role. A UL94 vertical combustion method shows that the flame-retardant level can reach the V0 level, no smoke overflows in combustion, a composite material molding technology is facilitated due to the mesh distribution, and the influence on the outer surface performance of the composite material is avoided.

Description

technical field [0001] The invention belongs to the technical field of preparation of structure-function integrated composite materials, and relates to a composite material combustion barrier structure and a composite material thereof. Background technique [0002] Fire is one of the main safety hazards of commercial and military aircraft. The high heat, smoke and toxic substances produced by fire seriously threaten the lives of passengers. Among all aircraft accidents, fire ranks fourth among the reasons (Boeing2005, Statistical summary of commercial jet airplane accidents-worldwide operations 1959-2004, Seattle, Washington, US, P.18.), and fire fatalities are increasing at a rate of 4% per year [FAA website]. [0003] Carbon fiber-reinforced resin-based laminated composite materials are mainly used to manufacture the shell and skin of aerospace vehicles. Since entering the 21st century, represented by the US B787 and the European A380 large aircraft, continuous carbon fibe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B9/00B32B9/04B32B5/02C08J5/24C08L71/10C08L63/00C08L79/08C08L79/04
CPCB32B5/028B32B5/26B32B2250/20B32B2255/26B32B2260/021B32B2260/046B32B2262/106B32B2307/3065B32B2307/558C08J5/24C08J2363/00C08J2371/10C08J2379/04C08J2379/08
Inventor 郭妙才李亚锋洪旭辉
Owner AVIC BASIC TECH RES INST
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