Ceramic-based composite material and preparation method thereof

A composite material and ceramic-based technology, applied in the field of ceramic-based composite materials and their preparation, can solve the problems of long preparation cycle, low temperature, and great influence of fiber system, and achieve the advantages of shortening the impregnation cycle, improving the ceramic yield and reducing the preparation cost. Effect

Inactive Publication Date: 2020-04-03
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The invention provides a ceramic matrix composite material and a preparation method thereof, which are used to overcome defects in the prior art such as long preparat

Method used

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  • Ceramic-based composite material and preparation method thereof
  • Ceramic-based composite material and preparation method thereof
  • Ceramic-based composite material and preparation method thereof

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Example Embodiment

[0026] The present invention provides a method for preparing a ceramic matrix composite material, which includes the following steps:

[0027] S1: Weigh the silicone resin and the organic solvent according to the mass ratio, stir to form a silicone resin solution;

[0028] Preferably, the organic solvent is one of methanol, acetone and anhydrous ethanol, preferably anhydrous ethanol, which has good solubility, low toxicity, and low corrosiveness; the mass ratio of the silicone resin and anhydrous ethanol is ( 1:1)~(1:5); The stirring speed is 800~1500rpm, and the time is 2~8h. Too much silicone resin will result in a thicker solution, which is not conducive to impregnation, and too little will result in a dilute solution, which will lengthen the impregnation period of the material, which is not conducive to production; stir well to obtain a uniform silicone resin solution.

[0029] S2: Needle, puncture or stitch inorganic fiber cloth or fabric;

[0030] Preferably, the number of laye...

Example Embodiment

[0045] Example 1

[0046] This embodiment provides a method for preparing a ceramic matrix composite material, such as figure 1 As shown, including the following steps:

[0047] (1) Weigh the silicone resin and absolute ethanol, where the mass ratio of silicone resin and absolute ethanol is 1:1, and form a silicone resin solution by magnetic stirring for 4 hours;

[0048] (2) Lay 8 layers of 0.28mm thick T300-1K carbon fiber cloth, and then stitch them. The fiber used in the suture thread is commercially available T300-1K carbon fiber. In order to obtain better mechanical properties, two The stitch spacing is 5mm;

[0049] (3) Clamp the carbon fiber cloth sewn in step (2) with a graphite mold, place it in a vacuum container, vacuum suck the silicone resin solution (suspension) prepared in step (1), and immerse it for 8 hours;

[0050] (4) The carbon fiber impregnated in step (3) is arranged in a vacuum cracking furnace for compression crosslinking and high temperature cracking, specifi...

Example Embodiment

[0059] Example 2

[0060] This embodiment provides a method for preparing a ceramic matrix composite material, including the following steps:

[0061] (1) Weigh silicone resin and absolute ethanol, where the mass ratio of silicone resin and absolute ethanol is 1:2, and form a silicone resin solution by magnetic stirring for 8 hours;

[0062] (2) Spread 8 layers of 0.23mm thick second-generation SiC fiber cloth produced by National University of Defense Technology (Qing Wang.Effects of ZrO) 2 coating on the strength improvement of2.5D SiCf / SiO 2 composites.Ceramics International 43(2017)884–889), and then stitched. The fibers used in the sutures are the second-generation SiC fibers mentioned above. In order to obtain excellent mechanical properties, the spacing between every two sutures is designed to be 8mm;

[0063] (3) Clamp the carbon fiber cloth sewn in step (2) with a heat-resistant steel mold, place it in a vacuum container, vacuum inhale the silicone resin solution (suspension)...

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Abstract

The invention discloses a ceramic-based composite material and a preparation method thereof. The density of the composite material is 1.60-1.80g/cm<3>, the porosity is 11.5-14.5%, the interlaminar shear strength is 55-56MPa, the tensile strength at 1500 DEG C reaches 100MPa, and the bending strength in the fiber sewing direction at 1500 DEG C reaches 130MPa. According to the preparation method, the ceramic-based composite material is prepared by adopting a precursor impregnation-mold pressing low-temperature crosslinking-high-temperature cracking method. The composite material provided by theinvention is low in density, high in interlaminar strength and high in tensile strength at 1500 DEG C, and can be applied to the field of aerospace. The preparation method provided by the invention isshort in preparation period and low in cost, the temperature of mold pressing low-temperature crosslinking-high-temperature cracking is lower than 1000 DEG C, and the influence on a fiber system is small.

Description

technical field [0001] The invention relates to the technical field of composite materials, in particular to a ceramic matrix composite material and a preparation method thereof. Background technique [0002] Fiber-reinforced ceramic matrix composites are an emerging material system with high specific strength, high specific modulus, high temperature resistance and ablation resistance, which is developed rapidly in recent years with continuous fiber as reinforcement and ceramic as matrix. [0003] Fiber-reinforced ceramic matrix composites can be divided into 1D, 2D, and 3D according to the different reinforcement methods of continuous fibers inside the material, that is, composite materials are reinforced by unidirectional fibers (1D or UD, unidirectional), two-way fabric reinforcement (2D) and 3D. Three-dimensional fabric reinforcement (3D). Fiber reinforcement methods are different, and composite materials have different molding methods, pore structures, pore distributio...

Claims

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Application Information

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IPC IPC(8): C04B35/56C04B35/80C04B35/622
CPCC04B35/56C04B35/622C04B2235/5248C04B2235/5244C04B2235/77C04B2235/96C04B2235/6562
Inventor 向阳曹峰彭志航刘荣军
Owner NAT UNIV OF DEFENSE TECH
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