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C/SiC ceramic matrix composite spring and preparation method thereof

A composite material and ceramic-based technology, which is applied in the field of high-temperature sealing of thermal protection systems, can solve the problems of reduced oxidation resistance, high hardness of ceramic materials, and low reliability in use, and achieves the effects of low cost, low preparation temperature, and short cycle

Active Publication Date: 2013-06-26
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Nanjing University of Technology in China has also carried out nano-modification and partially stabilized ZrO 2 (PSZ) preparation of ceramic springs, but the ceramic material of ceramic springs has high hardness, difficult processing and preparation, and low reliability in use
The C / C composite material spring developed by Across Corporation of Japan has light weight, high strength, high modulus and excellent spring characteristics, but the oxidation resistance of C / C composite material decreases significantly at high temperature, which limits its oxidation resistance. use of atmosphere

Method used

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  • C/SiC ceramic matrix composite spring and preparation method thereof
  • C/SiC ceramic matrix composite spring and preparation method thereof

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Experimental program
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Effect test

Embodiment 1

[0028] a kind of like figure 1 , figure 2 The shown C / SiC ceramic matrix composite material spring of the present invention, this spring is to be matrix with silicon carbide, with the carbon fiber of volume fraction about 34% as reinforcing phase, the surface of spring is deposited with SiC coating; The stiffness reaches 3.5N / mm, and the stiffness still reaches 2.6N / mm in the air at 1000°C, and the stiffness retention rate exceeds 74%.

[0029] The C / SiC ceramic matrix composite material spring of this embodiment is prepared through the following steps:

[0030] (1) Forming of spring prefabricated parts: After 14 bundles of carbon fibers are bundled, twisted and plied, they are added to the PCS / DVB resin system containing curing agent for impregnation, wherein the mass ratio of polycarbosilane, divinylbenzene and curing agent is 1 : 1: 0.02, winding the impregnated carbon fiber preform on a paraffin wax mold or a water-soluble mold with a diameter of 16mm, and cross-linking...

Embodiment 2

[0035] A C / SiC ceramic matrix composite spring of the present invention, the spring is based on silicon carbide, carbon fiber with a volume fraction of about 42% is used as a reinforcement phase, and the surface of the spring is deposited with a SiC coating; The stiffness reaches 7.5N / mm, and the stiffness still reaches 6.3N / mm in the air at 1000°C, and the stiffness retention rate reaches 84%.

[0036] The C / SiC ceramic matrix composite material spring of this embodiment is prepared through the following steps:

[0037] (1) Forming of spring prefabricated parts: 20 bundles of carbon fibers are woven and wound in situ on a paraffin wax mold with a diameter of 20mm, and then impregnated in epoxy resin-acetone solution containing curing agent, in which epoxy resin, acetone, The mass ratio of the curing agent is 1:1.5:0.1, and the impregnated carbon fiber preform is cross-linked and cured at room temperature for 5 hours to obtain a spring preform;

[0038] (2) Forming of rough s...

Embodiment 3

[0042] A kind of C / SiC ceramic matrix composite material spring of the present invention, this spring is to be matrix with silicon carbide, with the carbon fiber of volume fraction about 37% as reinforcing phase, the surface of spring is deposited with SiC coating; The rigidity of this spring under room temperature It reaches 5.6N / mm, and the stiffness still reaches 4.4N / mm in the air at 1000°C, and the stiffness retention rate exceeds 78%.

[0043] The C / SiC ceramic matrix composite material spring of this embodiment is prepared through the following steps:

[0044] (1) Forming of spring prefabricated parts: 16 bundles of carbon fibers are woven and wound in situ on a water-soluble mold with a diameter of 20mm, and then added to a phenolic resin-ethanol solution containing a curing agent for impregnation. The mass ratio of the agent is 1:2:0.05, and the impregnated carbon fiber preform is cross-linked and cured at room temperature for 3 hours to obtain a spring preform;

[0...

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Abstract

The invention discloses a C / SiC ceramic matrix composite spring and a preparation method thereof. According to the spring, silicon carbide is used as a matrix, 30 to 45 volume percent of carbon fibers are used as a reinforced phase, and a SiC coating is deposited on the surface of the spring; and the rigidity of the spring is 3.5 to 8 N / mm at room temperature, and the retention rate of the rigidity in the air at the temperature of between 800 and 1,200 DEG C is 70 to 85 percent. The method for preparing the spring comprises the following steps of: impregnating, winding for forming, and crosslinking at the room temperature to obtain a spring prefabricated member; heating, so that a paraffin die is melted or is dissolved in water, sleeving the demolded spring prefabricated member on a graphite die, and cracking to obtain a spring rough blank; compacting repeatedly to obtain a semi-finished product of the spring; and performing surface antioxidation treatment through chemical vapor deposition. The preparation method is simple, low in requirement on equipment and short in period, the net forming of the product is realized, and the quality and performance of the product are high.

Description

technical field [0001] The invention belongs to the technical field of high-temperature sealing of thermal protection systems, and in particular relates to a high-temperature-resistant spring and a preparation method thereof. Background technique [0002] The flight speed of a hypersonic vehicle is above 6Ma. During the flight, the pressure difference between the inside and outside of the heat shield panel is large, and the surface temperature is high (>1500°C). The thermal protection system is composed of multiple heat-resistant panels embedded on the surface of the aircraft. In order to prevent high-temperature air from passing to the interior, high-temperature sealing is required between the panels. Using C / SiC composite gaskets with excellent high temperature resistance to achieve high temperature sealing is a good sealing method, but this method has the problem of insufficient compression and resilience of the gaskets, so high temperature springs can be used to seal ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/622C04B41/85
Inventor 胡海峰张玉娣张长瑞陈思安熊鑫李广德
Owner NAT UNIV OF DEFENSE TECH
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