Ceramic-based composite material screw, and preparation method thereof

A composite material and ceramic-based technology, applied in the direction of screws, mechanical equipment, threaded fasteners, etc., can solve the problems of polycarbosilane production process complexity, long production cycle, short production cycle, etc., to achieve easy synthesis and collection, equipment Low cost, low cost effect

Inactive Publication Date: 2019-09-03
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The invention provides a ceramic matrix composite material screw and a preparation method thereof, which are used to overcome the long production cycle of the ceramic matrix composite material screw in the prior art, and the complex p

Method used

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

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preparation example Construction

[0023] The present invention proposes a method for preparing a ceramic matrix composite screw, such as figure 1 shown, including the following steps:

[0024] (1) Using carbon fiber cloth as a reinforcement, vacuum pretreatment is carried out on the carbon fiber cloth to remove the organic glue on the surface of the carbon fiber;

[0025] Preferably, in the step (1), the temperature for the vacuum pretreatment of the carbon fiber cloth is 1000-1600° C., and the time is 0.5-2 hours;

[0026] Preferably, the thickness of the carbon fiber cloth is 0.20-1.0 mm; the temperature of the vacuum pretreatment is preferably 1400° C., which facilitates the removal of the organic glue on the surface of the carbon fiber.

[0027] (2) The pretreated carbon fiber cloth is laminated to several layers, and the carbon fiber prefabricated part is obtained by needle punching and sewing; the number of layers of carbon fiber cloth can be selected according to actual needs, so that it can be used in...

Embodiment 1

[0042] This embodiment provides a method for preparing a ceramic matrix composite screw, comprising the following steps:

[0043] (1) Use T300-1K carbon fiber cloth as the reinforcement, the thickness of the carbon fiber cloth is 0.200mm, vacuum pretreatment, the pretreatment temperature is 1000 ℃, heat preservation for 1h;

[0044] (2) Laminate the carbon fiber cloth to a predetermined thickness of 10 mm, and suture it with needle punching, and the suture density is 5 mm;

[0045] (3) Using polyoxysilane as a precursor, the carbon fiber preform was vacuum impregnated and cracked in an inert atmosphere. The impregnation time was 6 hours, the cracking temperature was 1000°C, and the dipping and cracking was repeated 6 times to obtain the green body;

[0046] (4) Process the blank into a round bar, and use a diamond grinding wheel for thread processing to form a screw semi-finished product;

[0047] (5) The processed screw semi-finished products are subjected to several vacuum im...

Embodiment 2

[0050] This embodiment provides a method for preparing a ceramic matrix composite screw, comprising the following steps:

[0051] (1) Use T300-3K carbon fiber cloth as reinforcement, the thickness of carbon fiber cloth is 0.25mm, vacuum pretreatment, pretreatment temperature is 1200 ℃, heat preservation 0.5h;

[0052] (2) Laminate the carbon fiber cloth to a predetermined thickness of 8mm, and suture it with needle punching, and the suture density is 10mm;

[0053] (3) Using polyoxysilane as a precursor, the carbon fiber preform was vacuum impregnated and cracked in an inert atmosphere. The dipping time was 4 hours, the cracking temperature was 800°C, and the dipping and cracking was repeated 6 times to obtain the green body;

[0054] (4) Process the blank into a round bar, and use a diamond grinding wheel for thread processing to form a screw semi-finished product;

[0055] (5) The processed screw semi-finished products are subjected to several vacuum impregnation and inert ...

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Abstract

The invention discloses a ceramic-based composite material screw, and a preparation method thereof. The preparation method comprises five steps including carbon fiber cloth pretreatment, carbon fibercloth lamination needling sewing, carbon fiber cloth prefabricated component initial densification, machining, and densification. Compared with the prior art, the characteristics of the ceramic-basedcomposite material screw are that: the density is 1.60 to 1.70g/cm3, the room temperature tensile breaking strength is 152 to 175MPa, the room temperature shearing strength is 66 to 81MPa, the tensilebreaking strength after 1h of oxidation at 1000 DEG C is 81 to 96MPa, and the room temperature shearing strength is 41 to 60MPa. The preparation method technology is mature; production efficiency ishigh; preparation cost is reduced obviously; operation is simple; the preparation method is a promising effective method used for large scale production of the ceramic-based composite material screw in industrial industry; and the application prospect is promising.

Description

technical field [0001] The invention relates to the technical field of preparation of inorganic non-metallic material screws, in particular to a ceramic matrix composite material screw and a preparation method thereof. Background technique [0002] With the development of high-temperature technology, people put forward higher performance requirements for the materials used to prepare high-temperature devices. Ceramic matrix composites have excellent properties such as high temperature resistance and high specific strength, and have been widely used in high temperature fields. However, large ceramic matrix composite high-temperature devices are often difficult to form as a whole, and screws and other connectors are needed to mechanically connect the separately prepared parts into a whole. [0003] Although traditional metal screws are easy to process and form, they have low specific strength and are not resistant to high temperatures. Screws made of graphite and C / C composit...

Claims

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Application Information

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IPC IPC(8): C04B35/571C04B35/80C04B35/622F16B35/00
CPCC04B35/806C04B35/571C04B35/622C04B2235/5248C04B2235/616C04B2235/77C04B2235/96F16B35/00
Inventor 向阳曹峰刘荣军彭志航郑周朱程鑫
Owner NAT UNIV OF DEFENSE TECH
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