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Ceramic base compound material bolt preparation method

A composite material, ceramic-based technology, used in screws, mechanical equipment, threaded fasteners, etc., can solve the problems of poor quality and high cost, reduce production costs, and ensure the effect of processing quality and strength

Inactive Publication Date: 2010-02-10
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the shortcomings of poor quality and high cost of the prior art, the present invention provides a method for preparing ceramic matrix composite bolts, which utilizes the deposition of a pyrolytic carbon interface layer on the prefabricated body, combined with CVI deposition and polymer impregnation cracking (hereinafter referred to as PIP) to prepare C / SiC composite bolts, which can improve the tensile fracture strength of the bolts and reduce the preparation cost

Method used

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  • Ceramic base compound material bolt preparation method
  • Ceramic base compound material bolt preparation method
  • Ceramic base compound material bolt preparation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] Example 1: Use 1K carbon fiber to lay the first layer at 0°, lay the second layer perpendicular to the first layer above it, and lay the third layer obliquely at +45° on the second layer, and then lay the Lay the fourth layer obliquely on top of the third layer at an angle of -45°, and alternately lay layers in this order, and prepare a carbon fiber two-dimensional plate prefabrication body according to the size of the required bolts. The normal ply fiber 3 is parallel to the center line of the screw rod of the bolt, and the oblique ply fiber 4 is parallel to the screw thread 2 surface of the bolt.

[0021] The pyrolytic carbon interface layer was deposited on the carbon fiber two-dimensional plate preform. The process conditions were: deposition temperature 800°C, pressure 0.2kPa, propylene flow rate 35ml / min, Ar gas flow rate 250ml / min, and deposition time 60h.

[0022] The silicon carbide substrate was deposited on the carbon fiber two-dimensional sheet deposited wit...

Embodiment 2

[0027] Example 2: Use 1K carbon fiber to lay the first layer according to 0°, lay the second layer perpendicular to the first layer above it, and lay the third layer obliquely on the second layer at an angle of +45°, and then lay the Lay the fourth layer obliquely on top of the third layer at an angle of -45°, and alternately lay layers in this order, and prepare a carbon fiber two-dimensional plate prefabrication body according to the size of the required bolts. The normal ply fiber 3 is parallel to the center line of the screw rod of the bolt, and the oblique ply fiber 4 is parallel to the screw thread 2 surface of the bolt.

[0028] The pyrolytic carbon interface layer was deposited on the carbon fiber two-dimensional plate preform. The process conditions were: deposition temperature 840°C, pressure 0.3kPa, propylene flow rate 28ml / min, Ar gas flow rate 270ml / min, and deposition time 45h.

[0029] The silicon carbide substrate was deposited on the carbon fiber two-dimension...

Embodiment 3

[0034] Example 3: Use 1K carbon fiber to pave the first layer according to 0°, lay the second layer perpendicular to the first layer on it, and lay the third layer obliquely on the second layer at an angle of +30°, and then lay the Lay the fourth layer obliquely on top of the third layer at an angle of -30°, and lay layers alternately in this order, and prepare a carbon fiber two-dimensional plate prefabricated body according to the size of the required bolts. The normal ply fiber 3 is parallel to the center line of the screw rod of the bolt, and the oblique ply fiber 4 is parallel to the screw thread 2 surface of the bolt.

[0035] The pyrolytic carbon interface layer was deposited on the carbon fiber two-dimensional plate prefabricated body. The process conditions were as follows: deposition temperature 870°C, pressure 0.3kPa, propylene flow rate 31ml / min, Ar gas flow rate 310ml / min, and deposition time 55h.

[0036] The silicon carbide substrate was deposited on the carbon ...

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Abstract

The invention discloses a preparation method for a ceramic matrix composite bolt, which is characterized in that the method comprises the following steps: producing a fiber prefabricated product by shaping with a graphite plate after alternatively laminating a 1K carbon fiber 0 / 90 degree positive ply and a plus / minus Theta inclined ply; depositing a pyrolysis carbon interface layer on the prefabricated product and then depositing a silicon carbide matrix on the two-dimensional sheet with a deposited pyrolysis carbon interface layer to produce a semi-finished product of ceramic matrix compositesheet which is cut to form a bolt blank; grinding wheel and tapping the bolt blank; lastly obtaining the product of C / SiC composite bolt after many times of infiltration pyrolysis of polycarbosilaneand continuing CVI depositing of SiC anti-oxidation coating. By the method, the bolt is processed and tapped on the semi-finished ceramic matrix composite prefabricated product which is not fully deposited and dense, so that the diamond grinding wheel wear is slow and the production cost is reduced. The technology of CVI combining with PIP process enables the elongation breaking strength of composite bolts to improve from 180 to 190MPa in prior art to 210 to 230MPa.

Description

technical field [0001] The invention relates to a preparation method of a ceramic matrix composite material bolt. Background technique [0002] In the known aerospace field, the bolts and nuts used to connect the structural parts of the thermal protection system of the aerospace vehicle, due to the very harsh flight conditions of the aerospace vehicle, friction with the air when re-entering the atmosphere, the nose cone, the leading edge of the wing and the surface of the fuselage flap The highest temperature can reach 1650°C, which requires bolts and nuts to have excellent thermophysical, chemical and mechanical properties. [0003] Standard bolt and nut materials for aerospace include graphite, C / C composites and C / SiC composites. Graphite has a series of advantages such as high temperature resistance, low density and good wear resistance, but it has poor high temperature oxidation resistance and low strength. C / C composite materials have a series of advantages such as h...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16B35/00
Inventor 梅辉成来飞张立同徐永东柯晴青
Owner NORTHWESTERN POLYTECHNICAL UNIV
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