High-temperature-resistant ablation carbon/ carborundum composite material fixing hinge and preparation method

A technology for fixing hinges and composite materials, which is applied in the field of high-temperature-resistant ablation carbon/silicon carbide composite material fixing hinges and its preparation, which can solve the problem of making fixed hinges without C/SiC composite materials, high-temperature alloy materials with high density, and difficult to meet the use requirements and other issues, to achieve the effect of improving the overall mechanical properties, improving fracture toughness, and improving rigidity

Inactive Publication Date: 2016-01-27
SHANDONG UNIV +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] At present, there is a big gap between the production level of high-temperature alloys in my country and the United States, Russia and other countries. With the emergence of new aerospace vehicles/vehicles, simply using high-temperature alloys to make aerospace components—fixed hinges can no longer meet the needs of aerospace and aerospace industries. The req

Method used

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  • High-temperature-resistant ablation carbon/ carborundum composite material fixing hinge and preparation method
  • High-temperature-resistant ablation carbon/ carborundum composite material fixing hinge and preparation method
  • High-temperature-resistant ablation carbon/ carborundum composite material fixing hinge and preparation method

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Example Embodiment

[0062] Example 1

[0063] A method for preparing a high-temperature ablation-resistant carbon / silicon carbide composite material fixed hinge includes the following steps:

[0064] (1) Design the structure and size of the fixed hinge

[0065] Such as Figure 1~4 As shown, according to the use of the fixed hinge in aerospace and specific extreme environments, the fixed hinge is designed as a hinge type hinge structure, including a rotating shaft 3; the upper hinge support 1 has a first installation for connecting with the connected object The first mounting surface structure is provided with 6 first through holes, through the first through holes 6 to realize the fixation of the hinge upper support 1 and the connected object; the hinge lower support 2 has The second mounting surface structure connected by the connected object, the second mounting surface structure is provided with six second through holes 5, through the second through holes 6 to realize the fixation of the hinge lower ...

Example Embodiment

[0088] Example 2

[0089] A method for preparing a high-temperature ablation-resistant carbon / silicon carbide composite material fixed hinge includes the following steps:

[0090] (1) Design the structure and size of the fixed hinge

[0091] Such as Figure 1~4 As shown, according to the use of the fixed hinge in aerospace and specific extreme environments, the fixed hinge is designed as a hinge type hinge structure, including a rotating shaft 3; the upper hinge support 1 has a first installation for connecting with the connected object The first mounting surface structure is provided with 6 first through holes, through the first through holes 6 to realize the fixation of the hinge upper support 1 and the connected object; the hinge lower support 2 has The second mounting surface structure connected by the connected object, the second mounting surface structure is provided with six second through holes 5, through the second through holes 6 to realize the fixation of the hinge lower ...

Example Embodiment

[0114] Example 3

[0115] A method for preparing a high-temperature ablation-resistant carbon / silicon carbide composite material fixed hinge includes the following steps:

[0116] (1) Design the structure and size of the fixed hinge

[0117] Such as Figure 1~4 As shown, according to the use of the fixed hinge in aerospace and specific extreme environments, the fixed hinge is designed as a hinge type hinge structure, including a rotating shaft 3; the upper hinge support 1 has a first installation for connecting with the connected object The first mounting surface structure is provided with 6 first through holes, through the first through holes 6 to realize the fixation of the hinge upper support 1 and the connected object; the hinge lower support 2 has The second mounting surface structure connected by the connected object, the second mounting surface structure is provided with six second through holes 5, through the second through holes 6 to realize the fixation of the hinge lower ...

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Abstract

The invention discloses a high-temperature-resistant ablation carbon/ carborundum composite material fixing hinge and a preparation method. The preparation method includes the following steps that 1, the structure and size of the fixing hinge are designed; 2, precast bodies of all components are prepared; 3, the precast bodies are formed, wherein an upper support base and a lower support base complete integral forming of the precast bodies in step 2 through a technology combining a needle punching technology and a stitching technology; accessories complete integral forming of the precast bodies through the needle punching technology; 4, a C/SiC composite material fixing hinge is prepared, wherein the formed precast bodies of all the components are subjected to deposition and densification through a chemical vapor deposition technology, a C/C composite material fixing hinge component blank is generated, then ceramization treatment and mechanical machining are conducted, and the C/SiC composite material fixing hinge is obtained. The fixing hinge is small in thermal expansion coefficient, high in mechanical property, small in high temperature ablation volume and capable of bearing tension, shear and other complex loads and has excellent weather resistance.

Description

technical field [0001] The invention relates to a high-temperature-resistant ablation carbon / silicon carbide composite material fixed hinge and a preparation method thereof. Background technique [0002] Carbon / silicon carbide composite material (C / SiC) composite material first appeared in the 1980s as a thermal protection material for the US space shuttle, and has been applied to panels and fuselage hatches of returnable spacecraft, thermal protection systems of space shuttles, etc. . When hypersonic vehicles such as the space shuttle fly in the atmosphere, they face a very harsh thermal environment. The surface of the vehicle, especially the aerodynamic windward side of the nose cone, wing leading edge, flap and other structures, is very hot. When the flight speed is Mach 6 After a few hours, the temperature of the nose cone can reach about 1800K (about 1530°C), which poses a serious challenge to the high temperature resistance of the aircraft's Thermal Protection Systems...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B35/565C04B35/80
Inventor 袭建人邵济明李保江杨晓涛王兆辉虞松齐广慧庄光山张刚葛建华
Owner SHANDONG UNIV
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