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Method for manufacturing ultra-high temperature ceramic matrix composite material ablation head radome body

A technology of ultra-high temperature ceramics and composite materials, applied in the direction of the radiation unit cover and other directions, can solve the problems of changing the aerodynamic shape of the radome, affecting the missile strike accuracy, and a large amount of ablation of the radome stagnation point, so as to shorten the preparation period and improve the impregnation. The effect of compounding efficiency and improving impregnation efficiency

Active Publication Date: 2018-07-31
湖北三江航天江北机械工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, the commonly used radome material in China is quartz / quartz composite ceramic material, and its temperature resistance is only 1200°C. As a "mushroom head", there is a problem of changing the aerodynamic shape of the radome and seriously affecting the accuracy of missile strikes

Method used

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  • Method for manufacturing ultra-high temperature ceramic matrix composite material ablation head radome body
  • Method for manufacturing ultra-high temperature ceramic matrix composite material ablation head radome body

Examples

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Effect test

Embodiment 1

[0034] A method for manufacturing an ultra-high temperature ceramic matrix composite material ablation head radome cover body 1, comprising the following steps:

[0035] 1) Use the carbon fiber three-phase orthogonal method to weave the ablation head flat fabric to obtain the ablation head braid; weaving parameters: radial direction 3K×1, density 3 / cm, weft direction 3K×8, density 5 / cm , normal direction 3K×1, density 3 / cm

[0036] 2) Submerge the braided fabric of the ablation head in the precursor, heat it in a water bath to 80-100°C, vacuum impregnate it for 6 hours, take it out, dry and solidify it, repeat 3 times, and obtain the immersed braided fabric; wherein, the precursor is a bismuth containing polycarbosilane Toluene solution; polycarbosilane content in xylene solution is 50%;

[0037] 3) Add zirconia powder to the precursor and mix evenly; obtain a mixed solution, then immerse the submerged braid in the mixed solution, fully impregnate and compound; then perform v...

Embodiment 2

[0046] A method for manufacturing an ultra-high temperature ceramic matrix composite material ablation head radome cover body 2, comprising the following steps:

[0047] 1) Use the carbon fiber three-phase orthogonal method to weave the ablation head flat fabric to obtain the ablation head braid; weaving parameters: radial direction 3K×1, density 3 / cm, weft direction 3K×4, density 5 / cm , normal direction 3K×1, density 3 / cm

[0048] 2) Submerge the braided fabric of the ablation head in the precursor, heat it in a water bath to 80-100°C, vacuum impregnate it for 6 hours, take it out, dry and solidify it, repeat 3 times, and obtain the immersed braided fabric; wherein, the precursor is a bismuth containing polycarbosilane Toluene solution; polycarbosilane content in xylene solution is 50%;

[0049] 3) Add zirconium carbide powder to the precursor and mix evenly; obtain a mixed solution, then immerse the submerged braid in the mixed solution, fully impregnate and compound; then ...

Embodiment 3

[0057] The method for manufacturing the radome body 3 of the ablation head radome made of ultra-high temperature ceramic matrix composite material comprises the following steps:

[0058] 1) Use the carbon fiber three-phase orthogonal method to weave the ablation head flat fabric to obtain the ablation head braid; weaving parameters: radial direction 3K×2, density 3 / cm, weft direction 3K×4, density 5 / cm , normal direction 3K×2, density 3 / cm

[0059] 2) Immerse the braided fabric of the ablation head in the precursor, heat it in a water bath to 80-100°C, vacuum impregnate it for 6 hours, take it out, dry and solidify it, repeat 5 times, and obtain the immersed braided fabric; wherein, the precursor is a bismuth containing polycarbosilane Toluene solution; polycarbosilane content in xylene solution is 50%;

[0060] 3) Add zirconium carbide powder to the precursor and mix evenly; obtain a mixed solution, then immerse the submerged braid in the mixed solution, fully impregnate and...

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Abstract

The invention discloses a fabrication method for a cover body of a superhigh temperature ceramic matrix composite material ablation head antenna cover. The method comprises the following steps of weaving an ablation head flat plate fabric by a carbon fiber three-phase orthogonal mode to obtain an ablation head woven fabric; immersing and compounding to obtain C / SiC-ZrC composite ceramic ablation head rough blank, and carrying out profiling weaving on the cover body fabric by a needling mode to obtain a cover body woven fabric; mechanically processing the cover body woven fabric to required product sizes to obtain an ablation head and the cover body; and connecting and forming the ablation head and the cover body by nuts, thereby obtaining the cover body of the ablation head antenna cover. According to the method, the C / SiC-ZrC composite material and a C / SiC-HfC composite material which have excellent temperature resistance reaching 2,000 DEG C and ablation resistance are used; and through optimal design on a prefabricated element of the ablation head and control on volume content of annular fibers, zero expansion of the ablation head composite material in an annular direction can be achieved, and thus, the obtained cover body of the antenna cover can be applied to intermediate and remote land attack cruise missiles with high mach (greater than 10Ma), long endurance (greater than 1,000 seconds) and high accuracy.

Description

technical field [0001] The invention relates to the manufacturing field of radome covers, in particular to a method for manufacturing a radome cover of an ablation head made of ultra-high temperature ceramic matrix composite material. Background technique [0002] The radome is located at the head of the missile weapon system. It has the functions of high temperature resistance, load bearing and wave penetration. It is the most important component of the missile weapon system. During flight, in order to ensure the strike accuracy of missile weapons, the radome must maintain a complete aerodynamic shape, so the radome should have excellent temperature resistance and ablation resistance. [0003] With the rapid development of aerospace technology, missile weapons have higher and higher requirements for high precision, long range, hypersonic speed (≥10Ma), large overload, and maneuvering flight, making the reentry environment of the entire weapon system extremely harsh. The lo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H01Q1/42C04B35/56C04B35/573C04B35/622C04B35/80
CPCC04B35/5622C04B35/573C04B35/622C04B35/806C04B2235/5248C04B2235/5256C04B2235/616H01Q1/42
Inventor 孙晓莉佘平江尹正帅陈海昆吴广力王芬
Owner 湖北三江航天江北机械工程有限公司
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