CN107415354A - 一种低导热耐高温碳纤维立体织物复合材料 - Google Patents

一种低导热耐高温碳纤维立体织物复合材料 Download PDF

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CN107415354A
CN107415354A CN201710604466.6A CN201710604466A CN107415354A CN 107415354 A CN107415354 A CN 107415354A CN 201710604466 A CN201710604466 A CN 201710604466A CN 107415354 A CN107415354 A CN 107415354A
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CN107415354B (zh
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余盛杰
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Suzhou Superlong Aviation Heat Resistance Material Technology Co Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
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    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
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Abstract

本发明公开了一种低导热耐高温碳纤维立体织物复合材料，其特征在于由碳纤维立体织物、热解碳基体和二氧化硅气凝胶构成，碳纤维立体织物具有上下两外壳层，两外层中碳纤维体积含量为30‑40%，两外层厚度均为1‑3mm，上下两外壳层之间相距1‑2cm，上下两外壳层之间由相互绞联的碳纤维束连接，形成支撑上下两外壳层的骨架，其中碳纤维表面沉积热解碳基体，热解碳基体厚度为10‑1000μm，骨架之间填充二氧化硅气凝胶，骨架直径1‑5mm，骨架之间相距2‑20mm。该材料导热系数低，能够在超高温度（＞800℃）环境下使用，随着温度的升高材料导热系数变化不明显，同时材料具有重量轻，密度仅为0.3‑0.5g/cm3，且耐高速气流的冲刷等优异性能。

Description

一种低导热耐高温碳纤维立体织物复合材料
技术领域
本发明涉及一种复合材料，特别是涉及一种低导热耐高温碳纤维立体织物复合材料。
背景技术
在刚性隔热瓦作为美国航天飞机大面积热防护材料，其有效性和可靠性已经被广泛证实。隔热瓦性能改进后，不断在X－43A、X－37B、X－51A等高超声速飞行器上得到应用。刚性隔热材料由互相搭接的纤维形成的多孔结构，具有密度小、热导率低、力学性能相对较高、综合性能好等优点。近年来，各国正在研制开发新型的热防护系统。一种陶瓷泡沫芯材作为热防护芯材广泛应用于航天飞行器，美国John H等人的一篇《Improved Fabricationof Ceramic Matrix Composite/Foam Core Integrated Structures》报道了C/SiC复合材料夹层碳化硅泡沫用作热防护层。但是由于碳化硅泡沫芯材空隙较大，在高温下热辐射传热占主导作用，导热系数随着温度的上升迅速增大，导致材料必须很厚才能起到隔热效果。
本发明通过再纤维表面沉积热解碳基体目的是对碳纤维立体织物进行固化，之后在碳纤维立体织物中填充二氧化硅气凝胶，大大降低保温芯材中的空隙大小，将原陶瓷泡沫中大孔变为纳米孔，能够有效降低材料在高温下的辐射传热影响，从而使得该保温材料在高温下依然具有较低的热导率。在本发明材料中，上下外层起到耐高温，抗冲刷的作用，而中间层由于填充二氧化硅气凝胶，起到绝热保温作用，该材料可以承受800℃以上的高温。本发明在国防工业、航空航天等方面将具有巨大的应用前景。
发明内容
本发明要解决的技术问题是克服碳材料导热系数高，隔热性能差的缺陷，提供了一种具有一种低导热耐高温的复合材料。
为实现本发明的目的所采用的技术方案是：一种低导热耐高温碳纤维立体织物复合材料，其特征在于由碳纤维立体织物、热解碳基体和二氧化硅气凝胶构成，碳纤维立体织物具有上下两外壳层，两外层中碳纤维体积含量为30-40%，两外层厚度均为1-3mm，上下两外壳层之间相距1-2cm，上下两外壳层之间由相互绞联的碳纤维束连接，形成支撑上下两外壳层的骨架，其中碳纤维表面沉积热解碳基体，热解碳基体厚度为10-1000μm，骨架之间填充二氧化硅气凝胶，骨架直径1-5mm，骨架之间相距2-20mm。
本发明优点在于：1. 导热系数低，能够在高温（＞800℃）环境下使用，随着温度的升高材料导热系数变化不明显；2. 材料重量轻，密度仅为0.3-0.5g/cm3；3. 耐高速气流的冲刷，材料的上下表面为具有一定厚度和致密度的C/C复合材料层，能够保护中间气凝胶不被高速气流带走。
附图说明
图1为一种低导热耐高温碳纤维立体织物复合材料截面图。
[10]为沉积有热解碳基体的支撑骨架，[20]为二氧化硅气凝胶，[30]为上下外壳层。
具体实施方式
下面结合具体实施例，进一步阐明本发明，应理解这些实施例仅用于说明本发明而不用于限制本发明的范围，在阅读了本发明之后，本领域技术人员对本发明的各种等价形式的修改均落于本申请所附权利要求所限定。
实施例一
一种低导热耐高温碳纤维立体织物复合材料，其特征在于由碳纤维立体织物、热解碳基体和二氧化硅气凝胶构成，碳纤维立体织物具有上下两外壳层，两外层中碳纤维体积含量为40%，两外层厚度均为3mm，上下两外壳层之间相距2cm，上下两外壳层之间由相互绞联的碳纤维束连接，形成支撑上下两外壳层的骨架，其中碳纤维表面沉积热解碳基体，热解碳基体厚度为800μm，骨架之间填充二氧化硅气凝胶，骨架直径4mm，骨架之间相距15mm。
实施例二
一种低导热耐高温碳纤维立体织物复合材料，其特征在于由碳纤维立体织物、热解碳基体和二氧化硅气凝胶构成，碳纤维立体织物具有上下两外壳层，两外层中碳纤维体积含量为35%，两外层厚度均为1mm，上下两外壳层之间相距1cm，上下两外壳层之间由相互绞联的碳纤维束连接，形成支撑上下两外壳层的骨架，其中碳纤维表面沉积热解碳基体，热解碳基体厚度为100μm，骨架之间填充二氧化硅气凝胶，骨架直径1.5mm，骨架之间相距5mm。

Claims (1)

1.一种低导热耐高温碳纤维立体织物复合材料，其特征在于由碳纤维立体织物、热解碳基体和二氧化硅气凝胶构成，碳纤维立体织物具有上下两外壳层，两外层中碳纤维体积含量为30-40%，两外层厚度均为1-3mm，上下两外壳层之间相距1-2cm，上下两外壳层之间由相互绞联的碳纤维束连接，形成支撑上下两外壳层的骨架，其中碳纤维表面沉积热解碳基体，热解碳基体厚度为10-1000μm，骨架之间填充二氧化硅气凝胶，骨架直径1-5mm，骨架之间相距2-20mm。
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109437951A (zh) * 2018-11-29 2019-03-08 苏州宏久航空防热材料科技有限公司 一种轻质耐烧蚀隔热一体化结构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101857456A (zh) * 2010-06-11 2010-10-13 垦利三合新材料科技有限责任公司 一种c/c复合材料的制备方法
JP2013024341A (ja) * 2011-07-22 2013-02-04 Gunze Ltd 断熱カバー及びその施工方法
CN103101262A (zh) * 2013-02-19 2013-05-15 中国人民解放军国防科学技术大学 一种耐高温隔热夹层结构复合材料及其制备方法

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101857456A (zh) * 2010-06-11 2010-10-13 垦利三合新材料科技有限责任公司 一种c/c复合材料的制备方法
JP2013024341A (ja) * 2011-07-22 2013-02-04 Gunze Ltd 断熱カバー及びその施工方法
CN103101262A (zh) * 2013-02-19 2013-05-15 中国人民解放军国防科学技术大学 一种耐高温隔热夹层结构复合材料及其制备方法

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109437951A (zh) * 2018-11-29 2019-03-08 苏州宏久航空防热材料科技有限公司 一种轻质耐烧蚀隔热一体化结构

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