CN106904973B - 一种轻质高强的泡沫碳基绝热复合材料 - Google Patents
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Abstract
一种轻质高强的泡沫碳基绝热复合材料，其特征在于所述的泡沫碳基复合材料包括基材泡沫碳，碳化硅涂层，网状碳化硅纳米线，碳化硅涂层包覆在泡沫碳骨架表面，网状碳化硅纳米线填充三维孔隙，孔隙率为90％～95％，平均孔径为50nm～500nm，表观密度为0.05～0.2g/cm3，抗压强度为5～15MPa。泡沫碳为柔性泡沫碳，由三聚氰胺泡沫高温热解得到，孔隙率为99％以上，平均孔径为20～50μm碳化硅涂层厚度为0.5～1μm，碳化硅纳米线直径为50～300nm，平均长度为30～50μm，均是采用化学气相沉积法制。本发明具有的优点：1、SiC包覆泡沫碳骨架表面，提高复合材料抗氧化能力；2、SiC包覆泡沫碳骨架表面，提高复合材料力学性能；3、碳化硅纳米线分割泡沫内部孔隙，减小内部孔径大小，降低材料的热导率。
Description
技术领域
本发明涉及一种泡沫碳基绝热复合材料，特别涉及一种轻质高强的泡沫碳基绝热复合材料。
背景技术
随着航天飞行器和导弹的发展，新型高超声速飞行器在稠密大气层长时巡航或再入过程中会遭受严重的气动加热。为防止高速飞行器长时间飞行时的气动加热对内部结构和仪器的热损坏，这类飞行器需要耐高温、高效、轻质的热防护系统。但是现有的有机隔热材料使用温度不高，而用于高温隔热的无机纤维隔热材料的隔热效果受到生产工艺的限制难以进一步的提高，特别是在高温环境下其导热系数相对室温环境大幅度增加。因此，传统隔热材料往往需要通过增加尺寸来提高隔热效果。而隔热材料的加厚则使飞行器的重量和使用成本大幅度增加，性能大幅降低。因此，寻求一种新型耐高温、轻质、高效的隔热材料是未来导弹、航天飞行器等表面热防护技术设计所追求的目标。
泡沫碳是一种碳素骨架和相互连通的孔腔组成的具有三维网状结构的轻质多孔材料，碳原子之间以一定的成键方式相互连接，密度约为0.05～0.1g/cm3。非石墨化泡沫碳具有密度低、热性能优异、尺寸稳定性好、抗热冲击性等优点，既是一种极具潜力的隔热材料，又是一种高性能的结构材料。但柔性泡沫碳抗压强度低，在严苛、复杂的气动环境可靠性难以保证，因此，需要通过改性提高柔性碳泡沫的抗压性能。陶瓷材料因具有优良的热稳定性和化学稳定性，可在高达1000℃以上温度工作，并且在氧化、还原等高温环境下具有很好的抗腐蚀性、强度保持率，比如碳化硅具有强度高、导热性好、热膨胀系数小、抗热冲击性强、高温高强度特点，能在高温交变热冲击环境中长期服役。这使得陶瓷材料在高温下具有突出的抗载荷能力。因此，本发明采用柔性碳泡沫与高强碳化硅陶瓷复合制备轻质、高强的隔热复合材料。
申请号为201410157562.7的中国发明专利公开了一种弹性碳泡沫氧气还原催化剂及其制备方法，其特征在于该弹性碳泡沫氧气还原剂是在含微量氧条件下，直接高温碳化三聚氰胺泡沫材料制备而成，通过该方法制备的弹性碳泡沫具有自支撑的三维网络结构、良好的回弹性，优异的氧气还原催化性能，并且其氧气还原性能和弹性可以通过调节微氧的浓度来调控。该专利是采用三聚氰胺泡沫热解得到碳泡沫应用于氧气还原催化剂载体，与本专利应用领域不相同，因此制备工艺以及材料结构存在较大的差异。
申请号为201410743407.3的中国发明专利公开了一种耐高温高强度SiC包覆碳泡沫复合隔热材料及其制备方法，其特征在于该耐高温高强度SiC包覆碳泡沫复合隔热材料是一种由碳泡沫和碳化硅气凝胶构成；其空气气氛中耐温性在690～700℃，比纯碳泡沫材料提高了约 100℃，表观密度在0.4～0.6g/cm3，抗压强度在11～15MPa，室温热导率在0.4～0.6W/(m.K)。其制备方法是二氧化硅溶胶注入到碳泡沫材料的孔洞中，经过溶胶-凝胶、老化和干燥得到碳泡沫增强的氧化硅气凝胶复合隔热材料，然后在惰性氛围保护下进行高温热处理，从而制备出一种耐高温高强度SiC包覆碳泡沫复合隔热材料。该发明具有用料简单和工艺简捷的优点，工艺过程操作简单，容易实现规模生产。但是该制备方法得到的SiC包覆材料结构疏松，致密性差，对于碳泡沫在有氧环境中耐温容限与力学性能提升有限。
发明内容
本发明要解决的技术问题是克服现有技术的不足，旨在提供一种轻质高强的泡沫碳基绝热复合材料，其特征在于所述的泡沫碳基复合材料包括基材泡沫碳，碳化硅涂层，网状碳化硅纳米线，碳化硅涂层包覆在泡沫碳骨架表面，网状碳化硅纳米线填充三维孔隙，孔隙率为 90％～95％，平均孔径为50nm～500nm，表观密度为0.05～0.2g/cm3，抗压强度为5～15MPa。
所述的泡沫碳基绝热复合材料，其特征在于所述的泡沫碳为柔性泡沫碳，由三聚氰胺泡沫高温热解得到，孔隙率为99％以上，平均孔径为20～50μm。
所述的泡沫碳基绝热复合材料，其特征在于所述的碳化硅涂层是采用化学气相沉积法制备，涂层厚度为0.5～1μm。
所述的泡沫碳基绝热复合材料，其特征在于所述的碳化硅纳米线，采用化学气相沉积法制备，直径为50～300nm，平均长度为30～50μm。
本发明具有的优点：1、SiC包覆泡沫碳骨架表面，提高复合材料抗氧化能力；2、SiC包覆泡沫碳骨架表面，提高复合材料力学性能；3、碳化硅纳米线分割泡沫内部孔隙，减小内部孔径大小，降低材料的热导率。
附图说明
图1为轻质高强的泡沫碳基复合材料扫描电子显微镜图
图2为轻质高强的泡沫碳基复合材料结构示意图
10为轻质高强的泡沫碳基复合材料；20为泡沫碳；30为碳化硅涂层；40为碳化硅纳米线。
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1
参照图1，泡沫碳基复合材料包括基材泡沫碳，碳化硅涂层，网状碳化硅纳米线，碳化硅涂层包覆在泡沫碳骨架表面，网状碳化硅纳米线填充三维孔隙，孔隙率为96％，平均孔径为100nm，表观密度为0.05g/cm3，抗压强度为6MPa，碳化硅涂层厚度为0.5μm，碳化硅纳米直径为100nm，平均长度为42μm。
实施例2
参照图2，泡沫碳基复合材料包括基材泡沫碳，碳化硅涂层，网状碳化硅纳米线，碳化硅涂层包覆在泡沫碳骨架表面，网状碳化硅纳米线填充三维孔隙，孔隙率为94.5％，平均孔径为60nm，表观密度为0.06g/cm3，抗压强度为9MPa，碳化硅涂层厚度为0.7μm，碳化硅纳米直径为60nm，平均长度为40μm。
上述仅为本发明的两个具体实施方式，但本发明的设计构思并不局限于此，凡利用此构思对本发明进行非实质性的改动，均应属于侵犯本发明保护的范围的行为。但凡是未脱离本发明技术方案的内容，依据本发明的技术实质对以上实施例所作的任何形式的简单修改、等同变化与改型，仍属于本发明技术方案的保护范围。
Claims (4)
1.一种轻质高强的泡沫碳基绝热复合材料，其特征在于所述的泡沫碳基复合材料包括基材泡沫碳，碳化硅涂层，网状碳化硅纳米线，碳化硅涂层包覆在泡沫碳骨架表面，网状碳化硅纳米线填充三维孔隙，孔隙率为90％～95％，平均孔径为50nm～500nm，表观密度为0.05～0.2g/cm3，抗压强度为5～15MPa。
2.根据权利要求1所述的泡沫碳基绝热复合材料，其特征在于所述的为柔性泡沫碳，由三聚氰胺泡沫高温热解得到，孔隙率为99％以上，平均孔径为20～50μm。
3.根据权利要求1所述的泡沫碳基绝热复合材料，其特征在于所述的碳化硅涂层是采用化学气相沉积法制备，涂层厚度为0.5～1μm。
4.根据权利要求1所述的泡沫碳基绝热复合材料，其特征在于所述的碳化硅纳米线，采用化学气相沉积法制备，直径为50～300nm，平均长度为30～50μm。
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| CN109836165B (zh) * | 2017-11-27 | 2021-10-15 | 航天特种材料及工艺技术研究所 | 一种SiC泡沫及其制备方法 |
| CN109485448A (zh) * | 2018-11-29 | 2019-03-19 | 苏州宏久航空防热材料科技有限公司 | 一种SiC泡沫/碳泡沫复合绝热材料及其制备方法 |
| CN109721945A (zh) * | 2019-01-16 | 2019-05-07 | 苏州宏久航空防热材料科技有限公司 | 一种高介电常数无机泡沫树脂基复合材料基板及其制备方法 |
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