CN111217593A - 一种火箭发射台用刚玉-莫来石基不定形耐高温材料 - Google Patents

一种火箭发射台用刚玉-莫来石基不定形耐高温材料 Download PDF

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CN111217593A
CN111217593A CN201811413228.8A CN201811413228A CN111217593A CN 111217593 A CN111217593 A CN 111217593A CN 201811413228 A CN201811413228 A CN 201811413228A CN 111217593 A CN111217593 A CN 111217593A
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鹿小林
马磊
王国鹏
赵许群
张万生
王晓东
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Dalian Institute of Chemical Physics of CAS
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Abstract

本发明公开了一种火箭发射台用刚玉‑莫来石基不定形耐火材料，该不定形耐火材料的组成组分由刚玉、莫来石、堇青石、碳化硅、Al2O3细粉、电熔锆刚玉、高铝水泥和硅微粉组成。该不定形耐高温材料能够保护火箭发射台金属结构不受高温燃气流的冲刷和高温烧蚀，有利于确保发射台工作的可靠性，延长发射台使用寿命；该定形耐火材料集合了刚玉和莫来石各自的优异性能，具有优良的热震稳定性、蠕变性、耐磨性，并且其机械强度高、高温性能好、导热低，适用于高湿、高盐雾、高紫外线照射的环境，防腐蚀性能好，符合火箭发射基地在向运输和发射更为便捷的沿海区域发展对保护火箭发射台基体防护材料的要求；该刚玉‑莫来石基涂抹料施工简单方便。

Description

一种火箭发射台用刚玉-莫来石基不定形耐高温材料
技术领域
本发明设计一种火箭发射台用不定形耐火材料，具体的是指一种火箭发射台用刚玉-莫来石基不定形耐火材料，属于高温绝热防护领域。
背景技术
随着航天、宇航事业的发展，除了飞行器本身进行热防护外，国内对地面设施如火箭发射台也增加了热防护措施。如果将发射台涂以热防护涂料，可使金属表面隔热，减少热烧蚀和热冲击，并防止发射台在多次热冲击载荷作用下产生热疲劳、热龟裂和热断裂、以及发射时持续喷水产生的强烈的热震效应对发射台造成的巨大损害，从而确保发射台工作的可靠性，延长发射台的使用寿命。在国外，欧洲航天局位于南美圭亚那的阿里安火箭发射平台为混凝土发射平台，这类完全由无机非金属材料构筑的发射台抗燃气吹扫烧蚀性能比有机烧蚀涂料好，但缺点是厚度厚、重量重，并且发射台无法进行移动。
本发明采用不定形耐火材料对火箭发射台进行热防护，以达到减轻发射台重量，是发射台耐热烧蚀、耐热冲击以及耐强烈的热震，确保发射台工作的可靠性，延长发射台使用寿命的目的。
发明内容
本发明所要解决的技术问题是对地面设施火箭发射台增加热防护措施，提供一种能够在火箭发动机高温、大推力、长时间且存在强烈热震情况下，对火箭发射台起到增加钢结构合理的强度和保护台面，延长发射台使用寿命的作用。该耐高温材料具有优异的热震稳定性、蠕变性、耐磨性、机械强度高、高温性能好、耐火箭尾焰燃气流冲刷性好、耐候性好、节能环保。
本发明解决上述问题所采用的技术方案是：
一种火箭发射台用刚玉-莫来石基不定形耐火材料，主要由刚玉、莫来石、堇青石、碳化硅、Al2O3细粉、电熔锆刚玉、高铝水泥和硅微粉等组成，其化学重量百分比如下表：
莫来石 22％-55％
刚玉 8％-32％
堇青石 10％-32％
高铝水泥 13％-30％
SiC 1％-10％
硅微粉 1％-10％
电熔锆刚玉 2％-8％
原料的优选重量配比为：
Figure BDA0001878721560000021
Figure BDA0001878721560000031
所述的莫来石由粒度为5-3mm和粒度为0.045-0.088mm的莫来石混合得到的混料，所述混料中，粒度为5-3mm的莫来石和粒度为0.045-0.088mm的莫来石的质量比为1：(0.2-1.1)。
所述的刚玉是由粒度0.088-1mm和Al2O3微粉混合得到的混料，所述混料中，粒度0.088-1mm的刚玉和Al2O3微粉的质量比为1：
(0.1-0.6)。
所述的堇青石的粒度为0.5-1mm。
所述的SiC的粒度为0.106-0.09mm。
所述的高铝水泥为铝酸盐水泥，优选为Secar71水泥。
所述的硅微粉为硅灰，优选型号为970。
所述的电熔锆刚玉为高电熔锆刚玉(ZrO2≥35％)。
火箭发射台用刚玉-莫来石基不定形耐火材料的制备方法为：按照重量配比城区各种原料，先加入5-3mm和0.045-0.088mm的莫来石颗粒、0.088-1mm刚玉和0.5-1mm堇青石颗粒充分混合均匀，在行星式搅拌机中搅拌10min，再加入其他粉料搅拌10-15min，以确保各种原料混合均匀。
本发明所述的火箭发射台用刚玉-莫来石基不定形耐高温材料作为火箭发射台的表面涂层使用，涂覆在发射台钢板表面上，厚度为8-30mm。
本发明的有点和有益效果是：
采用本发明的原料重量配比及制作方法制备火箭发射台刚玉-莫来石基不定形耐高温材料，主体骨料采用不同粒度等级和不同种类的原料，其中较大粒度的原料起骨架作用，较小粒度的原料起填充作用，其中粒状的刚玉晶体填充在联锁交错莫来石网络结构的间隙，促进了致密的堆积和更紧密的晶体结合，达到了极好的强化作用。添加SiC的加入可以提高不定形耐火材料的流变性和抗热震稳定性。添加电熔锆刚玉主要增加不定形耐火材料的常温和高温抗折强度。添加硅微粉，能减少加水量，以提高材料的体积密度，降低气孔率；添加高铝水泥，能使材料有适当的强度，并且不影响材料的耐高温性能。按本发明专利制备的火箭发射台用刚玉-莫来石基不定形耐火材料与其他材料相比热震稳定性优异，可重复在喷水条件下耐火箭尾焰燃气流冲刷多次；常温和高温强度高，有利于保持火箭发射台钢板的合理的强度，增加发射台服役年限；且使用简单方便，成型稳定。
附图说明
图1实验结果图，a为未烧蚀的涂覆莫来石-刚玉不定形耐火层的实验样块(190mm×120mm×5mm)，涂层厚度为30mm，样块表面平整；b为a样块经过一次烧蚀后，立即喷水冷却处理后的样块，样块出现局部减薄，且未出现裂纹和涂层的脱落的现象；c为b样块在相同烧蚀条件下烧蚀一次后，立即喷水冷却处理后的样块，样块同样出现局部减薄，也未出现裂纹和涂层的推落；d为c样块在相同烧蚀条件下烧蚀加喷水处理后的样块，样块出现小部分的脱落，但并仍未出现裂纹。
具体实施方式
下面结合具体实施例对本发明做进一步的详细说明。
所述莫来石的生产厂家是靖州华鑫莫来石有限公司；所述的板状刚玉的生产厂家是河南锐石集团；所述堇青石的生产厂家偃师市光明高科耐火材料制品有限公司；所述Secar71水泥的生产厂家是凯诺斯(中国)铝酸盐技术有限公司；所述型号970硅灰的生产厂家是上海天恺硅粉材料有限公司。所述的电熔锆刚玉的生产厂家是河南锐石集团；所述的SiC的生产厂家是宜兴鹏扬耐火材料有限公司。
实施例1
按重量配比称取粒度为5-3mm的莫来石20份；粒度0.045-0.088mm的莫来石14份；粒度0.088-1mm的刚玉18份；粒度为0.5-1mm堇青石22份；SiC,2份；Secar71水泥，18份；电熔锆刚玉，1份；α-Al2O3细粉，2份；970型硅灰，3份。水，12份(外加)。其制作方法是：按照重量配比城区各种原料，先加入5-3mm和0.045-0.088mm的莫来石颗粒、0.088-1mm刚玉和0.5-1mm堇青石颗粒充分混合均匀，在行星式搅拌机中搅拌10min，再加入其他粉料搅拌10-15min，以确保各种原料混合均匀.最后加入水搅拌5-10min。
实施例2
按重量配比称取粒度为5-3mm的莫来石18份；粒度0.045-0.088mm的莫来石16份；粒度0.088-1mm的刚玉14份；粒度为0.5-1mm堇青石21份；SiC,5份；Secar71水泥，18份；电熔锆刚玉，3份；α-Al2O3细粉，2份；970型硅灰，3份。水，10份(外加)。制作过程同上实施例1。
实施例3
按重量配比称取粒度为5-3mm的莫来石18份；粒度0.045-0.088mm的莫来石16份；粒度0.088-1mm的刚玉14份；粒度为0.5-1mm堇青石21份；SiC,2份；Secar71水泥，18份；电熔锆刚玉，3份；α-Al2O3细粉，5份；970型硅灰，3份。水，10份(外加)。制作过程同上实施例1。
下表是上述实施例所制备的火箭发射台用刚玉-莫来石基不定形耐火材料的各项物理性能。
Figure BDA0001878721560000061
表中各项理化性能参数测定分别按照下列标准进行：
体积密度按照YB/T5200-1993致密耐火浇注料显气孔率和体积密度试验方法测定；
常温抗折强度按照GB/T3001-2007耐火材料常温抗折强度试验方法测定；
常温耐压强度按照GB/T5072-2008耐火材料常温耐压强度试验方法测定；
导热系数按照YB/T4130-2005耐火材料导热系数试验方法(水流量平板法)测定；
实施例4
按实施例1中的配方进行缩比发动机尾焰烧蚀的热震稳定性极限次数实验。测试条件为：发动机燃料：氧气和煤油；发动机燃烧室压力：Pc＝1.4±0.05MPa；发动机余氧系数：α＝0.7±0.03；发动机喷口直径：65mm；喷管出口燃气温度：2210K喷管出口燃气速度：2390m/s；燃烧室度：3470K；烧蚀试验时间：10s/件；热流密度：17.9Mw/m2。
实验结果如下图1，由图可以出:a为未烧蚀的涂覆莫来石-刚玉不定形耐火层的实验样块(190mm×120mm×5mm)，涂层厚度为30mm，样块表面平整；b为a样块经过一次烧蚀后，立即喷水冷却处理后的样块，样块出现局部减薄，且未出现裂纹和涂层的脱落的现象；c为b样块在相同烧蚀条件下烧蚀一次后，立即喷水冷却处理后的样块，样块同样出现局部减薄，也未出现裂纹和涂层的推落；d为c样块在相同烧蚀条件下烧蚀一次后，立即喷水处理后的样块，样块出现小部分的脱落，但并仍未出现裂纹。该配方可以耐受3次缩比发动机尾焰烧蚀加喷水冷却的热震实验，其中第三次烧蚀后出现脱落是由于前两次的涂层减薄导致的，而且三次后仍无裂纹，充分说明了材料优异的热震稳定及高温的强度。刚玉-莫来石致密的网状结构的骨架，其中堇青石、SiC和电熔锆刚玉的低膨胀系数和高低温的强度，使材料具有优异的热震稳定性和高温强度。
结论:本发明保护的不定形耐火材料的组分和比例具有良好的常温抗折强度和耐压强度，具有较低的热膨胀系数和适当的导热系数，并且能够耐受3次高温燃气流冲刷的热震试验后，且没有产生涂层大面积脱落等不良现象。

Claims (6)

1.一种火箭发射台用刚玉-莫来石基不定形耐高温材料，其特征在于：它是由下述重量配比的原料，混合而成：各原料之和总计为100％，莫来石22％-55％，刚玉8％-32％，堇青石10％-32％，高铝水泥13％-30％，SiC 1％-10％，粒度为0.1-0.3μm的硅微粉1％-10％，电熔锆刚玉1％-8％。
2.一种火箭发射台用刚玉-莫来石基不定形耐高温材料，其特征在于：它是由下述重量配比的原料，混合而成：各原料之和总计为100％，莫来石28％-50％，刚玉10％-30％，堇青石15％-28％，高铝水泥15％-25％，SiC 3％-9％，粒度为0.1-0.3μm的硅微粉1％-7％，电熔锆刚玉1％-6％。
3.根据权利要求1或2所述的火箭发射台用刚玉-莫来石基不定形耐高温材料，其特征在于：所述的莫来石是由粒度为5-3mm和粒度为0.045-0.088mm的莫来石混合得到的混料，所述混料中，粒度为5-3mm的莫来石和粒度为0.045-0.088mm的莫来石的质量比为1：(0.2-1.1)。
4.根据权利要求1或2所述的火箭发射台用刚玉-莫来石基不定形耐高温材料，其特征在于：所述的刚玉是由粒度0.088-1mm和Al2O3微粉混合得到的混料，所述混料中，粒度0.088-1mm的刚玉和Al2O3微粉的质量比为1：(0.1-0.6)。
5.根据权利要求1或2所述的火箭发射台用刚玉-莫来石基不定形耐高温材料，其特征在于：所述的堇青石的粒度为0.5-1mm；所述的SiC的粒度为0.106-0.09mm；所述的高铝水泥为铝酸盐水泥；所述的硅微粉为粒度为0.1-0.3μm的硅灰。
6.根据权利要求1或2所述的火箭发射台用刚玉-莫来石基不定形耐高温材料，其特征在于：电熔锆刚玉为高电熔锆刚玉(ZrO2≥35％)。
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