CN114620999B - 一种火箭发射台用无机热防护涂层修补料配方及其应用 - Google Patents

一种火箭发射台用无机热防护涂层修补料配方及其应用 Download PDF

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CN114620999B
CN114620999B CN202011457803.1A CN202011457803A CN114620999B CN 114620999 B CN114620999 B CN 114620999B CN 202011457803 A CN202011457803 A CN 202011457803A CN 114620999 B CN114620999 B CN 114620999B
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鹿小林
马磊
王国鹏
张万生
王晓东
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Dalian Institute of Chemical Physics of CAS
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Abstract

本发明公开一种火箭发射台用无机热防护涂料修补料的配方及其应用。本发明所述的热防护涂料修补料由粒度级配后的粉料与液体结合剂组成：其中粉料采用了刚玉细粉、莫来石细粉、蓝晶石细粉三级粒度匹配，具有合适的体密，修补料粒度最大为1mm，可以用于修补减薄厚度为1～3mm的区域；本修补料以硅溶胶作为液体结合剂，直接添加于预先混合完成粉料中，搅拌均匀后涂抹使用。该修补料有以下优点：1.粘接性好：2.该热防护涂料修补料配方简单，固化速度快。3.该修补料体积密度低；4.该修补料成型快；5.成型后修补料具有一定的机械强度、具有一定的隔热性能和耐烧蚀性能；成型后耐腐蚀性耐水性优异，可以用于航天等行业。

Description

一种火箭发射台用无机热防护涂层修补料配方及其应用
技术领域
本发明涉及一种火箭发射台用热防护涂料修补料，具体的是指一种火箭发射台用无机热防护涂料表面减薄修补料，属于耐高温绝热防护领域。
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，对地面设施如火箭发射台也增加了热防护措施。国内火箭发射台采用在基体材料表面涂覆无机耐火材料以保护发射台免受高温燃气流的热烧蚀和热冲击。因火箭发射台面积较大，部分区域受燃气流烧蚀影响较小，仅发生1～3mm的减薄。目前，对于1～3mm减薄区域的处理方式是不进行修补处理，待损耗厚度达到6mm以上再进行重新施工。如果不对该区域进行修补，该区域的耐烧蚀性能会有一定的减弱(耐烧蚀性能和隔热性能可能无法满足保护发射台的要求)，并且其表面无法满足外观统一的要求。
本发明为粒度级配后的粉料与液体结合剂组成的修补料，可以对减薄 1-3mm的热防护涂层进行修补，确保热防护涂层耐烧蚀性能的可靠性，保证热防护涂层表面外观的统一性。
发明内容
本发明目的在于为发生减薄现象的火箭发射台热防护涂层提供一种常温固化的无机修补料的配方及其应用。无机热防护涂料修补料由粒度级配后的粉料与液体结合剂组成。
本发明解决上述问题所采用的技术方案是：
所述的级配的粉料是由下述重量配比的原料，总计100％，制备而成：
种类 质量比
刚玉 52～75％
莫来石 8～25％
蓝晶石 10～30％
高铝水泥 3～12％
氧化铝微粉 1～10％
硅微粉 1～12％
所述的级配的粉料优选重量配比为：
所述的级配的粉料最佳重量配比为：
种类 质量比
刚玉 58～68％
莫来石 12～20％
蓝晶石 15～25％
高铝水泥 3～8％
氧化铝微粉 1～7％
硅微粉 1～8％
所述的刚玉是由粒度为1～0.15mm和100～300目的刚玉混合得到的混料，所述混料中，粒度为1～0.15mm的刚玉和粒度为100～300目的刚玉的重量比为1：(0.9～1.5)；
所述蓝晶石的粒度为100～300目，优选为200目；
所述莫来石的粒度为300～400目，优选为325目；
所述的高铝水泥为铝酸盐水泥，优选为Secar71水泥；
所述硅微粉为硅灰，优选型号为970。
所述的Al2O3微粉的粒度为400目，优选为质量含量(Al2O3)≥99.8％。
所述的液体结合剂为硅溶胶，优选为质量含量(SiO2)≥30％，Ph≥9，胶体粒子平均粒度：(8～15nm)。
所述的硅溶胶和预混级配粉料的重量比为1：(2～8)。
火箭发射台用无机热防护涂层修补料的制备方法为：
(1)级配粉料的制备
火箭发射台热防护涂料修补料的级配粉料，其特征在于：热防护涂料修补料级配粉料的制备方法为：按照重量配比称取各种原料，先加入 1～0.15mm和100～300目刚玉粉料、100～300目蓝晶石粉料、300～400目莫来石粉料混合均匀，在搅拌机里搅拌2～3分钟，再加入其他粉料搅拌6～8 分钟，以确保各种原料混合均匀。
(2)粉料与液体结合剂的制备
将硅溶胶与级配粉料按照质量比例1：(2～8)在搅拌机内搅拌6～ 10min，即可以施工涂覆修补。
本发明的优点和有益效果是：
本发明利用级配的粉料和硅溶胶混合而成并涂覆于减薄(1-3mm)的热防护涂层之上进行修补。粉料采用高温性能优异的0.15～1mm和100～300目的刚玉作为骨料主体，加入300～400目高温性能优异、抗热震性能好的莫来石填充缝隙；100～300目蓝晶石的加入增强了成型后修补料的体积稳定性；添加氧化铝微粉因为微粉的填充及分散促进作用，修补料的流动性增加，提高其施工性能。添加纳米硅溶胶作为结合剂，硅溶胶分布于耐火材料颗粒表面，在颗粒周围形成凝胶，成型后凝胶把骨料之间和骨料与原热防护涂料层结合在一起形成一个整体，并能与原无机热防护涂层间有较强的粘接性能；添加高铝水泥，水泥的水合反应加强修补料的强度，并缩短修补料固化时间。修补料成型后具有一定的隔热性能和耐烧蚀性能，能够保证经过修补后减薄的热防护涂料仍能够满足发射台热防护的指标。适用于高湿、高盐雾、高紫外线照射的环境，防腐蚀性能好。
附图说明
图1烧蚀试验背温数据图；
图2本发明材料进行修补示意图；图中：1为无机热防护涂料层，2为修补料。
具体实施方式
下面结合具体实施例和附表来进一步描述本发明，本发明的优点和特点将会随着描述而更为清楚。
实施例1
1.修补料的制备
粒度级配的粉料按重量配比的称取24％的粒度为1-0.15mm的刚玉； 37％粒度100目的刚玉；10％的粒度为325目的莫来石；19％的粒度为200 目蓝晶石；6％的Secar71水泥；2％的970型硅灰；2％的400目Al2O3微粉；
硅溶胶同粒度级配的粉料质量比为1：6。所述的液体结合剂为硅溶胶，优选为质量含量(SiO2)≥30％，Ph≥9，胶体粒子平均粒度：(8～15nm)。
实施例1的制作方法是：按照重量配比称取各种原料，先加入1～0.15mm 和100目刚玉粉料、200目蓝晶石粉料、325目莫来石粉料混合均匀，在搅拌机里搅拌2～3分钟，再加入其他粉料搅拌6～8分钟，以确保各种原料混合均匀。
将硅溶胶与级配粉料按照质量比例1：6在搅拌机内搅拌6～10min，即可以施工涂覆修补。
2.修补料的涂覆
(1)采购一种火箭发射台用莫来石基热防护涂料，制成2个尺寸为长*宽*厚＝190×120×27mm的样块。(2)涂覆上述1中制备的无机热防护涂料修补料涂覆于步骤(1)中制备的2块尺寸为190×120×27mm的样块之上，涂覆厚度分别为3mm，1mm。
3.烧蚀结果
采用YA6804型氧气煤油发动机对上述制备的样块进行试验件背面温度的测试。试验条件：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；燃烧室温度：3470K；烧蚀试验时间：5s/件；热流密度：17.9Mw/m2。试验条件为模拟火箭发射时的尾焰吹扫情况，火焰吹扫涂有无机热防护修补料面。测试未涂覆修补料一侧的温度(背面温度)。烧蚀结果如图1所示：涂覆厚度为3mm样块烧蚀后在223s时，出现最高背温70℃，涂覆厚度为1mm样块烧蚀后在232s时，出现最高背温71℃。烧蚀试验过程中均未出现修补料脱层并吹飞的现象。涂覆厚度为3mm的样块经过烧蚀试验后，样块表面仍有未烧蚀掉的修补料。
对比例1
1.采购实施例1中同种的火箭发射台用莫来石基热防护涂料，制成尺寸为长*宽*厚＝190×120×27mm的样块。
2.对金属钢板上隔热性胶黏剂进行隔热的烧蚀试验
采用和实施例1中同样的YA6804型氧气煤油发动机，在同样的实验条件待对比例1中制备的样块进行试验件背面温度的测试。烧蚀结果如图1 所示：烧蚀后样块的背温最高温度74℃，出现最高温度对应的时间193s。
通过实施例1和对比例1的烧蚀试验结果，我们可以看出在相同的试验条件下，实施例1中采用了本专利中无机热防护修补料分别涂覆了3mm 和1mm，温度相对于对比例1中的样块背温降低了4℃和3℃，所以涂覆了无机修补料的涂层具有一定的耐烧蚀和隔热性能；且在试验过程中修补料在高速燃气流作用仅发生烧蚀现象而未发生脱层现象，说明修补料同原涂层的粘接力能够满足需求。
修补料粒度最大为1mm，可以用于修补减薄厚度为1～3mm的区域；本修补料以硅溶胶作为液体结合剂，直接添加于预先混合完成粉料中，搅拌均匀后涂抹使用。该修补料有以下优点：1.粘接性好：修补料与原无机热防护涂层间有较高的粘接性，修补后没有分层和脱层的现象。2.该热防护涂料修补料配方简单，原料易得，生产简易，易于施工，在常温下可修补，固化速度快。3.该修补料体积密度低，火箭发射时不会产生多余物对火箭箭体造成损伤；4.该修补料成型快，成型后修补料不会因为环境问题(风、高温、暴晒)而产生裂纹，适用于高湿、高盐雾、高紫外线照射的环境；5. 成型后修补料具有一定的机械强度、具有一定的隔热性能和耐烧蚀性能；成型后耐腐蚀性耐水性优异，可以用于航天等行业。

Claims (2)

1.一种火箭发射台用热防护涂料修补料的应用，其特征在于：它由粉料与液体结合剂组成；
粉料是由下述重量配比的原料混合而成，总计100%：刚玉58~68%，莫来石12~20%，蓝晶石19~25%，高铝水泥3~8%，氧化铝微粉1~7%，硅微粉1~8%；所述蓝晶石的粒度为100~300目；
液体结合剂为硅溶胶，硅溶胶和粉料的重量比为1：（2～8）；
该修补料作用于火箭发射台表面的、减薄厚度为1~3mm的无机热防护涂料表面；
所述的液体结合剂为硅溶胶，质量含量SiO2≥30%，pH≥9，胶体粒子平均粒度：8~15nm；
所述修补料中的粉料是由粒度级配后的粉料，所述的刚玉是由粒度为1~0.15mm和100~300目刚玉混合得到的混料，所述混料中，粒度为1~0.15mm 的刚玉和粒度为100~300目的刚玉的重量比为1：(0.9～1.5) ；所述莫来石粉的粒度为300~400目；所述的高铝水泥为铝酸盐水泥；所述硅微粉为硅灰，所述的氧化铝微粉的粒度为400-450目。
2.根据权利要求1所述的应用，其特征在于：火箭发射台热防护涂料修补料的混合方法为：
1）按照重量配比称取各种粉料原料，先加入1~0.15mm和100~300目刚玉粉料、100~300目蓝晶石粉料、300~400目莫来石粉料混合均匀，在搅拌机里搅拌2～3分钟，再加入其他粉料搅拌6～8分钟，以确保各种原料混合均匀；
2）将液体结合剂和预混粉料的重量比为1：（2～8）混合搅拌6～10min。
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