CN109397802A - 一种柔性复合防热套管及其制备方法 - Google Patents
一种柔性复合防热套管及其制备方法 Download PDFInfo
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- CN109397802A CN109397802A CN201811533000.2A CN201811533000A CN109397802A CN 109397802 A CN109397802 A CN 109397802A CN 201811533000 A CN201811533000 A CN 201811533000A CN 109397802 A CN109397802 A CN 109397802A
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Abstract
本发明公开了一种柔性复合防热套管及其制备方法,包括内层、外层和中间层,内层为硅橡胶管层,外层为铝箔复合防热布层,中间层从内至外依次为气凝胶低导热涂料层、相变储能涂料层、阻燃隔热涂料层和石英玻璃纤维层。制备该柔性复合防热套管的方法如下:将加成型液体硅橡胶、二氧化硅气凝胶粉按照质量比为65‑80:3混合得到气凝胶低导热涂料;将加成型液体硅橡胶中、有机固‑固相变材料按照质量比为6:3‑5混合得到相变储能涂料;将加成型液体硅橡胶、硼酸锌、二氧化硅气凝胶粉、玻璃粉、陶瓷粉、氢氧化铝、轻质氧化镁、云母粉按照质量比为90‑110:3‑5:2‑4:10‑14:10‑14:1‑3:1‑6:4‑4混合得到阻燃隔热涂料。该柔性复合防热套管具有极低的导热系数和良好的抗烧灼能力。
Description
技术领域
本发明涉及航天材料技术领域,特别涉及到一种柔性复合防热套管及其制备方法。
背景技术
近年来随着航天的不断发展,越来越多的航天飞行器被送入广袤的太空中, 人们因此对飞行器中热防护系统所用的热防护材料提出了更高的防隔热要求。根据仿真试验发现,多数用于包裹电缆的防热套管在真空受热环境下,由于其导热系数过高、抗烧灼性能较差,容易炭化、分解漂浮在飞行器舱体内。考虑到舱体内部分元器件裸露,分解的防热套管存在导电性,在真空条件下极易附着在裸露的元器件上,从而造成短路的风险。
陶瓷基热防护材料具有耐气流冲刷、阻燃的优点,但是由于飞行器舱体内空间相对狭小,热防护系统内置的电缆、芯线成网状铺设,所用防护材料必须要求柔性较好且质轻,而陶瓷基热防护材料显然无法达到上述要求,极大地限制了其在热防护材料中的应用。另外,陶瓷基热防护材料虽然具备一定的耐气流冲刷、阻燃效果,但是该材料的导热系数较高,在较高的热流条件下容易造成芯线的表面温度过高并出现故障。
公开号为CN 105810335 A的中国专利公开了一种柔性轻质镶嵌复合防热套管及其生产方法。该生产方法包括以下工艺步骤:A编织石英玻璃纤维套管,并浸涂过渡涂料;B、将一根硅橡胶管穿入石英玻璃纤维套管内,两端绑扎固定,制作成坯管;C、将坯管浸涂蓄热涂料;D、将坯管浸涂隔热涂料;E、将坯管浸涂防热涂料;F、粘贴铝箔复合布。该结构的套管可在40kW/m2的热流条件下,800s内管内壁温升不高于100℃,然而一旦热流超过200kW/m2,其很容易造成电缆出现故障,而在航天飞行器的飞行过程中热流经常超过200kW/m2,因此,该防热套管能满足日常生活中的电缆包覆需求,而并不适合将其应用于航天飞行器中。
发明内容
本发明要解决的技术问题在于提供一种导热系数较低、抗烧灼性能较好的柔性复合防热套管,该柔性复合防热套管可应用于航天飞行器中并起到极为优异的耐高温效果。
本发明还提供了上述柔性复合防热套管的制备方法。
为了解决上述问题,采用以下技术方案:包括内层、外层和中间层,所述内层为硅橡胶管层,所述外层为铝箔复合防热布层,所述中间层从内至外依次为气凝胶低导热涂料层、相变储能涂料层、阻燃隔热涂料层和石英玻璃纤维层。
其中,所述气凝胶低导热涂料层的厚度为0.15-0.25mm,所述相变储能涂料层的厚度为0.4-0.6mm,所述阻燃隔热涂料层的厚度为0.8-1.2mm。
优选地,所述气凝胶低导热涂料层的厚度为0.2mm,所述相变储能涂料层的厚度为0.5mm,所述阻燃隔热涂料层的厚度为1.0mm。
制备上述柔性复合防热套管的方法,包括以下步骤:
A.涂覆气凝胶低导热涂料层:制备气凝胶低导热涂料并浸涂至硅橡胶管层上,烘烤固化;
B.涂覆相变储能涂料层:制备相变储能涂料并浸涂至气凝胶低导热涂料层上,烘烤固化;
C.涂覆阻燃隔热涂料层:制备阻燃隔热涂料并浸涂至相变储能涂料层上,烘烤固化;
D. 以3-6股石英玻璃纤维纱为原材料,编织得到石英玻璃纤维层;
E. 将铝箔复合防热布剪裁成带状,缠绕至石英玻璃纤维层外部,得到铝箔复合防热布层。
其中,所述气凝胶低导热涂料由加成型液体硅橡胶、二氧化硅气凝胶粉按照质量比为(65-80):3混合并搅拌均匀得到;所述相变储能涂料由加成型液体硅橡胶中、相变温度为180-190℃的有机固-固相变材料按照质量比为6:(3-5)混合并搅拌均匀得到;所述阻燃隔热涂料由加成型液体硅橡胶、硼酸锌、二氧化硅气凝胶粉、玻璃粉、陶瓷粉、氢氧化铝、轻质氧化镁、云母粉按照质量比为90-110:3-5:2-4:10-14:10-14:1-3:1-6:4-4混合并搅拌均匀得到。
优选地,所述加成型液体硅橡胶、二氧化硅气凝胶粉的质量比为70:3。
优选地,所述加成型液体硅橡胶、相变温度为180-190℃的有机固-固相变材料的质量比为6:4。
优选地,所述加成型液体硅橡胶、硼酸锌、二氧化硅气凝胶粉、玻璃粉、陶瓷粉、氢氧化铝、轻质氧化镁、云母粉的质量比为100:4:3:12:12:2:2:3。
和现有技术相比,本发明具有以下有益效果:该柔性复合防热套管中的硅橡胶管层用于包覆电缆,抗击打抗撕裂,且较为环保;硅橡胶管层的外层为气凝胶低导热涂料层,其可以有效降低防热套管的导热系数,从而减少了进入下一层相变储能涂料层的热量;而相变储能涂料层可将热量在传输过程中储存起来,就像热阻一样延长能量传输时间,减少温度梯度;阻燃隔热涂料层不仅可以有效阻燃、提高防热套管的抗烧灼性能,而且具有较低的导热系数,可进一步起到隔热的作用。
本发明中的柔性复合防热套管导热系数较低、阻燃性能好,将其包覆于电缆外部可起到很好的防热隔热效果。将该柔性复合防热套管放置于超过200kW/m2的热流条件下约一分钟后,芯线表面温度低于220℃;将该柔性复合防热套管在氧气压力0.5mPa,乙炔压力0.08mPa的火焰烧蚀下30s,防热套管内壁温度超过195℃(以上两个测试均为对航天飞行时受热环境的模拟测试)。即将柔性复合防热套管具有极低的导热系数和良好的抗烧灼能力,非常适合应用作航天飞行器中的热防护材料,具有极为广阔的应用前景。
附图说明
图1为本发明中柔性复合防热套管的横截面结构示意图。
图2为本发明中柔性复合防热套管的工艺流程图。
图中:
1——硅橡胶管层 2——气凝胶低导热涂料层 3——相变储能涂料层
4——阻燃隔热涂料层 5——石英玻璃纤维层 6——铝箔复合防热布层。
具体实施方式
下面给出实施例以对本发明进行具体的描述,有必要在此指出的是以下实施例只用于对本发明进行进一步说明,不能理解为对本发明保护范围的限制,该领域的普通技术人员根据该实施例对本发明所做出的一些非本质的改进或调整仍属于本发明的保护范围。
实施例1
一种柔性复合防热套管,如图1所示,包括内层、外层和中间层,内层为硅橡胶管层1,外层为铝箔复合防热布层6,中间层从内至外依次为气凝胶低导热涂料层2、相变储能涂料层3、阻燃隔热涂料层4和石英玻璃纤维层5。
其中,气凝胶低导热涂料层2的厚度为0.2mm,相变储能涂料层3的厚度为0.5mm,阻燃隔热涂料层4的厚度为1.0mm。
上述柔性复合防热套管的制备方法包括以下步骤:
(1)将硅橡胶管紧固、充气、表面处理、烘烤干燥
硅橡胶管两端用硅橡胶塞堵塞填充,再用金属材质在硅橡胶管两端绑扎紧固,采用气泵在管内充入空气,保持硅橡胶管两端成圆柱形;采用脱脂棉粘取工业酒精擦拭硅橡胶管;将擦拭干净的硅橡胶管通过立式橡胶机进行烘烤、干燥即得硅橡胶管层1,立式上胶机内温度控制在110-120℃,立式上胶机转速控制在100-200r/min。
(2)配制气凝胶低导热涂料
将加成型液体硅橡胶、二氧化硅气凝胶粉按质量比70:3比例投入混合,启动搅拌装置,搅拌均匀后加入由AR级二甲苯和环己酮按质量比为1:1混合而成的稀释剂,调节粘度,稀释剂的加入量约为加成型液体硅橡胶和二氧化硅气凝胶粉总质量的一半,继续搅拌至均相,即得气凝胶低导热涂料。
其中,上述二氧化硅气凝胶粉的粒径为5nm-15nm。
(3)浸涂气凝胶低导热涂料
将硅橡胶管通过立式上胶机内的油槽,油槽内加入配置好的气凝胶低导热涂料,反复浸渍、固化,得到气凝胶低导热涂料层2。
(4)烘烤固化
将立式上胶机内温度控制在110-120℃,立式上胶机转速控制在100-200r/min,将浸渍气凝胶低导热涂料后的硅橡胶管此环境中烘烤固化。
(5)配制相变储能涂料
将加成型液体硅橡胶、相变温度为180-190℃的有机固-固相变材料按质量比6:4比例投入混合,搅拌均匀后加入由AR级二甲苯和环己酮按质量比为1:1混合而成的稀释剂,调节粘度,稀释剂的加入量约为加成型液体硅橡胶和有机固-固相变材料总质量的一半,继续搅拌至均相,即得气凝胶低导热涂料。
(6)浸涂相变储能涂料
将硅橡胶管通过立式上胶机内的油槽,油槽内加入配置好的相变储能涂料,反复浸渍、固化,得到相变储能涂料层3。
(7)烘烤固化
将立式上胶机内温度控制在110-120℃,立式上胶机转速控制在100-200r/min,将浸渍相变储能涂料后的硅橡胶管在此环境中烘烤固化。
(8)配制阻燃隔热涂料
将加成型液体硅橡胶、AR级的硼酸锌、二氧化硅气凝胶粉、玻璃粉、电缆用陶瓷粉、AR级三氧化二铝、轻质氧化镁、云母粉按质量比100:4:3:12:12:2:2:3的比例投入混合,搅拌均匀后加入由AR级二甲苯和环己酮按质量比为1:1混合而成的稀释剂,调节粘度,稀释剂的加入量约为以上八种组分混合所得涂料总质量的一半,继续搅拌至均相,即得阻燃隔热涂料。
其中,上述二氧化硅气凝胶粉的粒径为5nm-15nm。
(9)浸涂阻燃隔热涂料
将硅橡胶管通过立式上胶机内的油槽,油槽内加入配置好的阻燃隔热涂料,反复浸渍、固化,得到阻燃隔热涂料层4。
(10)烘烤固化
将立式上胶机内温度控制在110-120℃,立式上胶机转速控制在100-200r/min,将浸渍阻燃隔热涂料后的硅橡胶管在此环境中烘烤固化。
(11)外编石英玻璃纤维
以3-6股石英玻璃纤维纱为原材料,编织得到石英玻璃纤维层5,石英玻璃纤维纱选用规格为133 Tex的B型石英玻璃纤维纱,硅橡胶管层1的内径为d。当d≤10nm,采用3股石英玻璃纤维纱编织;当10nm≤d<20nm,采用4股编织;当20nm≤d<30nm,采用5股编织;当30nm≤d<40nm,采用6股编织。本实施例中所得硅橡胶管层1的内径为20nm,采用5股编织。
(12)黏贴铝箔复合防热布
将铝箔复合防热布剪裁成带状,按1/2搭接缠绕在石英玻璃纤维层5上,得到铝箔复合防热布层6。
实施例2
和实施例1相比,区别在于:气凝胶低导热涂料由加成型液体硅橡胶、二氧化硅气凝胶粉按照质量比为65:3混合并搅拌均匀得到;相变储能涂料由加成型液体硅橡胶中、相变温度为180-190℃的有机固-固相变材料按照质量比为2:1混合并搅拌均匀得到;阻燃隔热涂料由加成型液体硅橡胶、硼酸锌、二氧化硅气凝胶粉、玻璃粉、陶瓷粉、氢氧化铝、轻质氧化镁、云母粉按照质量比为90:6:4:10:10:1:1:2混合并搅拌均匀得到。
实施例3
和实施例1相比,区别在于:气凝胶低导热涂料由加成型液体硅橡胶、二氧化硅气凝胶粉按照质量比为80:3混合并搅拌均匀得到;相变储能涂料由加成型液体硅橡胶中、相变温度为180-190℃的有机固-固相变材料按照质量比为6:5混合并搅拌均匀得到;阻燃隔热涂料由加成型液体硅橡胶、硼酸锌、二氧化硅气凝胶粉、玻璃粉、陶瓷粉、氢氧化铝、轻质氧化镁、云母粉按照质量比为110:5:4: 14:14:3:3:4混合并搅拌均匀得到。
对比例1
一种柔性复合防热套管,生产工艺步骤是:
A、编织石英玻璃纤维套管,并浸涂过渡涂料,再放入100-130℃烘箱中烘烤40-60分钟;
B、将一根硅橡胶管先进行表面处理,再用橡胶塞将硅橡胶管的两端密封,并用气泵向管内充入空气,然后将硅橡胶管穿入石英玻璃纤维套管内,两端绑扎固定,制作成坯管;
C、将坯管浸涂蓄热涂料,再经过立式上胶机烘烤固化,烘烤时间40-60分钟 ,烘烤温度100-120℃,循环多次至规定厚度;
D、将坯管浸涂隔热涂料,再经过立式上胶机烘烤固化,烘烤时间40-60分钟 ,烘烤温度100-120℃,循环多次至规定厚度;
E、将坯管浸涂防热涂料,再经过立式上胶机烘烤固化,烘烤时间40-60分钟 ,烘烤温度100-120℃,循环多次至规定厚度;
F、粘贴铝箔复合布。
以上工艺方法参照背景技术中提到的公开号为CN 105810335 A的中国专利得到;其中,蓄热涂料、隔热涂料和防热涂料均为市购的较为普遍的具有防火功能的涂料。
(一)测试实施例1-3和对比例1中防热套管的防热性能
分别使用实施例1-3和对比例1中的柔性复合防热套管包覆相同型号的电缆,然后将其置于同一热流环境下,热流环境见下表1所示,热流结束后,测试各防热套管内包裹的电缆芯线的表面温度,结果见下表2所示。
(二)测试实施例1-3和对比例1中柔性复合防热套管的抗烧灼性能
分别使用实施例1-3和对比例1中的柔性复合防热套管包覆相同型号的电缆,在氧气压力0.5mPa,乙炔压力0.08mPa的火焰下烧蚀30s,然后测试防热套管内壁的温度,结果见下表3所示。
由实施例1-3可知,将本发明中的柔性复合防热套管置于与航天飞行器飞行过程中较为接近的环境进行模拟测试,该防热套管表现出了极为优异的防热性能和耐烧灼性能。而对比例1无论是防热性能还是耐烧灼性能均明显劣于实施例。
Claims (9)
1.一种柔性复合防热套管,其特征在于,包括内层、外层和中间层,所述内层为硅橡胶管层(1),所述外层为铝箔复合防热布层(6),所述中间层从内至外依次为气凝胶低导热涂料层(2)、相变储能涂料层(3)、阻燃隔热涂料层(4)和石英玻璃纤维层(5)。
2.根据权利要求1所述的柔性复合防热套管,其特征在于,所述气凝胶低导热涂料层(2)的厚度为0.15-0.25mm,所述相变储能涂料层(3)的厚度为0.4-0.6mm,所述阻燃隔热涂料层(4)的厚度为0.8-1.2mm。
3.根据权利要求2所述的柔性复合防热套管,其特征在于,所述气凝胶低导热涂料层(2)的厚度为0.2mm,所述相变储能涂料层(3)的厚度为0.5mm,所述阻燃隔热涂料层(4)的厚度为1.0mm。
4.制备权利要求1-3任一项所述的柔性复合防热套管的方法,其特征在于,包括以下步骤:
A.涂覆气凝胶低导热涂料层(2):制备气凝胶低导热涂料并浸涂至硅橡胶管层(1)上,烘烤固化;
B.涂覆相变储能涂料层(3):制备相变储能涂料并浸涂至气凝胶低导热涂料层(2)上,烘烤固化;
C.涂覆阻燃隔热涂料层(4):制备阻燃隔热涂料并浸涂至相变储能涂料层(3)上,烘烤固化;
D.以3-6股石英玻璃纤维纱为原材料,编织得到石英玻璃纤维层(5);
E. 将铝箔复合防热布剪裁成带状,缠绕至石英玻璃纤维层(5)外部,得到铝箔复合防热布层(6)。
5.根据权利要求4所述的柔性复合防热套管的制备方法,其特征在于,所述气凝胶低导热涂料由加成型液体硅橡胶、二氧化硅气凝胶粉按照质量比为(65-80):3混合并搅拌均匀得到;所述相变储能涂料由加成型液体硅橡胶中、相变温度为180-190℃的有机固-固相变材料按照质量比为6:(3-5)混合并搅拌均匀得到;所述阻燃隔热涂料由加成型液体硅橡胶、硼酸锌、二氧化硅气凝胶粉、玻璃粉、陶瓷粉、氢氧化铝、轻质氧化镁、云母粉按照质量比为90-110:3-5:2-4:10-14:10-14:1-3:1-6:4-4混合并搅拌均匀得到。
6.根据权利要求5所述的柔性复合防热套管的制备方法,其特征在于,所述加成型液体硅橡胶、二氧化硅气凝胶粉的质量比为70:3。
7.根据权利要求5所述的柔性复合防热套管的制备方法,其特征在于,所述加成型液体硅橡胶、有机固-固相变材料的质量比为6:4。
8.根据权利要求5所述的柔性复合防热套管的制备方法,其特征在于,所述加成型液体硅橡胶、硼酸锌、二氧化硅气凝胶粉、玻璃粉、陶瓷粉、氢氧化铝、轻质氧化镁、云母粉的质量比为100:4:3:12:12:2:2:3。
9.权利要求1-3任一项所述的柔性复合防热套管在航天飞行器的热防护材料中的应用。
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