CN111070830A - 一种飞行器用阻燃绝热材料 - Google Patents
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Abstract
本发明涉及一种飞行器用阻燃绝热材料，包括由外向内依次设置的聚醚醚酮层、金属层、阻燃硅气凝胶层和酚醛泡沫防火保温层；阻燃硅气凝胶层和酚醛泡沫防火保温层均呈板状结构；阻燃硅气凝胶层包括第一蜂窝材料和填充于蜂窝材料中的阻燃硅气凝胶，酚醛泡沫防火保温层包括第二蜂窝材料和填充于蜂窝材料中的酚醛泡沫材料，沿飞行器用阻燃绝热材料的厚度方向，第一蜂窝材料和第二蜂窝材料均包含若干层子蜂窝结构且子蜂窝结构的蜂窝密度依次减小或增大。
Description
技术领域
本发明涉及阻燃材料，尤其涉及一种飞行器用阻燃绝热材料。
背景技术
在航天航空领域的飞行器中，均使用阻燃绝热材料。这些材料均要求具有低密度且更小的体积，以达到与传统隔热材料等效的隔热效果，这一特点在飞行器热防护系统中具有举足轻重的优势。但是目前的阻燃绝热材料中，内层和外层的导热性差异不大，在高温环境下，势必影响材料的阻燃性，因此开发具有单向导热性的飞行器阻燃绝热材料十分必要。
发明内容
为解决上述技术问题，本发明的目的是提供一种飞行器用阻燃绝热材料，该材料重量轻、阻燃绝热性好，且具有单向的导热性能。
本发明的一种飞行器用阻燃绝热材料，包括由外向内依次设置的聚醚醚酮层、金属层、阻燃硅气凝胶层和酚醛泡沫防火保温层；阻燃硅气凝胶层和酚醛泡沫防火保温层均呈板状结构；阻燃硅气凝胶层包括第一蜂窝材料和填充于蜂窝材料中的阻燃硅气凝胶，酚醛泡沫防火保温层包括第二蜂窝材料和填充于蜂窝材料中的酚醛泡沫材料，沿飞行器用阻燃绝热材料的厚度方向，第一蜂窝材料和第二蜂窝材料均包含若干层子蜂窝结构且子蜂窝结构的蜂窝密度依次减小或增大。
由于沿飞行器用阻燃绝热材料的厚度方向，子蜂窝结构的蜂窝密度依次减小或增大，提高了阻燃硅气凝胶层和酚醛泡沫防火保温层的单向导热性能。
阻燃硅气凝胶具有很好的热稳定性、耐热冲击性以及隔热性，并且质量轻，节约所占空间。酚醛泡沫材料主要由酚醛树脂和阻燃剂、抑烟剂、固化剂、发泡剂等组成，为闭孔型硬质泡沫塑料，具有防火及保温性。
进一步地，聚醚醚酮层远离金属层的一侧连接有惰性气体层，惰性气体层中放置有若干密闭的袋体，袋体内充满惰性气体。惰性气体层的设置，不仅提高了飞行器用阻燃绝热材料的缓冲性能，同时袋体内填充的惰性气体能够在材料着火时被释放出，一定程度起到隔绝空气的作用。
进一步地，袋体的材质为聚氯乙烯。聚氯乙烯具有良好的阻燃性及可加工性。
进一步地，惰性气体为氮气。氮气安全性高，且成本低。
进一步地，袋体外部涂覆有聚四氟乙烯层。聚四氟乙烯层的设置，进一步提高了袋体的阻燃性。
进一步地，沿靠近至远离聚醚醚酮层的厚度方向，第一蜂窝材料中子蜂窝结构的蜂窝密度依次减小，第二蜂窝材料中子蜂窝结构的蜂窝密度依次减小。由于聚醚醚酮层一侧与外界空气接触，靠近聚醚醚酮层的一侧的子蜂窝结构的蜂窝密度大，因此，当阻燃绝热材料受热时，热量会缓慢进入子蜂窝结构的内部，因此，可发挥阻燃硅气凝胶层和酚醛泡沫防火保温层的绝热性能。优选地，第一蜂窝材料中子蜂窝结构的蜂窝密度大于第二蜂窝材料中子蜂窝结构的蜂窝密度。
进一步地，第一蜂窝材料和第二蜂窝材料均为铝蜂窝材料。
进一步地，金属层为铝或镍。
进一步地，金属层和阻燃硅气凝胶层之间还设有阻燃纤维层。
进一步地，阻燃纤维层为陶瓷纤维或聚酰胺纤维。
借由上述方案，本发明至少具有以下优点：
本发明的飞行器用阻燃绝热材料中包括多层具有阻燃性能的功能层，且通过设置阻燃硅气凝胶层和酚醛泡沫防火保温层提高了阻燃效果，减轻了材料的重量，并且由于第一蜂窝材料和第二蜂窝材料均包含若干层子蜂窝结构且子蜂窝结构的蜂窝密度依次减小或增大，赋予材料单向导热性。
上述说明仅是本发明技术方案的概述，为了能够更清楚了解本发明的技术手段，并可依照说明书的内容予以实施，以下以本发明的较佳实施例并配合详细附图说明如后。
附图说明
图1是本发明实施例1中飞行器用阻燃绝热材料的剖视结构示意图；
图2是阻燃硅气凝胶层的俯视结构示意图；
图3是酚醛泡沫防火保温层的俯视结构示意图；
图4是本发明实施例2中飞行器用阻燃绝热材料的剖视结构示意图
图5是本发明实施例3中飞行器用阻燃绝热材料的剖视结构示意图
附图标记说明：
1-聚醚醚酮层；2-金属层；3-阻燃硅气凝胶层；4-酚醛泡沫防火保温层；5-惰性气体层；6-阻燃纤维层；10-子蜂窝结构；30-阻燃硅气凝胶；31-第一蜂窝材料；40-酚醛泡沫材料；41-第二蜂窝材料。
具体实施方式
下面结合实施例，对本发明的具体实施方式作进一步详细描述。以下实施例用于说明本发明，但不用来限制本发明的范围。
实施例1
参见图1，本发明的一种飞行器用阻燃绝热材料，由外向内依次设置有聚醚醚酮层1、金属层2、阻燃硅气凝胶层3和酚醛泡沫防火保温层4；阻燃硅气凝胶层3和酚醛泡沫防火保温层4均呈板状结构。金属层2为铝或镍。
其中，阻燃硅气凝胶层3包括第一蜂窝材料31和填充于蜂窝材料中的阻燃硅气凝胶30(图2)。酚醛泡沫防火保温层4包括第二蜂窝材料41和填充于蜂窝材料中的酚醛泡沫材料40(图3)。第一蜂窝材料31和第二蜂窝材料41均为铝蜂窝材料。沿飞行器用阻燃绝热材料的厚度方向，第一蜂窝材料31和第二蜂窝材料41均包含若干层子蜂窝结构10。沿靠近至远离聚醚醚酮层1的厚度方向，第一蜂窝材料31中子蜂窝结构10的蜂窝密度依次减小，第二蜂窝材料41中子蜂窝结构10的蜂窝密度依次减小，且第一蜂窝材料31中子蜂窝结构10的蜂窝密度大于第二蜂窝材料41中子蜂窝结构10的蜂窝密度。
实施例2
参见图4，本发明的一种飞行器用阻燃绝热材料，由外向内依次设置有聚醚醚酮层1、金属层2、阻燃硅气凝胶层3和酚醛泡沫防火保温层4；阻燃硅气凝胶层3和酚醛泡沫防火保温层4均呈板状结构。金属层2为铝或镍。
其中，阻燃硅气凝胶层3包括第一蜂窝材料31和填充于蜂窝材料中的阻燃硅气凝胶30(图2)。酚醛泡沫防火保温层4包括第二蜂窝材料41和填充于蜂窝材料中的酚醛泡沫材料40(图3)。第一蜂窝材料31和第二蜂窝材料41均为铝蜂窝材料。沿飞行器用阻燃绝热材料的厚度方向，第一蜂窝材料31和第二蜂窝材料41均包含若干层子蜂窝结构10。沿靠近至远离聚醚醚酮层1的厚度方向，第一蜂窝材料31中子蜂窝结构10的蜂窝密度依次减小，第二蜂窝材料41中子蜂窝结构10的蜂窝密度依次减小，且第一蜂窝材料31中子蜂窝结构10的蜂窝密度大于第二蜂窝材料41中子蜂窝结构10的蜂窝密度。
聚醚醚酮层1远离金属层2的一侧表面还连接有惰性气体层5，惰性气体层5中放置有若干密闭的袋体，袋体内充满惰性气体。优选地，袋体的材质为聚氯乙烯，袋体外部涂覆有聚四氟乙烯层，惰性气体为氮气。
实施例3
参见图5，本发明的一种飞行器用阻燃绝热材料，由外向内依次设置有聚醚醚酮层1、金属层2、阻燃纤维层6、阻燃硅气凝胶层3和酚醛泡沫防火保温层4；阻燃硅气凝胶层3和酚醛泡沫防火保温层4均呈板状结构。金属层2为铝或镍。阻燃纤维层6为陶瓷纤维或聚酰胺纤维。
其中，阻燃硅气凝胶层3包括第一蜂窝材料31和填充于蜂窝材料中的阻燃硅气凝胶30(图2)。酚醛泡沫防火保温层4包括第二蜂窝材料41和填充于蜂窝材料中的酚醛泡沫材料40(图3)。第一蜂窝材料31和第二蜂窝材料41均为铝蜂窝材料。沿飞行器用阻燃绝热材料的厚度方向，第一蜂窝材料31和第二蜂窝材料41均包含若干层子蜂窝结构10。沿靠近至远离聚醚醚酮层1的厚度方向，第一蜂窝材料31中子蜂窝结构10的蜂窝密度依次减小，第二蜂窝材料41中子蜂窝结构10的蜂窝密度依次减小，且第一蜂窝材料31中子蜂窝结构10的蜂窝密度大于第二蜂窝材料41中子蜂窝结构10的蜂窝密度。
聚醚醚酮层1远离金属层2的一侧表面还连接有惰性气体层5，惰性气体层5中放置有若干密闭的袋体，袋体内充满惰性气体。优选地，袋体的材质为聚氯乙烯，袋体外部涂覆有聚四氟乙烯层，惰性气体为氮气。
以上仅是本发明的优选实施方式，并不用于限制本发明，应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明技术原理的前提下，还可以做出若干改进和变型，这些改进和变型也应视为本发明的保护范围。
Claims (10)
1.一种飞行器用阻燃绝热材料，其特征在于：包括由外向内依次设置的聚醚醚酮层、金属层、阻燃硅气凝胶层和酚醛泡沫防火保温层；所述阻燃硅气凝胶层和酚醛泡沫防火保温层均呈板状结构；所述阻燃硅气凝胶层包括第一蜂窝材料和填充于所述蜂窝材料中的阻燃硅气凝胶，所述酚醛泡沫防火保温层包括第二蜂窝材料和填充于所述蜂窝材料中的酚醛泡沫材料，沿所述飞行器用阻燃绝热材料的厚度方向，所述第一蜂窝材料和第二蜂窝材料均包含若干层子蜂窝结构且所述子蜂窝结构的蜂窝密度依次减小或增大。
2.根据权利要求1所述的飞行器用阻燃绝热材料，其特征在于：所述聚醚醚酮层远离所述金属层的一侧连接有惰性气体层，所述惰性气体层中放置有若干密闭的袋体，所述袋体内充满惰性气体。
3.根据权利要求2所述的飞行器用阻燃绝热材料，其特征在于：所述袋体的材质为聚氯乙烯。
4.根据权利要求2所述的飞行器用阻燃绝热材料，其特征在于：所述惰性气体为氮气。
5.根据权利要求2所述的飞行器用阻燃绝热材料，其特征在于：所述袋体外部涂覆有聚四氟乙烯层。
6.根据权利要求1所述的飞行器用阻燃绝热材料，其特征在于：沿靠近至远离所述聚醚醚酮层的厚度方向，所述第一蜂窝材料中子蜂窝结构的蜂窝密度依次减小，所述第二蜂窝材料中子蜂窝结构的蜂窝密度依次减小。
7.根据权利要求1所述的飞行器用阻燃绝热材料，其特征在于：所述第一蜂窝材料和第二蜂窝材料均为铝蜂窝材料。
8.根据权利要求1所述的飞行器用阻燃绝热材料，其特征在于：所述金属层为铝或镍。
9.根据权利要求1所述的飞行器用阻燃绝热材料，其特征在于：所述金属层和阻燃硅气凝胶层之间还设有阻燃纤维层。
10.根据权利要求9所述的飞行器用阻燃绝热材料，其特征在于：所述阻燃纤维层为陶瓷纤维或聚酰胺纤维。
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