CN110626011B - 一种热防护板 - Google Patents
一种热防护板 Download PDFInfo
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Abstract
本发明属于热防护系统技术领域，公开一种热防护板。由外至内依次包括盖板、隔热层、内面板，自盖板向内面板方向贯穿设置有螺栓，螺栓的末端延伸出内面板内壁并用螺母固定；内面板内壁上在螺栓和螺母所处位置的外周设有气凝胶隔热罩；所述盖板为碳纤维增强陶瓷基复合材料盖板；所述隔热层为气凝胶毡层；所述内面板为树脂基复合材料内面板；所述螺栓为碳纤维增强陶瓷基复合材料螺栓，所述螺母为碳纤维增强陶瓷基复合材料螺母。本发明热防护板性能优异，能够满足飞行器表面温度在900℃以下的范围内使用。
Description
技术领域
本发明属热防护系统技术领域，具体涉及一种热防护板。
背景技术
热防护系统 ( Thermal Pro tection System，TPS)，是用来保护空间飞行器在气动加热环境中免遭烧毁和过热的结构，在新型动力系统和载入式飞行器、空间探测飞行器、临近空间飞行器、重复使用运载器等飞行器中具有不可低估的作用，其性能与可靠性是相关动力系统和飞行器先进性与可靠性的决定因素之一。到目前为止，有两种类型的热防护系统：烧蚀防热系统及可重复使用热防护系统。烧蚀防热，其机理是利用防热材料在高温下热解后的气化产物对边界的质量引射效应来散热；其最大的优点是安全可靠，适应外部加热变化的能力强，并可承受高热流；其缺点是一次性使用，并会发生烧蚀变形。而可重复使用热防护系统在起飞及载入过程中不发生相变及质量的丢失，同时还能起到承载作用，保护机体内的设备及燃料免受微流星体和空间碎片撞击，在雷雨等恶劣天气也能够安全地完成飞行任务。
随着高超声速飞行器飞行速度的不断提高，服役环境越来越恶劣，飞行器的热防护问题成为限制飞行器发展的瓶颈。早期的热防护系统主要是柔性热防护系统，简称为AFEI(Advanced Flexible External Insulation)，其材料主要应满足轻质、柔性、可折叠、耐高温。接着是刚性陶瓷防热瓦体系，由陶瓷瓦、Nomex柔性应变隔离垫 (SIP)和室温固化硅胶(RTV)组成。陶瓷防热瓦主要应用于机身机翼下表面温度为 600~1260℃的较高温区。目前比较受欢迎的是金属热防护系统，金属TPS能承受 982~1093℃高温，内部防热材料防止热气流进入蒙皮结构，构成TPS结构整体，这种热防护系统其外层结构为耐高温合金，具有一定的强度和刚度，除了能够有效地起到隔热作用外，还能够承受一定的外载冲击。
从热防护系统的材料的发展过程来看，材料由柔性向刚性转化，这表示可重复使用热防护系统正在从单一的防热作用向多用途过渡。金属热防护系统是目前最常用的热防护结构，但是，金属盖板除了过热能力差、热膨胀变形拱曲导致面层过早地从层流转变为紊流以及设计制造工艺复杂、难于进行检验与质量监控之外，还存在非催化涂层的附着稳定性问题，此外，金属的热膨胀系数大，当其遭受大的温度梯度时，有可能发生热应力疲劳破坏。因此，对高效热防护系统的研究一直是行业内迫切需要解决的难题。
发明内容
本发明的目的旨在提供一种热防护板。
为实现上述目的，本发明提供三种技术方案，具体如下：
方案①：一种热防护板，由外至内依次包括盖板、隔热层、内面板，自盖板向内面板方向贯穿设置有螺栓，螺栓的末端延伸出内面板内壁并用螺母固定；内面板内壁上在螺栓和螺母所处位置的外周设有气凝胶隔热罩；
所述盖板为碳纤维增强陶瓷基复合材料盖板；所述隔热层为气凝胶毡层；所述内面板为树脂基复合材料内面板；所述螺栓为碳纤维增强陶瓷基复合材料螺栓，所述螺母为碳纤维增强陶瓷基复合材料螺母。
进一步地，内面板和螺母之间设置有弹簧垫片。
较好地，所述碳纤维增强陶瓷基复合材料盖板为编织结构碳纤维增强陶瓷基复合材料盖板；所述碳纤维增强陶瓷基复合材料螺栓为编织结构碳纤维增强陶瓷基复合材料螺栓；所述碳纤维增强陶瓷基复合材料螺母为编织结构碳纤维增强陶瓷基复合材料螺母；所述树脂基复合材料内面板为纤维增强树脂基复合材料内面板；所述气凝胶毡层为聚氨酯气凝胶毡层、聚酰亚胺气凝胶毡层或二氧化硅气凝胶毡层；所述气凝胶隔热罩为聚氨酯气凝胶隔热罩、聚酰亚胺气凝胶隔热罩或二氧化硅气凝胶隔热罩。
更好地，所述纤维增强树脂基复合材料内面板为玻璃纤维增强环氧树脂基复合材料内面板、碳纤维增强环氧树脂基复合材料内面板、氧化铝纤维增强环氧树脂基复合材料内面板、氧化硅纤维增强环氧树脂基复合材料内面板、硼酸铝纤维增强环氧树脂基复合材料内面板、玻璃纤维增强聚酰亚胺树脂基复合材料内面板、碳纤维增强聚酰亚胺树脂基复合材料内面板、氧化铝纤维增强聚酰亚胺树脂基复合材料内面板、氧化硅纤维增强聚酰亚胺树脂基复合材料内面板、硼酸铝纤维增强聚酰亚胺树脂基复合材料内面板、玻璃纤维增强酚醛树脂基复合材料内面板、碳纤维增强酚醛树脂基复合材料内面板、氧化铝纤维增强酚醛树脂基复合材料内面板、氧化硅纤维增强酚醛树脂基复合材料内面板或硼酸铝纤维增强酚醛树脂基复合材料内面板。
方案②：在方案①的基础上，进一步增加下述结构：内面板与螺母之间的螺栓上套设有第一气凝胶隔热垫；位于内面板内部的螺栓上套设有气凝胶隔热环。
较好地，所述第一气凝胶隔热垫为聚氨酯气凝胶隔热垫、聚酰亚胺气凝胶隔热垫或二氧化硅气凝胶隔热垫；所述气凝胶隔热环为聚氨酯气凝胶隔热环、聚酰亚胺气凝胶隔热环或二氧化硅气凝胶隔热环。
方案③：在方案②的基础上，进一步增加下述结构：位于隔热层内部的螺栓自其靠近内面板的一端向另一端依次套设有第二气凝胶隔热垫、陶瓷环。
较好地，所述第二气凝胶隔热垫为聚氨酯气凝胶隔热垫、聚酰亚胺气凝胶隔热垫或二氧化硅气凝胶隔热垫；所述陶瓷环为氧化锆环、碳化锆环、二硼化锆环、碳化铪环或二硼化铪环。
方案②和③中，进一步优选第一气凝胶隔热垫和螺母之间设置有弹簧垫片。
方案①、②和③中，进一步优选气凝胶隔热罩与内面板之间采用耐热温度不低于1000 ℃的高温胶粘接。所述高温胶更优选无机高温胶。
方案①、②和③中，进一步优选盖板的外表面设置有SiC涂层。
本发明中涉及的材料，比如（编织结构）碳纤维增强陶瓷基复合材料、高温胶、聚氨酯气凝胶、聚酰亚胺气凝胶、二氧化硅气凝胶、玻璃纤维增强环氧树脂基复合材料、碳纤维增强环氧树脂基复合材料、氧化铝纤维增强环氧树脂基复合材料、氧化硅纤维增强环氧树脂基复合材料、硼酸铝纤维增强环氧树脂基复合材料、玻璃纤维增强聚酰亚胺树脂基复合材料、碳纤维增强聚酰亚胺树脂基复合材料、氧化铝纤维增强聚酰亚胺树脂基复合材料、氧化硅纤维增强聚酰亚胺树脂基复合材料、硼酸铝纤维增强聚酰亚胺树脂基复合材料、玻璃纤维增强酚醛树脂基复合材料、碳纤维增强酚醛树脂基复合材料、氧化铝纤维增强酚醛树脂基复合材料、氧化硅纤维增强酚醛树脂基复合材料、硼酸铝纤维增强酚醛树脂基复合材料、氧化锆、碳化锆、二硼化锆、碳化铪、二硼化铪，均为已知产品，均可通过市购获得或者按现有制备方法制备获得。
本发明热防护板在具体使用时，需要多个热防护板拼接成与飞行器形状相适配的形状，拼接缝之间可以使用Cf/SiC螺栓和Cf/SiC螺母进行连接固定。
有益效果：本发明采用Cf/SiC板作为盖板，其具有高的抗氧化和层间剪切强度；采用气凝胶毡作为隔热层，利用气凝胶独有的特性使其具有优异的隔热性能，有效地保证舱段内所需的控温温度；内面板采用树脂基复合材料，其界面性能良好，且能够长期在安全温度范围内使用；本发明在螺栓与内面板之间设置气凝胶隔热环，在螺母与内面板之间设置第一气凝胶隔热垫，防止内面板过热，同时采用气凝胶隔热罩对螺栓和螺母整体包裹，进一步防止热量通过螺栓传递到舱内；本发明在盖板和内面板之间设置陶瓷环，能够避免因隔热层柔韧性变形时对盖板和内面板之间平行度的影响，同时为了避免陶瓷环对内面板的热破坏，在陶瓷环与内面板之间增加第二气凝胶隔热垫，保证良好隔热性能的同时保证其结构完整性；本发明得到的热防护板性能优异，能够满足飞行器表面温度在900℃以下的范围内使用，保证内部的温度在要求的范围内；本发明对飞行器用热防护系统的研究具有重要的推动作用。
附图说明
图1：本发明实施方式一的结构示意图；
图2：本发明实施方式二的结构示意图；
图3：本发明实施方式三的结构示意图；
1-盖板，2-隔热层，3-内面板，4-螺栓，5-螺母，6-弹簧垫片，7-气凝胶隔热罩，81-第一气凝胶隔热垫，82-第二气凝胶隔热垫，9-气凝胶隔热环，10-陶瓷环。
具体实施方式
下面结合具体实施例对本发明的技术方案做进一步详细、清楚地描述，但本发明的保护范围并不局限于此。
实施例1
如图1所示，一种热防护板，由外至内依次包括盖板1、隔热层2、内面板3，所述盖板1的外表面设置有SiC涂层（未示出），自盖板1向内面板3方向贯穿设置有螺栓4，螺栓4的末端延伸出内面板3内壁并用螺母5固定，内面板3和螺母5之间设置有弹簧垫片6；内面板3内壁上在螺栓4和螺母5所处位置的外周设有气凝胶隔热罩7，气凝胶隔热罩7与内面板3之间采用耐热温度不低于1000 ℃的无机高温胶粘接；
其中，所述盖板1为编织结构碳纤维增强陶瓷基复合材料盖板；所述隔热层2为二氧化硅气凝胶毡层；所述内面板3为玻璃纤维增强环氧树脂基复合材料内面板；所述螺栓4为编织结构碳纤维增强陶瓷基复合材料螺栓，所述螺母5为编织结构碳纤维增强陶瓷基复合材料螺母；所述气凝胶隔热罩7为二氧化硅气凝胶隔热罩。
实施例2
如图2所示，一种热防护板，由外至内依次包括盖板1、隔热层2、内面板3，所述盖板1的外表面设置有SiC涂层（未示出），自盖板1向内面板3方向贯穿设置有螺栓4，螺栓4的末端延伸出内面板3内壁并用螺母5固定，内面板3内壁上在螺栓4和螺母5所处位置的外周设有气凝胶隔热罩7，气凝胶隔热罩7与内面板3之间采用耐热温度不低于1000 ℃的无机高温胶粘接；内面板3与螺母5之间的螺栓4上套设有第一气凝胶隔热垫81，第一气凝胶隔热垫81和螺母5之间设置有弹簧垫片6；位于内面板3内部的螺栓4外部自其远离隔热层2的一端向另一端套设有一段气凝胶隔热环9；
其中，所述盖板1为编织结构碳纤维增强陶瓷基复合材料盖板；所述隔热层2为二氧化硅气凝胶毡层；所述内面板3为玻璃纤维增强环氧树脂基复合材料内面板；所述螺栓4为编织结构碳纤维增强陶瓷基复合材料螺栓，所述螺母5为编织结构碳纤维增强陶瓷基复合材料螺母；所述气凝胶隔热罩7为二氧化硅气凝胶隔热罩；所述第一气凝胶隔热垫81为二氧化硅气凝胶隔热垫；所述气凝胶隔热环9为二氧化硅气凝胶隔热环。
实施例3
如图3所示，一种热防护板，由外至内依次包括盖板1、隔热层2、内面板3，所述盖板1的外表面设置有SiC涂层（未示出），自盖板1向内面板3方向贯穿设置有螺栓4，螺栓4的末端延伸出内面板3内壁并用螺母5固定，内面板3内壁上在螺栓4和螺母5所处位置的外周设有气凝胶隔热罩7，气凝胶隔热罩7与内面板3之间采用耐热温度不低于1000 ℃的无机高温胶粘接；内面板3与螺母5之间的螺栓4上套设有第一气凝胶隔热垫81，第一气凝胶隔热垫81和螺母5之间设置有弹簧垫片6；位于内面板3内部的螺栓4上套设有气凝胶隔热环9；位于隔热层2内部的螺栓4自其靠近内面板3的一端向另一端依次套设有第二气凝胶隔热垫82、氧化锆环10；
其中，所述盖板1为编织结构碳纤维增强陶瓷基复合材料盖板；所述隔热层2为二氧化硅气凝胶毡层；所述内面板3为玻璃纤维增强环氧树脂基复合材料内面板；所述螺栓4为编织结构碳纤维增强陶瓷基复合材料螺栓，所述螺母5为编织结构碳纤维增强陶瓷基复合材料螺母；所述气凝胶隔热罩7为二氧化硅气凝胶隔热罩；所述第一气凝胶隔热垫81和第二气凝胶隔热垫82均为二氧化硅气凝胶隔热垫；所述气凝胶隔热环9为二氧化硅气凝胶隔热环；所述陶瓷环10为氧化锆环。
Claims (8)
1.一种热防护板，其特征在于：由外至内依次包括盖板、隔热层、内面板，自盖板向内面板方向贯穿设置有螺栓，螺栓的末端延伸出内面板内壁并用螺母固定；内面板内壁上在螺栓和螺母所处位置的外周设有气凝胶隔热罩；
所述盖板为碳纤维增强陶瓷基复合材料盖板；所述隔热层为气凝胶毡层；所述内面板为树脂基复合材料内面板；所述螺栓为碳纤维增强陶瓷基复合材料螺栓，所述螺母为碳纤维增强陶瓷基复合材料螺母；
内面板与螺母之间的螺栓上套设有第一气凝胶隔热垫；位于内面板内部的螺栓上套设有气凝胶隔热环；
位于隔热层内部的螺栓自其靠近内面板的一端向另一端依次套设有第二气凝胶隔热垫、陶瓷环。
2.如权利要求1所述的热防护板，其特征在于：内面板和螺母之间设置有弹簧垫片。
3.如权利要求1所述的热防护板，其特征在于：所述碳纤维增强陶瓷基复合材料盖板为编织结构碳纤维增强陶瓷基复合材料盖板；所述碳纤维增强陶瓷基复合材料螺栓为编织结构碳纤维增强陶瓷基复合材料螺栓；所述碳纤维增强陶瓷基复合材料螺母为编织结构碳纤维增强陶瓷基复合材料螺母；所述树脂基复合材料内面板为纤维增强树脂基复合材料内面板；所述气凝胶毡层为聚氨酯气凝胶毡层、聚酰亚胺气凝胶毡层或二氧化硅气凝胶毡层；所述气凝胶隔热罩为聚氨酯气凝胶隔热罩、聚酰亚胺气凝胶隔热罩或二氧化硅气凝胶隔热罩。
4.如权利要求1所述的热防护板，其特征在于：所述第一气凝胶隔热垫为聚氨酯气凝胶隔热垫、聚酰亚胺气凝胶隔热垫或二氧化硅气凝胶隔热垫；所述气凝胶隔热环为聚氨酯气凝胶隔热环、聚酰亚胺气凝胶隔热环或二氧化硅气凝胶隔热环。
5.如权利要求1所述的热防护板，其特征在于：所述第二气凝胶隔热垫为聚氨酯气凝胶隔热垫、聚酰亚胺气凝胶隔热垫或二氧化硅气凝胶隔热垫；所述陶瓷环为氧化锆环、碳化锆环、二硼化锆环、碳化铪环或二硼化铪环。
6.如权利要求1~5任一所述的热防护板，其特征在于：第一气凝胶隔热垫和螺母之间设置有弹簧垫片。
7.如权利要求1~5任一所述的热防护板，其特征在于：气凝胶隔热罩与内面板之间采用耐热温度不低于1000 ℃的高温胶粘接。
8.如权利要求1~5任一所述的热防护板，其特征在于：所述盖板的外表面设置有SiC涂层。
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