CN110524974A - 一种适用于负曲率外形的防隔热一体化热防护结构 - Google Patents
一种适用于负曲率外形的防隔热一体化热防护结构 Download PDFInfo
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Abstract
本发明公开了一种适用于负曲率外形的防隔热一体化热防护结构,属于高超声速临近空间飞行器热防护技术领域。包括:承力壳体;热防护层,热防护层包括隔热层和防热层,防热层内壁设置有网格状的防热层加强筋,所述隔热层设置在防热层加强筋的网格内,隔热层表面设有隔热层包覆蒙皮;防热层、隔热层包覆蒙皮、防热层加强筋在预浸料状态即与隔热层通过缝合线缝合成一体,再整体高温固化为防隔热一体化结构;粘接层位于承力壳体和热防护层之间,粘接层为具有耐高温和热匹配性能的粘接剂。本发明采用防隔热一体化热防护层并用耐高温粘接剂粘接在承力壳体上,可避免飞行器热防护结构负曲率部位出现界面分离。
Description
技术领域
本发明涉及高超声速临近空间飞行器热防护技术领域,具体是涉及一种适用于负曲率外形的防隔热一体化热防护结构。
背景技术
高超声速临近空间飞行器(一般指飞行速度超过5马赫,全程在大气层内飞行的飞行器)由于具有飞行速度高、突防能力强等特点,有着巨大的军事价值和潜在的经济价值,目前已成为国内外武器与航天器发展的主要方向。飞行器在大气层内以高超声速飞行时,气动加热非常严重,飞行器外表面的热防护问题一直是高超声速临近空间飞行器设计需要重点解决的问题。
常见高超声速飞行器外表面的热防护结构一般为热防护层与承力层复合而成的多层结构,热防护层可为单层防热层或防热层与隔热层组合的复合结构。热防护层一般有两种方式与承力层复合:最常用的一种是将预浸布通过缠绕或铺层等方式预固定在承力层上,再随承力层一起固化成型。另一种是通过模具将热防护层直接固化成型,再套装到承力壳体外表面,热防护层与承力层之间再通过粘接层进行连接。这两种结构都存在飞行过程中的高温条件下,防热层、隔热层、承力壳体之间的界面容易出现粘接失效而分离的问题;但对于正曲率外形,出现局部界面脱粘后,依靠外形闭合的防热层的约束力,各层界面之间仍然可以贴合,对热防护整体结构影响不大,问题不突出。
为获得较高的升阻比,高超声速临近空间飞行器对气动外形有较高的要求,一般设计为异形曲面的升力体外形,有的需要设计成带有负曲率的气动外形,但负曲率气动外形给高超声速飞行器的防热、隔热设计带来新的挑战:
(1)在飞行过程中的高温条件下,防热层、隔热层、承力壳体之间的粘接失效而分离后,对于存在负曲率外形的热防护结构,外形闭合的防热层在负曲率部位的没有约束力,因此,负曲率部位各层之间界面最先出现分离;同时,由于承力壳体的热膨胀比一般比防热层的热膨胀大,使得防热层在圆周方向的拉应力增加,进一步加剧了负曲率部位各层之间界面的分离。负曲率部位出现界面分离后,在高速气动载荷作用下,出现界面分离的部位的防热层应力会迅速增大,极易出现破坏,从而导致整个防热层破坏、飞行器结构破坏。
(2)防热层成型过程中,纤维布或预浸料需要铺覆在承力壳体或工装上,对于存在负曲率外形的热防护结构,由于纤维布或预浸料在平面内的变形能力较差,铺覆过程中,负曲率部位容易出现褶皱,成型的防热层会出现局部***或局部孔洞等缺陷,进而影响防热层热防护性能。
(3)对于采用预浸布缠绕或铺层预固定在承力层上,再随承力层一起固化成型的方式成型防热层,除了上述问题外,还存在负曲率部位由于缠绕、铺层张紧力难以控制,使得负曲率部位防热层材料性能难以保证;同时,由于承力壳体的热膨胀比防热层的大,固化后承力壳体收缩较多,负曲率部位的防热层和承力壳体之间的会最先出现界面分离。
因此,需要研究适用于负曲率外形飞行器使用,同时兼具优良抗烧蚀性能、防隔热性能以及热匹配性能的热防护结构。
发明内容
本发明的目的是为了克服上述背景技术中位于负曲率部位各层之间界面容易出现分离的不足,提供一种适用于负曲率外形的防隔热一体化热防护结构。
本发明提供一种适用于负曲率外形的防隔热一体化热防护结构,包括:
承力壳体;
热防护层,所述热防护层包括隔热层和防热层,所述防热层内壁设置有网格状的防热层加强筋,所述隔热层设置在防热层加强筋的网格内,隔热层表面设有隔热层包覆蒙皮;所述隔热层包覆蒙皮、防热层加强筋、防热层在预浸料状态下即与隔热层通过缝合线缝合成一体;
粘接层,所述粘接层位于承力壳体和热防护层之间,所述粘接层将热防护层粘接在承力壳体上。
优选方案:所述防热层、隔热层包覆蒙皮及防热层加强筋均是由多层预浸料层叠并高温固化而成,所述预浸料是由一定厚度的立体石英织物浸渍酚醛树脂制成。
优选方案:所述隔热层为气凝胶复合材料。
优选方案:所述粘接层为具有耐高温和热匹配性能的粘接剂,所述粘接层内设有多个通孔。
优选方案:所述通孔的轴线与所述粘接层的厚度方向垂直。
优选方案:所述缝合线为石英纤维材料。
在上述技术方案的基础上,与现有技术相比,本发明的优点如下:
本发明的一种适用于负曲率外形的防隔热一体化热防护结构,该一体化热防护结构可有效解决具有负曲率外形的高超声速临近空间飞行器负曲率部位防热层、隔热层、承力壳体之间的界面容易出现分离的问题,提高飞行器在高速气动载荷作用下,负曲率部位抵抗破坏的能力,从而保证飞行器热防护结构可靠工作。
1)本发明的粘接层是一种的具有良好高温粘接性能、良好热匹配性能的带通孔粘接层结构,从而保证负曲率部位不出现界面分离现象,避免了在高速气动载荷作用下,负曲率部位容易破坏的风险。粘接层的良好高温粘接性能使得飞行器在飞行过程中的高温条件下,热防护层与承力壳体之间的粘接牢固;粘接层的良好热匹配性能解决飞行器能适应高温条件下,承力壳体膨胀量比热防护层大而导致的承力壳体与热防护层变形协调问题;带通孔的粘接层结构既可以降低粘接层的压缩模量,进而提高承力壳体与热防护层变形协调能力,还为高温条件下热防护层碳化产生的气体提供了排气通道,降低热防护层与承力壳体之间由于气体内压而剥离的风险。
2)本发明的防热层、隔热层包覆蒙皮及防热层加强筋采用的立体织物,具有一定的变形能力,在铺覆过程中,在负曲率部位避免出现褶皱,进而减少局部***或局部孔洞等缺陷,提高热防护层的性能。
3)本发明的热防护层设有隔热层和防热层,防热层内壁设置有网格状的防热层加强筋,隔热层设置在防热层加强筋的网格内,隔热层表面设有隔热层包覆蒙皮;防热层、隔热层包覆蒙皮、防热层加强筋在预浸料状态即与隔热层通过缝合线缝合成一体,再整体高温固化为防隔热一体化结构。本热防护层可避免飞行器热防护结构负曲率部位出现界面分离,有效提高飞行器在高速气动载荷作用下,负曲率部位抵抗破坏的能力,从而保证飞行器结构可靠工作。
附图说明
图1是本发明实施例的热防护结构纵向剖面的结构示意图;
图2是本发明实施例的热防护结构横截面示意图。
附图标记:1-热防护层,2-粘接层,3-承力壳体,11-防热层,12-隔热层,13-隔热层包覆蒙皮,14-防热层加强筋,15-缝合线。
具体实施方式
下面结合附图及具体实施例对本发明作进一步的详细描述。
实施例1
参见图1和图2所示,本发明实施例提供一种适用于负曲率外形的防隔热一体化热防护结构,该一体化热防护结构由承力壳体3、热防护层1和粘接层2组成。
其中,承力壳体3为轻质高强的金属材料,承力壳体3主要起承载作用。
热防护层1包括隔热层12和防热层11,防热层11内壁设置有网格状的防热层加强筋14,隔热层12设置在防热层加强筋14的网格内,在隔热层12表面设有隔热层包覆蒙皮13。
该防热层加强筋14呈网格状排布,防热层加强筋14为隔热层12的排布提供空间,由于本实施例的隔热层12采用的是具有低导热系数、低密度的隔热材料,因此将隔热层12设置在防热层加强筋14的网格内,防止隔热层12受外力变形失效。
隔热层包覆蒙皮13、防热层加强筋14、及防热层11在预浸料状态即与隔热层12通过缝合线15缝合成一体,再整体高温固化为防隔热一体化结构。
粘接层2,粘接层2位于承力壳体3和热防护层1之间,粘接层2将热防护层1粘接在承力壳体3上。粘接层2为具有良好热匹配性能、高温粘接性能、涂覆工艺性能的粘接剂固化而成,该粘接层2内开设有多个通孔,且通孔的轴线与粘接层2的厚度方向垂直。粘接层2的典型性能要求见表1:
表1粘接层性能要求
序号 | 参数 | 状态 | 要求值 |
1 | 压缩模量(20%压缩率) | 常温~220℃ | 1~10MPa |
2 | 剪切强度 | 常温~220℃ | ≥0.2MPa |
3 | 拉断伸长率 | 常温 | ≥100% |
4 | 拉伸强度 | 常温 | ≥1.5MPa |
5 | 粘度 | 涂覆时 | ≤1×10<sup>5</sup>Pa.s |
工作原理
本发明的一种适用于负曲率外形的防隔热一体化热防护结构,该一体化热防护结构由承力壳体3、热防护层1和粘接层2组成。该一体化热防护结构可有效解决具有负曲率外形的高超声速临近空间飞行器负曲率部位防热层、隔热层、承力壳体之间的界面容易出现分离的问题,提高飞行器在高速气动载荷作用下,负曲率部位抵抗破坏的能力,从而保证飞行器热防护结构可靠工作。
本发明的粘接层2是一种的具有良好高温粘接性能、良好热匹配性能的带通孔粘接层结构,从而保证负曲率部位不出现界面分离现象,避免了在高速气动载荷作用下,负曲率部位容易破坏的风险。粘接层2的良好高温粘接性能使得飞行器在飞行过程中的高温条件下,热防护层1与承力壳体3之间的粘接牢固。
粘接层2的良好热匹配性能解决飞行器能适应高温条件下,承力壳体3膨胀量比热防护层1大而导致的承力壳体3与热防护层1变形协调问题。带通孔的粘接层2的结构既可以降低粘接层2的压缩模量,进而提高承力壳体3与热防护层1变形协调能力,还为高温条件下热防护层1碳化产生的气体提供了排气通道,降低热防护层1与承力壳体3之间由于气体内压而剥离的风险。
本发明的热防护层1设有隔热层12和防热层11,防热层11内壁设置有网格状的防热层加强筋14,隔热层12设置在防热层加强筋14的网格内,隔热层12表面设有隔热层包覆蒙皮13;防热层11、隔热层包覆蒙皮13、防热层加强筋14在预浸料状态即与隔热层12通过缝合线15缝合成一体,再整体高温固化为防隔热一体化结构。本热防护层1可避免飞行器热防护结构负曲率部位出现界面分离,有效提高飞行器在高速气动载荷作用下,负曲率部位抵抗破坏的能力,从而保证飞行器结构可靠工作。
实施例2
参见图1和图2所示,本发明实施例提供一种适用于负曲率外形的防隔热一体化热防护结构,本实施例与实施例1的区别在于:本热防护层1的防热层11、隔热层包覆蒙皮13及防热层加强筋14均是由多层预浸料层叠并高温固化而成,预浸料是由一定厚度的立体石英织物浸渍酚醛树脂制成。立体石英织物的具体厚度和酚醛树脂的具体种类本领域的技术人员根据实际需要具体设定。
热防护层1的防热层11、隔热层包覆蒙皮13及防热层加强筋14可根据需要采用不同厚度的立体织物、不同种类的树脂分别制备。
防热层11、隔热层包覆蒙皮13及防热层加强筋14采用的立体织物,具有一定的变形能力,在铺覆过程中,在负曲率部位避免出现褶皱,进而减少局部***或局部孔洞等缺陷,提高热防护层1的性能。
实施例3
参见图1和图2所示,本发明实施例提供一种适用于负曲率外形的防隔热一体化热防护结构,本实施例与实施例1的区别在于:本热防护层1的防热层11设有多层,防热层11的具体层数根据具体设计要求进行增减。多层防热层11叠合成设定厚度,多层防热层11通过缝合线15与隔热层12缝合成一体。将多层防热层11与实施例1中已经缝合成一体的热防护层1再次缝合成一体,防止层与层之间出现界面分离。
优选的,缝合线15采用抗高温性能的石英纤维材料。石英纤维材料具有耐热、耐腐蚀和柔软性。在高温下强度保持率高、尺寸稳定、抗热震性、化学稳定性、透光性及电绝缘性好。石英纤维材料耐高温性能比高硅氧纤维高,长期使用温度可达到1200℃,软化点温度高达1700℃,同时具有高的电绝缘性能,耐烧蚀,抗热震,优良的介电性能和良好的化学稳定性等。
本热防护层1采用缝合线15将热防护层1的隔热层包覆蒙皮13、防热层加强筋14、隔热层12及防热层11之间采用缝合线15缝合成一体化结构,在高温1200℃下依然能够保持强度保持率高、尺寸稳定的优异性能,不会出现变形和断裂的缺陷。保障了本热防护层1的隔热层包覆蒙皮13、防热层加强筋14、隔热层12及防热层11之间的整体性,防止层与层之间出现界面分离。
优选的,隔热层12选用为导热系数较低的材料,例如气凝胶复合材料。气凝胶复合材料是一种理想的透明隔热材料,具有非常好的隔热效果,是传统隔热材料2-5倍。采用气凝胶复合材料作为本隔热层12的隔热材料,能够有效的阻止飞行器在大气层内以高超声速飞行时产生的气动热进入飞行器内舱,为飞行器舱内设备提供良好工作环境。
本发明实施例的一种适用于负曲率外形的防隔热一体化热防护结构可以参照以下方法制备:
步骤101:热防护层1制作。首先在模具内铺设设定厚度的隔热层包覆蒙皮13,其次在隔热层包覆蒙皮13上铺设防热层加强筋14,防热层加强筋14在隔热层包覆蒙皮13上呈网格状排布。接下来在防热层加强筋14的网格内铺设隔热层12,然后在防热层加强筋14和隔热层12的顶部铺设防热层11,最后采用缝合线15将防热层11、隔热层12、隔热层包覆蒙皮13和防热层加强筋14缝合成一体化结构并在模具内固化成型。
步骤102:承力壳体3表面处理。首先在承力壳3的表面进行打磨和清理,确保承力壳体3的表面粗糙无杂物,然后在承力壳体3的表面涂覆增粘底涂剂并晾干。
步骤103:涂覆粘接层2。首先在承力壳体3的表面排布设定数量的杆状物,杆状物优选为钢丝;其次在在承力壳体3的表面均匀涂覆粘接层2,确保粘接层2能填充满热防护层1与承力壳体3之间的间隙;接下来将固化成型的热防护层1套装在承力壳体3的表面,待粘接层2处于半固化状态时将粘接层2内的杆状物抽出形成排气孔,最后待粘接层2处于完全固化后,该一体化热防护结构制备完成。
本领域的技术人员可以对本发明实施例进行各种修改和变型,倘若这些修改和变型在本发明权利要求及其等同技术的范围之内,则这些修改和变型也在本发明的保护范围之内。
说明书中未详细描述的内容为本领域技术人员公知的现有技术。
Claims (6)
1.一种适用于负曲率外形的防隔热一体化热防护结构,其特征在于,包括:
承力壳体(3);
热防护层(1),所述热防护层(1)包括隔热层(12)和防热层(11),所述防热层(11)内壁设置有网格状的防热层加强筋(14),所述隔热层(12)设置在防热层加强筋(14)的网格内,隔热层(12)表面设有隔热层包覆蒙皮(13);所述隔热层包覆蒙皮(13)、防热层加强筋(14)、防热层(11)在预浸料状态下即与隔热层(12)通过缝合线(15)缝合成一体;
粘接层(2),所述粘接层(2)位于承力壳体(3)和热防护层(1)之间,所述粘接层(2)将热防护层(1)粘接在承力壳体(3)上。
2.如权利要求1所述的一种适用于负曲率外形的防隔热一体化热防护结构,其特征在于:
所述防热层(11)、隔热层包覆蒙皮(13)及防热层加强筋(14)均是由多层预浸料层叠并高温固化而成,所述预浸料是由一定厚度的立体石英织物浸渍酚醛树脂制成。
3.如权利要求1所述的一种适用于负曲率外形的防隔热一体化热防护结构,其特征在于:
所述隔热层(12)为气凝胶复合材料。
4.如权利要求1所述的一种适用于负曲率外形的防隔热一体化热防护结构,其特征在于:
所述粘接层(2)为具有耐高温和热匹配性能的粘接剂,所述粘接层(2)内设有多个通孔。
5.如权利要求4所述的一种适用于负曲率外形的防隔热一体化热防护结构,其特征在于:
所述通孔的轴线与所述粘接层(2)的厚度方向垂直。
6.如权利要求1所述的一种适用于负曲率外形的防隔热一体化热防护结构,其特征在于:
所述缝合线(15)为石英纤维材料。
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