CN111136935B - 一种烧蚀防热结构一体化整体成型用应变协调层及其制备方法和应用 - Google Patents
一种烧蚀防热结构一体化整体成型用应变协调层及其制备方法和应用 Download PDFInfo
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Abstract
本发明涉及一种应变协调层,其由胶片和载体复合而成,胶片由耐高温酚醛改性环氧树脂体系制得;载体为玻璃纤维织物、石英纤维织物、涤纶纤维织物等。本发明还涉及制备所述应变协调层的方法、采用所述应变协调层制备舱体的方法以及由该方法制得的舱体。本发明能够实现金属舱体和外防热层一体成型、固化,工艺流程简单,生产周期短,特别适合于批量生产。本发明的应变协调层能够很好地实现与防热层/金属舱体之间的热变形及应力相匹配,实现高剪切强度和剥离强度要求,避免了舱体较大的变形和防热层开裂脱粘风险,具有高的抗冲击性能和减震抗震的特性,能够在多种复杂工况下在高速飞行器的金属结构表层材料的大面积烧蚀防热应用。
Description
技术领域
本发明涉及一种耐烧蚀防热层结构整体成型用抗脱粘用界面协调层及其舱体的制备方法,属于功能复合材料技术领域。
背景技术
热防护材料一般称为烧蚀材料或烧蚀防热材料,烧蚀防热材料方面的应用是复合材料在高科技领域的主要用途之一。目前复合结构舱段防热层主要采用分体成型方案:防热层在缠绕芯模上缠绕固化成型、然后机械加工保证外形尺寸;脱模后,再与金属舱体胶接套装。防热层分体成型,工艺流程相对复杂,生产周期长,且防热层成型需要模具、工装,生产成本相对较高。同时,随着导弹弹头、宇宙飞船、航天飞机等再入飞行器发展,其外形越来越复杂,给外防热材料成型带来了很大的技术难度,采用传统的缠绕+套装粘接工艺很难实现,因此,近年发展的防热层与金属舱体一体化成型技术得到了发展。由于防热层与金属舱体弹性模量和线膨胀系数不同,在固化过程中产生热应力,同时,固化过程中树脂的化学收缩,使它们之间可能产生较大的热变形,导致防热层与金属舱体一体化成型易发生脱粘或分层现象。
专利CN108034371A提出一种耐高温胶膜及其制备方法:耐高温热固性树脂与增韧剂混合,添加微纳米短切纤维及热稳定齐聚物在溶液中混合均匀,然后采用溶液法制成一定厚度的胶膜。用以实现高温结构复合材料与金属部件的界面匹配粘接问题,提出原位发泡层及微纳米纤维实现微连接,提高复合材料与金属部件的粘接强度。专利CN109021847A提出一种与环氧基碳纤维复合材料共固化弹性胶膜材料及其制备方法。该种胶膜材料由功能性弹性层和工艺层制备而成,弹性层具有良好的粘接性,利于胶膜的铺贴;而工艺层表面为粘性且表面光滑,解决了裙体与壳体之间的套装问题。该胶膜用以解决复合材料裙与复合材料壳体大面积粘接时局部脱粘问题。目前公布的专利均未提及烧蚀防热层与金属舱体一体成型用界面协调层或胶膜的技术方案。工程技术中常采用J47环氧胶膜或9621改性丁腈胶片作为应变协调层,经工程型号验证这两种材料作为界面协调层均存在不同程度防热层与金属舱体发生脱粘的问题,不能满足胶膜在防热结构中的需求。
因此,亟需一种能适用于树脂基烧蚀防热材料与金属结构的界面协调层,来解决烧蚀防热材料固化过程中防热层与金属舱体脱粘问题。
发明内容
本发明的目的在于防热结构中通过引入应变协调层,该协调层位于防热层和金属舱体之间,在成型过程中,将胶片铺覆在两者界面,在充分考虑产品结构刚度、纤维铺层等影响条件下,可获得无脱粘防热结构,能够满足长时间烧蚀隔热的高可靠性要求,可广泛应用于烧蚀防热的航空航天领域用复合材料及其制备方法。
为实现上述目的,本发明在第一方面提供了一种应变协调层,所述应变协调层由胶片和载体复合而成,所述胶片由耐高温酚醛改性环氧树脂体系制得;所述载体选自由玻璃纤维织物、石英纤维织物、涤纶纤维织物、芳纶纤维织物、尼龙纱网、聚酯纱网和无纺布组成的组。
本发明在第二方面提供了一种制备第一方面所述的应变协调层的方法,所述方法包括如下步骤:
(1)将用于制备耐高温酚醛改性环氧树脂体系的组分在800-5000r/min的速率的搅拌条件下,于80-150℃的温度恒温搅拌1-5小时,得到主体树脂;
(2)将所述主体树脂在20-80℃的温度下混合均匀,得到胶料;
(3)将所述胶料在20-120℃的温度下,采用双辊热压延方式与载体复合,得到应变协调层。
本发明在第三方面提供了一种舱体耐烧蚀防热结构一体化整体成型方法,所述舱体包括金属舱体、应变协调层和烧蚀防热层,所述方法包括如下步骤:
(1)对所述金属舱体的表面进行预处理;
(2)在经预处理的金属舱体的表面设置应变协调层;
(3)在所述应变协调层上设置烧蚀防热层;
(4)对步骤(3)得到的舱体进行固化处理,得到一体化整体成型的舱体。
本发明在第四方面体用了由本发明第三方面所述的方法制得的舱体。
本发明至少具有如下优点:
(1)本发明方法能够实现金属舱体和外防热层一体成型、固化,工艺流程简单,生产周期短,特别适合于批量生产。
(2)本发明人研发出了一种具有应变协调层的防热层结构,该应变协调层能够很好地实现与防热层/金属舱体之间的热变形及应力相匹配,实现高剪切强度和剥离强度要求,避免了舱体较大的变形和防热层开裂脱粘风险;
(3)本发明人研发出了一种具有应变协调层的防热层结构,提高舱体的抗冲击性能,具有减震抗震的特性,能够在多种复杂工况下实现应用。
本发明的应变协调层可以用于金属舱体的一体化整体成型的抗脱粘,所述成型方法适用于高速飞行器的控制舱、载荷舱、仪器舱、战斗部舱等金属结构表层材料的大面积烧蚀防热。
附图说明
图1为本发明方法的一个具体实施方式的制备工艺流程图。
图2为根据本发明方法制得的舱体耐烧蚀防热结构一体化整体成型结构的截面示意图;其中1为烧蚀防热层,2为应变协调层,3为金属舱体。
具体实施方式
为了对本发明的技术特征、目的和有益效果有更加清楚的理解,现结合以下具体实施方式对本发明的技术方案进行更加详细地说明,但这些具体实施方式不应被理解为对本发明的可实施范围的限定。
本发明在第一方面提供了一种应变协调层,所述应变协调层由胶片和载体复合而成,所述胶片由耐高温酚醛改性环氧树脂体系制得;所述载体选自由玻璃纤维织物、石英纤维织物、涤纶纤维织物、芳纶纤维织物、尼龙纱网、聚酯纱网和无纺布组成的组。
在一些优选的实施方式中,所述耐高温酚醛改性环氧树脂体系由40份至120份酚醛树脂(例如50、60、70、80、90、100或110份)、10份-50份(例如20、30或40份)的耐高温环氧树脂和2份-15份(例如5或10份)增韧树脂组成。更优选的是,所述应变协调层具有0.2mm~3.0mm(例如0.5、1.0或2.0mm)的厚度。更优选的是,所述酚醛树脂选自由钡酚醛树脂、镁酚醛树脂和氨酚醛树脂组成的组;所述耐高温环氧树脂选自由双酚A型环氧树脂、脂环族环氧树脂、脂肪族环氧树脂和酚醛环氧树脂组成的组;所述增韧树脂选自由固体丁腈橡胶、固体端环氧基丁腈橡胶、聚氨酯弹性体和固体端羧基丁腈橡胶组成的组。
本发明在第二方面提供了一种制备第一方面所述的应变协调层的方法,所述方法包括如下步骤:
(1)将用于制备耐高温酚醛改性环氧树脂体系的组分在800-5000r/min(例如1000、2000、3000或4000r/min)的速率的搅拌条件下,于80-150℃(例如100或120℃)的温度恒温搅拌1-5小时(例如2、3或4小时),得到主体树脂;
(2)将所述主体树脂在20-80℃(例如30、40、50、60或70℃)的温度下混合均匀,得到胶料;
(3)将所述胶料在20-120℃(例如30、40、50、60、80或100℃)的温度下,采用双辊热压延方式与载体复合,得到应变协调层。
在步骤(1)中,可以按配方将耐烧蚀树脂体系各组分均匀混合,然后与增强织物采用热熔法或溶剂法制备预浸料,分切制备作为应变协调层的预浸布带。
本发明在第三方面提供了一种舱体耐烧蚀防热结构一体化整体成型方法,所述舱体包括金属舱体、应变协调层和烧蚀防热层,所述方法包括如下步骤:
(1)对所述金属舱体的表面进行预处理;
(2)在经预处理的金属舱体的表面设置应变协调层;
(3)在所述应变协调层上设置烧蚀防热层;
(4)对步骤(3)得到的舱体进行固化处理,得到一体化整体成型的舱体。
图1为本发明第二方面所述的方法的一个具体实施方式的制备工艺流程图。图2为根据本发明方法制得的舱体耐烧蚀防热结构一体化整体成型结构的截面示意图;其中1为烧蚀防热层,2为应变协调层,3为金属舱体。
在一些优选的实施方式中,所述应变协调层如本发明第一方面所述或者由第二方面所述的方法制得。
在一些优选的实施方式中,所述方法还包括在粗糙化处理之后在设置应变协调层之前进行表面清洗的步骤。
在一些优选的实施方式中,所述方法还包括在固化处理后进行一体加工的步骤。更优选的是,所述一体加工通过使用数控设备按照图纸要求对烧蚀防热层的外形、开孔和两端部部位进行加工。
优选的是,在步骤(1)中,所述预处理通过打磨或喷砂的方式进行,以除去金属表面的氧化层并提高粗糙度,优先粗糙度提高至3.2Ra至12.8Ra(例如4、6、8或10Ra)。
优选的是,在步骤(2)中,所述应变协调层通过粘接的方式粘接在所述金属舱体的外表面上。在粘接时,可以在金属壳体的表面沿一个方向依次粘贴应变协调层,应变协调层的长度方向可以与金属壳体的高度一致,拼接时拼接缝隙优选小于1mm。在一个优选的实施方式中,所述应变协调层为酚醛改性环氧树脂,所述应变协调层的厚度为0.1mm-0.8mm(例如0.2、0.3、0.4、0.5、0.6或0.7mm)。
优选的是,在步骤(3)中,所述设置可以通过缠绕或者铺放实现。优选的是,根据所述金属舱体的形状通过平行缠绕、重叠缠绕、斜叠缠绕和/或铺放工艺在所述金属舱体上成型所述烧蚀放热层。在采用缠绕方式的情况下,可以根据舱体的结构形式采用适合的缠绕工艺,其中平行缠绕适用于圆柱形制品,锥形和特型曲面制品主要采用重叠缠绕、斜叠缠绕或铺放工艺。
另外优选的是,所述烧蚀防热层通过缠绕的方式缠绕在设置有应变协调层的金属舱体的表面,厚度为5mm-25mm(例如10或15mm)。
在一个优选的实施方式中,在步骤3)中,所述烧蚀防热层为高硅氧玻璃纤维预浸带,所述预浸带的宽度为25mm-200mm(例如50、100或150mm)。
优选的是,在步骤(4)中,所述固化处理为在真空状态下施加压力和升温进行固化;优选的是,所述固化处理通过如下方式进行:在成型后的烧蚀防热层的外表面依次铺覆隔离膜、吸胶毡、真空袋密封处理,抽真空,通过加热加压固化,使烧蚀防热层中的树脂与纤维复合成一体,真空度-0.085MPa以下,固化温度为120-180℃(例如140或160℃),固化时间为3-8h(例如5小时),固化压力0.8-10MPa(例如1.0、2.0、5.0或8.0MPa)。
在一些优选的实施方式中,所述金属舱体具有圆形回转体结构和/或负曲率异型结构等。更优选的是,所述金属舱体的材料为铝合金、钛合金或其他金属合金材料。进一步优选的是,所述舱体选自由控制舱、载荷舱、仪器舱和战斗部舱组成的组。
在一些优选的实施方式中,所述烧蚀防热层由耐烧蚀纤维织物和耐烧蚀树脂复合而成。
优选的是,所述耐烧蚀纤维织物为单编纤维织物或混编纤维织物,优选选自由平纹布、缎纹布、斜纹布和经编衬纬布组成的组。更优选由选自由碳纤维、玻璃纤维(例如高强玻璃纤维、无碱玻璃纤维)、高硅氧纤维、石英纤维、石英玻璃纤维、、聚丙烯腈基碳纤维、胶黏剂碳纤维、酚醛纤维和涤纶纤维组成的组的一种或多种纤维编织而成。所述耐烧蚀树脂为选自由酚醛树脂、改性酚醛树脂、苯并噁嗪树脂、聚芳基乙炔树脂和聚硅氮烷树脂组成的组中的一种。
优选的是,所述烧蚀防热层利用耐烧蚀树脂和耐烧蚀纤维织物通过溶液法或胶膜法制备烧蚀防热层预浸料,再利用所述烧蚀防热层预浸料制备预浸布带作为所述烧蚀防热层。优选的是,所述烧蚀防热层预浸料采用耐烧蚀树脂利用浸胶机浸渍或复合耐烧蚀织物来制得。
在采用溶液法的情况下,可以将耐烧蚀树脂加热成液体,用溶剂稀释至预定浓度,采用浸胶机直接浸润增强纤维织物,制备耐烧蚀树脂/耐烧蚀纤维织物(原为酚醛/防热纤维织物)预浸料,预浸料中耐烧蚀树脂含量30-60质量%(例如40或50质量%),挥发份2-10质量%(例如为5或8质量%)。
另外优选的是,所述烧蚀防热层具有25mm-200mm(例如50、100或150mm)的宽度。
本发明的舱体耐烧蚀防热结构一体化整体成型方法适用于高速飞行器的控制舱、载荷舱、仪器舱、战斗部舱等金属结构表层材料的大面积防热。
本发明在第四方面体用了由本发明第三方面所述的方法制得的舱体。所述舱体可以作为于高速飞行器的控制舱、载荷舱、仪器舱、战斗部舱等舱体使用。
以下将结合附图和具体实例对本发明进行更加详细的说明。
实施例1
在本实施例中,舱体结构由金属舱体、应变协调层、烧蚀防热层组成。所述金属舱体材料为2A12铝合金,采用旋压工艺成型。应变协调层为耐高温酚醛改性环氧树脂体系(80份钡酚醛树脂,30份双酚A型环氧树脂和8份固体丁腈橡胶),厚度为0.8mm。烧蚀防热层中耐烧蚀纤维织物为高硅氧纤维平纹布,耐烧蚀树脂为钡酚醛树脂,采用溶液法制成预浸布带,布带宽度为80mm,采用斜叠缠绕铺层方式,厚度为8mm。
应变协调层采用如下方式制备:将用于制备耐高温酚醛改性环氧树脂体系的组分在800-5000r/min的速率的搅拌条件下,于120℃的温度恒温搅拌3小时,得到主体树脂;将所述主体树脂在50℃的温度下混合均匀,得到胶料;将所述胶料在70℃的温度下,采用双辊热压延方式与载体复合,得到应变协调层。
舱体制作步骤如下:
(1)按耐烧蚀树脂体与增强织物采用溶液法或胶膜法制备防热层预浸料,分切制备预浸布带备用,预浸布带宽度为80mm;
(2)金属舱体表面喷砂粗糙度处理,并清洗金属舱体表面;
(3)粘贴应变协调层:在金属壳体表面沿一个方向依次粘贴应变协调层,应变协调层的长度方向与金属壳体的高度一致,拼接时拼接缝隙小于1mm。
(4)在粘贴有应变协调层的金属舱体表面缠绕防热层,厚度为8mm。
(5)真空加压固化:缠绕成型后的防热层外表面依次铺覆隔离膜、吸胶毡、真空袋密封处理,抽真空,通过加热加压固化,使树脂与增强纤维复合成一体,真空度-0.085MPa以下,固化温度控制为120-180℃,固化时间5h,固化压力8.0MPa;
(6)机械加工:使用数控设备对防热层外形、开孔和两端部等部位进行加工,从而满足图纸要求。
然后,测试金属舱体和烧蚀防热层之间的剪切强度(GB/T7124-2008,胶粘剂拉伸剪切强度的测定(刚性材料对刚性材料))和剥离强度(GB/T15254-1994,硫化橡胶与金属粘接180度剥离试验),结果如下表1所示。
实施例2
采用与实施例1基本相同的方式进行,不同之处在于,用于制备所述耐高温酚醛改性环氧树脂体系的原料由40份钡酚醛树脂,50份双酚A型环氧树脂和15份固体丁腈橡胶组成。
实施例3
采用与实施例1基本相同的方式进行,不同之处在于,用于制备所述耐高温酚醛改性环氧树脂体系的原料由120份钡酚醛树脂,10份双酚A型环氧树脂和15份固体丁腈橡胶组成。
实施例4
采用与实施例1基本相同的方式进行,不同之处在于,用于制备所述耐高温酚醛改性环氧树脂体系的原料由120份钡酚醛树脂,50份双酚A型环氧树脂和2份固体丁腈橡胶组成。
实施例5
采用与实施例1基本相同的方式进行,不同之处在于,采用同样厚度的9621改性丁腈胶片(购自北京橡胶工业研究设计院)作为应标协调层。
实施例6
舱体结构由金属舱体、应变协调层、烧蚀防热层组成;所述金属舱体材料为2A12铝合金,采用旋压工艺成型;应变协调层为耐高温酚醛改性环氧树脂体系(80份镁酚醛树脂,30份脂环族环氧树脂和8份聚氨酯弹性体),厚度为0.8mm;烧蚀防热层为复合型耐烧蚀防热复合材料:内侧隔热层增强纤维为无碱无捻玻璃纤维网格布,耐烧蚀树脂为钡酚醛树脂,低导热填料为空心玻璃微珠,采用胶膜法制成预浸布带,浸布带宽度为20mm,采用平行缠绕铺层方式,厚度为3mm。外侧防热层组增强纤维为高硅氧纤维平纹布,耐烧蚀树脂为钡酚醛树脂,采用溶液法制成预浸布带,布带宽度为50mm,采用斜叠缠绕铺层方式,厚度为6mm。
应变协调层制作方法同实施例1。舱体制作方法具体步骤如下:
(1)按配方将耐烧蚀树脂体系各组分均匀混合,与增强织物采用溶液法或胶膜法制备防热层预浸料,分切制备预浸布带备用,预浸布带宽度为80mm;
(2)金属舱体表面喷砂粗糙度处理,并清洗金属舱体表面;
(3)粘贴应变协调层:在金属壳体表面沿一个方向依次粘贴应变协调层,应变协调层的长度方向与金属壳体的高度一致,拼接时拼接缝隙小于1mm。
(4)在粘贴有应变协调层的金属舱体表面缠绕内侧隔热层,内侧隔热层厚度为3mm;
(5)在步骤(4)处理后的舱体表面缠绕外侧防热层,外防热层的厚度为6mm。
(6)真空加压固化:缠绕成型后的防热层外表面依次铺覆隔离膜、吸胶毡、真空袋密封处理,抽真空,通过加热加压固化,使树脂与增强纤维复合成一体,真空度-0.085MPa以下,固化温度120-180℃,固化时间3-8h,固化压力0.8-10MPa;
(7)机械加工:使用数控设备对防热层外形、开孔和两端部等部位进行加工,以满足图纸要求。
实施例7
采用与实施例6基本相同的方式进行,不同之处在于,应变协调层为耐高温酚醛改性环氧树脂体系(80份氨酚醛树,15份脂肪族环氧树脂、15份酚醛环氧树脂和8份固体端羧基丁腈橡胶)。
实施例8
采用与实施例7基本相同的方式进行,不同之处在于,采用同样厚度的J47环氧胶膜(购自黑龙江省科学院石油化学研究院)作为应变协调层。
表1.各个实施例制得的舱体的性能
最后应说明的是:以上实施例仅用以说明本发明的技术方案,而非对其限制;尽管参照前述实施例对本发明进行了详细的说明,本领域的普通技术人员应当理解:其依然可以对前述各实施例所记载的技术方案进行修改,或者对其中部分技术特征进行等同替换;而这些修改或者替换,并不使相应技术方案的本质脱离本发明各实施例技术方案的精神和范围。
Claims (9)
1.一种烧蚀防热结构一体化整体成型用应变协调层,其特征在于,所述应变协调层由胶片和载体复合而成,所述胶片由耐高温酚醛改性环氧树脂体系制得;所述载体选自由玻璃纤维织物、石英纤维织物、涤纶纤维织物、芳纶纤维织物、尼龙纱网、聚酯纱网和无纺布组成的组;
所述耐高温酚醛改性环氧树脂体系由40份至120份酚醛树脂、10份-50份的耐高温环氧树脂和2份-15份增韧树脂组成;其中,所述酚醛树脂选自由钡酚醛树脂、镁酚醛树脂和氨酚醛树脂组成的组;所述耐高温环氧树脂选自由双酚A型环氧树脂、脂环族环氧树脂、脂肪族环氧树脂和酚醛环氧树脂组成的组;所述增韧树脂选自由固体丁腈橡胶、固体端环氧基丁腈橡胶、聚氨酯弹性体和固体端羧基丁腈橡胶组成的组;
所述应变协调层通过粘接的方式粘接在金属舱体的外表面上;
所述应变协调层具有0.2 mm~3.0mm的厚度。
2.一种制备权利要求1所述的应变协调层的方法,其特征在于,所述方法包括如下步骤:
(1)将用于制备耐高温酚醛改性环氧树脂体系的组分在800-5000r/min的速率的搅拌条件下,于80-150℃的温度恒温搅拌1-5小时,得到主体树脂;
(2)将所述主体树脂在20-80℃的温度下混合均匀,得到胶料;
(3)将所述胶料在20-120℃的温度下,采用双辊热压延方式与载体复合,得到应变协调层。
3.一种舱体耐烧蚀防热结构一体化整体成型方法,其特征在于,所述舱体包括金属舱体、应变协调层和烧蚀防热层,所述方法包括如下步骤:
(1)对所述金属舱体的表面进行预处理;
(2)在经预处理的金属舱体的表面设置应变协调层;
(3)在所述应变协调层上设置烧蚀防热层;
(4)对步骤(3)得到的舱体进行固化处理,得到一体化整体成型的舱体;
其中,所述应变协调层由胶片和载体复合而成,所述胶片由耐高温酚醛改性环氧树脂体系制得;所述载体选自由玻璃纤维织物、石英纤维织物、涤纶纤维织物、芳纶纤维织物、尼龙纱网、聚酯纱网和无纺布组成的组;
所述耐高温酚醛改性环氧树脂体系由40份至120份酚醛树脂、10份-50份的耐高温环氧树脂和2份-15份增韧树脂组成;其中,所述酚醛树脂选自由钡酚醛树脂、镁酚醛树脂和氨酚醛树脂组成的组;所述耐高温环氧树脂选自由双酚A型环氧树脂、脂环族环氧树脂、脂肪族环氧树脂和酚醛环氧树脂组成的组;所述增韧树脂选自由固体丁腈橡胶、固体端环氧基丁腈橡胶、聚氨酯弹性体和固体端羧基丁腈橡胶组成的组。
4.根据权利要求3所述的方法,其特征在于:
所述方法还包括在粗糙化处理之后在设置应变协调层之前进行表面清洗的步骤;和/或
所述方法还包括在固化处理后进行一体加工的步骤;其中,所述一体加工通过使用数控设备按照图纸要求对烧蚀防热层的外形、开孔和两端部部位进行加工。
5.根据权利要求3至4中任一项所述的方法,其特征在于:
在步骤(1)中,所述预处理通过打磨或者喷砂进行,使得所述表面粗糙化处理获得3.2Ra-12.8 Ra粗糙度的表面;
在步骤(2)中,所述应变协调层通过粘接的方式粘接在所述金属舱体的外表面上;
在步骤(3)中,根据所述金属舱体的形状通过平行缠绕、重叠缠绕、斜叠缠绕和/或铺放工艺在所述金属舱体上成型所述烧蚀防热层;
在步骤(4)中,所述固化处理为在真空状态下施加压力和升温进行固化;其中所述固化处理通过如下方式进行:在成型后的烧蚀防热层的外表面依次铺覆隔离膜、吸胶毡、真空袋密封处理,抽真空,通过加热加压固化,使烧蚀防热层中的树脂与纤维复合成一体,真空度-0.085MPa以下,固化温度为120-180℃,固化时间为3-8h,固化压力0.8-10MPa。
6.根据权利要求3至4中任一项所述的方法,其特征在于:
所述烧蚀防热层通过缠绕的方式缠绕在粘接有应变协调层的金属舱体的表面,厚度为5mm-25mm。
7.根据权利要求3至4中任一项所述的方法,其特征在于:
所述金属舱体具有圆形回转体结构和/或负曲率异型结构;
所述金属舱体的材料为铝合金和/或钛合金;和/或
所述舱体选自由控制舱、载荷舱、仪器舱和战斗部舱组成的组。
8.根据权利要求3至4中任一项所述的方法,其特征在于:
所述烧蚀防热层由耐烧蚀纤维织物和耐烧蚀树脂复合得到的复合材料;所述耐烧蚀纤维织物为单编纤维织物或混编纤维织物,选自由平纹布、缎纹布、斜纹布和经编衬纬布组成的组,由选自由高硅氧纤维和石英纤维组成的组的一种或多种纤维编织而成;所述耐烧蚀树脂为选自由酚醛树脂、改性酚醛树脂、苯并噁嗪树脂、聚芳基乙炔树脂和聚硅氮烷树脂组成的组中的一种;
所述烧蚀防热层利用耐烧蚀树脂和耐烧蚀纤维织物通过溶液法或胶膜法制备烧蚀防热层预浸料,再利用所述烧蚀防热层预浸料制备预浸布带作为所述烧蚀防热层;所述烧蚀防热层预浸料采用耐烧蚀树脂或复合耐烧蚀织物利用浸胶机浸渍来制得;
所述烧蚀防热层具有25mm-200mm的宽度。
9.由权利要求3至8中任一项所述的方法制得的舱体。
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